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1.发明公开公开(公告)号：US20240141833A1
公开(公告)日：2024-05-02
申请号：US17977680
申请日：2022-10-31
Applicant: Pratt & Whitney Canada Corp.
Inventor： Eray Akcayoz , Mark Cunningham , Raja Ramamurthy , Roberto Marrano
Abstract: An air intake for an aircraft propulsion system includes an air inlet duct, a core flow duct, a bypass flow duct, and a flow control device. The air inlet duct includes an intake inlet of the air intake. The core flow duct includes a core flow outlet. The core flow duct extends between and to the air inlet duct and the core flow outlet. The bypass flow duct includes a bypass flow outlet. The bypass flow duct extends between and to the air inlet duct and the bypass flow outlet. The bypass flow duct includes an interior surface forming and surrounding a bypass flow passage through the bypass flow duct. The flow control device is disposed on the interior surface. The flow control device is configured to variably control an area of a cross-sectional flow area of the bypass flow passage.
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公开(公告)号：US10883414B2
公开(公告)日：2021-01-05
申请号：US16707362
申请日：2019-12-09
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.
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公开(公告)号：US10533489B2
公开(公告)日：2020-01-14
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 , F01C1/22 , F01C11/00 , F01D13/00 , F02K5/00 , F02C6/12 , F02B33/34 , F02B41/10 , F02B53/00 , F02B61/04
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.
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公开(公告)号：US10030581B2
公开(公告)日：2018-07-24
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
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.
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公开(公告)号：US12163486B2
公开(公告)日：2024-12-10
申请号：US18152326
申请日：2023-01-10
Applicant: PRATT & WHITNEY CANADA CORP.
Inventor： Metin Ilbay Yaras , Mark Cunningham , Raja Ramamurthy
Abstract: An exhaust mixer assembly for a gas turbine engine includes a core passage extending along a central engine axis for directing a core gas flow. An outer annular passage coaxially surrounds the core passage for directing a bypass gas flow. An exhaust mixer communicating with the core passage and outer annular passages has an upstream end, a downstream end and an annular wall extending therebetween. The annular wall defines a mixing plane at a trailing edge thereof at the downstream end at which the core and bypass gas flows are mixed. The annular wall has a radially inner surface and a radially outer surface. A plurality of protrusions are disposed on and extend laterally along and radially from at the radially inner surface and/or the radially outer surface. The plurality of protrusions are arranged one alongside another on the radially inner surface and/or the radially outer surface.
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Patent Agency Ranking
公开(公告)号：US12018615B2
公开(公告)日：2024-06-25
申请号：US17977680
申请日：2022-10-31
Applicant: Pratt & Whitney Canada Corp.
Inventor： Eray Akcayoz , Mark Cunningham , Raja Ramamurthy , Roberto Marrano
Abstract: An air intake for an aircraft propulsion system includes an air inlet duct, a core flow duct, a bypass flow duct, and a flow control device. The air inlet duct includes an intake inlet of the air intake. The core flow duct includes a core flow outlet. The core flow duct extends between and to the air inlet duct and the core flow outlet. The bypass flow duct includes a bypass flow outlet. The bypass flow duct extends between and to the air inlet duct and the bypass flow outlet. The bypass flow duct includes an interior surface forming and surrounding a bypass flow passage through the bypass flow duct. The flow control device is disposed on the interior surface. The flow control device is configured to variably control an area of a cross-sectional flow area of the bypass flow passage.
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公开(公告)号：US11535386B2
公开(公告)日：2022-12-27
申请号：US16671551
申请日：2019-11-01
Applicant: PRATT & WHITNEY CANADA CORP.
Inventor： Philippe Beauchesne-Martel , Mark Cunningham
IPC: G01C23/00 , B64D15/16 , B64C27/00 , B64D15/20 , F02C6/02 , F02C6/20 , F02C9/22 , F02C9/26 , B64C27/06 , B64D27/10 , B64D31/14
Abstract: There is provided a system and a method for operating a multi-engine rotorcraft. When the rotorcraft is cruising in an asymmetric operating regime (AOR) at least one engine is an active engine and is operated in an active mode to provide motive power to the rotorcraft and at least one second engine is a standby engine and is operated in a standby mode to provide substantially no motive power to the rotorcraft, at least one of a power level of the at least one second engine is increased and at least one variable geometry mechanism of the at least one second engine is moved to shed any ice accumulation on the at least one second engine.
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公开(公告)号：US11415079B2
公开(公告)日：2022-08-16
申请号：US16226717
申请日：2018-12-20
Applicant: PRATT & WHITNEY CANADA CORP.
Inventor： Guorong Yan , Mark Cunningham , Franco Di Paola
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.
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公开(公告)号：US11339716B2
公开(公告)日：2022-05-24
申请号：US16573013
申请日：2019-09-17
Applicant: PRATT & WHITNEY CANADA CORP.
Inventor： Guorong Yan , Mark Cunningham
Abstract: 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.
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公开(公告)号：US11085333B2
公开(公告)日：2021-08-10
申请号：US13937587
申请日：2013-07-09
Applicant: Pratt & Whitney Canada Corp.
Inventor： Mark Cunningham , Remo Marini , Sami Girgis , Mohammad Reza Kameshki , Raja Ramamurthy
Abstract: An exhaust mixer for a gas turbine engine where each outer lobe has at the downstream end a circumferential offset in a direction corresponding to that of the swirl component of the flow entering the mixer. The mixer has a crest line having at least a downstream portion curved with respect with respect to a circumferential direction of the mixer and/or a center line at the downstream end tilted with respect to a radial line extending to the tip of the outer lobe to define the circumferential offset. A method of mixing a core flow and a bypass flow surrounding the core flow with an annular mixer is also provided.
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