СПОСОБ ЭКСПЛУАТАЦИИ СТАЦИОНАРНОЙ ГАЗОТУРБИННОЙ УСТАНОВКИ И ВСАСЫВАЮЩИЙ КАНАЛ ДЛЯ ВСАСЫВАЕМОГО ВОЗДУХА ГАЗОТУРБИННОЙ УСТАНОВКИ

Способ (39) эксплуатации стационарной газотурбинной установки (10), которая оснащена по меньшей мере одним фильтром (32, 34) для очистки всасываемого воздуха (А) и подсоединена к генератору (20). Генератор выполнен с возможностью запитывания электрической энергии в электрическую токораспределительную сеть (22). При необходимости поддержания частоты токораспределительной сети (22) и для повышения отдаваемой от газотурбинной установки (10) генератору (20) мощности осуществляют подачу в стационарную газотурбинную установку (10) от частично до полностью нефильтрованного окружающего воздуха (А). Достигается возможность избежать повышения температуры на входе, сокращающего срок службы конструктивных элементов, направляющих горячий газ, несмотря на увеличенную отдачу мощности. 2 з.п. ф-лы, 3 ил.

Фильтровальная камера для газовых турбин и способ технического обслуживания указанной камеры

Изобретение относится к системе фильтрации, предназначенной для фильтрации воздуха на впуске газовой турбины. Система фильтрации содержит первый фильтр (25) и расположенный ниже по потоку от него второй фильтр (29), обладающий более высокой степенью улавливания по сравнению с первым фильтром (25). Между первым фильтром (25) и вторым фильтром (29) расположен защитный фильтр (31), обладающий более низкой степенью улавливания по сравнению с первым фильтром (25). Технический результат: высокая эффективность фильтрации. 4 н. и 15 з.п. ф-лы, 3 ил.

Двухконтурный газотурбинный двигатель со средствами отведени избыточного количества воздуха с упрощенным управлением

Изобретение касается двухконтурного газотурбинного двигателя, в частности авиационного двухконтурного турбореактивного двигателя, содержащего между каналом первичного контура и каналом вторичного контура промежуточный структурный корпус, располагающийся в осевом направлении между компрессором низкого давления и компрессором высокого давления, и который содержит средства отведения избыточного количества воздуха, позволяющие обеспечить отведение части газового потока, нагнетаемого компрессором низкого давления, в канал вторичного контура. Средства отведения избыточного количества воздуха содержат кольцевую полость, образующую коллектор, располагающуюся по потоку перед промежуточным корпусом в наружной стенке канала первичного контура и сообщающуюся в непрерывном режиме с каналом этого первичного контура, множество по существу осевых каналов, выполненных в этом промежуточном корпусе и соединенных с коллектором, и множество трубок, располагающихся вокруг компрессора высокого давления для того ...

ВОЗДУХОЗАБОРНИК ГАЗОТУРБИННОГО ДВИГАТЕЛЯ В ГОНДОЛЕ

Система газотурбинного двигателя установлена в гондоле, содержащей обтекатель воздухозаборника, образующий воздухозаборник, содержит орган отклонения посторонних объектов, образующий вместе с обтекателем воздухозаборника впускной воздушный канал, и на выходе отклоняющего органа - вторичный отклоняющий канал и главный канал подачи воздуха в двигатель. Впускной воздушный канал выполнен с возможностью отклонения, по меньшей мере, части посторонних объектов, засасываемых через воздухозаборник, в направлении вторичного отклоняющего канала. Вторичный отклоняющий канал выполнен таким образом, чтобы скорость течения проходящего через него воздуха увеличивалась от входа к выходу. Вторичный канал содержит выход с отверстием, выходящим на наружную стенку гондолы. Изобретение направлено на повышение защиты двигателя от попадания посторонних объектов при сохранении аэродинамических характеристик гондолы. 11 з.п. ф-лы, 8 ил.

ВОЗДУХОЗАБОРНИК ДЛЯ ТУРБОДВИГАТЕЛЯ, САМОЛЕТ, СНАБЖЕННЫЙ ТАКИМ ВОЗДУХОЗАБОРНИКОМ, И СПОСОБ ОПТИМИЗАЦИИ РАБОТЫ АВИАЦИОННОГО ТУРБОДВИГАТЕЛЯ С ПОМОЩЬЮ ВОЗДУХОЗАБОРНИКА

Настоящее изобретение относится к области авиации, в частности к конструкциям воздухозаборников газотурбинных двигателей самолетов. Воздухозаборник (10) содержит подводящий воздухопровод (20), удлиненный динамическим входным каналом (30), расположенным вдоль динамической оси (АХ1). Динамический входной канал (30) имеет сетку (40) для защиты от попадания инородных тел. Сетка (40) поступательно перемещается по указанной динамической оси (АХ1) относительно указанного переднего сечения (31). Воздухозаборник (10) включает, по меньшей мере, одно боковое впускное отверстие (50), выполненное в боковой стенке (21), и средства крышки (41) для закрывания указанного бокового впускного отверстия (50), которые перемещаются относительно указанного бокового впускного отверстия (50), и средство перемещения (60), управляемое указанным поступательным движением сетки (40), чтобы вызвать движение указанных средств крышки (41) относительно указанного бокового впускного отверстия (50). Способ оптимизации работы ...

ФИЛЬТР-КАССЕТА, ФИЛЬТРОВАЛЬНОЕ УСТРОЙСТВО И ГАЗОВАЯ ТУРБИНА С ТАКОЙ ФИЛЬТР-КАССЕТОЙ

Группа изобретений относится к фильтровальному устройству для удаления частиц из потока воздуха, используемому в газовых турбинах, аварийных парогенераторах, газовых компрессорах, системах вентиляции и кондиционирования, а также при добыче газа. Фильтр-кассета для удаления частиц из потока воздуха содержит верхний по потоку конец и нижний по потоку конец, установочную раму, на которой воздухонепроницаемо закреплена фильтровальная среда и на которой предусмотрена установочная поверхность, приспособленная для установки фильтр-кассеты в отверстии перегородки, и расположенная между верхним и нижним по потоку концами фильтр-кассеты на первом расстоянии Dот указанного верхнего по потоку конца и на втором расстоянии Dот указанного нижнего по потоку конца. Величина каждого из указанных первого и второго расстояния, D, Dсоставляет более 10% общей длины L фильтр-кассеты. Фильтровальное устройство включает перегородку с отверстием и установочной плоскостью, окружающей указанное отверстие. Фильтр-кассета ...

ЛЕТАТЕЛЬНЫЙ АППАРАТ С ВОЗДУХОЗАБОРНИКОМ ДЛЯ ДВИГАТЕЛЯ, ИСПОЛЬЗУЮЩЕГО ВОЗДУХ КАК ОКИСЛИТЕЛЬ

Изобретение относится к летательным аппаратам. Летательный аппарат (1) содержит фюзеляж (2) с двигателем (8a). Максимальная ширина фюзеляжа (2) определена в области двигателя (8a). Передний обтекатель фюзеляжа и задний обтекатель фюзеляжа закрывают двигатель (8a) частично и разнесены друг от друга в направлении, поперечном продольной оси двигателя (8a), посредством предварительно определенного смещения обтекателя, для определения динамического воздухозаборника (9), через который поток всасываемого воздуха подается к упомянутому по меньшей мере одному двигателю (8a), использующему воздух как окислитель при работе. Изобретение повышает защиту двигателя летательного аппарата. 14 з.п. ф-лы, 16 ил.

ЧИСТАЯ КАМЕРА ВОЗДУХООЧИСТИТЕЛЬНОГО УСТРОЙСТВА

Изобретение относится к машиностроению. Чистая камера воздухоочистительного устройства содержит верхний модуль с защитным колпаком (6) шатрового типа и фильтрующими элементами (8), установленными в стойках с противоположных сторон, образующими чистую камеру (7). Чистая камера (7) разделена на две равные части перегородкой (10), идущей параллельно фильтрующим элементам. Перегородка (10) выполнена капитальной и прикреплена на кронштейнах с амортизирующими прокладками. Технический результат заключается в обеспечении равномерной подачи воздуха на вход в газотурбинный двигатель. 2 з.п. ф-лы, 6 ил.

Воздухозаборное устройство вертолетного газотурбинного двигателя, удаляющее из воздуха частицы песка и пыли

Предлагается воздухозаборное устройство вертолетного газотурбинного двигателя, удаляющее из воздуха частицы песка и пыли. Особенностью устройства по сравнению с существующим отечественным пылезащитным устройством (ПЗУ) «грибкового» типа является то, что рассматриваемое устройство производит очистку воздуха не только на режимах перемещения вертолета с малыми скоростями у земли (руления, висения, взлет-посадки), но и при полете на крейсерской скорости в условиях загрязненного пылью воздуха. Положительный эффект достигается за счет введения в конструкцию обтекателя устройства («грибкового» ПЗУ) экрана, служащего для сбора и отвода обогащенного пылью воздуха из центральной зоны обтекателя и последующей его очистки перед поступлением в двигатель. Кроме того, с помощью указанного экрана производится очистка воздуха, поступающего в воздухозаборное отверстие устройства из периферийной зоны потока, за счет отражения частиц от конической поверхности экрана в боковых направлениях. Также положительной ...

ВОЗДУХООЧИСТИТЕЛЬНОЕ УСТРОЙСТВО

Изобретение относится к области машиностроения и может быть использовано в энергетике, газовой, нефтяной и других отраслях промышленности в качестве воздухоочистительного устройства (ВОУ) накопительного типа для очистки воздуха, подаваемого в газотурбинные и компрессорные установки (ГТУ) в объеме от 84 тыс. м3/ч до 165 тыс. м3/ч. Устройство состоит из двух модулей верхнего 1 и нижнего 2. В верхнем модуле 1 между блоками воздушных фильтров 8 расположен проход 9. Блоки воздушных фильтров 8 расположены инверсно и включают в себя наборы фильтроэлементов 6, каждый из которых состоит из влагоотделителя и фильтров грубой и тонкой очистки. Количество наборов фильтроэлементов в каждом блоке воздушных фильтров определяется его габаритами. Защитный колпак снабжен воздухозаборными козырьками 5, которые выполнены со сплошными боковыми стенками и снабжены защитной сеткой 10 расположенной в нижней части воздухозаборных козырьков. В верхнем модуле 1 дополнительно установлена противооблединительная система ...

Циклон

Изобретение относится к области авиационной техники, в частности предназначено для защиты газотурбинных двигателей от попадания пыли и посторонних предметов. Также может применяться в автомобильной и индустриальной промышленности для очистки воздуха от пыли и посторонних предметов. Циклон включает в себя вихревую трубку с завихрителем и выпускную трубку с кольцом, образующие кольцевой канал пылеудаления. Вихревая трубка с элементами фиксации представляет собой корпус цилиндрической формы по всей длине, а на выпускной трубке с элементами фиксации выполнены центровочные упоры, обеспечивающие соосность вихревой и выпускной трубок. Уменьшаются габариты и масса циклона с сохранением гидравлического сопротивления и степени очистки, а также обеспечивается удобство монтажа циклонов и их замены в процессе эксплуатации. 2 ил.

ФИЛЬТРАЦИОННАЯ СИСТЕМА И СПОСОБ ОЧИСТКИ ВХОДЯЩЕГО ВОЗДУХА ГАЗОВОЙ ТУРБИНЫ

Фильтрованная камера для газовых турбин и способ технического обслуживания указанной камеры

ВСТРОЕННАЯ СИСТЕМА ПРОМЫВКИ ДЛЯ ГАЗОТУРБИННОГО ДВИГАТЕЛЯ

ФИЛЬТР-КАССЕТА, ФИЛЬТРОВАЛЬНОЕ УСТРОЙСТВО И ГАЗОВАЯ ТУРБИНА С ТАКОЙ ФИЛЬТР-КАССЕТОЙ

... 1. Фильтр-кассета (1) для удаления частиц из потока воздуха, содержащая верхний по потоку конец (14) и нижний по потоку конец (16), установочную раму (8), на которой герметично закреплена фильтровальная среда (4) и на которой предусмотрена установочная поверхность (5), приспособленная для установки фильтр-кассеты в отверстии перегородки (6), и расположенная между верхним и нижним по потоку концами (14, 16) фильтр-кассеты на первом расстоянии (D) от указанного верхнего по потоку конца (14) и на втором расстоянии (D) от указанного нижнего по потоку конца (16), причем величина каждого из указанных первого и второго расстояния, (D, D) составляет более 10% общей длины (L) фильтр-кассеты.2. Фильтр-кассета (1) по п.1, в которой указанные первое и второе расстояния (D, D) равны, по меньшей мере, 40 мм, более предпочтительно, 100 мм или более.3. Фильтр-кассета (1) по п.1 или 2, в которой величина каждого из указанных первого и второго расстояния (D, D) составляет более 25%.4. Фильтр-кассета (1) ...

КОМПЛЕКСНОЕ ВОЗДУХООЧИСТИТЕЛЬНОЕ УСТРОЙСТВО

Полезная модель относится к устройствам для очистки забираемого из атмосферы воздуха и подготовки его для подачи в компрессор газотурбинного двигателя газоперекачивающего агрегата. Техническим результатом полезной модели является создание конструкции нового комплексного воздухоочистительного устройства, обеспечивающего надежность работы газоперекачивающего агрегата в зимний период в прибрежной арктической зоне Крайнего Севера. Технический результат достигается в заявляемом комплексном воздухоочистительном устройстве, содержащем воздухоприемную камеру (1), в которой установлены блоки комбинированной системы фильтрации, включающие фильтры грубой очистки (2); осадкозащитные козырьки (3), систему подогрева (4) всасываемого атмосферного воздуха, глушители шума (5), согласно полезной модели, фильтры грубой очистки (2) выполнены в виде гидрофобных коалесцирующих фильтров карманного типа, установленных против входящего потока воздуха и соединенных в блоки с кассетными фильтрами тонкой очистки ( ...

Self-cleaning filter for a gaseous media compact system with dust-entry superelevation, process and implementation therefor

With a combined feed and exhaust air fan which is driven by a centripetal turbine, seated on the same shaft, and which is impinged by a front take-off stage of the axial compressor of the gas turbine, advantages result with respect to automatic control of speed of rotation, maximum air-flow rate, automatic run-up and start with the gas turbine. The dust-entry superelevation described in the main patent is put into effect in a compact air-intake filter system which provides the air-intake orifice at the highest point and the air conduction leading vertically downwards in the direction of fall of the dust particles. This process is optimum with respect to the dust-intake load, the dust separation and prevention of reentry of the dust. Because of the easily implementable sequential arrangement of the module - see Fig. 11 - a double arrangement is shown - the volume of the filter system is still further reduced, without the advantages according to the invention being impaired in the separation ...

WIRBELLUFTREINIGERANORDNUNG MIT EINER SCHALLDAEMPFUNGSEINRICHTUNG

Improvements in and relating to combustion turbine plants

... 719,775. Gas turbines; centrifugal compressors. PARSONS & CO., Ltd., C. A., and HRYNISZAK, W. Dec. 11, 1951 [Sept. 11, 1950], No. 22333/50. Classes 110(1) and 110(3) [Also in Groups XIII and XXVIII] A gas turbine plant which is of approximately cylindrical form and of a length greater than its diameter comprises an inlet air filter 1b, a centrifugal compressor 1d, a centripetal turbine 2a driving the compressor and delivering useful power, a combustion chamber arrangement 2b surrounding an exhaust diffuser 2c, and an air preheater. These elements are arranged axially in the order named. The plant is intended for driving road vehicles or pumps. A drive can be taken off the turbine shaft 3a at 3c or 3d. The inlet air filter has inlet louvres 1a and comprises felt .discs a held in position by frames b1, b2 and spacing caps c and bolted to the compressor casing e. After leaving the diffuser vanes of the compressor the air passes through a second diffuser 1e to the cold gas side 2i of the preheater ...

Gas turbine engine variable bleed pivotal flow splitter or flap valve.

A plurality of pivotal flow splitters 30 between compressor sections 22, 24 are provided to bleed off air flow and remove particles, particularly ice in the case of an aircraft fan-jet gas turbine engine, by pivoting the leading edge 31 of the splitter 30 into the compressor flow thereby using the total pressure of the flow to drive blood flows overboard and remove particles. In the preferred embodiment the pivotal flow splitter is integral with a booster variable bleed valve (VBV) door 30 and includes a booster bleed duct means 18 having a bellmouth shaped inducer type inlet 48 to enhance the capture of compressor flow and particle removal. ...

Inlet particle separator for gas turbine engine

The invention is an improved inlet particle separator for removing extraneous matter from a stream of air directed into the engine's core section. The improved separator utilizes two stages of separation. The first stage is an axial flow separator for initially separating engine inlet air into a first flow of relatively contaminated air and a second flow of relatively clean air. This first stage of separation is accomplished by sharply turning the air flow radially inwardly so that the relatively dense extraneous matter continues in its original direction into a scavenge system. A second stage of separation is accomplished in the scavenge system and comprises a centrifugal separator that separates the first flow of air into third and fourth flows of relatively contaminated air for the purpose of protecting a blower that powers the flow through the scavenge system and which is in flow communication with only the relatively less contaminated fourth flow of air.

An electrostatic particle ingress inhibitor

The present invention relates to a system and method for inhibiting the ingress of particles into the compressor 14 of a turbofan jet engine 10. The system comprises a deflection electrode 24 arranged to electrostatically deflect the particles through an air bypass 20 of the engine. A charge electrode 22 may be arranged to electrically charge the particles. The charge electrode may be arranged to generate an electrostatic field proximal to an air intake of the engine. The charge electrode may be formed of one or more members arranged to extend across an air intake of the engine and may be fenestrated and/or be a grill or grid. The deflection electrode may be configured to be arranged between the internal periphery of the air intake and the hub of the jet engine. A sensor may be provided which is operable to detect an amount of airborne particles and the electric charge of the airborne particles ...

PARTICLE SEPARATOR FOR THE INLET OF A GAS TURBINE ENGINE

COALESCER

Turbine engine having an element for deflecting foreign objects

Gas turbine engine air inlet particle separator

An inlet particle separator for a gas turbine engine is provided with unique vanes distributed around an entrance to a particle collection chamber. The vanes are uniquely constructed to direct extraneous particles that enter the engine into the collection chamber and prevent the particles from rebounding back into the engine's air flow stream. The vanes are provided with several features to accomplish this function, including upstream faces that are sharply angled towards air flow stream direction to cause particles to bounce towards the collection chamber. In addition, throat regions between the vanes cause a localized air flow acceleration and a focusing of the particles that aid in directing the particles in a proper direction.

Separator assembly

Air is drawn into a turbine through a particle separator 10 which normally seats in an opening 14, but if the separator clogs then it is moved by power means 18 in a direction opposed to the air flow 16, to open a by-pass. As shown the separator pivots at 17, but in Figures 3,4 (not shown) the separator is moved rectilinearly out of opening 14. In Figures 5,6 copy in opposite directions. Means 18 may be manual, electric, hydraulic or pneumatic and may be controlled by a differential pressure sensor. ...

Method for operating a static gas turbine, and intake duct for intake air of a gas turbine

The invention relates to an ambient air intake duct (30) of a static gas turbine (10), having at least one filter (32, 34), which is arranged in the intake duct (30), for cleaning the ambient air (A) that can flow through the intake duct (30). The invention also relates to a method for operating a static gas turbine (10) which is equipped with a filter (32, 34) for cleaning the ambient air (A). To rapidly provide a higher level of gas turbine power to a generator (20), it is provided that, by means of a bypass or by means of flaps (36) arranged downstream of the filter (32, 34), partially to completely unfiltered ambient air (A) can temporarily flow into the compressor inlet (26).

FILTER CASSETTE, FILTER ARRANGEMENT, AND GAS TURBINE WITH SUCH FILTER CASSETTE

A filter cassette (1) for removing particles from an air stream, in particular from a gas stream entering a gas turbine, has an upstream end (14) and a downstream end (16) and comprises a mounting frame to which a filter media (4) is fitted and which has a mounting face (5) adapted for mounting the filter cassette to an opening (15) of a partition (6). The mounting face is positioned between the filter cassette's upstream and downstream ends at a first distance (Dup) from said upstream end (14) and a second distance (Ddown) from said downstream end (16). The first and second distances each amount to more than 10% of an overall length of the filter cassette. Preferably, the mounting face (5) is positioned centrally between the upstream and downstream ends (14, 16), approximately in a barycenter line of the filter cassette (1). The filter cassette thus extends to both sides of the partition opening (15). Filter surface area is increased and torque induced by the filter cassette (1) into the ...

INLET AIR CLEANER AND MIST ELIMINATOR ASSEMBLY FOR GAS TURBINE ENGINES

... 2-227 CIP: An inlet air cleaner and mist eliminator assembly is provided for the air intake of gas turbine engines or other air breathing devices comprising, in combination, in flow sequence, a first array of vortex air cleaners removing coarse and heavy liquid droplets and solid contaminant particles, but not light and well dispersed liquid and solid contaminant particles; a second array of sheets of filamentary woven or nonwoven material, arranged to receive partially cleaned air from the vortex air cleaner array, and remove and coalesce light and well dispersed liquid contaminant droplets and particles suspended therein, and a third array of vortex air cleaners, arranged at the same or preferably a higher density and flow-through capacity per unit of inlet open surface area than the first array to receive residual cleaned air from the second array, and removing additional light and well-dispersed coalesced liquid droplets and solid contaminant particles.

TURBOPROP AIRCRAFT ENGINE

The invention relates to a turboprop aircraft engine with at least one outer air intake 1 and with at least one downstream inner duct system 2 for the delivery of air to a compressor, characterized in that the inner duct system 2 spirals around the center axis 3 of the engine.

PARTICLE SEPARATOR USING BOUNDARY LAYER CONTROL

AIR INLET FILTER FOR GAS TURBINE ENGINE

INERTIAL PARTICLE SEPARATOR FOR COMPRESSOR SHROUD BLEED

... ²²An inertial particle separator (IPS) for an inlet housing that couples an ²inlet ²air plenum to a compressor in a gas turbine engine, wherein the IPS removes ²particles within reverse air flow passing through at least one inlet housing ²aperture ²in the inlet housing into shroud bleed apertures in a shroud for the ²compressor, ²having: at least one baffle that protrudes from each inlet housing aperture ²positioned to bend a reverse air flow stream through the inlet housing ²aperture to a ²degree such that particles in the reverse air flow stream flow into the inlet ²air ²plenum.²² ...

METHOD OF RUNNING AN AIR INLET SYSTEM

The present embodiments disclose a method of running an air inlet system upstream of one or more inlet air filters of a device protected by air filtration, wherein the method comprises: regulating the relative air humidity of the inlet air at the one or more inlet air filters in dependence of the inlet air filters differential pressure.

MOBILE ELECTRIC POWER GENERATION FOR HYDRAULIC FRACTURING OF SUBSURFACE GEOLOGICAL FORMATIONS

Providing mobile electric power comprising a power generation transport configured to convert hydrocarbon fuel to electricity and an inlet and exhaust transport configured to: couple to at least one side of the power generation transport such that the inlet and exhaust transport is not connected to a top side of the power generation transport, provide ventilation air and combustion air to the power generation transport, collect exhaust air from the power generation transport, and filter the exhaust air. In another embodiment, a fracturing pump transport comprising a first pump configured to pressurize and pump fracturing fluid, a second pump configured to pressurize and pump the fracturing fluid, and a dual shaft electric motor comprises a shaft and configured to receive electric power from a power source and drive in parallel, both the first pump and the second pump with the shaft.

INLET PARTICLE SEPARATOR FOR A TURBINE ENGINE

A method and apparatus for separating particles from an inlet airflow of a turbine engine has a centerbody with a radially outer scavenge conduit. The inlet airflow has entrained particulate matter, which can impact an impact surface defining part of the centerbody. The impact surface can be disposed at an angle or have a low coefficient of restitution to reduce the velocity of the incoming particulate matter. The particulate matter is radially diverted radially outward through the scavenge conduit, unable to make a turn defined by the shape of the centerbody.

PARTICLE SEPARATOR

An air-inlet duct includes an outer wall, an inner wall, and a splitter. The splitter cooperates with the outer wall to establish a particle separator which separates particles entrained in an inlet flow moving through the air-inlet duct to provide a clean flow of air to a compressor section of a gas turbine engine.

ENGINE AIR PARTICLE SEPARATOR.

WITH A SELF CLEANING MECHANISM OF EQUIPMENTS FILTER APPARATUS FOR A GAS FLOW.

Silencer and compressor using the same.

Schalldämpfer (10) eines Verdichters zum Ansaugen von zu verdichtender Luft, mit einem eine Frontplatte und eine Rückplatte (18) aufweisenden Gehäuse (16), mit einer sich zwischen der Frontplatte und der Rückplatte (18) erstreckenden, einen Ansaugbereich begrenzenden Umfangsfläche (19), über welche die Luft ansaugbar ist, und mit einer Ausnehmung (21) in der Rückplatte (18), über welche die angesaugte Luft dem Verdichter zuführbar ist. Im oder benachbart zum Ansaugbereich ist als Flammenabsorber ein metallisches Bauteil, insbesondere ein Drahtbauteil (22), angeordnet.

FILTERING SYSTEM FOR AIR INTAKES AIRCRAFT ENGINES AND CORRESPONDING METHODS

ENGINE HAS GAS TURBINE COMPRISING A SEPARATOR OF PARTICLES

AIR PUMP HAS ASPIRATION DUCTS PRIMARY AND SECONDARY

Improvements in Helicopter Engine Air Inlets

DEVICE OF GAS PURIFIER

Un dispositif de filtre à gaz (1) comprenant - un support (11) comprenant une partie de support fixe (112) et au moins une partie de support mobile (17, 111), et - pour chaque partie de support mobile, un jeu d'au moins un élément de filtration (12), dans lequel pour chaque élément de filtration, le dispositif de filtre à gaz comprend des moyens de fixation (13) du dit élément à la partie de support mobile correspondante, et au moins une partie de support mobile est déplaçable par rapport à la partie de support fixe de façon à pouvoir amener au moins un moyen de fixation dans une zone d'intervention (20), pour la fixation/le retrait de l'élément de filtration correspondant depuis ladite zone d'intervention.

SEPARATEUR DE PARTICULES ETRANGERES POUR MOTEUR A TURBINE A GAZ

Séparateur compatible avec la faible masse, la fiabilité élevée et la longueur réduite que doit avoir un moteur. Il comprend un dispositif 38, 40, placé au voisinage de l'entrée 14, qui retire du chemin d'écoulement principal les particules étrangères qui s'y trouvent ; un système de conduites 42, relié au dispositif séparant les particules, qui reçoit les particules retirées du chemin d'écoulement principal par le dispositif séparant les particules ; un éjecteur 46 ayant pour effet de provoquer dans le système de conduite un écoulement d'un second flux de fluide gazeux pour aspirer les particules à travers le système de conduites et les éloigner du dispositif séparant les particules ; et un mélangeur 45, placé en aval de la turbine et communiquant avec le système de conduites, qui reçoit le second flux de fluide et le mélange au flux de fluide circulant dans le chemin d'écoulement principal. Application aux moteurs d'hélicoptères. (CF DESSIN DANS BOPI) ...

INTAKE AIR OF ENGINES HAS GAS TURBINE Of AVIATION

HOUSING HUB FOR AIRCRAFT TURBOMACHINE COMPRISING AN AEROBIC COMPACT WITH INTEGRATED DEFLECTOR DOWNSTREAM FLANGE AT

AIR INTAKE Of a TURBOMOTOR Of AIRCRAFT, AIRCRAFT PROVIDED With SUCH an AIR INTAKE AND a METHOD FOR OPTIMIZING the OPERATION Of a TURBOMOTOR Of ONE AIRCRAFT USING an AIR INTAKE

INTAKE AIR OF ENGINES HAS GAS TURBINE Of AVIATION

Vanne de décharge de compresseur de turboréacteur

L'invention concerne un compresseur de turboréacteur d'aviation à double flux, ledit compresseur comportant, de façon connue, des vannes de décharge 7 placées dans des logements de la paroi externe pour décharger une partie du débit d'air Conformément à l'invention lesdites vannes 7 comportent des moyens 14a qui restent plaqués contre la paroi de la veine tant que la vanne n'a pas atteint un angle d'ouverture déterminé alpha et qui sont aptes, pour un angle d'ouverture beta supérieur, à faire saillie dans la veine 2 pour y recueillir l'eau en excès entrant dans le compresseur.

TURBOMACHINE COMPRISING A DEFLECTION UNIT OF FOREIGN OBJECTS

Turbomachine (110), comportant une nacelle (126) comprenant en amont un carénage d'entrée d'air (126a) et un organe (140) de déviation d'objets étrangers délimitant avec ledit carénage une veine d'entrée d'air et d'alimentation en air de deux veines coaxiales, respectivement radialement interne et radialement externe, ladite veine externe étant définie par un carter à moyeu (152) et des écopes, ledit carter à moyeu (152) et lesdites écopes étant montés en aval de l'organe (140) de déviation d'objets, caractérisée en ce que chaque écope comprend deux parties indépendantes, une partie amont (144a) portée par le carter à moyeu (152) et une partie aval (144b) portée par la nacelle (126).

에폭시-경화제 접착층이 형성된 폴리에테르설폰 나노섬유 및 내열성 고분자 나노섬유를 포함하는 나노섬유 필터 및 이의 제조방법

... 본 발명은 나노섬유를 포함하는 필터 및 이의 제조방법에 관한 것으로, 기재상에 폴리에테르설폰 나노섬유 및 내열성 고분자 나노섬유층을 포함하고, 기재와 나노섬유층 및 나노섬유층 사이를 에폭시 수지 용액 및 경화제 용액을 전기방사하여 접착층을 형성시킨 것을 특징으로 하고, 연속적인 공정이 가능하여 공정의 효율성 및 대량생산이 가능한 이점이 있으며, 탈리(脫離)가 잘 발생되지 않는 장점이 있다.

에폭시-경화제 접착층이 형성된 폴리아크릴로니트릴 나노섬유 및 내열성 고분자 나노섬유를 포함하는 나노섬유 필터 및 이의 제조방법

... 본 발명은 나노섬유를 포함하는 필터 및 이의 제조방법에 관한 것으로, 기재상에 폴리아크릴로니트릴 나노섬유 및 내열성 고분자 나노섬유층을 포함하고, 기재와 나노섬유층 및 나노섬유층 사이를 에폭시 수지 용액 및 경화제 용액을 전기방사하여 접착층을 형성시킨 것을 특징으로 하고, 연속적인 공정이 가능하여 공정의 효율성 및 대량생산이 가능한 이점이 있으며, 탈리(脫離)가 잘 발생되지 않는 장점이 있다.

에폭시-경화제 접착층이 형성된 폴리에테르설폰 나노섬유 및 소수성 고분자 나노섬유를 포함하는 나노섬유 필터 및 이의 제조방법

... 본 발명은 나노섬유를 포함하는 필터 및 이의 제조방법에 관한 것으로, 기재상에 폴리에테르설폰 나노섬유 및 소수성 고분자 나노섬유층을 포함하고, 기재와 나노섬유층 및 나노섬유층 사이를 에폭시 수지 및 경화제가 포함된 혼합용액을 전기방사하여 접착층을 형성시킨 것을 특징으로 하고, 연속적인 공정이 가능하여 공정의 효율성 및 대량생산이 가능한 이점이 있으며, 탈리(脫離)가 잘 발생되지 않는 장점이 있다.

NANOFIBER FILTER INCLUDING BICOMPONENT SUBSTRATE AND EPOXY RESIN CURING AGENT

The present invention relates to a nanofiber filter comprising nanofibers and, more specifically, to a nanofiber filter comprising epoxy resin nanofibers and curing agent nanofibers. The nanofiber filter has simplified manufacturing processes, thereby reducing the total costs. COPYRIGHT KIPO 2017 (AA,CC) Amine curing agent (BB) Epoxy resin (DD) Bicomponent substrate ...

NANOFIBER FILTER INCLUDING POLYVINYL ALCOHOL NANOFIBER AND HYDROPHOBIC POLYMER NANOFIBER WITH EPOXY-CURING AGENT ADHESION LAYER AND MANUFACTURING METHOD THEREOF

The present invention relates to a filter including nanofibers and a manufacturing method thereof. The filter comprises polyvinyl alcohol nanofiber and hydrophobic polymer nanofiber layers on a substrate. An adhesive layer is formed by electrospinning an epoxy resin solution and a curing agent solution between the substrate and the nanofiber layer and between the nanofiber layers. According to the present invention, a consecutive process is possible so efficiency of processes is high; mass-production is possible; and elimination does not occur well. COPYRIGHT KIPO 2017 (AA) Hydrophobic polymer (B1,B2) Adhesive layer (CC) Polyvinyl alcohol (DD) Substrate ...

AIR FILTER SYSTEM FOR TURBINE ENGINES

GAS TURBINE ENGINE HAVING A FLOW CONTROL SURFACE WITH A COOLING CONDUIT

DIRT SEPARATOR FOR GAS TURBINE AIR SUPPLY

A gas turbine engine is provided with a radially outer cooling air flow. A dirt separator is placed in the path of the radially outer cooling air flow, and includes a radially outer leg that defines a space to capture dirt or other impurities. A radially inner leg of the dirt separator includes open air flow passages to allow air to flow through the inner leg and downstream to cool various components within the gas turbine engine.

Gas Turbine Filtration System With Inlet Filter Orientation Assembly

The present application provides a filtration system for a gas turbine engine. The filtration system may include a holding frame with a positioning element extending therefrom and a filtration unit for mounting within the holding frame. The filtration unit may include a positioning slot therein such that the positioning element extends through the positioning slot when the filtration unit is mounted within the holding frame. Fig. 3 ...

AIRCRAFT ENGINE INLET PIVOTABLE BARRIER FILTER

An inlet barrier filter system for an aircraft engine includes a filter panel (35) including filter media for filtering air prior to intake (15) into the engine. The filter panel has a forward edge (F). The system further includes an actuator for selectively pivoting the panel to form an opening around the panel for allowing air to bypass the filter. The opening is rearward of the forward edge of the filter panel.

GAS TURBINE ENGINE AIR INTAKE IN A NACELLE

An assembly including a gas turbine engine and a nacelle in which the engine is housed, the nacelle including an air intake fairing that forms an air inlet and includes: a member for deflecting foreign objects, which together with the fairing, forms an air intake duct; and, downstream from the deflecting member, a secondary deflecting channel, and a main channel for supplying air to the engine. The air intake duct is configured to deflect at least some of the foreign objects sucked in through the air inlet towards the secondary deflecting channel. The secondary deflecting channel is shaped such that the flow velocity of the air flowing therethrough increases from upstream to downstream, the secondary channel having an outlet with an opening leading into the outer wall of the nacelle.

Apparatus of Centrifugal Fan and a Dust-Collecting Module Using the Same

A centrifugal fan apparatus is disclosed in the present invention. The characteristics of the centrifugal fan apparatus lies in that the width of airflow channel defined between the rim of the impeller and the inner wall of the housing accommodating the impeller is uniform, and two airflow spaces defined between the axial cross section of the impeller and upper housing and lower housing respectively are not symmetry. Due to these two characteristics, the centrifugal fan apparatus is capable of making larger pressure difference to inducing higher flow rate and reducing noise while the centrifugal fan apparatus is operated. The present invention also provides a dust-collecting module that is formed by adopting the centrifugal fan apparatus with a designed dust-collecting casing, which is capable of being a sucker of a vacuum cleaner to collect dust of the surroundings for the purpose of environment cleaning.

Inlet particle separator with anti-icing means

Gas-turbine engine with bleed-air tapping device

A gas-turbine engine with at least one compressor and at least one bleed-air tapping device, which includes an annular duct in a radially outer wall of a flow duct, and with an annular closing element, which is arranged in the region of the annular duct and can be moved in a substantially axial direction from a closed position to an open position, with the closing element having an annular flow divider projection which in the open position projects in the flow duct.

FOREIGN SUBSTANCE REMOVAL APPARATUS FOR GAS TURBINE

A foreign substance removal apparatus for a gas turbine includes a combustor casing having a first cooling air passage formed in a tangential direction of a combustor in a gas turbine in order to move cooling air into the combustor, a first foreign substance collection unit disposed on a flow path in the first cooling air passage in order to primarily filter foreign substances contained in the cooling air, a second cooling air passage extending radially toward a turbine blade in a circumferential direction of a torque tube located in the combustor, and a second foreign substance collection unit disposed on a flow path in the second cooling air passage and communicating with the second cooling air passage to secondarily filter foreign substances contained in the cooling air introduced through the first cooling air passage.

ADAPTIVE-CURVATURE INERTIAL PARTICLE SEPARATORS

A particle separator adapted for use with a gas turbine engine includes an inner wall, an outer wall, and a splitter. The splitter cooperates with the inner wall and the outer wall to separate particles suspended in an inlet flow moving through the particle separator to provide a clean flow of air to the gas turbine engine.

HELICOPTER ENGINE AIR INLETS

Mobile fracturing pump transport for hydraulic fracturing of subsurface geological formations

Providing pressurized fracturing fluid with a fracturing pump transport comprising a first fracturing pump and a second fracturing pump that are coupled on opposite sides of a dual shaft electric motor. A first drive line assembly comprising a first engagement coupling that allows for selective engagement and/or disengagement of the first fracturing pump with the dual shaft electric motor. A second drive line assembly comprising a second engagement coupling that allows for selective engagement and/or disengagement of the second fracturing pump with the dual shaft electric motor. The fracturing pump transport also comprising an engagement panel that allows for selective engagement or disengagement at the first engagement coupling based on receiving a remote command.

METHOD AND SYSTEM FOR TESTING FILTER ELEMENT PERFORMANCE

A system for testing at least one air filter element is provided. The system includes a test rig, wherein the test rig includes an elongated duct, and at least one measurement device coupled to the duct. The at least one measurement device is configured to measure at least one characteristic representative of a condition within the duct. At least one air filter element is coupled within the test rig. At least one first salt spray test is performed on the at least one air filter element. The collected salt spray water and equivalent amount of dry salt remaining in the test rig are quantified. At least one second salt spray test is performed on the at least one air filter element, wherein the at least one air filter element is dust loaded prior to the at least one second salt spray test.

Air Particle Separator for a Gas Turbine Engine

An assembly for separating debris from a pressurization air flow adjacent to a bearing compartment seal (38) includes a baffle (64) and a capture annulus (48). The baffle (64) is disposed in the pressurization air flow upstream of the compartment seal. The capture annulus (48) is positioned adjacent the baffle (64) and has a cavity (50) to collect the debris.

ФИЛЬТРАЦИОННАЯ СИСТЕМА И СПОСОБ ОЧИСТКИ ВХОДЯЩЕГО ВОЗДУХА ГАЗОВОЙ ТУРБИНЫ

Изобретение предназначено для фильтрования. Фильтрационная система, в частности, для очистки входящего воздуха газовой турбины содержит проточный канал, окруженный стенками, с входным отверстием и выходным отверстием, разделительной стенкой, которая расположена между входным отверстием и выходным отверстием и ограничена стенкой проточного канала и по меньшей мере двумя фильтрами для очистки текучей среды, протекающей по проточному каналу. По меньшей мере один первый фильтр образует одну сборочную единицу и смонтирован на разделительной стенке, и по меньшей мере один второй фильтр также образует одну сборочную единицу и смонтирован на разделительной стенке. Второй фильтр расположен за первым фильтром. Первый и второй фильтры по меньшей мере частично перекрываются в одном направлении, главным образом в направлении, перпендикулярном разделительной стенке. Описаны также способ очистки входящего воздуха газовой турбины посредством фильтрационной системы и комплект фильтров. Технический результат ...

СПОСОБ И УСТРОЙСТВО ДЛЯ ПРЕДОТВРАЩЕНИЯ ПРОХОДА ПОСТОРОННИХ ПРЕДМЕТОВ ВО ВНУТРЕННИЙ ТРАКТ ВЕНТИЛЯТОРНОГО ГАЗОТУРБИННОГО ДВИГАТЕЛЯ

Способ и устройство для предотвращения прохода посторонних предметов во внутренний тракт вентиляторного газотурбинного двигателя с целью предохранения деталей газовоздушного тракта от повреждений, основанные на использовании инерционной сепарации тяжелых частиц во вращающихся межлопаточных каналах вентиляторной ступени и перемещении посторонних предметов из центральной привтулочной зоны вентилятора в периферийную зону, в наружный тракт двигателя. Для реализации способа и устройства в вентиляторной ступени устанавливают барьерные отражающие стойки, обеспечивающие эффективную сепарацию посторонних предметов в радиальном направлении в наружный тракт в пределах осевого пространства вентиляторной ступени, и предотвращающие проход посторонних предметов во внутренний тракт вентиляторного газотурбинного двигателя. Применение способа и устройства не вызывает существенного ухудшения характеристик двигателя и может быть использовано на разных типах двигателей. Обеспечивается защита внутреннего тракта ...

УСТРОЙСТВО ДЛЯ ПОДАЧИ ВОЗДУХА ДЛЯ ГОРЕНИЯ К ДВИГАТЕЛЮ ЛЕТАТЕЛЬНОГО АППАРАТА

Изобретение относится к устройству для подачи воздуха для горения к двигателю летательного аппарата. Устройство для подачи воздуха для горения к двигателю, содержащему воздушный входной канал (4), который проходит между внешней поверхностью (5) летательного аппарата и двигателем (3а, 3b), расположенным во внутренней области, причем воздушный входной канал (4) начинается от воздушных входных отверстий (2а, 2b), расположенных в области внешней поверхности (5), при этом с целью реализации концепции двухпутевого воздушного потока, по меньшей мере, один дополнительный воздушный входной канал (8а, 8b) ведет из другой точки на внешней поверхности (5) к двигателю (3а, 3b), причем дополнительный воздушный входной канал (8а, 8b) содержит соответствующий дополнительный фильтрующий элемент (9а, 9b) крышки входного отверстия, кроме того, подача воздуха к двигателю (3а, 3b) в случае блокировки в воздушном входном отверстии (2а, 2b) переключается на дополнительный воздушный входной канал (8а, 8b; 8') ...

Циклон

Изобретение относится к области авиационной техники, в частности предназначено для защиты газотурбинных двигателей от попадания пыли и посторонних предметов. Также может применяться в автомобильной и индустриальной промышленности для очистки воздуха от пыли и посторонних предметов. Циклон включает в себя вихревую трубку с завихрителем и выпускную трубку с кольцом, образующие кольцевой канал пылеудаления. Вихревая трубка с элементами фиксации представляет собой корпус цилиндрической формы по всей длине, а на выпускной трубке с элементами фиксации выполнены центровочные упоры, обеспечивающие соосность вихревой и выпускной трубок. Уменьшаются габариты и масса циклона с сохранением гидравлического сопротивления и степени очистки, а также обеспечивается удобство монтажа циклонов и их замены в процессе эксплуатации. 2 ил.

ВОЗДУХООЧИСТИТЕЛЬНОЕ УСТРОЙСТВО ГАЗОПЕРЕКАЧИВАЮЩЕГО АГРЕГАТА

Изобретение относится к области газотурбинных технологий и может быть использовано для газоперекачивающих агрегатов (ГПА) компрессорных станций на магистральных газопроводах. В воздухоочистительном устройстве газоперекачивающего агрегата прямоугольной формы в плане с продольными и боковыми сторонами, содержащем сгруппированные в модули и закрепленные в верхнем модуле блоки воздушных фильтров, и средство защиты воздушных фильтров от прямого попадания атмосферных осадков в виде защитного колпака шатрового типа, при этом все модули выполнены в виде прямоугольных призм, содержащих боковые стенки с внутренней и внешней обшивками, собранные на прямоугольных каркасах, имеющих угловые и вертикальные стойки, скосы части фланцев, образующие в сборе фланцы, предназначенные для фланцевых соединений, зазор между обшивками заполнен теплоизоляцией, тем, что воздухоочистительное устройство состоит из модулей, в верхнем из которых расположены четыре Г-образных в плане рамы фильтров, каждая пара рам фильтров ...

ВОЗДУХООЧИСТИТЕЛЬНОЕ УСТРОЙСТВО ДЛЯ СУДОВЫХ ЭНЕРГЕТИЧЕСКИХ УСТАНОВОК

Изобретение относится к области судостроения, в частности к системам очистки воздуха, подаваемого в судовой двигатель для горения топлива, преимущественно газотурбинным, для которых требования по содержанию воды и соли, например морской, являются наиболее жесткими. Воздухоочистительное устройство включает расположенные в корпусе по ходу воздуха три ступени очистки для удаления из воздуха находящихся в нем влаги и солей, из которых первая и третья ступени представляют собой сепараторы, состоящие из набора профилированных жалюзи, а вторая ступень выполнена в виде установленного между ними, с возможностью выема, фильтра-коагулятора, и размещенные в нижней части корпуса сепараторов выводы отсепарированной из воздуха влаги. Устройство оснащено установленной за первой ступенью очистки перед фильтром - коагулятором системой увлажнения воздуха, состоящей из ряда вертикальных трубок с перфорированными стенками, объединенных верхним входным и нижним выходным коллекторами, причем перфорация стенок ...

ФИЛЬТРАЦИЯ ПОТОКА, СОСТОЯЩЕГО ИЗ ГАЗА И ЧАСТИЦ

УСТРОЙСТВО ФИЛЬТРАЦИИ ВОЗДУХА НА ВХОДЕ ДВИГАТЕЛЯ ВНУТРЕННЕГО СГОРАНИЯ СО СРЕДСТВОМ ВЕНТИЛЯЦИИ

... 1. Устройство фильтрации воздуха на входе в двигатель внутреннего сгорания, содержащее по меньшей мере один фильтрующий элемент (8) с входом для подлежащего обработке воздуха, первый выход очищенного воздуха в направлении двигателя и второй выход воздуха в окружающую среду, средство вентиляции (10), обеспечивающее вытяжку воздуха, начиная со второго выхода воздуха, отличающееся тем, что средство вентиляции содержит колесо вентилятора (23), приводимое во вращение турбиной (24), приводимой в движение газовым потоком, отбираемым с двигателя, турбину (24) и колесо вентилятора (23), располагающиеся концентрично относительно друг друга.2. Устройство по п.1, лопасти которого, образующие турбину (24), располагаются радиально снаружи кольца (25), соединяющего наружные концы лопастей (23) вентилятора.3. Устройство по п.2, турбина (24) которого относится к типу активных.4. Устройство по п.1, в котором колесо вентилятора (23) и турбина (24) образуют ротор (20), установленный в картере (30), в котором ...

FLUESSIGKEITSABSCHEIDER

Verzögerungs- und Filterreinigungsverfahren und -system

Filterreinigungssystem für einen Gasturbinenmotor, welches Folgendes aufweist: einen Gasturbinenmotor (12), der einen Kompressorabschnitt (14) und einen Brennerabschnitt (16) aufweist; einen Mechanismus (32), der betriebsmäßig mit dem Gasturbinenmotor gekoppelt ist und konfiguriert ist, um von dem Gasturbinenmotor in einem ersten Betriebszustand angetrieben zu werden, und der konfiguriert ist, um den Gasturbinenmotor in einem zweiten Betriebszustand anzutreiben; ein erster Flusspfad (58) zum Liefern von Luft an den Kompressorabschnitt zumindest einen Luftfilter (22; 24), der konfiguriert ist, um Luft zu filtern, die in den ersten Flusspfad eintritt; einen zweiten Flusspfad (60) zum Liefern von komprimierter Luft vom Kompressorabschnitt zum Brennerabschnitt während des ersten Betriebszustandes; und einen dritten Flusspfad (62) zum Liefern von komprimierter Luft vom Kompressorabschnitt zu dem mindestens einen Luftfilter während des zweiten Betriebszustandes.

Systems and methods for assembling an evaporative cooler

A method of assembling an evaporative cooler for use with a gas turbine engine system. The method includes coupling a drain pan to a support frame, wherein the drain pan includes a front wall and a back wall. A media support assembly is coupled to the drain pan to form the evaporative cooler. The media support assembly includes a media support wall and a rear flange. The media support wall extends substantially perpendicularly from the drain pan front wall and defines a continuous drainage chamber between the drain pan front wall and the back wall.

Gas turbine engine intake duct

A gas turbine engine intake duct 70 comprising a main duct 72 and a scavenge duct 78 having a scavenge inlet 80 from the main duct. The intake duct comprises a protrusion 100 extending at least partially across the intake duct in the scavenge inlet, or/and upstream of the scavenge inlet. The protrusion reduces the intake duct area in use thereby to increase the flow rate of a flow passing around the protrusion into the scavenge duct from the main duct. The protrusion may be blade like. The protrusion may be substantially radially aligned. A chord of the protrusion may be substantially axially aligned. The protrusion may taper away from a root 102 as it extends across the intake duct. The root may be integral with, or joined to a radially outer internal surface of the intake duct. The protrusion may be a vane spanning the full extent of the scavenge inlet. The protrusion may be a cusp, extending only part way across the intake duct.

Turbine engine having an element for deflecting foreign objects

A turbine engine 110 having a nacelle 126 comprising, upstream, an air intake fairing 126a and an element 140 for deflecting foreign objects which defines with said fairing an air intake flow path for supplying air to two coaxial flow paths, namely a radially inner and a radially outer flow path. The outer flow path is defined by a hub housing 152 and scoops (144, fig.4), the hub housing and the scoops are installed downstream of the element for deflecting objects. The engine is characterised in that each scoop comprises two independent portions, namely an upstream portion 144a borne by the hub housing and a downstream portion 144b borne by the 126. The downstream portion of each scoop may be attached to a cowl 126a which is detachable from the nacelle. A sealing means (161a, fig. 5) may be installed between the upstream and downstream portions of each scoop.

Gas turbine inlet particle separator.

A gas turbine engine (1) in a helicopter has an air intake separator (4) from which separated particles are removed by an ejector (5), driven by high pressure gas supplied by an auxiliary power unit (6). The invention provides a reduction in fuel and main engine power consumption compared with known systems which drive the ejector (5) with gas bled from the main engine (1). Valve (9) enables ejector (5) to be switched off during high flying, when the separator is not needed. ...

IMPROVEMENTS IN OR RELATING TO PARTICLE SEPARATORS

INLET PARTICLE SEPARATOR FOR GAS TURBINE ENGINE

Apparatus for removing impurities from gses

Apparatus for removing impurities from a gas comprises in flow series an electrostatic separator (14) which receives contaminated gas from a coal burning fluidised bed combustor (10). The partially cleansed gas flows from the separator (14) to a pair of cyclone separators (20, 21) connected together in series. The clean air produced is to drive a gas turbine (23). ...

GAS TURBINE ENGINE INLET PARTICLE SEPERATOR

AIR INTAKE EQUIPMENT

INLET AIR CLEANER ASSEMBLY FOR TURBINE ENGINES

SUCTION FILTER, TURBO COMPRESSOR AND PROCEDURE FOR THE PACKING OF THE COMPRESSOR

AIR INTAKE OF A FLIGHT TL ENGINE, AIRPLANES WITH SUCH AIR INTAKE AND PROCEDURES FOR THE OPTIMIZATION OF THE ENTERPRISE THE FLIGHT TLTRIEBWERKS WITH SUCH AN AIR INTAKE

EASY ACCESS FILTER ASSEMBLY FOR HELICOPTER AIR INTAKE

Arrangement and method for purification of flowing gas

ENGINE AIR PARTICLESEPARATOR

Устройство фильтрации воздуха

Настоящая полезная модель относится к системам фильтрации воздуха, в частности к устройству фильтрации воздуха, содержащему фильтры первой, второй и третьей ступеней очистки, причем фильтры размещены соответственно в первом, втором и третьем корпусах, последовательно скрепленных друг с другом с возможностью отсоединения. Первый корпус скреплен со вторым корпусом посредством верхнего фиксатора и боковых защелок. В результате обеспечивается возможность легкой, быстрой и удобной замены фильтра первой ступени очистки. 2 ил. РОССИЙСКАЯ ФЕДЕРАЦИЯ (19) RU (11) (13) 171 602 U1 (51) МПК B01D 46/00 (2006.01) F02C 7/052 (2006.01) ФЕДЕРАЛЬНАЯ СЛУЖБА ПО ИНТЕЛЛЕКТУАЛЬНОЙ СОБСТВЕННОСТИ (12) ФОРМУЛА ПОЛЕЗНОЙ МОДЕЛИ К ПАТЕНТУ РОССИЙСКОЙ ФЕДЕРАЦИИ (21)(22) Заявка: 2017100678, 12.01.2017 (24) Дата начала отсчета срока действия патента: 12.01.2017 (72) Автор(ы): Львов Владимир Евгеньевич (RU), Китаин Михаил Борисович (RU) 07.06.2017 (56) Список документов, цитированных в отчете о поиске: RU 79802 U1, 20.01.2009. RU 145900 Приоритет(ы): (22) Дата подачи заявки: 12.01.2017 Адрес для переписки: 191002, Санкт-Петербург, а/я 5, Общество с ограниченной ответственностью "Ляпунов и партнеры" 1 7 1 6 0 2 R U (57) Формула полезной модели 1. Устройство фильтрации воздуха, содержащее фильтры первой, второй и третьей ступеней очистки, отличающееся тем, что фильтры размещены соответственно в первом, втором и третьем корпусах, последовательно скрепленных друг с другом с возможностью отсоединения, причем первый корпус скреплен со вторым корпусом посредством верхнего фиксатора и боковых защелок. 2. Устройство фильтрации воздуха по п. 1, отличающееся тем, что второй корпус содержит фланец для стыковки с третьим корпусом. 3. Устройство фильтрации воздуха по п. 1, отличающееся тем, что фиксатор и каждая защелка содержат по два элемента, выполненных с возможностью зацепления друг с другом, один из которых размещен на первом корпусе, а другой - на втором корпусе. 4. Устройство фильтрации воздуха по п. 3, ...

Clustered inlet particle separator

A particle separator for a gas turbine engine is disclosed. The particle separator includes flow dividers operable to divide flow in a gas turbine engine particle separator and flow scavengers operable to scavenge flow in a gas turbine engine particle separator.

Gas turbine engine heat exchanger

A gas turbine engine having a heat exchanger is disclosed. In one form the gas turbine engine includes a particle separator that can be used to separate particles or foreign objects and create a dirty flow and a clean flow. A blower can be used to discharge the particles or foreign objects from the separator. The heat exchanger includes a relatively warm flow path from a downstream region of a compressor and a relatively cool flow path from an upstream region of the compressor. The relatively cool flow path is merged with the dirty flow. In another embodiment, the gas turbine engine is a turbofan and the relatively cool flow path is merged with a bypass flow. In one embodiment of the engine the relatively warm flow path, after having exchanged heat with the relatively cool flow path is delivered to a working component without passing through a turbomachinery component.

Turbine Inlet Air Filter System

The present application provides a turbine inlet air filter system for an incoming flow of air. The turbine inlet air filter system may include a gas turbine engine, a chimney, a weather hood positioned on the chimney, and a filter house. The incoming flow of air flows through the weather hood, the chimney, the filter house, and into the gas turbine engine.

Gas Turbine Engine Particle Separator

Embodiments of the present invention provide an inlet particle separator for a gas turbine engine having an inlet flow path, a scavenge flow path, a core flow path, and a flow splitter disposed between the scavenge and core flow paths. A plurality of grooves may be disposed about an inner surface of a wall of the separator within the inlet flow path.

Combustion turbine inlet anti-icing resistive heating system

A resistive heating system for a combustion turbine susceptible to inlet air filter house component and compressor icing includes a plurality of heating panels (bundles) arranged in a substantially-planar array, adapted to be located on or adjacent to the turbine's inlet air filter house. Each heating panel is provided with one or more electrically-resistive heating elements; and a controller for selectively activating the resistive heating elements on each of the plurality of heating panels.

Filter media and filter device comprised thereof

This disclosure describes examples of a filter media for use in filter devices, e.g., pulse filter cartridges found in power generating systems. Embodiments of the filter media include a base media and a membrane, which partially covers one or both sides of the base media. In one embodiment, the membrane covers a membrane area of at least one side of the base media, wherein the membrane area is less than a total area of the side on which the membrane is disposed.

Air supply and conditioning system for a gas turbine

An air supply and conditioning system for an inlet system of a gas turbine includes an air processing unit having an inlet configured to receive compressed air from a compressor of the gas turbine. The air processing unit includes a heat exchanger that is downstream from the inlet. A vortex cooler is disposed downstream from the inlet of the air processing unit. The vortex cooler is in fluid communication with the heat exchanger and with an outlet of the air processing unit. The system further includes a self-cleaning filter that is disposed within a duct of the inlet system. The self-cleaning filter is in fluid communication with at least one of the outlet of the air processing unit or an outlet of the vortex cooler.

PARTICULATE INGESTION SENSOR FOR GAS TURBINE ENGINES

A multi-angle multi-wave array may comprise a first set of sensing elements, a second set of sensing elements, and a third set of sensing elements wherein the first set of sensing elements, the second set of sensing elements, and the third set of sensing elements are collectively configured to detect and discriminate between categories of foreign object debris including solid objects and particulates including silicate sand, water vapor, dust, volcanic ash, and smoke. 1. A multi-angle , multi-wave array , comprisinga first set of sensing elements, a second set of sensing elements, and a third set of sensing elements,wherein the first set of sensing elements, the second set of sensing elements, and the third set of sensing elements are collectively configured to detect and discriminate between categories of foreign object debris including solid objects and particulates including silicate sand, water vapor, dust, volcanic ash, and smoke,wherein the first set of sensing elements comprises a first light sensor, a second light sensor, and a third light sensor each aligned along a common axis,wherein the second set of sensing elements and the third set of sensing elements are arranged in at least one of circumferentially about a center defined by the second light sensor or in a ladder pattern.2. The multi-angle claim 1 , multi-wave array of claim 1 , wherein the first set of sensing elements comprises a first infrared light source and a first blue light source claim 1 ,wherein the first infrared light source and the first blue light source are each divided by the common axis and located circumferentially about the center defined by the second light sensor,{'b': 1', '2, 'wherein the first infrared light source and the first blue light source define, respectively, an angle θ and an angle θ between the common axis.'}3. The multi-angle claim 2 , multi-wave array of claim 2 , further comprising a second infrared light source and a second blue light source claim 2 , wherein the ...

Systems and methods for particle separator in a gas turbine engine

A particle separator system for use with a turbomachine is provided. The particle separator system includes a first end, a second end opposite the first end, a main separator body extending between the first and second ends, the main separator body including at least one step configured to cause a fluid flow to turn up to 180 degrees, and at least one transversely oriented cyclone separator disposed within the main separator body and defining at least one of a swirling cylinder, a bent cylinder, and a conical volume.

Motive Air Conditioning System for Gas Turbines

A motive air conditioning system for a gas turbine assembly is provided. The motive air conditioning system may include an inlet flow channel configured to be fluidly coupled with the gas turbine assembly. The motive air conditioning system may also include a filtration assembly fluidly coupled with the inlet flow channel and configured to filter motive air. The filtration assembly may include a plurality of filter modules disposed adjacent one another and further disposed circumferentially about a longitudinal axis of the inlet flow channel. 1. A motive air conditioning system for a gas turbine assembly , comprising:an inlet flow channel configured to be fluidly coupled with the gas turbine assembly; anda filtration assembly fluidly coupled with the inlet flow channel and configured to filter motive air, the filtration assembly comprising a plurality of filter modules disposed adjacent one another and further disposed circumferentially about a longitudinal axis of the inlet flow channel.2. The motive air conditioning system of claim 1 , wherein each filter module of the plurality of filter modules comprises an upper endwall claim 1 , a lower endwall claim 1 , and a plurality of sidewall panels coupled with one another and defining an inlet of the filter module.3. The motive air conditioning system of claim 2 , wherein at least a portion of the upper endwall is arcuate.4. The motive air conditioning system of claim 2 , wherein at least a portion of the lower endwall is arcuate.5. The motive air conditioning system of claim 1 , wherein the inlet flow channel comprises:an annular duct fluidly coupled with the filtration assembly and configured to receive the motive air from the filtration assembly; andan elbow fluidly coupled with the annular duct, the elbow configured to receive the motive air from the annular duct and at least partially turn the motive air toward the gas turbine assembly, and further configured to attenuate the generation of sound to control ...

MULTI-STATION DEBRIS SEPARATION SYSTEM

The present disclosure generally relates to separating solid particles from an airflow in a gas turbine engine. A system for separating debris includes a first separation device in fluid communication with an inlet flow path of a compressor and a second separation device in fluid communication with an outlet flow path of the compressor and an inlet flow path of a combustor. The first separation device is adapted to remove coarse particles from the airflow. The second separation device is adapted to remove fine particles from the airflow. The course particles have a larger mean particle diameter than the fine particles. 1. A system for separating debris from an airflow in a gas turbine engine , comprising:a first separation device in fluid communication with an inlet flow path of a compressor, the first separation device adapted to remove coarse particles from the airflow; anda second separation device in fluid communication with an outlet flow path of the compressor and an inlet flow path of a combustor, the second separation device adapted to remove fine particles from the airflow, wherein the course particles have a larger mean particle diameter than the fine particles.2. The system of claim 1 , wherein the first separation device is a radial inlet particle separator.3. The system of claim 1 , wherein the first separation device includes a plurality of circumferential vanes extending in a radially proximal direction along an inlet to a core of the gas turbine engine.4. The system of claim 3 , wherein the vanes are angled toward a forward air inlet of the gas turbine engine.5. The system of claim 2 , wherein the first separation device is vented to a bypass airflow.6. The system of claim 1 , wherein the second separation device is a multiple stage separation system.7. The system of claim 6 , wherein the multiple stage separation system includes a cyclonic separator and a clean air offtake downstream from the cyclonic separator.8. The system of claim 6 , wherein the ...

VEHICLE PROVIDED, AT THE INTAKE, WITH AN AIR FILTER AND CORRESPONDING AIR FILTER

A vehicle provided with an engine, at least one air intake through which the engine takes in the external air needed to operate, and an air filter, which is arranged downstream of the air intake. The air filter presents: one wave-shaped filtering material panel comprising a single and unique fabric layer which is made up of a plurality of weft wires and a plurality of warp wires interlaced with one another to form a plurality of meshes; an outer reinforcement net, which rests against an outer surface of the filtering material panel, through which the air taken in enters so as to flow through said filtering material panel; and an inner reinforcement net, which is rests against an inner surface of the filtering material panel opposite the outer surface. The warp wires and the weft wires which make up the fabric of the filtering material panel are made of polymeric material, and the fabric meshes of the filtering material panel have a micrometric size comprised between 15 and 75 microns. 11242949) A vehicle () provided with an engine () , at least one air intake () through which the engine () takes in the external air needed to operate , and an air filter () , which is arranged downstream of the air intake (); the air filter () comprises:{'b': 11', '15', '14, 'one wave-shaped filtering material panel () comprising a fabric layer which is made up of a plurality of weft wires () and a plurality of warp wires () interlaced with one another to form a plurality of meshes;'}{'b': 12', '11', '11, 'an outer reinforcement net (), which rests against an outer surface of the filtering material panel (), through which the air taken in enters so as to flow through said filtering material panel (); and'}{'b': 13', '11, 'an inner reinforcement net (), which is rests against an inner surface of the filtering material panel () opposite the outer surface;'}{'b': '11', 'wherein the filtering material panel () comprises only a single layer of fabric;'}{'b': 14', '15', '11, 'wherein the ...

FINE DEBRIS MULTI-STAGE SEPARATION SYSTEM

The present disclosure generally relates to separating entrained solid particles from an input airflow in a gas turbine engine. A cyclonic separator receives the input airflow from a compressor and separates a first portion of the input airflow. The cyclonic separator remove solid particles from the first portion of the input airflow to provide a first cleaned airflow to a first cooling system. A clean air offtake downstream from the cyclonic separator separates a second cleaned airflow from a remaining portion of the input air stream and provides the second cleaned airflow to a second cooling system. The remaining portion of the input airflow is provided to a combustor. 1. A system for separating entrained solid particles from an input airflow in a gas turbine engine , comprising:a cyclonic separator that receives the input airflow from a compressor and separates a first portion of the input airflow, the cyclonic separator further removes solid particles from the first portion of the input airflow to provide a first cleaned airflow to a first cooling system; anda clean air offtake downstream from the cyclonic separator that separates a second cleaned airflow from a remaining portion of the input air stream and provides the second cleaned airflow to a second cooling system,wherein the remaining portion of the input airflow is provided to a combustor.2. The system of claim 1 , wherein the compressor includes a centripetal impeller.3. The system of claim 2 , wherein the cyclonic separator includes at least one opening arranged circumferentially about a compressor impeller shroud surrounding the centripetal impeller.4. The system of claim 3 , where each of the at least one opening is connected to a respective vortex chamber of the cyclonic separator.5. The system of claim 4 , wherein each vortex chamber includes a vortex finder that separates an outer vortex fed by the respective opening from an inner vortex of relatively clean air.6. The system of claim 5 , wherein ...

FAN INTEGRATED INERTIAL PARTICLE SEPARATOR

A gas turbine engine includes a fan, an engine core, and an airflow duct assembly. The fan is mounted for rotation about a central axis of the gas turbine engine assembly to produce thrust for the gas turbine engine. The engine core is coupled to the fan and configured to drive the fan about the central axis. The airflow duct assembly defines a core passageway configured to conduct a first portion of air pushed by the fan into the engine core and a by-pass passageway configured to conduct a second portion air pushed by the fan around the engine core. 1. A gas turbine engine comprisinga fan mounted for rotation about a central axis of the gas turbine engine,an engine core coupled to the fan and configured to drive the fan about the central axis to cause the fan to push a mixture of air and particles suspended in the air to provide thrust for the gas turbine engine, andan airflow duct assembly configured to conduct the mixture of air and particles through the gas turbine engine, the airflow duct assembly defining a core passageway configured to conduct a first portion of the mixture of air and particles pushed by the fan into the engine core and a by-pass passageway configured to conduct a second portion of the mixture of air and particles pushed by the fan around the engine core, andwherein the airflow duct assembly includes a particle-separator splitter positioned in the core passageway and configured to separate the first portion of the mixture of air and particles into a clean flow substantially free of particles and a dirty flow containing the particles and the particle-separator splitter is arranged to direct the clean flow into the engine core and the dirty flow away from the engine core.2. The gas turbine engine of claim 1 , wherein the airflow duct assembly further includes an inner wall arranged circumferentially around the central axis claim 1 , an outer wall arranged circumferentially around the inner wall and the fan claim 1 , and a by-pass flow splitter ...

PARTICLE SEPARATOR

An air-inlet duct includes an outer wall, an inner wall, and a splitter. The splitter cooperates with the outer wall to establish a particle separator which separates particles entrained in an inlet flow moving through the air-inlet duct to provide a clean flow of air to a compressor section of a gas turbine engine. 1. An air-inlet duct for a gas-turbine engine , the air-inlet duct comprisingan outer wall spaced apart from an engine rotation axis,an inner wall located between the outer wall and the engine rotation axis, the inner wall and the outer wall defining an air-inlet passageway therebetween,a splitter located between the outer wall and the inner wall and including an outer splitter surface cooperating with the outer wall to define a scavenge channel therebetween and an inner splitter surface cooperating with the inner wall to define an engine channel therebetween, anda flow regulator configured to regulate a portion of an inlet flow including particles to cause a size and duration of a separated flow region formed along the outer wall and upstream of a scavenge inlet to the scavenge channel to be minimized so that the particles are collected in the scavenge channel and an amount of particles entering the engine channel are minimized.2. The air-inlet duct of claim 1 , wherein the flow regulator includes a series of flow control devices arranged to extend between and interconnect the outer wall and the outer splitter surface and each flow control device is arranged to extend upstream from the separated flow region and through the separated flow region claim 1 , and to lie in spaced-apart circumferential relation to one another.3. The air-inlet duct of claim 2 , wherein each flow control device is further arranged to extend through the scavenge inlet and into the scavenge channel.4. The air-inlet duct of claim 2 , wherein the series of flow control devices are each spaced an equal distance between neighboring flow control devices.5. (canceled)6. The air-inlet ...

FILTRATION SYSTEM FOR A GAS TURBINE AIR INTAKE AND METHODS

A gas turbine air filter system includes a housing having an interior, an inlet arrangement, and an outlet hood having an outlet arrangement. The inlet arrangement defines an inlet flow face for taking in unfiltered air. The outlet arrangement defines an outlet flow face for exiting filtered air. The inlet flow face and the outlet flow face are angled relative to each other. The angle can range between 45-135° relative to each other. The system includes at least first and second stages of filter element arrangements held within the interior of the housing. The first and second stages of filter element arrangements are operably sealed within the housing such that air flowing through the inlet arrangement must pass through the first and second stages of filter element arrangements before exiting through the outlet arrangement. The outlet hood is free of the first and second stages of filter element arrangements. 144-. (canceled)45. An air intake filter system for a gas turbine inlet; the air intake filter system comprising: '(i) the inlet flow face and the outlet flow face being angled 45-135° relative to each other;', '(a) a housing having an interior, an inlet arrangement defining an inlet flow face for taking in unfiltered air, and an outlet hood having an outlet arrangement defining an outlet flow face for exiting filtered air;'}(b) at least first and second stages of filter element arrangements held within the interior of the housing; the first and second stages of filter element arrangements being operably sealed within the housing such that air flowing through the inlet arrangement must pass through the first and second stages of filter element arrangements before exiting through the outlet arrangement;(c) the outlet hood being free of the first and second stages of filter element arrangements;(d) a pulse jet system oriented within the housing interior and disposed to periodically send a blast of fluid to the first stage filter element arrangement;(e) a ...

COMPACT GAS TURBINE AIR INLET SYSTEM

A system includes a modularized air inlet system. The modularized air inlet system includes an air filter house section configured to receive air via an air inlet. The modularized air inlet system also includes a transition/silencer section configured to direct the air from the modularized air inlet system, via an air outlet, into an air inlet plenum coupled to a gas turbine engine enclosure. The modularized air inlet system is configured to couple directly to the air inlet plenum and the gas turbine enclosure without an expansion joint disposed between the modularized air inlet system and the air inlet plenum. 1. A system , comprising: an air filter house section configured to receive air via an air inlet; and', 'a transition/silencer section configured to direct the air from the modularized air inlet system, via an air outlet, into an air inlet plenum coupled to a gas turbine engine enclosure;, 'a modularized air inlet system, comprisingwherein the modularized air inlet system is configured to couple directly to the air inlet plenum and the gas turbine enclosure without an expansion joint disposed between the modularized air inlet system and the air inlet plenum.2. The system of claim 1 , wherein a height from a top surface of the modularized air inlet system disposed opposite of the air inlet plenum to a top surface of the air inlet plenum that contacts the modularized air inlet system is between about 2.0 meters and 4.0 meters.3. The system of claim 1 , wherein transition/silencer section comprises a wall disposed upstream of the air outlet relative to a longitudinal axis of the gas turbine enclosure claim 1 , wherein the wall extends in a vertical direction from a top surface to a bottom surface of the transition/silencer section claim 1 , and the wall extends in a horizontal direction beyond a perimeter of the air outlet.4. The system of claim 3 , wherein the transition/silencer section comprises a first plurality of turning vanes configured to turn the air ...

Inlet particle separator system with hub and/or shroud suction

An inlet particle separator system for a vehicle engine includes a hub section, a shroud section, a splitter, and a hub suction flow passage. The shroud section surrounds at least a portion of the hub section and is spaced apart therefrom to define a main flow passageway that has an air inlet. The splitter is disposed downstream of the air inlet and extends into the passageway to divide the main flow passageway into a scavenge flow path and an engine flow path. The hub suction flow passage has a hub suction inlet port and a hub suction outlet port. The hub suction inlet port extends through the hub section and is in fluid communication with the air inlet. The hub suction outlet port extends through the splitter and is in fluid communication with the scavenge flow path.

GAS TURBINE ENGINE WITH INERTIAL PARTICLE SEPARATOR

An inertial particle separator (IPS) has: a main duct having an inlet fluidly connected to an environment outside of the aircraft engine, the main duct having a first segment and a second segment, the first segment extending longitudinally away from the inlet and vertically toward an elbow, the second segment extending vertically and longitudinally away from the elbow, the main duct having a concave side and a convex side; two inlet ducts extending from the concave side of the main duct, the two inlet ducts extending laterally away from one another and vertically away from the elbow; and a bypass duct communicating with the main duct, an intersection between the bypass duct and the main duct defining a splitter, the bypass duct extending along the longitudinal direction and laterally between the two inlet ducts, the two inlet ducts and the bypass duct extending vertically away from one another. 1. An inertial particle separator (IPS) for fluid communication with an engine inlet of an aircraft engine , the IPS defining a longitudinal direction , a lateral direction normal to the longitudinal direction , and a vertical direction normal to both of the longitudinal direction and the lateral direction , comprising:a main duct having an inlet fluidly connected to an environment outside of the aircraft engine, the main duct having a first segment and a second segment, the first segment extending longitudinally away from the inlet and vertically toward an elbow, the second segment extending vertically and longitudinally away from the elbow, the main duct having a concave side and a convex side;two inlet ducts communicating with the main duct and extending from the concave side of the main duct, the two inlet ducts extending laterally away from one another and vertically away from the elbow; anda bypass duct communicating with the main duct and extending from the convex side of the main duct at a junction between the two inlet ducts and the main duct, an intersection between ...

FILTER ELEMENT, SYSTEMS, AND METHODS

A gas turbine air intake system uses a filter element having a seal member with radial projections and radial recesses. The seal member forms a seal with components on the tube sheet of the system and at the end opposite of the tube sheet. At the end opposite of the tube sheet, there can be an assembly cover, or alternatively, an additional filter cartridge. 1. A filter element comprising:(a) a tubular section of filter media; and (i) each of the first and second end caps having a seal arrangement along an inner radial surface of each of the end caps;', '(ii) each of the seal arrangements including a seal member having an inwardly radially directed seal surface and a thickness that varies along the seal member surface., '(b) first and second opposite open end caps secured to the filter media;'}2. The filter element of wherein each the seal arrangements has a same shape as the other.3. The filter element of wherein the tubular section of media is conical claim 1 , and the seal arrangements vary in proportion to each other.4. The filter element of further including a seal support; the seal member being supported by the seal support; wherein the seal support comprises an inner liner extending between the first and second end caps.5. The filter element of wherein the thickness of the seal member surface varies in a radial direction along the seal member surface.6. The filter element of wherein a length of the seal member surface is constant in an axial direction.7. The filter element of wherein the seal member thickness varies by a minimum thickness and a maximum thickness claim 1 , wherein the maximum thickness is at least 1.1 times the minimum thickness.8. The filter element of wherein the radially directed seal surface comprises a plurality of outwardly projecting and axially extending portions and a plurality of inwardly projecting and axially extending portions.9. The filter element of wherein the plurality of outwardly projecting and axially extending portions and ...

SYSTEM, METHOD AND COMPUTER PROGRAM PRODUCT FOR AIR FILTER MANAGEMENT

The present invention relates to a system () for air filter management, the system comprising a plurality of air filter devices () and an air filter control station (). Each air filter device () is provided at an air filter arrangement in an air flow inlet to an industrial installation and comprises at least one filter medium capable of removing particulate material and/or airborne molecular contamination, AMC, from an air flow received at the air flow inlet. Each air filter device comprises a set of sensors arranged to gather sensor data representative of an operating state of the air filter arrangement, a microprocessor and a communication unit. The air filter control station () comprises communication unit arranged to receive operating state information from the plurality of air filter devices and a user interface for selecting an air filter arrangement of an air filter device. The air filter control station also comprises processing circuitry arranged to estimate a life expectancy of the selected air filter arrangement based on the operating state information received from an air filter device provided at the selected air filter arrangement and on operating state information received from one or more other air filter devices provided at other filter arrangements. 140414241424141a,ba,bab. A system for air filter management () , the system comprising air filter devices () and an air filter control station () , wherein each air filter device () is provided at an air filter arrangement in an air flow inlet to an industrial installation , the air filter arrangement comprising at least one filter medium capable of removing particulate material and/or airborne molecular contamination , AMC , from an air flow received at the air flow inlet , wherein each air filter device comprises a set of sensors arranged to gather sensor data representative of an operating state of the air filter arrangement , a microprocessor arranged to determine operating state information for the ...

PUSHER TURBOPROP POWERPLANT INSTALLATION

A turboprop gas turbine engine mountable to an aircraft has an engine core and a gearbox driving a propeller, the engine core and the gearbox being enclosed within a nacelle. The propeller is located rearward of the gearbox and the engine core relative to a direction of travel of the aircraft. An air intake is disposed within the nacelle and formed to direct ambient air into the engine core. The air intake includes an air inlet duct, having a forward-facing intake inlet receiving the ambient air, with an upstream section and a downstream section. The upstream section is in fluid communication with the intake inlet and extends downstream from the intake inlet. The downstream section fluidly connects to and directs air from the upstream section into the engine air inlet. A second air outlet duct is located within the nacelle and directs air into an air-cooled-oil-cooler (ACOC). 1. A turboprop gas turbine engine adapted to be mounted to an aircraft , the turboprop gas turbine engine comprising:an engine core and a gearbox driving a propeller, the engine core and the gearbox being enclosed within a nacelle, the propeller located rearward of the gearbox and the engine core relative to a direction of travel of the aircraft, the turboprop gas turbine engine being a pusher engine; andan air intake disposed within the nacelle and formed to direct ambient air into the engine core of the turboprop gas turbine engine, the air intake including an air inlet duct having a forward-facing intake inlet receiving the ambient air, the air inlet duct including an upstream section and a downstream section, the upstream section of the air inlet duct in fluid communication with the intake inlet and extending downstream from the intake inlet, the downstream section of the air inlet duct fluidly connected to and directing air from the upstream section into the engine air inlet of the engine core, and a second air outlet duct located within the nacelle, the second air outlet duct directing ...

REMOVAL OF CONTAMINANTS FROM AIR FOR USE IN AIRCRAFT ENGINES

A secondary air system for an aircraft engine comprises an air flow path communicating between a source of pressurized cooling air and an air consuming component. A filtering baffle is disposed in the air flow path upstream from the air consuming component. The filtering baffle has a monolithic body at least partly made of a cellular material, the cellular material including a non-stochastic lattice structure having a plurality of cells arranged in an ordered, repeating manner for trapping particulate matter contained in a flow of contaminated air. 1. A secondary air system (SAS) for an aircraft engine comprising:an air flow path communicating between a core gas path of the aircraft engine and an air consuming component; anda filtering baffle disposed in the air flow path upstream from the air consuming component, the filtering baffle including a monolithic body at least partly made of a cellular material, the cellular material including a non-stochastic lattice structure having a plurality of cells arranged in an ordered, repeating manner for trapping particulate matter contained in a flow of contaminated air.2. The secondary air system according to claim 1 , wherein the non-stochastic lattice structure includes first and second non-stochastic lattice structures claim 1 , said first and second non-stochastic lattice structures having different cell geometries and/or cell sizes.3. The secondary air system according to claim 1 , wherein the filtering baffle defines first and second traps on an upstream side thereof relative to the flow of contaminated air claim 1 , the first and second traps fluidly interconnected by a first constricted passageway claim 1 , and wherein the non-stochastic lattice structure is provided inside said first and second traps.4. The secondary air system according to claim 3 , wherein the first and second traps are bounded by bottom and side surfaces forming part of said monolithic body of the filtering baffle claim 3 , and wherein the non- ...

Integrated Environmental Control System Manifold

A compressor intermediate case for a gas turbine engine includes a plurality of intermediate case struts joining the compressor intermediate case to an inner engine structure. Each strut of the plurality of intermediate case struts includes a leading edge. A turning scoop is disposed at the leading edge of each strut of the plurality of intermediate case struts. A plurality of diffusers extends radially outwardly from the compressor intermediate case so that each diffuser of the plurality of diffusers engages with a corresponding turning scoop. A substantially annular structural fire wall extends radially outwardly from the compressor intermediate case. An environmental control system manifold is disposed on the compressor intermediate case. The environmental control system manifold includes an exit port. 1. An intermediate case for a gas turbine engine compressor , the intermediate case comprising:a plurality of intermediate case struts joining the intermediate case to an inner engine structure, each strut of the plurality of intermediate case struts including a leading edge;a turning scoop being disposed at the leading edge of each strut of the plurality of intermediate case struts;a plurality of diffusers extending radially outwardly from the intermediate case, each diffuser of the plurality of diffusers being engaged with a corresponding turning scoop;a substantially annular structural fire wall extending radially outwardly from the intermediate case; andan environmental control system manifold being disposed on the intermediate case, the environmental control system manifold including an exit port.225. The intermediate case of claim 1 , further including a non-structural fairing extending radially outwardly from the intermediate case claim 1 , the non-structural fairing disposed upstream of the annular structural fire wall to define a . bleed duct therebetween.3252525. The intermediate case of claim 2 , further including a . stability bleed valve in operable ...

INTAKE AIR FILTER DEVICE, FILTER REPLACEMENT METHOD OF INTAKE AIR FILTER DEVICE, AND GAS TURBINE

An intake air filter device with a filter member disposed in an intake air path of a gas turbine. The intake air filter device including: a frame body that supports the filter member inserted thereinto from the upstream side in a direction in which a fluid flows through the intake air path; and a closure plate engaging part mounted on the downstream side of the frame body and serving to engage a closure plate that covers the downstream side of the filter member. 1. An intake air filter device with a filter member disposed in an intake air path of a gas turbine , the intake air filter device comprising:a frame body that supports the filter member inserted thereinto from the upstream side in a direction in which a fluid flows through the intake air path; anda closure plate engaging part mounted on the downstream side of the frame body and serving to engage a closure plate that covers the downstream side of the filter member.2. The intake air filter device according to claim 1 , wherein the engaging part includes a guide member that supports the closure plate so as to be movable in a direction intersecting the direction in which a fluid flows through the intake air path.3. The intake air filter device according to claim 2 , comprising a pair of guide members disposed one on each side of the filter member claim 2 , wherein the pair of guide members each have a groove capable of receiving the closure plate claim 2 , and openings of the grooves face each other.4. The intake air filter device according to claim 1 , comprising a closure plate that is mounted on the frame body through the engaging part.5. The intake air filter device according to claim 1 , wherein the frame body includes a plate-like tube sheet claim 1 , and the filter member is supported on the tube sheet.6. The intake air filter device according to claim 2 , comprising a fixture that detachably fixes the closure plate to the frame body through the guide member.7. The intake air filter device according to ...

Scavenge methodologies for turbine engine particle separation concepts

A method for scavenging small particles from a turbine engine includes directing compressed air through a flowpath, downstream of a compressor, which causes a reduction in a radial flow component and the introduction of or an increase in an axial flow component of the compressed air, removing a portion of the compressed air from the flowpath and directing the portion into a scavenge plenum, the scavenge plenum being positioned adjacent to and radially outward from the flow path, and returning the portion of the compressed air from the plenum to the flowpath while maintaining a majority of the small particles that were present in the portion within the scavenge plenum. Further, the method includes removing the majority of small particles from the plenum. The step of removing occurs intermittently during engine operation, during engine shutdown, or while the engine is not operation, but does not occur continuously during engine operation.

PARTICLE SEPARATOR

An air-inlet duct includes an outer wall, an inner wall, and a splitter. The splitter cooperates with the outer wall and the inner wall to establish a particle separator which separates particles entrained in an inlet flow moving through the air-inlet duct to provide a clean flow of air to a compressor section of a gas turbine engine. 1. An air-inlet duct for use with a gas turbine engine , the air-inlet duct comprisingan outer wall arranged circumferentially about an engine rotation axis of the air-inlet duct,an inner wall located radially between the outer wall and the engine rotation axis, the inner wall and the outer wall cooperate to define an air-inlet passageway adapted to receive a mixture of air and particles suspended in the air, anda splitter located radially between the outer wall and the inner wall and configured to separate the mixture of air and particles into a clean flow substantially free of particles and a dirty flow containing the particles, the dirty flow located adjacent the outer wall and the clean flow located radially between the dirty flow and the inner wall,wherein the outer wall is formed to include a plurality of apertures arranged to extend radially through the outer wall to block a wall-normal vortex from forming in the air-inlet passage ahead of the splitter so that a number of particles entering the clean flow is reduced.2. The air-inlet duct of claim 1 , wherein the splitter includes an outer splitter surface that cooperates with the outer wall to define a scavenge channel and an inner splitter surface that cooperates with the inner wall to define an engine channel and the splitter is configured to direct the dirty flow into the scavenge channel and the clean flow into the engine channel.3. The air-inlet duct of claim 2 , wherein the outer splitter surface and the inner splitter surface form a splitter rim and the plurality of apertures include apertures located axially forward of the splitter rim.4. The air-inlet duct of claim 1 , ...

INLET PARTICLE SEPARATOR SYSTEM WITH AIR INJECTION

An inlet particle separator system for a vehicle engine includes a hub section, a shroud section, a splitter section, and an injection opening. The shroud section surrounds at least a portion of the hub section and is spaced apart therefrom to define a passageway having an air inlet. The splitter is disposed downstream of the air inlet and extends into the passageway to divide the passageway into a scavenge flow path and an engine flow path. The injection opening is formed in and extends through the hub section, and is disposed downstream of the air inlet. 1. An inlet particle separator system for a vehicle engine , comprising:a hub section;a shroud section surrounding at least a portion of the hub section and spaced apart therefrom to define a passageway, the passageway having an air inlet;a splitter disposed downstream of the air inlet and extending into the passageway to divide the passageway into a scavenge flow path and an engine flow path; andan injection opening formed in and extending through the hub section, the injection opening disposed downstream of the air inlet.2. The system of claim 1 , wherein:the passageway has a cross sectional flow area;the hub section and the shroud section are configured such that the cross sectional flow area of the passageway decreases downstream of the air inlet to define a throat section; andthe injection opening is disposed between the air inlet and the throat section.3. The system of claim 2 , wherein the injection opening is adapted to receive a flow of pressurized air and is configured claim 2 , upon receipt of the pressurized air claim 2 , to form a ramp of air that extends from the injection opening to the throat section.4. The system of claim 2 , wherein:the hub section and the shroud section are configured such that the cross sectional flow area of the passageway increases downstream of the throat section to define a separation section that includes the scavenge flow section and the engine flow path; andthe splitter ...

FILTER UNIT QUALITY MANAGEMENT SYSTEM AND FILTER UNIT QUALITY MANAGEMENT METHOD

The present application relates to a system for quality management of a filter unit disposed in an intake passage. The system includes a plurality of evaluation parameter detection units configured to detect an evaluation parameter relating to of each filter constituting a filter layer of the filter unit. By determining a distribution of the evaluation parameter based on the detection values, the quality evaluation is performed. 1. A filter unit quality management system for managing quality of a filter unit that is disposed in an intake passage and includes at least one filter layer having a plurality of filters arranged along a cross-sectional direction of the intake passage , the filter unit quality management system comprising:a plurality of evaluation parameter detection units each of which is disposed corresponding to each of at least part of the plurality of filters constituting one of the at least one filter layer, and configured to detect an evaluation parameter relating to a filter life time of the corresponding filter; anda quality evaluation unit configured to determine a distribution of the evaluation parameter in the plurality of filters based on detection values of the plurality of evaluation parameter detection units, and evaluate quality of the at least one filter layer based on the distribution.2. The filter unit quality management system according to claim 1 , wherein the quality evaluation unit evaluates degree of clogging of each of the plurality of filters based on a transient change in the evaluation parameter.3. The filter unit quality management system according to claim 2 ,wherein each of the plurality of filters has a filter element accommodated in a housing, andwherein the evaluation parameter is filter differential pressure inside the housing.4. The filter unit quality management system according to claim 3 , wherein the evaluation parameter is degree of strain of the housing.5. The filter unit quality management system according to ...

SOUNDPROOF CABIN OF TURBINE ENGINE

The present invention discloses a soundproof cabin of a turbine engine. The soundproof cabin is sleeved on the turbine engine. The soundproof cabin includes a cabin body, an induction noise reduction unit and a ventilation noise reduction unit, wherein the induction noise reduction unit and the ventilation noise reduction unit are disposed on the cabin body, the surrounding of which is filled with soundproof materials, the induction noise reduction unit is used to reduce the induction noise of the turbine engine, the ventilation noise reduction unit is used to reduce the noise of the ventilation system of the turbine engine. Beneficial effects: an induction noise reduction unit is disposed at an air inlet of the turbine engine to reduce the induction noise of the turbine engine; a ventilation noise reduction unit is disposed on the transmission direction of the turbine engine to reduce the ventilation and cooling noise of the turbine engine; the surrounding of the turbine engine is filled with soundproof materials to achieve the overall noise reduction around the turbine engine. 1. A soundproof cabin of a turbine engine , wherein the soundproof cabin is sleeved on the turbine engine; the soundproof cabin comprises a cabin body , an induction noise reduction unit and a ventilation noise reduction unit; the induction noise reduction unit and the ventilation noise reduction unit are disposed on the cabin body , the surrounding of which is filled with soundproof materials; the induction noise reduction unit is used to reduce the induction noise of the turbine engine , and the ventilation noise reduction unit is used to reduce the noise of the ventilation system of the turbine engine.2. The soundproof cabin of the turbine engine according to claim 1 , wherein the induction noise reduction unit comprises an intake filter claim 1 , an intake silencer claim 1 , an intake chamber and an intake piping claim 1 , the intake chamber is arranged on the top of the cabin body claim ...

DIRT COLLECTOR SYSTEM

A combustor may comprise a combustion chamber encapsulated by a combustor casing, wherein the combustor casing comprises a casing forward portion, a casing radially inward portion, a casing radially outward portion, and a casing aft portion. The casing radially inward portion may comprise a dirt collector system comprising a hot panel adjacent to the combustion chamber; a cold shell panel coupled to the hot panel such that the hot panel is between the combustion chamber and the cold shell panel; and a dirt collector panel coupled to the cold shell panel such that the cold shell panel is between the hot panel and the dirt collector panel. The cold shell panel and the dirt collector panel at least partially define a dirt collecting space. 1. A combustor , comprising:a combustion chamber encapsulated by a combustor casing, wherein the combustor casing comprises a casing forward portion, a casing radially inward portion, a casing radially outward portion, and a casing aft portion, a hot panel adjacent to the combustion chamber;', 'a cold shell panel coupled to the hot panel such that the hot panel is between the combustion chamber and the cold shell panel; and', 'a dirt collector panel coupled to the cold shell panel such that the cold shell panel is between the hot panel and the dirt collector panel, wherein the cold shell panel and the dirt collector panel at least partially define a dirt collecting space., 'wherein the casing radially inward portion comprises a dirt collector system, comprising2. The combustor of claim 1 , wherein the dirt collector panel comprises a dirt collector hole disposed through a forward portion of the dirt collector panel claim 1 , wherein the dirt collector hole spans a first length through the dirt collector panel substantially perpendicular to the cold shell panel such that an airflow may flow through the dirt collector hole claim 1 , into the dirt collecting space claim 1 , and contact a shell forward portion of the cold shell panel.3. ...

METHODS AND SYSTEMS FOR OPTIMIZING FILTER CHANGE INTERVAL

Provided is a method for determining a filter change schedule for a gas turbine. The method includes determining differential pressure variation across filters and a time elapsed since a last filter change, where the differential pressure variation and the time elapsed are each associated with at least one filter disposed in the gas turbine. The method also includes estimating a future power loss and/or a future fuel consumption caused by the differential pressure variation. Moreover, the method can include determining the filter change schedule based on a cost of the filter change, the time elapsed, a cost of the future power loss, and optionally a cost of the future fuel consumption, a cost of emission variation, and a cost of production loss. 1. A method for determining a filter change schedule of one or more filters arranged upstream an air intake inlet of a gas turbine , the method comprising:measuring differential pressure variation across the one or more filters and a time elapsed since a last filter change, the differential pressure variation and the time elapsed each being associated with at least one filter;estimating a future power loss and, optionally, a future fuel consumption caused by the differential pressure variation; anddetermining the filter change schedule based on a cost of the filter change, the time elapsed, a cost of the future power loss, and optionally a cost of the future fuel consumption, and a cost of emission variation due to the differential pressure variation and a cost of production loss.2. The method according to claim 1 , wherein the future power loss is estimated measuring ambient temperature and pressure claim 1 , the discharge temperature of the gas turbine and the speed of the gas turbine.3. The method according to claim 1 , further comprising determining claim 1 , the future power loss claim 1 , the future fuel consumption claim 1 , the future emission variation claim 1 , based on claim 1 , respectively claim 1 , an actual ...

AIR INTAKE UNIT FOR AN AIRCRAFT ENGINE

An air intake unit for an engine of an aircraft; the intake unit has: a tubular housing; a first inlet opening which is obtained through an outer wall of the tubular housing and through which external air can be taken in; an air filter which engages the first inlet opening; a second inlet opening which is obtained through the outer wall of the tubular housing and through which external air can be taken in; a shutter device which is coupled to the second inlet opening and is movable between a closed position, in which it closes the second inlet opening, and an open position, in which it sets the passage through the second inlet opening free; and an actuator, which moves the shutter device. 1313) An air intake unit () for an engine of an aircraft (); the intake unit () comprises:{'b': 4', '5', '6', '4', '14', '15, 'a tubular housing (), which has a longitudinal symmetry axis (), is provided with an outer wall () delimiting the space enclosed by the tubular housing (), and has a front portion () and a rear portion ();'}{'b': 7', '15', '6', '4', '2, 'at least one first inlet opening () which is obtained in the rear portion () through the outer wall () of the tubular housing () and through which the external air needed to operate the engine () can be taken in;'}{'b': 8', '4', '7', '7, 'at least one air filter () which is supported by the tubular housing () and engages the first inlet opening (), so as to filter the external air flowing through the first inlet opening ();'}{'b': 9', '14', '6', '4', '7', '8', '2, 'at least one second inlet opening () which is obtained in the front portion () through the outer wall () of the tubular housing (), is separate from and independent of the first inlet opening () and the air filter (), and through which the external air needed to operate the engine () can be taken in;'}{'b': 10', '9', '9', '9, 'a shutter device () which is coupled to the second inlet opening () and is movable between a closed position, in which it closes the ...

INERTIAL PARTICLE SEPARATOR FOR AIRCRAFT ENGINE

An inertial particle separator, having: an inlet duct defining an intake; an intermediate duct extending from the inlet duct to an engine inlet; a bypass duct in fluid communication with and extending downstream from the inlet duct, the bypass duct defining an outlet communicating with the environment of the aircraft engine, a splitter defined at an intersection of a wall of the bypass duct and a wall of the intermediate duct; a splitter vane within the intermediate duct and having a leading edge located upstream of the splitter relative to a flow circulating through the separator, the splitter vane and the wall of the intermediate duct defining a channel therebetween; and a porous plate extending across the channel and defining openings sized so as to aggregate ice and be blocked by ice under icing conditions. 1. An inertial particle separator (IPS) communicating with an engine inlet of an aircraft engine , comprising: an inlet duct defining an intake communicating with an environment of the aircraft engine; an intermediate duct extending from the inlet duct to the engine inlet; a bypass duct in fluid communication with and extending downstream from the inlet duct , the bypass duct defining an outlet communicating with the environment of the aircraft engine , a splitter defined at an intersection of a wall of the bypass duct and a wall of the intermediate duct; a splitter vane within the intermediate duct and having a leading edge located upstream of the splitter relative to a flow circulating through the IPS , the splitter vane and the wall of the intermediate duct defining a channel therebetween; and a porous plate extending across the channel and defining openings sized so as to aggregate ice and be blocked by ice under icing conditions.2. The IPS of claim 1 , wherein the splitter vane has an airfoil-shaped cross-section.3. The IPS of claim 1 , wherein an extrapolation of the wall of the bypass duct connects the leading edge of the splitter vane and wherein an ...

MOBILE GAS TURBINE INLET AIR CONDITIONING SYSTEM AND ASSOCIATED METHODS

A system, as well as associated methods, for increasing the efficiency of a gas turbine including an inlet assembly and a compressor may include a housing configured to channel airstream towards the inlet assembly, an air treatment module positioned at a proximal end the housing, and at least one air conditioning module mounted downstream of the air treatment module for adjusting the temperature of the airstream entering the compressor. The air treatment module may include a plurality of inlet air filters and at least one blower configured to pressurize the air entering the air treatment module. 1. An air treatment system to increase the efficiency of a gas turbine comprising an inlet assembly and a compressor , the inlet assembly located upstream of the compressor and forming an input side of the gas turbine , the air treatment system comprising:a housing positioned to channel an airstream towards the inlet assembly, the housing positioned upstream of the input side, which channels the airstream to the compressor; and a plurality of inlet air filters to provide fluid flow to a first internal chamber, and', 'one or more blowers mounted in the first internal chamber and providing fluid flow to an interior of the housing via at least one outlet of the first internal chamber, the one or more blowers configured to pressurize the air entering the air treatment module, and', 'one or more air conditioning modules mounted downstream of the air treatment module for adjusting the temperature of the airstream entering the compressor, such that the airstream enters the one or more air conditioning modules at a first temperature and exits the one or more air conditioning modules at a second temperature., 'an air treatment module positioned at a proximal end of the housing, the air treatment module comprising2. The air treatment system of claim 1 , wherein the one or more air conditioning modules comprise at least one chiller module.3. The air treatment system of claim 2 , ...

Inlet Filter For Gas Turbine Engines Using Disposable Surface Adhesive

A method of filtering air entering the intake opening of a gas turbine engine. A straightening tube provides a straight channel for incoming air flow. A flow redirector provides a path for air flow that is at right angles to the channel provided by the straightening tube and that leads to the intake opening of the engine. A filter at the downstream end of the flow redirector has a pair of rollers for unrolling and re-rolling a roll of adhesive tape, with an exposed section of the adhesive tape blocking the downstream end of the flow redirector and capturing particles in the air flow. The rollers are activated as needed to expose fresh sections of tape. 1. A method of filtering air entering the intake opening of a gas turbine engine , comprising:installing a straightening tube upstream the intake opening, the straightening tube providing a straight channel for incoming air flow;interposing a flow redirector between a downstream end of the straightening tube and the intake opening, the flow redirector providing a path for air flow that is at right angles to the channel provided by the straightening tube and that leads to the intake opening of the gas turbine engine;wherein the flow redirector has an upstream end for receiving air flow from the straightening tube and an downstream end opposite the receiving end;installing a filter at the downstream end of the flow redirector, the filter comprising a first roller for storing and unrolling a roll of adhesive tape and a second roller for re-rolling and storing the roll of adhesive tape;wherein the first roller and the second roller are spaced across the downstream end of the flow redirector, such that an exposed section of tape passing from the first roller to the second roller blocks the downstream end of the flow redirector with the adhesive side of the tape facing the air flow; andincrementally unrolling the first roller and rolling the second roller such that a fresh exposed section of the adhesive tape blocks the ...

PARTICLE SEPARATORS FOR TURBOMACHINES AND METHOD OF OPERATING THE SAME

A particle separator includes a separator body in a primary fluid passageway of a machine. The primary fluid passageway includes one or more bleed holes through which a diverted portion of the fluid flowing in the primary fluid passageway toward a volume of the machine is diverted into an auxiliary flow passageway that bypasses the volume and directs the diverted portion of the fluid toward one or more other components of the machine. The separator body is coupled with the inner wall and/or outer wall of the primary fluid passageway. The separator body includes an upstream edge positioned to separate at least some particles carried by the fluid from the fluid as the diverted portion of the fluid bends around and flows over the at least one upstream edge of the separator body and into the auxiliary flow passageway. 1. A particle separator comprises:a separator body configured to be disposed in a primary fluid passageway of a machine that directs a particle-carrying fluid along a flow path in the primary fluid passageway toward a volume of the machine, the primary fluid passageway located between opposing first and second walls,wherein the primary fluid passageway includes one or more bleed holes through which a diverted portion of the fluid flowing in the primary fluid passageway is diverted into an auxiliary flow passageway that bypasses the volume and directs the diverted portion of the fluid toward one or more components of the machine that are outside of the volume of the machine,wherein the separator body extends along the flow path from an upstream end that is configured to be coupled with the first wall of the primary fluid passageway, the separator body including at least one upstream edge positioned to separate at least some particles carried by the fluid from the fluid as the diverted portion of the fluid bends around and flows over the at least one upstream edge of the separator body and into the auxiliary flow passageway via the one or more bleed holes ...

APPARATUS AND METHOD FOR AIR PARTICLE SEPARATION IN A GAS TURBINE ENGINE

A particle separator for removing particles in a flow of air is provided. The particle separator having: a conduit for directing air towards a curved section of the conduit; and a drum in fluid communication with the conduit proximate to the curved section of the conduit, wherein particles in the air travelling towards the curved section will contact a surface of the drum. 1. A particle separator for removing particles in a flow of air , comprising:a conduit for directing air towards a curved section of the conduit; anda drum in fluid communication with the conduit proximate to the curved section of the conduit, wherein particles in the air travelling towards the curved section will contact a surface of the drum.2. The particle separator of claim 1 , wherein the surface of the drum is provided with a plurality of grooves.3. The particle separator of claim 1 , wherein the surface of the drum is provided with an adhesive layer to captivate the particles that contact the surface of the drum.4. The particle separator of claim 1 , wherein the surface of the drum is provided with a solvent layer that dissolves particles that contact the surface of the drum.5. The particle separator of claim 1 , wherein the curved section is located between an inlet section and an outlet section of the conduit.6. The particle separator of claim 1 , wherein the drum is rotatably secured to the particle separator and wherein the particle separator further comprises a scraper configured and positioned to contact the surface of drum as it rotates due to the particles contacting the surface of the drum claim 1 , wherein the scraper is configured to separate particles captured on the surface of the drum from the surface of the drum.7. The particle separator of claim 6 , further comprising a second conduit fluidly coupled to the surface of the drum claim 6 , wherein particles separated from the surface of the drum by the scraper are deposited into the second conduit.8. The particle separator of ...

TURBINE ENGINE COMPONENT AND METHOD OF COOLING

A component for a turbine engine includes a body having an outer surface confronting a combustion air flow path and defining an interior, as well as a first cooling passage having at least a portion supplying cooling air to the interior of the body. The component also includes a cyclone separator having a cooling air inlet, a clean air outlet, and a dirty air outlet. 1. A component for a turbine engine comprising:a body having an outer surface confronting a combustion air flow path and defining an interior;a first cooling passage having at least a portion supplying cooling air to the interior of the body;a second cooling passage having at least a portion supplying cooling air to the interior of the body and fluidly separated from the first cooling passage;a scavenge passage fluidly separated from the second cooling passage; anda first cyclone separator having a cooling air inlet, a clean air outlet fluidly coupled to the first cooling passage, and a dirty air outlet fluidly coupled to the scavenge passage.2. The component of wherein the scavenge passage supplies dirty cooling air to a benign region of the turbine engine.3. The component of wherein the body further comprises a monolithic body having the outer surface claim 1 , the first cooling passage claim 1 , the second cooling passage claim 1 , the scavenge passage claim 1 , and the first cyclone separator.4. The component of further comprising an intersection fluidly coupling the first cooling passage and the second cooling passage.5. The component of wherein the intersection is positioned downstream of the first cyclone separator.6. The component of wherein the intersection is within the interior of the body.7. The component of further comprising an interior cooling passage within the body fluidly coupled to the first and second cooling passages via the intersection.8. The component of further comprising one of a nozzle support claim 1 , a platform claim 1 , an inner band claim 1 , an outer band claim 1 , a ...

INLET PARTICLE SEPARATOR SYSTEM

An inlet particle separator system coupled to an engine having an engine exhaust is presented. The inlet particle separator system includes an axial flow separator for separating air from an engine inlet into a first flow of substantially contaminated air and a second flow of substantially clean air. The inlet particle separator system further includes a scavenge subsystem in flow communication with the axial flow separator for receiving the first flow of substantially contaminated air. Furthermore, the inlet particle separator system includes a fluidic device including a first inlet and an exhaust, where the fluidic device is configured to accelerate the first flow of substantially contaminated air through the scavenge subsystem and emit the first flow of substantially contaminated air via the exhaust of the fluidic device, wherein the exhaust of the fluidic device is different from an exhaust of the engine. 1. An inlet particle separator system configured to be coupled to an engine , the inlet particle separator system comprising:an axial flow separator for separating air from an engine inlet into a first flow of substantially contaminated air and a second flow of substantially clean air;a scavenge subsystem in fluid communication with the axial flow separator for receiving the first flow of substantially contaminated air; anda fluidic device comprising a first inlet and an exhaust, wherein the fluidic device is disposed in flow communication with the scavenge subsystem, wherein the fluidic device is configured to accelerate the first flow of substantially contaminated air through the scavenge subsystem and emit the first flow of substantially contaminated air via the exhaust of the fluidic device,wherein the exhaust of the fluidic device is different from an exhaust of the engine.2. The inlet particle separator system of claim 1 , wherein the fluidic device is disposed such that the first inlet of the fluidic device receives the first flow of substantially ...

FILTERING CHAMBER FOR GAS TURBINES AND METHOD OF MAINTENANCE THEREOF

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

FILTRATION SYSTEM FOR USE IN A GAS TURBINE ENGINE ASSEMBLY AND METHOD OF ASSEMBLING THEREOF

A filtration system and methods of assembly and operation are provided. The filtration system includes an array of perforated tubes in flow communication with a flow of intake air. Each perforated tube comprises a solids inlet and a solids outlet. The system also includes a solids feed system comprising a feed line coupled in flow communication with said solids inlet and configured to channel sorbent material through each perforated tube in said array. The filtration system also includes a monitoring arrangement for monitoring a parameter associated with the intake air, and varying the operation of the system based upon said parameter. 1. A filtration system for use in a gas turbine engine assembly , said system comprising:an array of perforated tubes in flow communication with a flow of intake air, wherein each perforated tube comprises a solids inlet and a solids outlet; anda solids feed system comprising a feed line coupled in flow communication with said solids inlet and configured to channel sorbent material through each perforated tube in said array, wherein the sorbent material is configured to remove gaseous contaminants entrained in the flow of intake air.2. The system in accordance with claim 1 , wherein said solids feed system further comprises:a recycle line coupled in flow communication with said solids outlet and configured to receive spent sorbent material from said array of perforated tubes; anda heater coupled in flow communication with said recycle line, wherein said heater is configured to regenerate the spent sorbent material.3. The system in accordance with claim 2 , wherein said heater comprises an outlet configured to channel a flow of contaminant-rich off-gas away from the flow of intake air as the spent sorbent material is regenerated.4. The system in accordance with claim 2 , wherein said solids feed system is configured to channel sorbent material through said array of perforated tubes at a flow rate based at least partially on a ...

MOBILE ELECTRIC POWER GENERATION FOR HYDRAULIC FRACTURING OF SUBSURFACE GEOLOGICAL FORMATIONS

Providing mobile electric power comprising a power generation transport configured to convert hydrocarbon fuel to electricity and an inlet and exhaust transport configured to: couple to at least one side of the power generation transport such that the inlet and exhaust transport is not connected to a top side of the power generation transport, provide ventilation air and combustion air to the power generation transport, collect exhaust air from the power generation transport, and filter the exhaust air. 1. A system for providing mobile electric power , the system comprising: an inlet plenum; and', 'an exhaust collector; and, 'a gas turbine generator transport comprising an air inlet filter housing; and', 'an exhaust stack,, 'an inlet and exhaust transport comprisingwherein the gas turbine generator transport and the inlet and exhaust transport are separate transports that are independently movable,wherein the gas turbine generator transport and the inlet and exhaust transport are both configured to be positioned side-by-side to each other in an operational mode,wherein in the operational mode the air inlet filter housing is connected to the inlet plenum and the exhaust stack is connected to the exhaust collector between facing sides of the gas turbine generator transport and the inlet and exhaust transport, andwherein the facing sides are not end sides of the gas turbine generator transport and inlet and exhaust transport.2. The system of claim 1 , wherein the inlet and exhaust transport comprises a hydraulic walking system used to position the inlet and exhaust transport at a predetermined distance for coupling to the gas turbine generator transport.3. The system of claim 1 , wherein the exhaust stack is laid in a horizontal position on the inlet and exhaust transport in a transportation mode and lifted to a vertical position on the inlet and exhaust transport in an operational mode claim 1 , and wherein the exhaust stack aligns with an exhaust end connector on the ...

LIQUID INJECTION INLET PARTICLE SEPARATOR SYSTEMS AND METHODS

An inlet particle separator system for a vehicle engine includes a separator assembly and a liquid injection system. The separator assembly defines an inlet flow path for receiving inlet air and includes a scavenge flow path and an engine flow path downstream of the inlet flow path. The separator assembly is configured to separate the inlet air into scavenge air and engine air such that the scavenge air is directed from the inlet flow path into the scavenge flow path and the engine air is directed from the inlet flow path into the engine flow path. The liquid injection system is coupled to the separator assembly and configured to introduce a diffused liquid into the inlet air flowing through the separator assembly. 1. An inlet particle separator system for a vehicle engine , comprising:a separator assembly defining an inlet flow path for receiving inlet air, the separator assembly including a scavenge flow path and an engine flow path downstream of the inlet flow path, the separator assembly configured to separate the inlet air into scavenge air and engine air such that the scavenge air is directed from the inlet flow path into the scavenge flow path and the engine air is directed from the inlet flow path into the engine flow path;a liquid injection system coupled to the separator assembly and configured to introduce a diffused liquid into the inlet air flowing through the separator assembly.2. The inlet particle separator system of claim 1 , wherein the liquid injection system includes a nozzle proximate to the inlet configured to introduce the diffused liquid.3. The inlet particle separator system of claim 2 , wherein the liquid injection system further includes a controller for selectively activating or deactivating the liquid injection system.4. The inlet particle separator system of claim 1 , further comprising a collector assembly coupled to the scavenge flow path and configured to receive the scavenge air.5. The inlet particle separator system of claim 4 , ...

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 ...

SEPARATOR ASSEMBLY FOR A GAS TURBINE ENGINE

A separator assembly for removing entrained particles from a fluid stream passing through a gas turbine engine includes a first particle separator for separating the fluid stream into a reduced-particle stream and a particle-laden stream, and emitting the particle-laden stream through a scavenge outlet. Another particle remover is fluidly coupled to the scavenge outlet to remove more particles from the air stream. 1. A separator assembly for removing entrained particles from a fluid stream passing through a gas turbine engine , comprising: an inlet receiving the fluid stream;', 'a reduced-particle outlet emitting the reduced-particle stream; and', 'a scavenge outlet emitting the particle-laden stream; and, 'a first particle separator for separating the fluid stream into a reduced-particle stream and a particle-laden stream, comprisinga particle remover fluidly coupled to the scavenge outlet and comprising a return outlet emitting a second reduced-particle stream from the particle-laden stream;wherein the return outlet is fluidly coupled to the first particle separator to return the second reduced-particle stream to the first particle separator.2. The separator assembly of wherein the first particle separator comprises a plurality of swirl vanes located within the fluid stream and imparting a tangential velocity to the fluid stream claim 1 , thereby providing the fluid stream with a swirling motion downstream of the swirl vanes.3. The separator assembly of wherein at least one of the swirl vanes comprises a return passage fluidly coupled with the return outlet and having a passage outlet fluidly coupled to the fluid stream claim 2 , and wherein the second reduced-particle stream is returned to the fluid stream through the return passage.4. The separator assembly of wherein the at least one of the swirl vanes comprises a root and a tip claim 3 , with the passage outlet provided at the root and a passage inlet of the return passage provided at the tip.5. The separator ...

Assembly and Method for a Bag Filter

The present application provides a filtration unit for filtering a flow. The filtration unit may include one or more first layers and a second layer. The one or more first layers may include a prefilter layer and a wave layer.

GAS TURBINE ENGINE HAVING A FLOW CONTROL SURFACE WITH A COOLING CONDUIT

The invention relates to a gas turbine engine comprising a casing having a compressor section, combustion section and turbine section, axially arranged in a flow direction about a rotational axis of the engine. The engine includes a rotor located within the casing and rotatable about the rotational axis, including multiple sets of circumferentially arranged blades, with at least one set corresponding to the compressor section and another set corresponding to the turbine section. The engine also includes a set of vanes circumferentially arranged about the rotational axis and at a location upstream of the combustion section, with the vanes having a pressure side and a suction side. The engine further includes a cooling conduit extending from upstream of the combustion section to downstream of the combustion section, with an inlet located on the suction side of at least one of the vanes which allows cooling air to enter the inlet and is directed through the cooling conduit for cooling. 1. A gas turbine engine comprising:a casing having a compressor section, combustion section and turbine section, axially arrange in flow direction about a rotational axis of the engine;a rotor located within the casing and rotatable about the rotational axis, and having multiple sets of circumferentially arranged blades, with at least one set corresponding to the compressor section and another set corresponding to the turbine section;a set of vanes circumferentially arranged about the rotational axis and location upstream of the combustion section, with the vanes having a pressure side and a suction side; anda cooling conduit extending from upstream of the combustion section to downstream of the combustion section, with an inlet located on the suction side of at least one of the vanes.2. The gas turbine engine of wherein the inlet is located on the suction side where a reduced particle flow is present during operation.3. The gas turbine engine of wherein the reduced particle flow has ...

ENGINE INTAKE ASSEMBLY WITH SELECTOR VALVE

An engine assembly including an engine core including at least one internal combustion engine each including a rotor sealingly and rotationally received within a respective internal cavity to provide rotating chambers of variable volume in the respective internal cavity, a compressor having an outlet in fluid communication with an inlet of the engine core, a first intake conduit in fluid communication with an inlet of the compressor and with a first source of air, a second intake conduit in fluid communication with the inlet of the compressor and with a second source of air warmer than the first source of air, and a selector valve configurable to selectively open and close at least the fluid communication between the inlet of the compressor and the first intake conduit. A method of supplying air to a compressor is also discussed. 1. A method of supplying air to a compressor providing compressed air to an internal combustion engine core , the method comprising:directing air through an air conduit and through at least one heat exchanger extending across the air conduit;directing part of the air from the air conduit to an inlet of the compressor through a selected one of a first and second intake conduits, the first intake conduit connected to the air conduit upstream of the at least one heat exchanger and the second intake conduit connected to the air conduit downstream of the at least one heat exchanger; andpreventing the air from flowing from the air conduit to the inlet of the compressor through the other one of the first and second conduits.2. The method as defined in claim 1 , wherein the internal combustion engine core is part of a compound engine assembly for an aircraft claim 1 , the method further comprising selecting the first intake conduit to direct the part of the air from the air conduit to the inlet of the compressor during flight claim 1 , and selecting the second intake conduit to direct the part of the air from the air conduit to the inlet of the ...

FILTRATION SYSTEM AND METHOD FOR CLEANING THE INTAKE AIR OF A GAS TURBINE

In a filtration system, in particular for cleaning the intake air of a gas turbine, including a flow channel surrounded by walls with an inflow opening and an outflow opening, a partition wall with at least two openings between a dirty side and a clean side which is positioned between the inflow opening and the outflow opening and limited by the walls of the flow channel, and at least two filters for purifying a flowing fluid. At least one filter is installed at a first opening on the dirty side of the partition wall and at least one filter at a second opening on the clean side of the partition wall. 1110142146148108146148142110116122124100110100116122108100116124108. A filtration system for the cleaning intake air of a gas turbine , comprising: a flow channel () surrounded by walls () with an inflow opening () and an outflow opening () , a partition wall () positioned between the inflow opening () and the outflow opening () and limited by the walls () of the flow channel () with at least two openings () between a dirty side () and a clean side () , and at least two filters () for the cleaning a fluid that flows through the flow channel () , the at least two filters including at least one first filter () mounted at a first opening () on the dirty side () of the partition wall () and at least one second filter () at a second opening () on the clean side () of the partition wall ().2118100108. The filtration system of claim 1 , wherein frames () of the first and the second filters () overlap at least partially in one direction largely vertically to the partition wall ().3118100108108. The filtration system of claim 2 , wherein an area in which the frames () of the first and the second filters () overlap in one direction largely vertically to the partition wall () amounts to at least 5% of an overall projected area of filtration at the partition wall ().4100136108100136122124108. The filtration system of claim 1 , wherein the filters () are arranged in at least one row ...

Gas Turbine Filtration System with Inlet Filter Orientation Assembly

The present application provides a filtration system for a gas turbine engine. The filtration system may include a holding frame with a positioning element extending therefrom and a filtration unit for mounting within the holding frame. The filtration unit may include a positioning slot therein such that the positioning element extends through the positioning slot when the filtration unit is mounted within the holding frame.

EJECTOR DRIVEN SCAVENGE SYSTEM FOR PARTICLE SEPARATOR ASSOCIATED WITH GAS TURBINE ENGINE

An ejector driven scavenge system for a particle separator having a scavenge branch associated with a gas turbine engine includes at least one anti-icing circuit to receive an anti-icing fluid. The at least one anti-icing circuit is to be coupled to the particle separator. The ejector driven scavenge system includes at least one flow ejector bank to be coupled to the scavenge branch and fluidly coupled to the anti-icing fluid to direct the anti-icing fluid through the scavenge branch to drive air with entrained particles and water droplets from the particle separator. 1. An ejector driven scavenge system for a particle separator having a scavenge branch associated with a gas turbine engine , comprising:at least one anti-icing circuit configured to receive an anti-icing fluid, the at least one anti-icing circuit configured to be coupled to the particle separator; andat least one flow ejector bank configured to be coupled to the scavenge branch and fluidly coupled to the anti-icing fluid to direct the anti-icing fluid through the scavenge branch to drive air with entrained particles and water droplets from the particle separator.2. The ejector driven scavenge system of claim 1 , wherein the at least one anti-icing circuit includes a first anti-icing circuit and a second anti-icing circuit claim 1 , and the at least one flow ejector bank includes a first flow ejector nozzle bank and a second flow ejector nozzle bank claim 1 , with the first flow ejector nozzle bank fluidly coupled to the first anti-icing circuit and the second flow ejector nozzle bank fluidly coupled to the second anti-icing circuit.3. The ejector driven scavenge system of claim 2 , wherein the first flow ejector nozzle bank is opposite the second flow ejector nozzle bank in the scavenge branch.4. The ejector driven scavenge system of claim 2 , wherein the first anti-icing circuit is configured to be coupled to an opposite side of the particle separator than the second anti-icing circuit.5. The ejector ...

SCAVENGE METHODOLOGIES FOR TURBINE ENGINE PARTICLE SEPARATION CONCEPTS

A method for scavenging small particles from a turbine engine includes directing compressed air through a flowpath, downstream of a compressor, which causes a reduction in a radial flow component and the introduction of or an increase in an axial flow component of the compressed air, removing a portion of the compressed air from the flowpath and directing the portion into a scavenge plenum, the scavenge plenum being positioned adjacent to and radially outward from the flow path, and returning the portion of the compressed air from the plenum to the flowpath while maintaining a majority of the small particles that were present in the portion within the scavenge plenum. Further, the method includes removing the majority of small particles from the plenum. The step of removing occurs intermittently during engine operation, during engine shutdown, or while the engine is not operation, but does not occur continuously during engine operation. 1. A method for scavenging small particles from a turbine engine , the method comprising the steps of:compressing air in a compressor that rotates about a longitudinal axis to generate compressed air, wherein the compressed air that exits the compressor includes at least a tangential flow component and a radial flow component, and wherein the compressed air comprises a plurality of small particles;directing the compressed air through a flowpath, downstream of the compressor, which causes a reduction in the radial flow component and the introduction of or an increase in an axial flow component;removing a portion of the compressed air from the flowpath and directing the portion into a scavenge plenum, the scavenge plenum being positioned adjacent to and radially outward from the flow path;returning the portion of the compressed air from the plenum to the flowpath while maintaining a majority of the small particles that were present in the portion within the scavenge plenum; andremoving the majority of the small particles from the ...

PARTICLE SEPARATORS FOR TURBOMACHINES AND METHOD OF OPERATING THE SAME

A particle separator for a turbomachine includes a first portion including a first end and a second end opposite the first end. The turbomachine includes a first wall and a second wall defining a primary fluid passage. The first wall further defines an auxiliary fluid passage. The first end is coupled to the first wall. The second end extends from the first wall into the at least one primary fluid passage and extends in a direction defined by the fluid flow through the primary fluid passage. The second end and the first wall define a fluid diversion passage coupled in flow communication with the primary fluid passage and the auxiliary fluid passage. The fluid diversion passage is configured to divert fluid from the primary fluid passage to the auxiliary fluid passage in a direction at least partially opposed to the fluid flow through the primary fluid passage. 1. A particle separator for a turbomachine , the turbomachine including a first wall and a second wall at least partially defining at least one primary fluid passage , the first wall further defining at least one auxiliary fluid passage , said particle separator comprising a first portion comprising a first end and a second end opposite said first end , said first end coupled to the first wall , said second end extending from the first wall into the at least one primary fluid passage and extending in a direction at least partially defined by a direction of fluid flow through the at least one primary fluid passage , wherein said second end and the first wall at least partially define at least one fluid diversion passage coupled in flow communication with the at least one primary fluid passage and the at least one auxiliary fluid passage , said at least one fluid diversion passage configured to divert fluid from the at least one primary fluid passage to the at least one auxiliary fluid passage in a direction at least partially opposed to the direction of fluid flow through the at least one primary fluid passage. ...

AIR INLET DUCT HAVING A PARTICLE SEPARATOR AND AN AGGLOMERATOR FOR A GAS TURBINE ENGINE

An air-inlet duct includes a particle separator and an agglomerator. The particle separator is configured to receive atmospheric air laden with particles and to direct the particles into a scavenge passageway while allowing the atmospheric air to move into a compressor passageway thereby reducing the number of particles that enter the compressor passageway. The agglomerator is configured to cause the particles to be attracted to one another and cluster together. 1. An air-inlet duct for a gas turbine engine , the air-inlet duct comprisinga particle separator formed to include an inlet passageway for receiving a stream of air, a compressor passageway that extends downstream from the inlet passageway, and a scavenge passageway that extends downstream from the inlet passageway and that is positioned radially outward of the compressor passageway, the particle separator configured to receive atmospheric air laden with fine particles and large particles and to direct the large particles into the scavenge passageway while allowing the atmospheric air to move into the compressor passageway thereby reducing the number of large particles that enter the compressor passageway, andan agglomerator configured to emit an electro-magnetic field into the inlet passageway to charge the fine particles in the inlet passageway to cause the fine particles to be attracted to one another and cluster together to form large particles directed into the scavenge passageway by the particle separator to reduce the number of fine particles directed into the compressor passageway.2. The air-inlet duct of claim 1 , wherein the particle separator includes an outer wall spaced apart from an engine rotation axis claim 1 , an inner wall located between the outer wall and the engine rotation axis claim 1 , the inner wall and the outer wall defining the inlet passageway therebetween claim 1 , and a splitter located between the outer wall and the inner wall and including an outer splitter surface that ...

DIRT MITIGATION IN A GAS TURBINE ENGINE

An aspect includes a dirt mitigation system for a gas turbine engine. The dirt mitigation system includes a plurality of bleeds of the gas turbine engine and a control system configured to determine a particulate ingestion estimate indicative of dirt ingested in the gas turbine engine. The control system is further configured to determine one or more operating parameters of the gas turbine engine and alter a bleed control schedule of the gas turbine engine to purge at least a portion of the dirt ingested in the gas turbine engine through one or more of the bleeds of the gas turbine engine based on the particulate ingestion estimate and the one or more operating parameters. 1. A dirt mitigation system for a gas turbine engine , the dirt mitigation system comprising:a plurality of bleeds of the gas turbine engine; and determine a particulate ingestion estimate indicative of dirt ingested in the gas turbine engine;', 'determine one or more operating parameters of the gas turbine engine; and', 'alter a bleed control schedule of the gas turbine engine to purge at least a portion of the dirt ingested in the gas turbine engine through one or more of the bleeds of the gas turbine engine based on the particulate ingestion estimate and the one or more operating parameters., 'a control system configured to2. The dirt mitigation system of claim 1 , wherein the particulate ingestion estimate is determined based on a plurality of particle sensor data from the gas turbine engine.3. The dirt mitigation system of claim 2 , wherein the particle sensor data is received from one or more particle sensors at an inlet of a low pressure compressor of the gas turbine engine downstream of a fan of the gas turbine engine.4. The dirt mitigation system of claim 2 , wherein the control system is further configured to determine whether the particle sensor data indicates that a dirt concentration is above a threshold claim 2 , an engine deterioration is within a deterioration limit claim 2 , and ...

ADAPTIVE BLEED SCHEDULE IN A GAS TURBINE ENGINE

An aspect includes a system for a gas turbine engine. The system includes one or more bleeds of the gas turbine engine and a control system configured to check one or more activation conditions of a dirt rejection mode in the gas turbine engine. A bleed control schedule of the gas turbine engine is adjusted to extend a time to hold the one or more bleeds of the gas turbine engine partially open at a power setting above a threshold based on the one or more activation conditions. One or more deactivation conditions of the dirt rejection mode in the gas turbine engine are checked. The dirt rejection mode is deactivated to fully close the one or more bleeds based on the one or more deactivation conditions. 1. A system for a gas turbine engine , the system comprising:one or more bleeds of the gas turbine engine; and check one or more activation conditions of a dirt rejection mode in the gas turbine engine;', 'adjust a bleed control schedule of the gas turbine engine to extend a time to hold the one or more bleeds of the gas turbine engine partially open at a power setting above a threshold based on the one or more activation conditions;', 'check one or more deactivation conditions of the dirt rejection mode in the gas turbine engine; and', 'deactivate the dirt rejection mode to fully close the one or more bleeds based on the one or more deactivation conditions., 'a control system configured to2. The system of claim 1 , wherein the dirt rejection mode is activated based on meeting all of the one or more activation conditions claim 1 , and the dirt rejection mode is deactivated based on meeting at least one of the one or more deactivation conditions.3. The system of claim 1 , wherein the one or more activation conditions comprise detecting that the gas turbine engine is incorporated in an aircraft on the ground and an engine speed command of the gas turbine engine is less than a full maximum takeoff thrust setting with a thrust margin.4. The system of claim 3 , wherein the ...

AIR INTAKE HOOD FOR TURBINE INLET FILTER HOUSE

An air intake hood for channeling an incoming air flow downward in a filter house. The intake hood includes an inlet that is inclined. 1. An air intake hood extending from a vertical wall of a filter house for channeling an incoming air flow downward , the air intake hood comprising:an intake hood inlet for drawing intake air therethrough;an intake hood outlet configured for delivering the intake air into a filter house,wherein the intake hood inlet comprises an intake plane positioned at an inclined angle relative to the vertical wall.2. The air intake hood of claim 1 , further comprising a coalescer positioned across the intake hood inlet for removing moisture from the intake air claim 1 , wherein an axis of the coalescer is parallel with the intake plane.3. The air intake hood of claim 1 , wherein the inclined angle is about forty five degrees.4. The air intake hood of claim 1 , further comprising a deflector positioned downstream of the intake hood inlet for channeling the intake air through the intake hood outlet at a preselected direction.5. The air intake hood of claim 3 , wherein the deflector is positioned at about the inclined angle.6. The air intake hood of claim 5 , wherein the deflector is a detachable deflector.7. The air intake hood of claim 5 , wherein the deflector is formed to be integral with a top surface of the intake hood.8. A filter house comprising:a plurality of air intake hoods disposed on an exterior vertical wall of the filter house; anda plurality of filter elements disposed on an interior wall of the filter house,wherein the plurality of air intake hoods each comprise:an intake hood inlet for drawing intake air therethrough;an intake hood outlet configured for delivering the intake air into the filter house,wherein the intake hood inlet is positioned at an inclined angle relative to the vertical wall.9. The filter house of claim 8 , wherein the plurality of air intake hoods each further comprise a coalescer positioned across the intake ...

Control technologies for turbine engine with integrated inlet particle separator and infrared suppression system

A propulsion system includes a gas turbine engine, an inlet particle separator, an infrared suppression system, and an engine controller. The engine controller may be configured to determine an activation state of the inlet particle separator, adjust one or more engine operating parameters based on the activation state, and control the gas turbine engine based on the adjusted engine operating parameters. The engine operating parameters may be adjusted based on inlet flow, which is determined based on the activation state. The engine controller may be further configured to determine an activation state of the infrared suppression system, adjust one or more engine operating parameters based on the activation state, and control the gas turbine engine based on the adjusted engine operating parameters. The engine operating parameters may be adjusted based on backpressure, which is determined based on the activation state.

Air intake arrangement

An intake for channeling air flowing past a propeller to an inlet of an aircraft engine driving the propeller through a drive shaft comprising: a static cowling extending about an axis and which flares from an upstream end, an intake slot formed in the flared portion which bounds a passage to the inlet of the aircraft engine, the intake slot opening over an arc that extends less than 360 degrees of the circumference of the cowling and having an axially rearward edge that blends into the cowling through a curve having a vertex, wherein the vertex is radially inside a projected extension of the flared portion from an upstream portion of the flared cowling across the intake slot.

ADAPTABLE INERTIAL PARTICLE SEPARATOR

An adaptive inertial particle separation system may include an active configuration and a passive configuration. The system may comprise an air-intake duct including an outer wall spaced apart from a central axis, an inner wall located between the outer wall and the engine rotation axis, an intake passage defined in part by the inner wall and the outer wall, and a splitter located between the outer wall and the inner wall. The system may further include a sensor operatively connected to the air-intake duct and operative to initiate at least one of the active configuration and passive configuration. 1. A system for adaptive inertial particle separation and having an active configuration and a passive configuration , the system comprising:an air-intake duct configured to receive an intake flow, the air-intake duct including an outer wall spaced apart from a central axis, an inner wall located between the outer wall and the central axis, and an intake passage defined in part by the inner wall and the outer wall;a splitter located between the outer wall and the inner wall and including an outer splitter surface and an inner splitter surface, the inner splitter surface and the inner wall defining a compressor passage having a first area in the active configuration and a second area in the passive configuration, and the outer splitter surface and outer wall defining a scavenge passage in the active configuration; andan electrostatic generator configured to apply a charge to the intake flow and urge the intake flow toward the scavenge passage.2. The system of claim 1 , wherein the intake flow includes particulates and the electrostatic generator is configured to apply at least one of a positive charge and a negative charge to the intake flow to cluster the particulates and urge the clustered particulates to the scavenge passage.3. The system of claim 1 , wherein the intake flow includes an outer flow adjacent the outer wall and an inner flow adjacent the inner wall claim 1 ...

INLET BLEED HEAT CONTROL SYSTEM

The present application provides an inlet bleed heat control system for a compressor of a gas turbine engine. The inlet bleed heat control system provides an inlet bleed heat manifold and an ejector in communication with the inlet bleed heat manifold such that the ejector is in communication with a flow of compressor discharge air and a flow of ambient air. 1. An inlet bleed heat control system for a compressor of a gas turbine engine , comprising:an inlet bleed heat manifold; andan ejector in communication with the inlet bleed heat manifold;the ejector in communication with a flow of compressor discharge air and a flow of ambient air.2. The inlet bleed heat control system of claim 1 , wherein the ejector is in communication with a filter house line with the flow of ambient air.3. The inlet bleed heat control system of claim 2 , wherein the filter house line comprises a filter house line valve thereon.4. The inlet bleed heat control system of claim 1 , wherein the ejector is in communication with a compressor discharge line with the flow of compressor discharge air.5. The inlet bleed heat control system of claim 4 , wherein the compressor discharge line comprises a compressor discharge valve thereon.6. The inlet bleed heat control system of claim 5 , wherein the compressor discharge line comprises an ejector valve thereon.7. The inlet bleed heat control system of claim 1 , further comprising an ejector bypass line positioned between the compressor and the inlet bleed heat manifold.8. The inlet bleed heat control system of claim 7 , wherein the bypass line comprises a bypass valve thereon.9. The inlet bleed heat control system of claim 1 , wherein the inlet bleed heat manifold comprises a plurality of acoustic nozzles.10. The inlet bleed heat control system of claim 1 , further comprising a controller.11. The inlet bleed heat control system of claim 10 , wherein the controller comprises anti-icing signals.12. The inlet bleed heat control system of claim 10 , wherein ...

ADAPTIVE BLEED SCHEDULE IN A GAS TURBINE ENGINE

An aspect includes a system for a gas turbine engine. The system includes one or more bleeds of the gas turbine engine and a control system configured to check one or more activation conditions of a dirt rejection mode in the gas turbine engine. A bleed control schedule of the gas turbine engine is adjusted to extend a time to hold the one or more bleeds of the gas turbine engine partially open at a power setting above a threshold based on the one or more activation conditions. One or more deactivation conditions of the dirt rejection mode in the gas turbine engine are checked. The dirt rejection mode is deactivated to fully close the one or more bleeds based on the one or more deactivation conditions. 1. A system for a gas turbine engine , the system comprising:one or more bleeds of the gas turbine engine; and check one or more activation conditions of a dirt rejection mode in the gas turbine engine;', 'read a default bleed control schedule from the memory system as a bleed control schedule;', 'determine that both a dirt concentration is above a threshold and the gas turbine engine is within an operability limit;', 'in response to determining that both the dirt concentration is above a threshold and the gas turbine engine is within the operability limit, adjust the bleed control schedule of the gas turbine engine to extend a time to hold the one or more bleeds of the gas turbine engine partially open at a power setting above a threshold based on the one or more activation conditions;', 'check one or more deactivation conditions of the dirt rejection mode in the gas turbine engine; and', 'deactivate the dirt rejection mode to fully close the one or more bleeds based on the one or more deactivation conditions and restore the bleed control schedule of the gas turbine engine by updating the bleed control schedule with the default bleed control schedule from the memory system., 'a control system comprising processing circuitry and a memory system, the memory system ...

PARTICLE SEPARATORS FOR TURBOMACHINES AND METHOD OF OPERATING THE SAME

A particle separator includes a separator body in a primary fluid passageway of a machine. The primary fluid passageway includes one or more bleed holes through which a diverted portion of the fluid flowing in the primary fluid passageway toward a volume of the machine is diverted into an auxiliary flow passageway that bypasses the volume and directs the diverted portion of the fluid toward one or more other components of the machine. The separator body is coupled with the inner wall and/or outer wall of the primary fluid passageway. The separator body includes an upstream edge positioned to separate at least some particles carried by the fluid from the fluid as the diverted portion of the fluid bends around and flows over the at least one upstream edge of the separator body and into the auxiliary flow passageway. 1. A method comprising:establishing a fluid flow of particle-laden fluid in a primary fluid passageway of a machine that is defined by opposing first and second walls;filtering a first portion of the particle-laden fluid by passing the particle-laden fluid over an undulating separator body having one or more separator openings that extends over at least one bleed hole through the first wall, the first portion of the particle-laden fluid filtered by the first portion of the particle-laden fluid bending around an edge of the separator body at the one or more separator openings and flowing into an auxiliary fluid passageway, wherein a second portion of the fluid passes over the separator body without being filtered by the separator body; anddirecting the first portion of the fluid that is filtered to one or more downstream components of the machine.2. The method of claim 1 , wherein filtering the first portion of the fluid includes passing the fluid over an undulating shape of the separator body.3. The method of claim 1 , wherein the one or more components of the machine to which the first portion of the fluid is directed include one or more turbine blades.4. ...

MOBILE ELECTRIC POWER GENERATION FOR HYDRAULIC FRACTURING OF SUBSURFACE GEOLOGICAL FORMATIONS

Providing mobile electric power comprising a power generation transport configured to convert hydrocarbon fuel to electricity and an inlet and exhaust transport configured to: couple to at least one side of the power generation transport such that the inlet and exhaust transport is not connected to a top side of the power generation transport, provide ventilation air and combustion air to the power generation transport, collect exhaust air from the power generation transport, and filter the exhaust air. In another embodiment, a fracturing pump transport comprising a first pump configured to pressurize and pump fracturing fluid, a second pump configured to pressurize and pump the fracturing fluid, and a dual shaft electric motor comprises a shaft and configured to receive electric power from a power source and drive in parallel, both the first pump and the second pump with the shaft. 1. A system for providing mobile electric power , the system comprising:a gas turbine generator transport that comprises an inlet plenum and an exhaust collector; andan inlet and exhaust transport comprising an air inlet filter housing and an exhaust stack,wherein the inlet and exhaust transport is configured to couple to at least one side of the gas turbine generator transport such that the inlet plenum and the exhaust collector are not connected to the air inlet filter housing and the exhaust stack at a top side of the gas turbine generator transport.2. The system of claim 1 , wherein the inlet and exhaust transport comprises a hydraulic walking system used to position the inlet and exhaust transport at a predetermined distance for coupling to the gas turbine generator transport.3. The system of claim 1 , wherein the exhaust stack is mounted on its side on the inlet and exhaust transport in a transportation mode.4. The system of claim 1 , wherein at least a portion of the exhaust stack is rotated to a standing position on the inlet and exhaust transport in an operational mode.5. The ...

SYSTEM AND METHOD WITH INLET PARTICLE SEPARATOR

A turbine engine system includes an inlet particle separator receiving an inlet fluid flow and having a clean outlet for a first flow of substantially clean fluid, and a scavenge outlet for a second flow of scavenge fluid. A fluid pump communicates with the scavenge outlet. The flow of scavenge fluid through the fluid pump is selectively regulated. 1. A turbine engine system , comprising:an inlet particle separator having an inlet receiving an inlet fluid flow, a clean outlet receiving a first flow of substantially clean fluid, and a scavenge outlet receiving a second flow of scavenge fluid;a fluid pump in fluid communication with the scavenge outlet;an air flow control device regulating the flow of scavenge fluid through the fluid pump; anda controller coupled with the air flow control device for selectively adjusting the flow of scavenge fluid through the fluid pump.2. The turbine engine system of claim 1 , wherein the fluid pump comprises a blower.3. The turbine engine system of claim 2 , further comprising an accessory gearbox coupled with the blower for driving the blower.4. The turbine engine system of claim 2 , wherein the blower comprises a blower inlet in fluid communication with the scavenge outlet and a blower outlet claim 2 , and wherein the air flow control device is downstream of the blower inlet.5. The turbine engine system of claim 4 , wherein the blower outlet is in fluid communication with a duct claim 4 , and wherein the air flow control device regulates the flow of scavenge fluid through the duct.6. The turbine engine system of claim 1 , wherein the air flow control device comprises a throttle.7. The turbine engine system of claim 6 , wherein the throttle comprises a butterfly valve claim 6 , a globe valve claim 6 , or a diaphragm valve.8. The turbine engine system of claim 6 , further comprising a flow path comprising at least the scavenge outlet and the fluid pump claim 6 , and wherein the throttle comprises an adjustable body within the flow ...

GAS TURBINE ENGINE INTAKE DUCT

A gas turbine engine intake duct having an internal duct surface comprising a main region having a particular finish and a secondary region having a different finish. 1. A gas turbine engine intake duct having an internal duct surface comprising a main region having a particular finish and a secondary region having a different finish.2. A gas turbine engine intake duct according to where the different finish of the secondary region is arranged to alter the direction in which debris particles will bounce from that surface by comparison with particle bounce directions that would occur if the second region had the same finish as the main region.3. A gas turbine engine intake duct according to where the main region and secondary region comprise materials having different coefficients of restitution.4. A gas turbine engine intake duct according to where the secondary region has a lower coefficient of restitution than the main region.5. A gas turbine engine intake duct according to where the main region is substantially smooth and the secondary region comprises variations in surface profile.6. A gas turbine engine intake duct according to where the secondary region is located to encompass an intersection with the internal duct surface of a substantially ballistic path travelled by a debris particle claim 1 , the debris particle entering an inlet to the intake duct on a path parallel to a conventional fluid stream direction that would enter the inlet in use of the gas turbine engine.7. A gas turbine engine intake duct according to where the substantially ballistic path incorporates at least one previous intersection with the internal duct surface and bounce therefrom.8. A gas turbine engine intake duct according to where there are provided one or more additional secondary regions.9. A gas turbine engine intake duct according to where the intake duct comprises an inlet duct which bifurcates into a core duct and a scavenge duct.10. A gas turbine engine intake duct according ...

System for reducing inlet air temperature of a device

The present embodiments disclose a system ( 100 ) for reducing inlet air temperature of a device, comprising: a fogging system that provides air cooling, wherein the fogging system comprises at least one low pressure atomiser ( 110 ).

Hydrophobic filtration of tempering air

A gas turbine system may include an exhaust gas processing system configured to process exhaust gas received from a gas turbine engine of the system. An exhaust path of the exhaust processing system is configured to flow the exhaust gas through the exhaust processing system. A tempering air system of the exhaust processing system is configured to introduce tempering air into the exhaust path to cool the exhaust gas. The tempering air system includes a tempering air pathway extending from an air inlet of the tempering air system to a tempering air outlet where tempering air is introduced from the tempering air system and into the exhaust path. A filter system of the tempering air system has a hydrophobic filter positioned along the tempering air pathway, the hydrophobic filter being configured to remove hygroscopic and deliquescent materials from the air flowing through the tempering air pathway.

MOBILE GAS TURBINE INLET AIR CONDITIONING SYSTEM AND ASSOCIATED METHODS

A system, as well as associated methods, for increasing the efficiency of a gas turbine including an inlet assembly and a compressor may include a housing configured to channel airstream towards the inlet assembly, an air treatment module positioned at a proximal end the housing, and at least one air conditioning module mounted downstream of the air treatment module for adjusting the temperature of the airstream entering the compressor. The air treatment module may include a plurality of inlet air filters and at least one blower configured to pressurize the air entering the air treatment module. 1. An air treatment system to increase the efficiency of a gas turbine comprising an inlet assembly and a compressor , the inlet assembly located upstream of the compressor and forming an input side of the gas turbine , the air treatment system comprising:a housing positioned to channel an airstream towards the inlet assembly, the housing positioned upstream of the input side; and one or more inlet air filters to provide fluid flow to a first internal chamber, and', 'one or more blowers mounted in the first internal chamber and providing fluid flow to an interior of the housing via at least one outlet of the first internal chamber, the one or more blowers configured to pressurize the air entering the air treatment module, and', 'one or more air conditioning modules mounted downstream of the air treatment module to decrease the temperature of the airstream entering the compressor, such that the airstream enters the one or more air conditioning modules at a first temperature and exits the one or more air conditioning modules at a second temperature lower than the first temperature., 'an air treatment module positioned at a proximal end of the housing, the air treatment module comprising2. The air treatment system of claim 1 , wherein the one or more air conditioning modules comprise at least one chiller module.3. The air treatment system of claim 2 , wherein the at least one ...

Recuperated Gas Turbine Engine

A gas turbine engine that includes a compressor, a turbine, a heat exchanger, and a combustor. The compressor is mounted on a rotating shaft with at least one rotor with an inlet and an outlet, and at least one diffuser downstream from each rotor. The turbine includes at least one stator, and at least one rotor with an inlet and outlet located downstream of each stator, and mounted on the rotating shaft as the at least one of the compressor rotors. The inlet of the compressor rotor faces toward the outlet of the turbine rotor. The heat exchanger is configured to preheat the compressed air leaving the compressor by transferring heat from the turbine exhaust. The combustor can be configured for mixing fuel with the compressed air, either upstream or downstream from the heat exchanger, and further configured for igniting the preheated fuel/air mixture located downstream from the heat exchanger. 1. A gas turbine engine , comprising:a compressor comprising at least one rotor with an inlet and an outlet, mounted on a rotating shaft, configured for accelerating and compressing air, and at least one diffuser downstream from each rotor, configured for decelerating the air and converting its kinetic energy to additional static pressure;a turbine comprising at least one stator configured to expand and accelerate heated, compressed air and combustion products in a swirling motion, and at least one rotor with an inlet and outlet located downstream of each stator, mounted on the rotating shaft as the at least one of the compressor rotors, and configured to convert the kinetic energy of the swirling air and combustion products to useful shaft work, wherein the compressor rotor inlet is axially closer to the turbine than the compressor rotor outlet, and the turbine rotor outlet is axially closer to the compressor than the turbine rotor inlet;a heat exchanger configured to preheat the compressed air leaving the compressor by transferring heat from the turbine exhaust; anda combustor ...

ELECTROSTATIC CHARGE CONTROL INLET PARTICLE SEPARATOR SYSTEM

An inlet particle separator system for an engine includes an inner flowpath section, an outer flowpath section, a splitter, a first electrostatic discharge device, and a second electrostatic discharge device. The outer flowpath section surrounds at least a portion of the inner flowpath section and is spaced apart therefrom to define a passageway having an air inlet. The splitter is disposed downstream of the air inlet and extends into the passageway to divide the passageway into a scavenge flow path and an engine flow path. The first electrostatic charge device is disposed between the air inlet and the splitter and is electrostatically charged to a first polarity. The second electrostatic charge device is disposed downstream of the first electrostatic charge device and is electrostatically charged to a second polarity that is opposite to the first polarity. 1. An inlet particle separator system for an engine , comprising:an inner flowpath section;an outer flowpath section surrounding at least a portion of the inner flowpath section and spaced apart therefrom to define a passageway, the passageway having an air inlet;a splitter disposed downstream of the air inlet and extending into the passageway to divide the passageway into a scavenge flow path and an engine flow path;a first electrostatic charge device disposed between the air inlet and the splitter, the first electrostatic charge device electrostatically charged to a first polarity to thereby impart an electrostatic charge of a first polarity to at least a portion of particulate entering the air inlet; anda second electrostatic charge device disposed downstream of the first electrostatic charge device and electrostatically charged to a second polarity that is opposite to the first polarity, whereby particulate charged to the first polarity is attracted toward the second polarity.2. The system of claim 1 , further comprising:a third electrostatic charge device disposed between the air inlet and the splitter and ...

ENGINE INTAKE ASSEMBLY WITH SELECTOR VALVE

An engine assembly including an engine core including at least one internal combustion engine each including a rotor sealingly and rotationally received within a respective internal cavity to provide rotating chambers of variable volume in the respective internal cavity, a compressor having an outlet in fluid communication with an inlet of the engine core, a first intake conduit in fluid communication with an inlet of the compressor and with a first source of air, a second intake conduit in fluid communication with the inlet of the compressor and with a second source of air warmer than the first source of air, and a selector valve configurable to selectively open and close at least the fluid communication between the inlet of the compressor and the first intake conduit. A method of supplying air to a compressor is also discussed. 1. An engine assembly comprising:an engine core including at least one internal combustion engine each including a rotor sealingly and rotationally received within a respective internal cavity to provide rotating chambers of variable volume in the respective internal cavity;a compressor having an outlet in fluid communication with an inlet of the engine core;a first intake conduit in fluid communication with an inlet of the compressor and with a first source of air;a second intake conduit in fluid communication with the inlet of the compressor and with a second source of air warmer than the first source of air; anda selector valve configurable to selectively open and close at least the fluid communication between the inlet of the compressor and the first intake conduit.2. The engine assembly as defined in claim 1 , wherein the selector valve closes the fluid communication between the inlet of the compressor and the second intake conduit when the fluid communication between the inlet of the compressor and the first intake conduit is open and opens the fluid communication between the inlet of the compressor and the second intake conduit when ...

INTERGRATED ENVIRONMENTAL CONTROL SYSTEM MANIFOLD

A compressor intermediate case for a gas turbine engine includes a plurality of intermediate case struts joining the compressor intermediate case to an inner engine structure. Each strut of the plurality of intermediate case struts includes a leading edge. A turning scoop is disposed at the leading edge of each strut of the plurality of intermediate case struts. A plurality of diffusers extends radially outwardly from the compressor intermediate case so that each diffuser of the plurality of diffusers engages with a corresponding turning scoop. A substantially annular structural fire wall extends radially outwardly from the compressor intermediate case. An environmental control system manifold is disposed on the compressor intermediate case. The environmental control system manifold includes an exit port. 1. An intermediate case for a gas turbine engine compressor , the intermediate case comprising:a plurality of intermediate case struts joining the intermediate case to an inner engine structure, each strut of the plurality of intermediate case struts including a leading edge;a structural fire wall extending radially and outwardly from the intermediate case;a turning scoop being disposed at the leading edge of each strut of the plurality of intermediate case struts;a plurality of diffusers extending radially outwardly from the intermediate case, each diffuser of the plurality of diffusers being associated with a corresponding turning scoop; andan asymmetrical environmental control system manifold being disposed on the intermediate case, the asymmetrical environmental control system manifold being associated with the plurality of diffusers, the asymmetrical environmental control system manifold having a first collection wall and a second collection wall, wherein a downstream extension of the second collection wall tapers such that the second collection wall extends a first distance from the structural fire wall adjacent to an exit port of the asymmetrical ...

COMBUSTION CHAMBER WITH PARTICLE SEPARATOR

A combustion chamber () comprising a wall at least partially defining a combustion zone and having a first surface () facing away from the combustion zone and a second surface () facing the combustion zone, the wall having at least one effusion cooling aperture () extending there-through from the first surface to the second surface, the effusion cooling aperture having an inlet in the first surface and an outlet in the second surface, the first surface having a particle separator () at least partially located upstream of the inlet of the effusion cooling aperture, the particle separator projecting away from the first surface and away from the combustion zone. 1. A combustion chamber comprising a wall at least partially defining a combustion zone , the wall having an upstream end and a downstream end , the wall having a first surface facing away from the combustion zone and a second surface facing the combustion zone , the wall having at least one effusion cooling aperture extending there-through from the first surface to the second surface , the effusion cooling aperture having an inlet in the first surface and an outlet in the second surface , the first surface having a particle separator at least partially located upstream of the inlet of the effusion cooling aperture , the particle separator projecting away from the first surface and away from the combustion zone , the particle separator having a distal end remote from the inlet of the effusion cooling aperture and a proximal end adjacent to the inlet of the effusion cooling aperture , the particle separator having a maximum height above the first surface at a location spaced from the proximal end , the particle separator increasing in height in a direction from the distal end towards the proximal end to the maximum height.2. A combustion chamber as claimed in claim 1 , wherein the particle separator is triangular in cross-section.3. A combustion chamber as claimed in claim 1 , wherein the particle separator has ...

System and method for injecting tempering air for hot scr catalyst

A gas turbine system includes a gas turbine engine, an exhaust processing system disposed downstream of and fluidly coupled to the gas turbine engine, and an air delivery system that may supply treated air to the gas turbine engine and the exhaust processing system. The air delivery system includes a main air duct fluidly coupled to the gas turbine engine and that may supply a first portion of the treated air to the gas turbine engine, an auxiliary air duct fluidly coupled to the main air duct and the exhaust processing system and that may supply a second portion of the treated air to the exhaust processing system, and an air treatment unit fluidly coupled to the main air duct and that may generate the treated air.

AIR FILTRATION ASSEMBLIES FOR GAS TURBINE SYSTEMS AND METHODS FOR FILTERING INTAKE AIR IN GAS TURBINE SYSTEMS

Air filtration assemblies configured to provide instant detection of particles and/or improve particle filtration are disclosed. The assemblies may include an air inlet duct in fluid communication with a compressor of a gas turbine system. The air inlet duct may include an inlet for receiving intake air including intake air particles, and an outlet positioned opposite the inlet. The assembly may also include a plurality of vane filters at the inlet, an array of fabric filters positioned in the air inlet duct, downstream of the vane filters, and a silencer assembly positioned in the air inlet duct, downstream of the fabric filters. Additionally, the assembly may include an electrostatic component positioned in the air inlet duct, downstream of the fabric filters. The electrostatic component may be configured to charge the intake air particles that pass through the vane filters and the fabric filters. 1. An air filtration assembly for a gas turbine system , the air filtration assembly comprising: an inlet for receiving intake air including intake air particles; and', 'an outlet positioned opposite the inlet;, 'an air inlet duct in fluid communication with a compressor of the gas turbine system, the air inlet duct includinga plurality of vane filters at the inlet of the air inlet duct;an array of fabric filters positioned in the air inlet duct, downstream of the plurality of vane filters;a silencer assembly positioned in the air inlet duct, downstream of the array of fabric filters, the silencer assembly positioned adjacent the outlet of the inlet duct; andan electrostatic component positioned in the air inlet duct, downstream of the array of fabric filters, the electrostatic component configured to charge the intake air particles that pass through the plurality of vane filters and the array of fabric filters.2. The air filtration assembly of claim 1 , wherein the electrostatic component includes one of:a matrix of ionizers spanning over a front cross-sectional area of ...

INLET PARTICLE SEPARATOR FOR A TURBINE ENGINE

A method and apparatus for separating particles from an inlet airflow of a turbine engine has a centerbody with a radially outer scavenge conduit. The inlet airflow has entrained particulate matter, which can impact an impact surface defining part of the centerbody. The impact surface can be disposed at an angle or have a low coefficient of restitution to reduce the velocity of the incoming particulate matter. The particulate matter is radially diverted radially outward through the scavenge conduit, unable to make a turn defined by the shape of the centerbody. 1. A method of separating particles from an inlet airflow of a turbine engine having a centerbody and defining an engine centerline , the method comprising:impacting at least a portion of particulate matter entrained in the inlet airflow against an impact surface;after impacting, turning the airflow about the centerbody; andradially diverting a portion of the airflow relative to the engine centerline during the turning to form a scavenge flow containing inertially bound particles incapable of making the turn.2. The method of wherein impacting the particulate matter entrained in the inlet airflow comprises impacting the at least a portion of the particulate matter entrained in the inlet airflow against an impact surface that forms a forward angle of 90 degrees or less to one of the engine centerline and an inlet airflow streamline.3. The method of wherein the impact surface forms a forward angle of 90 degrees or less to both of the engine centerline and the inlet airflow streamline.4. The method of wherein the impact surface forms an acute forward angle relative to at least one of the engine centerline and the inlet airflow streamline.5. The method of further comprising diverting the scavenge flow from the airflow at an apex of the turn.6. The method of wherein the airflow velocity is about constant during the turning.7. The method of wherein the turning the airflow is through at least 120 degrees relative to ...

Asymmetric inlet particle separator system

An asymmetric inlet particle separator system (AIPS) includes a bifurcated duct system that defines an inlet for receiving inlet air. The bifurcated duct system includes a core air channel and a scavenge air channel and is configured to separate the inlet air into core air and scavenge air. The scavenge air channel includes a first plurality of turning vanes configured to turn the scavenge air in a first direction and a second plurality of turning vanes configured to turn the scavenge air in a second direction. The AIPS also includes an asymmetric scroll coupled to the scavenge air channel. The asymmetric scroll includes a first arm having a first arm length and a second arm having a second arm length that is different than the first arm length.

BYPASS VALVE SYSTEM STATE INDICATION

A fluid system may comprise a fluid passage comprising a passage inlet and a passage outlet, through which fluid may flow by entering the passage inlet as an inlet flow and exiting the passage outlet as an outlet flow; a bypass valve comprising a bypass inlet and a bypass outlet, the bypass inlet being in fluid communication with the passage inlet, wherein the bypass valve further comprises a piston coupled to a spring; and a position sensor coupled to the bypass valve and configured to detect a position of the piston in the bypass valve. The spring may retain the piston in a rest position, and the spring and the piston may be configured to block the fluid from passing through the bypass outlet in response to the inlet flow exerting a pressure below a bypass pressure threshold. 1. A fluid system , comprising:a fluid passage comprising a passage inlet and a passage outlet, wherein the fluid passage is configured to allow a fluid to pass through the fluid passage by entering the passage inlet as an inlet flow and exiting the passage outlet as an outlet flow;a bypass valve comprising a bypass inlet and a bypass outlet, the bypass inlet being in fluid communication with the passage inlet, wherein the bypass valve further comprises a piston coupled to a spring, wherein the spring retains the piston in a rest position, and the spring and the piston are configured to block the fluid from passing through the bypass outlet in response to the inlet flow exerting a pressure below a bypass pressure threshold; anda position sensor coupled to the bypass valve and configured to detect a position of the piston in the bypass valve.2. The fluid system of claim 1 , wherein the fluid passage is at least one of an oil filter claim 1 , a fuel filter claim 1 , or an air filter.3. The fluid system of claim 1 , wherein the fluid passage is a heat exchanger.4. The fluid system of claim 1 , wherein the piston is in the rest position in the bypass outlet claim 1 , wherein the bypass outlet ...

DEVICES AND METHODS FOR ALIGNING FILTERS IN A HOLDING FRAME

A filtration system for a gas turbine engine is provided. The filtration system may include a holding frame with a positioning element extending therefrom and a filter element for mounting within the holding frame. The frame of the filter element may include a positioning slot therein such that the positioning element extends into the positioning slot when the filter element is mounted within the holding frame. 1. A filter element for use with a filtration system , wherein the filtration system includes a rectangular holding frame defining a holding frame plane , the holding frame having a clamping assembly comprising a positioning element extending a projection depth in the holding frame plane , the clamping assembly further comprising a clamp member , the filter element comprising:a filter frame, wherein the filter frame includes a key edge having a positioning notch having a first depth and a first width wherein the positioning notch is sized and positioned to receive the positioning element with the filter element adapted for interfitting use with the rectangular holding frame; anda filter media coupled to the filter frame,wherein the filter frame comprises a rectangular shape.2. The filter element of claim 1 , wherein the filter frame includes a second positioning notch having a second depth and a second width claim 1 , at least one of the second depth and the second width being different than the first depth and the first width claim 1 , respectively claim 1 , so as to provide a keying configuration.3. The filter element of claim 1 , wherein the filter media comprises a mini-pleat filter with a plurality of pleats therein or a bag filter with a plurality of pockets therein.4. The filter element of claim 1 , wherein the filter frame comprises a rectangular gasket positioned inwardly of the positioning notch.5. The filter element of claim 1 , wherein the gasket is contoured around the positioning notch.6. The filter element of claim 5 , wherein the gasket is ...

INERTIAL PARTICLE SEPARATOR FOR ENGINE INLET

An inertial particle separator for an aircraft engine inlet, including inlet, intermediate and bypass ducts. The intermediate duct extends generally transversally from the inlet duct to the engine inlet, and communicates with the inlet duct adjacent its downstream end. The bypass duct extends downstream from the inlet duct and intermediate duct, and defines an outlet communicating with the environment of the engine. A wall of the intermediate duct intersects a wall of the inlet duct on an engine side of the wall of the inlet duct. The engine side of the wall of the inlet duct defines an engine-side inlet air flow line of the inertial particle separator. A wall of the bypass duct intersects the wall of the intermediate duct closer to a central axis of the engine than an extension of the engine-side inlet air flow line into the bypass duct. 1. An aircraft engine having an inertial particle separator communicating with an engine inlet of the aircraft engine , the inertial particle separator comprising:an inlet duct defining an intake communicating with an environment of the engine;an intermediate duct extending generally transversally from the inlet duct to the engine inlet, the intermediate duct communicating with the inlet duct adjacent a downstream end of the inlet duct; anda bypass duct in fluid communication with and extending downstream from the inlet duct and intermediate duct, the bypass duct defining an outlet communicating with the environment of the engine;wherein a wall of the intermediate duct intersects a wall of the inlet duct on an engine side of the wall of the inlet duct, the engine side of the wall of the inlet duct defining an engine-side inlet air flow line of the inertial particle separator, a wall of the bypass duct intersecting the wall of the intermediate duct closer to the a central axis of the engine than an extension of the engine-side inlet air flow line into the bypass duct.2. The aircraft engine as defined in claim 1 , wherein a central ...

FOLDABLE RAM AIR INLET FILTER

A filtering assembly that receives an inlet air includes a modulation panel subassembly, an air filter subassembly downstream of the modulation panel subassembly, wherein the air filter subassembly is configured to discharge the inlet air from the filtering assembly, and an arm subassembly configured to move the modulation panel subassembly and to move the air filter subassembly. The air filter subassembly moves into and out of a flow of the inlet air. 1. A filtering assembly that receives an inlet air , comprising:a modulation panel subassembly;an air filter subassembly downstream of the modulation panel subassembly;wherein the air filter subassembly is configured to discharge the inlet air from the filtering assembly; andan arm subassembly configured to move the modulation panel subassembly and to move the air filter subassembly;whereby the air filter subassembly moves into and out of a flow of the inlet air.2. The assembly of claim 1 , further comprising an actuator directly connected to the arm subassembly.3. The assembly of claim 1 , further comprising an actuator indirectly connected to the air filter subassembly.4. The assembly claim 1 , wherein the modulation panel subassembly is configured to articulate.5. The assembly of claim 1 , wherein the assembly is configured to direct the inlet air to a component downstream of the assembly claim 1 , wherein the component is susceptible to damage from particulates in the inlet air.6. The assembly of claim 1 , wherein the air filter subassembly is configured to move between a folded position and an extended position.7. A filtering assembly that receives an inlet air claim 1 , comprising:an air filter subassembly downstream of an inlet air side of the filtering assembly; andan arm subassembly configured to move the air filter subassembly between a folded position and an extended position.8. The assembly of claim 7 , further comprising a modulation panel subassembly configured to receive the inlet air at the inlet air ...

FILTRATION SYSTEM AND METHOD FOR CLEANING THE INTAKE AIR OF A GAS TURBINE

In a filtration system, in particular for cleaning the intake air of a gas turbine, including a flow channel surrounded by walls with an inflow opening and an outflow opening, a partition wall with at least two openings between a dirty side and a clean side which is positioned between the inflow opening and the outflow opening and limited by the walls of the flow channel, and at least two filters for purifying a flowing fluid. At least one filter is installed at a first opening on the dirty side of the partition wall and at least one filter at a second opening on the clean side of the partition wall. 1110142146148108146148142110100106156110100106156108100106156108. A filtration system for the cleaning of an intake air of a gas turbine , with a flow channel () surrounded by walls () with an inflow opening () and an outflow opening () , a partition wall () positioned between the inflow opening () and the outflow opening () and limited by the walls () of the flow channel () with at least first and second filters ( , , ) for cleaning a fluid that flows through the flow channel () , at least the first filter ( , , ) constitutes one single mounting unit that is mounted on the partition wall () and at least the second filter ( , , ) also constitutes one single mounting unit is mounted on the partition wall () , wherein{'b': 100', '106', '156', '100', '106', '156, 'the second filter (, , ) is sealed directly to the first filter (, , ).'}2108100106156108. The filtration system of claim 1 , wherein the partition wall () includes at least one mounting beam and the at least two filters ( claim 1 , claim 1 , ) are sealed to the at least one mounting beam of the partition wall ().3100106156120. The filtration system of claim 2 , wherein the at least two filters ( claim 2 , claim 2 , ) are sealed () by a compressible gasket.4100106156100106156158100106156. The filtration system of claim 3 , wherein the gasket of the first filter ( claim 3 , claim 3 , ) protrudes outward from the ...

Inlet air filter arrangement, inlet air filter cartridge, and equipment for supporting inlet air filter cartridges for a gas turbine or a combustion turbine

An inlet air filter arrangement for a gas turbine or a combustion turbine includes a housing with an inlet side and an outlet side separated by a planar tubesheet including multiple tubesheet openings. Each multiple cylindrical filter cartridge includes a symmetry axis, an open end, and a closed end. A connection assembly for each of the multiple cylindrical filter cartridges seals the open end of the cylindrical filter cartridge to the tubesheet around one of the tubesheet openings. The connection assembly includes a mainly cylindrical guide sleeve including a symmetry axis, a shell with a cylindrical external surface, an inner end attached around the tubesheet opening and an outer end at the inlet side of the housing. The shell is provided with at least two slots extending mainly helically from the outer end towards the inner end. A collar attaches to the open end of the cylindrical filter cartridge.

Turbine engine lubrication system with wash flow filter

An assembly is provided for a turbine engine. This turbine engine assembly includes a turbine engine component and a lubrication system. The lubrication system directs lubricant through the turbine engine component. The lubrication system includes a wash flow filter.

VEHICLE PROVIDED, AT THE INTAKE, WITH AN AIR FILTER PROVIDED WITH A HEATING DEVICE

A vehicle provided with an engine, at least one air intake opening through which the engine takes in the external air needed to operate, and an air filter, which is arranged in the area of the air intake opening; the air filter has: at least one wave-shaped filtering material element; an outer reinforcement mesh; an inner reinforcement mesh; and a heating device, which is electrically connected to a group of electrified wires of the outer reinforcement mesh and is designed to cause an electric current to flow through the electrified wires, so as to generate heat, due to Joule effect, on the inside of the outer reinforcement mesh. 1. A vehicle provided with an engine , at least one air intake opening through which the engine takes in the external air needed to operate , and an air filter , which is arranged in the area of the air intake opening;the air filter comprises:at least one wave-shaped filtering material element;an outer reinforcement mesh, which is pleated, is made up of a plurality of weft wires and a plurality of warp wires, and rests against an outer surface of the filtering material element, through which the air taken in enters so as to flow through the filtering material element;an inner reinforcement mesh, which is pleated, is made up of a plurality of weft wires and a plurality of warp wires, and rests against an inner surface of the filtering material element, which is opposite the outer surface; anda heating device, which is designed to heat the filtering material element;wherein;the heating device is electrically connected to a group of electrified wires of the outer reinforcement mesh and is designed to cause an electric current to flow through the electrified wires, so as to generate heat, due to Joule effect, on the inside of the outer reinforcement mesh; andthe electrified wires are externally coated with a coating made of an electrically insulating material.2. The vehicle according to claim 1 , wherein the heating device is designed to cause ...

FILTER ASSEMBLY INCLUDING PLEAT TIP SHAPES

Solutions for efficiently filtering air for a machine are disclosed. In one embodiment, a filter element for a filter assembly of a rotary machine is provided. The filter element includes: a first set of pleats, each pleat including a first tip radius and a first spacing; and a second set of pleats, each pleat including a second tip radius and a second spacing, wherein the first and second set of pleats are positioned upon a continuous filter media. 1. A filter element for a filter assembly , the filter element comprising:a first set of pleats, each pleat including a first tip radius and a first spacing, wherein the first tip radius and the first spacing are at a circumference of the filter element; anda second set of pleats, each pleat including a second tip radius and a second spacing wherein the second tip radius and the second spacing, are at the circumference of the filter element,wherein the first and second set of pleats are positioned upon a continuous filter media, wherein the first tip radius is different than the second tip radius, and wherein the first spacing is larger than the second spacing.23-. (canceled)4. The filter element of claim 1 , wherein a pleat height for each pleat of the first set of pleats and a pleat height for each pleat of the second set of pleats is substantially equal.5. The filter element of claim 1 , further comprising a third set of pleats claim 1 , each pleat including a third tip radius and a third spacing.6. The filter element of claim 5 , wherein the third tip radius is different than the second tip radius.7. The filter element of claim 6 , wherein the second spacing is larger than the third spacing.8. A system comprising:a gas turbine; and a first set of pleats, each pleat including a first tip radius and a first spacing, wherein the first tip radius and the first spacing are at a circumference of the filter assembly; and', 'a second set of pleats, each pleat including a second tip radius and a second spacing wherein the ...

Driven cavity particle separator

A particle separator includes a housing defining an inlet and an outlet. A flow stream is directed from the inlet to the outlet. A number of dividers are disposed in the housing and separate flow channels from each other. The flow channels extend from the inlet to the outlet. The dividers each have a profile so that the flow channels follow the profile. The dividers each include a plurality of cavities that open to each of the flow channels and that have blind ends. The cavities each have an aspect ratio greater than one, and are configured to collect particles from the flow stream.

AIR-INLET PARTICLE SEPARATOR HAVING A BLEED SURFACE

An air-inlet particle separator includes an outer wall, an inner wall, and a splitter. The splitter cooperates with the outer wall and the inner wall to separate particles entrained in an inlet flow moving through the air-inlet particle separator to provide a clean flow of air for a compressor section of a gas turbine engine. 1. An air-inlet particle separator for use with a gas turbine engine , the air-inlet particle separator comprisingan inner wall arranged circumferentially about an axis of the air-inlet particle separator,an outer wall arranged circumferentially about the inner wall to define an air-inlet passageway adapted to receive a mixture of air and particles suspended in the air and the outer wall formed to include a plurality of apertures that extend through the outer wall to block the mixture of air and particles from forming vortices, anda splitter located radially between the outer wall and the inner wall and configured to separate the mixture of air and particles into a clean flow substantially free of particles and a dirty flow containing the particles, the splitter and the inner wall define an engine channel arranged to receive the clean flow, and the splitter and the outer wall define a scavenge channel arranged to receive the dirty flow,wherein the outer wall is configured to change shape selectively from an operating arrangement to a cleaning arrangement to cause particles attached to the outer wall and particles plugging the plurality of apertures to separate from the outer wall and move into the scavenge channel to clean the outer wall.2. The air-inlet particle separator of claim 1 , wherein the outer wall comprises bimetallic materials configured to change shape in response to electric energy being applied to the bimetallic materials included in the outer wall.3. The air-inlet particle separator of claim 1 , further comprising an inflatable bladder arranged adjacent the outer wall and configured to inflate and deflate to change the outer ...

MULTI-CHANNEL PARTICLE SEPARATOR

A multi-channel particle separator includes a plurality of vanes. Each vane is spaced apart from at least one other adjacent vane to define a flow channel, and includes a leading edge, a trailing edge, a first side wall, a second sidewall, and a splitter. The first side wall extends between the leading edge and the trailing edge. The second side wall is spaced apart from the first side wall and extends from the leading edge toward the trailing edge. The splitter may be rotationally coupled to the trailing edge and extend toward the leading edge. The splitter is spaced apart from the first side wall to define a scavenge volume and is rotatable between an extended position and a retracted position. The vanes may also or instead be coupled to a ring-shaped structure. 1. A multi-channel particle separator , comprising: a leading edge and a trailing edge,', 'a first side wall extending between the leading edge and the trailing edge;', 'a second side wall spaced apart from the first side wall, the second side wall extending from the leading edge toward the trailing edge, and', 'a splitter rotationally coupled to the trailing edge and extending toward the leading edge, the splitter spaced apart from the first side wall to define a scavenge volume and rotatable between (i) an extended position, in which the splitter is spaced apart from the second side wall to place the scavenge volume in fluid communication with the flow channel, and (ii) a retracted position, in which the splitter engages the second side wall to fluidly isolate the scavenge volume from the flow channel., 'a plurality of vanes, each vane spaced apart from at least one other adjacent vane to define a flow channel, each vane comprising2. The multi-channel particle separator of claim 1 , further comprising:at least one actuator coupled to each splitter, the at least one actuator adapted to receive actuator control signals and configured, in response thereto, to move each splitter to either the extended ...

FLUID INTAKE

A fluid intake including first and second ducts and a particle separation spinner defining an interface between the first and second ducts is disclosed. Spinner includes flow passages passing from first duct side of the spinner to second duct side of the spinner and splitter bodies separating the flow passages. Flow passages and splitter bodies are arranged in thread-like screw manner about spinner. In use, the spinner is spun about an axis of rotation, axis and direction of rotation being such that, from static frame of reference with respect to first duct, splitter bodies and flow passages have a component of movement towards a main travel direction of a fluid flow incident towards spinner from first duct. Splitter bodies are arranged such that they oblige fluid in the fluid flow to follow a convoluted path if it is to pass from first duct to second duct via the flow passages. 1. A fluid intake comprising a first duct , a second duct and a particle separation spinner defining an interface between the first duct and the second duct , the spinner comprising flow passages passing from a first duct side of the spinner to a second duct side of the spinner and splitter bodies separating the flow passages , the flow passages and splitter bodies being arranged in a thread-like screw manner about the spinner and where further , in use , the spinner is spun about an axis of rotation , the axis and direction of rotation being such that , from a static frame of reference with respect to the first duct , the splitter bodies and flow passages have a component of movement towards a main travel direction of a fluid flow incident towards the spinner from the first duct , the splitter bodies being arranged such that they oblige fluid in the fluid flow to follow a convoluted path if it is to pass from the first duct to the second duct via the flow passages.2. A fluid intake according to where the splitter bodies are arranged to conceal the flow passages from the main travel ...

FILTRATION SYSTEM AND METHOD FOR CLEANING THE INTAKE AIR OF A GAS TURBINE

In a filtration system, in particular for cleaning the intake air of a gas turbine, including a flow channel surrounded by walls with an inflow opening and an outflow opening, a partition wall with at least two openings between a dirty side and a clean side which is positioned between the inflow opening and the outflow opening and limited by the walls of the flow channel, and at least two filters for purifying a flowing fluid. At least one filter is installed at a first opening on the dirty side of the partition wall and at least one filter at a second opening on the clean side of the partition wall. 1110142146148108146148142110100106156110100106156108100106156108. A filtration system for cleaning intake air of a gas turbine , with a flow channel () surrounded by walls () with an inflow opening () and an outflow opening () , a partition wall () positioned between the inflow opening () and the outflow opening () and limited by the walls () of the flow channel () with at least two filters ( , , ) for the cleaning a fluid that flows through the flow channel () , wherein at least one first filter ( , , ) , which constitutes one single mounting unit , is mounted on the partition wall () and at least one second filter ( , , ) which again constitutes one single mounting unit is mounted on the partition wall () , wherein{'b': 100', '106', '156', '100', '106', '156', '100', '106', '156', '108, 'the second filter (, , ) is lying beside the first filter (, , ) and the first and the second filters (, , ) overlap at least partially in one direction largely vertically to the partition wall ().'}2. The filtration system of claim 1 , wherein{'b': 118', '100', '106', '156', '108', '108, 'an area in which frames () of the first and the second filters (, , ) overlap in one direction largely vertically to the partition wall () amounts to at least 5% of an overall projected area of filtration at the partition wall ().'}3. The filtration system of claim 2 , wherein{'b': 100', '106', '156 ...

INDUCER ASSEMBLY FOR A TURBINE ENGINE

A turbine engine having an inducer assembly. The inducer assembly includes a centrifugal separator fluidly coupled to an inducer with an inducer inlet and an inducer outlet. The centrifugal separator includes a body, an angular velocity increaser to form a concentrated-particle stream and a reduced-particle stream, a flow splitter, and an exit conduit fluidly coupled to the body to receive the reduced-particle stream and define a separator outlet. 138-. (canceled)39. An inducer assembly for a turbine engine defining an engine centerline and having a compressor section , a combustion section , and a turbine section , the inducer assembly comprising:an inducer comprising a flow passage; and a body defining a body centerline and having a wall defining a through passage with a passage inlet, wherein the passage inlet is fluidly coupled to the compressor section to define a fluid stream;', 'an angular velocity increaser located within the through passage and configured to increase angular velocity of the fluid stream to form a radially-outward portion and a radially-inward portion, with the radially-outward portion of the fluid stream having increased entrained particles to form a concentrated-particle stream, and the radially-inward portion having decreased entrained particles to form a reduced-particle stream;', 'a flow splitter located fluidly downstream of the angular velocity increaser and configured to split the concentrated-particle stream and the reduced-particle stream; and', 'an exit conduit fluidly coupled to the body to receive the reduced-particle stream and defining a separator outlet, wherein the exit conduit is fluidly coupled to the inducer., 'a centrifugal separator comprising40. The inducer assembly of claim 39 , wherein the exit conduit is shaped to substantially preserve angular velocity relative to the body centerline or tangential velocity relative to the engine centerline.41. The inducer assembly of claim 40 , wherein the shape of the exit conduit ...

Gas turbine engine with bleed duct for minimum reduction of bleed flow and minimum rejection of hail during hail ingestion events

A gas turbine engine includes a bleed structure which includes a forward wall and a rear structural wall to define a deposit space downstream of the bleed structure for a hail event of a predetermined duration.

ADAPTABLE INERTIAL PARTICLE SEPARATOR

An adaptive inertial particle separation system may include an active configuration and a passive configuration. The system may comprise an air-intake duct including an outer wall spaced apart from a central axis, an inner wall located between the outer wall and the engine rotation axis, an intake passage defined in part by the inner wall and the outer wall, and a splitter located between the outer wall and the inner wall. The system may further include a sensor operatively connected to the air-intake duct and operative to initiate at least one of the active configuration and passive configuration. 1. An adaptive inertial particle separation system having an active configuration and a passive configuration , the system comprising: an outer wall spaced apart from a central axis;', 'an inner wall located between the outer wall and the central axis;', 'an intake passage defined in part by the inner wall and the outer wall;, 'an air-intake duct includinga splitter located between the outer wall and the inner wall and including an outer splitter surface and an inner splitter surface, the inner splitter surface and the inner wall defining a compressor passage having a first area in the active configuration and a second area in the passive configuration, and the outer splitter surface and outer wall defining a scavenge passage in the active configuration,a sensor operatively connected to the air-intake duct, the sensor being configured to measure a particulate level with respect to the intake passage and initiate at least one of the active configuration and passive configuration based in part on the particulate level.2. The system of claim 1 , wherein the first area of the compressor passage increases to the second area of the compressor passage between the active configuration and the passive configuration.3. The system of claim 1 , further comprising an actuator to move the outer wall and inner wall relative to the splitter to selectively open the scavenge passage in the ...

FILTER ASSEMBLY INCLUDING PLEAT TIP SHAPES

Solutions for efficiently filtering air for a machine are disclosed. In one embodiment, a filter element for a filter assembly of a rotary machine is provided. The filter element includes: a first set of pleats, each pleat including a first tip radius and a first spacing; and a second set of pleats, each pleat including a second tip radius and a second spacing, wherein the first and second set of pleats are positioned upon a continuous filter media. 1. A filter element for a filter assembly , the filter element comprising:a first set of pleats, each pleat including a first tip radius and a first spacing, wherein the first tip radius and the first spacing are at a circumference of the filter element; anda second set of pleats, each pleat including a second tip radius and a second spacing wherein the second tip radius and the second spacing, are at the circumference of the filter element,wherein the first and second set of pleats are positioned upon a continuous filter media, wherein the first tip radius is different than the second tip radius, and wherein the first spacing is larger than the second spacing.23-. (canceled)4. The filter element of claim 1 , wherein a pleat height for each pleat of the first set of pleats and a pleat height for each pleat of the second set of pleats is substantially equal.5. The filter element of claim 1 , further comprising a third set of pleats claim 1 , each pleat including a third tip radius and a third spacing.6. The filter element of claim 5 , wherein the third tip radius is different than the second tip radius.7. The filter element of claim 6 , wherein the second spacing is larger than the third spacing.8. A system comprising:a gas turbine; and a first set of pleats, each pleat including a first tip radius and a first spacing, wherein the first tip radius and the first spacing are at a circumference of the filter assembly; and', 'a second set of pleats, each pleat including a second tip radius and a second spacing wherein the ...

PARTICLE-TRAPPING DEVICE FOR A TURBOMACHINE AND TURBOMACHINE WITH SUCH A DEVICE

The invention relates to a particle-trapping device () for a turbomachine, said particles being contained in an air stream flowing inside a turbomachine, in particular the air stream flowing in the bypass region () of the combustion chamber () of said turbomachine. The device is characterized in that it comprises:—at least two particle deflectors (),—a member () for collecting and storing the particles deflected by said deflector,—and means () for attaching said trapping device () to a part of the turbomachine. 2. The device according to claim 1 , wherein said support frame is a ring which extends in a plane perpendicular or substantially perpendicular to the axis of revolution (X-X′) of the deflectors claim 1 , in that the deflectors of a pair of contiguous deflectors are attached respectively along the outer circular edge and the inner circular edge of said annular support frame and in that this support frame is perforated with openings for passage of the air flow.3. The device according to claim 1 , wherein the inner face of a deflector has an angle of inclination (α claim 1 , β) with respect to said axis of revolution (X-X′) greater than the angle of inclination (β claim 1 , γ) with respect to this same axis of revolution (X-X′) of the inner face of a deflector disposed radially further inside the device.412. The device according to claim 1 , wherein the inner radius (R) of an outermost deflector of a pair of contiguous deflectors is less than or equal to the outer radius (R) of a deflector located further inside.5. The device according to claim 1 , wherein it comprises three deflectors.6. The device according to claim 1 , wherein at least one of said deflectors has a rectilinear cross section.7. The device according to claim 1 , wherein at least one of said deflectors has a curved cross section claim 1 , the concavity whereof is turned toward the particle collecting and storing element.8. The device according to claim 1 , wherein the collecting and storing ...