公开(公告)号：US20230031511A1

公开(公告)日：2023-02-02

申请号：US17957058

申请日：2022-09-30

Applicant: PRATT & WHITNEY CANADA CORP.

Inventor： Jean THOMASSIN ,  Serge DUSSAULT ,  Joseph Brent STAUBACH

IPC: B64D27/04 ,  B64D27/24 ,  F01K25/10 ,  F02B37/00 ,  F02C5/00 ,  F02C5/06 ,  F02C7/00 ,  F02G5/02

Abstract: Aircraft power plants including combustion engines, and associated methods for recuperating waste heat from such aircraft power plants are described. A method includes transferring the heat rejected by the internal combustion engine to supercritical CO2 (sCO2) used as a working fluid in a heat engine. The heat engine converts at least some the heat transferred to the sCO2 to mechanical energy to perform useful work onboard the aircraft.

公开(公告)号：US20190256217A1

公开(公告)日：2019-08-22

申请号：US15898732

申请日：2018-02-19

Applicant: PRATT & WHITNEY CANADA CORP.

Inventor： Luc DIONNE ,  Bruno VILLENEUVE ,  Jean THOMASSIN

IPC: B64D35/02 ,  B64C1/06 ,  B64C25/34 ,  B64D27/08 ,  B64D33/08 ,  F01P11/10 ,  F01P3/18 ,  F01P7/02 ,  F02B53/00 ,  F02B41/10 ,  F02B37/00

Abstract: An assembly for an aircraft having a propeller, including a wheel well for a retracted landing gear, first and second cooling ducts; and an engine assembly having an engine shaft configured for driving engagement with the propeller, the engine assembly including a coolant circulation system for circulation of a liquid coolant, a lubricant circulation system for circulation of a lubricant, a first heat exchanger in fluid communication with at least the coolant circulation system, and a second heat exchanger in fluid communication with at least the lubricant circulation system. Each heat exchanger is positioned and configured for receiving a cooling airflow from the respective cooling duct. The wheel well is located between the heat exchangers. A method of cooling a lubricant and a liquid coolant of an engine assembly is also discussed.

公开(公告)号：US20190203620A1

公开(公告)日：2019-07-04

申请号：US16292846

申请日：2019-03-05

Applicant: PRATT & WHITNEY CANADA CORP.

Inventor： Andre JULIEN ,  Serge DUSSAULT ,  Jean THOMASSIN

IPC: F01N3/05 ,  B64D27/08 ,  B64D33/04 ,  F02B61/04 ,  F02B53/14 ,  F01N13/08 ,  B64D27/02 ,  F02C7/18 ,  F02C6/20 ,  F02C5/00 ,  F02K1/38 ,  B64D33/10 ,  B64D27/10

CPC classification number: F01N3/055 ,  B64D27/02 ,  B64D27/08 ,  B64D27/10 ,  B64D33/04 ,  B64D33/10 ,  F01N13/082 ,  F01N2260/022 ,  F01N2270/02 ,  F02B53/14 ,  F02B61/04 ,  F02B2053/005 ,  F02C5/00 ,  F02C6/206 ,  F02C7/18 ,  F02K1/386 ,  F05D2260/213 ,  Y02T50/672 ,  Y02T50/676

Abstract: A turboprop engine assembly for an aircraft, including an internal combustion engine having a liquid coolant system, an air duct in fluid communication with an environment of the aircraft, a heat exchanger received within the air duct having coolant passages in fluid communication with the liquid coolant system and air passages air passages in fluid communication with the air duct, and an exhaust duct in fluid communication with an exhaust of the internal combustion engine. The exhaust duct has an outlet positioned within the air duct downstream of the heat exchanger and upstream of an outlet of the air duct, the outlet of the exhaust duct spaced inwardly from a peripheral wall of the air duct. In use, a flow of cooling air surrounds a flow of exhaust gases. A method of discharging air and exhaust gases in an turboprop engine assembly having an internal combustion engine is also discussed.

公开(公告)号：US20190128177A1

公开(公告)日：2019-05-02

申请号：US16226702

申请日：2018-12-20

Applicant: PRATT & WHITNEY CANADA CORP.

Inventor： Jean THOMASSIN

IPC: F02B53/14 ,  F01C11/00 ,  F02B53/10 ,  F02C6/20 ,  F01C1/22 ,  F02C6/12

Abstract: A compound cycle engine having a rotary internal combustion engine, a first turbine, and a second turbine is discussed. The exhaust port of the internal combustion engine is in fluid communication with the flowpath of the first turbine upstream of its rotor. The rotors of the first turbine and of each rotary unit drive a common load. The inlet of the second turbine is in fluid communication with the flowpath of the first turbine downstream of its rotor. The first turbine is configured as a velocity turbine and the first turbine has a pressure ratio smaller than that of the second turbine. A method of compounding a rotary engine is also discussed.

公开(公告)号：US20180339786A1

公开(公告)日：2018-11-29

申请号：US15983528

申请日：2018-05-18

Applicant: PRATT & WHITNEY CANADA CORP.

Inventor： Jean THOMASSIN ,  Eric Taillon

IPC: B64D35/08 ,  F02N11/04

Abstract: There is provided an engine assembly for an aircraft, comprising a heat engine in driving engagement with an engine shaft having a first end coupled to a mechanical gearbox and a second end opposite the first end, an electric generator coupled to the second end to provide a generator output voltage, the electric generator separate from the mechanical gearbox, a power electronics module connected to the electric generator and configured to regulate the generator output voltage to provide a regulated output voltage that meets an electrical power demand of at least one aircraft accessory, and a voltage bus connected to the power electronics module and configured to supply the regulated output voltage to the at least one aircraft accessory.

公开(公告)号：US20180209331A1

公开(公告)日：2018-07-26

申请号：US15938122

申请日：2018-03-28

Applicant: PRATT & WHITNEY CANADA CORP.

Inventor： Jean THOMASSIN ,  Edwin SCHULZ

IPC: F02B53/10 ,  F02D41/38 ,  F02B19/10 ,  F02D41/30 ,  F01C1/22 ,  F02B55/14

CPC classification number: F02B53/10 ,  F01C1/22 ,  F02B19/108 ,  F02B55/14 ,  F02B2275/32 ,  F02D41/3094 ,  F02D41/3827 ,  F02D41/3836 ,  Y02T10/125 ,  Y02T10/142 ,  Y02T10/17

Abstract: An internal combustion engine includes first and second common rails each having a metering or pressure regulating valve, with the valves settable at different pressure values from one another. Rotors are each sealingly and rotationally received within a respective cavity to define at least one combustion chamber of variable volume. The engine includes first and second fuel injectors for each of the rotors. Each first fuel injector is in fluid communication with the first common rail and each second fuel injector is in fluid communication with the second common rail. A method of feeding fuel in an internal combustion engine is also provided.

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：US20170268409A1

公开(公告)日：2017-09-21

申请号：US15134904

申请日：2016-04-21

Applicant: Pratt & Whitney Canada Corp.

Inventor： Jean THOMASSIN ,  David MEISELS ,  Richard ULLYOTT

IPC: F01P11/10 ,  F01P5/10 ,  B64C21/06 ,  F01P3/20 ,  B64D27/10 ,  B64C21/04

CPC classification number: F01P11/10 ,  B64C9/38 ,  B64C21/04 ,  B64C21/06 ,  B64C2230/04 ,  B64C2230/22 ,  B64D27/10 ,  B64D33/10 ,  F01P3/20 ,  F01P5/10 ,  Y02T50/166 ,  Y02T50/32 ,  Y02T50/44

Abstract: A method of providing active flow control for an aircraft includes cooling a liquid coolant in a heat exchanger by circulating a cooling airflow through the heat exchanger, and providing fluid communication between the cooling airflow and a boundary layer flow of at least one flight control surface of the aircraft. The cooling airflow affects the boundary layer flow of the flight control surface(s) to provide active flow control. A method of cooling an engine core of an engine assembly includes circulating a cooling fluid through the engine core, and cooling the cooling fluid with a cooling airflow used to provide active flow control to a flight control surface of the aircraft. An active flow control system for an aircraft is also discussed.

公开(公告)号：US20170037776A1

公开(公告)日：2017-02-09

申请号：US15227483

申请日：2016-08-03

Applicant: PRATT & WHITNEY CANADA CORP.

Inventor： Anthony JONES ,  Andre JULIEN ,  David MENHEERE ,  Jean THOMASSIN ,  Richard ULLYOTT

IPC: F02B63/04 ,  F02B53/14 ,  B64D41/00 ,  F01P5/04 ,  F01P5/06 ,  F02B37/00 ,  F02B63/06 ,  F01P1/06

CPC classification number: F02B63/04 ,  B64D33/08 ,  B64D41/00 ,  F01C1/22 ,  F01C21/18 ,  F01P1/06 ,  F01P5/04 ,  F01P5/06 ,  F02B37/00 ,  F02B53/02 ,  F02B53/14 ,  F02B63/06 ,  F02B67/04 ,  F02B2053/005 ,  F02C5/00 ,  F02C7/14 ,  F02C7/18 ,  F02K5/00 ,  F05D2220/50 ,  F05D2260/213 ,  Y02T10/144 ,  Y02T10/17 ,  Y02T50/53 ,  Y02T50/672 ,  Y02T50/676

Abstract: An auxiliary power unit for an aircraft, including an internal combustion engine having a liquid coolant system, a generator drivingly engaged to the internal combustion engine and having a liquid coolant system distinct from the liquid coolant system of the internal combustion engine, a first heat exchanger in fluid communication with the liquid coolant system of the internal combustion engine, a second heat exchanger in fluid communication with the liquid coolant system of the generator, an exhaust duct in fluid communication with air passages of the heat exchangers, and a fan received in the exhaust duct and rotatable by the internal combustion engine for driving a cooling air flow through the air passages. The liquid coolant system of the engine may be distinct from fuel and lubricating systems of the auxiliary power unit. A method of cooling a generator and an internal combustion engine is also discussed.

Abstract translation: 一种用于飞行器的辅助动力单元，包括具有液体冷却剂系统的内燃机，与内燃机驱动接合并具有与内燃机的液体冷却剂系统不同的液体冷却剂系统的发电机，第一热交换器 与所述内燃机的液体冷却剂系统流体连通的第二热交换器与所述发电机的液体冷却剂系统流体连通，与所述热交换器的空气通道流体连通的排气管道， 排气管道，并且可由内燃机旋转，用于驱动通过空气通道的冷却空气流。 发动机的液体冷却剂系统可以不同于辅助动力单元的燃料和润滑系统。 还讨论了一种冷却发电机和内燃机的方法。

公开(公告)号：US20160376021A1

公开(公告)日：2016-12-29

申请号：US14750179

申请日：2015-06-25

Applicant: Pratt & Whitney Canada Corp.

Inventor： Richard ULLYOTT ,  Anthony JONES ,  Andre JULIEN ,  Jean THOMASSIN

IPC: B64D41/00 ,  F01C21/00 ,  F01C21/06 ,  F01C21/08 ,  F04D29/32 ,  B64C13/40 ,  F04D29/46 ,  F04D29/56 ,  F01D5/06 ,  F04D29/58 ,  F04D27/00 ,  F01D15/10 ,  F01C1/22 ,  F04D29/28

Abstract: An auxiliary power unit for an aircraft, having a compressor, an intercooler including first conduit(s) having an inlet in fluid communication with the compressor outlet and second conduit(s) configured for circulation of a coolant therethrough, an engine core having an inlet in fluid communication with an outlet of the first conduit(s), and a bleed conduit in fluid communication with the outlet of the first conduit(s) through a bleed air valve. The auxiliary power unit may include a generator in driving engagement with the shaft of the engine core to provide electrical power for the aircraft. A method of providing compressed air and electrical power to an aircraft is also discussed.

Abstract translation: 一种用于飞机的辅助动力单元，具有压缩机，中间冷却器，包括具有与压缩机出口流体连通的入口的第一导管和构造成用于循环冷却剂的第二导管，具有入口 与第一导管的出口流体连通，以及通过排气阀与第一导管的出口流体连通的排放导管。 辅助动力单元可以包括与发动机芯的轴驱动接合的发电机，以为飞行器提供电力。 还讨论了向飞行器提供压缩空气和电力的方法。