公开(公告)号：US20180187591A1

公开(公告)日：2018-07-05

申请号：US15849991

申请日：2017-12-21

Applicant: PRATT & WHITNEY CANADA CORP.

Inventor： Jean THOMASSIN ,  Sebastien BOLDUC ,  Bruno VILLENEUVE ,  Stephane BERUBE ,  Mike FONTAINE ,  David GAGNON-MARTIN ,  Andre JULIEN ,  Mark CUNNINGHAM ,  Serge LAFORTUNE ,  Pierre-Yves LEGARE

IPC: F02B29/04 ,  F02C7/055 ,  F01C11/00 ,  F01C21/18 ,  F02B37/12 ,  F02B39/04 ,  F02B53/08 ,  F02M31/10 ,  F02M31/04 ,  F02C7/36 ,  F02C7/14 ,  F02C7/052 ,  F02C7/047 ,  F02C6/12 ,  F02B53/14 ,  F01C1/22

Abstract: 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.

公开(公告)号：US20180193782A1

公开(公告)日：2018-07-12

申请号：US15401237

申请日：2017-01-09

Applicant: PRATT & WHITNEY CANADA CORP.

Inventor： Francois BISSON ,  Mark CUNNINGHAM

IPC: B01D45/06

CPC classification number: B01D45/06 ,  B64D2033/0246 ,  F02C7/052 ,  F05D2260/607 ,  Y02T50/675

Abstract: 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.

公开(公告)号：US20170241341A1

公开(公告)日：2017-08-24

申请号：US15052189

申请日：2016-02-24

Applicant: Pratt & Whitney Canada Corp.

Inventor： Eugene GEKHT ,  Francois BISSON ,  Mark CUNNINGHAM ,  Michel DESJARDINS ,  Guo Rong YAN

IPC: F02C7/042 ,  B64D33/02

CPC classification number: F02C7/042 ,  B64D33/02 ,  B64D2033/0246 ,  B64D2033/0293 ,  F02C6/206 ,  F02C7/04 ,  F05D2250/51 ,  Y02T50/671

Abstract: An air intake for efficiently channeling a flow of ambient air toward an air inlet of a turboprop or turboshaft gas turbine engine is disclosed. The air intake comprises an intake inlet for receiving the flow of air, an intake duct for channelling the flow of air, and an intake outlet for discharging the flow of air toward the air inlet of the gas turbine engine. The air intake may comprise a scroll portion and a strutted portion configured to receive the flow of air from the intake duct and channel the flow of air toward the intake outlet. The strutted portion may comprise one or more vanes for interacting with the flow of air. The intake duct may be oriented toward a flow direction of the air pushed aft by a propeller coupled to the gas turbine engine.

公开(公告)号：US20230134390A1

公开(公告)日：2023-05-04

申请号：US17453387

申请日：2021-11-03

Applicant: PRATT & WHITNEY CANADA CORP.

Inventor： Damien LE PAPE ,  Guorong YAN ,  Mark CUNNINGHAM ,  Philippe BEAUCHESNE-MARTEL ,  Oleg ISKRA ,  Richard IVAKITCH

IPC: F02C7/32

Abstract: An aircraft engine comprises an air inlet duct extending from an inlet through which air is configured to enter the aircraft engine, to an outlet within the aircraft engine. At least one strut has a leading edge and a trailing edge and extends across at least part of the air inlet duct. The at least one strut has a strut passage and a plurality of static pressure measurement taps spaced apart on the trailing edge and in fluid communication with the strut passage.

公开(公告)号：US20200040819A1

公开(公告)日：2020-02-06

申请号：US16054252

申请日：2018-08-03

Applicant: PRATT & WHITNEY CANADA CORP.

Inventor： Nigel WALTERS ,  Nicholas NGOLY ,  David CERANTOLA ,  Mark CUNNINGHAM ,  Roger LACHANCE

IPC: F02C7/055 ,  B64D33/02

Abstract: An air inlet system for an auxiliary power unit (APU) has an intake duct having a wall defining an inlet plenum and forming an inlet opening configured to direct air into the inlet plenum. The system further comprising a load compressor passage in fluid communication with the inlet plenum and leading to a load compressor of the APU; and a core compressor passage in fluid communication with the inlet plenum and leading to a core compressor of the APU. A deflector is provided in the inlet plenum between the inlet opening and the core compressor inlet to deflect at least part of particles carried by an incoming airflow away from the core compressor inlet toward the load compressor inlet.

公开(公告)号：US20180030883A1

公开(公告)日：2018-02-01

申请号：US15708442

申请日：2017-09-19

Applicant: PRATT & WHITNEY CANADA CORP.

Inventor： Jean THOMASSIN ,  Sebastien BOLDUC ,  Bruno VILLENEUVE ,  Stephane BERUBE ,  Mike FONTAINE ,  David GAGNON-MARTIN ,  Andre JULIEN ,  Mark CUNNINGHAM ,  Serge LAFORTUNE ,  Pierre-Yves LEGARE

IPC: F02B29/04 ,  F01C11/00 ,  F01D13/00 ,  F02B33/34 ,  F02C6/12 ,  F02B61/04 ,  F01C1/22 ,  F02B41/10 ,  F02B53/00 ,  F02K5/00

CPC classification number: F02B29/0493 ,  B64D33/02 ,  B64D2033/0293 ,  F01C1/22 ,  F01C11/002 ,  F01C11/008 ,  F01D13/003 ,  F02B29/0412 ,  F02B29/0418 ,  F02B33/34 ,  F02B41/10 ,  F02B53/00 ,  F02B61/04 ,  F02B2053/005 ,  F02C6/12 ,  F02K5/00 ,  F05D2220/40 ,  Y02T10/146 ,  Y02T10/163 ,  Y02T10/17

Abstract: A compound engine assembly including a common air conduit having an inlet in fluid communication with ambient air, a compressor, at least one internal combustion engine 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 at least one internal combustion engine, the turbine section configured to compound power with the at least one internal combustion engine, and at least one heat exchanger in fluid communication with the common air conduit, each of the at least one heat exchanger configured to circulate a fluid of the engine assembly in heat exchange relationship with an airflow from the common air conduit circulating therethrough. The compressor has an inlet in fluid communication with the common air conduit upstream of the at least one heat exchanger. The internal combustion engine may be a reciprocating engine.

公开(公告)号：US20250116230A1

公开(公告)日：2025-04-10

申请号：US18481737

申请日：2023-10-05

Applicant: PRATT & WHITNEY CANADA CORP.

Inventor： Roberto MARRANO ,  Mark CUNNINGHAM ,  Eray AKCAYOZ ,  Corentin BRETTE

IPC: F02C7/055 ,  B64D33/02

Abstract: A system for an aircraft includes an aircraft engine having a central axis with a flowpath projecting into the aircraft engine from an airflow inlet. An inlet plenum at the airflow inlet extends between a front wall and a rear wall along the central axis. An inlet guard is arranged at the airflow inlet and extends across the flowpath. The inlet guard includes a first screen extending circumferentially about the central axis and axially from the front wall to the rear wall, and a second screen radially outward of the first screen and axially overlapping the first screen. An actuator is operable to move the first screen and the second screen relative to one another in one or more of a radial, axial and circumferential direction to shed ice from the inlet guard.

公开(公告)号：US20190217234A1

公开(公告)日：2019-07-18

申请号：US16359163

申请日：2019-03-20

Applicant: PRATT & WHITNEY CANADA CORP.

Inventor： Francois BISSON ,  Mark CUNNINGHAM

IPC: B01D45/06 ,  B64D33/02 ,  F02C7/052

Abstract: 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.

公开(公告)号：US20170241342A1

公开(公告)日：2017-08-24

申请号：US15052214

申请日：2016-02-24

Applicant: Pratt & Whitney Canada Corp.

Inventor： Eugene GEKHT ,  Francois BISSON ,  Mark CUNNINGHAM ,  Michel DESJARDINS ,  Guo Rong YAN

IPC: F02C7/042 ,  B64D33/02

CPC classification number: F02C7/042 ,  B64D33/02 ,  B64D2033/022 ,  B64D2033/0246 ,  B64D2033/0293 ,  F02C7/04 ,  F02K3/02 ,  F05D2250/51 ,  Y02T50/671

Abstract: An air intake for efficiently channeling a flow of ambient air toward an air inlet of a turboprop or turboshaft gas turbine engine is disclosed. The air intake comprises an intake inlet for receiving the flow of air, an intake duct for channelling the flow of air, and an intake outlet for discharging the flow of air toward the air inlet of the gas turbine engine. The intake duct may be oriented toward a flow direction of the air pushed aft by a propeller coupled to the gas turbine engine.

公开(公告)号：US20160245161A1

公开(公告)日：2016-08-25

申请号：US14806902

申请日：2015-07-23

Applicant: Pratt & Whitney Canada Corp.

Inventor： Jean THOMASSIN ,  Sebastien BOLDUC ,  Bruno VILLENEUVE ,  Stephane BERUBE ,  Mike FONTAINE ,  David GAGNON-MARTIN ,  Andre JULIEN ,  Mark CUNNINGHAM ,  Serge LAFORTUNE ,  Pierre-Yves LEGARE

IPC: F02B41/00 ,  F01C1/22 ,  F02C6/18 ,  F01C11/00 ,  F02C3/04 ,  F01C21/18 ,  F01C21/06

CPC classification number: F02B41/00 ,  B64D33/10 ,  F01C1/22 ,  F01C11/008 ,  F01C21/06 ,  F01C21/18 ,  F02C3/04 ,  F02C6/18 ,  F02C7/04 ,  F02C7/042 ,  F02C7/14 ,  Y02T50/675

Abstract: A compound engine assembly including a compressor, an engine core including at least one rotary internal combustion engine and 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 and configured to compound power with the engine core, and an air conduit having at least one heat exchanger extending thereacross. An outer wall of the air conduit has a plurality of openings defined therethrough downstream of the heat exchanger(s), each selectively closable by a pivotable flap movable between a retracted position where the opening is obstructed and an extended position away from the opening. Each opening defines a fluid communication between the air conduit and the ambient air when the respective flap is in the extended position. A method of directing flow through a compound engine assembly is also discussed.

Abstract translation: 一种复合发动机组件，包括压缩机，包括至少一个旋转内燃机的发动机内燃机，并且具有与压缩机的出口流体连通的入口，具有与发动机芯的出口流体连通的入口的涡轮部分，以及 配置成与发动机芯组合动力，以及具有至少一个在其上延伸的热交换器的空气管道。 空气管道的外壁具有在热交换器的下游限定的多个开口，每个开口可由可枢转的翼片选择性地关闭，所述枢转折翼可在开口被阻塞的缩回位置和远离开口的延伸位置之间移动。 当各个翼片处于伸出位置时，每个开口限定了空气管道和环境空气之间的流体连通。 还讨论了引导流过复合发动机组件的方法。