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公开(公告)号：US20170226959A1
公开(公告)日：2017-08-10
申请号：US15227519
申请日：2016-08-03
Applicant: PRATT & WHITNEY CANADA CORP.
Inventor： Andre JULIEN , Jean THOMASSIN , Maxime COURTOIS , Bruno VILLENEUVE , Serge DUSSAULT , Richard ULLYOTT , Serge LAFORTUNE , Luc DIONNE , Anthony JONES , Behzad HAGSHENAS , David MENHEERE
CPC classification number: F02K1/386 , B64D41/00 , B64D2041/002 , F01C1/22 , F01C21/18 , F01N3/05 , F01P5/02 , F01P11/10 , F02B53/02 , F02B63/04 , F02B63/06 , F02B67/04 , F02B2053/005 , F02C5/00 , F02C7/14 , F02C7/18 , F02K1/82 , F02K5/00 , F05D2220/50 , F05D2260/213 , F05D2300/173 , F05D2300/43 , F05D2300/603 , Y02T10/17 , Y02T50/53 , Y02T50/672 , Y02T50/676
Abstract: An engine assembly for an aircraft, including an internal combustion engine having a liquid coolant system in fluid communication with a heat exchanger, an exhaust duct in fluid communication with air passages of the heat exchanger, a fan in fluid communication with the exhaust duct for driving a cooling air flow through the air passages of the heat exchanger and into the exhaust duct, and an intermediate duct in fluid communication with an exhaust of the engine and having an outlet positioned within the exhaust duct downstream of the fan and upstream of the outlet of the exhaust duct. The outlet of the intermediate duct is spaced inwardly from a peripheral wall of the exhaust duct. The engine assembly may be configured as an auxiliary power unit. A method of discharging air and exhaust gases in an auxiliary power unit having an internal combustion engine is also discussed.
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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.
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公开(公告)号：US20190003430A1
公开(公告)日：2019-01-03
申请号：US15666773
申请日：2017-08-02
Applicant: PRATT & WHITNEY CANADA CORP.
Inventor： Luc DIONNE , Bruno VILLENEUVE , Andre JULIEN , Serge DUSSAULT
CPC classification number: F02M35/10268 , F01P3/18 , F01P3/20 , F01P7/14 , F01P11/12 , F01P2001/005 , F02B33/38 , F02B37/00 , F02M35/10157 , F02M35/10203
Abstract: An engine assembly includes an engine compartment containing an internal combustion engine and a cooler compartment adjacent the engine compartment containing a heat exchanger. The engine and cooler compartments have an opening defined therebetween. A forced air system is operable to drive an airflow. A method for cooling the engine and its compartment is disclosed.
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公开(公告)号：US20190186334A1
公开(公告)日：2019-06-20
申请号：US15846652
申请日：2017-12-19
Applicant: PRATT & WHITNEY CANADA CORP.
Inventor： Luc DIONNE
Abstract: An aircraft engine assembly having a turbo-compounded internal combustion engine having an engine shaft. A coolant cooler is fluidly connected to a coolant circuitry of the internal combustion engine and to the environment. A plenum is connected with the environment via the coolant cooler and via an air outlet. A fan is disposed adjacent the air outlet and is operable to drive an airflow from the environment into the plenum via the coolant cooler. The fan is spaced apart from the internal combustion engine in a direction perpendicular to the engine shaft. A method of defining a cooling air circulation is also discussed.
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公开(公告)号：US20180106225A1
公开(公告)日：2018-04-19
申请号：US15294285
申请日：2016-10-14
Applicant: PRATT & WHITNEY CANADA CORP.
Inventor： Luc DIONNE , Bruno VILLENEUVE , Maxime COURTOIS , Behzad HAGSHENAS , Andre JULIEN
IPC: F02M35/10 , F02M35/024 , F02B53/14
Abstract: An inlet assembly for an auxiliary power unit for an aircraft, including a particle separator and a plenum having first and second inlets. A first duct configured to deliver air to an engine of the auxiliary power unit is in fluid communication with an outlet of the plenum. A second duct configured to deliver air to a compartment containing the auxiliary power unit is in fluid communication with the outlet of the plenum. The assembly is selectively configurable between a first configuration where the plenum is in fluid communication with the environment of the aircraft through the second inlet and through the particle separator, and a second configuration where the plenum is in fluid communication with the environment of the aircraft through the first inlet independently of the particle separator. An auxiliary power unit assembly and a method of feeding air to an auxiliary power unit assembly are also discussed.
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Patent Agency Ranking
公开(公告)号：US20180105283A1
公开(公告)日：2018-04-19
申请号：US15294298
申请日：2016-10-14
Applicant: PRATT & WHITNEY CANADA CORP.
Inventor： Luc DIONNE , Bruno VILLENEUVE , Maxime COURTOIS , Behzad HAGSHENAS , Andre JULIEN
Abstract: An auxiliary power unit assembly for an aircraft, including an engine assembly including an internal combustion engine, a first duct in fluid communication with an inlet of the internal combustion engine and configured to be in fluid communication with an environment of the aircraft, and a second duct configured to be in fluid communication with the environment. The second duct may be in fluid communication with an inlet of a compressor drivable by the internal combustion engine or with a compartment receiving the engine assembly. A filter extends across the first duct. The filter is removable from the first duct through an opening in a wall of the first duct, the opening accessible from an exterior of the engine assembly.
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公开(公告)号：US20210317742A1
公开(公告)日：2021-10-14
申请号：US16842981
申请日：2020-04-08
Applicant: PRATT & WHITNEY CANADA CORP.
Inventor： Luc DIONNE
Abstract: A method of cooling an aircraft power plant having a combustion engine is disclosed. The method comprises in a first operating mode, inducing a cooling air flow through a heat exchanger in an air conduit via a flow inducing device fluidly connected to the air conduit, the heat exchanger connected in heat exchange relationship with the power plant of the aircraft. The method comprises, in a second operating mode, bypassing the cooling air flow from the flow inducing device via a selectively closable air outlet of the air conduit downstream of the heat exchanger. A cooling system for an aircraft power plant is also disclosed.
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公开(公告)号：US20190256214A1
公开(公告)日：2019-08-22
申请号：US15898741
申请日：2018-02-19
Applicant: PRATT & WHITNEY CANADA CORP.
Inventor： Luc DIONNE , Bruno VILLENEUVE , Jean THOMASSIN
IPC: B64D27/08 , F02B53/14 , F02B41/10 , B64C25/16 , B64C25/14 , B64C25/34 , B64D29/04 , B64D33/08 , B64D35/02
Abstract: An assembly for an aircraft having a propeller, including a wheel well configured for receiving a retracted landing gear, the wheel well including walls and a closable bottom opening for deploying the landing gear therethrough, an engine assembly having an engine shaft configured for driving engagement with the propeller, and a mount assembly for supporting the engine assembly, the mount assembly connected to at least one of the walls of the wheel well. A method of supporting an engine assembly in an aircraft having a retractable landing gear and a propeller driven by the engine assembly is also discussed.
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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
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.
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公开(公告)号：US20220112846A1
公开(公告)日：2022-04-14
申请号：US17070154
申请日：2020-10-14
Applicant: PRATT & WHITNEY CANADA CORP.
Inventor： Luc DIONNE
Abstract: An aircraft propulsion system comprises an engine, a propeller drive shaft drivingly engaged with the engine, a propeller for propelling an aircraft and a fan driving cooling air along a flow path in thermal communication with the engine. The engine may be an internal combustion engine or other engine type having heat rejection requirements and the fan may facilitate cooling of the engine. The propulsion system may have a pusher configuration.
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