公开(公告)号：US20200217248A1

公开(公告)日：2020-07-09

申请号：US16822396

申请日：2020-03-18

Applicant: PRATT & WHITNEY CANADA CORP.

Inventor： Andre JULIEN ,  Jean THOMASSIN ,  Serge DUSSAULT

IPC: F02C5/06 ,  F02C9/18 ,  F02K3/06 ,  F02C7/36 ,  F02B53/02 ,  F02C7/18 ,  F02C5/00 ,  F02C7/143 ,  F02K5/00

Abstract: A turbofan engine assembly including a compressor, an intermittent internal combustion engine having an inlet in fluid communication with an outlet of the compressor through at least one first passage of an intercooler, a turbine having an inlet in fluid communication with an outlet of the intermittent internal combustion engine, the turbine compounded with the intermittent internal combustion engine, a bypass duct surrounding the intermittent internal combustion engine, compressor and turbine, and a fan configured to propel air through the bypass duct and through an inlet of the compressor, wherein the intercooler is located in the bypass duct, the intercooler having at least one second passage in heat exchange relationship with the at least one first passage, the at least one second passage in fluid communication with the bypass duct.

公开(公告)号：US20200130534A1

公开(公告)日：2020-04-30

申请号：US16171473

申请日：2018-10-26

Applicant: PRATT & WHITNEY CANADA CORP.

Inventor： Andre JULIEN ,  Serge DUSSAULT

IPC: B60L58/27 ,  B64D27/02 ,  F01P3/12 ,  F01P3/20 ,  F01M5/00 ,  F01M1/02 ,  H01M10/613 ,  H01M10/663 ,  H01M10/6568 ,  H01M10/615 ,  H01M10/625

Abstract: A method of operating a hybrid electric power plant in cold climates comprises absorbing heat generated by an internal combustion engine, and using at least part of the heat absorbed from the internal combustion engine to warm a battery pack operatively connected to an electric motor.

公开(公告)号：US20190112973A1

公开(公告)日：2019-04-18

申请号：US16164148

申请日：2018-10-18

Applicant: PRATT & WHITNEY CANADA CORP.

Inventor： Sylvain LAMARRE ,  Mike FONTAINE ,  Andre JULIEN ,  Michael GAUL ,  Jean THOMASSIN ,  Lazar MITROVIC ,  Ilya MEDVEDEV ,  Sergey USIKOV ,  Andrey ZOLOTOV

IPC: F02B41/00 ,  F02C6/20 ,  F02C7/052 ,  F02C7/36 ,  F01C21/18 ,  F01C11/00 ,  F02C6/12

Abstract: A compound engine assembly with an inlet duct, a compressor, an engine core including at least one internal combustion engine, and a turbine section including a turbine shaft configured to compound power with the engine shaft. The turbine section may include a first stage turbine and a second stage turbine. The turbine shaft and the engine shaft are parallel to each other. The turbine shaft, the engine shaft and at least part of the inlet duct are all radially offset from one another. A method of driving a rotatable load of an aircraft is also discussed.

公开(公告)号：US20190107042A1

公开(公告)日：2019-04-11

申请号：US16177752

申请日：2018-11-01

Applicant: PRATT & WHITNEY CANADA CORP.

Inventor： Jean THOMASSIN ,  Andre JULIEN ,  Serge DUSSAULT

IPC: F02B19/10

Abstract: A method of combusting fuel, e.g. heavy fuel, in a rotary engine, including injecting a main quantity of fuel directly into a combustion chamber to form a first fuel-air mixture having a first air-fuel equivalence ratio λ higher than 1, injecting a pilot quantity of fuel into a pilot subchamber to form a second fuel-air mixture having a second air-fuel equivalence ratio λ smaller than the first air-fuel equivalence ratio, igniting the second fuel-air mixture within the pilot subchamber, using the ignited second fuel-air mixture from the pilot subchamber to ignite the first fuel-air mixture, and injecting a supplemental quantity of fuel directly into the combustion chamber after igniting the first fuel-air mixture, upstream of an exhaust port of the rotary engine with respect to a direction of rotation of the rotor. A rotary engine with interburner fuel injector is also discussed.

公开(公告)号：US20180106224A1

公开(公告)日：2018-04-19

申请号：US15294247

申请日：2016-10-14

Applicant: PRATT & WHITNEY CANADA CORP.

Inventor： Luc DIONNE ,  Bruno VILLENEUVE ,  Maxime COURTOIS ,  Behzad HAGSHENAS ,  Andre JULIEN

IPC: F02M35/08 ,  F02M35/10 ,  F02M35/02 ,  F02C7/04 ,  B01D46/00

Abstract: An inlet assembly for an auxiliary power unit for an aircraft, including a duct configured to provide fluid communication from an environment of the aircraft to an inlet of an engine of the auxiliary power unit, and a filter received in and extending across the duct. The filter includes a first filter portion permeable to air, positioned across only part of the duct and defining a transverse edge in the duct; a second filter portion permeable to air and extending from the transverse edge to an end downstream of the transverse edge, and a collection member impermeable to water. The collection member extends between the downstream end and a duct wall. The first and second filter portions are non-parallel and the second filter portion and the collection member are non-parallel. An auxiliary power unit assembly and a method of feeding air to an internal combustion engine are also discussed.

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：US20170267370A1

公开(公告)日：2017-09-21

申请号：US15616187

申请日：2017-06-07

Applicant: PRATT & WHITNEY CANADA CORP.

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

IPC: B64D41/00 ,  F02C3/10 ,  H02K7/18

CPC classification number: B64D41/00 ,  B64D2013/0611 ,  F01C1/22 ,  F01C11/008 ,  F02C3/10 ,  H02K7/1815 ,  H02K7/1823 ,  Y02T50/44 ,  Y02T50/53

Abstract: An engine assembly for use as an aircraft auxiliary power unit, having internal combustion engine(s) in driving engagement with an engine shaft, a generator having a generator shaft directly engaged to the engine shaft such as to be rotatable at a same speed, a compressor having an outlet in communication with the internal combustion engine inlet, and a turbine having an inlet in communication with the internal combustion engine outlet. The turbine may be a first stage turbine, and the assembly may include a second stage turbine having an inlet in communication with the first stage turbine outlet. A method of providing electrical power to an aircraft is also discussed.

公开(公告)号：US20170218783A1

公开(公告)日：2017-08-03

申请号：US15010634

申请日：2016-01-29

Applicant: Pratt & Whitney Canada Corp.

Inventor： Jean THOMASSIN ,  Marie-Claude VALLIERES ,  Mike FONTAINE ,  Andre JULIEN ,  John PERERA

IPC: F01D9/04 ,  F01D5/12 ,  F01D5/02 ,  F02B37/00 ,  F02B53/08

CPC classification number: F01D9/041 ,  F01D1/026 ,  F01D5/02 ,  F01D5/12 ,  F01D17/12 ,  F02B37/00 ,  F02B53/08 ,  F02B2053/005 ,  F05D2220/40 ,  F05D2260/961 ,  Y02T10/144

Abstract: An inlet guide assembly for a turbine receiving a pulsed flow, including a duct having an internal volume, and an inlet port, first outlet nozzle and second outlet nozzle each communicating with the internal volume. The inlet port is configured to receive at least part of the pulsed flow. The first and second outlet nozzles each define a respective nozzle area communicating between the internal volume and a flow path of the turbine. The first and second outlet nozzles are spaced from one another with the first outlet nozzle located closer to the inlet port than the second outlet nozzle relative to a flow direction through the duct, the nozzle area of the first outlet nozzle being smaller than the nozzle area of the second outlet nozzle. A compound engine assembly and method of introducing a pulsed flow into a flow path of a turbine are also discussed.

公开(公告)号：US20170037774A1

公开(公告)日：2017-02-09

申请号：US15227318

申请日：2016-08-03

Applicant: PRATT & WHITNEY CANADA CORP.

Inventor： Anthony JONES ,  Andre JULIEN ,  David MENHEERE ,  Jean THOMASSIN ,  Richard ULLYOTT ,  Daniel VAN DEN HENDE

IPC: F02B53/14 ,  F02B63/04 ,  F02B53/04

CPC classification number: F02B53/14 ,  B64D41/00 ,  F02B53/04 ,  F02B63/04 ,  Y02T50/53

Abstract: An auxiliary power unit for an aircraft includes a rotary intermittent internal combustion engine, a turbine having an inlet in fluid communication with an outlet of the engine, the turbine compounded with the engine, a compressor having an inlet in fluid communication with an environment of the aircraft and an outlet in fluid communication with the aircraft, the compressor rotatable independently of the turbine, an electric motor drivingly engaged to the compressor, and a transfer generator drivingly engaged to the engine, the transfer generator and the electric motor being electrically connected to allow power transfer therebetween. The compressor or an additional compressor may be in fluid communication with the inlet of the engine. A method of operating an auxiliary power unit of an aircraft is also discussed.

Abstract translation: 用于飞行器的辅助动力单元包括旋转间歇内燃机，具有与发动机的出口流体连通的入口的涡轮机，与发动机混合的涡轮，具有与所述发动机的环境流体连通的入口的压缩机 飞机和与飞机流体连通的出口，压缩机可独立于涡轮机旋转，驱动地接合到压缩机的电动机和驱动地接合到发动机的转移发电机，转移发电机和电动机电连接以允许 电力传输。 压缩机或额外的压缩机可以与发动机的入口流体连通。 还讨论了一种操作飞行器的辅助动力单元的方法。

公开(公告)号：US20170037756A1

公开(公告)日：2017-02-09

申请号：US15227506

申请日：2016-08-03

Applicant: PRATT & WHITNEY CANADA CORP.

Inventor： Andre JULIEN ,  Jean THOMASSIN ,  Serge DUSSAULT

IPC: F01N3/05 ,  F02B61/04 ,  B64D33/04 ,  F02B53/14 ,  F01N13/08 ,  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.

Abstract translation: 一种用于飞行器的涡轮螺旋桨发动机组件，包括具有液体冷却剂系统的内燃机，与飞行器的环境流体连通的空气管道;容纳在空气管道内的热交换器，其具有与液体冷却剂流体连通的冷却剂通道 系统和空气通道与空气管道流体连通的空气通道，以及与内燃机的排气流体连通的排气管道。 排气管道具有位于热交换器下游的空气管道中的出口和空气管道的出口的上游，排气管道的出口与空气管道的周壁隔开。 在使用中，冷却空气流围绕废气流。 还讨论了在具有内燃机的涡轮螺旋桨发动机组件中排出空气和废气的方法。