公开(公告)号：US10533487B2

公开(公告)日：2020-01-14

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 ,  F02C6/12 ,  F02C7/047 ,  F02C7/052 ,  F02C7/055 ,  F02C7/14 ,  F02C7/36 ,  F01C11/00 ,  F02B33/40 ,  F02B39/04 ,  F01C21/18 ,  F02M31/04 ,  F02M31/10 ,  F02B37/12 ,  F02B53/08 ,  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：US10197009B2

公开(公告)日：2019-02-05

申请号：US14514770

申请日：2014-10-15

Applicant: Pratt & Whitney Canada Corp.

Inventor： Guorong Yan ,  Mark Cunningham ,  Franco Di Paola

IPC: F02K1/38 ,  F02K1/34 ,  F02K1/48 ,  F02C3/10

Abstract: An ejector comprises a primary nozzle having an annular wall forming part of an outer boundary of an exhaust portion of a primary flow path of a gas turbine engine. The annular wall has a downstream end defining a plurality of circumferentially distributed lobes. The ejector further comprises a secondary nozzle having an annular wall disposed about the primary nozzle, the primary nozzle and the secondary nozzle defining a secondary flow passage therebetween for channeling a secondary flow. The secondary nozzle defines a mixing zone downstream of an exit of the primary nozzle. A flow guide ring is mounted to the primary nozzle lobes. The ring has an aerodynamic surface extending from a leading edge to a trailing edge respectively disposed upstream and downstream of the exit of the primary nozzle. The aerodynamic surface of the ring is oriented to guide the high velocity primary flow into the mixing zone.

公开(公告)号：US09896998B2

公开(公告)日：2018-02-20

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: F02G3/00 ,  F02G1/00 ,  F02C7/06 ,  F02C7/10 ,  B64D33/10 ,  B64D41/00 ,  F02B33/00 ,  F04C18/00 ,  F01C1/063 ,  F02B41/00 ,  F02C7/04 ,  F02C7/042 ,  F02C7/14 ,  F01C1/22 ,  F01C11/00 ,  F01C21/06 ,  F01C21/18 ,  F02C3/04 ,  F02C6/18

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.

公开(公告)号：US09797297B2

公开(公告)日：2017-10-24

申请号：US14806918

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

CPC classification number: F02B29/0493 ,  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 an air conduit having an inlet in fluid communication with ambient air around the compound engine assembly, a compressor having an inlet in fluid communication with the air conduit, 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 at least one heat exchanger in fluid communication with the air conduit, each heat exchanger configured to circulate a fluid of the engine assembly in heat exchange relationship with an airflow from the air conduit circulating therethrough. A method of supplying air to a compound engine assembly is also discussed.

公开(公告)号：US12241412B1

公开(公告)日：2025-03-04

申请号：US18481705

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. The first screen has a first screen axial width L1 extending from the front wall to the rear wall. The inlet guard further includes a second screen extending at least partially circumferentially about the central axis. The second screen is disposed radially outward of the first screen and axially overlaps the first screen. The second screen has a second screen axial width L2 less than the first screen axial width L1.

公开(公告)号：US20240254942A1

公开(公告)日：2024-08-01

申请号：US18593232

申请日：2024-03-01

Applicant: Pratt & Whitney Canada Corp.

Inventor： Eray Akcayoz ,  Mark Cunningham

IPC: F02K1/40

CPC classification number: F02K1/40 ,  F05D2220/323 ,  F05D2250/51 ,  F05D2250/52 ,  F05D2250/71 ,  F05D2250/73

Abstract: An exhaust duct of an aircraft engine includes an annular inlet conduit having an inlet central axis, and at least two outlet conduits in flow communication with the inlet conduit. The at least two outlet conduits are located non-parallel to the inlet central axis. Each of the at least two outlet conduits include an outlet port defining a distal end of each of the two outlet conduits. At least one of the outlet ports is non-circular in cross-sectional shape.

公开(公告)号：US12000358B1

公开(公告)日：2024-06-04

申请号：US18109428

申请日：2023-02-14

Applicant: Pratt & Whitney Canada Corp.

Inventor： Mark Cunningham ,  Eray Akcayoz

IPC: F02K1/62 ,  F02K1/58

CPC classification number: F02K1/62 ,  F02K1/58 ,  F05D2220/323

Abstract: An engine nacelle assembly includes a nacelle that defines a flow path between an intake end and an exhaust end, and a nozzle that is disposed at the exhaust end of the nacelle about a central axis. The nozzle includes opposing thrust reverser openings and thrust reverser doors. A cross-sectional area transverse to the central axis proximate a forward side of each of the opposing thrust reverser openings is oval shaped with an offset radius within offset arc segments that are aligned with the opposing thrust reverser openings and a first radius outside of the offset arc segment. The first radius is less than the offset radius.

公开(公告)号：US11994064B2

公开(公告)日：2024-05-28

申请号：US17977722

申请日：2022-10-31

Applicant: Pratt & Whitney Canada Corp.

Inventor： Mark Cunningham ,  Eray Akcayoz ,  Raja Ramamurthy ,  Roberto Marrano

IPC: F02C7/042

CPC classification number: F02C7/042 ,  F05D2220/323 ,  F05D2270/60

Abstract: An air intake for an aircraft propulsion system includes an air inlet duct and a flow control device. The air inlet duct includes an interior surface and an intake inlet. The interior surface extends from the intake inlet. The interior surface forms and surrounds an inlet flow passage through the air inlet duct. The intake inlet includes a top side, a bottom side, a first lateral side, and a second lateral side. Each of the first lateral side and the second lateral side extend between and to the top side and the bottom side. The flow control device is disposed inside the air inlet duct at the first lateral side. The flow control device is configured to form an asymmetrical shape of the intake inlet at the first lateral side relative to the second lateral side.

公开(公告)号：US11965460B1

公开(公告)日：2024-04-23

申请号：US17977737

申请日：2022-10-31

Applicant: Pratt & Whitney Canada Corp.

Inventor： Raja Ramamurthy ,  Eray Akcayoz ,  Mark Cunningham ,  Roberto Marrano

IPC: F02C7/05 ,  F02C7/042 ,  F02C7/057 ,  F02C9/18

CPC classification number: F02C7/05 ,  F02C7/042 ,  F02C7/057 ,  F02C9/18 ,  F05D2220/323

Abstract: An air intake for an aircraft propulsion system includes an air inlet duct, a core flow duct, a bypass flow duct, a splitter, and a flow control device. The air inlet duct includes an intake inlet and a gas path floor. The core flow duct includes a core flow outlet. The bypass flow duct includes a bypass flow outlet. The bypass flow duct includes the gas path floor. The splitter separates the core flow duct and the bypass flow duct. The flow control device is disposed on a portion of the gas path floor. The flow control device is configured to be selectively positioned to control an air flow path for air flowing through the air inlet duct, the core flow duct, and the bypass flow duct.

公开(公告)号：US20240035393A1

公开(公告)日：2024-02-01

申请号：US17876854

申请日：2022-07-29

Applicant: Pratt & Whitney Canada Corp.

Inventor： Damien Le Pape ,  Mark Cunningham

IPC: F01D21/00

CPC classification number: F01D21/003 ,  F05D2220/323 ,  F05D2260/30 ,  F05D2270/3011

Abstract: A system is provided for an aircraft. This aircraft system includes a gas turbine engine and a sensor system. The gas turbine engine includes an inlet and a compressor section. A flowpath projects radially inward into the gas turbine engine from the inlet and extends through the compressor section. The sensor system includes a plurality of static pressure sensors at least partially within the flowpath. The sensor system is configured to determine a total pressure characteristic within the flowpath using the plurality of static pressure sensors.