РАБОЧАЯ ЛОПАТКА ПАРОВОЙ ТУРБИНЫ ДЛЯ СЕКЦИИ НИЗКОГО ДАВЛЕНИЯ ПАРОВОЙ ТУРБИНЫ

Рабочая лопатка (20) паровой турбины для секции низкого давления паровой турбины (10). Рабочая лопатка (20) паровой турбины содержит участок (42) аэродинамической поверхности. Секция (44) хвостовика прикреплена к одному концу участка (42) аэродинамической поверхности. Часть (40) в виде ласточкиного хвоста выступает от секции (44) хвостовика, а часть (40) в виде ласточкиного хвоста содержит скошенную часть (40) в виде ласточкиного хвоста с осевой заводкой, имеющую угол скоса, составляющий 19°. Секция (46) венца прикреплена к участку (42) аэродинамической поверхности на конце, противоположном секции (44) хвостовика. Бандажная полка (48) выполнена за одно целое в виде части секции (46) венца. Полка (50) прикреплена к промежуточной секции участка (42) аэродинамической поверхности между его концами. Рабочая лопатка (20) имеет площадь выходного кольцевого сечения, составляющую около 4,43 мили больше. Участок (42) аэродинамической поверхности имеет длину, составляющую около 68,1 см или больше.

ПАРОВАЯ ТУРБИНА, ИМЕЮЩАЯ СТУПЕНЬ С ЛОПАТКАМИ, ВЫПОЛНЕННЫМИ ИЗ РАЗЛИЧНЫХ МАТЕРИАЛОВ

... 1. Паровая турбина (10), содержащая: ! ступень (100), включающую в себя множество лопаток, включающих в себя комплект первых лопаток (150), выполненных из первого материала, и комплект вторых лопаток (152), выполненных из второго материала, причем первый материал отличается от второго материала. ! 2. Паровая турбина (10) по п.1, в которой первые лопатки (150) и вторые лопатки (152) чередуются через одну лопатку по окружности ступени (100). ! 3. Паровая турбина (10) по п.1, в которой комплект первых лопаток (150) расположен в подгруппах, по меньшей мере, из двух лопаток, равномерно распределенных по окружности вокруг ступени (100) между комплектом вторых лопаток (152). ! 4. Паровая турбина (10) по п.1, в которой первый материал включает в себя сплав нержавеющей стали, а второй материал включает в себя никелевый сплав. ! 5. Паровая турбина (10) по п.1, в которой каждая лопатка включает в себя интегрированную накладку (154), причем интегрированные накладки, по меньшей мере, двух лопаток имеют ...

ИЗГОТОВЛЕНИЕ ИМПЕЛЛЕРА ТУРБОМАШИНЫ

... 1. Способ изготовления импеллера турбомашины, включающего ступицу и множество лопаток, с использованием порошкового материала в процессе послойного аддитивного наращивания, включающий: приложение энергии к порошковому материалу посредством высокоэнергетического источника, и отверждение порошкового материала, где по меньшей мере одну массивную часть ступицы облучают так, что порошковый материал затвердевает с образованием решеточной структуры, окруженной внешней монолитной структурой оболочки, охватывающей решеточную структуру.2. Способ по п. 1, дополнительно включающий:- нанесение первого слоя порошкового материала на поверхность цели;- облучение первого участка первого слоя порошкового материала при помощи высокоэнергетического источника и отверждение первого участка порошкового материала, причем первый участок соответствует первой области поперечного сечения импеллера турбомашины;- нанесение второго слоя порошкового материала на первый участок;- облучение второго участка второго слоя ...

ГЕРМЕТИЧНЫЙ ЭЛЕКТРОНАСОС С ПРИВОДОМ НА ПОСТОЯННЫХ МАГНИТАХ С КОРПУСОМ, ЗАЩИЩЕННЫМ ОТ КОРРОЗИИ

... 1. Герметичный электронасос с приводом на постоянных магнитах с корпусом, защищенным от коррозии, в частности для применения при перекачке токсичных, горючих и коррозионно-опасных жидкостей с высокой температурой, содержащий кожух насоса, треугольную опору, рабочее колесо, защитную оболочку, стационарный вал и герметичный электродвигатель, гдекожух насоса оснащен каналом потока, адаптированным для размещения рабочего колеса, впуском, выпуском и передним упорным кольцом, расположенным на внутренней поверхности кожуха насоса и в положении рядом с впуском; для совместного образования передним упорным кольцом и упорным подшипником, расположенным возле стороны впуска рабочего колеса, осевого упорного подшипника;треугольная опора установлена рядом с впуском кожуха насоса и проходит в осевом направлении в отверстие ступицы рабочего колеса для опоры конца стационарного вала;рабочее колесо расположено в кожухе насоса, при этом задний диск соединен с выступающей в осевом направлении частью внутреннего ...

СЕКЦИОНИРОВАННЫЙ РОТОР, ПАРОВАЯ ТУРБИНА, ВКЛЮЧАЮЩАЯ СЕКЦИОНИРОВАННЫЙ РОТОР, И СПОСОБ ИЗГОТОВЛЕНИЯ СЕКЦИОНИРОВАННОГО РОТОРА

... 1. Секционированный ротор, включающий:высокотемпературную секцию, включающую:первую секцию из жаропрочного материала,вторую секцию из жаропрочного материала исекционированную секцию из жаропрочного материала, сформированную из нескольких компонентов-подсекций из жаропрочного материала, причем секционированная секция из жаропрочного материала соединена с первой секцией из жаропрочного материала и со второй высокотемпературной секцией; ив котором высокотемпературные компоненты-подсекции независимо изготовлены из жаропрочного сплава на основе никеля.2. Секционированный ротор по п.1, в котором компоненты-подсекции из жаропрочного материала соединены друг с другом с помощью болтового соединения.3. Секционированный ротор по п.1, в котором компоненты-подсекции из жаропрочного материала изготовлены из, по существу, идентичных композиций.4. Секционированный ротор по п.1, в котором компоненты-подсекции из жаропрочного материала изготовлены из различных композиций.5. Секционированный ротор по п.1, ...

Сальниковое устройство паровой турбины

СТУПЕНЬ (РАБОЧИЙ ОРГАН) ПОГ�СТУПЕНЬ (РАБОЧИЙ ОРГАН) ПОГРУЖНОГО МНОГОРУЖНОГО МНОГОСТУПЕНЧАТОГО СТУПЕНЧАТОГО НАСОСА�АСОСА

... 1. Ступень (рабочий орган) погружного многоступенчатого насоса, содержащая рабочее колесо с ведущим и ведомым дисками, между которыми размещены лопатки, и направляющий аппарат, включающий в себя стакан с верхним и нижним дисками, между которыми размещены профилированные лопатки, отличающаяся тем, что она изготовлена из алюминиевого сплава либо из стали или чугуна с нанесенным на стальную или чугунную поверхность покрытием на основе алюминия, при этом на ступени сформировано керамическое покрытие AlОиз не менее чем двух слоев.2. Ступень (рабочий орган) погружного многоступенчатого насоса по п.1, отличающаяся тем, что первый - нижний - барьерный слой керамического покрытия AlОимеет толщину от 0,01 мкм до 4 мкм и высокую плотность - около 100%.3. Ступень (рабочий орган) погружного многоступенчатого насоса по п.1, отличающаяся тем, что суммарная толщина керамического покрытия AlОнаходится в диапазоне от 2 до 1000 мкм.4. Ступень (рабочий орган) погружного многоступенчатого насоса по п.1, отличающаяся ...

Dampfturbinenschaufel für ein Dampfkraftwerk

Turbine machine such as axial and radial compressor

The turbine machine has a hot-running component made of high-alloy heat-resistant steel, supported by a frame or casing part, and connected to it so that the supporting and fixing elements of the hot-running component can expand in all three axial directions, so that the center point, adjusted in the cold state, remains where it is. Thermal insulation (37) is fitted in the contact region of the supporting and fixing elements (25-27) which act with each other. The insulation withstands the mechanical and thermal loads from the machine.

METAL CERAMICS COMPOSITE ARTICLE AND A METHOD OF PRODUCING THE SAME

Self-induction centrifugal pump has all parts of pump coming into contact with pumped material made of sterile material

The pump has all the parts of the pump coming into contact with the material being pumped made of a material which meets the appropriate requirements for sterility, or coated with such a material The induction cover (2) and the flow channel housing (6), like all the other static components open to the functional cavities, are sealed off from each other.

METAL-CERAMICS COMPOSITE ARTICLE AND A METHOD OF PRODUCING THE SAME

Drive shafts

A composite drive shaft for a pump 1 for handling a corrosive and/or abrasive fluid and a method of manufacturing it are provided. The composite shaft comprises a first part 12 of a first metal / alloy resistant to the corrosive/abrasive fluid, connected to the pumping elements 3 of the pump 1. When in use, the first part 12 is actually or potentially in contact with the corrosive / abrasive fluid inside the pump 1. The first part 12 extends outside the pump body through a rotary seal 5. The shaft further comprises a second part 9 of a second cheaper metal/alloy, axially aligned with and abutting the first part 12 and connected to the extended length of the first part 12 by a butt friction weld. The second part 9 of the composite shaft is connectable to the power source for driving the pump 1. Both first and second metals/alloys have adequate mechanical properties to operate the pump reliably for a full working life.

Vacuum pump and vacuum pump set for evacuating a semiconductor processing chamber

A vacuum pump, a set of vacuum pumps and method for evacuating a semiconductor processing chamber is disclosed. The pump is configured for mounting to a semiconductor processing chamber to evacuate it to between 1 mbar and 5 X10-2 mbar. The pump comprises: a rotor having a plurality of angled blades 30 arranged along a helical path from an inlet 16 to an outlet 18, mounted within a stator having a plurality of perforated elements 50-53 intersecting the helical path. The perforations 38 allow molecules to travel along the helical path. The rotor is mounted on a magnetically levitated bearing. The perforated elements located towards an inlet of the pump comprise a transparency of more than 40% and the perforated elements located towards an outlet comprise a transparency of more than 30%. The set comprises the described pump, a roots blower and a primary vacuum pump. The method comprises attaching the described pump to a processing chamber by a conduit of less than 2m and remotely locating ...

Containment case for a gas turbine engine

A containment case for a gas turbine comprises a cylindrical outer casing 20; a coaxially arranged cylindrical inner skin 22 formed of a harder material than the outer casing joined to the inner surface of the cylindrical outer casing; and an array of ribs extending radially from the inner skin towards the axis. The outer casing 20 may be formed from a lightweight material such as aluminium, aluminium alloy or a composite of carbon or glass fibres in an epoxy resin. The inner skin 22 may be of steel, eg a stainless alloy, eg of 1-2mm thickness. The inner skin 22 may be located in a channel in the outer casing 20 and may be joined to the inner surface of the outer casing by a galvanic isolation layer (30, fig.3) eg of polyurethane or an elastomer which may be cured to bond the casing and skin together. The skin 22 may be an assembly of lap-jointed sheet sections. Each rib (32, figs.3a,3b) may be solid or hollow. The skin 22 or casing 20 may have dimples to increase stiffness. An acoustic ...

A geared gas turbine engine and a gearbox

Process components, containers, and pipes suitablefor containing and transporting cryogenic tempera ture fluids.

SELFSUCKING IN CENTRIFUGAL PUMP

PROZESSKOMPONENTEN, BEHÄLTER UND ROHRE, GEEIGNET ZUM AUFNEHMEN UND TRANSPORTIEREN VON FLUIDEN KRYOGENER TEMPERATUR

VACCUM PUMP

WET RUN CENTRIFUGAL PUMP AGGREGATE

METAL-CERAMICS COMPOSITE ARTICLE AND A PROCESS FOR MANUFACTURING THE SAME

Disclosed herein is a metal-ceramic composite article comprising a metallic member made of a precipitation hardening alloy and a ceramic member, wherein a projection formed at the ceramic member is fitted into a hole or a through hole formed at the metallic member and the metallic member of the composite article is hardened through precipitation hardening. A process for manufacturing such a metal-ceramics composite article is also disclosed. The manufacturing process comprises steps of: fitting a projection formed at a ceramic member into a hole formed at a metallic member made of a precipitation hardening alloy in a state in which precipitation-hardening is not carried out to form a metal-ceramics joint body, and subjecting the thus formed metal-cramics composite body to a precipitation hardening treatment to harden the metallic member.

TURBOMACHINE WITH AN INGESTION SHIELD AND USE OF THE TURBOMACHINE

Subject matter of the invention is a turbomachine as well as a use of the turbomachine. The turbomachine, for instance a gas turbine or a steam turbine, comprises a stator with at least one stator component, a rotor with at least one rotor component, at least one working fluid channel for channeling a working fluid for driving the rotor, wherein the working fluid channel is bordered by the stator component and the rotor component, and a cavity located downstream of the stator component and upstream of the rotor component in respect of the flow of the working fluid in the working fluid channel. Furthermore the turbomachine comprises at least one heat shield that is located in the cavity separating the cavity into a first cavity and a second cavity for reducing the working fluid ingress into the second cavity for protecting the stator component and/or the rotor component from an erosive attack of the working fluid.

CERAMIC-ENCAPSULATED THERMOPOLYMER PATTERN OR SUPPORT WITH METALLIC PLATING

A method for fabricating a ceramic component is disclosed. The method may comprise: 1) forming a polymer template having a shape that is an inverse of a shape of the ceramic component, 2) placing the polymer template in a mold; 3) injecting the polymer template with a ceramic slurry, 4) firing the ceramic slurry at a temperature to produce a green body, and 5) sintering the green body at an elevated temperature to provide the ceramic component.

ENGINE ASSEMBLY WITH MODULAR COMPRESSOR AND TURBINE

An engine assembly including an engine core with at least one internal combustion engine, a first casing, a turbine module including a second casing located outside of the first casing, and a compressor module including a third casing located outside of the first and second casings. The turbine shaft extends into the first casing, is rotationally supported by a bearings all contained within the first casing, and is free of rotational support within the second casing. The first casing may be a gearbox module casing through which the turbine shaft is in driving engagement with the engine shaft. A method of driving a rotatable load of an aircraft, and an engine assembly with a rotary engine core, a gearbox module with a first casing, and a second module including a second casing located outside of the first casing and detachably connected to the first casing are also discussed.

ANTI-COKING COATINGS, PROCESSES THEREFOR, AND HYDROCARBON FLUID PASSAGES PROVIDED THEREWITH

A method for providing an anti-coking coating system (22) on a surface at elevated temperatures when contacted by a hydrocarbon fluid, for example, a surface of an interior fuel passage within a fuel nozzle of a type utilized in gas turbine engines. The surface of the passage is rough as a result of the passage being part of a component manufactured by an additive manufacturing (AM) process. In addition, the passage may have a complex geometry of a type that can be fabricated with AM processes, for example, geometries comprising combinations of sharp bends and narrow cross-sections. The coating system (22) comprises at least one ceramic barrier layer and an outermost metallic layer, each of which is formed using a conformal vapor deposition process.

Plant for taking up and transporting a fluid of cryogenic temperature.

Burst Protection Device For A Turbo Machine

Die Erfindung betrifft eine Berstschutzvorrichtung für eine Strömungsmaschine (10) mit einem Schaufelradgehäuse (11), welche eine Achse (12) und ein in dem Schaufelradgehäuse (11) um die Achse (12) drehbar gelagertes Schaufelrad (13) aufweist, wobei die Berstschutzvorrichtung das Schaufelradgehäuse (11) zumindest im Bereich des Schaufelrades (13) in eine Umfangsrichtung des Schaufelrades (13) umschliesst und einteilig aus zumindest einem Berstschutzelement (1) gebildet ist, wobei das zumindest eine Berstschutzelement (1) aus einem Material mit einer Bruchdehnung von zumindest 30% besteht.

Process Components, Containers and Pipes Suitable For Containing and Transporting Cryogenic Temperature Fluids

Fan non-contact mechanical sealing structure

COMPRESSOR CASING RESISTANT TO TITANIUM FIRE, HIGH PRESSURE COMPRESSOR INCLUDING SUCH A CASING AND AIRCRAFT ENGINE INCLUDING SUCH A COMPRESSOR

METHOD FOR TREATMENT OF A PIECE COMPOSITE

Procédé de traitement d'une pièce composite (10) comportant un bouclier de protection métallique (12) fixé sur une âme (11) à l'aide d'un liant (14), en vue de séparer le bouclier de l'âme, comportant les étapes consistant à : a) soumettre le bouclier métallique à des contraintes de compression tendant à l'allonger, b) si nécessaire, chauffer la pièce ou la refroidir pour ramollir ou fragiliser le liant.

Device for pumping gas at high temperature

Ball bearing and lubricant combination for electrical motors, has properties to meet requirements of resisting critical temperature, where bearing is lubricated with grease for motor having specific viscosity of oil base

Combinaison d'un roulement et d'un lubrifiant destinée à servir de système de support pour un arbre tournant dans un système de ventilation d'évacuation de fumées et de chaleur et ayant des propriétés lui permettant de répondre à l'exigence de résistance à une température critique de 600°C pendant au moins 60 min., avec un arrêt de 2 min. après 15 min. d'exposition à la température critique, le roulement étant un roulement (bagues) en acier martensitique inoxydable avec une cage en acier ; et lequel roulement étant lubrifié avec une graisse ordinaire pour moteur électrique à viscosité d'huile de base de l'ordre de 50 à 200 cSt à 40°C.

ROTOR OF COMPRESSOR IN PARTICULAR OF RADIAL COMPRESSOR FOR TURBOSHAFT ENGINE

가스 터빈 연소기의 연료 노즐 및 그 제조 방법, 가스 터빈 연소기

... 내구성 및 강도 신뢰성이 우수한 가스 터빈 연소기의 연료 노즐을 제공한다. 가스 터빈 연소기의 연소실에 연료를 분출하는 가스 터빈 연소기의 연료 노즐이며, 상기 연료 노즐은, 당해 연료 노즐을 지지하는 베이스 플레이트와 야금적으로 일체화 접합되어 있고, 상기 연료 노즐과 상기 베이스 플레이트의 계면은, 표면에 있어서 융접 또는 브레이징에 의해 접합되고, 내부는 압접에 의해 접합되어 있는 것을 특징으로 한다.

Turbine external compartment, frame for turbine external compartment, and method of constructing frame for turbine external compartment

An object of the present invention is to provide a turbine external compartment, a frame for a turbine external compartment, and a method of constructing a frame for a turbine external compartment that can improve a flow of steam inside of the compartment and can enhance the rigidity of the compartment using a simple structure. A turbine external compartment according to the present invention is placed in a frame having a steel-plate reinforced concrete structure obtained by filling a space between a plurality of steel plates with concrete. The turbine external compartment includes a lower half part having a side plate part or an end plate part made of the steel plates that constitute the frame.

FAN BLADE HAVING CLOSED METAL SHEATH

A blade for use in a gas turbine engine is disclosed. In various embodiments, the blade includes a pressure side sheath and a suction side sheath secured to the pressure side sheath. The pressure side sheath and the suction side sheath are configured to form a continuous sheath that wraps around an interior section of the blade.

Exhaust-gas turbocharger

An exhaust-gas turbocharger (1) having a compressor housing (2); a turbine housing (3); and a bearing housing (4) which has a compressor-side flange (5) and which has a turbine-housing-side flange (6). The turbine-housing-side flange (6) is produced from a material which corresponds in terms of its mechanical and thermal properties to the material of the turbine housing (2).

AXIAL FLOW COMPRESSOR

An axial flow compressor includes: a rotor having a rotor vane; a first pressing member joined to one end surface of the rotor; a second pressing member joined to the other end surface of the rotor; a rotor shaft portion penetrating the first pressing member, the rotor and the second pressing member; and a nut which fixes the first pressing member and the second pressing member on the rotor shaft portion with the first pressing member and the second pressing member holding the rotor between. The rotor shaft portion is made of a material having a lower linear expansion coefficient than that of a material making at least a part of the rotor. The material making at least a part of the rotor may be aluminum or aluminum alloy.

Lightweight journal support pin

A journal support pin to support intermediate gears for use in gas turbine engine comprises a titanium body, and an outer surface outside of the titanium body having a surface hardness that is harder than the body. A gas turbine engine and a method of forming a journal support pin to support intermediate gears for use in gas turbine engine are also disclosed.

ALLOY MEMBER, METHOD FOR PRODUCING ALLOY MEMBER, AND PRODUCT WHICH USES ALLOY MEMBER

ЭЛЕКТРИЧЕСКИ ПРОВОДЯЩАЯ СТРУКТУРА ДЛЯ РЕАКТИВНОГО ДВИГАТЕЛЯ

Электрически проводящая структура для пропускания и отвода электрического тока от основного тела выходной направляющей лопасти в наружную опорную структуру содержит обшивку из металла, покрывающую переднюю кромку основного тела лопасти, и электрически проводящую прокладку из металла, содержащую контактную часть, имеющую такой размер, чтобы перекрывать одним концом обшивку, и часть в виде шайбы, предназначенную для ввода болта для затягивания в опорную структуру, при этом одно или больше соединений, выбранных из группы, содержащей сварку, точечную сварку, пайку, соединение с помощью электрически проводящей пасты и зажим, создают соединение между концом обшивки и контактной частью. Предотвращаются повреждения матричной смолы основного тела лопасти за счет безопасного отвода электрического тока при ударе в самолет молнии, ток обходит основное тело лопасти. 3 з.п. ф-лы, 8 ил.

Lagerträger aus Stahldrahtgestrick für eine Spaltrohrpumpe

Die Erfindung betrifft einen Lagerträger im vorderen, dem Pumpenlaufrad zugewandten Bereich eines Spalttopfes oder Spaltrohres einer Kreiselpumpe, wobei der buchsenförmige Lagerträger ausschließlich aus einem gepressten Drahtgestrick besteht, das als Filterring das Radiallager der Motorenwelle umgibt.

DIFFUSOR GUIDE VANE HAVING A DEVICE FOR OPEN-OR CLOSED-LOOP CONTROL OF A GAS TURBINE.

Drive shafts

A power transfer assembly

A power transfer assembly comprises a power turbine 35 constructed of a nickel alloy, a gear shaft 85 constructed of a low carbon carburized gear material, and a transition portion 80 between and welded to each of the power turbine and gear shaft. The nickel alloy may be welded to the transition portion by inertia welding and the low carbon carburized gear material may be welded to the transition portion by electron beam welding.

A composite vane for a turbine engine

PROCEDURE FOR THE PRODUCTION OF A WAVE FOR COMPRESSORS

WELDING METHOD, METAL COMPOSITION AND FROM IT MANUFACTURED ARTICLE

ARTICLE FROM METAL AND CERAMIC(S) AND METHOD TO ITS PRODUCTION.

CENTRIFUGAL COMPRESSOR AND SHROUD THEREFORE

The shroud can have a wall curved radially outwardly from an axially oriented inlet to an outlet end, a structural member having a flange at the outlet end, and an insert of Greek Ascoloy exposed on an inner face of the wall.

HIGH TEMPERATURE, RADIATION-RESISTANT, FERRITIC-MARTENSITIC STEELS

This disclosure describes new high temperature, radiation-resistant, ferritic-martensitic steel compositions. The new steels generally contain 9.0-12.0 wt. % Cr, 0.001-1.0 wt. % Mn, 0.001-2.0 wt. % Mo, 0.001-2.5 wt. % W, and 0.1-0.3 wt. % C, with the balance being primarily Fe. More specifically, steels having from 10.0-12.0 wt. % Cr are considered particularly advantageous. Small amounts of N, Nb, V, Ta, Ti, Zr, and B may or may not also be present, depending on the particular embodiment. Impurities may be present in any embodiment, in particular impurities of less than 0.01 wt. % S, less than 0.04 wt. % P, less than 0.04 wt. % Cu, less than 0.05 wt. % Co, and less than 0.03 wt. % As are contemplated. Examples of these steels exhibit improved fracture toughness and reduced thermal creep and swelling.

METAL LEADING EDGE PROTECTIVE STRIPS, CORRESPONDING AIRFOIL AND METHOD OF PRODUCING

A metallic leading edge protective strip (12) adapted to provide impact protection for a leading edge of an airfoil of a turbomachine. The protective strip (12) is formed of a stainless steel or a nickel-based alloy and is denser and provides increased strength and elasticity characteristics as compared to an identical protective strip formed of a titanium-based alloy. The protective strip is particularly suitable for use with composite blades (10) and allows for thinner airfoils, thereby improving engine efficiency. Corresponding airfoil and method of producing such airfoil are also provided.

HIGH TEMPERATURE RADIATsIONNOSTOIKIE FERRITE - MARTENSITNYE STEEL

Austenite-based heat-resistant steel, and turbine component

Turbocharger

To provide a turbocharger whose lifetime is long, which is capable of inexpensively and precisely performing nozzle vane angle synchronous control by using inexpensive and highly wear resistant components in a link mechanism for driving a rotation mechanism of nozzle vanes of an adjustable nozzle mechanism. As pins fixedly arrayed in a ring plate rotatably supported on the turbocharger, that set an angle of the nozzle vanes for controlling an amount of exhaust gas for rotating a turbine rotor, each pin in which a hard coating with a thickness of approximately 2 [mu]m which is formed of Al, Cr, Si, and N by physical vapor deposition is formed onto an austenitic stainless steel as a base material, is used.

GAS IMPULSE DEVICE AT HIGH TEMPERATURE

Water pump turbine made of sintered alloy

PROCESSING METHOD FOR CONSUMABLE ELECTRODE

ROTOR OF COMPRESSOR IN PARTICULAR OF RADIAL COMPRESSOR FOR TURBOSHAFT ENGINE

VACUUM PUMP

ROTOR WINDAGE NUT

PURPOSE: A rotor windage nut is provided to improve the design of the rear part windage nut used with bolts that tie sections of a rotor or stator assembly together. CONSTITUTION: A nut(44) for a rotor fastening bolt has a nut main body having a center hole(46) with a screw thread in it, a first peripheral edge surface(56) on one side of the center hole extending in the both side directions by threading over the center hole and to constitute a pair of wing parts(52,54) and second and third peripheral edge surfaces(62,64) including a pair of supporting wall parts(68,70) to support the wing parts, the support wall parts of which are respectively connected to both ends of the first peripheral edge surface and which are connected to each other on a roundish surface(66) on the opposite side of the center hole. © KIPO 2002 ...

고온, 방사선 저항성, 페라이트-마르텐사이트 강

... 본 개시는, 새로운, 고온, 방사선 저항성, 페라이트-마르텐사이트 강 조성들을 설명한다. 새로운 강들은 일반적으로, 9.0-12.0 중량%의 Cr, 0.001-1.0 중량%의 Mn, 0.001-2.0 중량%의 Mo, 0.001-2.5 중량%의 W, 및 0.1-0.3 중량%의 C를, 주로 Fe인 나머지와 함께 함유한다. 더욱 구체적으로, 10.0-12.0 중량%의 Cr을 갖는 강들은, 특히 유리한 것으로 고려된다. 소량의 N, Nb, V, Ta, Ti, Zr, 및 B가, 특정 실시예에 의존하여, 또한 존재하거나 존재하지 않을 수 있을 것이다. 불순물들이, 임의의 실시예에서 존재할 수 있으며, 구체적으로, 0.01 중량% 미만의 S, 0.04 중량% 미만의 P, 0.04 중량% 미만의 Cu, 0.05 중량% 미만의 Co, 및 0.03 중량% 미만의 As의 불순물들이 예상된다. 이러한 강들의 예들은, 개선된 파괴 인성 그리고 감소된 열적 크리프 및 팽창을 보인다.

ROTATION UNIT OF ROTARY MACHINE AND METHOD FOR MANUFACTURING ROTATION UNIT OF ROTARY MACHINE

According to one aspect of the present invention, a rotation unit of a rotary machine comprises: a base unit of which a portion of a surface is formed to be a floor surface of a fluid passage; a plurality of blade units formed to protrude from the base unit; a plurality of shroud segment support units connected to the blade unit and formed to be extended in a direction in parallel to the floor surface of the fluid passage; a shroud segment disposed between the shroud segment support units adjacent to each other to be bonded; and a first reinforcement unit disposed in a boundary portion of the blade unit and the shroud segment support unit. Provided is the rotation unit of a rotary machine wherein a distance from a center line in a protruding direction of the blade unit to an end part of the shroud segment support unit is larger than the maximum distance from the center line in the protruding direction of the blade unit to the end part of the first reinforcement unit. COPYRIGHT KIPO 2016 ...

HIGH ELASTIC MODULUS SHAFTS AND METHOD OF MANUFACTURE

Hermetic motor and gas booster

A fuel booster operable to compress a combustible fuel, the fuel booster comprising a compressor housing, a compressor rotor, and a seal assembly coupled to the compressor housing. The seal assembly and the compressor housing cooperate to at least partially define a hermetically sealed compressor chamber. A motor housing is coupled to the seal assembly. The motor housing and seal assembly cooperate to at least partially define a motor chamber that is sealed from the compressor chamber to prevent fluid flow therebetween. The fuel booster also includes a motor having a motor rotor and a motor stator. The motor rotor and the compressor rotor are contained within the compressor chamber. The motor rotor includes a cylindrical surface. The motor stator substantially surrounds the cylindrical surface and is contained within the motor chamber.

Burst Protection Device For A Turbo Machine

A burst protection device for a turbo machine having a rotor housing, which includes an axle and a rotor that is rotatably mounted about the axle in the rotor housing. The burst protection device surrounds the rotor housing at least in the region of the rotor in a circumferential direction of the rotor and is formed in one part of at least one burst protection element. The at least one burst protection element is a material having an elongation at break of at least 30%.

Compressor blade or vane having an erosion-resistant hard material coating

A compressor blade for a gas turbine is provided. The compressor blade has a blade substrate that consists of a metal alloy and has an aluminum diffusion zone on a surface of the blade substrate. In addition, the compressor blade has a hard material coating provided on the surface of the blade substrate. A compressor that has a compressor blade and a method of producing such a compressor blade is also provided.

Casing

A containment case for a gas turbine including: a cylindrical outer casing extending about an axis and having a radially outer and a radially inner surface; a coaxially arranged cylindrical inner skin formed of a harder material than the outer casing joined to the inner surface of the cylindrical outer casing; and an array of ribs extending radially from the inner skin towards the axis. The case for can have the coaxially arranged cylindrical inner skin formed of a harder material than the outer casing joined to the inner surface of the cylindrical outer casing by a galvanic isolation layer.

AUSTENITIC STAINLESS STEEL ALLOYS AND TURBOCHARGER KINEMATIC COMPONENTS FORMED FROM STAINLESS STEEL ALLOYS

An austenitic stainless steel alloy and turbocharger kinematic components are provided. An austenitic stainless steel alloy includes, by weight, about 23% to about 27% chromium, about 18% to about 22% nickel, about 0.5% to about 2.0% manganese, about 1.2% to about 1.4% carbon, about 1.6% to about 1.8% silicon, about 0% to about 0.5% molybdenum, sulfur in an amount of less than about 0.01%, phosphorous in an amount of less than about 0.04%, and a balance of iron, and other inevitable/unavoidable impurities that are present in trace amounts. The turbocharger kinematic components are made at least in part using this stainless steel alloy.

Airfoil Conformable Membrane Erosion Coating

A coating membrane for a component of a gas-turbine engine includes a solid membrane having a metallic foil or a polymeric film, and having a thickness and at least one kerf extending through the thickness to define a kerf pattern such that the solid membrane can be applied to a compound-curved surface. Also disclosed are a coated component coated with the membrane, and a method for producing a coated component with the membrane. 1. A coating membrane for a component of a gas-turbine engine , comprising:a solid membrane comprising a polymeric film having a thickness and at least one kerf extending through the thickness to define a kerf pattern such that the solid membrane can be applied to a compound-curved surface.24-. (canceled)5. The coating membrane of claim 1 , wherein the polymeric film is selected from the group consisting of films of epoxy resin claim 1 , polyphenylene ether claim 1 , polyurethane and combinations thereof.6. The coating membrane of claim 1 , wherein the polymeric film is an elastomeric film.7. The coating membrane of claim 1 , wherein the polymeric film is fiber reinforced.8. The coating membrane of claim 1 , wherein the solid membrane has a thickness of between about 0.003 and about 0.030 inches.9. The coating membrane of claim 1 , wherein the at least one kerf has a kerf width of between 0.002 and 0.006 inches.10. The coating membrane of claim 1 , wherein the kerf pattern defines a reticulated kerf pattern in a monolithic membrane structure.11. The coating membrane of claim 1 , wherein the kerf pattern is a recurring pattern of intersecting kerfs.12. The coating membrane of claim 1 , wherein the kerf pattern is defined by the at least one kerf in a spiral pattern.13. A coated gas-turbine engine component claim 1 , comprising:a surface of a gas-turbine engine component;a solid membrane comprising a polymeric film having a thickness and at least one kerf extending through the thickness to define a kerf pattern, wherein the solid membrane is ...

ЛОПАТКА СТАТОРА С ИЗМЕНЯЮЩИМСЯ УГЛОМ УСТАНОВКИ, ГАЗОТУРБИННЫЙ ДВИГАТЕЛЬ, СОДЕРЖАЩИЙ ТАКУЮ ЛОПАТКУ, И СПОСОБ РЕМОНТА ТАКОЙ ЛОПАТКИ

Лопатка статора с изменяющимся углом установки, установленная в картере газотурбинного двигателя, содержит перо, площадку, поворотный шкворень, накладку с диском и, по меньшей мере, одну стопорную лапку. Диск накладки установлен одной стороной на площадке и опирается другой стороной непосредственно или посредством втулки на стенку картера. Накладка является неподвижной во вращении относительно оси поворотного шкворня. Каждая стопорная лапка жестко соединена с диском и взаимодействует с комплементарной поверхностью, такой как лыска, выполненной на площадке. Поворотный шкворень содержит кольцеобразный хомут, образующий подшипник, а в диске накладки выполнено центральное отверстие, достаточно большое, чтобы обеспечить прохождение накладки вдоль поворотного шкворня. Другое изобретение группы относится к газотурбинному двигателю, содержащему, по меньшей мере, один ряд лопаток статора с изменяющимся углом установки, установленных в картере и оборудованных указанной выше накладкой, взаимодействующей ...

СТОПОРНОЕ КОЛЬЦО ЛОПАТОК СТАТОРА ОСЕВОЙ ТУРБОМАШИНЫ И ОСЕВАЯ ТУРБОМАШИНА

Группа изобретений относится к статору компрессора низкого давления осевой турбомашины. Статор содержит кольцевой ряд лопаток статора 26, имеющих радиальные концы, проходящие через отверстия 36 внутреннего кожуха 28, и содержащие радиальные крепежные пазы 38. Пазы 38 имеют конусность, образованную крюками 44. Статор содержит кольцо 30 для закрепления лопаток 26 на кожухе 28. Кольцо 30 изогнуто по окружности для его установки в крепежные пазы 38 и имеет форму полосы с дугообразным поперечным профилем, который находится в контакте с конусами и опирается на них так, чтобы кольцо 30 удерживалось внутри пазов 38. Кожух 28 содержит кольцевой слой истираемого материала 32, который окружает кольцо таким образом, чтобы блокировать кривизну дугообразного профиля кольца 30 с целью предотвращения расцепления его контакта с конусами пазов 38. Группа изобретений направлена на улучшение закрепления между лопаткой и кольцом с дугообразным поперечным профилем в осевой турбомашине, а также на увеличение ...

КОНСТРУКЦИЯ СТЕНКИ С ШУМОИЗОЛИРУЮЩИМИ СВОЙСТВАМИ И ГАЗОТУРБИННАЯ УСТАНОВКА, СНАБЖЕННАЯ ТАКОЙ СТЕНКОЙ

... 1. Конструкция стенки (30) с шумопоглощающими изолирующими свойствами, в частности, для воздухозаборного коллектора газотурбинной установки (10), содержащая первое средство (31, 33) для механического крепления внешнего листа (32), герметично разделяющего пространства с обеих сторон стенки, а также второе средство (25, 34-36) для крепления шумоизолирующего материала между пространствами с обеих сторон стенки, с помощью которого указанное второе средство (25, 34-36) крепится к первому средству (31, 33), отличающаяся тем, что указанное второе средство (25, 34-36) расположено внутри первого средства (31, 33).2. Конструкция стенки по п.1, отличающаяся тем, что первое средство включает в себя несколько двутавровых балок (31), установленных на одной общей плоскости своими ребрами (31а) перпендикулярно данной общей плоскости, внешний лист (32), прикрепленный к первому фланцу (31b) двутавровых балок (31), при этом вышеупомянутое второе средство включает в себя пространство между двутавровыми балками ...

СТОПОРНОЕ КОЛЬЦО ЛОПАТОК ДЛЯ ВНУТРЕННЕГО КОЖУХА КОМПРЕССОРА ОСЕВОЙ ТУРБОМАШИНЫ

... 1. Статор осевой турбомашины (2), в частности компрессора (4, 6), содержащий:кожух (28) с кольцевым рядом отверстий (36),кольцевой ряд лопаток статора (26), проходящих, по существу, в радиальном направлении через отверстия (36), при этом каждая лопатка содержит крепежный паз (38) и перо лопатки, предназначенное для нахождения в потоке турбомашины, причем каждый крепежный паз (38) имеет конусное входное отверстие и расположен на противоположной стороне пера лопатки по отношению к отверстию (36), через которое проходит соответствующая лопатка (26),по меньшей мере одно стопорное кольцо (30) для лопаток (26), установленное в пазы, при этом кольцо (30) имеет форму полосы с дугообразным поперечным профилем, который находится в контакте с конусом, таким образом, удерживая кольцо (30) в пазах (38),отличающийся тем, чтокожух (28) содержит слой истираемого материала (32) окружает поперечный профиль кольца (30) таким образом, чтобы блокировать кривизну дугообразного поперечного профиля, предотвращая ...

Lüfterrad aus Kunststoff

Verdichterschaufel für ein Flugzeugtriebwerk

Eine Verdichterschaufel für ein Flugzeugtriebwerk umfasst einen Schaufelkern (1) aus einem Faserverbundwerkstoff und eine metallische Umhüllung (2). Die Umhüllung ist mehrteilig aufgebaut und besteht aus einem saugseitig und einem druckseitig mit dem Schaufelkern über ein Metallgewebe (6) verbundenen Deckblech (4, 5), wobei die beiden Deckbleche an der aerodynamisch geformten Führungskante der Verdichterschaufel über ein Führungskanten-Formstück (3) fest miteinander verbunden sind. In Abhängigkeit von der unterschiedlichen Belastung auf der Saug- und auf der Druckseite sind die Fügenähte (8, 9) zueinander versetzt angeordnet und die Materialstärken der Umhüllungsteile aufeinander abgestimmt.

Device for suppression of airborne noise, e.g. in turbochargers of internal combustion engines, has deep-drawn parts which are welded together to form one unit and can be manufactured from plastic or steel

Noise suppression device suppresses airborne noise of simultaneously existing middle and high frequency components in flow noises of piping systems, e.g. in turbochargers of internal combustion engines. The device consists of deep-drawn parts that are welded together to form one unit, and can be manufactured from plastic or steel.

External rotor motor especially as ventilator drive, has inner stator arranged in pot-shaped housing and gas-tightly separated from outer rotor

An external rotor motor has a fixed inner stator and an outer rotor, rotatable about the inner stator. The inner stator (4) is arranged in a pot-shaped housing and is separated in a gas tight manner from the outer rotor (6). The pot-shaped housing (8) is made thermally insulated and/or the inner stator is provided with a cooling device.

Turbine frame assembly and method of designing turbine frame assembly

A structural case assembly comprises a frame, fairing and heat shield. The frame is fabricated from a material having a temperature limit below an operating point of a gas turbine engine, and comprises an outer ring, an inner ring and a plurality of struts extending therebetween to define a flow path. The fairing is fabricated from a material having a temperature limit above the operating point of the gas turbine engine, and comprises a ring-strut-ring structure that lines the flow path. The heat shield is disposed between the frame and the fairing to inhibit radiant heat transfer therebetween. The heat shield may block all line-of-sight between the fairing and the frame. The frame may be produced from CA-6NM alloy. A method for designing a turbine case structure includes selecting a frame material having a temperature limit below the operating point of an engine.

Nanocrystalline bainitic steels, shafts, gas turbine engines, and methods of manufacturing nanocrystalline bainitic steels

PUMP IMPELLER.

CAMP CARRIER OUT STAHLDRAHTGESTRICK FOR A GAP PIPELINE MOUNTED PUMP

HEAT RESISTANT HTNT NI-CR-MO-V STEEL FOR AN INTEGRATED ROTOR

TURBINE ENGINE BEARING USED AS A STATIC ELECTRICITY LEAK PATH

A gas turbine engine with a rotor having a shaft mounted to the engine with a plurality of electrically insulating bearings is provided. The electrically insulating bearings are coupled to the shaft to support the rotor in the engine. There is at least one electrically conductive bearing coupled to the shaft and that further support the rotor in the engine. An electrically conductive path is defined between the rotor and an electrical ground of the engine. The electrically conductive path is defined through the electrically conductive bearing to reach the electrical ground of the engine. A method for electrostatically discharging a rotor supported in the gas turbine engine is also provided.

ANTI-COKING COATINGS, PROCESSES THEREFOR, AND HYDROCARBON FLUID PASSAGES PROVIDED THEREWITH

A method for providing an anti-coking coating system (22) on a surface at elevated temperatures when contacted by a hydrocarbon fluid, for example, a surface of an interior fuel passage within a fuel nozzle of a type utilized in gas turbine engines. The surface of the passage is rough as a result of the passage being part of a component manufactured by an additive manufacturing (AM) process. In addition, the passage may have a complex geometry of a type that can be fabricated with AM processes, for example, geometries comprising combinations of sharp bends and narrow cross-sections. The coating system (22) comprises at least one ceramic barrier layer and an outermost metallic layer, each of which is formed using a conformal vapor deposition process.

TURBO-MACHINE IMPELLER MANUFACTURING

A turbo-machine impeller (120) is described, comprising a plurality of solidified layers formed by solidified powder material. The impeller comprises at least one portion made of a lattice structure (L) surrounded by a solid skin structure (S).

TURBOMACHINE WITH AN INGESTION SHIELD AND USE OF THE TURBOMACHINE

A turbomachine, for instance a gas turbine or a steam turbine, has a stator with at least one stator component, a rotor with at least one rotor component, at least one working fluid channel for channeling a working fluid for driving the rotor, wherein the working fluid channel is bordered by the stator component and the rotor component, and a cavity located downstream of the stator component and upstream of the rotor component in respect of the flow of the working fluid in the working fluid channel. At least one heat shield is located in the cavity separating the cavity into a first cavity and a second cavity for reducing the working fluid ingress into the second cavity for protecting the stator component and/or the rotor component from an erosive attack of the working fluid.

TURBINE ROTOR BLADE

A turbine rotor blade which is enhanced in erosion resistance and reduced in stress corrosion cracking sensitivity is provided. When a blade tip end of the turbine rotor blade is hardened by heat treatment, hardness at an outer circumferential side in a radial direction is made higher than hardness at an inner circumferential side, and thereby, enhancement in erosion resistance and reduction in stress corrosion cracking sensitivity are made compatible with each other all over in a blade length direction.

INTERLOCKED PLATED POLYMERS

A plated polymer component is disclosed. The plated polymer component may comprise a polymer substrate having an outer surface, a metal plating attached to the outer surface of the polymer substrate, and at least one interlocking feature connecting the polymer substrate and the metal plating. The interlocking feature may improve the interfacial bond strength between the polymer substrate and the metal plating.

BLADE RETAINING RING FOR AN INTERNAL SHROUD OF AN AXIAL-FLOW TURBOMACHINE COMPRESSOR

A stator of a low-pressure compressor of an axial-flow has an annular row of stator blades including radial extremities which pass through the openings of an internal shroud, and which include radial retaining slots having tapers formed by hooks. The stator also includes a ring for retaining the blades on the internal shroud. The ring is curved circumferentially in order to be inserted into a plurality of retaining slots and exhibits the form of a strip having an arched transversal profile which is in abutment against the tapers, in such a way as to maintain the ring in the interior of the slots. The shroud includes an annular layer of abradable material made from silicone, which encloses the ring in such a way as to block the curvature of the arched profile of the ring in order to prevent it from disengaging from the tapers of the slots.

STEEL SOFT WALL FAN CASE

A steel soft wall fan case assembly according to one embodiment configured with a thin-walled steel support structure shell including a plurality of annular axial walls of thin sheet metal reinforced by a plurality of rings interconnecting axially adjacent annular axial walls. The steel support structure shell is structurally integrated with honeycomb materials and an annular metallic inner wall. A fabric containment layer may be wrapped around one of the annular axial walls of the steel support structure shell.

DEHYDROGENATION PROCESSING METHOD FOR TURBINE BLADES

Reinforcing Element for Use with a Ventilator Hub

In order to provide a ventilator hub ( 1 ) having means ( 2, 3 ) for connecting to a ventilator spindle and an essentially cylindrical fastening section ( 4 ) having radial adapters ( 6 ) for a number of ventilator blades, whereby the fastening section ( 4 ) has an inner casing surface ( 5 ) that ensures fastening of the ventilator blades with sufficient tensile strength, even at high temperatures, such as they can occur in tunnel fires, without thereby having an undesirably high mass, it is proposed to provide the ventilator hub with an essentially annular, closed reinforcement element ( 7 ) having means ( 10 ) for fastening the ventilator blades with high tensile strength, that is designed essentially separate from the fastening section ( 4 ).

Wall structure with noise damping insulation properties and gas turbine with such a wall structure

A wall structure is provided with noise damping insulation properties, for an air intake manifold of a gas turbine. The wall structure includes a first structure for mechanically supporting an outer sheet, which separates the spaces on both sides of the wall in an airtight manner, and further includes a second structure for establishing noise damping insulation between the spaces on both sides of the wall. The second structure is secured to the first structure. A gas turbine including the wall structure is also provided.

Casing

A containment case for a gas turbine including: a cylindrical outer casing extending about an axis and having a radially outer and a radially inner surface; a coaxially arranged cylindrical inner skin formed of a harder material than the outer casing joined to the inner surface of the cylindrical outer casing; and an array of ribs extending radially from the inner skin towards the axis. The case for can have the coaxially arranged cylindrical inner skin formed of a harder material than the outer casing joined to the inner surface of the cylindrical outer casing by a galvanic isolation layer.

Turbocompressor rotor and method for producing the same

A turbocompressor rotor for a turbocompressor for compressing process gas has a rotor body which makes contact with the process gas and which is produced entirely from a stainless steel material including 0.3 to 1.2% carbon and 12 to 19% chromium, wherein the steel material includes the alloy X39CrMo17-1.9. A process for producing such a turbocompressor rotor by casting includes manufacturing a casting model corresponding to the geometry of the rotor body by rapid technology and producing a casting mold using the casting model, or manufacturing a casting mold corresponding to the negative geometry of the rotor body by rapid technology, introducing the liquid steel material into the casting mold to form a cast workpiece as the rotor body, and finishing the turbocompressor rotor with the rotor body.

Mechanical fastening system for rotating or stationary components

A mechanical fastening system for rotating or stationary components such as turbine or compressor blades on a rotor or a shaft or a casing, respectively, is disclosed. The system includes a circumferential mounting groove adapted for receiving root sections of the rotating or stationary components as well as intermediate fastening components for fixation of the components in equidistance positions. The intermediate fastening components comprise at least an upper platform and at least a side plate having a groove for mounting on said rotor. The intermediate fastening components are made of a plurality of distinct parts of different materials from which at least one clamping part is made of or comprises a shape memory alloy or similar material having a pseudo-elasticity behavior.

Fuel Nozzle of Gas Turbine Combustor and Manufacturing Method Thereof, and Gas Turbine Combustor

To provide a fuel nozzle for a gas turbine combustor, offering favorable durability and strength reliability. In a fuel nozzle for a gas turbine combustor, jetting fuel into a combustion chamber of the gas turbine combustor, the fuel nozzle is metallurgically and integrally bonded with a base plate that supports the fuel nozzle, and an interface between the fuel nozzle and the base plate includes a surface in which bonding is performed by a fusion joint or a brazing joint and an inside part in which bonding is performed by pressure bonding.

COMPRESSOR BLADE OR VANE HAVING AN EROSION-RESISTANT HARD MATERIAL COATING

A compressor blade for a gas turbine is provided. The compressor blade has a blade substrate that consists of a metal alloy and has an aluminum diffusion zone on a surface of the blade substrate. In addition, the compressor blade has a hard material coating provided on the surface of the blade substrate. A compressor that has a compressor blade and a method of producing such a compressor blade is also provided. 111-. (canceled)12. A compressor blade or vane for a gas turbine , the compressor blade or vane comprising:a blade or vane substrate;a metal alloy;an aluminum diffusion zone on a surface of the blade or vane substrate as a result of the diffusion of aluminum into a surface on the blade or vane substrate; anda hard material coating arranged on the surface of the blade or vane substrate .13. The compressor blade or vane of claim 12 , wherein the hard material coating comprises TiN claim 12 , TiAlN claim 12 , AlTiN claim 12 , CrN as single-layer or multi-layer ceramics or comprises TiN claim 12 , TiAlN claim 12 , AlTiN claim 12 , CrN as single-layer or multi-layer ceramics.14. The compressor blade or vane of claim 12 , wherein the aluminum diffusion zone has a thickness of 10 to 30 micrometers.15. The compressor blade or vane of claim 12 , wherein the aluminum diffusion zone has an aluminum proportion of 0.05 to 0.2% by weight.16. The compressor blade or vane of claim 12 , wherein the metal alloy is a creep-resistant steel.17. A compressor for a gas turbine and having a plurality of compressor blades or vanes claim 12 , wherein at least one compressor blade or vane of the plurality of compressor blades or vanes is designed as claimed in .18. The compressor of claim 12 , wherein the plurality of compressor blades or vanes are arranged in a plurality of rows claim 12 , wherein each row of the plurality of rows has a plurality of compressor blades or vanes arranged transversely to a main direction of flow of the compressor claim 12 , and wherein the plurality of ...

COMPOSITE AIRFOIL METAL LEADING EDGE ASSEMBLY

An airfoil assembly () comprises a composite airfoil () having a leading edge () and a trailing edge (), a pressure side () extending between the leading edge and the trailing edge, a suction side () extending between the leading edge and the trailing edge, opposite the leading edge, a metallic leading edge assembly () disposed over the composite air-foil, the metallic leading edge assembly including a high density base (), the metallic leading edge assembly also including a nose () disposed over the base, an adhesive bond layer disposed between the composite airfoil and the metallic leading edge assembly. 1. An airfoil assembly , comprising: a leading edge and a trailing edge;', 'a pressure side extending between said leading edge and said trailing edge;', 'a suction side extending between said leading edge and said trailing edge, opposite said leading edge;, 'a composite foil havinga metallic leading edge assembly disposed over said composite foil;said metallic leading edge assembly including a high density base;said metallic leading edge assembly also including a nose disposed one of over or under said base;an adhesive bond layer disposed between the composite foil and the metallic leading edge assembly.2. The airfoil assembly of claim 1 , wherein said high density base is formed of a uniform thickness.3. The airfoil assembly of claim 1 , wherein said high density base is formed of a varying thickness.4. The airfoil assembly of claim 1 , said base being welded to said nose.5. The airfoil assembly of claim 1 , said base being bonded to said nose.6. The airfoil of claim 1 , said base having first and second legs which are longer than side walls of said nose.7. The airfoil of claim 1 , wherein said metal leading edge assembly is formed of a single construction in a radial direction.8. The airfoil of claim 1 , wherein said metal leading edge assembly is formed of multiple segments in a radial direction.9. The airfoil of claim 1 , wherein said nose is bonded to said ...

EXPANSION JOINT AND METHODS OF ASSEMBLING THE SAME

An expansion joint for use between a turbine duct and a diffuser duct includes a first flange coupled to the turbine duct, a second flange coupled to the diffuser duct, and a flexible element positioned between and coupled to the first flange of the turbine duct and the second flange of the diffuser duct. The flexible element defines a trough for receiving a liquid therein. The trough includes a drain pipe configured to channel the liquid away from the trough. 1. An expansion joint for use between a turbine duct and a diffuser duct , said expansion joint comprising:a first flange coupled to the turbine duct;a second flange coupled to the diffuser duct; anda flexible element positioned between and coupled to said first flange of the turbine duct and said second flange of the diffuser duct, said flexible element defining a trough for receiving a liquid therein, said trough comprising a drain pipe configured to channel the liquid away from said trough.2. The expansion joint in accordance with claim 1 , wherein said flexible element comprises a plurality of flexible seals coupled to said first flange and said second flange.3. The expansion joint in accordance with claim 2 , wherein each flexible seal of said plurality of flexible seals is formed from a single sheet component and comprises a curved profile shape comprising at least one bend radius having a radius selected to reduce a stress and strain of said each flexible seal.4. The expansion joint in accordance with claim 3 , wherein said each flexible seal comprises a plurality of apertures therein.5. The expansion joint in accordance with claim 2 , wherein said plurality of flexible seals comprises a first layer of flexible seals forming a first complete circumferential array claim 2 , and a second layer of flexible seals forming a second complete circumferential array claim 2 , wherein each flexible seal of said second layer of flexible seals overlaps a radial seam defined between adjacent flexible seals of said ...

COMPOSITE AIRFOIL WITH METAL STRENGTH

A laminated composite airfoil assembly includes a first lamina formed of a material including metal fibers, and at least a second lamina formed of a material including at least one of metal fibers intermixed with carbon fibers, only metal fibers, only carbon fibers, a substrate including metal fibers, a substrate including carbon fibers, and combinations thereof. 1. A laminated composite airfoil assembly comprising:a first lamina formed of a material comprising metal fibers; and wherein the airfoil assembly comprises a plurality of laminae formed from materials including the first lamina and the second lamina, and', 'wherein a subset of laminae of the plurality of laminae are formed from material comprising carbon fibers, the airfoil assembly further comprising metal threads extending into the subset of laminae of the plurality of laminae., 'at least a second lamina formed of a material comprising at least one of metal fibers intermixed with carbon fibers, only metal fibers, only carbon fibers, a substrate comprising metal fibers, a substrate comprising carbon fibers, and combinations thereof,'}2. The airfoil assembly of claim 1 , wherein the material of the first lamina is a pre-preg material claim 1 , and wherein the material of the second lamina is a pre-preg material.3. The airfoil assembly of claim 2 , wherein the pre-preg material of the first lamina comprises the metal fibers oriented in a first direction and the pre-preg material of the second lamina comprises the carbon fibers oriented in a second direction.4. The airfoil assembly of claim 1 , wherein the carbon fibers are unidirectional carbon fibers oriented in a first direction and the metal fibers crisscross the carbon fibers in at least one of the first lamina and the second lamina.5. The airfoil assembly of claim 1 , wherein the metal threads extend into the subset of the plurality of laminae in a 2.5D configuration.6. The airfoil assembly of claim 1 , wherein the metal threads extend into the subset ...

METHOD OF CHROMIZING AN ARTICLE INCLUDING INTERNAL PASSAGES OF THE ARTICLE

A method for chromizing an article includes applying a slurry to an article. The slurry has active chromium and a residue-removal agent. The method also includes heating the article and slurry to diffuse chromium from the slurry into the article. The heating leaves a residue on the article with the residue-removal agent. The heating also includes removing the residue-removal agent to thus remove the residue from the article, using a cleaning solution. A method for chromizing parts and a method of cleaning a chromized part are also disclosed. 1. A method for chromizing an article , the method comprising:applying a slurry to an article, the slurry including active chromium and a residue-removal agent;heating the article and slurry to diffuse chromium from the slurry into the article, the heating leaving a residue on the article with the residue-removal agent; andremoving the residue-removal agent, to thus remove the residue from the article, using a cleaning solution.2. The method of claim 1 , wherein the article includes internal passages claim 1 , and the residue is in the internal passages.3. The method of claim 2 , wherein the slurry flows into the internal passages.4. The method of claim 2 , wherein the amount of solids in the slurry is greater than about 25 percent by weight of the slurry.5. The method of claim 2 , wherein the amount of solids in the slurry is between about 50 and about 75 percent by weight of the slurry.6. The method of claim 1 , wherein the residue-removal agent is inert with respect to the article and the slurry in the heating.7. The method of claim 1 , wherein the residue-removal agent includes silica.8. The method of claim 1 , wherein the residue-removal agent forms a matrix during the heating claim 1 , the matrix trapping the residue.9. The method of claim 8 , wherein the slurry contains an amount of residue-removal agent sufficient to form a continuous matrix of residue-removal agent during the heating step.10. The method of claim 9 , ...

GEARED GAS TURBINE ENGINE AND A GEARBOX

A gas turbine engine comprises a gearbox comprises a sun gear, an annulus gear, a plurality of planet gears and a carrier. The sun gear meshes with the planet gears and the planet gears mesh with the annulus gear. The planet gear carrier comprising a first ring, a second ring spaced axially from the first ring and a plurality of circumferentially spaced axles extending axially between the first ring and the second ring. Each planet gear is rotatably mounted on a respective one of the axles and the axles are arranged at a first radius. At least one of the first ring and the second ring comprises a metal matrix composite material ring and the metal matrix composite ring comprises a ring of reinforcing fibres and the ring of reinforcing fibres having a second radius greater than the first radius. 1. A gas turbine engine comprising a gearbox , the gearbox comprising a sun gear , an annulus gear , a plurality of planet gears and a carrier , the sun gear meshing with the planet gears and the planet gears meshing with the annulus gear , the carrier comprising a first ring , a second ring spaced axially from the first ring and a plurality of circumferentially spaced axles extending axially between the first ring and the second ring , each planet gear being rotatably mounted on a respective one of the axles , the axles being arranged at a first radius , at least one of the first ring and the second ring comprising a metal matrix composite material , the metal matrix composite material comprising a ring of reinforcing fibres and the ring of reinforcing fibres having a second radius greater than the first radius.2. A gas turbine engine as claimed in wherein the first ring comprises a first metal matrix composite material and the second ring comprises a second metal matrix composite material claim 1 , the first metal matrix composite material comprises a first ring of reinforcing fibres claim 1 , the first ring of reinforcing fibres having a second radius greater than the first ...

CENTRIFUGAL COMPRESSOR AND SHROUD THEREFORE

The shroud can have a wall curved radially outwardly from an axially oriented inlet to an outlet end, a structural member having a flange at the outlet end, and an insert of Greek Ascoloy exposed on an inner face of the wall. 1. A shroud for a centrifugal compressor having a rotation axis , the shroud having a wall curved radially outwardly from an axially oriented inlet to an outlet end , a structural member having a flange at the outlet end , and an insert of Greek Ascoloy exposed on an inner face of the wall.2. The shroud of wherein the wall further comprises a honeycomb core sandwiched between the insert of Greek Ascoloy and the structural member.3. The shroud of wherein the honeycomb core is made of steel.4. The shroud of wherein the honeycomb core is brazed to the insert of Greek Ascoloy.5. The shroud of wherein the insert of Greek Ascoloy forms a layer entirely covering the inner face of the wall.6. The shroud of wherein the structural member has a layer extending along an entire outer face of the wall.7. The shroud of wherein the flange protrudes from the layer of the structural member claim 6 , and is integral thereto.8. The shroud of wherein the structural member is of Inconel.9. A gas turbine engine having claim 1 , in serial flow communication claim 1 , a compressor section claim 1 , a combustor claim 1 , and a turbine section claim 1 , the compressor section having a centrifugal compressor claim 1 , the centrifugal compressor having a rotor rotatably mounted within an engine casing for rotation around a rotation axis claim 1 , and a shroud having a wall curved radially outwardly from an axially oriented inlet to an outlet end claim 1 , a structural member having a radially-oriented flange at the outlet end claim 1 , the flange connecting the shroud to the engine casing claim 1 , and an exposed layer of Greek Ascoloy facing the rotor.10. The gas turbine engine of wherein the gas turbine engine is a turbofan engine claim 9 , wherein the centrifugal ...

TURBINE BLADE TIP TREATMENT FOR INDUSTRIAL GAS TURBINES

A method of preventing transfer of metal of a gas turbine rotor blade having a metal tip to a blade outer air seal coating on a gas turbine case includes forming a coating on the metal tip. The coating comprises a bond coat layer on the metal tip and a ceramic filled metallic layer having a ceramic component in a matrix of a metal MCr, MCrAl, MCrAlY or a refractory modified CMCrAlY where M is nickel, cobalt, iron or mixtures thereof. 1. A method of preventing transfer of metal of a gas turbine rotor blade having a metal tip to a blade outer air seal coating , comprising:a blade outer air seal coating on a gas turbine case; anda coating on the metal tip, the coating comprising a ceramic filled metallic layer having a ceramic component in a matrix of a metal.2. The method of claim 1 , wherein the ceramic component has a hardness of seven or more on the Mohs Scale.3. The method of claim 2 , wherein the ceramic component is selected from the group consisting of silica claim 2 , quartz claim 2 , alumina claim 2 , zirconia and mixtures thereof.4. The method of claim 1 , wherein the metal is selected from the group consisting MCr claim 1 , MCrAl claim 1 , MCrAlY or a refractory modified MCrAlY where M is nickel claim 1 , cobalt claim 1 , iron or mixtures thereof.5. The method of claim 1 , which further includes a bond coat on the metal tip between the metal tip and the ceramic filled metallic layer.6. The method of claim 1 , wherein the ceramic component is selected from the group consisting of silica claim 1 , quartz claim 1 , alumina claim 1 , zirconia and mixtures thereof and the metal is selected from the group consisting of MCr claim 1 , MCrAl claim 1 , MCrAlY or a refractory modified MCrAlY where M is nickel claim 1 , cobalt claim 1 , iron or mixtures thereof.7. A rotor and blade seal coating preventing transfer of metal of a gas turbine rotor blade having a metal tip to a blade outer air seal coating claim 1 , comprising:a blade outer air seal coating on a gas ...

TURBINE COMPONENTS AND METHOD FOR FORMING TURBINE COMPONENTS

Turbine components are disclosed including a component wall defining a constrained portion, a manifold having an impingement wall, and a post-impingement cavity disposed between the manifold and the component wall. The impingement wall includes a wall thickness and defines a plenum and a tapered portion. The tapered portion tapers toward the constrained portion and includes a plurality of impingement apertures and a wall inflection. The wall inflection is disposed proximal to the constrained portion, and the tapered portion is integrally formed as a single, continuous object. The wall inflection may include an inflection radius of less than about 3 times the wall thickness of the impingement wall, or the tapered portion may include a consolidated portion with the impingement wall extending across the plenum. A method for forming the turbine component is also disclosed, including forming the tapered portion as a single, continuous tapered portion by an additive manufacturing technique. 1. A turbine component , comprising:a component wall including a plurality of external apertures and defining a constrained portion;a manifold disposed within the component wall, the manifold including an impingement wall, the impingement wall including a wall thickness and defining a plenum and a tapered portion, the tapered portion tapering toward the constrained portion and including a plurality of impingement apertures and a wall inflection, the wall inflection being disposed proximal to the constrained portion; anda post-impingement cavity disposed between the manifold and the component wall, the post-impingement cavity arranged to receive a fluid from the plenum through the plurality of impingement apertures and exhaust the fluid through the plurality of external apertures, the post-impingement cavity including an enervated zone disposed between the tapered portion and the constrained portion,wherein the tapered portion is integrally formed as a single, continuous object, and the ...

RELIEF VALVE FOR A TURBOCHARGER AND PROCESS FOR MANUFACTURING A RELIEF VALVE

The present invention relates to a relief valve () for a turbocharger, in which the crank arm () is made of a first material and the shaft () is made of a second material different from the first material used for manufacturing the crank arm (), each of the materials containing a composition that provides the necessary properties according to the application of each component of the relief valve (). The present invention also relates to a process for manufacturing the relief valve (), which allows the crank arm () and the shaft () to be manufactured separately, using different materials for the manufacture of each component. 115-. (canceled)1611. A relief valve () for a turbocharger , the relief valve () comprising:{'b': '2', '#text': 'a valve flap (); and'}{'b': ['3', '4'], '#text': 'a support element, the support element being formed by a crank arm () and a shaft (),'}{'claim-text': [{'b': '3', '#text': 'the crank arm () is made of a first material; and'}, {'b': ['4', '3'], '#text': 'the shaft () is made of a second material different to the first material used for manufacturing the crank arm ().'}], '#text': 'wherein:'}1713. The relief valve () according to claim 16 , wherein the first material used for manufacturing the crank arm () is composed of a nickel-based material with at least 30% nickel by weight.1813. The relief valve () according to claim 17 , wherein the first material used for manufacturing the crank arm () contains up to 0.08% carbon by weight claim 17 , 0.5% silicon by weight claim 17 , up to 0.5% manganese by weight claim 17 , up to 0.015% phosphorus by weight claim 17 , up to 0.01% sulphur by weight claim 17 , between 13.5% and 15.5% chrome by weight claim 17 , between 30% and 33.5% nickel by weight claim 17 , between 0.4% and 1% molybdenum by weight claim 17 , between 1.6% and 2.2% aluminum by weight claim 17 , and iron as residue.1913. The relief valve () according to claim 16 , wherein the first material used for manufacturing the crank arm ...

Turbopump with a single piece housing and a smooth enamel glass surface

A turbopump such as a liquid oxygen (LOX) turbopump for a liquid rocket engine is formed using a metal additive manufacturing process in which a single-piece impeller is formed within a single piece housing, the impeller being trapped within the single piece housing. The impeller is formed with an axial bore in which a shaft is inserted after the impeller and housing have been formed. The turbopump includes a protective coating that forms a reaction resistant surface on the base metal in areas of the base metal that are exposed to an oxidizer during pumping. The protective coating may be an enamel glass, a superalloy layer beneath an enamel glass layer, a composite layer of a mixture of enamel glass and superalloy, a composite mixture of oxide and superalloy, or a composite layer of a mixture of enamel glass, superalloy, and oxide.

Airfoil Conformable Membrane Erosion Coating

A coating membrane for a component of a gas-turbine engine includes a solid membrane having a metallic foil or a polymeric film, and having a thickness and at least one kerf extending through the thickness to define a kerf pattern such that the solid membrane can be applied to a compound-curved surface. Also disclosed are a coated component coated with the membrane, and a method for producing a coated component with the membrane. 1. A coating membrane for a component of a gas-turbine engine , comprising:a solid membrane comprising a metallic foil or a polymeric film, and having a thickness and at least one kerf extending through the thickness to define a kerf pattern such that the solid membrane can be applied to a compound-curved surface.2. The coating membrane of claim 1 , wherein the solid membrane comprises a metallic foil.3. The coating membrane of claim 2 , wherein the metallic foil is selected from the group consisting of foils of titanium alloy claim 2 , nickel alloy claim 2 , stainless ferrous alloy and combinations thereof.4. The coating membrane of claim 1 , wherein the solid membrane comprises a polymeric film.5. The coating membrane of claim 4 , wherein the polymeric film is selected from the group consisting of films of epoxy resin claim 4 , polyphenylene ether claim 4 , polyurethane and combinations thereof.6. The coating membrane of claim 4 , wherein the polymeric film is an elastomeric film.7. The coating membrane of claim 4 , wherein the polymeric film is fiber reinforced.8. The coating membrane of claim 1 , wherein the solid membrane has a thickness of between about 0.003 and about 0.030 inches.9. The coating membrane of claim 1 , wherein the at least one kerf has a kerf width of between 0.002 and 0.006 inches.10. The coating membrane of claim 1 , wherein the kerf pattern defines a reticulated kerf pattern in a monolithic membrane structure.11. The coating membrane of claim 1 , wherein the kerf pattern is a recurring pattern of intersecting kerfs. ...

ADJUSTABLE SPACER WITH HARDENED ENDS

An adjustable spacer with a non-hardened intermediate portion therebetween is mountable between a pair of roller bearings also mounted on a shaft such an axle or spindle or the like. The intermediate portion allows the spacer to collapse in the axial direction to maintain desired axial loads on the bearings. 1. An adjustable spacer comprising:an annular spacer comprising a first end portion comprising a first material, and a second end portion opposite said first end portion; andan intermediate portion of said annular spacer located between said first end portion and said second end portion, said intermediate portion comprising a second material of lesser hardness than the first material and more deformable than that first material.2. The spacer of wherein the second material is similar to the first material.3. The spacer of wherein the second material is different than the first material.4. The spacer of wherein the second end portion comprises a material which is harder than the second material.5. The spacer of wherein the first end portion and second end portion comprise the first material.6. The spacer of wherein said first end portion and second end portion are formed separately from said first end portion or second end portion to be assembled together.7. The spacer of wherein the intermediate portion is formed separately from said first end portion and second end portion.8. An assembly comprising:a shaft;an annular spacer mounted on said shaft, said annular spacer comprising a first end portion comprising a first material and a second opposite end portion; andan intermediate portion of said annular spacer, located between said first end portion and said second end portion, said intermediate portion comprising a second material of lesser hardness than the first material and more deformable than the first material.9. The assembly of wherein the second material is different than the first material.10. The assembly of wherein the second end portion comprises a ...

Steam Turbine Rotor

It is an objective of the invention to provide a steam turbine rotor that is capable of both reducing SCC susceptibility and improving LCF life thereof. There is provided a steam turbine rotor, comprising a rotor disk in a low pressure final stage L-0, and another rotor disk in a plurality of stages including a stage L-1 positioned closer to a high pressure side than the low pressure final stage L-0, the rotor disk in the low pressure final stage L-0 and the rotor disk in a plurality of stages including the stage L-1 being joined by welding, wherein a material of both the rotor disk in the low pressure final stage L-0 and the rotor disk in a plurality of stages including the stage L-1 is a 12Cr steel and has a tensile strength of 900 to 1200 MPa. 1. A steam turbine rotor , comprising a rotor disk in a low pressure final stage L-0 , and another rotor disk in a plurality of stages including a stage L-1 positioned closer to a high pressure side than the low pressure final stage L-0 , the rotor disk in the low pressure final stage L-0 and the rotor disk in a plurality of stages including the stage L-1 being joined by welding ,wherein a material of both the rotor disk in the low pressure final stage L-0 and the rotor disk in a plurality of stages including the stage L-1 is a 12Cr steel and has a tensile strength of 900 to 1200 MPa.2. The steam turbine rotor according to claim 1 , wherein the 12Cr steel that forms both the rotor disk in the low pressure final stage L-0 and the rotor disk in a plurality of stages including the stage L-1 contains 8.0 to 13 mass % of Cr.3. The steam turbine rotor according to claim 2 , wherein the rotor disk material in the low pressure final stage L-0 and the rotor disk material in a plurality of stages including the stage L-1 are the same material.4. The steam turbine rotor according to claim 3 , wherein: the rotor disk in a plurality of stages including the stage L-1 includes a stage L-2 in addition to the stage L-1;the steam turbine ...

TURBINE SHROUD ASSEMBLY

A turbine shroud assembly is disclosed including an inner shroud having a surface adjacent to a hot gas path, an outer shroud, a damper block disposed between the inner shroud and the outer shroud, a first biasing apparatus, and a second biasing apparatus. The first biasing apparatus provides a first biasing force to the inner shroud, biasing the inner shroud a first deflection distance in a direction toward the hot gas path and away from the outer shroud. The second biasing apparatus provides a second biasing force to the damper block, biasing the damper block a second deflection distance in a direction toward the hot gas path and away from the outer shroud. The second deflection distance is greater than the first deflection distance. 1. A turbine shroud assembly , comprising:an inner shroud having a surface adjacent to a hot gas path;an outer shroud;a damper block disposed between the inner shroud and the outer shroud;a first biasing apparatus providing a first biasing force to the inner shroud, biasing the inner shroud a first deflection distance in a direction toward the hot gas path and away from the outer shroud; anda second biasing apparatus providing a second biasing force to the damper block, biasing the damper block a second deflection distance in the direction toward the hot gas path and away from the outer shroud,wherein the second deflection distance is greater than the first deflection distance, loading the damper block to the inner shroud.2. The turbine shroud assembly of claim 1 , wherein the first biasing apparatus includes at least one spring claim 1 , the spring connecting to or contacting the inner shroud and configured to exert the first biasing force on the inner shroud.3. The turbine shroud assembly of claim 1 , wherein the first biasing apparatus is a springless biasing apparatus.4. The turbine shroud assembly of claim 3 , wherein the biasing apparatus is driven by a pressurized fluid.5. The turbine shroud assembly of claim 1 , wherein the ...

ANTI-COKING COATINGS, PROCESSES THEREFOR, AND HYDROCARBON FLUID PASSAGES PROVIDED THEREWITH

A method for providing an anti-coking coating system on a surface at elevated temperatures when contacted by a hydrocarbon fluid, for example, a surface of an interior fuel passage within a fuel nozzle of a type utilized in gas turbine engines, is disclosed. The surface of the passage is rough as a result of the passage being part of a component manufactured by an additive manufacturing (AM) process. In addition, the passage may have a complex geometry of a type that can be fabricated with AM processes, for example, geometries comprising combinations of sharp bends and narrow cross-sections. The coating system comprises at least one ceramic barrier layer and an outermost metallic layer, each of which is formed using a conformal vapor deposition process. 1. A method for producing a component having an internal passage with an interior surface thereof configured and adapted to contact a hydrocarbon fluid , the method comprising:producing the component and the internal passage thereof and the interior surface thereof using an additive manufacturing process; andperforming a vapor deposition process that comprises flowing a first precursor through the internal passage to deposit a conformal interior layer directly on the interior surface and flowing a second precursor through the internal passage so as to deposit a conformal outermost layer overlying the interior layer, the interior layer and the outermost layer defining a conformal anti-coking coating system on the interior surface and the outermost layer defining an outermost surface of the anti-coking coating system.2. The method according to claim 1 , wherein at least a portion of the interior surface on which the coating system is deposited has a surface roughness of up to 30 micrometers Ra.3. The method according to claim 1 , wherein the internal passage has a nonlinear shape.4. The method according to claim 1 , wherein the internal passage comprises at least one passage section with a geometry that is at least one ...

Wear resistant slurry pump parts produced using hot isostatic pressing

In one aspect, a method for manufacturing a part for a centrifugal slurry pump is provided, comprising: forming a skeleton of the part having an outer dimension smaller than the part; placing the skeleton of the part in a metal enclosure having an interior dimension larger than the outer dimension of the skeleton of the part and thereby forming a space; adding a metal matrix composite powder into the metal enclosure to fill the space; and subjecting the metal enclosure to hot isostatic pressing, thereby allowing bonding of the metal matrix composite to the skeleton of the part to form the part.

ROTOR CONSTRUCTION FOR HIGH SPEED MOTORS

A rotor shaft for a high speed motor that has a coating that is secured to a shaft body. The coating and the shaft body are formed from dissimilar materials. More specifically, the coating may be an alloy material, such as, for example, a copper alloy, while the shaft body may be a steel material. According to certain embodiments, the alloy material of the coating may be secured to at least a portion of a rotor body blank in a solution treated condition via a low temperature welding procedure. Additionally, the coating may be hardened, such as for example, through the use of an age hardening process. The coating and the rotor body blank may be machined together to form the rotor shaft. According to certain embodiments, such machining may configure the rotor shaft for use with a turbo-compressor that is configured for air compression. 121-. (canceled)22. A method for manufacturing a rotor shaft for a high speed motor , the method comprising:forming a rotor body blank from a steel material;solution heat treating an alloy material, wherein a duration of heat treating the alloy material is dependent on a thickness of the alloy material, the alloy material and the steel material of the rotor body blank being different materials;securing the solution treated alloy material to at least a portion of the rotor body blank to provide a coating;heat treating the coating when the coating is secured to the rotor body blank, the heat treating process adapted to minimize the loss of a core property of the steel material of the rotor body blank; andmachining the rotor body blank and the coating to form the rotor shaft, the rotor shaft configured for operation in the high speed motor.23. The method of claim 22 , wherein the duration of heat treating the alloy material ranges from three minutes to three hours.24. The method of claim 22 , wherein the alloy material is a copper alloy.25. The method of claim 24 , wherein the step of securing the alloy material includes using a low ...

COUPLING AND ASSOCIATED METHOD OF TRANSFERRING TORQUE

The coupling can have a female member configured to rotate around an axis, defining an axial recess, and having a plurality of connections circumferentially arranged along a radially inner face; a male member extending inside the axial recess concentrically to the female member and having a plurality of connections circumferentially arranged along a radially outer face; and a plurality of circumferentially arranged links, each link having an inner end engaged with a corresponding one of the male member connections, and an outer end engaged with a corresponding female member connection, the links being slanted off the radial orientation, with the inner end being circumferentially offset from the outer end, the links subjected to compression when transmitting torque between the female member and male member. 1. A coupling comprising:a female member configured for rotation around an axis, defining an axial recess, and having a plurality of female member connections circumferentially arranged along a radially inner face;a male member extending inside the axial recess concentrically to the female member and having a plurality of male member connections circumferentially arranged along a radially outer face; anda plurality of circumferentially arranged links, each link having an inner end connected to the male member via a corresponding one of the male member connections, and an outer end connected to the female member via a corresponding one of the female member connections, with the inner end being circumferentially offset from the outer end in a given angular direction, the given angular direction configured for subjecting the links to compression when transmitting torque between the female member and male member.2. The coupling of wherein both the male member connections and the female member connections are pivotal connections claim 1 , allowing pivot movement ability of the corresponding link ends claim 1 , and blocking circumferential displacement ability.3. The ...

HIGH HEAT RESISTANT STEEL WITH LOW NICKEL

Provided herein is heat resistant steel for a turbine housing of an automotive turbocharger. In some instances, the high heat resistant steel with low nickel has high tensile strength and high heat resistance at a high temperature. The low Ni content provides cost reduction. 1. High heat resistant steel with low Ni:wherein a value of X/Y is 0.44 to 0.47; [{'br': None, '[Equation 1]'}, {'br': None, 'i': 'X', '=wt % of Cr+wt % of 1.5×Si+wt % of 0.5×Nb'}], 'the X is a value calculated by Equation 1;'} [{'br': None, '[Equation 2]'}, {'br': None, 'i': 'Y', '=wt % of Ni+wt % of 0.5×Mn+wt % of 30×C+wt % of 30×N'}], 'the Y is a value calculated by Equation 2.'}2. The high heat resistant steel with low Ni of claim 1 , wherein wt % of the C is from about 0.5 to 0.7 wt %.3. The high heat resistant steel with low Ni of claim 1 , wherein wt % of the Si is from about 1.3 to 1.7 wt %.4. The high heat resistant steel with low Ni of claim 1 , wherein wt % of the Mn is from about 0.6 to 1.0 wt %.5. The high heat resistant steel with low Ni of claim 1 , wherein wt % of the Ni is from about 24.0 to 26.0 wt %.6. The high heat resistant steel with low Ni of claim 1 , wherein wt % of the Cr is from about 18.0 to 20.0 wt %.7. The high heat resistant steel with low Ni of claim 1 , wherein wt % of the Nb is from about 1.0 to 2.0 wt %.8. The high heat resistant steel with low Ni of claim 1 , wherein wt % of the N is from about 0.15 to 0.20 wt %.9. The high heat resistant steel with low Ni of claim 1 , wherein wt % of the C is from about 0.5 to 0.7 wt % claim 1 , wt % of the Si is from about 1.3 to 1.7 wt % claim 1 , wt % of the Mn is from about 0.6 to 1.0 wt % claim 1 , wt % of the Ni is from about 24.0 to 26.0 wt % claim 1 , wt % of the Cr is from about 18.0 to 20.0 wt % claim 1 , wt % of the Nb is from about 1.0 to 2.0 wt % claim 1 , and wt % of the N is from about 0.15 to 0.20 wt %.10. An automotive turbine housing manufactured by the high heat resistant steel with low Ni of . This ...

Rotor construction for high speed motors

A rotor shaft for a high speed motor that has a coating that is secured to a shaft body. The coating and the shaft body are formed from dissimilar materials. More specifically, the coating may be an alloy material, such as, for example, a copper alloy, while the shaft body may be a steel material. According to certain embodiments, the alloy material of the coating may be secured to at least a portion of a rotor body blank in a solution treated condition via a low temperature welding procedure. Additionally, the coating may be hardened, such as for example, through the use of an age hardening process. The coating and the rotor body blank may be machined together to form the rotor shaft. According to certain embodiments, such machining may configure the rotor shaft for use with a turbo-compressor that is configured for air compression.

STATOR VANE ADJUSTING DEVICE OF A GAS TURBINE

A stator vane adjusting device of a gas turbine having a plurality of stator vanes each swivellable about a radial axis and arranged in at least one radial plane, as well as at least one stator vane adjusting ring which is connected to the respective stator vanes and rotatable in the circumferential direction by means of an actuating device, where the stator vane adjusting ring is braced on a centrally arranged casing in the radial direction by means of several spacers distributed about the circumference and mounted on the stator vane adjusting ring, characterized in that a bush on which the spacer is mounted is fastened to the stator vane adjusting ring for each spacer, the bush being made from a plastic material with a high thermal expansion coefficient. 1. A stator vane adjusting device of a gas turbine having a plurality of stator vanes each swivellable about a radial axis and arranged in at least one radial plane , as well as at least one stator vane adjusting ring which is connected to the respective stator vanes and rotatable in the circumferential direction by means of an actuating device , where the stator vane adjusting ring is braced on a centrally arranged casing in the radial direction by means of several spacers distributed about the circumference and mounted on the stator vane adjusting ring , wherein a bush on which the spacer is mounted is fastened to the stator vane adjusting ring for each spacer , the bush being made from a plastic or composite material with a higher thermal expansion coefficient than a thermal expansion coefficient of the stator vane adjusting ring.2. The Stator vane adjusting device in accordance with claim 1 , wherein the bush is designed tube-like and that the spacer has a shaft centrally fastened inside the bush.3. The stator vane adjusting device in accordance with claim 2 , wherein the shaft is fastened to the radially outer area of the bush.4. The stator vane adjusting device in accordance with claim 2 , wherein the shaft ...

Flow Meter with Rotor Assembly

A flow meter for determining a flow rate of a fluid. The flow meter includes a housing comprising a flow bore, a rotor assembly rotatable by the flow of fluid within the flow bore and comprising a thermally diffused metallic material, and a sensor unit configured to generate a signal indicative of a rotational rate of the rotor assembly. 1. A flow meter for determining a flow rate of a fluid , comprising:a housing comprising a flow bore; 'comprising a thermally diffused metallic material, wherein the thermally diffused metallic material comprises a metallic material and a diffusion substance; and', 'a rotor assembly rotatable by the flow of fluid within the flow bore and'}a sensor unit configured to generate a signal indicative of a rotational rate of the rotor assembly.2. The flow meter of claim 1 , wherein the rotor assembly comprises a rotor shaft comprising the thermally diffused metallic material.3. The flow meter of claim 2 , wherein the rotor assembly comprises a rotor shaft and a rotor comprising rotor blades claim 2 , the rotor being at least partially located in the flow bore.4. The flow meter of claim 3 , wherein the rotor blades comprise turbine blades.5. The flow meter of claim 3 , wherein the rotor is fixedly coupled to the rotor shaft by machine pressing.6. The flow meter of claim 1 , wherein the rotor assembly comprises a rotor shaft and rotor blades integral with the rotor shaft claim 1 , the rotor blades being at least partially located in the flow bore.7. The flow meter of claim 6 , wherein the integral rotor blades comprise turbine blades.8. The flow meter of claim 6 , wherein the rotor shaft and the integral rotor blades are formed by additive manufacturing.9. The flow meter of claim 1 , wherein the thermally diffused metallic material comprises a hardened surface claim 1 , hardened by changing a molecular structure of the surface through thermal chemical diffusion of the diffusion substance.10. The flow meter of claim 1 , wherein the thermally ...

METHOD FOR MANUFACTURING COMPONENTS FOR GAS TURBINE ENGINES

A method of manufacturing a component for a gas turbine engine. The method may include the steps of: providing a forged preform of the component that is made from a stainless steel alloy; identifying two non-overlapping portions of the component that together form a whole of the component: a target portion and a remainder portion; and treating the component with a regionally selective tempering process in which a treated region receives a tempering process while an untreated region is excluded from receiving the tempering process. The target portion may be the treated region while the remainder portion is the untreated region. The tempering process of the regionally selective tempering process may be configured to appreciably increase a hardness of the target portion of the component relative to a hardness of the remainder portion of the component. 1. A method of manufacturing a component for a gas turbine engine , the method including the steps of:providing a forged preform of the component, the forged preform being made from a stainless steel alloy;identifying two non-overlapping portions of the component that together form a whole of the component: a target portion and a remainder portion; andtreating the component with a regionally selective tempering process configured such that a treated region receives the regionally selective tempering process while an untreated region is prevented from receiving the regionally selective tempering process; the target portion comprises the treated region and the remainder portion comprises the untreated region of the regionally selective tempering process; and', 'the regionally selective tempering process is configured to appreciably increase a hardness of the target portion of the component relative to a hardness of the remainder portion of the component., 'wherein2. The method according to claim 1 , wherein the stainless steel alloy comprises a martensitic stainless steel alloy comprising claim 1 , by weight: about 12.0 to ...

DEHYDROGENATION PROCESSING METHOD FOR TURBINE BLADES

A dehydrogenation processing method for a turbine blade of a steam turbine includes: a step of heating the turbine blade by supplying heating steam into a casing of the steam turbine when a steam turbine plant is started or stopped. 113-. (canceled)14. A dehydrogenation processing method for a turbine blade of a steam turbine , the method comprising:a step of heating the turbine blade by supplying heating steam into a casing of the steam turbine when a steam turbine plant is started or stopped,wherein the heating steam has a higher temperature than steam passing through the turbine blade during operation of the steam turbine.15. The dehydrogenation processing method for a turbine blade according to claim 14 ,wherein the step of heating the turbine blade includes supplying gland steam as the heating steam into the casing via a gland seal portion of the steam turbine.16. The dehydrogenation processing method for a turbine blade according to claim 15 ,wherein the step of heating the turbine blade includes setting the temperature of the gland steam as the heating steam to be higher than gland steam during operation of the steam turbine.17. The dehydrogenation processing method for a turbine blade according to claim 16 ,wherein the temperature of the gland steam is adjusted by a temperature adjuster disposed in a gland steam line for supplying the gland steam to the gland seal portion.18. The dehydrogenation processing method for a turbine blade according to claim 17 ,wherein the temperature adjuster is a desuperheater disposed in the gland steam line between a gland steam header and the gland seal portion, andwherein the desuperheater is configured to adjust a temperature decrease amount of the gland steam.19. The dehydrogenation processing method for a turbine blade according to claim 18 ,wherein the step of heating the turbine blade includes increasing a temperature setting value of the gland steam at the desuperheater compared to during operation of the steam turbine ...

ARTICLE HAVING VARIABLE COMPOSITION COATING

A coated article includes a substrate and an MCrAlY coating supported on the substrate. The M includes at least one of nickel, cobalt, and iron, Cr is chromium, Al is aluminum, and Y is yttrium. The composition of the MCrAlY coating varies in an amount of at least one of Cr, Al, and Y by location on the substrate with respect to localized property requirements. In one example, the coated article is an article of a gas turbine engine. 1. A coated article comprising:a substrate; andan MCrAlY coating supported on the substrate, where the M includes at least one of nickel, cobalt, and iron, Cr is chromium, Al is aluminum, and Y is yttrium, the composition of the MCrAlY coating varying in an amount of at least one of Cr, Al, and Y by lateral location on the substrate and with respect to localized property requirements.2. The coated article as recited in claim 1 , wherein the localized property requirements are selected from the group consisting of corrosion resistance claim 1 , erosion resistance claim 1 , spallation resistance claim 1 , fatigue resistance claim 1 , oxidation resistance claim 1 , creep resistance claim 1 , impact resistance claim 1 , and combinations thereof.3. The coated article as recited in claim 1 , wherein the composition of the MCrAlY coating varies in the amount of Cr.4. The coated article as recited in claim 1 , wherein the composition of the MCrAlY coating varies in the amount of Al.5. The coated article as recited in claim 1 , wherein the composition of the MCrAlY coating varies in the amount of Y.6. The coated article as recited in claim 1 , wherein the MCrAlY coating includes at least one alloying element of Co claim 1 , tantalum (Ta) claim 1 , tungsten (W) claim 1 , molybdenum (Mo) claim 1 , silicon (Si) claim 1 , hafnium (Hf) claim 1 , and zirconium (Zr) claim 1 , and the amount of the alloying element differs by location on the substrate and with respect to localized property requirements.7. The coated article as recited in claim 1 , ...

Liner for mounting socket of magnesium housing of aircraft engine

Assemblies and methods useful for mounting an engine to an aircraft structure are disclosed. An exemplary assembly comprises a body made of a magnesium-based material defining a socket formed therein and a liner disposed in the socket for receiving and interfacing with an engine mounting element of the aircraft. The liner comprises a peripheral side wall and a bottom wall having an outer periphery in sealing engagement with a lower portion of the peripheral side wall. The liner is made of a liner material that provides a galvanic potential between the liner material and a material of the engine mounting element that is lower than a galvanic potential between the magnesium-based material of the body and the material of the engine mounting element.

COMPOUND ENGINE ASSEMBLY WITH OFFSET TURBINE SHAFT, ENGINE SHAFT AND INLET DUCT

A compound engine assembly with an inlet duct, a compressor, an engine core including at least one internal combustion engine, and a turbine section including a turbine shaft configured to compound power with the engine shaft. The turbine section may include a first stage turbine and a second stage turbine. The turbine shaft and the engine shaft are parallel to each other. The turbine shaft, the engine shaft and at least part of the inlet duct are all radially offset from one another. A method of driving a rotatable load of an aircraft is also discussed. 120.-. (canceled)21. A compound engine assembly comprising:an inlet duct having a longitudinal central axis, an air flow within the inlet duct occurring along a direction corresponding to that of the longitudinal central axis;a conduit communicating with the inlet duct;a compressor having an inlet in fluid communication with the conduit, the compressor including at least one compressor rotor connected to a turbine shaft;an engine core including at least one internal combustion engine in driving engagement with an engine shaft, the engine core having an inlet in fluid communication with an outlet of the compressor;a turbine section having an inlet in fluid communication with an outlet of the engine core, the turbine section including at least one turbine rotor connected to the turbine shaft, the turbine shaft configured to compound power with the engine shaft;wherein the turbine shaft and the engine shaft are parallel to each other; andwherein the turbine shaft, the engine shaft and the longitudinal central axis of at least part of the inlet duct are all radially offset from one another, the at least part of the inlet duct including an inlet of the inlet duct in fluid communication with ambient air around the compound engine.22. The compound engine assembly as defined in claim 21 , wherein the longitudinal central axis of at least part of the inlet duct is parallel to the turbine shaft and to the engine shaft.23. The ...

ROTOR OF ROTARY MACHINE AND ROTARY MACHINE

A rotor () of a rotary machine (T) according to the invention includes a plurality of rotor members (, and ) which are joined to each other in the axial direction in which the axis (P) extends, and among the plurality of rotor members ( and ), the first rotor member () in hydraulic fluid injection portions (and ) of a passageway () is formed of Ni-based alloy so that the inside thereof is hollow throughout the entire length in the axial direction. 113-. (canceled)14. A rotor of the steam turbine that is formed to have rotor members which are formed of different materials from each other and which are joined to each other in the axial direction , the rotor comprising:a first rotor member; anda second rotor member,wherein the first rotor member is formed of an Ni-based alloy,wherein the first rotor member includes a guide portion through which a working fluid is guided,wherein the first rotor member includes a rotor vane through which the working fluid passes,wherein the second rotor member is formed of a material which is more easily molded than the Ni-based alloy,wherein the second rotor member is joined to the first rotor member on the downstream side of flow of the working fluid,wherein the second rotor member includes a discharge portion through which the working fluid is discharged,wherein the second rotor member includes a rotor vane, through which the working fluid passes, on a joint side with the first rotor member and includes a sealing portion from the outside and a bearing on a side opposite to the joint side,wherein the first rotor member and a joint portion of the second rotor member with the first rotor member are disposed in the same pressure range,wherein the number of vane rows of the first rotor member is greater than the number of vane rows of the second rotor member, and{'sup': −6', '−6', '−6', '−6, 'wherein an average linear expansion coefficient of the first rotor member in a temperature range of room temperature to 700° C. which becomes an ...

CORE FOR HIGH-TEMPERATURE SHAPING OF A METAL PART AND MANUFACTURING, REGENERATION AND SHAPING PROCESS

A metal core for hot-forming a titanium-based alloy metal component is disclosed. The metal core has on an outer surface, intended to come into contact with the metal component, a layer of metal carbonitride-enriched material. The metal core comprises a nickel- or cobalt-based alloy. The metal core comprising a steel coating having an outer surface intended to come into contact with the metal component, the steel coating having a layer of metal carbonitride-enriched material. Processes for manufacturing and regenerating the metal core and a process for hot-forming a metal component using the metal core are also disclosed. 1. Metal core for hot-forming a titanium-based alloy metal component , the metal core comprising a nickel- or cobalt-based alloy core and the metal core comprising a steel coating having an outer surface intended to come into contact with the metal component , the steel coating having a layer of metal carbonitride-enriched material.2. Metal core according to claim 1 , wherein the steel coating has a thickness greater than or equal to 50 μm.3. Metal core according to claim 1 , wherein the outer surface has a surface roughness Ra greater than or equal to 0.5 μm.4. Metal core according to claim 1 , wherein the steel coating has a thickness equal to or greater than a thickness of the layer of metal carbonitride-enriched material.5. Process for manufacturing a metal core according to claim 1 , comprising the following steps:manufacturing the core of the metal core;coating of the core with a steel coating; andcarbonitriding of the outer surface of the steel coating so as to obtain a layer of metal carbonitride-enriched material.6. Process for manufacturing according to claim 5 , wherein the carbonitriding of the outer surface of the steel coating is carried out for a time of less than or equal to 10 hours.7. Process for manufacturing according to claim 5 , wherein prior to the carbonitriding step claim 5 , the steel coating is sandblasted.8. Process for ...

COATED COMPONENT AND METHOD OF PREPARING A COATED COMPONENT

A coated component and a method of preparing a coated component are provided. The method comprises providing a substrate; and applying a dual coating system to the substrate. The applying of the dual coating system includes applying a diffusion barrier coating; and applying a corrosion-resistant coating. The corrosion-resistant coating comprises a greater concentration of silicon and aluminum than the diffusion barrier coating, and the dual layer coating system includes an aluminide interdiffusion zone. 1. A coated component comprising:a substrate; and a diffusion barrier coating:', 'a corrosion-resistant coating,, 'a dual layer coating system overlying the substrate, comprisingwherein the corrosion-resistant coating comprises a greater concentration of silicon and aluminum than the diffusion barrier coating, andwherein the dual layer coating system includes an aluminide interdiffusion zone.2. The coated component of claim 1 , wherein the substrate comprises an alloy selected from the group consisting of cobalt-based alloy claim 1 , iron-based alloy claim 1 , nickel-based alloy and combinations thereof.3. The coated component of claim 1 , wherein the substrate is devoid of aluminum.4. The coated component of claim 1 , wherein the corrosion-resistant coating includes a sufficient amount of silicon and aluminum to form the aluminide interdiffusion zone.5. The coated component of claim 1 , wherein the diffusion barrier coating is selected from the group consisting of MCrAlY claim 1 , gel aluminide and combinations thereof.6. The coated component of claim 1 , wherein the diffusion barrier coating is devoid of silicon.7. The coated component of claim 1 , wherein the diffusion barrier coating or the corrosion-resistant coating is adjacent the substrate.8. The coated component of claim 1 , wherein the dual layer coating system comprises a concentration gradient in silicon and aluminum decreasing from a boundary between the substrate and the corrosion-resistant coating to ...

LIGHTWEIGHT JOURNAL SUPPORT PIN

A journal support pin to support intermediate gears for use in gas turbine engine comprises a titanium body, and an outer surface outside of the titanium body having a surface hardness that is harder than the body. A gas turbine engine and a method of forming a journal support pin to support intermediate gears for use in gas turbine engine are also disclosed. 1. A journal support pin to support intermediate gears for use in gas turbine engine comprising:a titanium body, and an outer surface outside of said titanium body having a surface hardness that is harder than said body;said outer surface is provided by one of a steel sleeve, a coating, nitriding or high velocity oxyfuel spray; andoil supply holes extend from a central bore in said body through said outer surface.2. The journal support pin as set forth in claim 1 , wherein said oil supply holes extend through said outer surface at a recess claim 1 , wherein a thickness of said outer surface is thinner than at axial ends of said titanium body.3. The journal support pin as set forth in claim 2 , wherein said recess extends only over a limited circumferential portion of said outer surface.4. The journal support pin as set forth in claim 1 , wherein said outer surface is provided by a steel sleeve.5. The journal support pin as set forth in claim 4 , wherein said steel sleeve is pinned to said body to secure said sleeve to said body.6. The journal support pin as set forth in claim 1 , wherein said outer surface is provided by a coating.7. The journal support pin as set forth in claim 6 , wherein said coating is one of silver claim 6 , steel and titanium nitride.8. The journal support pin as set forth in claim 1 , wherein said outer surface is provided by nitriding.9. The journal support pin as set forth in claim 1 , wherein said outer surface is provided by high velocity oxyfuel spray.10. A gas turbine engine comprising:a fan and a fan drive turbine, said fan drive turbine driving said fan through a gear reduction; ...

STAINLESS STEEL ALLOYS, TURBOCHARGER TURBINE HOUSINGS FORMED FROM THE STAINLESS STEEL ALLOYS, AND METHODS FOR MANUFACTURING THE SAME

Disclosed is an austenitic stainless steel alloy that includes, by weight, about 22% to about 28% chromium, about 3.5% to about 6.5% nickel, about 1% to about 6% manganese, about 0.5% to about 2.5% silicon, about 0.3% to about 0.6% carbon, about 0.2% to about 0.8% nitrogen, and a balance of iron. Molybdenum, niobium, and tungsten are excluded. The alloy is suitable for use in turbocharger turbine housing applications for temperature up to about 980° C. 1. An austenitic stainless steel alloy , comprising , by weight:about 22% to about 28% chromium;about 3.5% to about 6.5% nickel;about 1% to about 6% manganese;about 0.5% to about 2.5% silicon;about 0.3% to about 0.6% carbon;about 0.2% to about 0.5% nitrogen; anda balance of iron, with the proviso that molybdenum, niobium, and tungsten are excluded from the alloy.2. The austenitic stainless steel alloy of comprising about 23% to about 27% chromium.3. The austenitic stainless steel alloy of comprising about 4.0% to about 6.0% nickel.4. The austenitic stainless steel alloy of comprising about 1.5% to about 5.5% manganese.5. The austenitic stainless steel alloy of comprising about 1.0% to about 2.0% silicon.6. The austenitic stainless steel alloy of comprising about 0.4% to about 0.5% carbon.7. The austenitic stainless steel alloy of comprising about 0.3% to about 0.5% nitrogen.8. An turbocharger turbine housing comprising:an austenitic stainless steel alloy, wherein the austenitic stainless steel alloy comprises, by weight:about 22% to about 28% chromium;about 3.5% to about 6.5% nickel;about 1% to about 6% manganese;about 0.5% to about 2.5% silicon;about 0.3% to about 0.6% carbon;about 0.2% to about 0.5% nitrogen; anda balance of iron, with the proviso that molybdenum, niobium, and tungsten are excluded from the alloy.9. The turbocharger turbine housing of comprising about 23% to about 27% chromium.10. The turbocharger turbine housing of comprising about 4.0% to about 6.0% nickel.11. The turbocharger turbine housing of ...

TURBINE HOUSING FOR AN EXHAUST GAS TURBOCHARGER

The invention relates to a turbine housing () for an exhaust gas turbocharger. The turbine housing () comprises an outer housing () and an inner housing () as well as a bearing flange (). The outer housing () is joined to the bearing flange (). The inner housing () comprises a first shell component () and a second shell component (), wherein said first shell component and said second shell component are made of different cast steel materials and are placed side by side in a transverse plane (QE), which is oriented transversely to the longitudinal axis (LA) of the turbine housing (), and are joined to each other. The bearing flange () is a one-piece part, made of uniform material, of the first shell component (). 13453547878. Turbine housing , which is designed for an exhaust gas turbocharger and which comprises an outer housing () and an inner housing () as well as a bearing flange () , wherein the outer housing () is joined to the bearing flange () , characterized in that the inner housing () comprises a first shell component () and a second shell component () , said first shell component and said second shell component being joined to each other; and the two shell components ( , ) are made of different cast steel materials.257. Turbine housing claim 1 , as claimed in claim 1 , characterized in that the bearing flange () is a one-piece part claim 1 , made of uniform material claim 1 , of the first shell component ().37821094. Turbine housing claim 1 , as claimed in claim 1 , characterized in that the two shell components ( claim 1 , ) are placed side by side in a transverse plane (QE) claim 1 , which is oriented transversely to the longitudinal axis (LA) of the turbine housing () claim 1 , and are connected to each other by means of a circumferential joint claim 1 , seam () on the outer periphery () of the inner housing ().451335. Turbine housing claim 1 , as claimed in claim 1 , characterized in that the bearing flange () has an external circumferential web () ...

IN-SITU LASER MACHINING USING MIRRORED OPTICS

The present disclosure is directed to a system for performing in-situ laser machining on a component within a gas turbine engine, in which the component includes a substrate defining a surface. The system includes a laser system disposed externally of the gas turbine engine, a focusing optic, and a conduit. The laser system includes a laser unit that produces an output beam. The focusing optic is disposed between the laser unit and the component. The conduit defines a first end external of the engine and a second end that ingresses into the engine through an access port. The conduit includes a plurality of mirrors within the conduit. The plurality of mirrors directs the output beam from the laser system onto the component. 1. A system for performing in-situ laser machining on a component within a gas turbine engine , wherein the component comprises a substrate defining a surface , the system comprising:a laser system disposed externally of the gas turbine engine, wherein the laser system comprises a laser unit that produces an output beam;a focusing optic disposed between the laser unit and the component; anda conduit defining a first end external of the engine and a second end that ingresses into the engine through an access port, wherein the conduit includes a plurality of mirrors within the conduit, and wherein the plurality of mirrors directs the output beam from the laser system onto the component.2. The system of claim 1 , wherein the laser system further comprises:a galvanometer system in serial arrangement with the laser unit and the plurality of mirrors of the conduit.3. The system of claim 1 , wherein the focusing optic is an F-theta objective in serial arrangement with the laser system and the plurality of mirrors of the conduit.4. The system of claim 1 , wherein the focusing optic is a dynamic focusing unit in serial arrangement with the laser system and the plurality of mirrors of the conduit.5. The system of claim 1 , wherein the conduit is defined by ...

Austenite steel, and austenite steel casting using same

Provided herein are an austenite steel that satisfies desirable strength and desirable castability at the same time, and an austenite steel casting using same. The austenite steel according to an embodiment of the present invention contains Ni: 25 to 50%, Nb: 3.8 to 6.0%, Zr: 0.5% or less, B: 0.001 to 0.05%, Cr: 12 to 25%, Ti: 1.6% or less, Mo: 4.8% or less, and W: 5.2% or less in mass %, and the balance Fe and unavoidable impurities, wherein the parameter Ps represented by the following formula (1) satisfies Ps≦38, Ps=8.3[Nb]−7.5[Ti]+2.4[Mo]+3.5[W]  formula (1), where [Nb], [Ti], [Mo], and [W] represent the contents of Nb, Ti, Mo, and W, respectively, in mass %.

PRECIPITATION-HARDENED STAINLESS STEEL ALLOYS

Forged precipitation-hardened stainless steel alloys are provided. The forged precipitation-hardened stainless steel alloy can include, by weight, about 14.0% to about 16.0% chromium, about 6.0% to about 8.0% nickel, about 1.25% to about 1.75% copper, about 1.0% to about 2.0% molybdenum, about 0.001% to about 0.05% carbon, a carbide forming element in an amount of about 0.3% to about 0.8% and greater than about 8 times that of carbon, the balance iron, and incidental impurities. Generally, the carbide forming element is selected from the group consisting of titanium, zirconium, tantalum, and a mixture thereof. 1. A forged precipitation-hardened stainless steel alloy comprising , by weight , about 14.0% to about 16.0% chromium , about 6.0% to about 8.0% nickel , about 1.25% to about 1.75% copper , about 1.0% to about 2.0% molybdenum , about 0.001% to about 0.05% carbon , a carbide forming element in an amount of about 0.3% to about 0.8% and greater than about 8 times that of carbon , the balance iron , and incidental impurities;wherein the carbide forming element is selected from the group consisting of titanium, zirconium, tantalum, and a mixture thereof.2. The forged precipitation-hardened stainless steel alloy of claim 1 , wherein the forged precipitation-hardened stainless steel alloy consists of claim 1 , by weight claim 1 , about 14.0% to about 16.0% chromium claim 1 , about 6.0% to about 8.0% nickel claim 1 , about 1.25% to about 1.75% copper claim 1 , about 1.0% to about 2.0% molybdenum claim 1 , about 0.001% to about 0.05% carbon claim 1 , a carbide forming element in an amount of about 0.3% to about 0.8% and greater than about 8 times that of carbon claim 1 , the balance iron claim 1 , and incidental impurities.3. The forged precipitation-hardened stainless steel alloy of claim 1 , wherein the carbide forming element is selected from the group consisting of titanium claim 1 , zirconium claim 1 , and tantalum.4. The forged precipitation-hardened stainless ...

Devices And Methods For Exhaust Vectoring In Tilt Rotor Aircraft

Exhaust redirecting devices are described that are suitable for use in tilt rotor aircraft. Such devices are constructed of light weight material and permit redirection of exhaust gases from turbojet engines of tilt rotor aircraft as nacelles of the aircraft transition between vertical and horizontal flight. Use of a controller permits coordination between exhaust redirection and nacelle position. 1600. An exhaust directing device () for a tilt rotor aircraft , comprising:{'b': '610', 'an exhaust inlet portion () in fluidic communication with an exhaust stream of the tilt rotor aircraft;'}{'b': 630', '640, 'an outlet portion () coupled to a nozzle assembly (); and'}{'b': 620', '610', '630, 'an intermediate portion () interposed between the exhaust inlet portion () and the outlet portion (),'}{'b': 620', '610', '615', '620', '630', '625, 'wherein the intermediate portion () is slidably and fluidically coupled to the exhaust inlet portion () by a first interface () and the intermediate portion () is slidably and fluidically coupled to the outlet portion () by a second interface (), and'}{'b': 600', '600', '610', '620', '630', '600', '600', '610', '630, 'wherein the exhaust directing device () has a first position (A) in which the exhaust inlet portion (), the intermediate portion (), and the outlet portion () are in a linear arrangement, and wherein the exhaust directing device () has a second position (B) in which the exhaust inlet portion () and the outlet portion () are angled relative to one another.'}2600615625600600600. The exhaust directing device () of claim 1 , wherein the first interface () and the second interface () are not in a perpendicular orientation relative to a long axis of the exhaust directing device () when the exhaust directing device () is in the first position (A).3600610611612630631632620621611631622612632. The exhaust directing device () of claim 1 , wherein the exhaust inlet portion () comprises a first long wall portion () and a first ...

Plated polymers with intumescent compositions and temperature indicators

A plated polymer component is disclosed. The plated polymer component may comprise a polymer support, a metal plating deposited on a surface of the polymer support, and at least one flame-retardant additive included in the polymer support. In another aspect, the plated polymer component may comprise a polymer substrate, a metal plating deposited on a surface of the polymer substrate, and a temperature-indicating coating applied to at least one of of the polymer substrate.

METHOD FOR PRODUCING JOURNAL PART OF 9 TO 12% Cr STEEL TURBINE ROTOR, AND JOURNAL PART PRODUCED BY THE METHOD

In a journal part of a 9 to 12 wt % Cr steel turbine rotor, a groove face is formed, and on the groove face, a lower build-up layer is formed by using a first welding material containing C: 0.10 to 0.25 wt %, Si: 0.20 to 0.80 wt %, Mn: 1.0 to 2.5 wt %, Ni: 0.4 to 1.0 wt %, Cr: 1.0 to 3.0 wt %, Mo: 0.2 to 1.5 wt %, V: 0.03 to 0.10 wt %, and a remainder composed of Fe and inevitable impurities, and further on this lower build-up layer, an upper build-up layer is formed using a second welding material containing C: 0.10 to 0.25 wt %, Si: 0.20 to 0.80 wt %, Mn: 1.0 to 2.5 wt %, Ni: 0.4 to 1.0 wt %, Cr: 1.0 to 3.0 wt %, Mo: 0.2 to 1.5 wt %, and a remainder consisting of Fe and inevitable impurities.

HIGH-MODULUS COATING FOR LOCAL STIFFENING OF AIRFOIL TRAILING EDGES

An airfoil is disclosed. The airfoil may comprise a leading edge, a body portion and a trailing edge formed from a high-modulus plating. The body portion of the airfoil may be formed from a material having a lower elastic modulus than the high-modulus plating. The high-modulus plating may improve the stiffness of the trailing edge, allowing for thinner trailing edges with improved fatigue life to be formed. 1. An airfoil , comprising:a leading edge;a body portion; anda trailing edge formed from a high-modulus plating, the body portion being formed from a material that has a lower elastic modulus than the high-modulus plating.2. The airfoil of claim 1 , wherein the material forming the body portion is selected from the group consisting of aluminum claim 1 , titanium claim 1 , and a composite material.3. The airfoil of claim 2 , wherein the high-modulus plating is formed from one or more layers of a metal or a metal alloy selected from the group consisting of nickel claim 2 , iron claim 2 , cobalt claim 2 , and an alloy of any of the foregoing elements comprising at least 50 wt. % of the alloy.4. The airfoil of claim 1 , wherein the body portion is truncated at a back side prior to the trailing edge claim 1 , and wherein the high-modulus plating is applied to a back surface of the back side to form the trailing edge.5. The airfoil of claim 4 , wherein the high-modulus plating is applied to the back surface of the body portion by a method selected from the group consisting of electrolytic plating claim 4 , electroless plating claim 4 , brush plating claim 4 , spray metal deposition claim 4 , chemical vapor deposition claim 4 , plasma vapor deposition claim 4 , and a powder spray deposition process.6. The airfoil of claim 4 , wherein the high-modulus plating has a thickness of about 1.3 mm near the back surface of the body portion claim 4 , and a thickness of about 0.025 mm near a tip of the trailing edge.7. The airfoil of claim 1 , wherein at least one surface of the ...

ADJUSTABLE SPACER WITH HARDENED ENDS

An adjustable spacer with hardened end portions and a non-hardened intermediate portion therebetween is mountable between a pair of roller bearings also mounted on a shaft such an axle or spindle or the like. The hardened material contacts the faces of the roller bearings but helps prevent wear therebetween and unwanted movement of the bearings on the shaft. The unhardened material allows the spacer to collapse in the axial direction to maintain desired axial loads on the bearings. 1. An adjustable spacer system comprising:an annular spacer configured to be mounted on a shaft to apply a force to one or more roller bearings mounted on said shaft, the annular spacer comprising a first end portion and a second end portion opposite said first end portion, the first end portion and the second end portion of said annular spacer comprising a hardened material; andan intermediate portion of said annular spacer located between said first end portion and said second end portion, said intermediate portion comprising a non-hardened material, the intermediate portion being more deformable than that first end portion.2. The system of wherein said annular spacer is configured to be assembled on a shaft between two roller bearings to apply a force axially on said two roller bearings.3. The system of wherein the first end portion comprises a first face exposed in an axial direction claim 2 , the first face being formed of a hardened material.4. The system of wherein the second end portion comprises a second face exposed in an axial direction claim 3 , the second face being formed of a hardened material.5. The system of wherein said annular spacer is formed from a first starting material and wherein the first end portion and second end portion are hardened from said first starting material.6. The system of wherein said first end portion and second end portion are hardened without hardening the intermediate portion of said annular spacer.7. The system of wherein the intermediate ...

Brush sealing arrangement for a turbomachine, installation securing arrangement and turbomachine

Disclosed is a brush sealing arrangement for a turbomachine, comprising at least one stator, one rotor and one brush seal. The brush seal comprises at least one brush element and one ring for receiving the brush element. The brush sealing arrangement seals a gap between the stator and the rotor. The ring is connected to the stator by means of a press-fit. The ring comprises a first material having a first thermal expansion coefficient and at least a portion of the stator comprises for receiving the ring a second material having a second thermal expansion coefficient. Also disclosed are an installation securing arrangement comprising the brush sealing arrangement and a turbomachine.

PASSIVE INTERNAL ICE PROTECTION SYSTEMS FOR ENGINE INLETS

A system includes an engine cover covering a side-facing rotorcraft engine and having an opening and an ice protection member mounted on the engine cover between the opening and the engine, an area of the ice protection member smaller than an area of the opening. The ice protection member is configured to partially cover the opening to prevent ice having a particular size from entering into the engine and to allow air flow downstream into the engine. 1. A system comprising:an engine cover covering a side-facing rotorcraft engine, the engine cover having an opening; andan ice protection member mounted on the engine cover between the opening and the engine, an area of the ice protection member smaller than an area of the opening,wherein the ice protection member is configured to partially cover the opening to prevent ice having a particular size from entering into the engine and to allow air flow downstream into the engine.2. The system of claim 1 , wherein the ice protection member comprises a mesh screen.3. The system of claim 2 , wherein the mesh screen is configured to catch and hold the ice with suction generated by an air flow into the engine claim 2 , the particular size of the ice larger than a size certified for the engine.4. The system of claim 3 , wherein the ice protection member is configured to catch the ice with the particular size of about slightly wider than a half of the opening.5. The system of claim 2 , wherein the mesh screen comprises a plurality of pores each having a pore size of about 0.25 inch up to 0.50 inch.6. The system of claim 2 , wherein the mesh screen comprises stainless steel.7. The system of claim 2 , wherein the ice protection member comprises a frame surrounding the mesh screen claim 2 , and the frame comprises fiberglass.8. The system of claim 7 , wherein the ice protection member is mounted on the engine cover by fastening the frame onto the engine cover.9. The system of claim 1 , wherein the engine cover is configured to be ...

HEAT RESISTANT CAST STEEL HAVING SUPERIOR HIGH TEMPERATURE STRENGTH AND OXIDATION RESISTANCE

A heat-resistant cast steel includes, based on a total weight of the heat-resistant cast steel, 0.2 to 0.4 wt % carbon; 0.5 to 1.0 wt % silicon; 0.3 to 0.8 wt % manganese; 0.7 to 1.0 wt % nickel; 17 to 23 wt % chromium; 0.5 to 1.0 wt % niobium; 1.5 to 2.0 wt % tungsten; 0.2 to 0.5 wt % vanadium; 0.05 to 0.1 wt % cerium; 0.05 to 0.1 wt % nitrogen; and a balance of iron. 1. A heat-resistant cast steel comprising:based on a total weight of the heat-resistant cast steel,0.2 to 0.4 wt % carbon;0.5 to 1.0 wt % silicon;0.3 to 0.8 wt % manganese;0.7 to 1.0 wt % nickel;17 to 23 wt % chromium;0.5 to 1.0 wt % niobium;1.5 to 2.0 wt % tungsten;0.2 to 0.5 wt % vanadium;0.05 to 0.1 wt % cerium;0.05 to 0.1 wt % nitrogen; anda balance of iron.2. The heat-resistant cast steel of claim 1 , wherein:a content of carbon is 0.27 to 0.38 wt %;a content of silicon is 0.65 to 0.95 wt %;a content of manganese is 0.35 to 0.72 wt %;a content of nickel is 0.53 to 0.94 wt %;a content of chromium is 17.5 to 22.8 wt %;a content of niobium is 0.53 to 0.92 wt %;a content of tungsten is 1.52 to 1.86 wt %;a content of vanadium is 0.25 to 0.43 wt %;a content of cerium is 0.06 to 0.09 wt %; anda content of nitrogen is 0.05 to 0.07 wt %.3. The heat-resistant cast steel of claim 1 , wherein:a content of carbon is 0.38 wt %;a content of silicon is 0.83 wt %;a content of manganese is 0.41 wt %;a content of nickel is 0.93 wt %;a content of chromium is 22.8 wt %;a content of niobium is 0.85 wt %;a content of tungsten is 1.79 wt %;a content of vanadium is 0.43 wt %;a content of cerium is 0.08 wt %; anda content of nitrogen is 0.07 wt %.4. An exhaust manifold comprising the heat-resistant cast steel of .5. An exhaust manifold comprising the heat-resistant cast steel of .6. An exhaust manifold comprising the heat-resistant cast steel of .7. A turbine housing comprising the heat-resistant cast steel of .8. A turbine housing comprising the heat-resistant cast steel of .9. A turbine housing comprising the heat- ...

Interlocked plated polymers

A plated polymer component is disclosed. The plated polymer component may comprise a polymer substrate having an outer surface, a metal plating attached to the outer surface of the polymer substrate, and at least one interlocking feature connecting the polymer substrate and the metal plating. The interlocking feature may improve the interfacial bond strength between the polymer substrate and the metal plating.

COMPONENTS HAVING SEPARABLE OUTER WALL PLUGS FOR MODULATED FILM COOLING

A component includes an outer wall that includes an exterior surface and an opposite interior surface. The component also includes at least one internal void defined adjacent the interior surface and configured to receive a cooling fluid therein. The component further includes a plurality of openings defined in and extending through the outer wall such that the outer wall defines an edge of each of the plurality of openings. Additionally, the component includes a plurality of separable plugs each positioned in a corresponding opening. Each of the separable plugs is sized to fit within the corresponding opening such that a clearance gap is defined between the separable plug and the edge of the corresponding opening. Each of the separable plugs is coupled to the outer wall by at least one tab that extends across the clearance gap from the each separable plug to the edge of the corresponding opening. 1. A component comprising:an outer wall comprising an exterior surface and an opposite interior surface;at least one internal void defined adjacent said interior surface and configured to receive a cooling fluid therein;a plurality of openings defined in and extending through said outer wall such that said outer wall defines an edge of each of said plurality of openings; anda plurality of separable plugs, each plug of said plurality of separable plugs positioned in a corresponding opening of said plurality of openings, each of said separable plugs sized to fit within said corresponding opening such that a clearance gap is defined between said separable plug and said edge of said corresponding opening, each of said separable plugs coupled to said outer wall by at least one tab that extends across said clearance gap from said each separable plug to said edge of said corresponding opening.2. The component of claim 1 , further comprising a filler material positioned in said clearance gap of each of said separable plugs claim 1 , said filler material cooperates with each of ...

FERRITIC STEEL FOR TURBOCHARGERS

A waste gate component for a turbo charger made of a ferritic steel including C, Cr, Ni, Nb, V, Mn, and optionally Si, and Ti as main alloying elements. 1. A turbocharger component comprising a ferritic steel of the following composition:C 0.1 to 0.8 wt.-%,Cr 15.0 to 23.0 wt.-%,Ni 1.5 to 3.0 wt.-%,Nb 0.2 to 1.0 wt.-%, andV 0.2 to 1.0 wt.-%;Mn 1.0 to 4.0 wt.-%;wherein combined amount of Nb and V is at least 0.40 wt.-% and wherein the weight ratio of Mn to the total amount of Nb and V to is at least 1.6;optionally one or more of the following elements:Si 0.5 to 1.8 wt.-%,Ti 0.1 to 1.1 wt.-%;optionally other elements in a total amount of less than 3 wt.-% (impurities); andFe as balance.2. The turbocharger component according to claim 1 , wherein the ferritic steel is characterized by a microstructure having an average grain size of between 2 and about 4 claim 1 , measured according to ASTM E112-12.3. The turbocharger component according to claim 1 , wherein the steel is preparable by subjecting the ferritic steel to a heat treatment for at least 1 hour claim 1 , followed by cooling at a rate of at least 40° C. and up to 90° C./h.4. A method for preparing a turbo charger component claim 1 , said component comprising a ferritic steel of the following composition:C 0.1 to 0.8 wt.-%,Cr 15.0 to 23.0 wt.-%,Ni 1.5 to 3.0 wt.-%,Nb 0.2 to 1.0 wt.-%, andV 0.2 to 1.0 wt.-%;Mn 1.0 to 4.0 wt.-%;wherein combined amount of Nb and V is at least 0.40 wt.-% and wherein the weight ratio of Mn to the total amount of Nb and V to is at least 1.6;optionally one or more of the following elements:Si 0.5 to 1.8 wt.-%,Ti 0.1 to 1.1 wt.-%;optionally other elements in a total amount of less than 3 wt.-% (impurities); andFe as balance;wherein the steel is subjected to a heat treatment at 900 to 940° C. for at least 1 hour, followed by cooling at a rate of at least 40° C. and up to 90° C./h.5. The turbocharger component according to claims 1 , wherein the ferritic steel contains the following ...

TURBOMACHINE WITH AN INGESTION SHIELD AND USE OF THE TURBOMACHINE

A turbomachine, for instance a gas turbine or a steam turbine, has a stator with at least one stator component, a rotor with at least one rotor component, at least one working fluid channel for channeling a working fluid for driving the rotor, wherein the working fluid channel is bordered by the stator component and the rotor component, and a cavity located downstream of the stator component and upstream of the rotor component in respect of the flow of the working fluid in the working fluid channel. At least one heat shield is located in the cavity separating the cavity into a first cavity and a second cavity for reducing the working fluid ingress into the second cavity for protecting the stator component and/or the rotor component from an erosive attack of the working fluid. 115.-. (canceled)16. A turbomachine comprising:a stator with at least one stator component, with a guide vane component as a first one of the stator component and a stator ring as a second one of the stator component;a rotor with at least one rotor component;at least one working fluid channel for channeling a working fluid for driving the rotor, wherein the working fluid channel is bordered by the guide vane component and the rotor component,a cavity located downstream of the guide vane component and upstream of the rotor component in respect of the flow of the working fluid in the working fluid channel,at least one heat shield located in the cavity separating the cavity into a first cavity and a second cavity for reducing the working fluid ingress into the second cavity for protecting the stator ring and/or the rotor component from an erosive attack of the working fluid,wherein the heat shield is mechanically fixed between the stator ring and a guide vane component and the heat shield is a consumable.17. The turbomachine according to claim 16 ,wherein the working fluid is hot gas of a gas turbine or superheated steam of a steam turbine.18. The turbomachine according to claim 16 ,wherein the ...

SELECTIVE THERMAL BARRIER COATING REPAIR

A method of selectively applying an overlay coating to a coated article and a selectively treated coated article are provided. The method includes the steps of providing the coated article having a treatment region that includes a bond coat and a thermal barrier coating and selectively applying an overlay coating to the treatment region without stripping the treatment region from the coated article. The bond coat of the coated article which has been exposed to an operational temperature includes a first volume fraction of a β-phase microstructure that is less than a second volume fraction of a β-phase microstructure of a comparable bond coat of a comparable article which has not been exposed to the operational temperature. A coated article including an overlay coating selectively applied over a treatment region is also disclosed. 1. A method for treating a coated article , the method comprising:providing the coated article having a treatment region having a bond coat and a thermal barrier coating, the coated article having been exposed to an operational temperature; andselectively applying an overlay coating to the treatment region without stripping the treatment region from the coated article, the overlay coating enabling coating life extension of the coated article,wherein the bond coat having a first volume fraction of a β-phase microstructure that is less than a second volume fraction of a β-phase microstructure of a comparable bond coat of a comparable article which has not been exposed to the operational temperature.2. The method of claim 1 , wherein the bond coat is a MCrAlY claim 1 , M being selected from the group consisting of nickel claim 1 , cobalt claim 1 , iron claim 1 , alloys thereof claim 1 , and combinations thereof.3. The method of claim 1 , wherein the first volume fraction of the β-phase microstructure is reduced by between about 20% and about 80% relative to the second volume fraction of the β-phase microstructure of the comparable bond coat.4. ...

Systems and methods for making blade sheaths

A method of making a sheath for an airfoil may include the steps of forming an upper sleeve and a lower sleeve, and forming a central portion bonded to the upper sleeve and the lower sleeve. The central portion may be formed by depositing a material on the upper sleeve and the lower sleeve. A portion of the material may be removed from at least one of the central portion, the upper sleeve, or the lower sleeve. The sheath may include a first flank, a central portion bonded to the first flank, and a second flank bonded to the central portion. The central portion may have a substantially uniform microstructure resulting from additive manufacturing.

MOLD ASSEMBLY INCLUDING A DEOXYGENATED CORE AND METHOD OF MAKING SAME

A mold assembly for use in forming a component having an internal passage defined therein includes a mold defining a mold cavity therein, and a deoxygenated core positioned with respect to the mold. The deoxygenated core includes an inner wall that at least partially defines a sealed core chamber within the deoxygenated core. The sealed core chamber has a substantially reduced oxygen content, and a portion of the deoxygenated core is positioned within the mold cavity such that the inner wall of the portion of the deoxygenated core defines the internal passage when the component is formed in the mold assembly. 1. A mold assembly for use in forming a component having an internal passage defined therein , said mold assembly comprising:a mold defining a mold cavity therein; anda deoxygenated core positioned with respect to said mold, said deoxygenated core comprising an inner wall that at least partially defines a sealed core chamber within said deoxygenated core, wherein:said sealed core chamber has a substantially reduced oxygen content, anda portion of said deoxygenated core is positioned within said mold cavity such that said inner wall of said portion of said deoxygenated core defines the internal passage when the component is formed in said mold assembly.2. The mold assembly of claim 1 , wherein said deoxygenated core further comprises a hollow structure that extends from a first end to a second end claim 1 , a first sealing plug coupled to said hollow structure proximate said first end claim 1 , and a second sealing plug coupled to said hollow structure proximate said second end.3. The mold assembly of claim 2 , wherein said hollow structure is formed from a first material selected to have a melting point greater than a casting temperature of the component.4. The mold assembly of claim 3 , wherein said first material is at least one of a titanium-based material claim 3 , a tantalum-based material claim 3 , and a niobium-based material.5. The mold assembly of ...

Hot gas path component and methods of manufacture

Various embodiments of the disclosure include a turbomachine component. and methods of forming such a component. Some embodiments include a turbomachine component including: a first portion including at least one of a stainless steel or an alloy steel; and a second portion joined with the first portion, the second portion including a nickel alloy including an arced cooling feature extending therethrough, the second portion having a thermal expansion coefficient substantially similar to a thermal expansion coefficient of the first portion, wherein the arced cooling feature is located within the second portion to direct a portion of a coolant to a leakage area of the turbomachine component.

ROTOR CONSTRUCTION FOR HIGH SPEED MOTORS

A rotor shaft for a high speed motor that has a coating that is secured to a shaft body. The coating and the shaft body are formed from dissimilar materials. More specifically, the coating may be an alloy material, such as, for example, a copper alloy, while the shaft body may be a steel material. According to certain embodiments, the alloy material of the coating may be secured to at least a portion of a rotor body blank in a solution treated condition via a low temperature welding procedure. Additionally, the coating may be hardened, such as for example, through the use of an age hardening process. The coating and the rotor body blank may be machined together to form the rotor shaft. According to certain embodiments, such machining may configure the rotor shaft for use with a turbo-compressor that is configured for air compression. 1. A rotor shaft for a high speed motor , the rotor shaft comprising:a shaft body configured for rotational displacement during operation of the high speed motor, the shaft body being constructed from a steel material; anda coating secured to at least a portion of an outer surface of the shaft body, the coating configured to carry an induced electrical current for the rotational displacement of the shaft body, the coating being an alloy material, the alloy material of the coating and the steel material of the shaft body being dissimilar materials.2. The rotor shaft of claim 1 , wherein the alloy material is a copper alloy.3. The rotor shaft of claim 2 , wherein the coating is secured to the shaft body by a low temperature bonding process.4. The rotor shaft of claim 3 , wherein the coating is secured to the shaft body by explosion welding.5. The rotor shaft of claim 4 , wherein the coating is an age hardened material.6. The rotor shaft of claim 5 , wherein the shaft body has a unitary construction.7. The rotor shaft of claim 6 , wherein the rotor shaft is configured to operate at a tip speed greater than 300 meters/second.8. The rotor ...

METHOD FOR PRODUCING TURBINE ROTOR AND METHOD FOR PRODUCING TURBINE

A method for producing a turbine rotor includes forming a rotor base material having a maximum outer diameter of 1000 mm or less from low-alloy steel including carbon, silicon, manganese, nickel, chromium, molybdenum, and vanadium; heating the rotor base material, by a quenching process, to a temperature range of 940° C. to 960° C.; performing oil quenching on the rotor base material, after the quenching process, in a temperature range of 250° C. to 500° C., at a cooling rate of at least 2.0° C./min; and tempering the rotor base material, after the quenching process, at a temperature of at least 630° C., and under a condition that a tempering parameter P is in the range of 19700 to 19900, wherein P is defined by the formula P=T (C+log(t)). 1. A method for producing a turbine rotor , comprising: carbon of 0.20% to 0.35%,', 'silicon of up to 0.35%,', 'manganese of up to 1.00%,', 'nickel of 0.50% to 1.50%,', 'chromium of 2.00% to 2.50%,', 'molybdenum of 0.90% to 1.50%, and', 'vanadium of 0.20% to 0.30%;, 'forming a rotor base material having a maximum outer diameter of 1000 mm or less from low-alloy steel containing, in weight %heating the rotor base material, by a quenching process, to a temperature range of 940° C. to 960° C.;performing oil quenching on the rotor base material, after the quenching process, in a temperature range of 250° C. to 500° C., at a cooling rate of at least 2.0° C./min; andtempering the rotor base material, after the quenching process, at a temperature of at least 630° C., and under a condition that a tempering parameter P is in a range of 19700 to 19900, wherein P is defined by a Formula Expression P=T (C+log t)), where T is an absolute temperature measured in Kelvin, t is time measured in hours, and C is a material constant.2. A method for producing a turbine , comprising:{'claim-ref': {'@idref': 'CLM-00001', 'claim 1'}, 'fixing a plurality of blade rows to a turbine rotor such that the plurality of blade rows is arranged in a direction of a ...

COMPOUND ENGINE ASSEMBLY WITH CANTILEVERED COMPRESSOR AND TURBINE

A compound engine assembly with an engine core including at least one internal combustion engine, a compressor, and a turbine section where the turbine shaft is configured to compound power with the engine shaft. The turbine section may include a first stage turbine and a second stage turbine. The turbine shaft is rotationally supported by a plurality of bearings all located on a same side of the compressor rotor(s) and all located on a same side of the turbine rotor(s), for example all located between the compressor rotor(s) and the turbine rotor(s), such that the compressor rotor(s) and the turbine rotor(s) are cantilevered. A method of driving a rotatable load of an aircraft is also discussed. 1. A compound engine assembly comprising:an engine core including at least one internal combustion engine in driving engagement with an engine shaft;a compressor having an outlet in fluid communication with an inlet of the engine core, the compressor including at least one compressor rotor connected to a turbine shaft;a turbine section having an inlet in fluid communication with an outlet of the engine core, the turbine section including at least one turbine rotor connected to the turbine shaft;wherein the turbine shaft is configured to compound power with the engine shaft; andwherein the turbine shaft is rotationally supported by a plurality of bearings, all of the plurality of bearings being located between the at least one compressor rotor and the at least one turbine rotor such that the at least one compressor rotor and the at least one turbine rotor are cantilevered.2. The compound engine assembly as defined in claim 1 , wherein the turbine shaft is connected to the engine shaft through a gear train contained in a casing claim 1 , the compressor and turbine section being located outside of the casing claim 1 , the plurality of bearings being contained in the casing.3. The compound engine assembly as defined in claim 2 , further comprising a lubricant circulation system ...

ELECTRIC CONDUCTION STRUCTURE FOR JET ENGINE

An electric conduction structure for conducting and diverting electric current from a vane main body of an cutlet guide vane into en exterior support structure is comprised of: a sheath of a metal covering a leading edge of the vane main body; and an electrically conductive pad of the metal comprising a contact portion so dimensioned as to have an overlap with an end of the sheath, and a washer portion into which a bolt for being tightened into the support structure is insertable, wherein any joints of a weld, a spot-weld, a solder, a bond by an electrically conductive paste and a crimp establish connection between the end of the sheath and the contact portion. 1. An electric conduction structure for conducting and diverting electric current from a vane main body of an outlet guide vane into an exterior support structure , comprising:a sheath of a metal covering a leading edge of the vane main body; andan electrically conductive pad of the metal comprising a contact portion so dimensioned as to have an overlap with an end of the sheath, and a washer portion into which a bolt for being tightened into the support structure is insertable,wherein any joints of a weld, a spot-weld, a solder, a bond by an electrically conductive paste and a crimp establish connection between the end of the sheath and the contact portion.2. The electric conduction structure of claim 1 , wherein the metal is any of titanium claim 1 , titanium alloys claim 1 , nickel claim 1 , nickel alloys claim 1 , and stainless steels.3. The electric conduction structure of claim 1 , wherein the overlap has a width of 1 mm or more and a length of 10 mm or more.4. The electric conduction structure of claim 1 , further comprising:an electrically conductive wire interposed between the sheath and the vane main body and electrically connected with the electrically conductive pad. This application is a Continuation Application of PCT International Application No. PCT/JP2014/069337 (filed Jul. 22, 2014), which ...

STEAM TURBOMACHINE VALVE HAVING A FLOATING SEAL ASSEMBLY

A steam turbomachine valve includes a valve body having an inlet portion, an outlet portion, and an interior portion. The interior portion includes an inner wall. A valve member is moveably disposed within the interior portion of the valve body. The valve member includes an outer surface that is spaced from the inner wall by a gap. A floating seal is mounted to the inner wall. The floating seal spans the gap and contacts the outer surface of the valve member. 1. A steam turbomachine valve comprising:a valve body including an inlet portion, an outlet portion, and an interior portion, the interior portion including an inner wall;a valve member moveably disposed within the interior portion of the valve body, the valve member including an outer surface that is spaced from the inner wall by a gap; anda floating seal mounted to the inner wall, the floating seal spanning the gap and contacting the outer surface of the valve member.2. The steam turbomachine valve according to claim 1 , further comprising: a first seal support mounted to the inner wall and a second seal support mounted to the inner wall spaced from the first seal support claim 1 , the floating seal being arranged between the first and second seal supports.3. The steam turbomachine valve according to claim 2 , wherein each of the first and second seal supports extends into claim 2 , and is constrained by claim 2 , the inner wall.4. The steam turbomachine valve according to claim 2 , wherein the first seal support comprises a first split ring and the second seal support comprises a second split ring.5. The steam turbomachine valve according to claim 2 , wherein each of the first and second seal supports are formed from a nickel-chromium based superalloy.6. The steam turbomachine valve according to claim 1 , wherein the floating seal comprises a plurality of seal members.7. The steam turbomachine valve according to claim 1 , wherein the floating seal is formed from a nickel-chromium based superalloy.8. The ...

STEEL SOFT WALL FAN CASE

A steel soft wall fan case assembly according to one embodiment configured with a thin-walled steel support structure shell including a plurality of annular axial walls of thin sheet metal reinforced by a plurality of rings interconnecting axially adjacent annular axial walls. The steel support structure shell is structurally integrated with honeycomb materials and an annular metallic inner wall. A fabric containment layer may be wrapped around one of the annular axial walls of the steel support structure shell. 1. A turbine engine having a fan case surrounding a set of fan blades rotating about a central axis of a turbine engine , the fan case comprising:a steel support structure shell having a plurality of annular axial walls of sheet metal in an axial series including first, second and third annular axial walls, the second annular axial wall having a diameter greater than a diameter of the respective first and third annular axial walls, a plurality of radially extending rings including a first ring radially interconnecting the first and second annular axial walls and a second ring radially interconnecting the second and third annular axial walls;an annular metallic inner axial wall positioned within and secured to the support structure shell;honeycomb material sandwiched radially between the annular metallic inner axial wall and the second annular axial wall; anda layer of containment fabric material wrapped around a radial outer surface of the second annular axial wall.2. The turbine engine as defined in wherein a radial outer edge of the respective first and second rings projects radially outwardly from the second annular axial wall.3. The turbine engine as defined in wherein the annular metallic inner axial wall is aluminium.4. The turbine engine as defined in further comprising additional honeycomb material secured to a radially inner side of the annular metallic inner axial wall claim 1 , and wherein the honeycomb material and the additional honeycomb ...

MULTI-MATERIAL LEADING EDGE PROTECTOR

An airfoil that includes an airfoil body having a root and a tip, and convex and concave sides that extend between a leading edge and a trailing edge. The airfoil also includes at least a first cladding element that is attached to the airfoil body. The first cladding element includes a first portion and a second portion. The second portion is configured to separate from the first portion when the first cladding element encounters a force of at least a predetermined amount. 1. An airfoil , comprising:an airfoil body having a root and a tip, and convex and concave sides extending between a leading edge and a trailing edge;at least a first cladding element attached to the airfoil body;the first cladding element including a first portion and a second portion; andthe second portion being configured to separate from the first portion when the first cladding element encounters a force of at least a predetermined amount.2. The airfoil of wherein the airfoil body comprises a composite material including a matrix having reinforcing fibers embedded therein.3. The airfoil of wherein the airfoil body comprises a polymeric matrix composite claim 2 , including carbon reinforcing fibers.4. The airfoil of wherein the first cladding element is a leading edge guard attached to the leading edge of the airfoil body claim 2 , the leading edge guard comprising a nose with spaced-apart first and second wings extending therefrom.5. The airfoil of the airfoil body includes a second cladding element.6. The airfoil of wherein the second cladding element is a tip cap.7. The airfoil of wherein the first portion of the first cladding element and the second portion of the second cladding element define a boundary and the first cladding element is configured to fail near the boundary when the first cladding element encounters a predetermined force.8. The airfoil of wherein the first portion of the first cladding element is comprised of a first material and the second portion of the first cladding ...

TURBINE ROTOR MATERIAL FOR GEOTHERMAL POWER GENERATION AND METHOD FOR PRODUCING THE SAME

A turbine rotor material for geothermal power generation containing C: 0.20 to 0.30 mass %, Si: 0.01 to 0.2 mass %, Mn: 0.5 to 1.5 mass %, Cr: 2.0 to 3.5 mass %, V: more than 0.15 mass % and 0.35 mass % or less, predetermined amounts of Ni and Mo, and a remainder consisting of Fe and inevitable impurities, the Ni made to be more than 0 and 0.25 mass % or less, the Mo made to be 1.05 to 1.5 mass %. Even a body diameter of 1600 mm or more can thereby be quenched, enabling provision of a turbine rotor material for geothermal power generation less prone to stress corrosion cracking even in a hydrogen sulfide environment and a method for producing the same. 14-. (canceled)5. A turbine rotor material for geothermal power generation , comprising:C: 0.20 to 0.30 mass %;Si: 0.01 to 0.2 mass %;Mn: 0.5 to 1.5 mass %;Cr: 2.0 to 3.5 mass %;V: more than 0.15 mass % and 0.35 mass % or less;predetermined amounts of Ni and Mo; anda remainder consisting of Fe and inevitable impurities, the Ni made to be more than 0 and0.25 mass % or less, the Mo made to be 1.05 to 1.5 mass %.6. The turbine rotor material for geothermal power generation according to claim 5 ,wherein there is no ferrite in a matrix structure and the matrix structure is a bainitic homogeneous microstructure.7. The turbine rotor material for geothermal power generation according to claim 5 ,wherein the turbine rotor material for geothermal power generation is provided with a body having a diameter of at least 1600 mm, room-temperature 0.2% yield strength of 685 MPa or more, room-temperature Charpy impact absorption energy of 20 J or more, and ductility-brittleness transition temperature of 80° C. or lower.8. The turbine rotor material for geothermal power generation according to claim 6 , wherein the turbine rotor material for geothermal power generation is provided with a body having a diameter of at least 1600 mm claim 6 , room-temperature 0.2% yield strength of 685 MPa or more claim 6 , room-temperature Charpy impact ...

COMPACT ADVANCED PASSIVE TIP CLEARANCE CONTROL

A section of a gas turbine engine includes a rotor blade designed to rotate about an axis. The section also includes a case positioned radially outward from the rotor blade and extending circumferentially about the axis. The section also includes a control ring being annular, positioned radially inward from the case and designed to move radially relative to the case. The section also includes a segmented blade outer air seal (BOAS) including a plurality of BOAS segments each being positioned radially outward from the rotor blade, movably coupled to the control ring, and designed to move circumferentially relative to each other such that a circumferential gap between each of the plurality of BOAS segments changes in size in response to a temperature change in the section of the gas turbine engine. 1. A section of a gas turbine engine , comprising:a rotor blade configured to rotate about an axis;a case positioned radially outward from the rotor blade and extending circumferentially about the axis;a control ring being annular, positioned radially inward from the case, and configured to move radially relative to the case; anda segmented blade outer air seal (BOAS) including a plurality of BOAS segments each being positioned radially outward from the rotor blade, movably coupled to the control ring, and configured to move circumferentially relative to each other such that a circumferential gap between each of the plurality of BOAS segments changes in size in response to a temperature change in the section of the gas turbine engine.2. The section of claim 1 , further comprising a spring positioned radially between the segmented BOAS and the control ring and configured to exert a radially inward force on the segmented BOAS towards the rotor blade.3. The section of claim 1 , further comprising a circumferential locking tab coupled to the case claim 1 , slidably coupled to the segmented BOAS claim 1 , and configured to resist circumferential movement of the segmented BOAS ...

TURBO-MACHINE IMPELLER MANUFACTURING

A method of manufacturing a turbo-machine impeller, which includes a hub and a plurality of blades, using powder material in an additive-manufacturing process. The method includes: applying energy to the powder material by way of a high energy source, and solidifying the powder material. At least one bulky portion of the hub is irradiated such that the powder material solidifies in a lattice structure surrounded by an outer solid skin structure enclosing the lattice structure. 1. A method of manufacturing a turbo-machine impeller comprising a hub and a plurality of blades , using powder material in an additive-manufacturing process , the method comprising:applying energy to the powder material by way of a high energy source; andsolidifying the powder material, wherein at least one bulky portion of the hub is irradiated such that the powder material solidifies in a lattice structure surrounded by an outer solid skin structure enclosing the lattice structure.2. The method according to claim 1 , further comprising:depositing a first layer of powder material onto a target surface;irradiating a first portion of the first layer of powder material with the high energy source and solidifying the first portion of powder material, the first portion corresponding to a first cross-sectional region of the turbo-machine impeller;depositing a second layer of powder material onto the first portion;irradiating a second portion of said second layer of powder material with the high energy source and solidifying the second portion of powder material, the second portion corresponding to a second cross-sectional region of the turbo-machine impeller, the first portion and the second portion being joined to one another;depositing successive layers of powder material onto the previous portion and irradiating a portion of each successive layer to produce the turbo-machine impeller, further comprising a plurality of solidified, wherein each of the plurality of solidified layer portions ...

METHOD OF SIMULTANEOUSLY APPLYING THREE DIFFERENT DIFFUSION ALUMINIDE COATINGS TO A SINGLE PART

A method of simultaneously applying three different diffusion aluminide coatings to a metal part with an external surface and internal passageways includes first placing the part in an enclosed retort. Areas of the part are then coated with aluminum containing slurry for a first diffusion aluminide coating. Interior walls of the retort are then coated with a vapor source slurry for a second vapor phase aluminide coating on the surface of the part. Areas on the surface of the part not requiring coating are coated with masking materials. A closed chamber inside the retort containing source material for a third vapor phase diffusion aluminide coating for the internal passageways is then attached to the internal passageways. The retort is then placed in a furnace under a protective atmosphere and subjected to a diffusion heat treat to coat the external surfaces and internal passageways with the three different aluminide coatings. 1. A method of simultaneous application of three different diffusion aluminide coatings to a metal part with an external surface and internal passageways , the method comprising:placing the part in a retort;applying an aluminum containing source slurry for a first diffusion aluminide coating to a first area of the external surface of the part;coating the interior walls of the retort with a vapor phase coating source slurry for a second vapor phase diffusion aluminide coating on a second surface of the part;masking areas not requiring diffusion aluminide coating with masking material; andattaching a closed chamber inside the retort containing source material for a third vapor phase diffusion aluminide coating to the internal passageways of the part.2. The method of wherein the retort is placed in a furnace under a protective atmosphere and a diffusion heat treat is performed to coat the external surface and internal passageways of the part with the three diffusion aluminide coatings.3. The method of wherein the aluminide coatings comprise ...

TURBINE ENGINE WITH A SEAL

A turbine engine includes an engine core defining a higher pressure region and a lower pressure region. A seal can fluidly separate the higher pressure region from the lower pressure region and be movably mounted to a component within the turbine engine, where a side of the seal can confront the component. 1. A turbine engine comprising:an engine core comprising a stator and a rotor, and also defining a higher pressure region and a lower pressure region;a seal fluidly separating the higher pressure region from the lower pressure region and movably mounted to the stator, the seal having a first side confronting the stator and a second side confronting the rotor; andan air supply conduit fluidly coupling the higher pressure region to at least one of the first side and second side of the seal.2. The turbine engine of further comprising a spring configured to apply an axial force to the seal.3. The turbine engine of further comprising a second spring configured to apply a second force to the seal claim 2 , the second force being non-aligned with the axial force.4. The turbine engine of further comprising a first counterbore in a portion of the stator that confronts the first side claim 1 , wherein the first counterbore is fluidly coupled to the air supply conduit.5. The turbine engine of further comprising a second counterbore in a portion of the rotor that confronts the second side claim 1 , wherein the second counterbore is fluidly coupled to the air supply conduit.6. The turbine engine of wherein the seal comprises one of carbon claim 1 , steel claim 1 , or a nickel alloy.7. The turbine engine of wherein the seal further comprises a plurality of segments.8. The turbine engine of further comprising a wear coating on one of the seal claim 1 , the rotor claim 1 , or the stator.9. The turbine engine of further comprising a stator cooling passage fluidly coupling the higher pressure region to the first side of the seal.10. The turbine engine of further comprising a rotor ...

Gas turbine engine containment structures

A containment structure for a gas turbine engine includes a stator shroud with a wall. The stator shroud wall extends axially between a shroud inlet aperture and the shroud outlet aperture. The wall includes a stainless steel alloy material having less than 44% nickel by mass to provide containment protection for an impeller rotateably disposed within an interior of the stator shroud.

System and method for turbine nozzle cooling

A system having an impingement sleeve configured to receive a cooling flow is provided. The impingement sleeve includes a column of ports extending from an outer surface of the impingement sleeve, wherein each port of the column of ports is configured to direct an impingement stream toward a heated structure, and each impingement stream includes a portion of the cooling flow. Further, one or more pins are disposed outside the outer surface relative to the cooling flow, wherein each pin of the one or more pins is coupled between pairs of ports of the column of ports.

STAINLESS STEEL ALLOYS, TURBOCHARGER TURBINE HOUSINGS FORMED FROM THE STAINLESS STEEL ALLOYS, AND METHODS FOR MANUFACTURING THE SAME

Disclosed is an ferritic stainless steel alloy that includes, by weight, about 20% to about 22% chromium, about 0% to about 0.5% nickel, about 0.5% to about 1.0% manganese, about 1.0% to about 2.5% silicon, about 1.5% to about 2.2% tungsten, about 1.3% to about 1.8% niobium, about 0.35% to about 0.45% carbon, and a balance of iron. The alloy is suitable for use in turbocharger turbine housing applications for temperature up to about 1050° C. 1. An ferritic stainless steel alloy , comprising , by weight:about 20% to about 22% chromium;about 0% to about 0.5% nickel;about 0.5% to about 1.0% manganese;about 1.0% to about 2.5% silicon;about 1.5% to about 2.2% tungsten;about 1.3% to about 1.8% niobium;about 0.35% to about 0.45% carbon; anda balance of iron.2. The ferritic stainless steel alloy of comprising about 20% to about 21% chromium.3. The ferritic stainless steel alloy of comprising about 0.5% nickel.4. The ferritic stainless steel alloy of comprising about 0.6% to about 0.9% manganese.5. The ferritic stainless steel alloy of comprising about 1.5% to about 2.0% silicon.6. The ferritic stainless steel alloy of comprising about 1.7% to about 2.0% tungsten.7. The ferritic stainless steel alloy of comprising about 0% nickel.8. The ferritic stainless steel alloy of comprising about 1.5% to about 1.7% niobium.9. The ferritic stainless steel alloy of comprising about 0.38% to about 0.42% carbon.10. A turbocharger turbine housing comprising:an ferritic stainless steel alloy, wherein the ferritic stainless steel alloy comprises, by weight:about 20% to about 22% chromium;about 0% to about 0.5% nickel;about 0.5% to about 1.0% manganese;about 1.0% to about 2.5% silicon;about 1.5% to about 2.2% tungsten;about 1.3% to about 1.8% niobium;about 0.35% to about 0.45% carbon; anda balance of iron.11. The turbocharger turbine housing of comprising about 20% to about 21% chromium.12. The turbocharger turbine housing of comprising about 0.5% nickel.13. The turbocharger turbine housing ...

VARIABLE NOZZLE MECHANISM AND VARIABLE CAPACITY TURBOCHARGER

A variable nozzle mechanism for a variable capacity turbocharger includes: a first plate having an annular shape; a second plate facing the first plate and having an annular shape, the second plate and the first plate defining an exhaust gas path in between; a plurality of nozzle vanes rotatably supported between the first plate and the second plate; and an annular member inserted on an inner circumference side of the first plate. The first plate includes a front surface facing the exhaust gas path and a back surface on an opposite side to the front surface, the annular member includes a front surface facing the exhaust gas path and a back surface on an opposite side to the front surface, and a gap is provided between the first plate and the annular member, the gap extending along a thickness direction of the first plate, from a point between an inner circumference edge of the front surface of the first plate and an outer circumference edge of the front surface of the annular member. 112.-. (canceled)13. A variable nozzle mechanism for a variable capacity turbocharger , the variable nozzle mechanism comprising:a first plate having an annular shape;a second plate facing the first plate and having an annular shape, the second plate and the first plate defining an exhaust gas path in between;a plurality of nozzle vanes rotatably supported between the first plate and the second plate; andan annular member inserted on an inner circumference side of the first plate, whereinthe first plate includes a front surface facing the exhaust gas path and a back surface on an opposite side to the front surface,the annular member includes a front surface facing the exhaust gas path and a back surface on an opposite side to the front surface,a gap is provided between the first plate and the annular member, the gap extending along a thickness direction of the first plate, from a point between an inner circumference edge of the front surface of the first plate and an outer circumference ...

STEAM TURBINE INNER CASING COMPONENT AND REPAIR METHOD THEREFOR

Embodiments of the present invention relate to an inner casing component configured to form part of a steam flow path of a last stage of an axial flow steam turbine, the steam turbine inner casing component having a base made of nodular cast iron and a coating, on the base, in a region exposed to the steam flow path, consisting of manganese austenitic steel. 1. An inner casing component configured to form part of a steam flow path of a last stage of an axial flow steam turbine , the steam turbine inner casing component comprising:a base made of nodular cast iron; anda coating, on the base, in a region exposed to the steam flow path, comprising manganese austenitic steel.2. The inner casing component of claim 1 , wherein the coating is comprised of a material defined by the code EN 1.4370.3. The casing component of claim 1 , wherein the last stage comprises a stationary vane row and a downstream rotating blade row claim 1 , and wherein the coating is located in a region radially between the rotating blade row and the base.4. A method for manufacturing an inner casing component having a base configured to form part of a steam flow path of a last stage of an axial flow low pressure steam turbine claim 1 , the method comprising the step of:applying a coating of manganese austenitic steel to the base in a region exposed to the steam flow path.5. The method of claim 4 , wherein the last stage comprises a stationary vane row and a downstream rotating blade row claim 4 , further comprising the step of applying the coating to the inner casing component in a location radially between the rotating blade row and the base.6. The method of claim 4 , wherein the coating is applied by welding.7. A method for repairing erosion damage of an inner casing component configured to form part of a steam flow path of a last stage of an axial flow low pressure steam turbine claim 4 , the method comprising the step of:applying a coating of manganese austenitic steel to the base in a region ...

ROTOR STAGE OF AXIAL TURBINE WITH IMPROVED CHORD/PITCH RATIO

Rotor stage of an axial turbine comprising a shaft, adapted to rotate around an axis, and a plurality of blades, having at least one airfoil portion, which extends in a substantially radial direction normal to the axis, at a first radial distance from the axis, being arranged a number of airfoil portions lower than the number of airfoil portions arranged at a second radial distance from the axis, the first radial distance being smaller than the second radial distance, said rotor stage comprising a plurality of bearing blades, and a plurality of additional blade, said bearing blades comprising a first and a second rest element said additional blade being connected to said two subsequent bearing blades. 1. Rotor stage of an axial turbine comprising a shaft , adapted to rotate around an axis , and a plurality of blades , having at least one blade , which extends in a substantially radial direction normal to the axis , at a first radial distance from the axis , being arranged a number of airfoil portions lower than the number of airfoil portions which are arranged at a second radial distance from the axis , the first radial distance being smaller than the second radial distance , said rotor stage comprising a plurality of bearing blades , each of which comprises a root adapted to constrain the bearing blade to the shaft , a blade tip and an airfoil portion , having a suction side and a pressure side and extending from the top of the root to the blade tip in a substantially radial direction , said rotor stage comprising a plurality of additional blades , each of which comprises a blade tip , a base , an airfoil portion , extending from the base to the blade tip in a substantially radial direction , and a foot extending from the base in a substantially tangential direction normal to the axis and to the radial direction , said bearing blades comprising a first and second rest element extending from the suction and the pressure sides of the airfoil portion , respectively , ...

WEAR RESISTANT TURBINE BLADE TIP

A gas turbine engine includes: a turbine section including a casing extending circumferentially about a plurality of turbine blades and having at least one seal member coated with an abradable coating. At least one turbine blade has sides and a tip and at least one seal member is located adjacent to the tip of the at least one turbine blade. The tip of the at least one turbine blade has a wear resistant layer and an abrasive coating disposed on the wear resistant layer. The wear resistant layer has a thickness less than or equal to 10 mils (254 micrometers) and includes metal boride compounds. 1. A gas turbine engine comprising: a turbine section comprising a casing extending circumferentially about a plurality of turbine blades and having at least one seal member coated with an abradable coating; wherein at least one turbine blade has sides and a tip and at least one seal member is located adjacent to the tip of the at least one turbine blade , wherein the sides have a thermal barrier coating and the tip of the at least one turbine blade has a wear resistant layer and an abrasive coating disposed on the wear resistant layer , wherein wear resistant layer has a thickness less than or equal to 10 mils (254 micrometers) and comprises metal boride compounds.2. The gas turbine of claim 1 , wherein the wear resistant layer is formed in a base metal surface of the blade and the metal boride compounds comprise MBand M can be titanium claim 1 , vanadium claim 1 , chromium claim 1 , zirconium claim 1 , niobium claim 1 , molybdenum claim 1 , tantalum claim 1 , tungsten claim 1 , or a combination thereof.3. The gas turbine engine of claim 1 , wherein the wear resistant layer has a hardness of 1500 to 2500 HV 0.05 g.4. The gas turbine engine of claim 1 , wherein the blade comprises titanium claim 1 , titanium alloy claim 1 , steel claim 1 , nickel claim 1 , cobalt claim 1 , nickel alloy claim 1 , cobalt alloy claim 1 , iron- or nickel- or cobalt-based superalloys or a ...

METHOD FOR TREATING A COMPOSITE PART

A method for treating a composite part including a metal protective duct fixed to a core by a binder, so as to be able to separate the duct from the core, including the steps of: subjecting the metal duct to compressive stresses tending to lengthen same, and b) if necessary, heating or cooling the part in order to soften or weaken the binder. 129-. (canceled)30. A process for treating a composite part comprising a protective metal shield fastened to a core with the aid of a binder , with a view to separating the shield from the core , comprisinga) subjecting the metal shield to compressive stresses that tend to elongate it,b) if necessary, heating the part or cooling it in order to soften or embrittle the binder.31. The process as claimed in claim 30 , step a) being carried out before step b).32. The process as claimed in claim 30 , step b) being carried out before step a).33. The process as claimed in claim 30 , steps a) and b) taking place simultaneously claim 30 , step a) taking place in a furnace claim 30 , an oven or in a refrigerated chamber claim 30 , or by using a source of heat or cold coupled with a tool used to exert the compressive.34. The process as claimed in claim 30 , step a) being applied exclusively.35. The process as claimed in claim 30 , the introduction of the compressive stresses in step a) being carried out mechanically or by shock wave.36. The process as claimed in claim 30 , step a) being carried out so as to generate a plastic deformation of the metal shield claim 30 , and induce residual stresses in said shield.37. The process as claimed in claim 35 , the introduction of the compressive stresses being carried out by conventional or ultrasonic shot peening claim 35 , straightening claim 35 , hammering claim 35 , roller burnishing claim 35 , including LPB claim 35 , flap peening claim 35 , laser shock peening claim 35 , autofrettage claim 35 , cavitation peening claim 35 , water-jet peening and/or magnetic shock peening.38. The process as ...

ELASTIC SHEET USED FOR TURBINE FOLLOW-UP SUSPENDED STEAM SEAL BELT AND STEAM SEAL STRUCTURE THEREOF

The present invention discloses an elastic sheet used for a turbine follow-up suspended steam seal belt and a steam seal structure thereof, which comprises a plurality of elastic L-shaped metal sheets correspondingly overlapped on the same rim, one rim of the L-shaped metal sheet is a toothed rim, the toothed notches of the toothed rim extend laterally through the entire toothed rim so that the other rim of the L-shaped metal sheet can be bent longitudinally toward the toothed rim to form an arc shape; the toothed notches and the toothed tabs of the toothed rims of the plurality of L-shaped metal sheets are misoriented with each other to cover the toothed notches, and the other rim of the L-shaped metal sheet is fixed within the arc-shaped steam seal ring block along the steam seal ring teeth, the steam seal ring teeth extend out from the top of the toothed rim to seal the gap between the seal ring teeth and the turbine main shaft, and the toothed rims of the L-shaped metal sheet perform elastic beating reciprocately down after being subjected to the force at the top; the invention has the advantages of simple structure and the sealing of the main shaft side is well achieved; and the main shaft of the turbine can be completely achieved by utilizing the elastic characteristics of the seal elastic sheet of the invention. 1. An elastic sheet used for a turbine follow-up suspended steam seal belt , which is an elongated metal sheet , characterized in that the metal sheet is longitudinally bent in an elongated shape to form an elongated L-shape , one rim of the L-shaped metal sheet is a toothed rim alternately formed from a plurality of toothed notches and toothed tabs , the toothed notches extend laterally through the entire toothed rim so that the other rim of the L-shaped metal sheet can be bent longitudinally toward the toothed rim to form an arc shape; The toothed notches continue to extend forward an opening on the other rim , so that the toothed tabs of the ...

ARTICLE HAVING VARIABLE COMPOSITION COATING

A coated article includes a substrate and an MCrAlY coating supported on the substrate. The M includes at least one of nickel, cobalt, and iron, Cr is chromium, Al is aluminum, and Y is yttrium. The composition of the MCrAlY coating varies in an amount of at least one of Cr, Al, and Y by location on the substrate with respect to localized property requirements. In one example, the coated article is an article of a gas turbine engine. 1. A coated article comprising:a substrate; andan MCrAlY coating supported on the substrate, where the M includes at least one of nickel, cobalt, and iron, Cr is chromium, Al is aluminum, and Y is yttrium, the composition of the MCrAlY coating varying in an amount of at least one of Cr, Al, and Y by location on the substrate and with respect to localized property requirements.2. The coated article as recited in claim 1 , wherein the localized property requirements are selected from the group consisting of corrosion resistance claim 1 , erosion resistance claim 1 , spallation resistance claim 1 , fatigue resistance claim 1 , oxidation resistance claim 1 , creep resistance claim 1 , impact resistance claim 1 , and combinations thereof.3. The coated article as recited in claim 1 , wherein the composition of the MCrAlY coating varies in the amount of Cr.4. The coated article as recited in claim 1 , wherein the composition of the MCrAlY coating varies in the amount of Al.5. The coated article as recited in claim 1 , wherein the composition of the MCrAlY coating varies in the amount of Y.6. The coated article as recited in claim 1 , wherein the MCrAlY coating includes at least one alloying element of Co claim 1 , tantalum (Ta) claim 1 , tungsten (W) claim 1 , molybdenum (Mo) claim 1 , silicon (Si) claim 1 , hafnium (Hf) claim 1 , and zirconium (Zr) claim 1 , and the amount of the alloying element differs by location on the substrate and with respect to localized property requirements.7. The coated article as recited in claim 1 , wherein the ...

NANOCRYSTALLINE BAINITIC STEELS, SHAFTS, GAS TURBINE ENGINES, AND METHODS OF MANUFACTURING NANOCRYSTALLINE BAINITIC STEELS

A nanocrystalline bainitic steel consisting of, by weight percentage: 0.3% to 0.6% carbon; 9.0% to 20.0% nickel; up to 10% cobalt; 1.0% to 4.5% aluminium; up to 0.5% molybdenum; up to 0.5% manganese; up to 0.5% tungsten; up to 3.0% chromium; and the balance being iron and impurities. 1. A nanocrystalline bainitic steel consisting of , by weight percentage:0.3% to 0.6% carbon;9.0% to 20.0% nickel;up to 10% cobalt;1.0% to 4.5% aluminium;up to 0.5% molybdenum;up to 0.5% manganese;up to 0.5% tungsten;up to 3.0% chromium; andthe balance being iron and impurities.2. A nanocrystalline bainitic steel as claimed in claim 1 , consisting of claim 1 , by weight percentage:0.35% to 0.45% carbon;11.0% to 15.0% nickel;2.0% to 6.0% cobalt;2.0% to 3.0% aluminium;0.2% to 0.4% molybdenum;0.05% to 0.25% manganese;up to 0.5% tungsten;up to 3% chromium; andthe balance being iron and impurities.3. A nanocrystalline bainitic steel as claimed in claim 1 , consisting of claim 1 , by weight percentage:0.4% carbon;13.0% nickel;4.0% cobalt;2.5% aluminium;0.3% molybdenum;0.15% manganese; andThe balance being iron and impurities.4. A nanocrystalline bainitic steel as claimed in claim 1 , comprising a plurality of nickel aluminide intermetallic particles.5. A shaft comprising the nanocrystalline bainitic steel as claimed in .6. A shaft as claimed in claim 5 , wherein the shaft is a low pressure shaft and includes a low pressure compressor shaft and a low pressure turbine shaft claim 5 , the low pressure turbine shaft having a first end claim 5 , a second opposite end claim 5 , and a longitudinal axis extending between the first end and the second end claim 5 , the low pressure turbine shaft having no joint between the first end and the second end.7. A method of manufacturing a nanocrystalline bainitic steel as claimed in claim 1 , comprising maintaining a transformation temperature of the steel between 150 Celsius and 350 Celsius.8. A method as claimed in claim 7 , further comprising tempering the ...

VANE CARRIER FOR A COMPRESSOR OR A TURBINE SECTION OF AN AXIAL TURBO MACHINE

A vane carrier is provided for a compressor or a turbine section of an axial turbo machine, especially one of a gas turbine, steam turbine, compressor, expander, comprises least a first and second functional means. The first functional means is a cylinder made of a material with a coefficient of thermal expansion (CTE) below 1.3×10[1/K]. The cylinder is provided for carrying a plurality of vanes on its inner side. The second functional means is a support structure made of a material different to and less expensive than the material of said first functional means. The support structure is provided for defining an axial and lateral position of the first functional means within an outer casing of the axial turbo machine. 1. A vane carrier for a compressor or a turbine section of an axial turbo machine , especially one of a gas turbine , steam turbine , compressor , expander , said vane carrier comprising least a first and second functional means , whereby said first functional means is a cylinder made of a material with a coefficient of thermal expansion (CTE) below 1.3×10[1/K] , which cylinder is provided for carrying a plurality of vanes on its inner side , and whereby said second functional means is a support structure made of a material different to and less expensive than the material of said first functional means , which support structure is provided for defining an axial and lateral position of said first functional means within an outer casing of said axial turbo machine.2. The vane carrier as claimed in claim 1 , wherein said cylinder is split at a split plane and consists of two or more cylindrical parts claim 1 , which are connected together.3. The vane carrier as claimed in claim 2 , wherein said split plane is a horizontal or vertical or general axial plane.4. The vane carrier as claimed in claim 2 , wherein said cylindrical parts are connected together by bolts or pins.5. The vane carrier as claimed in claim 1 , wherein said support structure comprises a ...

NON-CONTACTING DYNAMIC SEAL

A seal for a gas turbine engine includes a full hoop outer ring, a shoe coupled to the full hoop outer ring via an inner beam and an outer beam, and a wave spring in contact with at least one of the inner beam or the outer beam. 1. A seal for a gas turbine engine comprising:a full hoop outer ring;a shoe coupled to the full hoop outer ring via an inner beam and an outer beam; anda wave spring in contact with at least one of the inner beam or the outer beam.2. The seal of claim 1 , wherein the wave spring is located between the inner beam and the outer beam.3. The seal of claim 1 , wherein the wave spring is located between the shoe and the inner beam.4. The seal of claim 1 , wherein the wave spring is located between the outer beam and the full hoop outer ring.5. The seal of claim 1 , wherein the wave spring comprises at least three antinodes.6. The seal of claim 5 , wherein the antinodes are configured to slide against at least one of the inner beam or the outer beam in response to a vibration in the seal.7. The seal of claim 1 , wherein the seal is a non-contacting dynamic seal.8. The seal of claim 1 , further comprising a plurality of inner segments claim 1 , wherein each inner segment comprises a respective wave spring.9. The seal of claim 1 , wherein the shoe is configured to move radially with respect to the outer ring.10. The seal of claim 9 , wherein the inner beam is disposed radially from the outer beam.11. The seal of claim 10 , wherein the wave spring is located radially between the inner beam and the outer beam.12. The seal of claim 10 , wherein the wave spring is located radially between the shoe and the inner beam.13. The seal of claim 10 , wherein the wave spring is located radially between the outer beam and the full hoop outer ring. This application is a divisional of, and claims priority to, and the benefit of U.S. application Ser. No. 14/852,838, entitled “NON-CONTACTING DYNAMIC SEAL,” filed on Sep. 14, 2015, which is a nonprovisional of, and ...

GAS TURBINE ENGINE FAN BLADE CONTAINMENT SYSTEMS

Gas turbine engine fan blade containment systems are disclosed. An example fan blade containment system includes a shield to be coupled to an aircraft structure and to at least partially surround a circumference of an aircraft engine. The shield is to be spaced from an outer surface the aircraft engine when the shield is coupled to the aircraft structure. A shield termination fitting is to couple a terminating end of the shield to the aircraft structure. 1. A fan blade containment system comprising:a shield to be coupled to an aircraft structure and to at least partially surround a circumference of an aircraft engine, the shield to be spaced from an outer surface of the aircraft engine when the shield is coupled to the aircraft structure; anda shield termination fitting coupled to a terminating end of the shield, the shield termination fitting to couple the terminating end of the shield to the aircraft structure.2. The system of claim 1 , wherein shield includes a first layer claim 1 , a second layer claim 1 , and a third layer claim 1 , wherein the second layer is positioned between the first layer and the third layer.3. The system of wherein the first layer includes steel claim 2 , the second layer includes a dry Kevlar fabric claim 2 , and the third layer includes aluminum.4. The system of claim 2 , wherein the terminating end includes a composite laminate claim 2 , the composite laminate having a hole to receive a fastener.5. The system of claim 4 , wherein the shield termination fitting includes a body defining a cavity to receive the terminating end of the shield claim 4 , wherein the body receives the fastener to retain the terminating end of the shield in the cavity.6. The system of claim 5 , wherein the shield termination fitting includes a clevis projecting from the body claim 5 , the clevis to couple to the aircraft structure claim 5 , the body and the clevis being a unitary structure claim 5 , the body including a first wall spaced from a second wall to ...

Turbine engine bearing used as a static electricity leak path

A gas turbine engine with a rotor having a shaft mounted to the engine with a plurality of electrically insulating bearings is provided. The electrically insulating bearings are coupled to the shaft to support the rotor in the engine. There is at least one electrically conductive bearing coupled to the shaft and that further support the rotor in the engine. An electrically conductive path is defined between the rotor and an electrical ground of the engine. The electrically conductive path is defined through the electrically conductive bearing to reach the electrical ground of the engine. A method for electrostatically discharging a rotor supported in the gas turbine engine is also provided.

Method for manufacturing shaft body

A method for manufacturing a shaft body by welding a plurality of shaft members together and forming the shaft body, the method including: a primary tempering step of subjecting a range in at least one of the shaft members, which is in the vicinity of an end of another shaft member side adjacent thereto, to tempering before the shaft members are welded together so that a strength of an end side of a region thereof is lower than a strength at a side which is opposite to the end of the region thereof; a welding step of welding the shaft members together after the primary tempering step; and a secondary tempering step of tempering the vicinity of a weld part between the shaft members after the welding step.

DOUBLE BORE BASKET

A compressor section or a turbine section of a gas turbine engine having an axis includes a drum. The compressor section or the turbine section also includes a plurality of bores extending radially inward from the drum including a first bore and a second bore. The compressor section or the turbine section also includes a first bore basket at least partially defining a first cavity such that the first bore has at least one surface located in the first cavity. The compressor section or the turbine section also includes a second bore basket at least partially defining a second cavity that is isolated from the first cavity such that the second bore has at least one surface located in the second cavity. 1. A compressor section or a turbine section of a gas turbine engine having an axis , comprising:a drum;a plurality of bores extending radially inward from the drum including a first bore and a second bore;a first bore basket at least partially defining a first cavity such that the first bore has at least one surface located in the first cavity; anda second bore basket at least partially defining a second cavity that is isolated from the first cavity such that the second bore has at least one surface located in the second cavity.2. The compressor section or the turbine section of claim 1 , wherein the drum defines a first bleed port in fluid communication with the first cavity claim 1 , and a second bleed port in fluid communication with the second cavity claim 1 , the first bleed port and the second bleed port each configured to receive compressed gas from a core airflow of the compressor section or the turbine section.3. The compressor section or the turbine section of claim 2 , wherein the first bore basket defines a fluid channel configured to receive the compressed gas from the first cavity via the first bleed port claim 2 , and the drum further defines a fluid out port configured to receive the compressed gas from the fluid channel of the first bore basket and to ...

PASSIVE INTERNAL ICE PROTECTION SYSTEMS FOR ENGINE INLETS

A system includes an engine cover covering a side-facing rotorcraft engine and having an opening and an ice protection member mounted on the engine cover between the opening and the engine, an area of the ice protection member smaller than an area of the opening. The ice protection member is configured to partially cover the opening to prevent ice having a particular size from entering into the engine and to allow air flow downstream into the engine. 1. An ice protection apparatus for a flush type engine inlet comprising:a frame surrounding a mesh screen, the frame comprising a first part and a second part;the first part extending in a first direction from a back edge to a front edge;the second part connected to the back edge of the first part and extending in a second direction at an angle to the first part;the second part configured to be attached to the flush type engine inlet such that the first part and the second part are below an opening of the flush type engine inlet; andthe first part configured to be smaller than the opening such that a portion of the opening remains uncovered at all times.2. The ice protection apparatus of claim 1 , wherein the angle comprises an obtuse angle claim 1 , an acute angle or about 90 degrees.3. The ice protection apparatus of claim 1 , wherein the portion of the opening comprises about 50% of an area of the opening.4. The ice protection apparatus of claim 1 , wherein:the first part further comprises a first side edge and a second side edge; andthe second part is connected to first side edge and the second side edge of the first part and extending in the second direction.5. The ice protection apparatus of claim 1 , wherein the mesh screen is configured to catch and hold a particular size of ice with a suction generated by an air flow into an engine claim 1 , wherein the particular size of ice is larger than a size certified for the engine.6. The ice protection apparatus of claim 1 , wherein the mesh screen comprises a plurality ...

Wear resistant airfoil tip

A gas turbine engine includes an engine static structure extending circumferentially about an engine centerline axis; a compressor section, a combustor section, and a turbine section within the engine static structure. At least one of the compressor section and the turbine section includes at least one airfoil and at least one seal member adjacent to the at least one airfoil. A tip of the at least one airfoil is metal having a wear resistant coating and the at least one seal member is coated with an abradable coating. The wear resistant coating is formed as a layer in a base metal surface of the airfoil, has a thickness less than or equal to 10 mils (254 micrometers) and includes metal boride compounds.

WEAR RESISTANT TURBINE BLADE TIP

A gas turbine engine includes: a turbine section including a casing extending circumferentially about a plurality of turbine blades and having at least one seal member coated with an abradable coating. At least one turbine blade has sides and a tip and at least one seal member is located adjacent to the tip of the at least one turbine blade. The tip of the at least one turbine blade has a wear resistant layer and an abrasive coating disposed on the wear resistant layer. The wear resistant layer has a thickness less than or equal to 10 mils (254 micrometers) and includes metal boride compounds.

INSERTS FOR SLOTTED INTEGRALLY BLADED ROTOR

Integrally bladed rotors (IBRs) are described. The IBRs include a central hub, an outer rim defining an outer circumference of the central hub, the outer rim defining a plurality of platforms, a plurality of circumferentially distributed blades, wherein a blade extends from each of the plurality of platforms, a rotor slot arranged between two adjacent blades, wherein the rotor slot is defined by a cut within the outer rim, and a rotor slot insert installed within the rotor slot, the rotor slot insert sized and shaped to fit within the rotor slot and prevent air leakage from a first side of the central hub to a second side of the central hub through the rotor slot during operation of the integrally bladed rotor.

Precipitation hardened martensitic stainless steel, manufacturing method therefor, and turbine moving blade and steam turbine using the same

The precipitation hardened martensitic stainless steel is characterized by containing, in percent by weight, 12.25 to 14.25% Cr, 7.5 to 8.5% Ni, 1.0 to 2.5% Mo, 0.05% or less C, 0.2% or less Si, 0.4% or less Mn, 0.03% or less P, 0.005% or less S, 0.008% or less N, 0.90 to 2.25% Al, the balance substantially being Fe, and the total content of Cr and Mo being 14.25 to 16.75%. A turbine moving blade and a steam turbine are manufactured by using this martensitic stainless steel.

DUCT ASSEMBLY AND METHOD OF FORMING

Duct assembly and method of forming a duct assembly, the method including providing a preform body having an outer surface, disposing the preform body adjacent a sacrificial mandrel such that at least a portion of the preform body abuts an outer surface of the sacrificial mandrel, forming the duct assembly by depositing metal on the outer surface of the sacrificial mandrel and the preform body to define a unitary metallic tubular element with integral preform body and where depositing metal occurs at a temperature that does not damage the sacrificial mandrel, and removing the sacrificial mandrel to define the duct assembly. 1. A method of forming a duct assembly , the method comprising:providing a preform body having an outer surface;disposing the preform body adjacent a sacrificial mandrel such that at least a portion of the preform body abuts an outer surface of the sacrificial mandrel;forming the duct assembly by depositing metal on the outer surface of the sacrificial mandrel and the preform body to define a unitary metallic tubular element with the preform body and where depositing metal occurs at a temperature that does not damage the sacrificial mandrel; andremoving the sacrificial mandrel to define the duct assembly.2. The method of claim 1 , further comprising forming claim 1 , via additive manufacturing or injection molding claim 1 , the sacrificial mandrel having the outer surface with a predetermined geometry.3. The method of wherein the depositing metal includes electroforming.4. The method of wherein the preform body is a metal body including nickel claim 1 , nickel alloy claim 1 , or steel.5. The method of wherein providing the preform body further comprises forming the preform body.6. The method of wherein forming the preform body includes at least one of additively manufacturing the preform body claim 5 , milling the preform body claim 5 , casting the preform body claim 5 , or machining the preform body.7. The method of wherein the preform body is ...

DUCT ASSEMBLY AND METHOD OF FORMING

Duct assembly and method of forming a duct assembly, the method including providing a preform having a unitary body with multiple sleeve sections defining multiple apertures, disposing multiple sacrificial mandrel pieces adjacent the preform body such that at least one of the multiple sacrificial mandrel pieces abuts at least one of the multiple sleeve sections, and forming the duct assembly to define a unitary metallic tubular element. 1. A method of forming a duct assembly , the method comprising:providing a preform having a unitary body with multiple sleeve sections defining multiple apertures and wherein the preform defines an interior surface and an exterior surface;disposing multiple sacrificial mandrel pieces adjacent the preform body such that at least one of the multiple sacrificial mandrel pieces abuts at least one of the multiple sleeve sections;forming the duct assembly by depositing metal on the multiple sacrificial mandrel pieces and the preform body to define a unitary metallic tubular element with the preform body and where depositing metal occurs at a temperature that does not damage the multiple sacrificial mandrel pieces; andremoving the multiple sacrificial mandrel pieces to define the duct assembly.2. The method of claim 1 , further comprising forming claim 1 , via additive manufacturing or injection molding claim 1 , the multiple sacrificial mandrel pieces having a predetermined geometry.3. The method of wherein the forming via injection molding comprises injecting sacrificial material into a mold around the preform body.4. The method of wherein the depositing metal includes electroforming.5. The method of wherein the preform body is a metal body including nickel claim 4 , nickel alloy claim 4 , or steel.6. The method of wherein providing the preform body further comprises forming the preform body via direct metal laser melting.7. The method of further comprising identifying a high stress area of the metallic tubular element prior to forming ...

Method for preventing corrosion and component obtained by means of such

A method for preventing corrosion in a component of a turbo-machine having a metal substrate made of carbon steel, low alloy steel and stainless steel includes: a first deposition step of depositing a first metallic layer on the substrate by electroplating; a second deposition step of depositing at least a second layer of a nickel alloy on the first layer by electroless plating; at least one thermal treatment step after the deposition steps, said thermal treatment being applied at a temperature and for a time depending on the overall thickness of the layers, the value of said temperature being directly proportional to the thickness, the value of said time being inversely proportional to the temperature.

AUSTENITIC HEAT RESISTANT STEEL AND TURBINE COMPONENT

The austenitic heat resistant steel of the embodiment contains: 24 to 50% by mass of Ni, 5 to 13% by mass of Cr, 0.1 to 12% by mass of Co, 0.1 to 5% by mass of Nb, 0.1 to 0.5% by mass of V, 1.90 to 2.35% by mass of Ti, 0.01 to 0.30% by mass of Al, 0.001 to 0.01% by mass of B, 0.001 to 0.1% by mass of C, and the balance being Fe and inevitable impurities. 1. Austenitic heat resistant steel , containing:24 to 50% by mass of Ni, 5 to 13% by mass of Cr, 0.1 to 12% by mass of Co, 0.1 to 5% by mass of Nb, 0.1 to 0.5% by mass of V, 1.90 to 2.35% by mass of Ti, 0.01 to 0.30% by mass of Al, 0.001 to 0.01% by mass of B, 0.001 to 0.1% by mass of C, and the balance being Fe and inevitable impurities.2. The austenitic heat resistant steel according to claim 1 , containing 0.01 to 0.20% by mass of Al.3. The austenitic heat resistant steel according to claim 1 , containing 0.01 to 0.10% by mass of Al.4. The austenitic heat resistant steel according to claim 1 , containing 34 to 45% by mass of Ni.5. The austenitic heat resistant steel according to claim 1 , containing 38 to 45% by mass of Ni.6. The austenitic heat resistant steel according to claim 1 ,{'sup': '−6', 'wherein the austenitic heat resistant steel has an average linear expansion coefficient of 18×10/K or less in temperatures from a room temperature to 700° C.'}7. A turbine component including a portion made of the austenitic heat resistant steel according to .8. A turbine component welded by the austenitic heat resistant steel according to . This application is a continuation of prior International Application No. PCT/JP2016/000048, filed on Jan. 7, 2016 which is based upon and claims the benefit of priority from Japanese Patent Application No. 2015-001910 filed on Jan. 7, 2015; the entire contents of all of which are incorporated herein by reference.Embodiments described herein generally relate to austenitic heat resistant steel and a turbine component.In recent years, increasing efficiency of power generation plants ...