公开(公告)号：US10934930B2

公开(公告)日：2021-03-02

申请号：US16284381

申请日：2019-02-25

Applicant: PRATT & WHITNEY CANADA CORP.

Inventor： Anthony Jones ,  Andre Julien ,  David Menheere ,  Jean Thomassin ,  Richard Ullyott ,  Daniel Van Den Ende

IPC: F02B53/14 ,  B64D41/00 ,  F02B33/40 ,  F02B37/10 ,  F02B37/24 ,  F02B39/10 ,  F02B39/12 ,  F02B61/06 ,  F02B63/04 ,  F02C6/12 ,  F02C7/32 ,  F02C7/36 ,  F02B53/00

Abstract: An auxiliary power unit for an aircraft includes a rotary intermittent internal combustion engine drivingly engaged to an engine shaft, a turbine section having an inlet in fluid communication with an outlet of the engine(s), the turbine section including at least one turbine compounded with the engine shaft, and a compressor having an inlet in fluid communication with an environment of the aircraft and an outlet in fluid communication with a bleed duct for providing bleed air to the aircraft, the compressor having a compressor rotor connected to a compressor shaft, the compressor shaft drivingly engaged to the engine shaft. The driving engagement between the compressor shaft and the engine shaft is configurable to provide at least two alternate speed ratios between the compressor shaft and the engine shaft.

公开(公告)号：US10724429B2

公开(公告)日：2020-07-28

申请号：US16227141

申请日：2018-12-20

Applicant: PRATT & WHITNEY CANADA CORP.

Inventor： Anthony Jones ,  Andre Julien ,  David Menheere ,  Jean Thomassin ,  Richard Ullyott ,  Daniel Van Den Ende

IPC: F02B53/14 ,  B64D41/00 ,  F02B53/04 ,  F02B63/04

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.

公开(公告)号：US10710738B2

公开(公告)日：2020-07-14

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 ,  F01C1/22 ,  F02B63/04 ,  F02B41/10 ,  F02C7/32 ,  F02C7/36 ,  F02B33/40 ,  F02B55/00 ,  F01D17/20 ,  B64D33/08 ,  B64D13/06 ,  F02C6/08 ,  F01C11/00 ,  F02C9/18 ,  F01C21/00 ,  F01C21/06 ,  F02C7/06 ,  F01D25/18

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.

公开(公告)号：US10598086B2

公开(公告)日：2020-03-24

申请号：US15849977

申请日：2017-12-21

Applicant: PRATT & WHITNEY CANADA CORP.

Inventor： Sylvain Lamarre ,  Mike Fontaine ,  Andre Julien ,  Michael Gaul ,  Jean Thomassin ,  Lazar Mitrovic

IPC: F02B41/10 ,  F01C1/22 ,  F01C11/00 ,  F01D25/16 ,  F02C6/12 ,  F02C6/20 ,  F02C7/36 ,  F01C13/04 ,  F01C21/00 ,  F02B53/02 ,  F02B53/10 ,  F02B53/00

Abstract: A compound engine assembly with an engine core including at least one internal combustion engine, a compressor, and a turbine section where the turbine shaft is 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 is rotationally supported by a plurality of bearings all located on a same side of the compressor rotor(s) and all located on a same side of the turbine rotor(s), for example all located between the compressor rotor(s) and the turbine rotor(s), such that the compressor rotor(s) and the turbine rotor(s) are cantilevered. A method of driving a rotatable load of an aircraft is also discussed.

公开(公告)号：US10508626B2

公开(公告)日：2019-12-17

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: B64D33/02 ,  F02C7/04 ,  F02M35/08 ,  B01D46/00 ,  F02M35/02 ,  F02M35/10

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：US10458325B2

公开(公告)日：2019-10-29

申请号：US15926568

申请日：2018-03-20

Applicant: PRATT & WHITNEY CANADA CORP.

Inventor： Michael Gaul ,  Andre Julien ,  Bruno Villeneuve

IPC: F02B53/12 ,  F02B19/10 ,  F02B55/08 ,  F01C1/22 ,  F02B53/10 ,  F02B19/12 ,  F02B53/02 ,  F02M53/02 ,  F02P19/02 ,  F02B55/14 ,  F02B53/00

Abstract: A rotary engine includes an insert having a pilot subchamber defined therein and communicating with the internal cavity of the engine. A pilot fuel injector has a tip in communication with the pilot subchamber. An ignition element extends into an element cavity defined through the insert adjacent the pilot subchamber. The element cavity is in communication with the pilot subchamber through a communication opening defined in the insert between the element cavity and the pilot subchamber. The communication opening is smaller than a portion of the ignition element adjacent the communication opening such as to prevent the portion of the ignition element from completely passing through the communication opening upon breaking off of the portion of the ignition element from a remainder of the ignition element. An outer body for a rotary engine and a method of combusting fuel in a rotary engine are also provided.

公开(公告)号：US10118695B2

公开(公告)日：2018-11-06

申请号：US15074454

申请日：2016-03-18

Applicant: Pratt & Whitney Canada Corp.

Inventor： Jean Thomassin ,  Serge Dussault ,  Andre Julien ,  Gordon Saby ,  Richard Ullyott

IPC: B64C27/82 ,  B64C21/04 ,  B64C27/12 ,  B64D33/04 ,  B64D33/02

Abstract: A directional control system for a rotorcraft having a tail boom including a no-tail-rotor apparatus configured to control rotorcraft yaw using forced air ejected from the tail boom and a duct configured to deliver the forced air to the no-tail-rotor apparatus. The directional control system comprises a heat exchanger having air passages and fluid passages, the air passages in fluid communication with the duct, the fluid passages in heat exchange relationship with the air passages and configured for receiving a cooling fluid, and a forced air driver in fluid communication with the duct for driving the forced air through the duct to the no-tail-rotor apparatus. Methods of providing directional control in a rotorcraft are also discussed.

公开(公告)号：US10006359B2

公开(公告)日：2018-06-26

申请号：US15143974

申请日：2016-05-02

Applicant: Pratt & Whitney Canada Corp.

Inventor： Michael Gaul ,  Andre Julien ,  Bruno Villeneuve

IPC: F02B53/12 ,  F01C1/22 ,  F02B19/10 ,  F02B53/10 ,  F02B55/08 ,  F02B19/12 ,  F02B53/02 ,  F02M53/02 ,  F02P19/02 ,  F02B55/14 ,  F02B53/00

CPC classification number: F02B53/12 ,  F01C1/22 ,  F02B19/108 ,  F02B19/12 ,  F02B53/02 ,  F02B53/10 ,  F02B55/08 ,  F02B55/14 ,  F02B2053/005 ,  F02M53/02 ,  F02P19/02 ,  Y02T10/125 ,  Y02T10/17

Abstract: A rotary engine including an insert in one of the walls of the outer body. The insert has a pilot subchamber defined therein communicating with the internal cavity and includes a subchamber wall surrounding the pilot subchamber. A main fuel injector is in communication with the internal cavity at a location spaced apart from the insert. A pilot fuel injector is in communication with the pilot subchamber. A heating element extends within the subchamber wall completely outside of the pilot subchamber, in heat transfer communication with the subchamber wall. An outer body for a rotary engine and a method of combusting fuel in a rotary engine are also provided.

公开(公告)号：US09994332B2

公开(公告)日：2018-06-12

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: F01D15/10 ,  F02C6/00 ,  H02K7/18 ,  H02P9/04 ,  B64D41/00 ,  F02C3/10 ,  F01C11/00 ,  F01C1/22 ,  F03G7/00 ,  B64D13/06

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：US09879591B2

公开(公告)日：2018-01-30

申请号：US14806883

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

CPC classification number: F02B29/0406 ,  F01C1/22 ,  F01C11/008 ,  F01C21/18 ,  F02B29/0412 ,  F02B33/40 ,  F02B37/12 ,  F02B39/04 ,  F02B53/08 ,  F02B53/14 ,  F02C6/12 ,  F02C7/047 ,  F02C7/052 ,  F02C7/055 ,  F02C7/14 ,  F02C7/36 ,  F02M31/042 ,  F02M31/10 ,  F02M31/107 ,  F05D2250/312 ,  F05D2260/40311 ,  F05D2260/98 ,  Y02T10/126 ,  Y02T10/17 ,  Y02T50/675

Abstract: An intake assembly for a compressor providing compressed air to an internal combustion engine core, including an air conduit having at least one heat exchanger extending thereacross, an intake plenum for the compressor, a first intake conduit connected to the air conduit upstream of the heat exchanger(s), a second intake conduit connected to the air conduit downstream of the heat exchanger(s), and a selector valve configurable between a first configuration to allow a fluid communication between the intake plenum and the air conduit through the first intake conduit and a second configuration to prevent the fluid communication through the first intake conduit. Fluid communication between the intake plenum and the air conduit through the second intake conduit is allowed at least when the selector valve is in the second configuration. An engine assembly and method of supplying air to a compressor are also discussed.