УСТРОЙСТВО ДЛЯ ПОВОРОТА РОТОРА ТУРБОМАШИНЫ ИЗ ПЕРВОГО ПОЛОЖЕНИЯ ВО ВТОРОЕ ПОЛОЖЕНИЕ

Изобретение относится к машиностроению и может быть использовано для установки ротора турбомашины, в частности для поворота ротора из горизонтального положения в вертикальное. Ротор имеет несколько роторных дисков, которые стянуты друг с другом по меньшей мере одним стяжным болтом. Устройство содержит два расположенных параллельно друг другу боковых элемента, соединенных друг с другом мостовым элементом, и разъемное поворотное кольцо для помещения с геометрическим замыканием осевого участка устанавливаемого ротора. На поворотном кольце соосно расположены цапфы, опертые в боковых элементах с возможностью вращения и предназначенные для поворота поворотного кольца вокруг оси поворота, параллельной горизонтальной плоскости. В мостовом элементе размещен с возможностью опирания и передвигаемый перпендикулярно горизонтальной плоскости диск для фланцевого винтового соединения с вертикально установленным ротором. Обеспечивается надежная установка ротора в вертикальное положение и фиксация от опрокидывания ...

ГАЗОТУРБИННЫЙ ДВИГАТЕЛЬ, СПОСОБ ЕГО ЧАСТИЧНОЙ РАЗБОРКИ И СПОСОБ ПОДДЕРЖИВАНИЯ ЕГО ПЕРВОГО РОТОРА

Изобретение относится к газотурбинному двигателю и, в частности, к его несущей (опорной) конструкции. Газотурбинный двигатель сконфигурирован имеющим пропульсивную секцию, снабженную приводом вентилятора на основе узла зубчатой передачи, а также содержит газогенераторную секцию, которая содержит секцию компрессора, снабженную первым ротором, установленным, с возможностью вращения, на первом валу. Двигатель содержит также подшипниковый блок, поддерживающий, с возможностью вращения, первый вал. При этом подшипниковый блок поддерживает первый вал в период, предшествующий установке в двигатель узла зубчатой передачи, входящей в привод вентилятора, и/или в период, когда указанный узел зубчатой передачи извлечен из двигателя. Также представлены способ частичной разборки газотурбинного двигателя и способ поддерживания его первого ротора. Изобретение позволяет облегчить быстрое обслуживание газотурбинного двигателя. 3 н. и 17 з.п. ф-лы, 8 ил.

ТРУБНЫЙ СОЕДИНИТЕЛЬ И ТРУБНЫЙ СОЕДИНИТЕЛЬНЫЙ УЗЕЛ

Изобретение относится к трубному соединителю для соединения первого элемента со вторым элементом. Трубный соединитель содержит отрезок (11) трубы, первый фланец (12), расположенный у первого конца отрезка (11) трубы и выполненный с возможностью соединения с указанным первым элементом, и второй фланец (13), расположенный у второго конца отрезка (11) трубы и выполненный с возможностью соединения с указанным вторым элементом. Указанный первый фланец (12) содержит окружной анкерный фланец (18), который неподвижно соединен с отрезком (11) трубы у указанного первого конца, фланцевую вставку (19), которая выполнена с возможностью смещения в осевом направлении трубного соединителя (1) относительно анкерного фланца (18) между втянутым положением и выдвинутым положением, и средство для смещения фланцевой вставки (19) относительно анкерного фланца (18), в проходящем аксиально направлении от второго конца к первому концу отрезка (11) трубы, причем фланцевая вставка (19) в выдвинутом положении выступает ...

КОРОБКА ПЕРЕДАЧ И СПОСОБ РАЗБОРКИ ДЛЯ РАСЦЕПЛЕНИЯ ПРИВОДНОГО ВАЛА В ТАКОЙ КОРОБКЕ ПЕРЕДАЧ

Изобретение относится к коробке передач для турбовентиляторных реактивных двигателей. Коробка передач имеет основное устройство и вспомогательное устройство, содержащие соответствующие корпусы зубчатых передач и соответствующие полые валы, соединенные с помощью приводного вала. Вспомогательное устройство передает движение между двумя осями, образующими угол меньше чем 180°, и которое может быть удалено после отсоединения приводного вала. Приводной вал зацеплен способом угловой фиксации и осевого скольжения полыми валами и заблокирован в осевом направлении в одном направлении при помощи осевого удерживающего средства, которое является съемным. Осевое удерживающее средство сцеплено с одним из полых валов на осевом конце, который обращен к другому из полых валов. Одно отверстие может быть образовано между двумя корпусами для обеспечения доступа к такому осевому концу и отсоединения осевого удерживающего средства. Достигается упрощение технического обслуживания. 2 н. и 13 з.п. ф-лы, 7 ил.

ТУРБИНА

Турбина реактивного двигателя содержит корпус турбины, лопатки турбины, кожух. Корпус турбины имеет цилиндрическую форму. Лопатки турбины выполнены с возможностью вращения вокруг оси корпуса турбины. Кожух включает в себя множество сегментов кожуха, расположенных кольцеобразно вдоль внутренней периферийной поверхности корпуса турбины и окружающих лопатки турбины. Каждый из сегментов кожуха выполнен с первой зацепляющей частью, и второй зацепляющей частью. Сегмент кожуха прикреплен к корпусу турбины посредством зацепления первой зацепляющей части с корпусом турбины в осевом направлении корпуса турбины и зацепления второй зацепляющей части с корпусом турбины в радиальном направлении корпуса турбины. На сегменте кожуха выполнена ступенчатая часть для восприятия радиального в направлении от периферии к центру усилия от инструмента для устранения состояния зацепления второй зацепляющей части с корпусом турбины на этапе отделения сегмента кожуха от корпуса турбины. Обеспечивается возможность ...

СИСТЕМА НАПРАВЛЯЮЩИХ СРЕДСТВ ДЛЯ ГОНДОЛЫ ТУРБОРЕАКТИВНОГО ДВИГАТЕЛЯ

... 1. Гондола (1) турбореактивного двигателя, содержащая !воздухозаборную секцию (4), предназначенную для направления воздушного потока к вентилятору турбореактивного двигателя и содержащую по меньшей мере одну продольную наружную панель (40), объединенную с входной кромкой (4а), ! среднюю секцию (5), расположенную вокруг указанного вентилятора, причем к средней секции прикреплена воздухозаборная секция (4) таким образом, что обеспечена аэродинамическая целостность, ! по меньшей мере одну внутреннюю панель (41), содержащую звукопоглощающую обечайку (53) и прикрепленную своим нижним по потоку концом (70) к верхнему по потоку концу (72) средней секции (5), причем в результате данного крепления образуется неподвижная конструкция гондолы (1), и ! направляющие средства (15), предназначенные для направления наружной панели (панелей) (40) и обеспечивающие, по существу, возможность прямолинейного перемещения наружной панели (40) к верхнему по потоку концу гондолы (1) с целью открытия воздухозаборной ...

СРЕДСТВО СТОПОРЕНИЯ СЕКТОРОВ КОЛЬЦА НА КОРПУСЕ ГАЗОТУРБИННОГО ДВИГАТЕЛЯ, СОДЕРЖАЩЕЕ ОСЕВЫЕ КАНАЛЫ ДЛЯ ЕГО ЗАХВАТА

... 1. Средство (24) стопорения устройства крепления секторов кольца на корпусе газотурбинного двигателя летательного аппарата, выполненное в окружном направлении (С) от первого окружного конца (24а) до второго окружного конца (24b), при этом в разрезе по плоскости, перпендикулярной к указанному окружному направлению, указанное средство содержит две зажимные ветви (28, 30), сопрягающиеся между собой на своем заднем конце через соединительную часть (32), проходящую по существу параллельно общему направлению промежутка между двумя зажимными ветвями, при этом передние концы двух зажимных ветвей выполнены с возможностью прижатия между ними по меньшей мере одного конца сектора к по меньшей мере одному элементу корпуса, отличающееся тем, что по обе стороны от воображаемой центральной плоскости (Р2), перпендикулярной к указанному окружному направлению, средство содержит канал (42) для захвата этого средства, при этом каждый канал выполнен сквозным в указанной соединительной части (32) и выходит в ...

Фильтрованная камера для газовых турбин и способ технического обслуживания указанной камеры

СПОСОБ СНЯТИЯ КОРПУСА ПОДШИПНИКА С РОТОРА ГАЗОВОЙ ТУРБИНЫ, А ТАКЖЕ ТРУБЧАТОЕ ПРОДОЛЖЕНИЕ ВАЛА

... 1. Способ снятия корпуса (10) подшипника с ротора (12) предпочтительно стационарной газовой турбины (14), снабженной предпочтительно разъемным пополам корпусом, при закрытом корпусе, включающий этапы:- крепление продолжения (18) вала на соответствующем конце (20) ротора (12) иa) опирание ротора (12) и/илиb) удерживание ротора (12)для освобождения корпуса (10) подшипника от силы веса ротора (12),- размещение элементов (22) скольжения между корпусом (10) подшипника и ротором (12),- осевое движение корпуса (10) подшипника вдоль оси (24) машины на продолжение (18) вала.2. Способ по п. 1,при котором корпус (10) подшипника по окружности выполнен неразъемным.3. Способ по п. 1 или 2,при котором корпус (10) подшипника с помощью защиты (26) от прокручивания защищен от вращения во время и после осевого перемещения.4. Способ по п. 3,при котором для защиты (26) от прокручивания на продолжении (18) вала предусмотрена по меньшей мере одна проходящая в осевом направлении направляющая (28), которая ограничивает ...

ГАЗОТУРБИННЫЙ ДВИГАТЕЛЬ, ВСТРОЕННЫЙ ВНУТРЬ КОРПУСА РЕДУКТОРА

ЗАПИРАЮЩАЯ СИСТЕМА ДЛЯ КОНСТРУКЦИИ ВОЗДУХОЗАБОРНИКА ГОНДОЛЫ ТУРБОРЕАКТИВНОГО ДВИГАТЕЛЯ

... 1. Гондола для турбореактивного двигателя, содержащая конструкцию (2) воздухозаборника, обеспечивающую нагнетание потока воздуха к вентилятору турбореактивного двигателя, и среднюю конструкцию, которая окружает этот вентилятор и к которой прикреплена указанная конструкция воздухосборника с обеспечением аэродинамической неразрывности, при этом конструкция воздухосборника содержит, с одной стороны, по меньшей мере одну внутреннюю панель (21), прикрепленную к средней конструкции и образующую вместе с ней неподвижную конструкцию гондолы, и, с другой стороны, по меньшей мере одну внешнюю продольную панель (20), включающую в себя переднюю кромку (2а) воздухозаборника и прикрепленную с возможностью перемещения к неподвижной конструкции, образуя таким образом подвижную конструкцию воздухозаборника, отличающаяся тем, что указанная подвижная конструкция воздухозаборника оснащена периферическими запирающими средствами, содержащими по меньшей мере одну электрическую задвижку (10), каждая из которых ...

КОРОБКА ПЕРЕДАЧ И СПОСОБ РАЗБОРКИ ДЛЯ РАСЦЕПЛЕНИЯ ПРИВОДНОГО ВАЛА В ТАКОЙ КОРОБКЕ ПЕРЕДАЧ

ГАЗОТУРБИННЫЙ ДВИГАТЕЛЬ И СПОСОБ РАЗБОРКИ ПЕРЕДНЕЙ ЧАСТИ КОНСТРУКЦИИ ГАЗОТУРБИННОГО ДВИГАТЕЛЯ

... 1. Газотурбинный двигатель, содержащий:опору центрального узла, образующую внутреннюю кольцевую стенку для осевого контура и содержащую первое монтажное средство;узел зубчатой передачи, связывающей вал и вентилятор, установленный с возможностью вращения вокруг оси, игибкую опору, связывающую узел зубчатой передачи с опорой центрального узла и содержащую второе монтажное средство, сопрягаемое с первым монтажным средством для передачи крутящего момента от одного монтажного средства к другому.2. Двигатель по п. 1, в котором опора центрального узла содержит пространственно разделенные направляющие лопатки, расположенные радиально между внутренней и наружной кольцевыми стенками и соединяющие их.3. Двигатель по п. 2, в котором первое монтажное средство содержит взаимно смещенные по окружности группы зубцов, разделенные участками, не имеющими зубцов.4. Двигатель по п. 3, в котором направляющие лопатки согласованы по положению в радиальном направлении с участками, не имеющими зубцов.5. Двигатель ...

Vorrichtung zum Ausbauen von Schaufeln einer Turbine oder eines Verdichters

A transducer mount and a transducer assembly incorporating such a mount

A transducer assembly 100 for connecting a transducer 102 to a device, the transducer assembly comprising: a transducer mount 110 adapted to receive the transducer; and a clamp 120 comprising first and second jaws 122, 124, the first and second jaws being adapted to selectively clamp to a flange portion 106 of the device. The transducer mount 110 may comprise a housing 112, a resilient member 114 and first and second end walls 115, 116. The first end wall may be operatively connected to the device. The transducer 102 may be held within the housing 112 and adjacent to the first end wall 115, the resilient member 114 being disposed between the transducer 102 and the second end wall 116.

Access to subassemblies of a turbomachine

A turbomachine has a casing 2 in which a rotor 4 is mounted and an annular supporting structure 3 provided in the casing on which subassemblies 5, such as combustion chambers and cooling systems are mounted. The annular supporting structure 3 is rotatably mounted in the casing 2 and can be locked in at least one position. When subassemblies 5 require checking or exchanging the annular supporting structure 3 may be rotated into inspection or assembly positions where they are accessible through closable assembly openings 6 in the casing 2. More than one closable assembly opening 6 may be present.

An assembly for a turbine engine

Gas turbine engine

Rotating device for a gas turbine and method for rotating a component

The invention relates to a rotating device (1) for an at least partially opened gas turbine (2), which is designed for being mounted on a parting line (11) of the housing (10) of the at least partially opened gas turbine (2) by way of at least one connecting portion (21), wherein the rotating device (1) has at least one first fastening portion (31), which is designed for mechanically interacting with a force transmission means (40), in particular at least one traction cable (40), in order to pass on mechanically a rotating movement of at least one component of the at least partially opened gas turbine (2), wherein it comprises at least one sleeve (50), which has at least one second fastening portion (51), wherein the sleeve (50) is designed for being connected non-positively to the gas turbine rotor (15).

TURBINE SHAFT SUPPORTING STRUCTURE

The invention concerns a turbine structure for the expansion of gas and vapour, comprising a body or casing with a peripheral work fluid transit volute from an entrance to an exit passage, at least a first stator and possible subsequent stators, a turbine shaft rotating around an axis and carrying at least a first rotor and possible subsequent rotors working together downstream of the first stator and subsequent rotors, respectively, an external tube member jutting out frontally from said body or casing and coaxial to the rotating turbine shaft, and where between the tube member (18) and the turbine shaft (15) is positioned a supporting unit (19) extractable en bloc from said external tube (18) except for the shaft.

GAS TURBINE MODULE, GAS TURBINE PLANT INCLUDING THE SAME, METHOD OF UNLOADING GAS TURBINE MODULE, AND METHOD OF EXCHANGING GAS TURBINE MODULE

ABSTRACT OF THE DISCLOSURE A gas turbine module includes a gas turbine that has a gas turbine rotor and a turbine shell; an inlet plenum that is connected to an inlet of the gas turbine; an exhaust plenum that is connected to an exhaust of the gas turbine; an enclosure that covers the gas turbine; and a common base on which the gas turbine, the inlet plenum, the exhaust plenum, and the enclosure are mounted. When moving the gas turbine, the gas turbine module is moved together. CA 3099538 2020-11-16 ...

SEGMENTED INTERNAL FUEL MANIFOLD

A fuel manifold assembly for supplying fuel to a combustor of a gas turbine engine comprises an engine case defining a plenum around the combustor. An annular fuel manifold is mounted inside the engine case in the plenum. The fuel manifold has a plurality of manifold ring segments removable from the engine case via an access port defined in the engine case. A method of maintaining the fuel manifold comprises disconnecting a first manifold ring segment from a fuel source; opening an access port in a side of the engine case; and physically disconnecting the first manifold ring segment from the engine case. Then, the first manifold ring segment can be removed from the engine case via the access port for maintenance or replacement purposes.

VANE ARRANGEMENT OF A TURBO MACHINE

The invention relates to a vane arrangement (1) of a turbo machine (4), in particular of a gas turbine, comprising at least one vane carrier (2) attached to a housing (5) of a turbo machine (4), and several vanes (3) attached to the vane carrier (2) and arranged in circumferential direction side by side, wherein the attachment between the vane carrier (2) and respective vane (3) is adapted for being axially pluggable. In order to simplify dismounting of a single vane (3) at least one of the vanes (3) is provided with an extraction device (35) comprising at least one axially extending extraction through-hole (36). The respective extraction through hole (36) is provided with an inner thread (37), and the vane carrier (2) is provided with an abutment zone (38) axially opposing the extraction through hole (36). The extraction device (35) is adapted for inducing axially oriented extraction forces into the respective vane (3) by means of an extraction tool, which is provided with an outer thread ...

FAN CASE FOR USE IN A TURBOFAN ENGINE, AND METHOD OF ASSEMBLING A TURBOFAN ENGINE

A fan case for use in a turbofan engine is provided. The fan case includes an aft portion having a substantially cylindrical cross-sectional shape, and a forward portion extending from the aft portion. A cross-sectional shape of the forward portion progressively decreases in radial size as the forward portion extends from the aft portion.

MEMBER FOR LOCKING RING SECTORS ON A TURBINE ENGINE CASING, INCLUDING R DIAL PASSAGES FOR GRIPPING SAME

La présente invention se rapporte à un organe de verrouillage (24) pour dispositif de fixation de secteurs d'anneau sur un carter de turbomachine d'aéronef, l'organe présentant deux branches de serrage (28, 30) raccordées entre elles à leur extrémité arrière par une branche de raccord (32) s' étendant sensiblement parallèlement à une direction générale d'espacement des deux branches de serrage. Selon l'invention, l'organe est pourvu, de part et d'autre d'un plan médian fictif (P2) orthogonal à ladite direction circonf érentielle, d'un passage (42) permettant la préhension de l'organe, chaque passage étant pratiqué dans la branche de raccord (32), en s' étendant selon une ligne directrice (44) sensiblement parallèle à la direction d'espacement.

BLADED DISK ASSEMBLY WITH RETAINING CLIP

A bladed disk assembly is disclosed herein. The bladed disk assembly includes a disk centered on an axis. The disk has at least one groove extending along the axis. The bladed disk assembly also includes a blade received in the groove. The bladed disk assembly also includes a retaining clip contacting the blade and limiting movement of the blade along the axis. The retaining clip is engaged with the disk through a snap-fit.

Befestigungsvorrichtung für die Düsendeckel von Turbinen mittels eines Gewinderinges

Rotations-Strömungsmaschine für elastische Strömungsmittel

Turbomachine.

Strömungsmaschine, mit einem Rotor, der ein radial durchströmtes Laufrad (10) aufweist, und mit einem Stator, der ein Gehäuse (11) und ein am Gehäuse (11) montiertes Einsatzstück (12) aufweist, wobei das Einsatzstück (12) einen Strömungskanal für ein Arbeitsfluid, nämlich eine sich in Axialrichtung erstreckende erste Strömungspassage (17) und eine sich gegenüber der ersten Strömungspassage (17) bogenförmig nach radial aussen erstreckende zweite Strömungspassage (18) des Strömungskanals, zumindest abschnittsweise begrenzt, und wobei das Einsatzstück (12) im Bereich eines Einsatzstückflanschs (15) an einem Gehäuseflansch (16) des Gehäuses (11) über Verbindungselemente (14) derart befestigt ist, dass das Laufrad (10) bei montiertem Gehäuse (11) demontierbar und montierbar ist, wobei am Gehäuse (11) ein Prall- und Verformungskörper (20) montiert ist, der im Falle des Berstens des Laufrads (10) eine Bewegung des Einsatzstücks (12) formschlüssig unterbindet.

Turbomachine.

Strömungsmaschine, mit einem Rotor, der ein radial durchströmtes Laufrad (10) aufweist, und mit einem Stator, der ein Gehäuse (11) und ein am Gehäuse (11) montiertes Einsatzstück (12) aufweist, wobei das Einsatzstück (12) einen Strömungskanal für ein Arbeitsfluid, nämlich eine sich in Axialrichtung erstreckende erste Strömungspassage (17) und eine sich gegenüber der ersten Strömungspassage (17) bogenförmig nach radial außen erstreckende zweite Strömungspassage (18) des Strömungskanals, zumindest abschnittsweise begrenzt, und wobei das Einsatzstück (12) im Bereich eines Einsatzstückflanschs (15) an einem Gehäuseflansch (16) des Gehäuses (11) über Verbindungselemente (14) derart befestigt ist, dass das Laufrad (10) bei montiertem Gehäuse (11) demontierbar und montierbar ist, wobei am Gehäuse (11) ein Prall- und Verformungskörper (20) montiert ist, der im Falle des Berstens des Laufrads (10) eine Bewegung des Einsatzstücks (12) formschlüssig unterbindet.

ТУРБІНА НИЗЬКОГО ТИСКУ ГАЗОТУРБІННОГО ДВИГУНА

Турбіна низького тиску газотурбінного двигуна, який містить турбіну (10) високого тиску, розташовану перед турбіною (12) низького тиску, і кожух (14) колектора вихідних газів, розташований за турбіною низького тиску. Турбіна низького тиску містить ротор (16, 18), прикріплений до цапфи (20) низького тиску, вал (28) низького тиску і перший підшипник (30) кочення, який розташований на валу (28) низького тиску і служить опорою цапфі (26) високого тиску, до якої прикріплений ротор (22, 24) турбіни (10) високого тиску. Турбіна містить також другий підшипник (32) кочення, розташований на цапфі (20) низького тиску за першим підшипником (30) кочення, що забезпечує центрування цапфи (20) низького тиску відносно до кожуха (14) колектора вихідних газів, й систему рифлень (34), яка розташована між першим і другим підшипниками (30, 32) і яка забезпечує можливість приведення в рух вала (28) низького тиску за допомогою цапфи (20) низького тиску.

Turboshaft engine mountable in reduction gearbox

AIRCRAFT ENGINE ASSEMBLY WITH TRANSLATIONAL GUIDANCE OF A HOOD MOVABLE RELATIVE TO THE FUSELAGE

ASSEMBLY FOR A TURBOMACHINE

L'invention concerne un ensemble pour turbomachine, comportant un écrou (64) vissé sur une partie d'extrémité d'un arbre tubulaire (60) et un organe (86) de verrouillage de l'écrou (64) sur l'arbre (60), ledit organe (86) comportant des moyens (90, 78) de couplage en rotation à l'écrou (64) et des moyens (92, 68) de couplage en rotation à l'arbre (60), ledit organe (86) étant mobile entre une position de couplage en rotation de l'écrou (64) par rapport à l'arbre (60), et une position de libération de l'écrou (64) par rapport à l'arbre (60). L'écrou (64) comporte un logement (72) dans lequel ledit organe (86) est apte à être maintenu, dans sa position de libération.

ARM FOR A TURBOMACHINE CASING COMPRISING AN ADDITIONAL REMOVABLE

Pour permettre un démontage aisé d'un palier logé dans un bras de carter de turbomachine et assurant le guidage d'un arbre de transmission de la turbomachine, il est proposé un bras de carter (50) comprenant un corps (100) formé d'un montant (112) et d'une base (110) délimitant une partie d'un logement d'arbre (102), une pièce additionnelle (106) fixée de manière amovible sur le corps (100) et délimitant un logement de palier (104) débouchant dans le logement d'arbre (102), et une cale (140) amovible interposée entre la base (110) et la pièce additionnelle (106). Il est également proposé une turbomachine (10) comprenant un tel bras de carter (50) ainsi qu'un procédé de démontage du palier d'une telle turbomachine comprenant le retrait de la cale (140) et le déplacement de la pièce additionnelle (106) vers la base (110), permettant un accès au palier.

ASSEMBLY ENTERS a JOURNAL OF COMPRESSOR AND a BEVEL GEAR FOR the DRIVE Of a CASE Of ACCESSORIES Of a TURBOSHAFT ENGINE

L'invention concerne un assemblage entre un tourillon d'arbre de compresseur et un pignon conique pour l'entraînement d'un boîtier d'accessoires d'une turbomachine. L'assemblage comprend un pignon conique (12), un tourillon d'arbre de compresseur (10) disposé à l'intérieur du pignon conique coaxialement à celui-ci, des moyens (24) de transmission de couple entre le tourillon d'arbre de compresseur et le pignon conique, un écrou de blocage axial (26) du pignon conique sur le tourillon d'arbre de compresseur, l'écrou de blocage étant apte à être vissé sur le pignon conique et comprenant un épaulement (28) faisant saillie radialement vers l'extérieur et apte à venir en butée axiale, d'une part en amont contre un écrou de butée (30) vissé sur une extrémité amont du tourillon d'arbre de compresseur, et d'autre part en aval contre une portée (32) du tourillon d'arbre de compresseur, et une épingle d'anti-rotation (34) de l'écrou de blocage.

DECOUPLING DEVICES OF FIRST AND SECOND PARTS OF A TURBOMACHINE

Dispositif (10) de découplage de première et seconde pièces (12, 14) d'une turbomachine, lesdites pièces s'étendant autour d'un axe A, caractérisé en ce que ladite première pièce (14) comprend une rangée annulaire d'ouvertures (23) traversantes axialement et s'étendant autour de l'axe A, et en ce que ladite seconde pièce (12) comprend une rangée annulaire de pattes axiales (24) fusibles traversant axialement lesdites ouvertures et comportant des portions de filetage sur lesquelles un écrou (26) d'axe A et de serrage axial des pièces est vissé.

INSTALLATION OF GUIDANCE SYSTEM ON a NACELLE Of AIRCRAFT.

HARNESS LOW PRESSURE OF TURBOSHAFT ENGINE

LIMITING DEVICE SET FOR A TURBOMACHINE

TURBINE ENGINE FLUSH HOUSING REDUCER

HARNESS LOW PRESSURE OF TURBOSHAFT ENGINE

Turbine basse-pression d'une turbomachine, la turbomachine comportant une turbine haute-pression (10) disposée en amont de la turbine basse-pression (12) et un carter d'échappement (14) disposé en aval de la turbine basse-pression, la turbine basse-pression (12) comportant un rotor (16, 18) fixé sur un tourillon basse-pression (20), un arbre basse-pression (28), un premier palier à roulement (30) disposé sur ledit arbre basse-pression (28) et supportant un tourillon haute-pression (26) sur lequel est fixé un rotor (22, 24) de la turbine haute-pression (10), un second palier à roulement (32) disposé sur ledit tourillon basse-pression (20) en aval dudit premier palier à roulement (30) et permettant de centrer ledit tourillon basse-pression (20) par rapport audit carter d'échappement (14), et un système de cannelures (34) pour l'entraînement dudit arbre basse-pression (28) par ledit tourillon basse-pression (20), ledit système de cannelures (34) étant disposé entre lesdits premier (30) et ...

ASSEMBLY Of a SUPPORT OF LABYRINTH SEAL ON a ROTOR OF TURBOSHAFT ENGINE

La fixation selon l'invention d'un support de joint à labyrinthe (7) à un arbre (9) de turbomachine, par l'intermédiaire de boulons axiaux (95); lesdits boulons axiaux solidarisant par ailleurs un organe (93) d'entraînement de module de turbine audit arbre, des trous (91A) d'extraction de l'organe (93) d'entraînement par rapport à l'arbre étant ménagés sur l'arbre, est caractérisée par le fait que le support (7) de joint à labyrinthe est serré sur l'arbre (9) dans la zone des trous (91A) d'extraction au moyen de vis de serrage (100) introduites dans les trous d'extraction (91A).

INSTALLATION OF GUIDANCE SYSTEM ON a NACELLE Of AIRCRAFT.

La présente invention concerne une nacelle (1) pour turboréacteur comprenant : - une structure d'entrée d'air (4) apte à canaliser un flux d'air vers une soufflante du turboréacteur et comprenant au moins un panneau externe (40) longitudinal intégrant une lèvre d'entrée d'air (4a), -une structure médiane (5) destinée à entourer ladite soufflante et à laquelle est rattachée la structure d'entrée d'air (4) de manière à assurer une continuité aérodynamique, - au moins un panneau interne (41) comprenant une virole acoustique, fixée à son extrémité aval à une extrémité amont de la structure médiane (5) formant avec cette dernière une structure fixe de la nacelle (1), et - des moyens de guidage (15) du ou des panneaux externes (40) aptes à permettre un déplacement sensiblement rectiligne du panneau externe (40) vers l'amont de la nacelle (1) de manière à pouvoir ouvrir la structure d'entrée d'air (4), les moyens de guidage (15) étant entièrement fixés sur la structure médiane (5).

MANIFOLD DEVICE WITH SOLENOID VALVE AND METHOD OF ASSEMBLING AND DISASSEMBLING SAME

A manifold device according to the present invention includes a housing having an inflow hole for fluid inflow and a discharge hole for fluid discharge, a valve module detachably coupled to the housing, and a control module controlling the flow of the fluid in the housing. A manifold device assembly and disassembly method according to the present invention includes a step in which a bypass section is opened so that a fluid flows to a flow path connected to the bypass section, a step in which a blocking section is locked so that the fluid flowing into the housing is blocked from flowing to a valve module, a step in which an air vent section is opened so that the pressure by the fluid in the housing is lowered, and a step in which the valve module is separated from the housing. COPYRIGHT KIPO 2018 ...

Gas turbine disassembling/assembling method, gas turbine rotor, and gas turbine

This gas turbine disassembling/assembling method comprises a seal plate restriction state switching step for switching between a seal plate unrestricted state where a seal plate movement restriction part does not restrict radial movement of a seal plate and a seal plate restricted state where at least a portion of the seal plate movement restriction part projects from the seal plate in an axial direction and restricts the radial movement of the seal plate, by operating the seal plate movement restriction part from the other side in the axial direction via a gap between a platform of a moving blade and a region other than a blade groove to be fitted with the moving blade in the outer peripheral surface of a rotor disk.

GAS TURBINE AND METHOD FOR MAINTAINING AND INSPECTING THE SAME

A gas turbine (1) comprises a gas turbine body (100) for rotating a rotor (10) with the energy of combustion gas produced by combusting fuel and taking out rotary energy from the rotor (10), an inlet casing (121) fixed to the gas turbine body (100) and introducing air to a compression section for compressing the air, an intake chamber (31) connected with the inlet casing (121) and introducing the air which is taken in from the atmosphere to the gas turbine body (100), and a notch (34) so formed in the intake chamber (31) as to include the entire range where the rotor (10) passes or exists when the rotor is moved.

MEMBER FOR LOCKING RING SECTORS ON A TURBINE ENGINE CASING, INCLUDING RADIAL PASSAGES FOR GRIPPING SAME

The invention relates to a locking member (24) for a device used to fasten ring sectors on the casing of an aircraft turbine engine, wherein the member has two clamping arms (28, 30) connected together at the rear end thereof by a connection arm (32) extending substantially parallel to the general spacing direction between the two clamping arms. According to the invention, the member is provided, on either side of a virtual median plane (P2) orthogonal to the circumferential direction, with a passage (42) for gripping the member, each passage being formed through said connection arm (32) and extending along a guide line (44) substantially parallel to the spacing direction.

AID DEVICE

The invention relates to an aid device (1) for mounting and/or dismantling a guide ring segment (2) which is to be attached or is held on a support (3), in particular a turbine guide blade support of a gas turbine, having a main body (5) which can be fastened releasably to the guide ring segment (2), and having a holding device (18), to which a traction mechanism (28) can be fastened releasably, wherein the holding device (18) is configured to transmit a pulling force to the main body (5), which pulling force acts via the traction mechanism (28) in an installing direction or expelling direction (X) of the guide ring segment (2).

SYSTEM FOR SUPPORTING AND SERVICING A GAS TURBINE ENGINE

A power system (180) includes a gas turbine engine (182), which may include a gear box (312). The gear box may include a pipe connection (316) configured to receive a removable pipe (317). The power system may also include a moveable support (162) configured to fasten to the pipe connection to at least partially support the gear box.

Tooling provision for split cases

An apparatus for separating two flanges, comprising a first prying grip having at least one flange contact member, a second prying grip having at least one flange contact member; and means for separating the flange contact members.

Frangible cover for turbofan engine blade removal and access

A frangible cover is provided for a recess in a containment case for turbofan engine blade removal and access. The recess provided in the containment case allows outward radial movement of the engine fan blade when the engine fan blade is to be removed from the containment case. The present invention proposes a frangible component to cover the recess. A plurality of initiation points, notched in the frangible cover at intersections of surfaces encourages brittle fracture of the frangible component.

Variable vane arrangement for a turbomachine

A variable vane arrangement (36) for a compressor (26) of a gas turbine engine (10) comprises a plurality of circumferentially arranged vanes (38), a plurality of operating levers (64) and a control ring (66). Each vane (38) comprises a fixed upstream portion (40) secured to a casing (30) of the compressor (26) and a movable downstream portion (42) pivotally mounted to the casing (30). The movable portion (42) of each vane (38) is pivotally mounted about an axis (Y) at the upstream end (52) of the movable portion (42) adjacent the fixed portion (40) of the respective vane (38). The movable portion (42) of each vane (38) has a spindle (60) arranged to extend through a respective aperture (46) in the casing (30). Each aperture (46) in the casing (30) has an elongate shape in cross-section and each aperture (46) has a bush (120) arranged within the aperture (46) and around the spindle (60) to fill the elongate shaped aperture (46). The downstream end (50) of the fixed portion (40) of each ...

MODULAR COMPONENTS FOR GAS TURBINE ENGINES

A system for maintaining a position of a bearing compartment in a gas turbine during disassembly of a low-pressure turbine of the gas turbine engine includes a forward annular shaft defining an engine centerline axis. The system includes a ring radially inward from and engaged with an inner diameter surface of the forward annular shaft. An aft annular shaft is radially inward from the forward annular shaft and aft of the ring. The ring is connected to a forward end of the aft annular shaft for common rotation therewith. The ring retains the aft annular shaft during disassembly. The system includes a stack nut axially held between an aft facing shoulder of the forward annular stub shaft and a forward facing surface of the ring to retain the stack nut during disassembly. 1. A system for maintaining a position of a bearing compartment in a gas turbine during disassembly of a low-pressure turbine of the gas turbine engine comprising:a forward annular shaft defining an engine centerline axis;a ring radially inward from and engaged with an inner diameter surface of the forward annular shaft;an aft annular shaft radially inward from the forward annular shaft and aft of the ring, wherein the ring is connected to a forward end of the aft annular shaft for common rotation therewith, the ring retaining the aft annular shaft during disassembly; anda stack nut axially held between an aft facing shoulder of the forward annular shaft and a forward facing surface of the ring to retain the stack nut during disassembly.2. A system as recited in claim 1 , further comprising a shaft radially inward from the stack nut and aft annular shaft claim 1 , wherein the aft annular shaft is an aft annular stub shaft claim 1 , the shaft having a threaded outer diameter surface engaged with a corresponding threaded inner diameter surface of the stack nut.3. A system as recited in claim 1 , further comprising a shaft radially inward from the stack nut and aft annular shaft claim 1 , wherein the aft ...

Bushing for a variable stator vane and method of making same

A bushing for use in a stator vane assembly that includes an annular body that extends between a first end and a second end. The bushing is configured to be removable from the stator vane assembly without disassembly of the stator vane assembly.

SYSTEMS AND METHODS FOR SEPARATING ROTOR BLADE CUFFS FROM ROTOR BLADE BODIES

A rotor blade disassembly method includes applying spanwise support to a rotor blade body and heating a bond disposed on an end of the rotor blade body. The method also includes removing the spanwise support from the rotor blade body and exerting shear stress on the bond using weight of the rotor blade body. A blade disassembly system is also described.

GAS TURBINE ENGINE DISASSEMBLY/ASSEMBLY METHODS

A method is provided for disassembling a gas turbine engine. The gas turbine engine includes a compressor section, a combustor section, a turbine section, a static structure and a bypass duct. The static structure houses and supports the compressor section, the combustor section and the turbine section. The static structure includes a turbine support structure. The bypass duct includes an inner duct wall, an outer duct wall and a bypass flowpath formed radially between the inner duct wall and the outer duct wall. The outer duct wall extends axially along the static structure and overlaps the turbine support structure. During the method, the turbine support structure is removed from the gas turbine engine while the outer duct wall remains installed.

A method and system for operative reconversion of pairs of pre-existing steam turbo-units

Method and system in which a pair of pre-existing steam turbo-units are coupled to one another in a system configuration of a cross-compound type; in which high-pressure and medium-pressure sections of the first turbine are replaced with a single high-pressure section (10) made in such a way as to maintain the pre-existing foundations (70), and in which high-pressure and medium-pressure sections of the second turbine are replaced with a single medium-pressure section (14) made in such a way as to maintain the pre-existing foundations (70). A single supercritical boiler (22) supplies in cascaded fashion one and the same flow of steam to the new high-pressure and medium-pressure sections set on the first shaft and on the second shaft, respectively. A single piping downstream of the new medium-pressure section collects the flow of steam and supplies it in parallel, via a branch (20) thereof intercepted by a regulation valve (21), to the pre-existing low-pressure sections of both of the shafts ...

DEVICE FOR PIVOTING A ROTOR OF A TURBOMACHINE FROM A FIRST POSITION INTO A SECOND POSITION

Gas turbine

Eine Gasturbine (1) mit einer Brennkammer (4), einer Anzahl von Leitschaufelreihen und einem Leitschaufelträger (16), soll unter Beibehaltung eines besonders hohen Wirkungsgrades den Austausch von Leitschaufeln weiter vereinfachen und somit für eine besonders kurze Reparaturdauer ausgelegt sein. Dazu ist eine Anzahl von Leitschaufeln (14) mittels einer parallel zur Turbinenachse (9) ausgerichteten Schwalbenschwanzverbindung (34) am Leitschaufelträger (16) befestigt.

GAS TURBINE ENGINE ASSEMBLY AND METHOD OF DISASSEMBLING SAME

The gas turbine engine assembly (119) can include a first component (120) having a male fit perimeter (154), a second component (122) having a female fit perimeter (152) forming an interference fit (126) with the male fit perimeter (154), one of the first component (120) and the second component (122) having a pulling lip (136) spanning transversally and further spanning peripherally, and a structure (160) holding the pulling lip (136) transversally offset (162) from the interference fit (126), the structure (160) having a bending portion (164) extending at least partially transversally.

リンク機構、及びこれを備えている軸流流体機械の可変静翼駆動装置

A process for dismantling the front end bearing housing or low pressure compressor shaft component of an aircraft engine

PROCEDURE FOR THE MODIFICATION OF A COMPOUND STEAM TURBINE, AS WELL AS COMPOUND STEAM TURBINE

Rotating device for a gas turbine and method for rotating a component

The invention relates to a rotating device (1) for an at least partially opened gas turbine (2), which is designed for being mounted on a parting line (11) of the housing (10) of the at least partially opened gas turbine (2) by way of at least one connecting portion (21), wherein the rotating device (1) has at least one first fastening portion (31), which is designed for mechanically interacting with a force transmission means (40), in particular at least one traction cable (40), in order to pass on mechanically a rotating movement of at least one component of the at least partially opened gas turbine (2), wherein it comprises at least one sleeve (50), which has at least one second fastening portion (51), wherein the sleeve (50) is designed for being connected non-positively to the gas turbine rotor (15).

Composite material inlet plenum and gas turbine engine system comprising said plenum

An air inlet plenum for a gas turbine engine is described. The air inlet plenum (3) comprises a hollow body (17) having an air inlet aperture (19) and an air outlet aperture (21) arranged and configured for connection to the gas turbine engine (6). The air inlet plenum (3) comprises at least one removable portion (23L, 23R), which is removable from the hollow body (17) when the air inlet plenum (3) is connected to a gas turbine engine (6). The air inlet plenum is at least partly made of fiber-reinforced plastic.

SHIM REMOVING TOOL AND METHOD

A tool for removing a shim from a dovetail of a fan blade for a turbine engine rotor includes a clip and a handle. The clip includes a release edge configured to engage a flared lip of a dovetail shim. The handle extends from the clip and contacts the exterior surface of the shim. When the handle and the clip are rotated about a longitudinal axis of the handle, the release edge separates the flared lip of the shim from the dovetail and the handle applies a downward force to easily remove the shim from the dovetail.

MISTAKE-PROOF CABLE ASSEMBLY

A mistake proof cable assembly for promoting short time engine assembly and method of assembling same. The mistake proof cable assembly comprises a slotted member defining a slot having an open end, and a cable connected to the slotted member and extending longitudinally through the slot. First and second restrainers are mounted on the cable on opposite sides of the slotted member for limiting free movement of the cable in the longitudinal direction of the slotted member. A lock prevents removal of the cable from the slot through the open end thereof.

GUIDE BLADE ARRANGEMENT OF A NON-POSITIVE-DISPLACEMENT MACHINE

The invention relates to a guide blade arrangement (1) of a non-positive- displacement machine (4), particularly of a gas turbine, comprising at least one guide blade support (2) and a number of guide blades (3), which are fastened to the guide blade support (2) and are adjacently arranged in a peripheral direction. The fastening between the guide blade support (2) and the respective guide blade (3) is provided in an axially insertable manner. In order to simplify the removal of an individual guide blade (3), at least one of the guide blades (3) is equipped with a pull-off device (35) that has at least one axially extending pull-off through opening (36). The respective pull- off through opening (36) is equipped with an internal thread (37). The guide blade support (2) is equipped with am abutment region (38) located opposite the pull-off through opening (36). The pull-off device (35) is designed for introducing axially oriented pull-off forces into the respective guide blade (3) by means ...

ASSEMBLY OF SHAFT IN BEARING WITH AUTO-EXTRACTION NUT

La présente invention concerne un moteur à turbine à gaz comprenant un arbre, un palier (14), un manchon (18) supporté par le palier, l'arbre étant engagé par un tourillon (10) d'extrémité à l'intérieur du manchon (18) et fixé au manchon (18) au moyen d'un écrou cylindrique (23). Le moteur est caractérisé par le fait que l'écrou (23) est logé à l'intérieur du tourillon et est en butée axiale dans une première direction contre le manchon (18), lorsque le tourillon (10) est vissé sur l'écrou (23), un anneau d'arrêt (25) fendu logé dans une gorge (23C) annulaire ménagée sur la face extérieure de l'écrou (23) forme butée axiale contre le manchon (18) dans la direction opposée à la première permettant l'extraction du tourillon (10) du manchon (18) par dévissage de l'écrou (23).

METHOD FOR REMOVING AND/OR INSTALLING A TURBINE BEARING AND A DEVICE FOR CARRYING OUT THE METHOD

The invention relates to a method and a device (30) for carrying out the method for removing a turbine bearing (26) or a bearing segment of a preferably stationary turbo engine, having a housing that may preferably be split in half while the housing is closed, comprising the following steps: supporting the rotor (12) to relieve the turbine bearing (26) of the weight of the rotor (12), fastening a support plate (34) to a turbine bearing housing (10), attaching two parallel, rail-like supports (36) to the support plate (34) and fastening a cross-beam (40) to ends (38) of supports (36), fastening a counter-bearing plate (43) having at least two push/pull rods (46) to the turbine bearing housing (10), and fastening the push/pull rods (46) to the turbine bearing (10) and detaching the fastening of the turbine bearing (26) from the turbine bearing housing (10) and pulling the turbine bearing (26) located in the operating position thereof out of the turbine bearing housing (10) with the aid of ...

METHOD AND APPARATUS FOR TURBINE BLADE REHABILITATION

A method and apparatus for removing erosion shields from the blades of a turbine comprises means for gripping the turbine blade, means for heating the erosion shield to detach it from the blade, and means for removing the shield including a pneumatic cylinder actuating a stripping arm once sufficient heat has been applied to the shield to detach it from the blade.

Insert removal device for gas turbine stationary blade and insert removal method for gas turbine stationary blade

An insert removal device (20) for a gas turbine stationary blade, which removes weld metal which surrounds an insert collar so as to connect the insert collar protruding outwardly from the outer peripheral surfaces of inserts to a stationary blade outside shroud non-gas path surface by arc-discharge which is repeated in a short period between an electrode (21) and the gas turbine stationary blade, wherein the bottom surface (24) of the electrode (21) has the same planar view shape as the planar view shape of the weld metal.

Turbomachine compressor whose rotor has a movable upstream stage.

ASSEMBLY Of a SUPPORT OF LABYRINTH SEAL ON a ROTOR OF TURBOSHAFT ENGINE

BODY OF LOCKING OF SECTORS Of RING ON a CASING OF TURBOSHAFT ENGINE, INCLUDING/UNDERSTANDING RADIAL PASSAGES ALLOWING SA GRIPPING

EXTRACTION TOOL OF A METAL PART

L'invention concerne un outil d'extraction (30) d'une pièce métallique (15) située dans une veine aérodynamique d'une turbomachine, telle qu'un bec de séparation de flux, comprenant : - une tige (300) ; - une première butée (310) située à une extrémité distale de la tige et munie d'une griffe (312) destinée à venir en appui contre un premier bord (152) de la pièce métallique ; - un organe de préhension (320) monté en translation sur la tige (300) et comprenant une première portion (321) en saillie aménagée pour recevoir un deuxième bord (151) opposé de la pièce métallique ; - un mécanisme de serrage (330) configuré pour maintenir l'organe de préhension (320) en appui contre la pièce métallique (15) et la première butée (310).

Method for heating connection nut placed inside tubular space of twin-coil turbojet, involves guiding hot gas production unit in tubular element, where unit leaves element radially by side opening in direction of cylindrical part

La présente invention porte sur un procédé et un dispositif pour chauffer une pièce cylindrique logée à l'intérieur d'un espace tubulaire de turbomachine. On dispose à l'intérieur de l'espace tubulaire un élément tubulaire (112) présentant un moyen (110) de production de gaz chaud et une ouverture latérale (114) à proximité de la pièce cylindrique (20).Le gaz chaud est guidé dans l'élément tubulaire dont il sort radialement par ladite ouverture en direction de la pièce cylindrique. Le procédé s'applique en particulier au cas ou la pièce cylindrique est l'écrou de liaison du rotor HP au palier avant dans le carter intermédiaire d'un turboréacteur à double corps.

MOUNTING DEVICE AND/OR ROBOTIC MANIPULATOR PROPELLANT AND METHOD

TURBOSHAFT ENGINE HAS DISMOUNTABLE BODY HP BY the BACK

PROCEEDED OF UNSCREWING BEFORE NUT OF CONNECTION IN a TURBOJET HAVEHAS TWIN SPOOL, TOOLS OF UNSCREWING

La présente invention porte sur un procédé de dévissage de l'écrou de liaison du rotor HP d'un turboréacteur à double corps, comportant une soufflante avant, un carter intermédiaire (7), un module HP avec un rotor HP et un module de turbine BP, le carter intermédiaire ayant un palier support du rotor HP, ledit rotor étant retenu dans le palier par l'écrou de liaison, le procédé comportant une étape de mise en place d'un outil de dévissage par l'avant de l'écrou de liaison après avoir démonté la soufflante et dégagé à l'avant l'accès à l'écrou, le procédé est caractérisé par le fait que, le rotor HP étant calé en rotation, l'outil de dévissage avant comprenant une clé tubulaire (320) pourvue de dents de forme complémentaire à celle des dents de l'écrou de liaison, un support (310) pour la clé tubulaire (320) est fixé sur le carter intermédiaire, la clé tubulaire (320) est montée à rotation sur le support, et un couple de dévissage est appliqué sur ladite clé tubulaire (320). L'invention ...

Holding device for dismantling a turbomachine blade wheel and method using the same

MODULAR ASSEMBLY FOR A TURBOMACHINE

Ensemble modulaire pour une turbomachine, caractérisé en ce qu'il comporte un support annulaire de paliers (26), qui comprend des moyens de liaison à un premier palier à roulement (24) configuré pour être monté autour d'un premier arbre (16) de la turbomachine, et des moyens de liaison à un second palier à roulement (31) configuré pour être monté autour d'un second arbre (18) de la turbomachine non parallèle audit premier arbre.

NACELLE FOR A JET ENGINE

Two equipments e.g. electric generator, assembly for use on accessory support of aeronautic engine, has intermediate driving wheels equipped in cinematic chains increasing rotation speed of common driving shaft with respect to engine shaft

Ensemble constitué par deux équipements (1, 2) d'un moteur aéronautique reliés par un arbre d'entraînement commun (4), ledit arbre étant entraîné en rotation par l'intermédiaire d'une roue d'entraînement (16) apte à coopérer avec une roue d'un arbre moteur (6) entraîné par ledit moteur aéronautique, les deux équipements étant positionnés de part et d'autre du plan de ladite roue de l'arbre moteur et le diamètre de la roue d'entraînement (16) étant supérieur à la section du plus petit des deux équipements, caractérisé en ce que ladite roue d'entraînement est comprise dans une chaine cinématique (14, 15, 16, 17) générant une augmentation de la vitesse de rotation de l'arbre d'entraînement (4) par rapport à celle de l'arbre moteur (6).

TOOLING FOR PLACING A PROPELLANT ASSEMBLY FROM A HORIZONTAL POSITION TO A VERTICAL POSITION

CONVERTIBLE EJECTOR COOLED NOZZLE

EXCHANGING DEVICE FOR COMBUSTOR

Combustors (b) provided centrally of a gas turbine body (g) in a radial manner are held in such a manner that a hand (7) is supported through a centering slide (6), which vertically moves in a diametrical direction (y) of the combustors (b), on a drawing slide (5), which is supported through a vertical rotating shaft (3) directed ('alpha') toward a central axis of the gas turbine body (g) and a lateral rotating shaft (4) about a radial axis ('beta') of the gas turbine body (g) on a truck (2) adapted to revolve () around the combustors (b) through a rail (1) mounted to outer peripheries of the combustors (b) in a ring-like manner and which moves in an axial direction (z) of the radially arranged combustors (b). Also, a drawing slide (103) adapted to advance and retreat in the axial direction of the combustors (b) is supported on the truck (2) adapted to move along the rail (1) provided on the outer peripheries of the radially arranged combustors (b) in a ring-like manner, an expansion slide ...

Method and apparatus for turbine blade rehabilitation

A method and apparatus for removing erosion shields from the blades of a turbine includes a part for gripping the turbine blade, a part for heating the erosion shield to detach it from the blade, and a part for removing the shield including a pneumatic cylinder actuating a stripping arm once sufficient heat has been applied to the shield to detach it from the blade.

Gas turbine mannequin

A method of constructing a gas turbine system may include placing a foundation interface of a gas turbine mannequin on a foundation, aligning the gas turbine mannequin with a load and connecting the gas turbine mannequin to the load. The method may include constructing a pipeline and connecting the pipeline to the gas turbine mannequin. The method may include placing a foundation interface of a gas turbine mannequin on a foundation, aligning the gas turbine mannequin with an exhaust structure and connecting the gas turbine mannequin to the exhaust structure. The method also includes removing the gas turbine mannequin and installing a gas turbine.

ASSEMBLY FOR RELEASABLE LOCKING OF A SPINNER OR NOSECONE TO AN ENGINE STRUCTURE

Disclosed is an assembly for a gas turbine engine, the assembly includes: a spinner or nosecone comprising a threaded rear portion, an engine structure comprising a threaded front portion, the nosecone being threadingly connected to the engine structure, wherein rotation of the spinner or nosecone about the engine structure in a first direction secures the spinner or nosecone to the engine structure and rotation of the spinner or nosecone about the engine structure in a second direction releases the spinner or nosecone from the engine structure; and a lock ring slidingly connected to the engine structure to slide between: a forward position to engage the spinner or nosecone and block rotation of the spinner or nosecone in the second direction, and a rearward position, where the lock ring is spaced from the spinner or nosecone. 1. An assembly for a gas turbine engine , the assembly comprising:a spinner or nosecone comprising a threaded rear portion, 'wherein rotation of the spinner or nosecone about the engine structure in a first direction secures the spinner or nosecone to the engine structure and rotation of the spinner or nosecone about the engine structure in a second direction releases the spinner or nosecone from the engine structure; and', 'an engine structure comprising a threaded front portion, the spinner or nosecone being threadingly connected to the engine structure,'} a forward position to engage the spinner or nosecone and block rotation of the spinner or nosecone in the second direction, and', 'a rearward position, where the lock ring is spaced from the spinner or nosecone., 'a lock ring slidingly connected to the engine structure to slide between2. The assembly of claim 1 , wherein the rear portion of the spinner or nosecone includes a boss protruding rearwardly claim 1 , and the lock ring includes a groove claim 1 , and when the lock ring is in the forward position the groove receives the boss and blockingly engages the boss to prevent rotation of ...

GAS TURBINE ENGINE MAINTENANCE STAND

A gas turbine engine maintenance stand for a gas turbine engine that comprises modules including an engine core module that houses a high pressure compressor and a turbine module that houses a low pressure turbine. The gas turbine engine maintenance stand has a pair of base beams, each base beam having a first end, a midsection and a second end. The stand has an engine core module support that straddles the pair of base beams at their midsection, the engine core module support having engine core module support arms that are configured to engage opposing sides of the engine core module of the gas turbine engine. The stand also has a turbine module support that straddles the pair of beams adjacent their second ends, the turbine module support having turbine module support arms that are configured to engage opposing sides of the turbine module of the gas turbine engine. The gas turbine engine maintenance stand is useful for disassembling and reassembling modules of a gas turbine engine in ...

SEAL DISASSEMBLY AID

A seal assembly for a gas turbine engine includes a seal carrier and a seal press fit within an inner diameter of the seal carrier. The seal includes an outer ring supporting a radially moveable shoe supported by at least one beam. The outer ring includes an inner radial surface having at least one tab extending radially inward toward the shoe for aiding removal of the seal from the carrier.

ASSEMBLY FOR AIRCRAFT TURBINE ENGINE AND METHOD FOR MOUNTING SAME

An assembly for an aircraft turbine engine, including a rolling bearing bracket defining an inner space on either side thereof; a rotary assembly including a first gear; a housing for drawing mechanical power including a second gear mating with the first gear; a shaft for drawing mechanical power, inserted into the housing and rotated by the second gear, the shaft passing through a first opening of the bracket. The assembly includes a mounting device for mounting the housing on he bearing bracket, the mounting device passing through a second opening via the bracket, the mounting device passing through a second opening via the bracket, the second opening being configured so as to allow the housing to be inserted into the space.

Fixture and method for installing turbine buckets

A fixture and method for installing turbine buckets is disclosed. The fixture is adapted for mounting a plurality of turbine buckets with dovetails to a rotor wheel of a turbomachine that is separated from an adjacent rotor wheel by a spacer wheel, the rotor wheel and the spacer wheel each having a plurality of circumferentially aligned dovetail slots, the fixture includes: a turbine bucket holder having a dovetail that is configured to engage with one of the dovetail slots of the spacer wheel. The profile of a bucket holder dovetail slot substantially aligns the dovetail of the turbine bucket with a dovetail slot of the rotor wheel for at least partial transfer of a turbine bucket thereto.

Turbine for the expansion of gas/vapour

The invention regards a turbine for the expansion of gas and vapour that comprises a body or casing with a volute for the transit of the fluid from an input to an output passage through at least a statoric and a rotoric group, a possible front shield that extends radially from said volute towards the axis of the turbine shaft, an external tube member fixed in front of said shield or said volute designed to hold the turbine shaft with the interposition of a supporting unit ( 19 ), where said turbine shaft ( 15 ) has a head ( 15′ ) supporting the rotoric group ( 16, 17 ). The turbine shaft ( 15 ) together with the rotoric group ( 16, 17 ) is movable axially between a work position, in which the head of said shaft is at a distance from an internal end of the external tube member ( 18 ) facing towards the statoric group, and a retracted position, in which the head of the shaft or a part of the rotoric group rests against said internal end of said tube member with the interposition of at least a front seal ( 41 ).

Axial locking seals for aft removable turbine blade

A turbine blade rotor assembly provides sealing for the rotor components and bi-direction axially locking of the blades on the rotor using a seal plate on the aft exhaust side without axial locking on the forward intake side of the rotor and blade array. As a result, the blades can be removed from the aft direction without moving the turbine casing cover.

Bladed disk assembly

A bladed disk assembly is disclosed herein. The bladed disk assembly includes a disk centered on an axis. The disk has at least one groove extending along the axis. The bladed disk assembly also includes a blade received in the groove. The bladed disk assembly also includes a retaining clip contacting the blade and limiting movement of the blade along the axis. The retaining clip is engaged with the disk through a snap-fit.

Combustor Liner and Flow Sleeve Tool

A tool includes an annular frame portion including a mount portion extending radially from the frame portion, a hook portion arranged on the mount portion, the hook portion sized and shaped to engage a member of a tubular component of a turbine combustor, and a force exertion portion arranged on the mount portion, the force exertion portion operative to engage a portion of the turbine combustor.

Rotor centralization for turbine engine assembly

One or more support elements radially extend through one or more openings defined in a turbine engine casing and are configured to centralize and at least partially support a rotor assembly of the engine during an engine disassembly or assembly procedure. The support elements are configured to transfer any rotor assembly weight loads to an engine casing while a bearing support of the rotor assembly is absent or removed.

Component removal apparatus for use in turbine engines and methods of removing components from turbine engines

A component removal apparatus for use with a turbine engine is provided. The apparatus includes a main body and at least one alignment member that extends from the main body, wherein the alignment member is configured to position the apparatus relative to at least a portion of a component of the turbine engine. At least one leg member extends outwardly from at least one end portion of the main body. At least one lifting member is coupled to the leg member and is configured to apply a force to the leg member and/or the main body to facilitate the removal of the component from the turbine engine.

Method for removing an inner casing from a machine

The method for removing an inner casing from a machine includes removing a top part of the outer casing, removing a top part of the inner casing, removing the bottom part of the inner casing, before removing the bottom part of the inner casing connecting the bottom part of the inner casing to the rotor, such that the bottom part of the inner casing is supported by the rotor, then rotating the rotor around the longitudinal axis to make the bottom part of the inner casing accessible.

Method and fixture for airfoil array assembly

An example method of assembling a turbomachine airfoil array includes, among other things, securing a partial airfoil array within a fixture, the partial airfoil array having at least one existing airfoil extending radially between an inner and an outer fairing and an open area where at least one existing airfoil has been removed. The method includes mounting a positioning saddle relative to a base of the fixture, the positioning saddle aligned with the open area, holding a replacement airfoil using the positioning saddle, applying a curable material at an interface between the replacement airfoil and the inner and outer fairing, and curing the curable material while maintaining a relative position between the replacement airfoil and the inner and outer fairing.

REMOVABLE NOSECONE FOR A GAS TURBINE ENGINE

A gas turbine engine includes a nosecone assembly attached to a gas turbine engine. The nosecone assembly includes a support structure and a nosecone attached to the support structure. The nosecone includes at least a first tool hole extending through the nosecone. The first tool hole is structurally reinforced. 1. A gas turbine engine comprising: a support structure; and', 'a nosecone attached to the support structure, wherein the nosecone includes at least a first tool hole extending through the nosecone, wherein the first tool hole is structurally reinforced., 'a nosecone assembly attached to the gas turbine engine, the nosecone assembly comprising2. The gas turbine engine of claim 1 , wherein the first tool hole is structurally reinforced such that the nosecone is stronger adjacent the first tool hole than at least some other portions of the nosecone.3. The gas turbine engine of claim 1 , wherein the first tool hole is structurally reinforced via a first grommet attached to the nosecone at the first tool hole.4. The gas turbine engine of claim 1 , wherein the first tool hole is structurally reinforced via a hard anodized coating applied to the nosecone at the first tool hole.5. The gas turbine engine of claim 1 , wherein the nosecone includes a nosecone tip opposite a nosecone aft end claim 1 , and wherein the first tool hole is positioned on or nearer the nosecone tip than the nosecone aft end.6. The gas turbine engine of claim 1 , wherein the support structure comprises a support ring positioned radially outward of and in friction contact with an aft end of the nosecone.7. The gas turbine engine of claim 1 , wherein the gas turbine engine is an industrial gas turbine engine further comprising:a first compressor section attached to a first turbine section via a first shaft;a second compressor section attached to a second turbine section via a second shaft; anda power turbine section positioned downstream of the first and second turbine sections.8. The gas ...

FASTENER REMOVAL TOOLS AND METHODS

A fastener removal tool is provided. The fastener removal tool includes a body having a cylinder and a puller coupled to the body. The puller includes an arm for engaging an installed fastener and a piston inserted into the cylinder of the body such that, when the cylinder is pressurized, the piston is displaced within the cylinder to displace the arm relative to the body to cause removal of the fastener. 1. A fastener removal tool comprising:a body comprising a cylinder; and an arm for engaging an installed fastener; and', 'a piston inserted into said cylinder of said body such that, when said cylinder is pressurized, said piston is displaced within said cylinder to displace said arm relative to said body to cause removal of the fastener., 'a puller coupled to said body, said puller comprises2. A fastener removal tool in accordance with claim 1 , wherein said body comprises a pair of cylinders claim 1 , said puller comprises a pair of pistons each inserted into a respective one of said cylinders.3. A fastener removal tool in accordance with claim 1 , further comprising a return spring biasing said puller towards said body.4. A fastener removal tool in accordance with claim 3 , wherein said body comprises a sleeve claim 3 , said return spring inserted into said sleeve of said body.5. A fastener removal tool in accordance with claim 1 , wherein said arm defines an open-ended slot for slidably engaging the fastener.6. A fastener removal tool in accordance with claim 1 , wherein said body is generally U-shaped and comprises a first leg member claim 1 , a second leg member claim 1 , and a bridge member coupling said first leg member to said second leg member such that a passage is defined between said first and second leg members.7. A fastener removal tool in accordance with claim 1 , further comprising a shield coupled to said body and at least partially surrounding said puller.8. A fastener removal tool in accordance with claim 1 , wherein said tool is sized for ...

METHOD FOR REMOVING TURBINE BLADE, REMOVAL DEVICE FOR EXECUTING SAID METHOD, AND ROTOR SET WITH SAID REMOVAL DEVICE

A removal device includes a base, a push rod, a rod-moving mechanism and a rod guide. The base is restrained immovably in a first direction. The push rod can protrude from a front surface of the base toward a front side. The rod-moving mechanism is installed on the base. The rod-moving mechanism moves the push rod toward the front side. The rod guide is attached to the base. The rod guide guides movement of the push rod by the rod-moving mechanism in a second direction that forms an acute angle with respect to the first direction. 119-. (canceled)20. A removal device for a turbine blade , comprising:a base restrained immovably in a first direction;a push rod that is able to protrude from a front surface of the base facing a front side that is one side in the first direction toward the front side;a rod-moving mechanism installed on the base and configured to move the push rod toward the front side; anda rod guide attached to the base and configured to guide movement of the push rod by the rod-moving mechanism in a second direction that forms an acute angle with respect to the first direction,wherein the rod-moving mechanism has a taper-forming body inclined with respect to a virtual surface perpendicular to the first direction and on which a tapered surface facing the front side is formed, and the taper-forming body is formed on the base such that the tapered surface is relatively movable in a direction in which the virtual surface widens with respect to an end surface of a rear side while coming in contact with an end surface of the rear side of the push rod opposite to the front side.21. A removal device for a turbine blade , comprising:a base restrained immovably in a first direction;a push rod that is able to protrude from a front surface of the base facing a front side that is one side in the first direction toward the front side;a rod-moving mechanism installed on the base and configured to move the push rod toward the front side; anda rod guide attached to the ...

Blade removal device and method

A blade removal device for removing a blade in a circumferential direction of a blade ring along a groove, the blade being engaged with the groove extending in the circumferential direction on an inner peripheral side of the blade ring, is provided with a towing part for towing the blade, a string member connecting the towing part and the blade, and a first turning part attached to the blade ring so as to be in contact with a portion of the string member between the towing part and the blade to change a direction of a towing force transmitted via the string member.

Method of disassembling and assembling gas turbine and gas turbine assembled thereby

A method of assembling and disassembling a gas turbine, and a gas turbine assembled thereby, improves work efficiency and reduces time and cost by carrying out various disassembly and reassembly processes depending on circumstances. In one process, a turbine section is disassembled from a gas turbine by sequential steps of disassembling an upper turbine case; disassembling a rear diffuser assembly and a rear bearing assembly; disassembling a combustor assembly; disassembling a vane assembly; and disassembling a blade assembly. In another process, first-stage to fourth-stage blade assemblies and first-stage to fourth-stage vane assemblies in a turbine section are disassembled from the gas turbine by sequential steps of disassembling an upper turbine case; disassembling a combustor assembly; disassembling a vane assembly; and disassembling a blade assembly. The gas turbine includes a compressor section, a combustor section, and the turbine section assembled in a reverse order with respect to the disassembly method.

METHOD OF ASSEMBLING AND DISASSEMBLING GAS TURBINE AND GAS TURBINE ASSEMBLED THEREBY

A method of assembling and disassembling a gas turbine carries out various disassembly and reassembly processes depending on circumstances. In one process, a first-stage blade assembly and a first-stage vane assembly of a turbine section are disassembled from a gas turbine by sequential steps of disassembling a combustor assembly; disassembling a first-stage vane assembly; and disassembling a first-stage blade assembly. In another process, a fourth-stage blade assembly of a turbine section is disassembled from a gas turbine by sequential steps of disassembling a diffuser loading slot from a rear diffuser; and disassembling a fourth-stage blade assembly from a turbine disk. In another process, a rear bearing assembly of a turbine section is disassembled from a gas turbine by sequential steps of disassembling a rear diffuser cover from a rear diffuser; and supporting one end of a rotor shaft and disassembling a rear bearing from a rotor shaft support. 1. A method of disassembling a first-stage blade assembly and a first-stage vane assembly of a turbine section from a gas turbine , the method comprising sequential steps of:(a) disassembling a combustor assembly;(b) disassembling a first-stage vane assembly; and(c) disassembling a first-stage blade assembly.2. The method according to claim 1 , wherein the step (a) comprises sequential steps of:(a1) disassembling a combustor head assembly and a liner from a combustor mounting portion; and(a2) disassembling a transition piece from an upper front vane carrier assembly.3. The method according to claim 1 , wherein the step (b) comprises:(b1) disassembling an inner seal carrier bolt from a first-stage U-ring.4. The method according to claim 3 , wherein the step (b) further comprises:(b2) disassembling a first-stage vane from the first-stage U-ring.5. The method according to claim 4 , wherein the step (b) further comprises sequential steps of:(b3) disassembling an inner seal carrier bolt; and(b4) disassembling a first-stage ...

METHOD AND DRIVE-OUT DEVICE FOR DRIVING OUT A BLADE

A method is provided having the following steps: a) providing a drive-out device which has a drive-out punch that is actuated via a hydraulic cylinder; b) positioning the drive-out device between two adjacent wheel discs of the rotor such that a longitudinal axis of the drive-out punch is flush with the receiving groove of the blade to be driven out; c) adjusting a maximum pressure which can be applied to the hydraulic cylinder; d) extending the drive-out punch such that the drive-out punch presses against the blade root of the blade to be driven out with increasing pressure; e) reducing the pressure as soon as the pressure has reached the maximum pressure; and f) cyclically repeating the steps d) and e) until the blade has been removed from the receiving groove. A drive-out device is further provided. 1. A method for driving out a blade , a blade root of which is held in an elongate receiving groove of a wheel disk arranged on a stacked rotor , the method comprising:a) providing a drive-out device, which has a driving-out ram actuated by way of a hydraulic cylinder;b) positioning the drive-out device between two adjacent wheel disks of the stacked rotor in such a way that a longitudinal axis of the driving-out ram is in line with the elongate receiving groove of the blade to be driven out;c) setting a maximum pressure to which the hydraulic cylinder can be subjected;d) extending the driving-out ram, so that the driving-out ram presses with increasing pressure against the blade root of the blade to be driven out;e) reducing the pressure as soon as the pressure has reached the maximum pressure; andf) cyclically repeating steps d) and e) until the blade has been removed from the elongate receiving groove.2. The method as claimed in claim 1 , wherein the elongate receiving groove is inclined with respect to an axial direction of the stacked rotor.3. The method as claimed in claim 1 , wherein the maximum pressure is at least 150 bar.4. The method as claimed in claim 1 , ...

Assembly Tool for Exhaust Turbochargers

A lifting apparatus for assembly of exhaust turbocharger allows the removal of the rotor block from the housing in a horizontal direction. The lifting apparatus includes a cantilever, which is fastened on a vertical stop, i.e. on an axial end, of the housing, and on which there is arranged a structure which can be moved along the cantilever and which is likewise fastened on a vertical stop, i.e. an axial end of the rotor block. 1. A lifting apparatus for moving a rotor block , which is arranged in a housing of an exhaust turbocharger , along the axis of rotation of the rotor contained in the rotor block , wherein the lifting apparatus has a cantilever , which is provided for fastening on a vertical stop of the housing surrounding the rotor block , whereinthe cantilever comprises a supporting frame with rails arranged thereon and a carriage guided on the rails, wherein the mounting devices for fastening a structure that can be fastened on a vertical stop of the rotor block are arranged on the carriage, allowing the structure to be moved with the aid of the carriage along the rails arranged on the supporting frame of the cantilever.2. The lifting apparatus as claimed in claim 1 , wherein the carriage is connected to a spindle nut claim 1 , which is arranged on a threaded rod claim 1 , making it possible to move the spindle nut and thus the carriage along the threaded rod by rotating the threaded rod claim 1 , wherein a spindle wheel is preferably provided for rotating the threaded rod.3. The lifting apparatus as claimed in claim 2 , wherein a connection with play in the direction of the threaded rod is provided between the spindle nut and the carriage claim 2 , allowing the carriage to be moved along the threaded rod relative to the spindle nut within the range of the play claim 2 , even when the threaded rod is not being rotated.4. The lifting apparatus as claimed in claim 1 , wherein the structure comprises at least two vertically spaced fastening points for ...

SYSTEM AND METHOD FOR THE HYBRID CONSTRUCTION OF MULTI-PIECE PARTS

A multi-piece part includes multiple pieces fabricated via different types of fabrication processes, wherein the multiple parts are configured to be coupled to one another to form the assembly. At least one of the multiple parts is fabricated via an additive manufacturing method. The multi-piece part also includes a holder assembly that couples and holds together the multiple pieces of the multi-piece part, wherein the holder assembly comprises a reversible, mechanical-type coupling. 1. A method , comprising:fabricating a plurality of pieces of a multi-piece part via a plurality of different types of fabrication processes, wherein at least one piece of the plurality of pieces is fabricated via an additive manufacturing process;coupling the plurality of pieces together to assemble the multi-piece part; andsecuring the plurality of pieces of the multi-piece part to one another via a holder assembly.2. The method of claim 1 , wherein fabricating the plurality of pieces comprises fabricating a first alignment feature on a first end face of the at least one piece and fabricating a second alignment feature on a second end face of an additional piece of the plurality of pieces claim 1 , wherein the first alignment feature is configured to removably couple with the second alignment feature.3. The method of claim 2 , wherein coupling the plurality of pieces comprises engaging the first end face of the at least one piece with the second end face of the additional piece to enable the first alignment feature and the second alignment feature to receive and engage with one another.4. The method of claim 1 , wherein fabricating the at least one piece via the additive manufacturing process comprises fabricating the at least one piece via a binderjet process claim 1 , a three-dimensional printing process claim 1 , a direct metal laser melting process claim 1 , or a direct metal laser sintering process.5. The method of claim 1 , comprising fixedly coupling the plurality of pieces via ...

METHOD AND SYSTEM FOR REPAIRING TURBOMACHINE DOVETAIL SLOTS

A system for repairing dovetail slots includes a slot adaptor having a body configured and disposed to nest between first and second side walls of a dovetail slot, and a tool holder configured to be coupled with the slot adaptor. The tool holder includes a tool guidance system configured and disposed to direct a tool into contact with one of the first and second side walls of the dovetail slot. A cutting tool is mounted in the tool holder. The cutting tool includes a tapered surface configured and disposed to form a tapered recess in the one of the first and second side walls of the dovetail slot. 1. A system for repairing dovetail slots comprising:a slot adaptor having a body configured and disposed to nest between first and second side walls of a dovetail slot;a tool holder configured to be coupled with the slot adaptor, the tool holder including a tool guidance system configured and disposed to direct a tool into contact with one of the first and second side walls of the dovetail slot; anda cutting tool mounted in the tool holder, the cutting tool including a tapered surface configured and disposed to form a tapered recess in the one of the first and second side walls of the dovetail slot.2. The system of claim 1 , wherein the slot adaptor includes a slot retaining feature configured and disposed to nest within the dovetail slot.3. The system of claim 1 , wherein the slot adaptor includes at least one mechanical fastener configured and disposed to extend through the body and engage with the dovetail slot.4. The system of claim 1 , wherein the tool holder includes a slot adaptor mounting portion detachably coupled to the slot adaptor claim 1 , the tool guidance system being movably mounted relative to the slot adaptor mounting portion.5. The system of claim 4 , wherein the tool guidance system is coupled to the slot adaptor mounting portion through a screw claim 4 , the screw being selectively rotated to move the tool guidance system relative to the slot adaptor ...

Method for removing and/or installing a turbine bearing and a device for carrying out the method

A method and a device are provided for removing a turbine bearing or a bearing segment of a preferably stationary turbo engine, having a housing that may preferably be split in half while the housing is closed. The method includes: supporting the rotor to relieve the turbine bearing of the weight of the rotor, fastening a support plate to a turbine bearing housing, attaching two parallel, rail-like supports to the support plate and fastening a cross-beam to ends of supports, fastening a counter-bearing plate having at least two push/pull rods to the turbine bearing housing, and fastening the push/pull rods to the turbine bearing and detaching the fastening of the turbine bearing from the turbine bearing housing and pulling the turbine bearing located in the operating position thereof out of the turbine bearing housing with the aid of the push/pull rods.

GAS TURBINE ENGINE CONFIGURED FOR MODULAR ASSEMBLY/DISASSEMBLY AND METHOD FOR SAME

A method for assembling and disassembling a module of gas turbine engine is provided, along with a gas turbine engine configured for modular assembly/disassembly. The engine includes a first shaft and a second shaft. The first shaft connects a compressor section and a first turbine section. The second shaft is connected to the second turbine section. The first and second shafts are rotatable about the engine rotational axis. The second shaft and the second turbine section together form a module that can be assembled, or disassembled, or both from the engine. 1. A method of disassembling a gas turbine engine , comprising the steps of:providing a gas turbine engine having a rotational axis, a compressor section, a first turbine section, a second turbine section, a first shaft connecting the compressor section and the first turbine section, which first shaft is rotatable about the engine rotational axis, a second shaft connected to the second turbine section, which second shaft is rotatable about the engine rotational axis, a shaft spacer, and a first shaft nut;removing the shaft spacer;moving the second shaft and the second turbine section axially forward as a module to a disassembly position;uncoupling the first shaft nut; andremoving the second shaft and the second turbine section as a module from the gas turbine engine.2. The method of claim 1 , wherein the engine further comprises a frame spacer claim 1 , and the method further comprising the step of removing the frame spacer prior to moving the second shaft and the second turbine section module axially forward.3. The method of claim 2 , wherein the first shaft nut includes a castellated end surface claim 2 , and the second shaft includes a flange having a castellated distal end surface that mates with the castellated end surface of the first shaft nut claim 2 , and the method further includes engaging the castellated end surfaces of the first shaft nut and the second shaft claim 2 , and rotating the second shaft ...

GAS TURBINE ENGINE

A gas turbine engine for an aircraft, comprising: an engine core; a covering configured to cover at least part of the engine core; and an engine accessory that interacts with the engine core or a component of the engine core; wherein the engine accessory is outside the covering. 1. A gas turbine engine for an aircraft , comprising;an engine core;a covering configured to cover at least part of the engine core; andan engine accessory that interacts with the engine core or a component of the engine core; whereinthe engine accessory is disposed on the outside of the covering.2. The gas turbine engine of claim 1 , whereinthe covering further comprises a socket; andthe engine accessory is removably connected to the socket.3. The gas turbine engine of claim 1 , whereinthe gas turbine engine further comprises an interface connecting the engine accessory to the engine core or the component of the engine core.4. The gas turbine engine of claim 3 , whereinthe interface comprises a socket; andthe engine accessory is removably connected to the socket.5. The gas turbine engine of claim 3 , whereinthe interface comprises a conduit that provides a fluid connection from the engine accessory to the engine core or the component of the engine core.6. The gas turbine engine of claim 3 , whereinthe interface comprises an electrical connection from the engine accessory to the engine core or the component of the engine core.7. The gas turbine engine of claim 3 , whereinthe interface comprises an connecting member that provides an actuating mechanism between the engine accessory to the engine core or the component of the engine core.8. The gas turbine engine of claim 3 , whereinthe engine accessory is detachable from the interface.9. The gas turbine engine of claim 1 , whereinthe engine accessory is disposed on the covering such that the engine accessory and the covering form a continuous surface.10. The gas turbine engine of claim 9 , wherein the engine accessory is configured to transfer ...

HANDLING DEVICE

A handling device is provided for handling a burner of a stationary gas turbine during assembly and disassembly, including a base body having at least one contact surface designed to contact a rear end surface of a burner, fixing means for fixing the base body to the rear end surface of the burner, and two arms fixed to and protruding from the base body to different sides of the contact surface, wherein each arm is provided with receiving means, which are designed for removably receiving a fixing component of a lifting appliance and which are spaced apart from each other in the longitudinal direction of a burner during its handling. 1. A handling device for handling a burner of a stationary gas turbine during assembly and disassembly , comprising:a base body having at least one contact surface designed to contact a rear end surface of a burner;a fixing means for fixing the base body to the rear end surface of the burner; andtwo arms fixed to and protruding from the base body to different sides of the at least one contact surface;wherein each arm of the two arms is provided with a receiving means, designed for removably receiving a fixing component of a lifting appliance and which are spaced apart from each other in a longitudinal direction of the burner during handling.2. The handling device according to claim 1 , wherein the fixing means comprises at least one screw.3. The handling device according to claim 2 , wherein the base body comprises at least one slot hole for receiving the at least one screw claim 2 , the at least one slot hole extending along a predetermined circular arc corresponding to a screw-hole circle arranged at the rear end surface of the burner.4. The handling device according to claim 3 , wherein the at least one slot hole is arranged adjacent to the at least one contact surface.5. The handling device according to claim 1 , wherein the base body is provided with a plurality of additional protruding fixing pins.6. The handling device according ...

METHOD OF REMOVING BEARING COMPARTMENT

The present disclosure provides a method of removing a bearing compartment from a gas turbine engine comprising inserting a tool between an aft portion of a low pressure turbine and a forward portion of a turbine exhaust case, the tool comprising one of a single wedge-shaped ring or a plurality of wedge-shaped segments, removing a plurality of fasteners coupling a flange of a bearing compartment housing to the turbine exhaust case, the bearing compartment housing containing the bearing compartment, and removing the bearing compartment housing from an aft portion of the gas turbine engine. 1. A method of removing a bearing compartment from a gas turbine engine , comprising:inserting a tool between an aft portion of a low pressure turbine and a forward portion of a turbine exhaust case, the tool comprising one of a single wedge-shaped ring or a plurality of wedge-shaped segments;removing a plurality of fasteners coupling a flange of a bearing compartment housing to the turbine exhaust case, the bearing compartment housing containing the bearing compartment; andremoving the bearing compartment housing from an aft portion of the gas turbine engine.2. The method of claim 1 , wherein the tool is configured to redistribute weight of the low pressure turbine from the bearing compartment housing to the tool.3. The method of claim 1 , further comprising decoupling the bearing compartment housing from a low pressure turbine shaft.4. The method of claim 1 , wherein the tool contacts at least a portion of a radially inward surface of the low pressure turbine and at least a portion of a radially outward surface of the turbine exhaust case.5. The method of claim 1 , wherein the tool is localized between an upper portion of the low pressure turbine and an upper portion of the turbine exhaust case.6. The method of claim 1 , wherein the tool comprises a base claim 1 , an inner ring claim 1 , an outer ring claim 1 , and a vertex.7. The method of claim 1 , wherein the flange extends ...

Artificial lift

An electric submersible pump (ESP) is described. The ESP includes a stator chamber, a stator within the stator chamber, a rotor, and an electrical connection. The stator chamber is configured to reside in a wellbore. The stator chamber is configured to attach to a tubing of a well. The stator chamber defines an inner bore having an inner bore wall that, when the stator chamber is attached to the tubing, is continuous with an inner wall of the tubing. The rotor is positioned within the inner bore of the stator chamber. The rotor includes an impeller. The rotor is configured to be retrievable from the well while the stator remains in the well. The stator is configured to drive the rotor to rotate the impeller and induce well fluid flow in response to receiving power through the electrical connection.

METHOD OF ENGINE SPLIT AND REASSEMBLY

A method of axially separating an annular system, such as a gas turbine engine (), comprising first () and second () annular components. An annular array of fastenings () couples the first () and second () components together axially. The first () and second () components are supported by support tooling. The fastenings () are removed to leave one fastening () located on each side of the system. One of the remaining fastenings () is removed. The relative height of the first () and second () components is adjusted so that the apertures () for the fastening () removed at the previous step are aligned. Then the final fastening () is removed. 1101034364234364648. A method of axially separating an annular system (); the system () comprising a first annular component () , a second annular component () and an annular array of fastenings () that couple the first and second components ( , ) together axially through aligned apertures ( , ); the method comprising steps to:{'b': 34', '36, 'a) support the first and second components (, ) with support tooling;'}{'b': 42', '42', '10, 'b) remove fastenings () to leave one fastening () located on each side of the system ();'}{'b': '42', 'c) remove one of the remaining fastenings ();'}{'b': 34', '36', '46', '48', '42, 'd) adjust the relative height of the first and second components (, ) so that the apertures (, ) for the fastening () removed at step c) are aligned; and'}{'b': '42', 'e) remove the final fastening ().'}215242. A method as claimed in wherein the locations in step .b) are each less than or equal to 15° from a horizontal plane () through the diameter of the array of fastenings ().3142541042561011. A method as claimed in in which step .b) is modified to comprise leaving one fastening () located on one side () of the system () and two fastenings () located on the second side () of the system () claim 1 , the method having a further step between steps .b) and .c) to:{'b': 42', '56', '34', '36', '46', '48', '42, 'a) remove ...

Apparatus and method for servicing gas turbine engines

The present disclosure relates to an apparatus having an elongated body configured to be inserted into a tubular structure extending between a first combustor and a second combustor of a gas turbine engine. A movable arm may be positioned proximate to a first end of the elongated body, and the movable arm may be configured to engage a surface of the first combustor when the elongated body is placed within the tubular structure. A drive member may be accessible near a second end of the elongated body, and the drive member may be configured to rotate within the elongated body and to drive the movable arm along a longitudinal axis of the elongated body toward the second end to separate the tubular structure from the second combustor.

Method and device for changing a gasket in an aircraft engine

Method for removing a front seal plate ( 11 ) from an aircraft engine ( 1 ), the method comprising at least the following steps: a) separating a part engine unit ( 5 ) from the aircraft engine ( 1 ), the part engine unit ( 5 ) comprising the core engine ( 6 ) and the low-pressure turbine ( 7 ) of the aircraft engine ( 1 ), b) removing a front seal plate nut ( 10 ) from the part engine unit ( 5 ), c) removing the front seal plate ( 11 ) from the part engine unit ( 5 ).

TURBINE ENGINE WITH AN OIL GUIDING DEVICE AND METHOD FOR DISASSEMBLING THE TURBINE ENGINE

A turbine engine is provided with a longitudinal rotation axis having at least one shaft with a radial axis, in particular a pitch change system for the blades of a propeller, said shaft traversing a radial passage of a substantially cylindrical case around the longitudinal axis. The turbine engine includes an annular oil guiding device around the radial shaft. The device has first and second annular parts nested in one another and secured to one another by hooping. The first part is secured by hooping to the radial shaft, and the second part is configured so as to be separated from the first part under the action of a force oriented along the radial axis and exerted on the second part by a member of the turbine engine forming a stop during a radial movement of the radial shaft. 1. A turbine engine provided with a longitudinal rotation axis comprising at least one shaft with a radial axis , in particular a pitch change system for the blades of a propeller , said shaft traversing a radial passage of a substantially cylindrical case around the longitudinal axis , andwherein the turbine engine comprises an annular oil guiding device that extends around the radial shaft, said oil guiding device comprising a first annular part and a second annular part nested in one another and secured to one another by hooping, the first part being secured by hooping to the radial shaft and the second part being configured to be separated from the first part by the action of a force oriented along the radial axis and exerted on the second part by a member of the turbine engine forming a stop during a radial movement of the radial shaft.2. The turbine engine according to claim 1 , wherein the first part passes through the member claim 1 , the inner diameter of the member of the turbine engine being substantially larger than the outer diameter of the first part.3. The turbine engine according to claim 1 , wherein the first part comprises a cylindrical support step extending in a plane ...

FAN BLADE REMOVAL METHOD AND TOOLING

A tooling and a method for removing or mounting a fan blade from or to a fan disc of a ducted fan aeroengine are provided. The tooling comprises a cover adapted to be arranged on an inner wall of an air intake of the aeroengine and a boot adapted to be mounted on a leading edge tip of the blade and adapted to slide on the cover during removing or mounting the fan blade from or to the fan disc. 1. A method of removing/mounting a fan blade from/to a fan disc of a ducted fan aeroengine comprising:providing a cover on an inner wall of an air intake of the aeroengine; and/or a boot on a leading edge tip and/or a trailing edge tip of the fan blade; andremoving/mounting the fan blade from/to the fan disc by sliding the fan blade across the inner wall of the air intake of the aeroengine, wherein said cover and/or boot prevent the fan blade from contacting the inner wall of the air intake during removing/mounting.2. The method according to claim 1 , comprising providing the cover on the inner wall of the air intake of the aeroengine and wherein the cover is removably mounted to the inner wall of the air intake of the aeroengine.3. The method according to claim 2 , wherein the cover is removably mounted to the inner wall of the air intake of the aeroengine by fixing the cover to the air intake with any one of bolts claim 2 , clamps claim 2 , magnets claim 2 , suction cups or frames.4. The method according to claim 1 , comprising providing the boot on the leading edge tip and/or the trailing edge tip of the fan blade and wherein the boot is removably mounted to the leading edge tip and/or the trailing edge tip of the fan blade.5. The method according to claim 4 , wherein the boot is mounted with interference fit to the leading edge tip and/or the trailing edge tip of the fan blade.6. The method according to claim 1 , comprising providing the cover on the inner wall of the air intake of the aeroengine claim 1 , and providing the cover with a groove to axially guide the fan ...

GAS TURBINE ENGINE

There is disclosed a gas turbine engine for an aircraft comprising: a propulsive fan having a plurality of fan blades; a fan casing; and an air intake; wherein the air intake is mechanically coupled to the fan casing at a point having an axial position that is within a range of axial positions from a first axial position that is rearward of the leading edge of the fan blade at its radial tip by an axial component of a blade chord length, to a second axial position that is forward of the leading edge of the fan blade tip by an axial component of the blade chord length. 1. A gas turbine engine for an aircraft comprising:a propulsive fan having a plurality of fan blades;a fan casing; andan air intake;wherein the air intake is mechanically coupled to the fan casing at a point having an axial position that is within a range of axial positions from a first axial position that is rearward of the leading edge of the fan blade at its radial tip by an axial component of a blade chord length, to a second axial position that is forward of the leading edge of the fan blade tip by an axial component of the blade chord length.2. A gas turbine engine as claimed in claim 1 , wherein the point of mechanical coupling is axially forward of the leading edge of the fan blade tip by 10% claim 1 , 20% claim 1 , 30% claim 1 , 40% claim 1 , 50% claim 1 , 60% claim 1 , 70% claim 1 , 80% or 90% of the axial component of the blade chord length.3. A gas turbine engine as claimed in claim 1 , wherein the point of mechanical coupling is axially rearward of the leading edge of the fan blade tip.4. A gas turbine engine as claimed in claim 1 , wherein the point of mechanical coupling is at the same axial position as the leading edge of the fan blade tip.5. A gas turbine engine as claimed in claim 1 , wherein the fan comprises a central portion and the plurality of fan blades are formed integrally with the central portion.6. A gas turbine engine as claimed in claim 1 , wherein the fan casing is ...

EXHAUST CHAMBER INLET-SIDE MEMBER, EXHAUST CHAMBER, GAS TURBINE, AND LAST-STAGE TURBINE BLADE REMOVAL METHOD

An object of the present invention is to easily remove last-stage turbine blades. Provided is an exhaust chamber inlet-side member that has an annular shape around a rotor so as to form a part of an inner diffuser at a position facing, from the axially downstream side, base ends of last-stage turbine blades disposed on the most downstream side in the axial direction, and that is divided in the circumferential direction and provided so as to be detachable from the inner diffuser. When the exhaust chamber inlet-side member is dismounted from the inner diffuser, a space on the axially downstream side from the last-stage turbine blades is cleared. 1. An exhaust chamber inlet-side member that is provided on an inlet side of an exhaust chamber including:a casing wall that is disposed, relative to a turbine including a plurality of turbine blades that are provided around a rotating shaft and in multiple stages in an axial direction in which the rotating shaft extends and rotate with the rotating shaft, on the downstream side adjacent to the turbine and has a cylindrical shape centered at an axis of the rotating shaft;an outer diffuser provided along an inner peripheral surface of the casing wall and having an annular shape around the rotating shaft;an annular inner diffuser which is disposed on the radially inner side of the outer diffuser and between which and the outer diffuser a combustion gas passage is formed; anda plurality of struts that are disposed in a circumferential direction between the outer diffuser and the inner diffuser, and connect the casing wall and an annular bearing cover covering a bearing of the rotating shaft to each other,the exhaust chamber being divided in the circumferential direction into an upper-half part and a lower-half part, whereinthe exhaust chamber inlet-side member has an annular shape around the rotating shaft so as to form a part of the inner diffuser at a position facing, from the axially downstream side, base ends of last-stage ...

GEARBOX AND DISASSEMBLY METHOD FOR DISENGAGING A DRIVE SHAFT IN SUCH A GEARBOX

A gearbox comprising a main unit comprising a first casing and a first hollow shaft, and a secondary unit comprising a second casing and a second hollow shaft, and a drive shaft comprising a first clutch portion and a second clutch portion, which engage the first and second hollow shafts in an angularly fixed and axially sliding manner. The gearbox further including an axial retaining device comprising an axial shoulder supported in a fixed portion by an axial end on one of the first or second hollow shafts, and an external radial projection arranged in an intermediate position, and an external radial projection arranged in an intermediate position along the drive shaft between the first and second clutch portions. 115-. (canceled)16. A gearbox comprising: a first casing; and', 'a first hollow shaft;, 'a main unit comprising a second casing; and', 'a second hollow shaft;, 'a second unit comprisinga drive shaft comprising a first clutch portion and a second clutch portion, which engages the first and second hollow shafts, respectively, in an angularly fixed and axially slidable manner; and an axial shoulder supported in a fixed position by an axial end of one of the first or second hollow shafts and faces the other of the first and second hollow shafts; and', 'an external radial projection arranged in an intermediate position along the drive shaft between the first and second clutch portions;, 'an axial retaining device to prevent the drive shaft from translating axially in at least one direction, the axial retaining device being releasable and comprisingwherein the external radial projection axially faces the axial shoulder so as to prevent the drive shaft from translating axially towards the axial end.17. The gearbox of claim 16 , further comprising an annular shell provided between and joining the first and second casings to access the axial end and release the axial retaining device.18. The gearbox of wherein the annular shell is openable or removeable.19. The ...

GAS TURBINE ENGINE

A gas turbine engine comprising a casing, a bonding patch () bonded to a surface of the casing, and a liner attached to the bonding patch. The bonding patch () comprising a bonding region () configured to receive an adhesive for bonding the patch () to a surface. A plurality of de-bonding elements () is configured to be movable relative to the bonding region () in response to an energising signal. 1. A gas turbine engine comprising:a casing, a bonding patch bonded to a surface of the casing, and a liner attached to the bonding patch, the bonding patch comprising:a bonding region configured to receive an adhesive for bonding the patch to a surface;a plurality of de-bonding elements configured to be movable relative to the bonding region in response to an energising signal.2. The gas turbine engine according to claim 1 , wherein the de-bonding elements are configured to vibrate in response to the energising signal.3. The gas turbine engine according to claim 1 , wherein the energising signal is an electrical signal or a sound wave.4. The gas turbine engine according to claim 3 , wherein the frequency of the energising signal is in the ultrasonic range.5. The gas turbine engine according to claim 1 , wherein the de-bonding elements include one or more transducers configured to be movable relative to the bonding region in response to the energising signal.6. The gas turbine engine according to claim 5 , wherein the one or more transducers includes one or more piezoelectric transducers configured to be suppliable with an electrical signal suitable for causing the one or more piezoelectric transducers to move relative the bonding region.7. The gas turbine engine according to claim 1 , comprising a first group of de-bonding elements and a respective second group of de-bonding elements claim 1 , wherein the de-bonding elements of the first group are configured to move resonantly in response to a first energising signal of a first frequency claim 1 , and wherein the de- ...

APPARATUS FOR AN ASSEMBLY TOOL FOR MOUNTING OR DISMANTLING, REPLACEMENT AND MAINTENANCE OF A COMPONENT OF AN ENGINE

The present invention concerns of an apparatus as a part of an assembly tool or an assembly tool with additional frame for mounting or dismantling, replacement and maintenance of a component of an engine. The apparatus includes an eccentric hook having means to adjust, discretely or operatively communicating with a crane or an independently operated assembly tool. The position of the component operates in radial or quasi-radial position with respect to the engine housing, whereas the eccentric hook comprising an outer structure/casing, an inner ring, a cut out with an eccentric disposition, whereas the eccentric hook is self-locking or semi-self-locking with respect to a counterpart attached to the engine housing. 1100. An apparatus as a part of an assembly tool or an assembly tool with additional frame for mounting or dismantling , replacement and maintenance of a component of an engine , characterized in that the apparatus comprising an eccentric hook having means to adjust , discretely or operatively communicating with a crane or other transport means the position of the component in radial or quasi-radial position with respect to the engine housing , whereas the eccentric hook () comprising an outer structure/casing , an inner ring , a cut out with an eccentric deployment , whereas the eccentric hook is self-locking or semi-self-locking with respect to a counterpart attached to the engine housing.2. The apparatus according to claim 1 , wherein the outer structure/casing is movable/turnable while the inner ring behaves stationary or the inner ring is movable/turnable while the outer structure/casing behaves stationary.3. The apparatus according to claim 1 , wherein the eccentric rolling hook is driven by electrical means or a worm gear.4. The apparatus according to claim 1 , wherein the counterpart is bolted to a machined surface of the engine housing.5. The apparatus according to claim 1 , wherein the first designed assembly tool comprising the operational ...

Tool and method for frontal unscrewing of a link nut in a twin-spool turbine

A method for unscrewing a link nut of an HP rotor of a twin-spool turbine, including a front fan, an intermediate casing, a HP module with a HP rotor, and a LP turbine module, the intermediate casing including a support bearing for the HP rotor, the rotor being retained in the bearing by the link nut, the method including: placing an unscrewing tool in front of the link nut after having removed the fan and released access to the nut from the front; with rotation of the HP rotor locked and the frontal unscrewing tool including a socket spanner including teeth having a shape that complements that of teeth of the link nut, attaching a mounting for the socket spanner to the intermediate casing, the socket spanner being rotatably mounted on the mounting, and applying an unscrewing torque to the socket spanner. An unscrewing tool implements the method.

APPARATUS FOR HANDLING A TURBOMACHINE PART

An apparatus for handling a turbomachine part, particularly during disassembling and reassembling operations. More specifically, an apparatus for handling the stator cone of a gas turbine suitable to completely manipulate the stator cone during disassembling and reassembling operations. The apparatus allows to disassemble and reassemble the stator cone of a gas turbine without the need to dismount the turbomachine enclosure and without the necessity to have personnel inside the turbomachine package during the operations. 1. A handling apparatus for removing and repositioning a part of a turbomachine from/into its operative seat , the turbomachine having a longitudinal axis , the apparatus comprising:a base structure comprising a guide element developing along a longitudinal direction; and wherein, in an operative condition of the handling apparatus, the longitudinal direction of the guide element is arranged parallel to the longitudinal axis of the turbomachine, the main body comprising a gripping device configured to be connectable to the turbomachine part;', 'wherein the gripping device is pivotable at least about a transversal horizontal axis, and is also movable at least along a vertical direction, the rotation about the transversal horizontal axis and the movement along the vertical direction of the gripping device being obtained by means of a plurality of actuators., 'a main body movable along the guide element;'}2. The handling apparatus according to claim 1 , wherein the gripping device is configured to pivot the connectable turbomachine part about the transversal axis with respect to the base structure.3. The handling apparatus according to claim 1 , wherein the gripping device is configured to move the connectable turbomachine part along the vertical direction with respect to the base structure.4. The handling apparatus according to claim 1 , wherein the gripping device is further pivotable about a vertical axis.5. The handling apparatus according to claim ...

METHOD FOR ASSEMBLING AND DISASSEMBLING A TURBINE RING ASSEMBLY

A method for assembling/disassembling a turbine ring assembly including a turbine ring of ceramic matrix composite material and a ring support structure of metal equipped with a central shroud and with at least one single-piece annular plate positioned upstream of the ring with respect to the direction of an air flow passing through the assembly, the plate having in the radial direction a first free end and a second end opposite to the first end, the second end being removably attached to the first radial flange and shrink-fit to the central shroud, is disclosed. The method for assembling/disassembling includes, before the assembling/disassembling of the plate, a step of deformation of the central shroud and/or of the at least one annular plate. 2. The method for assembling according to claim 1 , wherein the heating step is maintained until the temperature of the central shroud is greater than or equal to 30° C.3. (canceled)4. The method for assembling according to claim 1 , further comprising claim 1 , prior to the assembling of said at least one annular plate to the ring support structure claim 1 , a step of cooling said at least one annular plate in order to obtain a shrinkage of said at least one annular plate.5. The method for assembling according to claim 1 , wherein the assembling of the ring assembly is accomplished in the vertical position with respect to the ground claim 1 , the turbine ring and the ring support structure being positioned with the axial direction of the ring parallel to the vertical direction.6. A method for disassembling a turbine ring assembly comprising a turbine ring of ceramic matrix composite material and a ring support structure of metal equipped with a central shroud from which protrude a first and a second radial flange from which the ring is held claim 1 , and of at least one single-piece annular plate positioned upstream of the turbine ring and of the first radial flange with respect to the direction of an air flow intended to ...

FILTERING CHAMBER FOR GAS TURBINES AND METHOD OF MAINTENANCE THEREOF

A filter system for filtering intake air of a gas turbine, comprising a first filter arrangement and a second filter arrangement, located downstream from the first filter arrangement and having a higher collection efficiency than the first filter arrangement. Furthermore, a guard filter arrangement, having a lower collection efficiency than the first filter arrangement, is located between the first filter arrangement and the second filter arrangement. 1. A filter system for filtering intake air of a gas turbine , comprising:a first filter arrangement;a second filter arrangement, located downstream from the first filter arrangement and having a higher collection efficiency than the first filter arrangement;wherein a first guard filter arrangement, having a lower collection efficiency than the first filter arrangement, is located between the first filter arrangement and the second filter arrangement.2. The filter system of claim 1 , wherein the first filter arrangement is a self-cleaning filter arrangement.3. The filter system of claim 1 , wherein the first filter arrangement is a pulse jet filter arrangement.4. The filter system of claim 1 , wherein a flow disturber is located between the first filter arrangement and the first guard filter arrangement.5. The filter system of claim 1 , wherein a second guard filter arrangement claim 1 , having a collection efficiency lower than the second filter arrangement claim 1 , is located downstream from the second filter arrangement.6. The filter system of claim 1 , wherein: the first filter arrangement and the second filter arrangement are located in a filter chamber having an air inlet side and an air outlet side; the first filter arrangement divides the filter chamber into an upstream volume and a downstream volume; and the first guard filter is arranged in the downstream volume.7. The filter system of claim 6 , wherein the flow disturber is arranged in the downstream volume claim 6 , between the first filter arrangement and ...

METHOD FOR REMOVING A TURBOFAN ENGINE HEATING DEVICE

A method for removing a twin-spool turbine including a front fan, a HP module with a HP rotor, and a LP turbine module, an intermediate casing including a support bearing for the HP rotor, the HP rotor being retained in the bearing by a link nut, the method including inserting a tool for unscrewing the link nut after having released access to the link nut, and preheating the link nut before starting the unscrewing tool. 110-. (canceled)11. A method for dismantling a twin-spool turbofan including a front fan , a HP module including a HP rotor , a LP turbine module , an intermediate casing including a bearing for supporting the HP rotor , the HP rotor being retained in the bearing by a connecting nut , the method comprising:introducing a tool for unscrewing the connecting nut once access to the connecting nut has been cleared;heating, beforehand, the connecting nut before engaging the unscrewing tool.12. The method as claimed in claim 11 , wherein claim 11 , once the LP turbine module claim 11 , with its shaft claim 11 , has been removed claim 11 , a tubular heating means is introduced from behind into the central space left free by the LP turbine module claim 11 , along the axis of the engine claim 11 , and the connecting nut is heated from inside.13. The method as claimed in claim 11 , further comprising claim 11 , after heating the connecting nut claim 11 , introducing a rear unscrewing tool comprising a tube and a plurality of fingers which are retractable between a position in which they are housed within the tube and a position in which they are deployed radially to come into contact with teeth of the connecting nut.14. The method as claimed in claim 13 , wherein an unscrewing torque is applied to the tool claim 13 , the torque being maintained at a value below that at which forces on the teeth would risk damaging them.15. The method as claimed in claim 11 , further comprising removing the fan to free up the connecting nut in a forward direction and putting in ...

AIRFOIL MATERIAL REMOVAL

A method of removing material from an airfoil includes engaging a root of the airfoil within a root-securing fixture, engaging a tip of the airfoil within a tip-securing fixture, and removing material from the airfoil. The method further includes disengaging the tip of the airfoil from the tip-securing fixture to allow movement of the tip from a clamped state position to a free-state position. The method further includes reengaging the tip of the airfoil within the tip-securing fixture in the free-state position, and removing additional material from the airfoil. 1. A method of removing material from an airfoil , the method comprising:engaging a root of the airfoil within a root-securing fixture;engaging a tip of the airfoil within a tip-securing fixture;removing material from the airfoil;disengaging the tip of the airfoil from the tip-securing fixture to allow movement of the tip from a clamped state position to a free-state position;reengaging the tip of the airfoil within the tip-securing fixture in the free-state position; andremoving additional material from the airfoil.2. The method of claim 1 ,wherein engaging the tip of the airfoil within the tip-securing fixture comprises engaging each of a plurality of tabs extending from a radially outer edge of the tip of the airfoil within the tip-securing fixture; andwherein disengaging the tip of the airfoil from the tip-securing fixture comprises disengaging each of the plurality of tabs from the tip-securing fixture.3. The method of claim 2 ,wherein the plurality of tabs comprises a leading edge tab proximate a leading edge of the airfoil, a trailing edge tab proximate a trailing edge of the airfoil, and a center tab disposed between the leading edge tab and the trailing edge tab, the center tab having a bore extending radially inward from a radially outer side of the center tab;wherein the tip-securing fixture comprises a leading edge clamping assembly configured to be selectively engageable and disengageable from ...

APPARATUS FOR CIRCUMFERENTIAL SEPARATION OF TURBINE BLADES

Embodiments of the present disclosure can provide an apparatus for circumferentially separating turbine blades. An apparatus according to the present disclosure may include: a length-adjustable elongate member having opposing first and second ends; a first clasp coupled to the first end of the length-adjustable elongate member, the first clasp shaped to at least partially engage an airfoil profile of a first turbine blade positioned circumferentially adjacent to a dovetail slot, relative to a centerline axis of the turbomachine; and a second clasp coupled to the second end of the length-adjustable elongate member, the second clasp shaped to at least partially engage an airfoil profile of a second turbine blade circumferentially positioned adjacent to the dovetail slot, the first and second turbine blades being circumferentially adjacent to the dovetail slot at opposing circumferential ends thereof. 1. An apparatus for circumferentially separating turbine blades , the apparatus comprising:a length-adjustable elongate member having opposing first and second ends;a first clasp coupled to the first end of the length-adjustable elongate member, the first clasp shaped to at least partially engage an airfoil profile of a first turbine blade positioned circumferentially adjacent to a dovetail slot, relative to a centerline axis of the turbomachine; anda second clasp coupled to the second end of the length-adjustable elongate member, the second clasp shaped to at least partially engage an airfoil profile of a second turbine blade circumferentially positioned adjacent to the dovetail slot, the first and second turbine blades being circumferentially adjacent to the dovetail slot at opposing circumferential ends thereof.2. The apparatus of claim 1 , wherein the first clasp and the second clasp are each rotatably coupled to one of the first or second end of the length-adjustable elongate member such that each of the first and second clasps are configured to rotate about the ...

DEVICE AND METHOD FOR MOUNTING OR DISMANTLING, REPLACEMENT AND MAINTENANCE OF A CAN-COMBUSTOR

The present invention concerning of a device for mounting or dismantling, replacement and maintenance of a can-combustor of a gas turbine engine including an assembly tool or assembly tool with additional frame having at least one lifting beam, at least one linear driver, wheels, at least one eccentric rolling hook for fixation of the gas turbine housing, optionally spacers for building the interface to the can-combustor, adapters, lifting points for the main crane. The eccentric rolling hook is connected to the gas turbine housing by giving in axial or quasi-axial direction a force for mounting or dismantling the can-combustor from the gas turbine housing. 1. A device for mounting or dismantling , replacement and maintenance of a can-combustor of a gas turbine engine comprising an assembly tool or assembly tool with additional frame having at least one lifting beam , at least one linear driver , wheels , at least one eccentric rolling hook for fixation of the gas turbine housing , optionally spacers for building the interface to the can-combustor , adapters , lifting points for the main crane , wherein the eccentric rolling hook is connected to the gas turbine housing by giving in axial or quasi-axial direction a force for mounting or dismantling the can-combustor from the gas turbine housing.2. The device according to claim 1 , wherein the outer structure/casing is movable/turnable and the inner ring behaves stationary claim 1 , or the inner ring is movable/turnable and the outer structure/casing behaves stationary.3. The device according to claim 1 , wherein the eccentric rolling hook having means to adjust claim 1 , discretely or operatively communicating with the crane claim 1 , the position of the can-combustor in radial or quasi-radial position.4. The device according to claim 1 , wherein the eccentric rolling hook is driven by electrical means or a worm gear.5. The device according to claim 1 , wherein the eccentric rolling hook is self-locking with respect ...

Gas turbine

A gas turbine comprises a strut assembly including an inner ring; an inclined member including a first end connected to the inner ring, a second end positioned opposite the first end, and a flange extending radially inward from the second end; an oil sump mounted to the second end or the flange; a thrust bearing fixed to the oil sump; and a thrust collar extending radially from a rotor, wherein the inclined member has an aperture portion formed therein, the aperture portion is positioned in an upper portion of a region between the thrust bearing and a journal bearing, and the aperture portion has a width and a circumferential length greater than at least the journal bearing. The gas turbine has the feature that the journal bearing is easily withdrawn and the total weight of the gas turbine is reduced.

ATR FULL RING SLIDING NACELLE

A gas turbine engine includes a core, a first annular portion, a rail, and a second annular portion. The first annular portion is stationary and adapted for partially surrounding an engine core. The first annular portion includes a fore pylon connecting portion, and a fore bi-fi. The rail is coupled to the fore pylon portion and extending in the aft direction from the stationary portion. The second annular portion is arranged aft of the first portion and coupled to the rail. The second annular portion is movable along an engine core centerline between a closed position and at least one open position. The second annular portion comprises an aft bi-fi configured to engage with the fore bi-fi when the gas turbine engine is in the closed position. 1. A gas turbine engine comprising: a fore pylon connecting portion; and', 'a fore bi-fi;, 'a first annular portion that is stationary and adapted for partially surrounding an engine core, wherein the first annular portion includesa rail coupled to the fore pylon portion and extending in the aft direction from the stationary portion; anda second annular portion, aft of the first portion and coupled to the rail, the second annular portion being movable along an engine core centerline between a closed position and at least one open position, wherein the second annular portion comprises an aft bi-fi configured to engage with the fore bi-fi when the gas turbine engine is in the closed position.2. The gas turbine engine of claim 1 , wherein the fore bi-fi and the aft bi-fi are configured to enclose a plurality of external core features in the closed position.3. The gas turbine engine of claim 3 , wherein the fore bi-fi and the aft bi-fi are disengaged to allow access to a plurality of external core features in a partially open position.4. The gas turbine engine of claim 1 , wherein the first annular portion and the second annular portion are separated by a distance sufficient to allow removal of the engine core when the second ...

INTEGRATED NOZZLE AND PLUG

A gas turbine engine includes a first annular portion that is stationary and adapted for partially surrounding an engine core. The first annular portion includes a fore pylon connecting portion. A rail is coupled to the fore pylon portion and extends in the aft direction from the stationary portion. A second annular portion is positioned aft of the first portion and coupled to the rail, the second portion being movable along an engine core centerline between a closed position and an open position, wherein the second annular portion is configured to engage with the first annular portion in the closed position to provide access to an engine core. The second annular portion includes a nozzle plug. 1. A gas turbine engine comprising:a first annular portion that is stationary and adapted for partially surrounding an engine core, the first annular portion including a fore pylon connecting portion;a rail coupled to the fore pylon portion and extending in the aft direction from the stationary portion; anda second annular portion, aft of the first portion and coupled to the rail, the second portion being movable along an engine core centerline between a closed position and an open position, wherein the second annular portion is configured to engage with the first annular portion in the closed position to provide access to an engine core, the second annular portion including a nozzle plug.2. The gas turbine engine of claim 1 , wherein the nozzle plug is arranged directly adjacent to the aft end of the engine core when the second annular portion is in the closed position.3. The gas turbine engine of claim 1 , wherein the second annular portion is configured to allow removal of the core when the second annular portion is arranged in a fully open position.4. The gas turbine engine of claim 1 , wherein the core further comprises a turbine exhaust case.5. The gas turbine engine of claim 4 , and further comprising:an inner seal configured to connect the nozzle plug and the core; ...

Turboshaft engine mountable in a reduction gearbox

A turboshaft engine for a helicopter, comprising a case inside which a gas generator and a turbine are accommodated, the turbine being mounted on a power shaft that extends along a longitudinal direction. The turboshaft engine further comprises means for removably mounting the power shaft into a reduction gearbox inside which at least one gear of a first reduction stage is accommodated. The means for removably mounting the power shaft include a pinion having a central bore, the shape of which is adapted to that of the power shaft in such a way that the pinion can slide over the power shaft; furthermore, the contour of the pinion is adapted to the shape of the gear of the first stage in such a way that the pinion can form a leading input pinion of the gearbox in said gear once the power shaft has been mounted in the reduction gearbox.

TURBINE BLADE REMOVAL TOOL AND METHOD THEREOF

An apparatus for removing a turbine blade, the apparatus including a main body having a front plate including at least one securing opening for receiving a securing bolt, a rear plate having a fixture groove, and first and second side plates, and a base block configured to slide along the fixture groove of the rear plate. 1. An apparatus for removing a turbine blade , the apparatus comprising: a front plate including at least one securing opening for receiving a securing bolt;', 'a rear plate having a fixture groove; and', 'first and second side plates; and, 'a main body includinga base block configured to slide along the fixture groove of the rear plate.2. The apparatus for removing a turbine blade according to claim 1 , whereinthe base block includes a rear side configured to receive a sliding bolt,the fixture groove includes a groove opening, andthe sliding bolt is received in the rear side of the base block through the grove opening.3. The apparatus for removing a turbine blade according to claim 2 , wherein the base block includes a front side with an incline surface.4. The apparatus for removing a turbine blade according to claim 3 , further comprises:a pusher block that includes a mounting pocket.5. The apparatus for removing a turbine blade according to claim 4 , further comprises:a ram having an actuated state and a non-actuated state, said ram including: a mounting end; a base portion; an extending arm; a pushing end; and an input valve, wherein in the actuated state the extending arm protrudes from the base portion.6. The apparatus for removing a turbine blade according to claim 5 , wherein the front plate includes an elongated opening.7. The apparatus for removing a turbine blade according to claim 5 , wherein the ram is mounted on the base block by positioning the mounting end of the ram on the incline surface of the front side of the base block.8. The apparatus for removing a turbine blade according to claim 7 , wherein the pushing end of the ram is ...

ASSEMBLY/DISASSEMBLY APPARATUS FOR FLANGED MECHANICAL DEVICE AND ASSEMBLY/DISASSEMBLY METHOD FOR FLANGED MECHANICAL DEVICES

An assembly/disassembly apparatus for flanged mechanical device comprising: a main body provided with a rear abutment sector having at least a seat; a coupling pin housed in part in the seat and extending from the seat in a first direction; a grabbing device coupled to said main body; an engagement mechanism provided at least by a first and a second retaining arm, said first and second retaining arms being movable together at least between a first and a second positions, in which, in said first position the first retaining arm faces the rear abutment sector while in said second position the second retaining arm faces the rear abutment sector. 1. An assembly/disassembly apparatus for flanged mechanical device , the apparatus comprising:a main body comprising with a rear abutment sector having at least a seat,a coupling pin housed in part in the seat and extending from the seat in a first direction,a grabbing device coupled to said main body,an engagement mechanism comprising at least a first and a second retaining arm, said first and second retaining arms being movable together at least between a first and a second positions, in which, in said first position the first retaining arm faces the rear abutment sector while in said second position the second retaining arm faces the rear abutment sector.2. The assembly/disassembly apparatus of claim 1 , wherein said first and a second retaining arm claim 1 , are movable together in a third safety position in which claim 1 , the first retaining arm partially faces the rear abutment sector and the second retaining arm partially faces the rear abutment sector.3. The assembly/disassembly apparatus of claim 1 , wherein the engagement mechanism comprises a coupling shaft rotatable coupled with said main body and extending from the latter in said first direction claim 1 , substantially parallel to the coupling pin claim 1 , said first and second retaining arms being fixedly coupled with said coupling shaft and extending in a ...

NOZZLE MAINTENANCE APPARATUS AND METHOD

Various embodiments include apparatuses for performing maintenance on a gas turbine (GT) nozzle, along with related methods. One apparatus can include: a nozzle engagement sled for releasably engaging the nozzle, the nozzle engagement sled including: a sled body; a locking member coupled with the sled body, the locking member sized to complement a slot in the nozzle; a sled slot within a side of the sled body, the sled slot for engaging a rail within the GT; and at least one wheel for transporting the sled body within the GT. 1. An apparatus for performing maintenance on a nozzle of a gas turbine (GT) , the apparatus comprising: a sled body;', 'a locking member coupled with the body, the locking member sized to complement a slot in the nozzle;', 'a sled slot within a side of the body, the sled slot for engaging a rail within the GT; and', 'at least one wheel for transporting the sled body within the GT., 'a nozzle engagement sled for releasably engaging the nozzle, the nozzle engagement sled including2. The apparatus of claim 1 , further comprising a towing system coupled with the nozzle engagement sled claim 1 , the towing system for at least one of raising or lowering the nozzle engagement sled within the GT.3. The apparatus of claim 2 , wherein the nozzle engagement sled further includes a coupler for connecting with the towing system.4. The apparatus of claim 3 , wherein the coupler includes at least one of a hook claim 3 , a loop or a slot sized to engage the towing system.5. The apparatus of claim 3 , wherein the towing system includes at least one of a line or a bar sized to engage the coupler.6. The apparatus of claim 3 , wherein the nozzle engagement sled further includes a lever connected with the locking member for actuating the locking member.7. The apparatus of claim 6 , wherein the lever is located on a side of the sled body adjacent the coupler.8. The apparatus of claim 6 , further comprising an actuator rod for engaging the lever.9. The apparatus of ...

DIFFUSER REMOVAL TOOL

A diffuser removal tool for displacing an exhaust diffuser from a gas turbine engine is provided, which includes a pair of support arms, a clamp and wedge assembly coupled to an exhaust diffuser, and a lead screw assembly coupled between the support arms and to the clamp and wedge assembly via a wedge of the clamp and wedge assembly. The tool also includes a pair of linear bearing assemblies coupled to the support arms and to the clamp and wedge assembly via wedges of the clamp and wedge assembly. The lead screw assembly is configured to displace the diffuser in an axial direction relative to a longitudinal axis of the gas turbine engine while the linear bearing assemblies are configured to both enable the displacement of the diffuser in the axial direction while vertically supporting the diffuser to maintain alignment between the diffuser and the gas turbine engine. 1. A system , comprising:a gas turbine engine comprising an exhaust diffuser;an exhaust collector coupled to the exhaust diffuser, wherein the exhaust diffuser is partially disposed within the exhaust collector; anda diffuser removal tool configured to couple to both the exhaust collector and the exhaust diffuser and to separate the exhaust diffuser from the gas turbine engine by displacing the exhaust diffuser further into the exhaust collector in an axial direction relative to a longitudinal axis of the gas turbine engine while vertically supporting the exhaust diffuser to maintain axial alignment between the exhaust diffuser and the gas turbine engine.2. The system of claim 1 , comprising: a compressor claim 1 , a combustor section claim 1 , and a turbine.3. The system of claim 1 , wherein the diffuser removal tool comprises a clamp and wedge assembly coupled to the exhaust diffuser claim 1 , wherein the clamp and wedge assembly comprises a plurality of wedges and a clamp claim 1 , the clamp is circumferentially disposed relative to the longitudinal axis about the exhaust diffuser claim 1 , and the ...

SYSTEM AND METHOD FOR REMOVING STATOR VANES FROM A CASING OF A ROTARY MACHINE

A stator vane removal system includes a reaction platform configured to couple between opposing sides of a slot defined in an inner surface of a casing of a rotary machine. At least one stator vane is retained in the slot. The reaction platform includes at least one wedge surface. The system also includes an actuator configured to couple to the reaction platform. The at least one wedge surface facilitates inducing a coupling force exerted by the reaction platform to the opposing sides of the slot when the actuator applies a pushing force to the at least one stator vane in the slot. 1. A stator vane removal system comprising:a reaction platform configured to couple between opposing sides of a slot defined in an inner surface of a casing of a rotary machine, wherein at least one stator vane is retained in the slot, said reaction platform comprises at least one wedge surface; andan actuator configured to couple to said reaction platform, said at least one wedge surface facilitates inducing a coupling force exerted by said reaction platform to the opposing sides of the slot when said actuator applies a pushing force to the at least one stator vane in the slot.2. The system according to claim 1 , wherein said reaction platform comprises a block and a sleeve slidably coupled to said block.3. The system according to claim 2 , wherein said block comprises a first bearing surface configured to couple to a first of the opposing sides of the slot claim 2 , and said sleeve comprises a second bearing surface configured to couple to a second of the opposing sides of the slot.4. The system according to claim 3 , wherein said block further comprises a reaction surface configured to couple to said actuator claim 3 , said reaction surface is generally perpendicular to said first bearing surface.5. The system according to claim 4 , wherein said at least one wedge surface includes a block wedge surface of said block and a sleeve wedge surface of said sleeve claim 4 , said sleeve wedge ...

TOOL AND METHOD FOR DISASSEMBLING AND MOVING A TRV-TYPE TURBINE CASING OF AN AIRCRAFT TURBINE ENGINE

A TRV-type turbine casing includes inner and outer annular shrouds that extend one inside the other and about the same axis and are connected together by arms. A tool for disassembling and moving the casing has a lower carriage for moving the tool, and an upper plate to be attached to the turbine casing. The plate is supported by the carriage and includes first members that cooperate with a first annular flange of one of the shrouds to support the casing and axially immobilize the casing relative to the tool. The plate further includes second members that cooperate with a second annular flange of the other shroud in order to prevent and/or guide the rotation of the casing about the axis. 1. A tool for disassembling and moving a TRV-type turbine casing of an aircraft turbine engine , the turbine casing comprising internal and external annular shells , which extend one inside the other and around a same axis and are connected together by arms , the tool comprising:a lower carriage configured to move the tool, andan upper plate configured to be fastened to the turbine casing the plate being supported by the carriage and comprising first members configured to cooperate with a first annular flange of one of the shells to support the casing and axially immobilize same with respect to the tool, and second members configured to cooperate with a second annular flange of the other of the shells to rotatably guide and/or block the casing about said axis,wherein the first members comprise hooks which are each connected to a knob and movable by the knob from a first unlocking position to a second position that locks and immobilizes the casing.2. The tool according to claim 1 , wherein the first members are supported by a ring sector of the upper plate claim 1 , the ring sector being configured to be applied axially to the first flange.3. The tool according to claim 1 , wherein each hook is L-shaped and comprises a first branch parallel to said axis and configured to be engaged ...

DEVICE FOR UNCOUPLING FIRST AND SECOND PARTS OF A TURBINE ENGINE

Device for uncoupling first and second parts of a turbine engine, the parts extending around an axis A, wherein the first part comprises an annular row of axial through-openings that extend around the axis A, and in that the second part comprises an annular row of axial fusible lugs that pass axially through the openings and include threaded portions onto which a nut having the axis A and intended for axially clamping the parts is screwed. 1. A device for uncoupling first and second parts of a turbine engine , said parts extending around an axis A , wherein said first part comprises an annular row of axial through-openings that extend around the axis A , and in that said second part comprises an annular row of axial fusible lugs that pass axially through said openings and include threaded portions onto which a nut having the axis A and intended for axially clamping the parts is screwed.2. The device according to claim 1 , wherein the first part comprises a radially outer annular wall for axially bearing the second part and including said row of openings.3. The device according to claim 1 , wherein each of said openings is generally elongate in the circumferential direction around the axis A.4. The device according to claim 1 , wherein the second part comprises a radial surface or wall for axially bearing on said first part claim 1 , said lugs axially projecting from said radial surface or wall.5. The device according to claim 1 , wherein each of said lugs comprises a free end portion which carries one of said threaded portions and which is connected by a fusible connection portion to the rest of said second part.6. The device according to claim 5 , wherein said fusible connection portion comprises a thinning.7. The device according to claim 5 , wherein said free end portion comprises said threaded portion on its outer periphery.8. The device according to claim 1 , wherein said lugs are integrally formed with said second part.9. The device according to claim 1 , ...

Gas turbine and method for replacing bearing thereof

A gas turbine and a method for replacing a bearing thereof to easily adjust a clearance of a bearing housing and a bearing covering a tie rod, such that the bearing can be easily replaced is disclosed.

Method for mounting or dismounting turbine component, device for executing the method, and method for installing the device

A hanging device of a component of a turbine includes: a bridge member that bridges upper ends of a pair of side wall plates facing each other with the turbine interposed therebetween, among plates which constitute an enclosure surrounding an outer periphery of the turbine, and has a traveling path; and a hanging tool that hangs the component of the turbine and travels along the traveling path.

Tool and Method for Removing Fan Blades

A fan decoupling apparatus for removing fan blades from a shaft includes a hub cover and an attachment removably connected to the hub cover. The hub cover includes a hub end to interface with a hub of the fan blades; a hub cover quick-locking end opposite the hub end; a hub cover axial hole extending from the hub end to the hub cover quick-locking end; and a non-threaded hub cover radial hole extending from the hub cover axial hole to an outer surface of the hub cover. The attachment includes an attachment quick-locking end to removably connect to the hub cover quick-locking end; a receiving end opposite the attachment quick-locking end; and an attachment axial hole extending from the attachment quick-locking end to the receiving end, the attachment axial hole including a threaded portion nearer the receiving end than the attachment quick-locking end. 1. A fan removal tool kit comprising: a hub end configured to at least partially surround a hub of a fan;', 'an attachment connection end opposite the hub end;', 'a hub cover axial hole defined in the hub cover and extending from the hub end to the attachment connection end; and', 'at least one radial hole defined in the hub cover nearer to the hub end than the attachment connection end and extending from the hub cover axial hole to an outer surface of the hub cover, wherein the at least one radial hole is configured to receive a set screw;, 'a hub cover including a head proximal end removably connectable to the attachment connection end of the hub cover;', 'a receiving end opposite the head proximal end; and', 'a head axial hole defined in the head and extending from the head proximal end to the receiving end, wherein the head axial hole is configured to receive an elongate member; and, 'a head connectable to the hub cover in a first arrangement, the head including a hub cover connection end removably connectable to the attachment connection end of the hub cover;', 'a head connection end opposite the hub cover ...

METHODS FOR SEPARATING ROTOR BLADE CUFFS FROM ROTOR BLADE BODIES

A rotor blade disassembly method includes applying spanwise support to a rotor blade body and heating a bond disposed on an end of the rotor blade body. The method also includes removing the spanwise support from the rotor blade body and exerting shear stress on the bond using weight of the rotor blade body. A blade disassembly system is also described. 1. A rotor blade disassembly system , comprising:a rotor blade cradle movable between continuous and cantilevered support positions;a blade cuff heater element disposed on an end of the cradle;a withdrawal mechanism operably connected to the support cradle; anda blade cuff seat fixed relative to the blade cradle, wherein the blade cuff heater element is connected to the blade cuff seat to apply heat to the blade cuff when the rotor blade cradle is in continuous support positions.2. A rotor blade disassembly system as recited in claim 1 , wherein the blade cradle includes an inboard support claim 1 , an outboard support claim 1 , and a mid-span interposed between the inboard support and the outboard support; wherein the blade cuff seat is disposed on a side of the inboard support opposite the mid-span support.3. A rotor blade disassembly system as recited in claim 1 , wherein the cantilevered support position is disposed between below the continuous support position relative to the direction of gravity.4. A rotor blade disassembly system as recited in claim 1 , further comprising a root plate cover configured to seat over an inboard end of a rotor blade body.5. A rotor blade disassembly system as recited in claim 4 , wherein the root plate cover has a semicircular profile.6. A rotor blade disassembly system as recited in claim 1 , further including a ram movable along an axis that is orthogonal relative to a withdrawal axis of the blade cradle.7. A rotor blade disassembly system as recited in claim 1 , wherein the blade cuff seat includes an anti-rotation feature. This application is a divisional of U.S. application ...

Turbine rotor locking assembly and method

A power turbine rotor locking assembly including a rotor shaft. The assembly also includes an aft rotor stage surrounding the rotor shaft. The assembly further includes a locknut torqued to the rotor shaft. The assembly yet further includes a plurality of torque resistance features located on an aft side of the aft rotor stage. The assembly also includes a tooling fixture having a plurality of corresponding torque resistance features, the corresponding torque resistance features selectively engageable with the torque resistance features of the aft rotor stage to resist circumferential movement during assembly and disassembly of the locknut with the rotor shaft.

INSTALLATION OR REMOVAL OF TURBINE BLADE AT TURBINE BLADE BASE

Embodiments of the present disclosure relate to the installation or removal of turbine blades at a turbine blade base thereof. An apparatus according to the present disclosure can include: an operative head configured to engage an axial sidewall of a turbine blade base; and a mount removably coupled to a portion of a turbomachine assembly by a coupler, wherein the operative head is slidably coupled to the mount such that the operative selectively engages the axial sidewall of the turbine blade base, and wherein the operative head is shaped to impart an axial and a circumferential force against the turbine blade base. 1. An apparatus for installation or removal of a turbine blade , the apparatus comprising:an operative head configured to engage an axial sidewall of a turbine blade base; anda mount removably coupled to a portion of a turbomachine assembly by a coupler, wherein the operative head is slidably coupled to the mount such that the operative selectively engages the axial sidewall of the turbine blade base, and wherein the operative head is shaped to impart an axial and a circumferential force against the turbine blade base.2. The apparatus of claim 1 , further comprising a vibrating assembly including a vibratory drive mechanism coupled to the operative head.3. The apparatus of claim 1 , wherein the operative head comprises a roller configured to rotate about an eccentric axis relative to the turbomachine assembly.4. The apparatus of claim 1 , wherein the operative head is further shaped to axially displace a turbine blade having an interlocking shroud profile.5. The apparatus of claim 1 , further comprising: atleast one lift member coupled to the mount; anda lash extending through the at least one lift member and coupled to the turbomachine assembly, such that the at least one lift member mechanically couples the mount to the turbomachine assembly through the lash.6. The apparatus of claim 1 , wherein the coupler comprises at least one hook configured to ...

Fan drive gear system module and inlet guide vane coupling mechanism

A gas turbine engine includes a fan that includes a plurality of fan blades rotatable about an axis. An on-wing portion includes a compressor section and a combustor that is in fluid communication with the compressor section. A turbine section is in fluid communication with the combustor. A core flow path is arranged within a core nacelle. The fan is arranged upstream from the core flow path. A fan drive gear system module is coupled to the turbine section for rotating the fan about the axis. A connector assembly including first and second members respectively is secured to the on-wing portion and the fan drive gear system module. The first and second members are removably secured to one another by radially extending fasteners. The first members are connected to an on-wing portion of the gas turbine engine and the second members are connected to the fan drive gear system module. The fasteners are accessible through the bypass flow path.

TEMPORARY POST MAINTENANCE OIL FILTER FOR GAS-TURBINE ENGINE

A method of maintaining a gas-turbine engine is provided. The method includes the steps of removing a conduit from the gas-turbine engine, installing a temporary oil filter in place of the conduit in the gas-turbine engine, and starting the gas-turbine engine with the temporary oil filter installed. A fan-drive gear system is also provided and comprises a journal bearing, a main oil pump fluidly coupled to the journal bearing, a main oil filter fluidly coupled between the journal bearing and the main oil pump, and an auxiliary oil pump fluidly coupled to the journal bearing. The auxiliary oil pump may be configured to supply oil to the journal bearing on startup. An auxiliary oil filter may also be installed between the auxiliary oil pump and the journal bearing. 1. A fan-drive gear system , comprising:a journal bearing;a main oil pump fluidly coupled to the journal bearing;a main oil filter fluidly coupled between the journal bearing and the main oil pump;an auxiliary oil pump fluidly coupled to the journal bearing, wherein the auxiliary oil pump is configured to supply oil to the journal bearing on startup; andan auxiliary oil filter installed between the auxiliary oil pump and the journal bearing.2. The fan-drive gear system of claim 1 , further comprising a substantially unobstructed conduit configured to replace the auxiliary oil filter. This application is a divisional application, and claims priority to and the benefit of U.S. Provisional Application No. 62/092,656, entitled “TEMPORARY POST MAINTENANCE OIL FILTER FOR GAS-TURBINE ENGINE,” filed on Dec. 16, 2014, and U.S. Non-Provisional application Ser. No. 14/855,854, filed on Sep. 16, 2015, both of which are hereby incorporated by reference in their entirety.The present disclosure relates to gas-turbine engines, and, more specifically, to a temporary oil filter for a gas-turbine engine.Gas-turbine engines comprise many moving parts. The moving parts often require lubrication in the form of oil. In particular ...

EXTRACTION DEVICE OF A PLATFORM FOR HOLDING A BLADE AND METHOD USING THIS DEVICE

An extraction device of a platform for holding a blade fitted with an upstream flange, out of a turbomachine rotor disc which includes a handle fitted with a radial annular shoulder extended by a threaded pin, a proximal ring and a distal ring which include a tube extended by a radial collar, and a sleeve, the proximal ring being arranged around the pin, the tapped distal ring being screwed onto the other end of the pin and the sleeve being arranged around the two rings between their respective collars, such that screwing of the handle results in moving the distal ring towards the proximal ring, radial deformation of the distal part of the sleeve against the flared part of the cylindrical orifice of the flange and its being joined to the latter, and that it is possible to conjointly extract said platform and the device from the disc. 1. An extraction device of a platform for holding a blade , out of a turbomachine rotor disc , said platform being fitted with an upstream flange having an orifice whereof the downstream part is flared , wherein the extraction device comprises:a handle having an opposite handling end and an engagement end, the engagement end being fitted with a radial annular shoulder which is extended by a threaded axial pin,a so-called “proximal” ring and a so-called “distal” ring, which each comprise a tube extended at one of its both ends by a radial collar which extends towards the exterior of said tube,and a sleeve,the proximal ring, whereof the inner tubular wall is smooth, being arranged around the proximal end of the pin, so that the collar of the proximal ring is against the annular shoulder of the manipulation handle, the distal ring, whereof the inner tubular wall is tapped being screwed around the distal end of the pin and arranged so that the collar of the distal ring is opposite the distal end of the pin, the sleeve being arranged around the two tubes of the two rings so that its two ends bear respectively against one and other of the two ...

SYSTEM AND METHOD FOR REMOVING STATOR VANES FROM A CASING OF A ROTARY MACHINE

A stator vane removal system includes a reaction platform configured to couple between opposing sides of a slot defined in an inner surface of a casing of a rotary machine. At least one stator vane is retained in the slot. The reaction platform includes at least one wedge surface. The system also includes an actuator configured to couple to the reaction platform. The at least one wedge surface facilitates inducing a coupling force exerted by the reaction platform to the opposing sides of the slot when the actuator applies a pushing force to the at least one stator vane in the slot. 1. A stator vane removal system comprising:a reaction platform configured to couple between opposing sides of a slot defined in an inner surface of a casing of a rotary machine, wherein at least one stator vane is retained in the slot, said reaction platform comprises at least one wedge surface; andan actuator configured to couple to said reaction platform, said at least one wedge surface facilitates inducing a coupling force exerted by said reaction platform to the opposing sides of the slot when said actuator applies a pushing force to the at least one stator vane in the slot.2. The system according to claim 1 , wherein said reaction platform comprises a block and a sleeve slidably coupled to said block.3. The system according to claim 2 , wherein said block comprises a first bearing surface configured to couple to a first of the opposing sides of the slot claim 2 , and said sleeve comprises a second bearing surface configured to couple to a second of the opposing sides of the slot.4. The system according to claim 3 , wherein said block further comprises a reaction surface configured to couple to said actuator claim 3 , said reaction surface is generally perpendicular to said first bearing surface.5. The system according to claim 4 , wherein said at least one wedge surface includes a block wedge surface of said block and a sleeve wedge surface of said sleeve claim 4 , said sleeve wedge ...

TURBINE SHROUD BLOCK REMOVAL APPARATUS

A turbine shroud block removal apparatus. In one embodiment, the apparatus includes a first base plate including a first armature. The first base plate may be releasably coupled to a first shroud block. The apparatus also may also include a second base plate including a second armature. The second base plate may be releasably coupled to a second shroud block positioned adjacent the first shroud block. Additionally, the apparatus may include an actuator coupled to the first armature of the first base plate and the second armature of the second base plate. The actuator may change a distance between the first shroud block and the second shroud block. 1. An apparatus comprising:a first base plate including a first armature, the first base plate for releasably coupling to a first shroud block;a second base plate including a second armature, the second base plate for releasably coupling to a second shroud block adjacent the first shroud block; andan actuator coupled to the first armature of the first base plate and the second armature of the second base plate, the actuator for changing a distance between the first shroud block and the second shroud block.2. The apparatus of claim 1 , wherein the first shroud block includes at least one hole extending through a side surface of the first shroud block claim 1 , andwherein the second shroud block includes at least one hole extending through a side surface of the second shroud block.3. The apparatus of claim 2 , wherein the side surface of the first shroud block is positioned adjacent the side surface of the second shroud block.4. The apparatus of claim 2 , wherein the first base plate includes at least one aperture claim 2 , the at least one aperture of the first base plate and the at least one hole of the first shroud block are configured to engage a releasable fastener for releasably coupling the first base plate to the first shroud block.5. The apparatus of claim 2 , wherein the second base plate includes at least one ...

HORIZONTAL ENGINE BUILD STAND

A horizontal support tool for an engine build stand, the horizontal support tool includes a support tube along an axis and a tie shaft between a handle and a puck assembly, said puck assembly including a puck selectively extendable and retractable transverse to the axis in response to rotation of the handle. A method of horizontally assembling a portion of a gas turbine engine including mounting a first module to an engine build stand; installing a horizontal support tool into the first module, the horizontal support tool supported in a spherical bearing supported by the engine build stand; and installing a second module to the first module, the horizontal support tool operable to at least partially support second module. 18-. (canceled)9. An engine build stand for a gas turbine engine , comprising:a support structure;a spherical bearing supported by the support structure;a horizontal support tool receivable within the spherical bearing, the horizontal support tool comprises a support tube along an axis, the support tube fits within rotational hardware of a gas turbine engine; anda tie shaft between a handle and a puck assembly, the puck assembly including a puck selectively extendable and retractable transverse to the axis through the support tube in response to rotation of the handle.10. The engine build stand as recited in claim 9 , wherein the horizontal support tool includes:a tie shaft between a handle and a puck assembly, the puck assembly including a puck selectively extendable and retractable transverse to the axis through the support tube in response to rotation of the handle.11. The engine build stand as recited in claim 10 , wherein the support tube is manufactured of a nonmetallic composite material.12. The engine build stand as recited in claim 10 , further comprising a turnbuckle to adjust a position of the horizontal support tool.13. The engine build stand as recited in claim 12 , further comprising a load cell to measure a weight applied to the ...

TURBINE MINIDISK BUMPER FOR GAS TURBINE ENGINE

An assembly for a gas turbine engine includes a minidisk that includes an axial extension extending from a disc. The axial extension includes an inner diameter surface and a recess arranged radially opposite the inner diameter surface. The recess provides a radially outwardly extending flange and a bumper extending radially inward from and proud of the inner diameter surface. A method of working on a gas turbine engine section includes inserting a tool into a cavity beneath a seal assembly, and engaging a flange of a minidisk with the tool to manipulate first and second rotors with respect to one another. 1. An assembly for a gas turbine engine comprising:a minidisk including an axial extension extending from a disc, the axial extension including an inner diameter surface and a recess arranged radially opposite the inner diameter surface, the recess providing a radially outwardly extending flange at an axially terminal end of the axial extension, and a bumper extending radially inward from and proud of the inner diameter surface, wherein the recess is axially elongated compared to a radial depth of the recess with respect to the flange.2. The assembly according to claim 1 , wherein the recess axially overlaps the bumper.3. The assembly according to claim 1 , comprising a turbine rotor having a hub claim 1 , the minidisk mounted on the hub claim 1 , and the hub operatively supported relative to an engine static structure by a bearing.4. The assembly according to claim 3 , comprising a seal assembly arranged between the minidisk and the bearing to create a bearing compartment.5. The assembly according to claim 4 , comprising a sleeve supported by the hub claim 4 , the bearing mounted to the sleeve.6. The assembly according to claim 5 , wherein the hub includes circumferentially spaced radially outwardly extending first tabs claim 5 , and the axial extension includes circumferentially spaced radially inwardly extending second tabs claim 5 , the first and second tabs ...

DISMANTLING DEVICE FOR BLADES AND CORRESPONDING DISMANTLING METHOD

A device for dismantling a blade from a turbine, the turbine including a set of blades, the device including: a holding element including a blocking surface; a dismantling opening; an attachment system configured to attach the holding element to a shaft of the turbine, the attachment system producing a pivot connection between the holding element and the shaft of the turbine, the defining of an angular position of the holding element allowing a first function of dismantling at least one blade facing the dismantling opening to be carried out and allowing a second function of blocking a set of blades facing the blocking surface to be carried out. 1. A device for dismantling at least one blade from a turbine , said turbine comprising a set of blades , said device comprising: a blocking surface;', 'a dismantling opening;, 'a holding element comprising'}an attachment system configured to attach the holding element to a shaft of the turbine, the attachment system producing a pivot connection between the holding element and the shaft of the turbine,a defining of an angular position of the holding element allowing a first function of dismantling at least one blade facing the dismantling opening and allowing a second function of blocking a set of blades facing the blocking surface.2. The dismantling device as claimed in claim 1 , wherein the dismantling opening is at a periphery of the holding element.3. The dismantling device as claimed in claim 1 , wherein the holding element comprises at least one access opening that allows an operator to access a zone of the space defined facing the blocking surface.4. The dismantling device as claimed in claim 1 , wherein the holding element is a ring.5. The dismantling device as claimed in claim 1 , wherein the attachment system comprises:a first ring;a second ring;a superposition of the first and second rings forming a circular groove for maintaining of the holding element and for driving in rotation the holding element with respect ...

TEMPORARY POST MAINTENANCE OIL FILTER FOR GAS-TURBINE ENGINE

A method of maintaining a gas-turbine engine is provided. The method includes the steps of removing a conduit from the gas-turbine engine, installing a temporary oil filter in place of the conduit in the gas-turbine engine, and starting the gas-turbine engine with the temporary oil filter installed. A fan-drive gear system is also provided and comprises a journal bearing, a main oil pump fluidly coupled to the journal bearing, a main oil filter fluidly coupled between the journal bearing and the main oil pump, and an auxiliary oil pump fluidly coupled to the journal bearing. The auxiliary oil pump may be configured to supply oil to the journal bearing on startup. An auxiliary oil filter may also be installed between the auxiliary oil pump and the journal bearing. 1. A method of maintaining a gas-turbine engine , comprising:removing an oil conduit from the gas-turbine engine;installing a temporary oil filter in place of the oil conduit in the gas-turbine engine; andstarting the gas-turbine engine with the temporary oil filter installed.2. The method of claim 1 , further comprising stopping the gas-turbine engine with the temporary oil filter installed.3. The method of claim 2 , further comprising removing the temporary oil filter after starting and stopping the gas-turbine engine.4. The method of claim 3 , further comprising reinstalling the oil conduit in place of the temporary oil filter in the gas-turbine engine.5. The method of claim 4 , wherein the temporary oil filter is installed between an auxiliary oil pump and a fan-drive gear system.6. The method of claim 1 , further comprising removing a panel to provide access to the oil conduit.7. The method of claim 1 , further comprising:decoupling a retention hardware from the oil conduit; andcoupling the retention hardware to the temporary oil filter.8. The method of claim 1 , further comprising;decoupling the oil conduit from an interface with a journal supply line; andcoupling the temporary oil filter to the ...

GEARBOX AND DISASSEMBLY METHOD FOR DISENGAGING A DRIVE SHAFT IN SUCH A GEARBOX

A gearbox () has a main unit () and a secondary unit () provided with respective casings () of respective gear transmissions and with respective hollow shafts () connected by means of a drive shaft (); the secondary unit transfers motion between two axes forming an angle of less than 180° and which can be removed after having released the drive shaft (); the drive shaft () is engaged in an angularly fixed and axially sliding manner to the hollow shafts and is axially locked, at least in one direction, by means of an axial retaining device (), which is releasable; the axial retaining device () is coupled to one () of the hollow shafts, at an axial end () which is facing towards the other () of the hollow shafts; at least one opening may be formed between the two casings (), so as to access such an axial end () and release the axial retaining device. 2565353. Gearbox according to claim 1 , characterized in that the profiles in circumferential direction of said external radial projection () and of said axial shoulder () are shaped so as to enable the drive shaft of sliding axially with respect to said axial shoulder () in both directions after a relative rotation.34453552532. Gearbox according to claim 2 , characterized in that said axial retaining means comprise a ring () claim 2 , which comprises said axial shoulder () claim 2 , is arranged around a first intermediate portion () of said drive shaft () and is releasably fixed to said axial end ().4445453. Gearbox according to claim 3 , characterized in that said ring () has a hole spline () defining said axial shoulder ().54432604432. Gearbox according to or claim 3 , characterized in that said ring () is coupled to said axial end () in an axially sliding and angularly fixed manner; said axial retaining means comprising axial locking means () that keep said ring () in axially fixed position with respect to said axial end ().632434144. Gearbox according to any one of to claim 3 , characterized in that said axial end () ...

RECONFIGURING A STATOR VANE STRUCTURE OF A TURBINE ENGINE

A turbine engine assembly and methods involving a turbine engine assembly are provided. In one method, the turbine engine assembly is received. The turbine engine assembly includes an annular stator vane structure disposed at a first orientation. The stator vane structure is reconfigured with the turbine engine assembly to be disposed at a second orientation. 1. A method involving a turbine engine assembly , comprising:receiving the turbine engine assembly, the turbine engine assembly including an annular stator vane structure disposed at a first orientation; andreconfiguring the stator vane structure with the turbine engine assembly to be disposed at a second orientation.2. The method of claim 1 , wherein the second orientation is angularly displaced about an axial centerline of the turbine engine assembly from the first orientation by between about five degrees and about one-hundred and eighty degrees.3. The method of claim 1 , whereinthe stator vane structure includes a plurality of bosses substantially uniformly disposed circumferentially about an axial centerline of the turbine engine assembly;each adjacent pair of the bosses are separated by an angular displacement increment about the axial centerline; andthe second orientation is angularly displaced about the axial centerline from the first orientation by a multiple of the angular displacement increment.4. The method of claim 1 , wherein the second orientation is angularly displaced about an axial centerline of the turbine engine assembly from the first orientation to change a hot spot location on the stator vane structure.5. The method of claim 1 , whereinthe turbine engine assembly includes a first turbine rotor and a second turbine rotor; andthe stator vane structure is arranged between the first turbine rotor and the second turbine rotor.6. The method of claim 1 , wherein the reconfiguring of the stator vane structure comprises:disassembling the turbine engine assembly to remove the stator vane structure; ...

COMBUSTOR ASSEMBLY LIFT SYSTEMS

A combustor assembly lift system comprises a track that extends in at least a longitudinal direction, a lift arm moveably engaged with the track such that it can traverse along the track in at least the longitudinal direction, and a combustor assembly engagement frame connected to the lift arm, wherein the combustor assembly engagement frame is configured to temporarily secure to at least a portion of a combustor assembly. 1. A combustor assembly lift system comprising:a track that extends in at least a longitudinal direction;a lift arm moveably engaged with the track such that it can traverse along the track in at least the longitudinal direction; and,a combustor assembly engagement frame connected to the lift arm, wherein the combustor assembly engagement frame is configured to temporarily secure to at least a portion of a combustor assembly.2. The combustor assembly lift system of claim 1 , wherein the lift arm is articulatable in a vertical direction.3. The combustor assembly lift system of claim 2 , wherein the lift arm is articulatable via powered lift.4. The combustor assembly lift system of claim 1 , wherein the lift arm comprises a linear lift arm.5. The combustor assembly lift system of claim 1 , wherein the lift arm is moveably engaged with the track via a support arm.6. The combustor assembly lift system of claim 5 , wherein the support arm rides along a rail on rail on the track.7. The combustor assembly lift system of claim 5 , wherein the support arm extends in a direction away from the track.8. The combustor assembly lift system of claim 5 , wherein the support arm is moveably engaged with the track via a rotatable connection such that the support arm can also rotate with respect to the track.9. The combustor assembly lift system of claim 1 , wherein at least a portion of the track extends along a non-linear path.10. The combustor assembly lift system of claim 1 , wherein the track comprises a junction that splits into at least two directions.11. The ...

SYSTEM FOR AND METHOD OF ACTUATING AN AIRCRAFT COWL

A method of and a system for actuating a cowl door. The method comprises detecting that current is drawn in a solenoid valve, the solenoid valve being selectively operable in a first mode to direct fluid from a fluid reservoir to an hydraulic actuator and in second mode to direct fluid from the hydraulic actuator to the fluid reservoir; and causing an electric motor to be powered based on the detection that current is drawn in the solenoid valve for actuating the cowl door, the electric motor being connected to a hydraulic pump in fluid communication with the solenoid valve, the hydraulic actuator and the fluid reservoir. 1. A power door opening system for an aircraft cowl , the system comprising:a first control switch electrically connected to a power source, the first control switch being operable to transition between a first position and a second position;a solenoid valve electrically connected to the control switch and in fluid communication with an hydraulic actuator and a fluid reservoir, the solenoid valve being selectively operable in a first mode to direct fluid from the fluid reservoir to the hydraulic actuator and in second mode to direct fluid from the hydraulic actuator to the fluid reservoir, the hydraulic actuator being mechanically connected to the aircraft cowl; andan electrical system controller electrically connected to the solenoid valve and configured to (1) detect that current is drawn in the solenoid valve and, (2) upon detecting that the current is drawn in the solenoid valve, cause an electric motor to be powered, the electric motor being connected to an hydraulic pump, the hydraulic pump being in fluid communication with the solenoid valve and the fluid reservoir.2. The power door opening system of claim 1 , wherein the electrical system controller further comprises a processor and a non-transitory computer-readable medium claim 1 , the non-transitory computer-readable medium comprising control logic which claim 1 , upon execution by the ...

GAS TURBINE

The aircraft-engine gas turbine includes an outer sealing ring for sealing an array of rotor blades that can be attached to a housing by a clamping means () in a friction fit, and a plurality of ring segments (), wherein a free axial path length (a) of a sealing ring segment counter to the direction of through-flow is at least as large as an axial engagement (a) of a rotation locking member () of the outer sealing ring (a≧a), which is free of form fit counter to the direction of through-flow, and/or an axial overhang (a) of a radial mounting rail () of the outer sealing ring (a≧a), and/or an axial offset (a, a) of a sealing fin (); and/or a quotient of a specific clearance sum of the outer sealing ring attached to the housing in a friction fit. 21211. The aircraft-engine gas turbine according to claim 1 , wherein the rotation locking member has a groove arrangement with at least one axial groove () in the housing that is open counter to the direction of through-flow claim 1 , in which a radial flange () of the outer sealing ring attached to the housing in a friction fit engages in the peripheral direction in a form-fitting manner claim 1 , and wherein the free axial path length of the sealing ring segment counter to the direction of through-flow is at least as large as a maximum groove length (a) of the groove arrangement (a≧a).331413242. The aircraft-engine gas turbine according to claim 1 , wherein the array of rotor blades has a first and a second sealing fin ( claim 1 , ) claim 1 , which is spaced apart axially from the first sealing fin claim 1 , and the stepped outer sealing ring has a first sealing face for sealing the first sealing fin and a second sealing face for sealing the second sealing fin claim 1 , which is spaced apart axially and radially from the first sealing face claim 1 , and the free axial path length of the sealing ring segment counter to the direction of through-flow is at least as large as an axial offset (a) of the first sealing fin with ...

TURBOFAN ENGINE ASSEMBLY AND METHODS OF ASSEMBLING THE SAME

A turbofan engine assembly includes a core gas turbine engine with a booster compressor having a radially outer diameter, a fan case assembly, and an outlet guide vane assembly. The outlet guide vane assembly includes a plurality of outlet guide vane segments spaced circumferentially about the core gas turbine engine. Each outlet guide vane segment of the plurality of outlet guide vane segments includes a radially inner fan hub frame flange configured to couple to the core gas turbine engine, a radially outer fan case flange configured to couple to the fan case assembly, and a plurality of outlet guide vanes extending therebetween. The radially inner diameter of the outlet guide vane assembly is smaller than the radially outer diameter of the booster compressor. 1. A turbofan engine assembly comprising:a core gas turbine engine comprising a booster compressor having a radially outer diameter;a fan case assembly; and a radially inner fan hub frame flange configured to couple to said core gas turbine engine;', 'a radially outer fan case flange configured to couple to said fan case assembly; and', 'a plurality of outlet guide vanes extending therebetween;, 'an outlet guide vane assembly comprising a plurality of outlet guide vane segments spaced circumferentially about said core gas turbine engine, each outlet guide vane segment of said plurality of outlet guide vane segments comprisingwherein a radially inner diameter of said outlet guide vane assembly is smaller than the radially outer diameter of said booster compressor.2. The assembly of claim 1 , wherein at least one outlet guide vane segment is removable from said outlet guide vane assembly.3. The assembly of claim 2 , wherein said core gas turbine engine is configured to shift in a radial direction away from at least one remaining outlet guide vane segments of said outlet guide vane assembly.4. The assembly of claim 1 , wherein at least one outlet guide vane segment is configured to be decoupled and removed from ...

SUPPORT APPARATUS FOR DISASSEMBLING AND ASSEMBLING GAS TURBINE ENGINE

A support apparatus for disassembling and assembling a gas turbine engine includes an exhaust nozzle attaching and detaching device for guiding movement of an exhaust nozzle in an axis direction and including: a first guide jig detachably fixed to a casing; and a first holding tool detachably supporting the nozzle and engaged with the first guide jig, thereby enabling attaching and detaching the nozzle easily and securely while leaving the engine in a horizontal attitude. The apparatus also includes a low-pressure turbine attaching and detaching device guiding movement of a low-pressure turbine in the axis direction and including: a second guide jig detachably fixed to the casing; and a second holding tool detachably supporting the turbine and engaged with the second guide jig, thereby enabling attaching and detaching the turbine easily and securely while leaving the engine in the horizontal attitude. 1. A support apparatus for disassembling and assembling a gas turbine engine housing a low-pressure shaft , a low-pressure turbine and an exhaust nozzle inside a cylindrical casing surrounding an axis of the gas turbine engine , the low-pressure shaft being disposed on the axis , the low-pressure turbine being fixed to an outer periphery of the low-pressure shaft , and the exhaust nozzle being disposed in a rear of the low-pressure turbine , the support apparatus comprising: a first guide jig which is detachably fixed to the casing, and', 'a first holding tool which detachably supports the exhaust nozzle and is engaged with the first guide jig; and, 'an exhaust nozzle attaching and detaching device configured to guide movement of the exhaust nozzle in a direction of the axis and including'} a second guide jig which is detachably fixed to the casing, and', 'a second holding tool which detachably supports the low-pressure turbine and is engaged with the second guide jig., 'a low-pressure turbine attaching and detaching device configured to guide movement of the low- ...

Mid-turbine frame stator with repairable bushing and retention pin

A gas-turbine engine is provided comprising a high-pressure turbine, a low-pressure turbine aft of the high-pressure turbine, and a housing around the low-pressure turbine and the high-pressure turbine. A stator may be disposed between the low-pressure turbine and the high-pressure turbine with a boss formed on the stator. A bushing may be retained in the boss with a pin coupled to the housing and partially within the bushing. A method of mounting a full-ring stator is also provided, the method including the steps of inserting a bushing into a boss of the full-ring stator by press fitting, and inserting a pin into the bushing of the full-ring stator.

RETAINING DEVICE FOR DISASSEMBLING A BLADED WHEEL OF A TURBINE ENGINE AND METHOD EMPLOYING IT

The invention relates to a retaining device for disassembling a bladed wheel of a turbine engine. 1. A retaining device for disassembling a wheel having blades of a turbine engine in order to remove a downstream retaining ring of the wheel when the wheel is disposed around a vertical axis with an upstream side of the wheel turned upward ,the blades of the wheel extending radially and being intended to be mounted circumferentially around a disk of the wheel, the wheel including, for each blade, a damping element disposed in a cavity which opens radially inward and which is delimited by a platform of the blade and by an inner upstream wall of the blade terminating by an upstream groove, the downstream retaining ring being housed in a downstream groove of the platform of the blade, the upstream groove and the downstream groove extending radially,wherein the retaining device is intended to be mounted coaxially with a vertical axis and includes:an inter-blade ring sector,a plurality of retaining clips, each retaining clip being intended to cooperate with one of the damping elements, the retaining clips extending radially while being attached circumferentially to the inter-blade ring sector.2. The device according to claim 1 , wherein the inter-blade ring sector extends circumferentially and comprises a flank extending radially claim 1 , the inter-blade ring sector being configured so that the flank can be inserted into a plurality of the upstream grooves being circumferentially adjacent.3. The device according to claim 2 , wherein the flank has a first contact zone configured to cooperate with the plurality of upstream grooves.4. The device according to claim 1 , wherein each retaining clip has a first end portion claim 1 , which is free and which is configured to be able to be inserted respectively into a lateral recess of each damping element.5. The device according to claim 4 , wherein the first end portion has a second zone of contact with the damping element.6. The ...

APPARATUS FOR CIRCUMFERENTIAL SEPARATION OF TURBINE BLADES

Embodiments of the present disclosure can provide an apparatus for circumferentially separating turbine blades. An apparatus according to the present disclosure may include: a length-adjustable elongate member having opposing first and second ends; a first clasp coupled to the first end of the length-adjustable elongate member, the first clasp shaped to at least partially engage an airfoil profile of a first turbine blade positioned circumferentially adjacent to a dovetail slot, relative to a centerline axis of the turbomachine; and a second clasp coupled to the second end of the length-adjustable elongate member, the second clasp shaped to at least partially engage an airfoil profile of a second turbine blade circumferentially positioned adjacent to the dovetail slot, the first and second turbine blades being circumferentially adjacent to the dovetail slot at opposing circumferential ends thereof. 1. An apparatus for circumferentially separating turbine blades , the apparatus comprising:a length-adjustable elongate member having opposing first and second ends;a first clasp coupled to the first end of the length-adjustable elongate member, the first clasp shaped to at least partially engage an airfoil profile of a first turbine blade positioned circumferentially adjacent to a dovetail slot, relative to a centerline axis of the turbomachine; anda second clasp coupled to the second end of the length-adjustable elongate member, the second clasp shaped to at least partially engage an airfoil profile of a second turbine blade circumferentially positioned adjacent to the dovetail slot, the first and second turbine blades being circumferentially adjacent to the dovetail slot at opposing circumferential ends thereof.2. The apparatus of claim 1 , wherein the first clasp and the second clasp are each rotatably coupled to one of the first or second end of the length-adjustable elongate member such that each of the first and second clasps are configured to rotate about the ...

System and Method for Removing or Installing a Main Shaft of a Wind Turbine

The present disclosure is directed to a system and method for removing or installing a main shaft of a drivetrain assembly of a wind turbine to and from a nacelle installed atop a wind turbine tower. The rail system includes at least one support component configured to support the main shaft. Further, the support component is configured horizontally with respect to the main shaft. The rail system also includes at least one sliding component connected between the support component and the main shaft. Thus, the sliding component is configured to move horizontally with respect to the support component so as to slide the main shaft between an installed position and an uninstalled position. 1. A rail system for removing or installing a main shaft of a drivetrain assembly of a wind turbine to and from a nacelle installed atop a wind turbine tower , the rail system comprising:at least one support component configured to support the main shaft, the support component configured substantially horizontally with respect to the main shaft; and,at least one sliding component connected between the support component and the main shaft,wherein the sliding component is configured to move horizontally with respect to the support component so as to slide the main shaft between an installed position and an uninstalled position.2. The rail system of claim 1 , wherein the at least one support component is configured above or below the main shaft.3. The rail system of claim 1 , wherein the at least one support component further comprises parallel support arms.4. The rail system of claim 3 , further comprising at least one sliding component configured with each of the parallel support arms.5. The rail system of claim 4 , wherein each of the parallel support arms comprises a track and each of the sliding components comprises at least one rolling element configured within each track.6. The rail system of claim 5 , wherein each of the sliding components further comprises at least one strap ...

ROTATING DEVICE FOR A GAS TURBINE AND METHOD FOR ROTATING A COMPONENT

A rotating device for an at least partially opened gas turbine, is designed for being mounted on a parting line of the housing of the at least partially opened gas turbine by way of at least one connecting portion, wherein the rotating device has at least one first fastening portion, which is designed for mechanically interacting with a force-transmitting connection, in particular at least one traction cable, in order to pass on mechanically a rotating movement of at least one component of the at least partially opened gas turbine, wherein it has at least one sleeve, which has at least one second fastening portion, wherein the sleeve is designed for being connected non-positively to the gas turbine rotor. 1. A rotating device for an at least partially opened gas turbine , which is designed to be installed on a parting joint of the casing of the at least partially opened gas turbine by means of at least one connection section , wherein the rotating device comprises:at least one first attachment section which is designed to mechanically cooperate with a force-transmitting connection, in order to mechanically impart a rotational movement to at least one component of the at least partially opened gas turbine, andat least one collar having at least one second attachment section, the collar being designed to be connected in a force-fitting manner to the gas turbine rotor.2. The rotating device as claimed in claim 1 ,wherein the rotating device, once installed on the casing, partially surrounds a gas turbine rotor of the at least partially opened gas turbine.3. The rotating device as claimed in claim 1 , further comprising:at least one adapter piece which can be mechanically connected both to the at least one connection section and to the parting joint of the casing of the gas turbine.4. The rotating device as claimed in claim 1 ,wherein the at least one first attachment section is designed to support a sheathed cable as the force-transmitting connection.5. The rotating ...

Fan Blade Removal Panel

A fan section of a gas turbine engine is disclosed. The fan section may comprise a fan having a hub and a plurality of blades extending radially from the hub. The fan section may further comprise a fan case surrounding the fan and an inlet structure located upstream of the fan and defining at least a portion of an airflow path leading to the fan. The inlet structure may have at least one panel removably connected to at least one structural element of the gas turbine engine, and an opening may be exposed when the panel is disconnected from the gas turbine engine. The opening may provide clearance for removal of at least one of the plurality of blades from the hub. 1. A fan section of a gas turbine engine , comprising:a fan having a hub and a plurality of blades extending radially from the hub;a fan case surrounding the fan; andan inlet structure located upstream of the fan and defining at least a portion of an airflow path leading to the fan, the inlet structure having at least one panel removably connected to at least one structural element of the gas turbine engine, the panel exposing an opening that provides clearance for removal of at least one of the plurality of blades from the hub when it is removed.2. The fan section of claim 2 , wherein the opening provides clearance for pulling at least one of the plurality of blades away from the hub in an axially forward direction with respect to a central axis of the gas turbine engine.3. The fan section of claim 2 , wherein the panel is hingedly connected to the inlet structure.4. The fan section of claim 2 , wherein the panel is removably connected to the fan section.5. The fan section of claim 4 , wherein the panel is removably connected to an inner surface of the fan case.6. The fan section of claim 5 , wherein the fan case comprises at least one flange extending inwardly from the inner surface claim 5 , and wherein the panel is removably connected to the at least one flange with at least one mechanical fastener.7. ...

GAS TURBINE ENGINES WITH INTERNALLY STRETCHED TIE SHAFTS

A tie shaft for a rotating group of an engine core includes a cylindrical body having an internal surface and an external surface and extending between a forward end and an aft end. The tie shaft further includes a first group of internal grooves on the internal surface of the cylindrical body proximate to the forward end and a second group of internal grooves on the internal surface of the cylindrical body proximate to the aft end 1. A tie shaft for a rotating group of an engine core , comprising:a cylindrical body having an internal surface and an external surface and extending between a forward end and an aft end;a first group of internal grooves on the internal surface of the cylindrical body proximate to the forward end; anda second group of internal grooves on the internal surface of the cylindrical body proximate to the aft end.2. The tie shaft of claim 1 , wherein the first group of internal grooves is a first group of buttress rings claim 1 , and wherein the second group of internal grooves is a second group of buttress rings.3. The tie shaft of claim 2 , wherein the first group of buttress rings and the second group of buttress rings are concentric claim 2 , circumferential rings.4. The tie shaft of claim 2 , wherein each of the first group of buttress rings includes a first surface that engages a first axial load in a first direction claim 2 , and wherein each of the second group of buttress rings includes a second surface that engages a second axial load in a second direction.5. The tie shaft of claim 1 , wherein the first group of internal grooves is configured to engage a first stretch load in a first direction and the second group of internal grooves is configured to engage a second stretch load in a second direction.6. The tie shaft of claim 1 , wherein the cylindrical body includes at least one set of slots extending from the internal surface proximate to at least one of the first group of internal grooves and the second group of internal grooves.7. ...

HOLDING SYSTEM FOR THE DISMANTLING OF A BLADE WHEEL

The present disclosure relates to a holding system for the dismantling of a blade wheel, the blade wheel comprising: a disc, a plurality of blades configured to be mounted circumferentially around the disc, the plurality of blades defining a plurality of inter-blade spaces, each of the inter-blade spaces being defined circumferentially between two adjacent blades of the plurality of blades, the holding system comprising a plurality of inserts, each of the inserts being configured to be inserted into each of the inter-blade spaces in a holding position so as to hold the relative position of the blades when the plurality of blades is dismantled from the disc. 2. The holding system according to claim 1 , wherein each of the inserts comprises at least one portion made of an aluminum-based alloy claim 1 , and/or a polymer having a Shore A hardness comprised between 75 and 100.3. The holding system according to claim 1 , wherein the inserts have a thickness in a radial direction greater than or equal to 10% of the height of an airfoil of a blade in the radial direction.4. The holding system according to claim 1 , comprising a grip portion configured to be mounted on an insert of the plurality of inserts claim 1 , the grip portion being configured to allow the gripping of the insert and facilitate the mounting of the insert in an inter-blade space.5. The holding system according to claim 1 , comprising a device for positioning the plurality of inserts claim 1 , each insert of the plurality of inserts being configured to be applied to the positioning device so as to hold the inserts in position.6. The holding system according to claim 5 , wherein the positioning device comprises a positioning ring claim 5 , the positioning ring comprising fastening elements to allow the fastening of the inserts on the positioning ring.7. The holding system according to claim 1 , wherein each of the inserts comprises:{'b': '43', 'a first member and a second member, the first and second ...

EXPANSION TURBINE

An expansion turbine including: a stator, a rotor facing the stator, a short pipe, a shaft rotatably mounted in the short pipe and removably connected to the rotor. The shaft is extractable from the short pipe from the side opposite said rotor. The turbine includes devices removably connecting the rotor to the shaft having a handling portion at a rotor front face. A front static seal, between the rotor and stator, at a radially inner position with respect to an expansion volume between the stator and rotor. The front static seal is mobile between a first position at which a passage is cleared between the stator and the rotor in fluid communication with the expansion volume, and a second position which seals the passage and isolates the expansion volume from a space for access to said handling portion. The front static seal may variable geometry and be an inflatable gasket. 1. An expansion turbine comprising:a case;a stator integrated or installed in the case and having stator blades;a rotor mounted in the case, having rotor blades and facing the stator, wherein the rotor is rotatable around a respective rotation axis (X-X);wherein the stator and the rotor delimit between them an expansion volume (V) for a working fluid, provided with said rotor and stator blades;a short pipe integrated or installed on the case;a shaft rotatably mounted in the short pipe and rotating around the rotation axis (X-X);wherein the shaft is removably connected to the rotor and said shaft is extractable from the short pipe from the side opposite said rotor;a device configured to removably connect the rotor to the shaft having a handling portion placed at a front face of the rotor opposite the short pipe and facing at a space configured to allow access to said handling portion;at least one front static seal interposed between the rotor and the stator and placed at a radially inner position with respect to the expansion volume (V);wherein the front static seal and the rotor are movable with ...

TOOL AND METHOD FOR FRONTAL UNSCREWING OF A LINK NUT IN A TWIN-SPOOL TURBINE

A method for unscrewing a link nut of an HP rotor of a twin-spool turbine, including a front fan, an intermediate casing, a HP module with a HP rotor, and a LP turbine module, the intermediate casing including a support bearing for the HP rotor, the rotor being retained in the bearing by the link nut, the method including: placing an unscrewing tool in front of the link nut after having removed the fan and released access to the nut from the front; with rotation of the HP rotor locked and the frontal unscrewing tool including a socket spanner including teeth having a shape that complements that of teeth of the link nut, attaching a mounting for the socket spanner to the intermediate casing, the socket spanner being rotatably mounted on the mounting, and applying an unscrewing torque to the socket spanner. An unscrewing tool implements the method. 1. An unscrewing tooling configured to unscrew a connecting nut of a rotor of a gas turbine engine module , comprising:a support for a tubular wrench comprising a cylindrical barrel and four branches extending in a star shape from the barrel, the tubular wrench comprising teeth mounted removably in the barrel of the support, the tubular wrench being locked axially with respect to the support; andan anti-rotation tool configured to block the rotor against any rotational movement about its axis.2. The tooling as claimed in claim 1 , wherein the anti-rotation tool comprises a tubular element comprising wedges claim 1 , the tubular element configured to be introduced inside the HP rotor to immobilize the rotor against rotation. This application is a division of U.S. application Ser. No. 14/397,361 filed Oct. 27, 2014, the entire contents of which is incorporated herein by reference. U.S. application Ser. No. 14/397,361 is a 371 of International application Ser. No. PCT/FR13/050978 filed May 2, 2013, and claims the benefit of priority from prior French Application No. 12 54028 filed May 2, 2012.The present invention relates to ...

System and Method for Rejuvenating Coated Components of Gas Turbine Engines

The present disclosure is directed to a method for rejuvenating a damaged coated component of a gas turbine engine. The method includes uninstalling the damaged coated component from the gas turbine engine. The method also includes isolating a first coated portion of the component of the gas turbine engine from a second coated portion of the component. In addition, the method includes simultaneously depositing a first coating material on the first coated portion of the component and a different, second coating material on the second coated portion of the component. The method also includes reinstalling the rejuvenated coated component into the gas turbine engine. 1. A method for rejuvenating a damaged coated component of a gas turbine engine , the method comprising:uninstalling the damaged coated component from the gas turbine engine;isolating a first coated portion of the component of the gas turbine engine from a second coated portion of the component;simultaneously depositing a first coating material on the first coated portion of the component and a different, second coating material on the second coated portion of the component; and,reinstalling the rejuvenated coated component into the gas turbine engine.2. The method of claim 1 , wherein the coated component of the gas turbine engine comprises at least one of a turbine blade claim 1 , a fan blade claim 1 , a compressor blade claim 1 , a nozzle claim 1 , shrouds claim 1 , shroud supports claim 1 , frames claim 1 , a turbine vane claim 1 , a guide vane claim 1 , or a compressor vane.3. The method of claim 1 , wherein simultaneously depositing the first coating material on the first coated portion of the component and the second coating material on the second coated portion of the component comprises at least one of diffusion coating claim 1 , plating claim 1 , slurry coating claim 1 , or powder coating.4. The method of claim 2 , wherein the first coated portion comprises a shank of the turbine blade and the ...

REMOVAL DEVICE

A tool for removing a component from a turbomachine is provided. The tool includes a body having an alignment portion and a connection portion. The alignment portion defines a longitudinal axis and a cross sectional shape complementary to a slot defined in a rotor wheel of the turbomachine. When the tool is positioned in the slot, the connection portion is configured to contact the component. The tool additionally includes a force section connected to the body and configured to transfer a force to the connection portion in a direction substantially parallel to the longitudinal axis of the alignment portion. 1. A tool for removing a component of a turbomachine , comprising: a connection portion configured to contact the component; and', 'an alignment portion defining a longitudinal axis and a cross-sectional shape, the cross-sectional shape being complementary to a slot defined in a rotor wheel of the turbomachine; and, 'a body, the body comprising'}a force section connected to the body and configured to transfer a force to the connection portion of the body in a direction substantially parallel to the longitudinal axis of the alignment portion.2. The tool as in claim 1 , wherein the alignment portion of the body is configured to slidably couple the body of the tool to the slot defined in the rotor wheel.3. The tool as in claim 1 , wherein the component is a near flow path seal and the slot defined in the rotor wheel is a dovetail slot configured to receive a rotor blade.4. The tool as in claim 1 , wherein the connection portion comprises a clamp removably attached to the component of the turbomachine.5. The tool as in claim 4 , wherein the clamp defines an upper clamping surface and a lower clamping surface claim 4 , each defined at an angle relative to the longitudinal axis of the alignment portion claim 4 , and wherein when the clamp is in a closed position claim 4 , the upper clamping surface is substantially flush with an outer surface of the component and the ...

Tool for manipulating cross-fire tube in combustor assembly, combustor maintenance assembly and method

Combustor maintenance assemblies, tools and methods for manipulating cross-fire tubes in combustor assemblies are provided. A tool includes a base and an arm pivotally connected to the base. The arm includes an effort portion and a load portion, the load portion extendable into a passage defined by the compressor discharge casing. The tool further includes a contact member extending from the load portion to contact the cross-fire tube. The contact member includes a head end for contacting a second end of the cross-fire tube, and a joint disposed between the head end and the load portion, the joint allowing movement of the head end relative to the load portion. The arm is movable such that the contact member contacts the cross-fire tube and applies a force to the cross-fire tube generally along a longitudinal axis of the cross-fire tube.

ROOT SPRING REMOVAL TOOL AND METHOD OF REMOVING A BLADE ROOT SPRING

An apparatus for removing a root spring, the apparatus including a main body, a punch secured to the main body, and a driving mechanism coupled to the punch, wherein actuation of the driving mechanism moves the linear moving punch forward for engaging the root spring. The main body includes a front plate, a rear plate, a right side plate, a left side plate and an interior portion; wherein the right side plate and left side plate are substantially parallel with each other and each includes an elongated opening and a plurality of notches; 1. An apparatus for removing a root spring , the apparatus comprising:a main body;a punch secured to said main body; anda driving mechanism coupled to said punch,wherein actuation of said driving mechanism moves said linear moving punch forward for engaging the root spring.2. An apparatus , comprising:a main body including a front plate, a rear plate, a right side plate, a left side plate and an interior portion; wherein the right side plate and left side plate are substantially parallel with each other and each includes an elongated opening and a plurality of notches;a linkage mechanism attached to the main body and configured to slide along the elongated openings;a punch provided in the interior portion and configured to be attached to the linkage mechanism;a driving mechanism coupled to the linkage mechanism and configured to engage the plurality of notches,wherein the driving mechanism drives the punch via the linkage mechanism by engaging at least one the plurality of notches in a ratchet like manner.3. The apparatus of claim 2 , wherein the front plate claim 2 , the rear plate claim 2 , the right side plate and the left side plate are joined together at substantial right angles.4. The apparatus of claim 2 , wherein the elongated openings extend across substantially the entire right and left side plates.5. The apparatus of claim 2 , wherein the plurality of notches extend across substantially the entire right and left side ...

TURBOMACHINE AND METHOD FOR DISASSEMBLING SUCH A TURBOMACHINE

A turbine includes an outer casing and an inner casing surrounded by said outer casing. The outer casing and inner casing are coaxially arranged with respect to a machine axis. The outer casing and inner casing are each divided in a split plane into an upper part and a lower part. The upper and lower parts are connected with each other in said split plane by means of a flanged connection. The disassembly process is improved by the flanged connection of the upper and lower part of the inner casing comprising a plurality of bolts, which extend each through through holes in respective flanges of said flanged connection of the inner casing, protrude from said through holes at both ends with a threaded section, and are tightened by means of nuts screwed on said threaded sections at both ends of said bolt. 1. A turbomachine , comprising an outer casing and an inner casing surrounded by said outer casing , whereby said outer casing and inner casing are coaxially arranged with respect to a machine axis , whereby said outer casing and inner casing are each divided in a split plane into an upper part and a lower part , and whereby said upper and lower parts are connected with each other in said split plane by means of a flanged connection , wherein the flanged connection of the upper and lower part of said inner casing comprises a plurality of bolts , which extend each through through holes in respective flanges of said flanged connection of said inner casing , protrude from said through holes at both ends with a threaded section , and are tightened by means of nuts screwed on said threaded sections at both ends of said bolt.2. The turbomachine according to claim 1 , further comprising washers disposed between each nut and the respective flange.3. The turbomachine according to claim 2 , wherein said bolts are designed as waisted shank bolts.4. The turbomachine according to claim 3 , wherein said bolts are provided with screw heads at their ends.5. A method for disassembling a ...

MOUNTING AND DISMOUNTING DEVICE FOR A LINER OF A GAS TURBINE AND A RELATED METHOD

A mounting and dismounting device for a liner of a gas turbine includes two inner rails attached at the turbine housing and each one having a first straight portion, two straight outer rails releasably attached at the turbine housing, wherein the adjacent free ends of the inner and outer rails can be positioned in full alignment one to the other. The rails are adapted to support the liner to be moveable in its axial direction. The inner rails include a second straight portion connected to the first straight portion through a curved portion wherein the axis of the second straight portion is parallel to the axis of the combustion gas passageway. 1. A mounting and dismounting device for a liner of a gas turbine wherein a front end of the liner is to be connected or disconnected to an inlet portion of a combustion gas passageway , comprising:two inner rails, arranged essentially parallel one to the other, each one attachable to the turbine housing and each one having a first straight portion, two outer rails, arranged essentially parallel one to the other and attachable to the turbine housing, wherein the adjacent free ends of the inner and outer rails can be positioned in full alignment one to the other, wherein the inner and outer rails are configured to support the liner to be moveable in its axial direction, wherein the inner rails include a second straight portion connected to the first straight portion through a curved portion.2. The device according to claim 1 , wherein the front free ends of the inner rails are attachable at the turbine housing preferably to reception holes in the housing claim 1 , and/or the base free ends of the inner rails are attachable to the turbine housing via connection plates.3. The device according to claim 1 , wherein the outer rails are attachable to the housing via connection plates.4. The device according to claim 1 , comprising:an advancing and retracting mechanism to advance and reject the liner along the inner and outer rails;an ...

Acoustic Panel of Turbine Engine and Method of Arranging the Acoustic Panel

An aircraft engine includes a rotating structure and a casing circumferentially surrounding the rotating structure. The aircraft engine further includes an acoustic panel for noise reduction circumferentially surrounding the rotating structure and disposed adjacent the casing. The acoustic panel comprises a plurality of acoustic panel members arranged adjacent to one another to form a substantially complete ring of the acoustic panel. A first acoustic panel member of the plurality of acoustic members is adjacent to a second acoustic panel member of the plurality of acoustic members. The first acoustic panel member is removably secured to the second acoustic panel member by a releasable fastening assembly. 1. An aircraft engine , comprising:a rotating structure;a casing circumferentially surrounding the rotating structure; andan acoustic panel for noise reduction circumferentially surrounding the rotating structure and disposed adjacent the casing, the acoustic panel comprising a plurality of acoustic panel members arranged adjacent to one another to form a substantially complete ring of the acoustic panel, wherein a first acoustic panel member of the plurality of acoustic members is adjacent to a second acoustic panel member of the plurality of acoustic members and wherein the first acoustic panel member is removably secured to the second acoustic panel member by a releasable fastening assembly.2. The aircraft engine of claim 1 , wherein the first acoustic panel member comprises a first front structural member and a first aft structural member claim 1 , wherein the second acoustic panel member comprises a second front structural member and a second aft structural member claim 1 , wherein the first front structural member is removably secured to the second front structural member by the releasable fastening assembly.3. The aircraft engine of claim 2 , wherein at least the first aft structural member is fastened to the casing surrounding the rotating structure to ...

SEAL ASSEMBLY IN A GAS TURBINE ENGINE

A gas turbine engine seal assembly () including: a rigid seal () cooperatively configured with a structure () of a gas turbine engine to define a leakage path () including a flow-controlling section (); and a compliant seal () positioned in the leakage path. 1. A gas turbine engine seal assembly comprising:a rigid seal cooperatively configured with a structure of a gas turbine engine to define a leakage path there between comprising a flow-controlling section; anda compliant seal positioned in the leakage path.2. The seal assembly of claim 1 , wherein the compliant seal is disposed in the leakage path and remote from the flow-controlling section.3. The seal assembly of claim 1 , wherein the compliant seal is disposed in the flow-controlling section.4. The seal assembly of claim 1 , wherein the compliant seal comprises a resilient seal claim 1 , and a resilience of the resilient seal urges the rigid seal toward the structure claim 1 , thereby minimizing the flow-controlling section.5. The seal assembly of claim 1 , wherein the compliant seal comprises a rope seal claim 1 , a brush seal claim 1 , or a crushable seal.6. A gas turbine engine seal assembly comprising:a first component and a second component spaced apart by a gap and defining a hot gas path, wherein the first component comprises a flange, wherein the second component comprises a ledge that extends toward the flange;a floating seal spanning the gap and comprising a first groove oriented radially and configured to receive and permit relative radial movement of the flange and a second groove oriented axially and configured to receive and permit relative axial movement of the ledge;contact regions between the floating seal and the flange and between the floating seal and the ledge that define limits of relative movement of the floating seal with respect to the flange and the ledge during operation;wherein the flange and the first groove define a first leakage path there between, and wherein the second groove ...

QUICK RELEASE ROTOR ATTACHMENT SYSTEMS AND METHODS

Provided herein is a rotor attachment assembly for an aircraft. A rotor attachment assembly includes a connecting assembly associated with the aircraft and a rotor assembly configured to be connected to the connecting assembly. The rotor assembly includes a plurality of fins configured to fit a respective plurality of cut-outs of the connecting assembly, a hollow section configured to accommodate at least a part of a pin of the connecting assembly so as to center the rotor assembly relative to the connecting assembly, and a spring configured to expand to allow the fins to pass and to close to retain the fins when the rotor assembly is connected to the connecting assembly. 1. A rotor attachment assembly for an aircraft , comprising:a connecting assembly associated with the aircraft; and a plurality of fins configured to fit a respective plurality of cut-outs of the connecting assembly,', 'a hollow section configured to accommodate at least a part of a pin of the connecting assembly so as to center the rotor assembly relative to the connecting assembly, and', 'a spring configured to expand to allow the fins to pass and to close to retain the fins when the rotor assembly is connected to the connecting assembly., 'a rotor assembly configured to be connected to the connecting assembly, wherein the rotor assembly comprises2. The rotor attachment assembly of claim 1 , wherein at least one of the plurality of fins comprises a width different from widths of remaining ones of the plurality of fins.3. The rotor attachment assembly of claim 1 , wherein widths of the plurality of fins correspond to widths of the respective plurality of cut-outs.4. The rotor attachment assembly of claim 1 , wherein the plurality of fins comprises first and second fins.5. The rotor attachment assembly of claim 1 , wherein the spring is made of metal.6. The rotor attachment assembly of claim 1 , wherein the rotor assembly is made of a polymer and/or a composite material.7. The rotor attachment ...

REMOVAL TOOL

A tool for removing a component from a turbomachine is provided. The tool includes a body having a connection portion for engaging the component. The tool additionally includes a force section connected to the body and configured to transfer a force to the connection portion in a direction at an acute angle relative to longitudinal axis of a dovetail slot of a rotor wheel adjacent to the component. 1. A tool for removing a component of a turbomachine , comprising:a body including a connection portion configured to engage the component; anda force section connected to the body and configured to transfer a force to the connection portion of the body in a direction at an acute angle relative to a longitudinal axis of a dovetail slot of a rotor wheel of the turbomachine.2. The tool as in claim 1 , wherein the component is a near flow path seal.3. The tool as in claim 1 , wherein the connection portion comprises a clamp removably attached to the component of the turbomachine.4. The tool as in claim 3 , wherein the clamp defines an upper clamping surface and a lower clamping surface claim 3 , and wherein in response to the clamp being in a closed position claim 3 , the upper clamping surface is substantially flush with an outer surface of the component and the lower clamping surface is substantially flush with an inner surface of the component.5. The tool as in claim 3 , wherein the clamp includes a set of clamps claim 3 , each clamp selectively coupled to the body and having a different sized clamping area between the upper clamping surface and the lower clamping surface than other clamps in the set of clamps.6. The tool as in claim 1 , wherein the force section is configured to transfer a pulling force to the body of the tool in a direction away from the component.7. The tool as in claim 1 , wherein the force section comprises a slide hammer attached to a rear end of the body.8. The tool as in claim 7 , wherein the slide hammer comprises:a rod attached to the body and ...

TURBINE

A low-pressure turbine of a jet engine includes: a turbine case; turbine blades rotatable about an axis of the turbine case; and a shroud including a plurality of shroud segments annularly placed along an inner peripheral surface of the turbine case while surrounding the turbine blades. Each shroud segment is provided with a projection and an outward groove. The shroud segment is fixed to the turbine case by allowing the projection to engage with a receiving groove of the turbine case in an axial direction, and allowing the outward groove to engage with an inward projection of the turbine case in a radial direction. The shroud segment is provided with a pressure receiving portion that receives a force to release an engaged state of the outward groove with the inward projection of the turbine case in a step of removing the shroud segment from the turbine case. This enables disassembling work to be performed easily, while realizing reduction of engine performance loss and mitigation of thermal fatigue of the turbine case. 1a turbine case of a cylindrical shape;turbine blades rotatable about an axis of the turbine case; anda shroud including a plurality of shroud segments annularly placed along an inner peripheral surface of the turbine case while surrounding the turbine blades, whereineach of the shroud segments of the shroud is provided with a first engaging portion and a second engaging portion,the shroud segment of the shroud is fixed to the turbine case by allowing the first engaging portion to engage with the turbine case in an axial direction of the turbine case, and allowing the second engaging portion to engage with the turbine case in a radial direction of the turbine case, andthe shroud segment of the shroud is provided with a pressure receiving portion that receives a force to release an engaged state of the second engaging portion with the turbine case in a step of removing the shroud segment from the turbine case.. A turbine of a jet engine, the turbine ...

ADDITIVE MANUFACTURING LIFT AND PULL TOOL

A method of making a tool includes creating a computer rile defining the tool in layers and building the tool using an additive manufacturing process that builds the tool on a layer-by-layer basis. The tool includes at least one of the following features: a substantially square dogleg inner end corner, a substantially completely cylindrical dogleg surface, an angled dogleg inlet, and an integral mounting point at or near one end of the body. 1. A method of making a tool , the method comprising: a cylindrical body having a first end and a second end; and', 'a plurality of dogleg slots at the second end of the tool;', 'wherein the tool includes at least one of the following features: a substantially square dogleg inner end corner, a substantially completely cylindrical dogleg surface, an angled dogleg inlet, and an integral mounting point on or proximate to the first end of the body; and, 'creating a computer file defining the tool in layers, the tool comprisingbuilding the tool using an additive manufacturing process that builds the tool on a layer-by-layer basis from the first end to the second end.2. The method of claim 1 , wherein the tool includes at least two of the following features: a substantially square dogleg inner end corner claim 1 , a substantially completely cylindrical dogleg surface claim 1 , an angled dogleg inlet claim 1 , and an integral mounting point on or proximate to the first end of the body.3. The method of claim 1 , wherein the tool includes at least three of the following features: a substantially square dogleg inner end corner claim 1 , a substantially completely cylindrical dogleg surface claim 1 , an angled dogleg inlet claim 1 , and an integral mounting point on or proximate to the first end of the body.4. The method of claim 1 , wherein the tool includes all of the following features: a substantially square dogleg inner end corner claim 1 , a substantially completely cylindrical dogleg surface claim 1 , an angled dogleg inlet claim 1 ...

INLET GUIDE VANE REMOVAL TOOLS AND METHODS

An inlet guide vane removal assembly includes a support frame with a support plate. At least one force device is coupled to the support plate. A puller bracket is attached to the at least one force device. The puller bracket has an open-ended slot defined therethrough, and a plurality of flanges positioned to engage an installed inlet guide vane. When the force device is actuated, the puller bracket is displaced relative to the support frame to facilitate removing the inlet guide vane. 1. An inlet guide vane removal assembly comprising:a support frame comprising a support plate;at least one force device coupled to said support plate; and an open-ended slot defined therethrough; and', 'a plurality of flanges positioned to engage an installed inlet guide vane such that, when said at least one force device is actuated, said puller bracket is displaced relative to said support frame to facilitate removal of the inlet guide vane., 'a puller bracket coupled to said at least one force device, said puller bracket comprising2. An inlet guide vane removal assembly in accordance with claim 1 , wherein said support plate comprises an open-ended slot defined therein and configured to receive an airfoil portion of the inlet guide vane.3. An inlet guide vane removal assembly in accordance with claim 1 , wherein said support frame further comprises a guide plate spaced from said support plate.4. An inlet guide vane removal assembly in accordance with claim 3 , wherein said support plate comprises an open-ended slot defined therein and configured to receive an airfoil portion of the inlet guide vane.5. An inlet guide vane removal assembly in accordance with claim 3 , wherein said guide plate comprises an open-ended slot defined therein and configured to receive an airfoil portion of the inlet guide vane.6. An inlet guide vane removal assembly in accordance with claim 3 , wherein said support frame comprises a positioning plate releasably coupled to said guide plate claim 3 , said ...