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    ENGINE ASSEMBLY WITH INTERCOOLER
    11.
    发明申请
    ENGINE ASSEMBLY WITH INTERCOOLER 审中-公开

    公开(公告)号：US20180363540A1

    公开(公告)日：2018-12-20

    申请号：US15624257

    申请日：2017-06-15

    Applicant: PRATT & WHITNEY CANADA CORP.

    Inventor： Andre JULIEN ,  Edwin SCHULZ ,  Michael LANKTREE ,  Serge DUSSAULT

    IPC: F02B29/04 ,  F02B37/00 ,  F02B53/08 ,  F02B61/04

    Abstract: A method of operating an engine assembly receiving fuel, including admitting atmospheric air at a temperature T1 through an inlet of a compressor having a pressure ratio of PRGT, compressing the air in the compressor, cooling the compressed air from the compressor through an intercooler to cool the air from a temperature TBIC to a temperature TAIC, delivering the cooled compressed air from the intercooler to an inlet of an intermittent internal combustion engine having an effective volumetric compression ratio rVC, and further compressing the air in the intermittent internal combustion engine before igniting the fuel, where (PRGT)a (rVC)b (TAIC/TBIC)(T1/TA)

    AIRCRAFT POWER PLANT
    13.
    发明公开
    AIRCRAFT POWER PLANT 审中-公开

    公开(公告)号：US20240092491A1

    公开(公告)日：2024-03-21

    申请号：US18522598

    申请日：2023-11-29

    Applicant: PRATT & WHITNEY CANADA CORP.

    Inventor： Serge DUSSAULT

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

    CPC classification number: B64D27/04 ,  F02B3/10 ,  F02B37/001 ,  F02B53/10 ,  F02B53/14 ,  F01P2003/001

    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.

    AIRCRAFT POWER SUPPLY ARRANGEMENTS
    14.
    发明申请
    AIRCRAFT POWER SUPPLY ARRANGEMENTS 有权

    公开(公告)号：US20210122487A1

    公开(公告)日：2021-04-29

    申请号：US16903021

    申请日：2020-06-16

    Applicant: PRATT & WHITNEY CANADA CORP.

    Inventor： Behzad HAGSHENAS ,  Serge DUSSAULT ,  Tim SULLIVAN ,  Francois BELLEVILLE

    IPC: B64D41/00 ,  B64D13/06

    Abstract: A power supply arrangement (PSA) for an aircraft having an electrical system and an environmental control system (ECS) operatively connected to a cabin of the aircraft, the PSA has: at least one propelling engine; a secondary power unit (SPU) having a rotary engine, at least one generator in driving engagement with the rotary engine and operatively connectable to the electrical system of the aircraft, and at least one load compressor operatively connected to the rotary engine and pneumatically connected to a pneumatic circuit connectable to the ECS of the aircraft, the PSA having a propelling configuration in which the at least one propelling engine and the SPU are both powered and a hotel configuration in which the at least one propelling engine is unpowered while the SPU is powered, the pneumatic circuit pneumatically disconnected from the at least one propelling engine in both of the hotel and propelling configurations.

    ROTARY ENGINE WITH PILOT SUBCHAMBERS
    15.
    发明申请
    ROTARY ENGINE WITH PILOT SUBCHAMBERS 审中-公开

    公开(公告)号：US20190162108A1

    公开(公告)日：2019-05-30

    申请号：US15825691

    申请日：2017-11-29

    Applicant: PRATT & WHITNEY CANADA CORP.

    Inventor： Serge DUSSAULT ,  Andre JULIEN ,  Michael LANKTREE ,  Edwin SCHULZ

    IPC: F02B19/10 ,  F02B53/10

    Abstract: A rotary engine including at least two pilot subchambers each in parallel fluid communication with the internal cavity, so that each pilot subchamber is in fluid communication with the combustion chambers as the rotor rotates. Each of the at least two pilot subchambers in fluid communication with a corresponding pilot fuel injector. At least one ignition source is configured for igniting fuel in the pilot subchambers. A compound engine assembly and a method of combusting fuel in a rotary engine are also discussed.

    COMPOUND ENGINE ASSEMBLY WITH EXHAUST PIPE NOZZLE
    17.
    发明申请
    COMPOUND ENGINE ASSEMBLY WITH EXHAUST PIPE NOZZLE 有权
    复合发动机组件与排气管喷嘴

    公开(公告)号：US20160369693A1

    公开(公告)日：2016-12-22

    申请号：US14740889

    申请日：2015-06-16

    Applicant: Pratt & Whitney Canada Corp.

    Inventor： Andre JULIEN ,  Serge DUSSAULT ,  Jade BILODEAU ,  Renaud BESNER

    IPC: F02C3/06 ,  F02B39/02 ,  F02C5/02 ,  F02C3/00

    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: A compound engine assembly with at least one rotary internal combustion engine, an impulse turbine, and an exhaust pipe for each internal combustion engine providing fluid communication between the exhaust port of the respective internal combustion engine and the flow path of the turbine. Each exhaust pipe terminates in a nozzle. For each exhaust pipe, a ratio Vp/Vd between the pipe volume Vp and the displacement volume Vd of the respective internal combustion engine is at most 1.5. A minimum value of a cross-sectional area of each 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 respective internal combustion engine is at least 0.2. A method of compounding at least one rotary engine is also discussed.

    Abstract translation: 一种复合发动机组件，其具有至少一个旋转内燃机，脉冲涡轮机和用于每个内燃机的排气管，从而在各个内燃机的排气口和涡轮机的流路之间提供流体连通。 每个排气管终止于喷嘴。 对于每个排气管，管内容Vp与各内燃机的排量之比Vp / Vd为1.5以下。 在喷嘴处限定每个排气管的横截面面积的最小值。 在一个实施例中，各个内燃机排气口的最小横截面面积A an与横截面面积Ae之间的比An / Ae至少为0.2。 还讨论了混合至少一个旋转发动机的方法。

    AIRCRAFT POWER PLANT
    18.
    发明申请
    AIRCRAFT POWER PLANT 有权

    公开(公告)号：US20250051017A1

    公开(公告)日：2025-02-13

    申请号：US18931509

    申请日：2024-10-30

    Applicant: PRATT & WHITNEY CANADA CORP.

    Inventor： Serge DUSSAULT

    IPC: B64D27/04 ,  F01P3/00 ,  F02B3/10 ,  F02B37/00 ,  F02B53/00 ,  F02B53/10 ,  F02B53/14

    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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