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    COMPOUND CYCLE ENGINE
    31.
    发明申请
    COMPOUND CYCLE ENGINE 有权
    化学循环发动机

    公开(公告)号：US20150275749A1

    公开(公告)日：2015-10-01

    申请号：US14740869

    申请日：2015-06-16

    Applicant: Pratt & Whitney Canada Corp.

    Inventor： Jean THOMASSIN

    IPC: F02B63/00 ,  F02B53/02

    CPC classification number: F02B63/00 ,  F01C1/22 ,  F01C11/002 ,  F01C11/008 ,  F02B53/02 ,  F02C5/00 ,  F02C6/12 ,  F02C6/20

    Abstract: A compound cycle engine having at least one rotary unit defining an internal combustion engine, a first stage turbine in proximity of each unit, and a turbocharger is discussed. The exhaust port of each rotary unit is in fluid communication with the flowpath of the first stage turbine upstream of its rotor. The rotors of the first stage turbine and of each rotary unit drive a common load. The outlet of the compressor of the turbocharger is in fluid communication with the inlet port of each rotary unit, and the inlet of the second stage turbine of the turbocharger is in fluid communication with the flowpath of the first stage turbine downstream of its rotor. The first stage turbine has a lower reaction ratio than that of the second stage turbine. A method of compounding at least one rotary engine is also discussed.

    Abstract translation: 具有限定内燃机的至少一个旋转单元，每个单元附近的第一级涡轮机和涡轮增压器的复合循环发动机。 每个旋转单元的排气口与其转子上游的第一级涡轮机的流动路径流体连通。 第一级涡轮机和每个旋转单元的转子驱动公共负载。 涡轮增压器的压缩机的出口与每个旋转单元的入口流体连通，并且涡轮增压器的第二级涡轮机的入口与其转子下游的第一级涡轮机的流路流体连通。 第一级涡轮机具有比第二级涡轮机更低的反应比。 还讨论了混合至少一个旋转发动机的方法。

    ROTARY INTERNAL COMBUSTION ENGINE WITH PILOT SUBCHAMBER
    32.
    发明申请
    ROTARY INTERNAL COMBUSTION ENGINE WITH PILOT SUBCHAMBER 审中-公开
    旋转式内燃式发动机

    公开(公告)号：US20150240710A1

    公开(公告)日：2015-08-27

    申请号：US14706457

    申请日：2015-05-07

    Applicant: Pratt & Whitney Canada Corp.

    Inventor： Jean THOMASSIN ,  Nigel DAVENPORT ,  Eugene GEKHT

    IPC: F02B55/08 ,  F02B53/02 ,  F02B53/10 ,  F02B19/12 ,  F02B53/12

    CPC classification number: F02B55/08 ,  F01C1/22 ,  F01C11/006 ,  F01C20/06 ,  F01C20/10 ,  F01C20/24 ,  F01C21/06 ,  F01C21/08 ,  F01C21/106 ,  F01C21/18 ,  F01C21/183 ,  F02B19/12 ,  F02B53/02 ,  F02B53/10 ,  F02B53/12 ,  F04C29/0092 ,  F04C2240/80 ,  Y02T10/125 ,  Y02T10/17

    Abstract: A rotary engine having an insert in a peripheral wall of the stator body, the insert being made of a material having a greater heat resistance than that of the peripheral wall, having a subchamber defined therein and having an inner surface, the subchamber communicating with the cavity through at least one opening defined in the inner surface and having a shape forming a reduced cross-section adjacent the opening, a pilot fuel injector having a tip received in the subchamber, an ignition element having a tip received in the subchamber, and a main fuel injector extending through the stator body and having a tip communicating with the cavity at a location spaced apart from the insert. The subchamber has a volume corresponding to from 5% to 25% of a sum of the minimum volume and the volume of the subchamber. A method of injecting heavy fuel into a Wankel engine is also discussed.

    Abstract translation: 一种旋转式发动机，其具有在定子体的周壁中的插入件，该插入件由具有比周壁更高的耐热性的材料制成，具有限定在其中并具有内表面的子室，该子室与 空腔通过限定在内表面中的至少一个开口，并且具有形成与开口相邻的减小的横截面的形状;引燃燃料喷射器，其具有容纳在子室中的尖端，点火元件，其具有接收在子室中的尖端，以及 主燃料喷射器延伸穿过定子体并且具有在与插入件间隔开的位置处与空腔连通的尖端。 子室具有对应于子室的最小体积和体积的总和的5％至25％的体积。 还讨论了将重质燃料注入汪克尔发动机的方法。

    ROTARY INTERNAL COMBUSTION ENGINE WITH VARIABLE VOLUMETRIC COMPRESSION RATIO
    33.
    发明申请
    ROTARY INTERNAL COMBUSTION ENGINE WITH VARIABLE VOLUMETRIC COMPRESSION RATIO 有权
    具有可变体积压缩比的旋转内燃机

    公开(公告)号：US20140224207A1

    公开(公告)日：2014-08-14

    申请号：US14152255

    申请日：2014-01-10

    Applicant: Pratt & Whitney Canada Corp.

    Inventor： Jean THOMASSIN ,  Andre JULIEN ,  Edwin SCHULZ ,  Michael LANKTREE

    IPC: F02B53/04

    CPC classification number: F02B53/06 ,  F01C1/22 ,  F01C11/006 ,  F01C20/06 ,  F01C20/10 ,  F01C20/24 ,  F01C21/06 ,  F01C21/08 ,  F01C21/106 ,  F01C21/18 ,  F01C21/183 ,  F02B53/02 ,  F02B53/04 ,  F02B55/16 ,  F02B2053/005 ,  F04C29/0092 ,  F04C2240/80

    Abstract: A method and apparatus for controlling an air input in a rotary engine, including selectively controlling a plurality of inlet ports communicating with an internal combustion cavity of the engine, the ports located serially downstream of the exhaust port relative direction of a revolution of a rotor of the engine. The inlet ports are controlled to alter air intake at various engine operational stages, such as start up, idle, etc., to allow for varying operational requirements to be met. For example: when a power demand on the engine lower than a predetermined threshold, control may be effected by opening a primary inlet port and closing a secondary inlet port; and, when the power demand exceeds the predetermined threshold, control may be effected by opening the primary inlet port and opening the secondary inlet port, the secondary inlet port being located such as to be in communication with the exhaust port throughout portions of the revolution of the engine to purge exhaust gases of the engine.

    Abstract translation: 一种用于控制旋转发动机中的空气输入的方法和装置，包括选择性地控制与发动机的内部燃烧腔相通的多个入口，排气口的下游侧的端口相对于转子转速的相对方向 引擎。 入口端口被控制以改变各种发动机操作阶段（例如起动，空转等）的进气口，以允许满足不同的操作要求。 例如：当发动机上的功率需求低于预定阈值时，可以通过打开主入口并关闭次级入口来实现控制; 并且当功率需求超过预定阈值时，可以通过打开主入口并打开次级入口来进行控制，次级入口位于与排气口连通的部分， 发动机来净化发动机的废气。

    SYSTEMS AND METHODS FOR AIRCRAFT WING PLUG
    35.
    发明公开
    SYSTEMS AND METHODS FOR AIRCRAFT WING PLUG 审中-公开

    公开(公告)号：US20230356852A1

    公开(公告)日：2023-11-09

    申请号：US18353162

    申请日：2023-07-17

    Applicant: PRATT & WHITNEY CANADA CORP.

    Inventor： Pierre BERTRAND ,  Jean THOMASSIN

    IPC: B64D27/24 ,  B64D27/12 ,  B64D29/02

    CPC classification number: B64D27/24 ,  B64D27/12 ,  B64D29/02 ,  B64D2027/026

    Abstract: The aircraft includes a fuselage and at least one wing extending from the fuselage. The wing includes first and second original portions and a plug portion positioned between the first and second original portions. A propulsion system is positioned on the at least one wing. The propulsion system includes at least one electric powerplant and at least one combustion powerplant. Each powerplant delivers power to a respective air mover for propelling the aircraft. The electric powerplant and/or the combustion powerplant is positioned outboard from the plug portion.

    ROTARY ENGINE LUBRICATION SYSTEM USING INTENSIFIER INJECTOR
    37.
    发明申请
    ROTARY ENGINE LUBRICATION SYSTEM USING INTENSIFIER INJECTOR 有权

    公开(公告)号：US20210355898A1

    公开(公告)日：2021-11-18

    申请号：US16872937

    申请日：2020-05-12

    Applicant: PRATT & WHITNEY CANADA CORP.

    Inventor： Etienne PLAMONDON ,  Sebastien BERGERON ,  Jean THOMASSIN

    IPC: F02M57/02 ,  F02M47/02

    Abstract: A rotary internal combustion engine (ICE) has: a housing defining a rotor cavity; a rotor received within the rotor cavity to define working chambers of variable volume around the rotor, the rotor having circumferentially spaced peripheral apex seals biased radially outwardly in sliding engagement against a peripheral wall of the housing to separate the working chambers from one another, the housing having a fluid passage defined therethrough and opening into an inner surface of the peripheral wall; and an injector having a lubricant inlet hydraulically connected to a lubricant source, an actuation inlet hydraulically connected to a source of an actuation fluid, and a lubricant outlet, the injector having an open state in which the lubricant outlet is in fluid flow communication with the fluid passage upon the actuation fluid received within the injector and a closed state in which the lubricant outlet is disconnected from the fluid passage.

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