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    TURBOFAN ENGINE ASSEMBLY WITH INTERCOOLER
    4.
    发明申请
    TURBOFAN ENGINE ASSEMBLY WITH INTERCOOLER 审中-公开

    公开(公告)号：US20200217248A1

    公开(公告)日：2020-07-09

    申请号：US16822396

    申请日：2020-03-18

    Applicant: PRATT & WHITNEY CANADA CORP.

    Inventor： Andre JULIEN ,  Jean THOMASSIN ,  Serge DUSSAULT

    IPC: F02C5/06 ,  F02C9/18 ,  F02K3/06 ,  F02C7/36 ,  F02B53/02 ,  F02C7/18 ,  F02C5/00 ,  F02C7/143 ,  F02K5/00

    Abstract: A turbofan engine assembly including a compressor, an intermittent internal combustion engine having an inlet in fluid communication with an outlet of the compressor through at least one first passage of an intercooler, a turbine having an inlet in fluid communication with an outlet of the intermittent internal combustion engine, the turbine compounded with the intermittent internal combustion engine, a bypass duct surrounding the intermittent internal combustion engine, compressor and turbine, and a fan configured to propel air through the bypass duct and through an inlet of the compressor, wherein the intercooler is located in the bypass duct, the intercooler having at least one second passage in heat exchange relationship with the at least one first passage, the at least one second passage in fluid communication with the bypass duct.

    ROTARY ENGINE AND METHOD OF COMBUSTING FUEL
    6.
    发明申请
    ROTARY ENGINE AND METHOD OF COMBUSTING FUEL 审中-公开

    公开(公告)号：US20190107042A1

    公开(公告)日：2019-04-11

    申请号：US16177752

    申请日：2018-11-01

    Applicant: PRATT & WHITNEY CANADA CORP.

    Inventor： Jean THOMASSIN ,  Andre JULIEN ,  Serge DUSSAULT

    IPC: F02B19/10

    Abstract: A method of combusting fuel, e.g. heavy fuel, in a rotary engine, including injecting a main quantity of fuel directly into a combustion chamber to form a first fuel-air mixture having a first air-fuel equivalence ratio λ higher than 1, injecting a pilot quantity of fuel into a pilot subchamber to form a second fuel-air mixture having a second air-fuel equivalence ratio λ smaller than the first air-fuel equivalence ratio, igniting the second fuel-air mixture within the pilot subchamber, using the ignited second fuel-air mixture from the pilot subchamber to ignite the first fuel-air mixture, and injecting a supplemental quantity of fuel directly into the combustion chamber after igniting the first fuel-air mixture, upstream of an exhaust port of the rotary engine with respect to a direction of rotation of the rotor. A rotary engine with interburner fuel injector is also discussed.

    TURBOPROP ENGINE ASSEMBLY WITH COMBINED ENGINE AND COOLING EXHAUST
    7.
    发明申请
    TURBOPROP ENGINE ASSEMBLY WITH COMBINED ENGINE AND COOLING EXHAUST 审中-公开
    涡轮发动机组件与组合发动机和冷却排气

    公开(公告)号：US20170037756A1

    公开(公告)日：2017-02-09

    申请号：US15227506

    申请日：2016-08-03

    Applicant: PRATT & WHITNEY CANADA CORP.

    Inventor： Andre JULIEN ,  Jean THOMASSIN ,  Serge DUSSAULT

    IPC: F01N3/05 ,  F02B61/04 ,  B64D33/04 ,  F02B53/14 ,  F01N13/08 ,  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.

    Abstract translation: 一种用于飞行器的涡轮螺旋桨发动机组件，包括具有液体冷却剂系统的内燃机，与飞行器的环境流体连通的空气管道;容纳在空气管道内的热交换器，其具有与液体冷却剂流体连通的冷却剂通道 系统和空气通道与空气管道流体连通的空气通道，以及与内燃机的排气流体连通的排气管道。 排气管道具有位于热交换器下游的空气管道中的出口和空气管道的出口的上游，排气管道的出口与空气管道的周壁隔开。 在使用中，冷却空气流围绕废气流。 还讨论了在具有内燃机的涡轮螺旋桨发动机组件中排出空气和废气的方法。

    AIRCRAFT POWER PLANT
    8.
    发明申请
    AIRCRAFT POWER PLANT 有权

    公开(公告)号：US20230085551A1

    公开(公告)日：2023-03-16

    申请号：US17475848

    申请日：2021-09-15

    Applicant: PRATT & WHITNEY CANADA CORP.

    Inventor： Serge DUSSAULT

    IPC: B64D27/04 ,  F02B3/10 ,  F02B53/14 ,  F02B53/10 ,  F02B37/00

    Abstract: Aircraft power plants and associated methods are provided. A method for driving a load on an aircraft includes: transferring motive power from an internal combustion (IC) engine to the load; discharging a flow of first exhaust gas from the IC engine when transferring motive power from the IC engine to the load; receiving the flow of first exhaust gas from the IC engine into a combustor; mixing fuel with the first exhaust gas in the combustor and igniting the fuel to generate a flow of second exhaust gas; receiving the flow of second exhaust gas at a turbine and driving the turbine with the flow of second exhaust gas from the combustor; and transferring motive power from the turbine to the load.

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