公开(公告)号：US20180010456A1

公开(公告)日：2018-01-11

申请号：US15205198

申请日：2016-07-08

Applicant: PRATT & WHITNEY CANADA CORP.

Inventor： Jean-Gabriel GAUVREAU ,  David Gagnon-Martin ,  Andre Julien

IPC: F01C21/08 ,  F02B37/00 ,  F02B53/08 ,  F01C1/22 ,  F02B53/00

CPC classification number: F01C21/08 ,  F01C1/22 ,  F01C21/106 ,  F02B37/00 ,  F02B53/08 ,  F02B2053/005 ,  F04C2250/20 ,  F04C2250/301

Abstract: A rotary engine where the rotor cavity has a peripheral inner surface having a peritrochoid configuration defined by a first eccentricity and the rotor has a peripheral outer surface having a peritrochoid inner envelope configuration defined by a second eccentricity larger than the first eccentricity. Also, a rotary engine where the rotor cavity has a peripheral inner surface having a peritrochoid configuration defined by an eccentricity, and a rotor with a peripheral outer surface between adjacent ones of the apex portions being inwardly offset from a peritrochoid inner envelope configuration defined by the eccentricity. The engine may have an expansion ratio with a value of at most 8. The rotary engine may be part of a compound engine system.

公开(公告)号：US09828906B2

公开(公告)日：2017-11-28

申请号：US15363099

申请日：2016-11-29

Applicant: PRATT & WHITNEY CANADA CORP.

Inventor： Jean Thomassin ,  Andre Julien ,  Edwin Schulz ,  Michael Lanktree

IPC: F02B53/00 ,  F02B53/06 ,  F01C1/22 ,  F01C20/06 ,  F01C20/10 ,  F01C20/24 ,  F01C21/08 ,  F01C21/10 ,  F01C21/18 ,  F02B53/04 ,  F02B53/02 ,  F02B55/16 ,  F01C11/00 ,  F01C21/06 ,  F04C29/00

CPC classification number: F02B53/06 ,  F01C1/22 ,  F01C11/006 ,  F01C20/06 ,  F01C20/10 ,  F01C20/24 ,  F01C21/06 ,  F01C21/08 ,  F01C21/106 ,  F01C21/18 ,  F01C21/183 ,  F02B53/02 ,  F02B53/04 ,  F02B55/16 ,  F02B2053/005 ,  F04C29/0092 ,  F04C2240/80

Abstract: A method of controlling an air intake flow in a rotary engine having primary and secondary inlet ports, including positioning the secondary inlet port rearwardly of the primary inlet port and forwardly of the exhaust port along a direction of a revolution of the rotor, and controlling air intake flows communicating between an air source and the primary and secondary inlet ports. During engine start-up, a primary valve is closed to prevent the intake air flow between the primary inlet port and the air source and a secondary valve is opened to allow the intake air flow between the secondary inlet port and the air source. A rotary engine defining different compression ratios through actuation of a valve is also discussed.

公开(公告)号：US09771165B2

公开(公告)日：2017-09-26

申请号：US14750207

申请日：2015-06-25

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 ,  F01C1/22 ,  F02C3/10 ,  F01C11/00 ,  B64D13/06

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

Abstract: A compound engine assembly for use as an aircraft auxiliary power unit, having an engine core including 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 engine core inlet, and a turbine section having an inlet in communication with the engine core outlet and configured to compound power with the engine core. The turbine section may include a first stage turbine having an inlet in communication with the engine core outlet, and 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：US11261781B2

公开(公告)日：2022-03-01

申请号：US16717422

申请日：2019-12-17

Applicant: PRATT & WHITNEY CANADA CORP.

Inventor： Serge Dussault ,  Andre Julien ,  Michael Lanktree ,  Edwin Schulz

IPC: F04C29/12 ,  F04C18/22 ,  F02B55/14 ,  F01C1/22 ,  F01C11/00 ,  F02B55/02 ,  F04B39/02 ,  F04B39/12 ,  F02B55/08 ,  F02B53/08 ,  F01C20/18 ,  F01C21/08 ,  F01C21/18 ,  F01C21/10 ,  F02B53/00 ,  F01C21/00

Abstract: A rotary internal combustion engine including a rotor assembly where at least a first and a second of the combustion chambers have unequal theoretical volumetric ratios. Also, a rotary internal combustion engine including first and second rotor assemblies where at least one of the combustion chambers of the first rotor assembly and at least one of the combustion chambers of the second rotor assembly have unequal effective volumetric compression ratios and/or unequal effective volumetric expansion ratios.

公开(公告)号：US11125185B2

公开(公告)日：2021-09-21

申请号：US16263113

申请日：2019-01-31

Applicant: PRATT & WHITNEY CANADA CORP.

Inventor： Sebastien Bergeron ,  Etienne Plamondon ,  Andre Julien

IPC: F02G5/02 ,  F01C1/22 ,  F01P3/12 ,  F01P3/20 ,  F01P5/12 ,  F01P5/14 ,  F02B3/06 ,  F02C7/12

Abstract: There is disclosed an engine assembly for an aircraft, including: a combustion engine including a coolant circuit in heat exchange relationship with a heat sink, the heat sink including a heat exchanger and at least one component, the at least one component having a main function that differs from thermal exchange. A method of operating the system is also disclosed.

公开(公告)号：US11002185B2

公开(公告)日：2021-05-11

申请号：US16366116

申请日：2019-03-27

Applicant: PRATT & WHITNEY CANADA CORP.

Inventor： Sebastien Bergeron ,  Andre Julien

IPC: F02B65/00 ,  F02B73/00

Abstract: There is disclosed a method of operating an engine assembly, including: driving a load with an internal combustion engine and an output of a turbine section, the turbine section driven by combustion gases from an exhaust the internal combustion engine; and injecting fuel upstream of the turbine section and downstream of the exhaust of the internal combustion engine. An engine assembly having a secondary injector for injecting fuel upstream of the turbine section and downstream of the combustion engine is also disclosed.

公开(公告)号：US10927734B2

公开(公告)日：2021-02-23

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

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：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.

公开(公告)号：US10801394B2

公开(公告)日：2020-10-13

申请号：US15825691

申请日：2017-11-29

Applicant: PRATT & WHITNEY CANADA CORP.

Inventor： Serge Dussault ,  Andre Julien ,  Michael Lanktree ,  Edwin Schulz

IPC: F01C1/00 ,  F01C1/22 ,  F01C21/18 ,  F02B19/10 ,  F02B53/02 ,  F02B53/10 ,  F02B53/12 ,  F02B53/00

Abstract: A rotary engine including at least two pilot subchambers each in parallel fluid communication with the internal cavity, so that each pilot subchamber is in fluid communication with the combustion chambers as the rotor rotates. Each of the at least two pilot subchambers in fluid communication with a corresponding pilot fuel injector. At least one ignition source is configured for igniting fuel in the pilot subchambers. A compound engine assembly and a method of combusting fuel in a rotary engine are also discussed.

公开(公告)号：US10590842B2

公开(公告)日：2020-03-17

申请号：US14750157

申请日：2015-06-25

Applicant: Pratt & Whitney Canada Corp.

Inventor： Richard Ullyott ,  Anthony Jones ,  Andre Julien ,  Jean Thomassin

IPC: F02B63/04 ,  B64D41/00 ,  F01C1/22 ,  F01C11/00 ,  F02B37/013 ,  F02B53/02 ,  F02C7/36 ,  B64D13/06 ,  F02B53/00

Abstract: A compound engine assembly for use as an auxiliary power unit for an aircraft and including an engine core with internal combustion engine(s), a compressor having an outlet in fluid communication with an engine core inlet, a bleed conduit in fluid communication with the compressor outlet through a bleed air valve, and a turbine section having an inlet in fluid communication with the engine core outlet and configured to compound power with the engine core. The turbine section may include a first stage turbine having an inlet in fluid communication with the engine core outlet and a second stage turbine having an inlet in fluid communication the first stage turbine outlet. A method of providing compressed air and electrical power to an aircraft is also discussed.