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    LOW VOLUMETRIC COMPRESSION RATIO INTEGRATED TURBO-COMPOUND ROTARY ENGINE
    2.
    发明申请
    LOW VOLUMETRIC COMPRESSION RATIO INTEGRATED TURBO-COMPOUND ROTARY ENGINE 审中-公开
    低体积压缩比综合涡轮复合发动机

    公开(公告)号：WO2004074655A1

    公开(公告)日：2004-09-02

    申请号：PCT/CA2004/000258

    申请日：2004-02-24

    Applicant: PRATT & WHITNEY CANADA CORP. ,  JULIEN, André ,  CHÈVREFILS, André

    Inventor： JULIEN, André ,  CHÈVREFILS, André

    IPC: F02C5/06

    CPC classification number: F02C6/12 ,  F02C3/055 ,  F02C3/08 ,  F02C3/107 ,  F02C5/06 ,  Y02T50/671

    Abstract: A compound cycle engine (10) comprises a compressor and a turbine section (14, 18), and at least one cycle topping device (16) providing an energy input to the turbine section (18). The compressor section (14) compresses the air according to a pressure ratio PR gt . The cycle topping device (16) further compresses the air according to a volumetric compression ratio R vc , and wherein PR gt x R vc are selected, according to one aspect of the invention, to provide a cycle which permit a more compact and lighter compound cycle engine to be provided.

    Abstract translation: 复合循环发动机（10）包括压缩机和涡轮部分（14,18），以及至少一个提供到涡轮部分（18）的能量输入的循环顶部装置（16）。 压缩机部14根据压力比PRgt压缩空气。 循环顶部装置（16）根据体积压缩比Rvc进一步压缩空气，并且其中根据本发明的一个方面选择PRgt×Rvc，以提供允许更紧凑和更轻的复合循环发动机 提供。

    AIRCRAFT HEATING ASSEMBLY WITH LIQUID COOLED INTERNAL COMBUSTION ENGINE AND HEATING ELEMENT USING WASTE HEAT
    3.
    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：WO2017024392A1

    公开(公告)日：2017-02-16

    申请号：PCT/CA2016/050918

    申请日：2016-08-04

    Applicant: PRATT & WHITNEY CANADA CORP.

    Inventor： JONES, Anthony ,  JULIEN, André ,  MENHEERE, David ,  THOMASSIN, Jean ,  ULLYOTT, Richard ,  VAN DEN ENDE, Daniel

    IPC: B64D33/08 ,  B64D33/00

    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，以及与要加热的飞行器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。

    COMPOUND ENGINE ASSEMBLY WITH EXHAUST PIPE NOZZLE
    5.
    发明申请
    COMPOUND ENGINE ASSEMBLY WITH EXHAUST PIPE NOZZLE 审中-公开
    复合发动机组件与排气管喷嘴

    公开(公告)号：WO2016201551A1

    公开(公告)日：2016-12-22

    申请号：PCT/CA2016/050646

    申请日：2016-06-07

    Applicant: PRATT & WHITNEY CANADA CORP.

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

    IPC: F02B53/14 ,  B64D41/00 ,  F01C1/22 ,  F02B33/40 ,  F02B37/02 ,  F02B41/10

    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为至少0.2。 还讨论了混合至少一个旋转发动机的方法。

    AUXILIARY POWER UNIT WITH VARIABLE SPEED RATIO
    7.
    发明申请
    AUXILIARY POWER UNIT WITH VARIABLE SPEED RATIO 审中-公开
    具有可变速比的辅助动力单元

    公开(公告)号：WO2017024391A1

    公开(公告)日：2017-02-16

    申请号：PCT/CA2016/050917

    申请日：2016-08-04

    Applicant: PRATT & WHITNEY CANADA CORP.

    Inventor： JONES, Anthony ,  JULIEN, André ,  MENHEERE, David ,  THOMASSIN, Jean ,  ULLYOTT, Richard ,  VAN DEN ENDE, Daniel

    IPC: B64D33/00 ,  B64D33/02

    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。

    COMPOUND ENGINE ASSEMBLY WITH DIRECT DRIVE OF GENERATOR
    8.
    发明申请
    COMPOUND ENGINE ASSEMBLY WITH DIRECT DRIVE OF GENERATOR 审中-公开
    具有发电机直接驱动的复合发动机总成

    公开(公告)号：WO2016205934A1

    公开(公告)日：2016-12-29

    申请号：PCT/CA2016/050724

    申请日：2016-06-20

    Applicant: PRATT & WHITNEY CANADA CORP.

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

    IPC: F02B53/14 ,  B64D41/00 ,  F02B33/40 ,  F02B37/02 ,  F02B41/10 ,  F02B63/04

    CPC classification number: B64D41/00 ,  B64D2013/0611 ,  F01C1/22 ,  F01C11/008 ,  F02C3/10 ,  H02K7/1815 ,  H02K7/1823 ,  Y02T50/44 ,  Y02T50/53

    Abstract: A compound engine assembly for use as an aircraft auxiliary power unit, having an engine core including 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 engine core inlet, and a turbine section having an inlet in 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 communication with the engine core outlet, and 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.

    Abstract translation: 一种用作飞机辅助动力单元的复合发动机组件，其具有包括与发动机轴驱动接合的内燃机的发动机芯，具有直接接合到发动机轴的发电机轴，该发电机轴能够以 相同的速度，具有与发动机芯入口连通的出口的压缩机，以及涡轮部分，其具有与发动机芯出口连通的入口并且被配置成与发动机芯体相互补给动力。 涡轮机部分可以包括具有与发动机芯出口连通的入口的第一级涡轮机和具有与第一级涡轮机出口连通的入口的第二级涡轮机。 还讨论了向航空器提供电力的方法。

    COMPOUND ENGINE ASSEMBLY WITH CONFINED FIRE ZONE
    9.
    发明申请
    COMPOUND ENGINE ASSEMBLY WITH CONFINED FIRE ZONE 审中-公开
    复合发动机装配有限制的火区

    公开(公告)号：WO2016131154A1

    公开(公告)日：2016-08-25

    申请号：PCT/CA2016/050166

    申请日：2016-02-19

    Applicant: PRATT & WHITNEY CANADA CORP.

    Inventor： LAMARRE, Sylvain ,  JULIEN, André ,  GAUL, Michael ,  THOMASSIN, Jean ,  MEDVEDEV, Ilya ,  USIKOV, Sergey ,  ZOLOTOV, Andrey

    IPC: F02C7/25 ,  F01C1/22 ,  F02B33/40 ,  F02B37/00 ,  F02C6/12 ,  F02C7/36

    CPC classification number: F02C7/36 ,  F01C1/22 ,  F01C11/008 ,  F02C3/04 ,  F02C6/12 ,  F02C7/25 ,  F05D2220/323 ,  F05D2230/51 ,  F05D2230/72 ,  F05D2250/312 ,  F05D2260/4031 ,  F05D2300/121 ,  F05D2300/171 ,  F23M11/02

    Abstract: A compound engine assembly with an engine core including at least one internal combustion engine, a turbine section including a turbine shaft in driving engagement with the engine shaft, and a compressor, and a firewall. The compressor is located on one side of the firewall, and the turbine section and the engine core are located on the other side. The assembly may include a gearbox module with the turbine section and the engine core located on a same side of the gearbox module casing and the compressor located on the opposite side of the gearbox module casing, and with the firewall extending from the gearbox module casing. One or more rotatable accessory may be located on a same side of the firewall as the compressor. A method of reducing fire hazard in a compound engine assembly is also discussed.

    Abstract translation: 具有包括至少一个内燃机的发动机芯的复合发动机组件，包括与发动机轴驱动接合的涡轮轴的涡轮部分，以及压缩机和防火墙。 压缩机位于防火墙的一侧，涡轮部分和发动机核心位于另一侧。 组件可以包括齿轮箱模块，其中涡轮部分和发动机芯位于齿轮箱模块壳体的同一侧并且压缩机位于齿轮箱模块壳体的相对侧上，防火墙从齿轮箱模块壳体延伸。 一个或多个可旋转附件可以位于防火墙与压缩机相同的一侧。 还讨论了在复合发动机组件中减少火灾危险的方法。

    AUXILIARY POWER UNIT WITH EXCESS AIR RECOVERY
    10.
    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：WO2016205933A1

    公开(公告)日：2016-12-29

    申请号：PCT/CA2016/050723

    申请日：2016-06-20

    Applicant: PRATT & WHITNEY CANADA CORP.

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

    IPC: F02B53/14 ,  B64D41/00 ,  F02B33/40 ,  F02B37/02 ,  F02B41/10 ,  F02B63/04

    CPC classification number: B64D41/00 ,  F02B41/10 ,  F02B53/02 ,  F02B2053/005 ,  F02C3/04 ,  H02K7/1807 ,  H02K7/1823 ,  Y02T50/44 ,  Y02T50/53

    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。

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