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公开(公告)号：US20200309025A1
公开(公告)日：2020-10-01
申请号：US16366116
申请日：2019-03-27
Applicant: PRATT & WHITNEY CANADA CORP.
Inventor： Sebastien BERGERON , Andre JULIEN
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.
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公开(公告)号：US20190203620A1
公开(公告)日：2019-07-04
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 , B64D27/08 , B64D33/04 , F02B61/04 , F02B53/14 , F01N13/08 , B64D27/02 , F02C7/18 , F02C6/20 , F02C5/00 , F02K1/38 , B64D33/10 , B64D27/10
CPC classification number: F01N3/055 , B64D27/02 , B64D27/08 , B64D27/10 , B64D33/04 , B64D33/10 , F01N13/082 , F01N2260/022 , F01N2270/02 , F02B53/14 , F02B61/04 , F02B2053/005 , F02C5/00 , F02C6/206 , F02C7/18 , F02K1/386 , F05D2260/213 , Y02T50/672 , Y02T50/676
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.
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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：US20180187591A1
公开(公告)日：2018-07-05
申请号：US15849991
申请日：2017-12-21
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 , F02C7/055 , F01C11/00 , F01C21/18 , F02B37/12 , F02B39/04 , F02B53/08 , F02M31/10 , F02M31/04 , F02C7/36 , F02C7/14 , F02C7/052 , F02C7/047 , F02C6/12 , 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.
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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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Patent Agency Ranking
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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7.发明申请COMPOUND ENGINE ASSEMBLY WITH COAXIAL COMPRESSOR AND OFFSET TURBINE SECTION 有权复合发动机组件与同轴压缩机和偏心涡轮机部分公开(公告)号：US20160245166A1
公开(公告)日：2016-08-25
申请号：US14806880
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 , Jade BILODEAU , Andre JULIEN , Pierre-Yves LEGARE , Jason NICHOLS
CPC classification number: F02B53/14 , F01C1/22 , F01C11/008 , F01C21/18 , F02B29/0418 , F02B33/40 , F02B39/04 , F02B41/10 , F02B2053/005 , F02C3/04 , F02C3/107 , F02C6/00 , F02C6/12 , F02C6/20 , F02C7/047 , F02C7/052 , F02C7/055 , F02C7/14 , F02C7/36 , F02M31/042 , F02M31/10 , F02M31/107 , F05D2250/312 , F05D2260/40311 , F05D2260/98 , Y02T10/126 , Y02T10/146 , Y02T10/163 , Y02T10/17 , Y02T50/675
Abstract: A compound engine assembly having an engine core including at least one internal combustion engine in driving engagement with an engine shaft, a compressor having an outlet in fluid communication with an inlet of the engine core and including at least one rotor rotatable about an axis coaxial with the engine shaft, the engine shaft in driving engagement with the compressor rotor, and a turbine section having an inlet in fluid communication with an outlet of the engine core and including at least one rotor engaged on a rotatable turbine shaft, the turbine shaft configured to compound power with the engine shaft. The turbine and engine shafts are parallel to and radially offset from one another, and the turbine shaft and the axis of the compressor rotor are parallel to and radially offset from one another. A method of driving a rotatable load of an aircraft is also discussed.
Abstract translation: 一种复合发动机组件，其具有包括与发动机轴驱动接合的至少一个内燃机的发动机机芯，具有与发动机机芯的入口流体连通的出口的压缩机，并且包括至少一个转子， 发动机轴，与压缩机转子驱动接合的发动机轴，以及涡轮部，其具有与发动机芯的出口流体连通的入口，并且包括接合在可旋转的涡轮轴上的至少一个转子，所述涡轮轴被配置为 与发动机轴组合动力。 涡轮机和发动机轴彼此平行并径向偏移，并且涡轮轴和压缩机转子的轴线彼此平行并径向偏移。 还讨论了驱动飞行器的可旋转载荷的方法。
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8.发明申请公开(公告)号：US20160245165A1
公开(公告)日：2016-08-25
申请号：US15143974
申请日：2016-05-02
Applicant: Pratt & Whitney Canada Corp.
Inventor： Michael GAUL , Andre JULIEN , Bruno VILLENEUVE
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.
Abstract translation: 一种旋转发动机，其包括在外体的一个壁中的插入件。 插入件具有限定在其中的引导子室，其与内部空腔连通并且包括围绕引导子室的子室壁。 主燃料喷射器在与插入件间隔开的位置处与内腔连通。 先导燃料喷射器与导向子室连通。 加热元件在子室壁内完全延伸到导向子室外部，与子室壁的热传递连通。 还提供了用于旋转发动机的外体和在旋转发动机中燃烧燃料的方法。
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9.发明申请COMPOUND ENGINE ASSEMBLY WITH OFFSET TURBINE SHAFT, ENGINE SHAFT AND INLET DUCT 审中-公开复合发动机组件与偏置涡轮轴，发动机轴和入口导管公开(公告)号：US20160245162A1
公开(公告)日：2016-08-25
申请号：US14864096
申请日：2015-09-24
Applicant: PRATT & WHITNEY CANADA CORP.
Inventor： Sylvain LAMARRE , Mike FONTAINE , Andre JULIEN , Michael GAUL , Jean THOMASSIN , Lazar MITROVIC , Ilya B. MEDVEDEV , Sergey USIKOV , Andrey ZOLOTOV
CPC classification number: F02B41/00 , F01C1/22 , F01C11/008 , F01C21/18 , F02C6/12 , F02C6/206 , F02C7/052 , F02C7/36 , F05B2220/40 , F05D2220/323 , F05D2230/51 , F05D2230/72 , F05D2250/312 , F05D2260/4031 , F05D2300/121 , F05D2300/171
Abstract: A compound engine assembly with an inlet duct, a compressor, an engine core including at least one internal combustion engine, and a turbine section including a turbine shaft 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 and the engine shaft are parallel to each other. The turbine shaft, the engine shaft and at least part of the inlet duct are all radially offset from one another. A method of driving a rotatable load of an aircraft is also discussed.
Abstract translation: 具有入口管道，压缩机，包括至少一个内燃机的发动机核心的复合发动机组件和包括被配置为与发动机轴组合动力的涡轮轴的涡轮部分。 涡轮机部分可以包括第一级涡轮机和第二级涡轮机。 涡轮轴和发动机轴彼此平行。 涡轮机轴，发动机轴和入口管道的至少一部分都相互径向偏移。 还讨论了驱动飞行器的可旋转载荷的方法。
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公开(公告)号：US20210010414A1
公开(公告)日：2021-01-14
申请号：US17031967
申请日：2020-09-25
Applicant: PRATT & WHITNEY CANADA CORP.
Inventor： Andre JULIEN , Edwin SCHULZ
Abstract: A method of operating a rotary engine including a rotor engaged to a shaft and rotationally received in a housing to define a plurality of working chambers of variable volume, including delivering a pilot quantity of fuel into a pilot cavity in successive communication with the working chambers, igniting the pilot quantity of fuel within the pilot cavity, and delivering a main quantity of fuel into the working chambers downstream of the successive communication of the pilot cavity with the working chambers, where at least one of the pilot quantity and the main quantity is varied between successive rotations of the shaft.
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