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    ROTARY ENGINE WITH PILOT SUBCHAMBERS
    41.
    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.

    INTERNAL COMBUSTION ENGINE WITH ROTOR HAVING OFFSET PERIPHERAL SURFACE
    43.
    发明申请
    INTERNAL COMBUSTION ENGINE WITH ROTOR HAVING OFFSET PERIPHERAL SURFACE 审中-公开

    公开(公告)号：US20190003307A1

    公开(公告)日：2019-01-03

    申请号：US16124663

    申请日：2018-09-07

    Applicant: PRATT & WHITNEY CANADA CORP.

    Inventor： Jean-Gabriel GAUVREAU ,  David GAGNON-MARTIN ,  Andre JULIEN

    IPC: F01C21/08 ,  F02B53/08 ,  F01C21/10 ,  F02B37/00 ,  F01C1/22 ,  F02B53/00

    Abstract: A rotary engine where the rotor cavity has a peripheral inner surface having a peritrochoid configuration defined by a first eccentricity and the rotor has a peripheral outer surface having a peritrochoid inner envelope configuration defined by a second eccentricity larger than the first eccentricity. Also, a rotary engine where the rotor cavity has a peripheral inner surface having a peritrochoid configuration defined by an eccentricity, and a rotor with a peripheral outer surface between adjacent ones of the apex portions being inwardly offset from a peritrochoid inner envelope configuration defined by the eccentricity. The engine may have an expansion ratio with a value of at most 8. The rotary engine may be part of a compound engine system.

    AUXILIARY POWER UNIT WITH EXCESS AIR RECOVERY
    46.
    发明申请
    AUXILIARY POWER UNIT WITH EXCESS AIR RECOVERY 审中-公开
    辅助动力单元与空气恢复

    公开(公告)号：US20160376022A1

    公开(公告)日：2016-12-29

    申请号：US14750187

    申请日：2015-06-25

    Applicant: Pratt & Whitney Canada Corp.

    Inventor： Richard ULLYOTT ,  Anthony JONES ,  Andre JULIEN ,  Jean THOMASSIN

    IPC: B64D41/00 ,  H02K7/18 ,  F02C3/04 ,  F02B41/10 ,  F02B53/02

    Abstract: An auxiliary power unit for an aircraft, having an engine core, a compressor having an outlet in fluid communication with the engine core inlet, a turbine section in fluid communication with the engine core outlet, and an excess air duct having a first end in fluid communication with the compressor outlet and a second end in fluid communication with a turbine inlet of the turbine section. The excess air duct defines a flow path between the compressor outlet and the turbine section separate from the engine core. The auxiliary power unit may include a generator in driving engagement with 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，具有发动机芯，具有与发动机芯入口流体连通的出口的压缩机，与发动机芯出口流体连通的涡轮部分，以及具有流体的第一端的过量空气管道 与压缩机出口的连通以及与涡轮机部分的涡轮机入口流体连通的第二端。 多余的空气管道限定了压缩机出口和与发动机芯分离的涡轮部分之间的流动路径。 辅助动力单元可以包括与发动机芯驱动接合以提供飞机电力的发电机。 还讨论了向飞行器提供压缩空气和电力的方法。

    COMPOUND ENGINE ASSEMBLY WITH EXHAUST PIPE NOZZLE
    47.
    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。

    COMPOUND ENGINE ASSEMBLY WITH INLET LIP ANTI-ICING
    48.
    发明申请
    COMPOUND ENGINE ASSEMBLY WITH INLET LIP ANTI-ICING 审中-公开
    复合发动机组件与入口防撞

    公开(公告)号：US20160245174A1

    公开(公告)日：2016-08-25

    申请号：US14864137

    申请日：2015-09-24

    Applicant: PRATT & WHITNEY CANADA CORP.

    Inventor： Sylvain LAMARRE ,  Mike FONTAINE ,  Andre JULIEN ,  Michael GAUL ,  Jean THOMASSIN ,  Ilya B. MEDVEDEV ,  Sergey USIKOV ,  Andrey ZOLOTOV

    IPC: F02C7/047 ,  F01C11/00 ,  F02C3/04 ,  F02C7/36 ,  F01C1/22 ,  F01C21/06 ,  F02B41/00 ,  F02C6/18 ,  F02B37/00 ,  F01C21/18

    Abstract: A compound engine assembly with an inlet duct having an inlet surrounded by an inlet lip including at least one conduit extending therethrough, a compressor, an engine core including at least one internal combustion engine, a turbine section having a turbine shaft in driving engagement with the engine shaft, and an exhaust conduit providing a fluid communication between the outlet of the turbine section and the conduit(s) of the inlet lip. An exhaust duct and ant exhaust conduit providing a fluid communication between the outlet of the turbine section and the exhaust duct may also be provided. The internal combustion engine(s) may be rotary engine(s). A method of driving a rotatable load of an aircraft is also discussed.

    Abstract translation: 具有入口管道的复合发动机组件，入口管道具有由入口唇缘包围的入口，入口唇缘包括至少一个延伸穿过其中的导管，压缩机，包括至少一个内燃机的发动机芯，具有涡轮轴的涡轮部分， 发动机轴和排气导管，其在涡轮部分的出口和入口唇缘的导管之间提供流体连通。 还可以提供在涡轮机部分的出口和排气管之间提供流体连通的排气管道和蚂蚁排气导管。 内燃机可以是旋转发动机。 还讨论了驱动飞行器的可旋转载荷的方法。

    COMPOUND ENGINE ASSEMBLY WITH MOUNT CAGE
    49.
    发明申请
    COMPOUND ENGINE ASSEMBLY WITH MOUNT CAGE 审中-公开
    复合发动机总成与安装笼

    公开(公告)号：US20160245170A1

    公开(公告)日：2016-08-25

    申请号：US14864124

    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

    IPC: F02C3/10 ,  F01C11/00 ,  F02C7/36 ,  F02B37/00

    CPC classification number: F02C7/36 ,  F01C1/22 ,  F01C11/008 ,  F02B33/34 ,  F02B41/10 ,  F02B53/00 ,  F02B61/04 ,  F02B2053/005 ,  F02C6/12 ,  F02C6/206 ,  F02C7/32 ,  F05B2220/40 ,  Y02T10/163 ,  Y02T10/17

    Abstract: A compound engine assembly with an engine core including at least one internal combustion engine, a turbine section, and a compressor having an outlet in fluid communication with an inlet of the engine core. A casing is connected to the turbine section, the compressor and the engine core. A mount cage is connected to mounts attached to the casing between the compressor and a hot zone including the turbine section and the engine core. The mount cage includes a plurality of struts all extending from the mounts away from the turbine section and engine core. The casing may be a gearbox module casing through which the turbine shaft in engaged with the engine shaft. The mount cage may be completely contained within an axial space with the turbine section and engine core being located outside of the axial space.

    Abstract translation: 具有包括至少一个内燃机，涡轮部分和具有与发动机芯的入口流体连通的出口的压缩机的发动机芯的复合发动机组件。 壳体连接到涡轮部分，压缩机和发动机核心。 安装架连接到附接到壳体之间的安装件，压缩机与包括涡轮部分和发动机芯部的热区域之间。 安装架包括从支架远离涡轮部分和发动机芯部延伸的多个支柱。 壳体可以是齿轮箱模块壳体，涡轮轴通过该外壳与发动机轴接合。 安装架可以完全容纳在轴向空间内，涡轮部分和发动机芯位于轴向空间的外部。

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