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公开(公告)号：US20180080371A1
公开(公告)日：2018-03-22
申请号：US15825683
申请日：2017-11-29
Applicant: PRATT & WHITNEY CANADA CORP.
Inventor： Serge DUSSAULT , Andre JULIEN , Michael LANKTREE , Edwin SCHULZ , Jean THOMASSIN , Nigel DAVENPORT , Eugene GEKHT
Abstract: A rotary engine including a rotor sealingly received within an internal cavity of an outer body to define a plurality of combustion chambers having a variable volume, a pilot subchamber located in a wall of the outer body, the pilot subchamber in fluid communication with the internal cavity via at least two spaced apart transfer holes defining a flow restriction between the pilot subchamber and the internal cavity, a pilot fuel injector in fluid communication with the pilot subchamber, an ignition element configured for igniting fuel in the pilot subchamber, and a main fuel injector extending through the stator body and communicating with the cavity at a location spaced apart from the pilot subchamber. A method of combusting fuel in a rotary engine is also discussed.
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公开(公告)号：US20170362998A1
公开(公告)日：2017-12-21
申请号：US15671221
申请日：2017-08-08
Applicant: Pratt & Whitney Canada Corp.
Inventor： Andre JULIEN , Serge DUSSAULT , Jade BILODEAU , Renaud BESNER
IPC: F02C3/06 , F02C5/02 , F02C5/00 , F02C3/00 , F02B39/02 , F01C1/22 , F02B37/00 , F01D1/02 , F01C11/00 , F02C6/12 , F02B53/04
CPC classification number: F02C3/06 , F01C1/22 , F01C11/002 , F01C11/008 , F01D1/026 , F02B37/00 , F02B39/02 , F02B53/04 , F02C3/00 , F02C5/00 , F02C5/02 , F02C6/12 , Y02T10/144 , Y02T10/17
Abstract: An engine assembly including an internal combustion engine, an impulse turbine, and an exhaust pipe providing fluid communication between the exhaust port of the internal combustion engine and the flow path of the turbine. The exhaust pipe terminates in a nozzle. A ratio Vp/Vd between the pipe volume Vp and the displacement volume Vd of the internal combustion engine is at most 1.5. A minimum value of a cross-sectional area of the exhaust pipe is defined at the nozzle. In one embodiment, a ratio An/Ae between the minimum cross-sectional area An and the cross-sectional area Ae of the exhaust port of the internal combustion engine is at least 0.2. A method of compounding at least one internal combustion engine is also discussed.
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公开(公告)号：US20170267341A1
公开(公告)日：2017-09-21
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
CPC classification number: B64C27/82 , B64C21/04 , B64C27/12 , B64C2027/8245 , B64D33/02 , B64D33/04 , B64D33/10 , B64D2033/024
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.
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公开(公告)号：US20170037775A1
公开(公告)日：2017-02-09
申请号：US15227496
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 ENDE
IPC: F02B53/14 , F02B61/06 , F02B33/40 , B64D41/00 , F02B39/12 , F02B39/10 , F02B37/10 , F02B63/04 , F02B37/24
CPC classification number: F02B53/14 , B64D41/00 , F02B33/40 , F02B37/10 , F02B37/24 , F02B39/10 , F02B39/12 , F02B61/06 , F02B63/04 , F02B2053/005 , F02C6/12 , F02C7/32 , F02C7/36 , F05D2220/50 , F05D2260/40 , Y02T10/144 , Y02T50/44 , Y02T50/671
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.
Abstract translation: 用于飞行器的辅助动力单元包括驱动地接合到发动机轴的旋转间歇内燃机，具有与发动机的出口流体连通的入口的涡轮部分，涡轮部分包括至少一个与 发动机轴和具有与飞行器的环境流体连通的入口的压缩机和与用于向飞行器提供放气的排气管流体连通的出口，压缩机具有连接到压缩机轴的压缩机转子， 压缩机轴驱动地接合到发动机轴。 压缩机轴和发动机轴之间的驱动接合可配置成在压缩机轴和发动机轴之间提供至少两个交替的速比。
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35.发明申请AIRCRAFT HEATING ASSEMBLY WITH LIQUID COOLED INTERNAL COMBUSTION ENGINE AND HEATING ELEMENT USING WASTE HEAT 审中-公开飞机加热组件与液体冷却内燃机和加热元件使用废热公开(公告)号：US20170036775A1
公开(公告)日：2017-02-09
申请号：US15227501
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
CPC classification number: B64D33/10 , B64D15/06 , B64D33/08 , B64D41/00 , B64D2033/0213 , B64D2033/0233 , B64F5/20 , F01P3/20 , F01P7/16 , F01P2025/08 , F01P2050/20 , F01P2060/18 , F05D2220/50 , F05D2260/213 , Y02P70/585 , Y02T50/675
Abstract: An aircraft heating assembly including an internal combustion engine having a liquid coolant system distinct from any fuel and lubricating system of the engine and including cooling passages in the internal combustion engine for circulating a liquid coolant from a coolant inlet to a coolant outlet, a coolant circulation path outside of the internal combustion engine and in fluid communication with the coolant inlet and the coolant outlet, and a heating element in heat exchange relationship with a portion of the aircraft to be heated. The coolant circulation path extends through a heat exchanger configured to remove a portion of a waste heat from the liquid coolant. The heating element is in heat exchange relationship with the coolant circulation path to receive another portion of the waste heat therefrom. A method of heating a portion of an aircraft is also discussed.
Abstract translation: 一种飞机加热组件，包括具有与发动机的任何燃料和润滑系统不同的液体冷却剂系统的内燃机，并且包括用于将液体冷却剂从冷却剂入口循环到冷却剂出口的内燃机中的冷却通道，冷却剂循环 并且与冷却剂入口和冷却剂出口流体连通，以及与被加热飞机的一部分热交换的加热元件。 冷却剂循环路径延伸穿过构造成从液体冷却剂中去除一部分废热的热交换器。 加热元件与冷却剂循环路径处于热交换关系，以从其中接收另一部分废热。 还讨论了加热飞机的一部分的方法。
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Patent Agency Ranking
公开(公告)号：US20170036773A1
公开(公告)日：2017-02-09
申请号：US15212883
申请日：2016-07-18
Applicant: PRATT & WHITNEY CANADA CORP.
Inventor： Anthony JONES , Andre JULIEN , David MENHEERE , Jean THOMASSIN , Richard ULLYOTT , Daniel VAN DEN HENDE
CPC classification number: B64D31/06 , B64D27/10 , B64D27/16 , B64D41/00 , B64D2221/00
Abstract: There is described herein methods and systems for selective use of an auxiliary power source inflight in order to reduce fuel consumption of an aircraft.
Abstract translation: 这里描述了用于选择性地使用辅助动力源飞行器以减少飞行器的燃料消耗的方法和系统。
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公开(公告)号：US20160376023A1
公开(公告)日：2016-12-29
申请号：US14750207
申请日：2015-06-25
Applicant: Pratt & Whitney Canada Corp.
Inventor： Richard ULLYOTT , Anthony JONES , Andre JULIEN , Jean THOMASSIN
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.
Abstract translation: 一种用作飞机辅助动力单元的复合发动机组件，其具有包括与发动机轴驱动接合的内燃机的发动机芯，具有直接接合到发动机轴的发电机轴，该发电机轴可以在 相同的速度，具有与发动机芯入口连通的出口的压缩机，以及涡轮部分，其具有与发动机芯出口连通的入口并且被配置成与发动机芯体相互补给动力。 涡轮机部分可以包括具有与发动机芯出口连通的入口的第一级涡轮机和具有与第一级涡轮机出口连通的入口的第二级涡轮机。 还讨论了向航空器提供电力的方法。
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公开(公告)号：US20200318547A1
公开(公告)日：2020-10-08
申请号：US16891187
申请日：2020-06-03
Applicant: PRATT & WHITNEY CANADA CORP.
Inventor： Richard ULLYOTT , Anthony JONES , Andre JULIEN , Jean THOMASSIN
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.
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公开(公告)号：US20190186352A1
公开(公告)日：2019-06-20
申请号：US16282754
申请日：2019-02-22
Applicant: PRATT & WHITNEY CANADA CORP.
Inventor： Anthony JONES , Andre JULIEN , Jean THOMASSIN , Richard ULLYOTT , David MENHEERE
IPC: F02B63/04 , F01C21/18 , F02B53/14 , F02B37/00 , F01P5/06 , F01P5/04 , F01P1/06 , B64D33/08 , B64D41/00 , F02B63/06 , F02B67/04 , F02B53/02 , F02C7/18 , F02C7/14 , F02C5/00 , F02K5/00 , F01C1/22
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.
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公开(公告)号：US20190186351A1
公开(公告)日：2019-06-20
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 , F02B61/06 , F02B39/12 , F02C7/36 , F02B37/24 , F02B37/10 , F02B33/40 , F02C6/12 , B64D41/00 , F02B63/04 , F02B39/10 , F02C7/32
CPC classification number: F02B53/14 , B64D41/00 , F02B33/40 , F02B37/10 , F02B37/24 , F02B39/10 , F02B39/12 , F02B61/06 , F02B63/04 , F02B2053/005 , F02C6/12 , F02C7/32 , F02C7/36 , F05D2220/50 , F05D2260/40 , Y02T10/144 , Y02T50/44 , Y02T50/671
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.
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