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    ROTARY INTERNAL COMBUSTION ENGINE WITH PILOT SUBCHAMBER
    2.
    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。

    HEAT SHIELD LABYRINTH SEAL
    3.
    发明申请
    HEAT SHIELD LABYRINTH SEAL 审中-公开
    热风烤漆密封

    公开(公告)号：US20170074170A1

    公开(公告)日：2017-03-16

    申请号：US15360161

    申请日：2016-11-23

    Applicant: PRATT & WHITNEY CANADA CORP.

    Inventor： Nigel DAVENPORT ,  Yen-Wen WANG

    IPC: F02C7/28 ,  F02C7/24 ,  F23R3/00

    Abstract: A seal for sealing a combustor heat shield against an interior surface of a combustor shell, the seal comprising: a first sealing surface on the interior surface of the combustor shell; and a second sealing surface on a rail on an edge of a heat shield, wherein each of the first and second sealing surfaces include first and second projections defining a non-linear leakage path between the projections.

    Abstract translation: 一种用于将燃烧器热屏蔽件密封到燃烧器壳体的内表面上的密封件，所述密封件包括：在所述燃烧器壳体的内表面上的第一密封表面; 以及在隔热板边缘上的轨道上的第二密封表面，其中第一和第二密封表面中的每一个包括限定突起之间的非线性泄漏路径的第一和第二突起。

    FUEL NOZZLE
    4.
    发明申请
    FUEL NOZZLE 有权
    燃油喷嘴

    公开(公告)号：US20160097536A1

    公开(公告)日：2016-04-07

    申请号：US14505765

    申请日：2014-10-03

    Applicant: PRATT & WHITNEY CANADA CORP.

    Inventor： Yen-Wen WANG ,  Nigel DAVENPORT ,  Eduardo HAWIE

    IPC: F23R3/28

    CPC classification number: F23R3/286 ,  F23D11/107 ,  F23D2900/11101 ,  F23R3/28

    Abstract: A fuel nozzle for a combustor of a gas turbine engine includes a body defining an axial direction and a radial direction, an air passageway defined axially in the body, and a fuel passageway defined axially in the body radially outwardly from the air passageway. The fuel passageway has an outer wall including an exit lip at a downstream portion of the outer wall. The exit lip has a surface treatment including a swirl-inducing relief. A gas turbine engine and a method of inducing swirl in at least one of pressurised fuel and air exiting a fuel nozzle of a gas turbine engine are also presented.

    Abstract translation: 用于燃气涡轮发动机的燃烧器的燃料喷嘴包括限定轴向方向和径向方向的主体，在主体中轴向限定的空气通道，以及从该空气通道径向向外在该体内轴向限定的燃料通道。 燃料通道具有在外壁的下游部分包括出口的外壁。 出口唇缘具有包括漩涡诱导浮雕的表面处理。 还提出了一种燃气涡轮发动机和在离开燃气涡轮发动机的燃料喷嘴的加压燃料和空气中的至少一个中引起涡流的方法。

    FUEL NOZZLE
    6.
    发明申请
    FUEL NOZZLE 有权
    燃油喷嘴

    公开(公告)号：US20160097538A1

    公开(公告)日：2016-04-07

    申请号：US14505787

    申请日：2014-10-03

    Applicant: PRATT & WHITNEY CANADA CORP.

    Inventor： Yen-Wen WANG ,  Nigel DAVENPORT

    IPC: F23R3/28

    CPC classification number: F23D11/383 ,  F23D11/102 ,  F23D11/103 ,  F23D11/107 ,  F23D2900/14021 ,  F23R3/12 ,  F23R3/286

    Abstract: A fuel nozzle for a combustor of a gas turbine engine includes a body defining an axial direction and a radial direction, an air passageway defined axially in the body, and a fuel passageway defined axially in the body radially outwardly from the air passageway. The air passageway has a swirl-inducing relief defined at an exit lip of an outer wall of the air passageway. A gas turbine engine and a method of inducing swirl in an air passageway of a fuel nozzle of a gas turbine engine are also presented.

    Abstract translation: 用于燃气涡轮发动机的燃烧器的燃料喷嘴包括限定轴向方向和径向方向的主体，在主体中轴向限定的空气通道，以及从该空气通道径向向外在该体内轴向限定的燃料通道。 空气通道具有限定在空气通道的外壁的出口处的旋涡诱导释放。 还提出了一种燃气涡轮发动机和在燃气涡轮发动机的燃料喷嘴的空气通道中引起涡流的方法。

    FUEL NOZZLE
    7.
    发明申请
    FUEL NOZZLE 审中-公开

    公开(公告)号：US20190226681A1

    公开(公告)日：2019-07-25

    申请号：US16374010

    申请日：2019-04-03

    Applicant: PRATT & WHITNEY CANADA CORP.

    Inventor： Yen-Wen WANG ,  Nigel DAVENPORT ,  Eduardo HAWIE

    IPC: F23R3/28 ,  F23R3/30 ,  F23R3/04 ,  F23D14/20 ,  F23R3/10 ,  F23R3/12

    Abstract: A method of delivering fuel from a fuel nozzle of a gas turbine engine includes carrying by a fuel passageway of the fuel nozzle a film of pressurised fuel, the fuel passageway being disposed radially outwardly from an air passageway carrying a flow of pressurised air, and directing the film of pressurised fuel onto an inside surface of an exit lip of an outer wall of the fuel passageway and thinning the film of pressurised fuel as it travels therealong. The exit lip generally increases in diameter as it extends downstream.

    FUEL NOZZLE
    8.
    发明申请
    FUEL NOZZLE 审中-公开

    公开(公告)号：US20170370590A1

    公开(公告)日：2017-12-28

    申请号：US15675084

    申请日：2017-08-11

    Applicant: PRATT & WHITNEY CANADA CORP.

    Inventor： Yen-Wen WANG ,  Nigel DAVENPORT ,  Eduardo HAWIE

    IPC: F23R3/28 ,  F23D11/10

    CPC classification number: F23R3/286 ,  F23D11/107 ,  F23D2900/11101 ,  F23R3/28

    Abstract: A fuel nozzle for a combustor of a gas turbine engine includes a body defining an axial direction and a radial direction, an air passageway defined axially in the body, and a fuel passageway defined axially in the body radially outwardly from the air passageway. The fuel passageway has an outer wall including an exit lip at a downstream portion of the outer wall. The exit lip has a surface treatment including a swirl-inducing relief. A gas turbine engine and a method of inducing swirl in at least one of pressurised fuel and air exiting a fuel nozzle of a gas turbine engine are also presented.

    ROTARY INTERNAL COMBUSTION ENGINE WITH PILOT SUBCHAMBER
    10.
    发明申请
    ROTARY INTERNAL COMBUSTION ENGINE WITH PILOT SUBCHAMBER 审中-公开

    公开(公告)号：US20180187593A1

    公开(公告)日：2018-07-05

    申请号：US15908987

    申请日：2018-03-01

    Applicant: PRATT & WHITNEY CANADA CORP.

    Inventor： Jean THOMASSIN ,  Nigel DAVENPORT ,  Eugene GEKHT

    IPC: F02B53/10 ,  F02B19/10

    Abstract: A non-Wankel rotary engine having an insert in the peripheral wall of the outer 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 bordering the cavity, 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 housing and having a tip communicating with the cavity at a location spaced apart from the insert.

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