公开(公告)号：US20180328284A1

公开(公告)日：2018-11-15

申请号：US16043629

申请日：2018-07-24

Applicant: PRATT & WHITNEY CANADA CORP.

Inventor： Michel LABRECQUE ,  Vincent COUTURE-GAGNON ,  Richard ULLYOTT

IPC: F02C7/045 ,  F02C7/052 ,  F02C7/042 ,  F01D17/08 ,  F02C7/05 ,  F01D17/10 ,  F02K3/02

CPC classification number: F02C7/045 ,  F01D17/08 ,  F01D17/105 ,  F02C7/042 ,  F02C7/05 ,  F02C7/052 ,  F02K3/025

Abstract: An aeroengine has an inlet system with a forward end with respect to a flight direction. The inlet system includes a main inlet duct for selectively directing a first air flow from a forward main intake opening of the main inlet duct to a compressor rotor, the forward main intake opening being defined at the forward end of the inlet system and a secondary inlet duct for directing a second air flow from a secondary intake opening of the secondary inlet duct to the compressor rotor only when the main inlet duct is closed. A control apparatus is provided for selecting the first and second air flow to enter into the compressor rotor.

公开(公告)号：US10082243B1

公开(公告)日：2018-09-25

申请号：US15621185

申请日：2017-06-13

Applicant: PRATT & WHITNEY CANADA CORP.

Inventor： Behzad Hagshenas ,  Eric Huff

IPC: G08B23/00 ,  F16N29/04 ,  G01K3/00 ,  F16N29/00 ,  F01D25/18

CPC classification number: F16N29/04 ,  B64D2033/0213 ,  F01D21/12 ,  F01D21/14 ,  F01D25/18 ,  F02C7/047 ,  F02C7/05 ,  F02C7/14 ,  F05D2220/50 ,  F16N29/00 ,  F16N2210/02 ,  F16N2250/08 ,  F16N2250/11 ,  F16N2260/05 ,  F16N2260/06 ,  G01K3/005 ,  Y02T50/675

Abstract: Herein provided are methods and systems for detecting blockage of an inlet of gas turbine engine. An oil temperature measurement of the engine and an ambient temperature measurement is obtained. The oil temperature measurement is compared to a threshold based on the ambient temperature measurement. Blockage of the inlet of the engine is detected when the oil temperature measurement exceeds the threshold.

公开(公告)号：US09915168B2

公开(公告)日：2018-03-13

申请号：US14728779

申请日：2015-06-02

Applicant: UNITED TECHNOLOGIES CORPORATION

Inventor： Thomas J. Robertson, Jr. ,  Steven Clarkson

IPC: F01D21/04 ,  F01D25/00 ,  F01D25/24 ,  F02C7/05

CPC classification number: F01D25/005 ,  F01D21/045 ,  F01D25/24 ,  F02C7/05 ,  F05D2240/14 ,  F05D2300/603 ,  Y02T50/672

Abstract: A turbofan engine has a fan having a circumferential array of fan blades. A fan case encircles the fan. There is at least one compressor section, a combustor, and at least one turbine section. The fan case comprises a containment case and a cartridge liner carried therein. A ballistic liner encircles at least a portion of the cartridge liner and is attached thereto.

公开(公告)号：US09863317B2

公开(公告)日：2018-01-09

申请号：US14415410

申请日：2011-12-20

Applicant: Marco Santini ,  Giorgio Marchetti

Inventor： Marco Santini ,  Giorgio Marchetti

IPC: F02G3/00 ,  F02C7/05 ,  F01D25/00 ,  F01D25/32 ,  F02C7/055 ,  B01D46/00 ,  B01D46/42

CPC classification number: F02C7/05 ,  B01D46/0087 ,  B01D46/4227 ,  F01D25/002 ,  F01D25/32 ,  F02C7/055 ,  Y10T29/49238

Abstract: A filtering chamber for a gas turbine having a combustor, compressor and air inlet duct, and a corresponding maintenance method is described. The filtering chamber includes a first chamber in an inlet plenum; a second chamber in the inlet plenum; and an air bypass mechanism configured to reduce a pressure difference across a final filter that separates the first chamber from the second chamber.

公开(公告)号：US09683490B2

公开(公告)日：2017-06-20

申请号：US14529810

申请日：2014-10-31

Applicant: ROLLS-ROYCE PLC

Inventor： Cedric Brett Harper ,  Ian Colin Deuchar Care ,  Julian Mark Reed

IPC: F02C7/05 ,  F01D11/12 ,  F01D21/04 ,  F02K3/06 ,  F01D21/10 ,  F01D25/24

CPC classification number: F02C7/05 ,  F01D11/122 ,  F01D21/04 ,  F01D21/045 ,  F01D21/10 ,  F01D25/246 ,  F02K3/06 ,  F05D2220/36

Abstract: A fan containment system includes an annular casing element and a hook projecting in a generally radially inward direction from the annular casing element. A fan track liner is connected to the hook via a fastener. The fan track liner has a forward end proximal to the hook and a rearward end distal to the hook. A pivot member protrudes radially inward from the annular casing element and is arranged and positioned between the forward and rearward end of the fan track liner such that a forward portion of the fan track liner is pivotable about the pivot member, so that upon release of a fan blade the forward portion of the fan track liner pivots about the pivot member into a voidal region provided between the annular casing element and the forward portion of the fan track liner to encourage engagement of the hook with a released fan blade.

公开(公告)号：US20170137135A1

公开(公告)日：2017-05-18

申请号：US15346612

申请日：2016-11-08

Applicant: SAFRAN AIRCRAFT ENGINES

Inventor： Philippe Gerard CHANEZ ,  Mathieu Patrick Jean-Louis LALLIA ,  Christian Sylvain VESSOT

IPC: B64D27/18 ,  B64D33/02 ,  F02C7/05

CPC classification number: B64D27/18 ,  B64D27/12 ,  B64D33/02 ,  B64D2033/0286 ,  F02C7/05 ,  F02K1/52 ,  F02K3/06 ,  F02K3/077 ,  F05D2240/40 ,  F05D2250/312

Abstract: The invention relates to an aircraft propulsion assembly (10), comprising a single gas generator (11) and two fans (12) drive in rotation by the gas generator (11) and offset on either side of a vertical plane passing through a longitudinal axis (X) of the gas generator, the rotational axes of the fans lying substantially in the same fan plane.According to the invention, the propulsion assembly (10) comprises an air inlet fairing formed upstream of a nacelle (25) connecting the fans, said fairing (15) having, between the fans (12), an air inlet opening (17, 17′) lying substantially perpendicular to the fan plane and on either side of this plane, the propulsion assembly further comprising an air supply device configured so as to supply the gas generator (11) with a part of the incoming air and to take off, from the remaining part of the incoming air, a cooling airflow intended to cool elements of the propulsion assembly and/or a wing supporting the propulsion assembly.

公开(公告)号：US20170101896A1

公开(公告)日：2017-04-13

申请号：US15314341

申请日：2015-05-28

Applicant: GENERAL ELECTRIC COMPANY

Inventor： Robert Francis MANNING ,  Timothy Deryck STONE ,  Jared Peter BUHLER ,  Victor Hugo Silva CORREIA ,  Gregory Michael LASKOWSKI ,  Robert Carl MURRAY ,  Jonathan Russell RATZLAFF ,  Robert PROCTOR ,  John Howard STARKWEATHER ,  Curtis Walton STOVER

IPC: F01D25/32 ,  F02C7/18 ,  B04C3/06 ,  F01D5/08 ,  F02C9/18 ,  B01D45/16 ,  F02C3/04 ,  F01D25/12

CPC classification number: F01D25/32 ,  B01D45/16 ,  B04C3/00 ,  B04C3/06 ,  B04C2003/003 ,  B04C2003/006 ,  B64D33/08 ,  B64D2033/022 ,  B64D2033/024 ,  B64D2033/0246 ,  F01D5/08 ,  F01D25/12 ,  F02C3/04 ,  F02C7/05 ,  F02C7/052 ,  F02C7/18 ,  F02C9/18 ,  F05D2220/32 ,  F05D2240/35

Abstract: A centrifugal separator for removing particles from a fluid stream includes an angular velocity increaser configured to increase the angular velocity of a fluid stream, a flow splitter configured to split the fluid stream to form a concentrated-particle stream and a reduced-particle stream, and an exit conduit configured to receive the reduced-particle stream. An inducer assembly for a turbine engine includes an inducer with a flow passage having an inducer inlet and an inducer outlet in fluid communication with a turbine section of the engine, and a particle separator, which includes a particle concentrator that receives a compressed stream from a compressor section of the engine and a flow splitter. A turbine engine includes a cooling air flow circuit which supplies a fluid stream to a turbine section of the engine for cooling, a particle separator located within the cooling air flow circuit, and an inducer forming a portion of the cooling air flow circuit in fluid communication with the particle separator. A method of cooling a rotating blade of a turbine engine having an inducer includes directing a cooling fluid stream from a portion of turbine engine toward the rotating blade, separating particles from the cooling fluid stream by passing the cooling fluid stream through a inertial separator, accelerating a reduced-particle stream emitted from the inertial separator to the speed of the rotating blade, and orienting the reduced-particle stream by emitting the reduced-particle stream from the inertial separator into a cooling passage in the inducer.

公开(公告)号：US09550581B2

公开(公告)日：2017-01-24

申请号：US14632254

申请日：2015-02-26

Applicant: PRATT & WHITNEY CANADA CORP.

Inventor： Carlos Adelino Marques Santos Loureiro

IPC: B64F1/00 ,  E06B9/02 ,  E06B5/00 ,  F02C7/05 ,  F02C7/055

CPC classification number: B64D33/04 ,  B64C7/02 ,  B64D29/00 ,  B64D33/02 ,  B64D2033/022 ,  B64F1/005 ,  E06B5/00 ,  E06B9/02 ,  F02C7/05 ,  F02C7/055

Abstract: A protective cover for an aircraft engine comprises a lower portion mountable to a corresponding lower portion of an opening of the engine, and an upper portion articulated to the lower portion. The upper portion is deployable from a collapsed position to a deployed position in which the upper portion extends upwardly from the lower portion. A handling tool may be used to operate the panel from a remote location on the ground.

Abstract translation: 用于飞机发动机的保护盖包括可安装到发动机的开口的相应下部的下部和铰接到下部的上部。 上部可以从折叠位置展开到展开位置，其中上部从下部向上延伸。 处理工具可用于从地面上的远程位置操作面板。

公开(公告)号：US09534540B2

公开(公告)日：2017-01-03

申请号：US14265388

申请日：2014-04-30

Applicant: Jose Antonio Tuero

Inventor： Jose Antonio Tuero

IPC: F02C7/057 ,  F02C7/25 ,  B64D25/00 ,  B64D31/06 ,  F02C7/05 ,  B64D45/00

CPC classification number: F02C7/25 ,  B64D25/00 ,  B64D31/06 ,  B64D2045/0095 ,  F02C7/05 ,  F02C7/057 ,  F05D2220/323 ,  F05D2230/80 ,  F05D2270/09 ,  F05D2270/44 ,  F05D2270/805

Abstract: An automatic emergency radar and proximity sensor activated protection system that could assist to prevent commercial, private, or military aircraft jet engines from being damaged or destroyed by the installment of a Shielding Blade Assembly which will immediately close when detection of objects such as; birds, debris, or other destructive elements try to enter through the engine intake while the aircraft is in FLIGHT causing the Internal Air Injection Unit (A.I.U.) to supply high volumes of air in order for the engine to stay operational and prevent it from stalling while in FLIGHT.

Abstract translation: 一种自动应急雷达和接近传感器激活的保护系统，可以帮助防止商业，私人或军用飞机喷气发动机被安装的屏蔽刀片组件损坏或破坏，当检测到诸如 鸟类，碎片或其他破坏性元素在飞机飞行时试图通过发动机进气进入，导致内部空气喷射单元（AIU）提供大量的空气，以使发动机保持运行并防止其停止，同时 在飞行中。

公开(公告)号：US20160348685A1

公开(公告)日：2016-12-01

申请号：US14721015

申请日：2015-05-26

Applicant: Pratt & Whitney Canada Corp.

Inventor： TIBOR URAC ,  KARAN ANAND

IPC: F04D27/02 ,  F04D29/08 ,  F04D29/52

CPC classification number: F04D27/0215 ,  F02C6/08 ,  F02C7/05 ,  F02K3/075 ,  F04D27/009 ,  F04D27/023 ,  F05D2240/55 ,  F05D2260/57 ,  F05D2260/606 ,  F05D2260/607

Abstract: A bleed of valve comprises a ring axially translatable between a retracted position in which the ring is configured to close an annular bleed off opening defined in a converging portion of a radially outer annular wall of a gas turbine engine gaspath and a deployed position in which the ring protrudes into the gaspath to mechanically scoop out incoming air and water/hail particles.

Abstract translation: 阀的泄漏包括在缩回位置之间可轴向平移的环，其中环被构造成封闭限定在燃气涡轮发动机气体路径的径向外部环形壁的会聚部分中的环形泄放开口和展开位置，其中 环突出到气路中以机械铲除进入的空气和水/冰雹颗粒。