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公开(公告)号：US20170037776A1
公开(公告)日：2017-02-09
申请号：US15227483
申请日：2016-08-03
Applicant: PRATT & WHITNEY CANADA CORP.
Inventor： Anthony JONES , Andre JULIEN , David MENHEERE , Jean THOMASSIN , Richard ULLYOTT
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.
Abstract translation: 一种用于飞行器的辅助动力单元，包括具有液体冷却剂系统的内燃机，与内燃机驱动接合并具有与内燃机的液体冷却剂系统不同的液体冷却剂系统的发电机，第一热交换器 与所述内燃机的液体冷却剂系统流体连通的第二热交换器与所述发电机的液体冷却剂系统流体连通，与所述热交换器的空气通道流体连通的排气管道， 排气管道，并且可由内燃机旋转，用于驱动通过空气通道的冷却空气流。 发动机的液体冷却剂系统可以不同于辅助动力单元的燃料和润滑系统。 还讨论了一种冷却发电机和内燃机的方法。
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公开(公告)号：US20160376021A1
公开(公告)日：2016-12-29
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 , F01C21/00 , F01C21/06 , F01C21/08 , F04D29/32 , B64C13/40 , F04D29/46 , F04D29/56 , F01D5/06 , F04D29/58 , F04D27/00 , F01D15/10 , F01C1/22 , F04D29/28
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.
Abstract translation: 一种用于飞机的辅助动力单元，具有压缩机，中间冷却器，包括具有与压缩机出口流体连通的入口的第一导管和构造成用于循环冷却剂的第二导管，具有入口 与第一导管的出口流体连通，以及通过排气阀与第一导管的出口流体连通的排放导管。 辅助动力单元可以包括与发动机芯的轴驱动接合的发电机，以为飞行器提供电力。 还讨论了向飞行器提供压缩空气和电力的方法。
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公开(公告)号：US20180346142A1
公开(公告)日：2018-12-06
申请号：US16004991
申请日：2018-06-11
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: An auxiliary power unit having internal combustion engine(s) in driving engagement with an engine shaft, a generator having a generator shaft drivingly engaged to the engine shaft, 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.
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公开(公告)号：US20160376981A1
公开(公告)日：2016-12-29
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 , F01C11/00 , F02C7/36 , F02B53/02 , F02B37/013
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.
Abstract translation: 一种用作飞行器的辅助动力单元并且包括具有内燃机的发动机芯的复合发动机组件，具有与发动机芯入口流体连通的出口的压缩机，与压缩机流体连通的排放管道 出口通过放气阀，以及涡轮部分，其具有与发动机芯出口流体连通的入口并且被配置成与发动机芯组合功率。 涡轮机部分可以包括具有与发动机芯出口流体连通的入口的第一级涡轮机和具有与第一级涡轮机出口流体连通的入口的第二级涡轮机。 还讨论了向飞行器提供压缩空气和电力的方法。
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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
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.
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Patent Agency Ranking
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
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。
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公开(公告)号：US20190218998A1
公开(公告)日：2019-07-18
申请号：US16359152
申请日：2019-03-20
Applicant: PRATT & WHITNEY CANADA CORP.
Inventor： Andre JULIEN , Jean THOMASSIN , Maxime COURTOIS , Bruno VILLENEUVE , Richard ULLYOTT , Serge DUSSAULT , Luc DIONNE , Serge LAFORTUNE , Anthony JONES , Behzad HAGSHENAS , David H. MENHEERE
IPC: F02K1/38 , B64D41/00 , F02K1/82 , F01C1/22 , F01C21/18 , F01N3/05 , F01P5/02 , F01P11/10 , F02B53/02 , F02B63/04 , F02B63/06 , F02B67/04 , F02C5/00 , F02K5/00 , F02C7/18 , F02C7/14
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：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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9.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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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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