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    EXHAUST MIXER WITH PROTRUSIONS
    12.
    发明公开
    EXHAUST MIXER WITH PROTRUSIONS 审中-公开

    公开(公告)号：US20240230089A1

    公开(公告)日：2024-07-11

    申请号：US18152336

    申请日：2023-01-10

    Applicant: PRATT & WHITNEY CANADA CORP.

    Inventor： Metin Ilbay YARAS ,  Mark CUNNINGHAM ,  Raja RAMAMURTHY

    IPC: F23R3/02 ,  B01F23/10 ,  B01F25/10

    CPC classification number: F23R3/02 ,  B01F23/10 ,  B01F25/10

    Abstract: An exhaust mixer assembly for a gas turbine engine includes a core passage extending along a central engine axis for directing a core gas flow. An outer annular passage coaxially surrounds the core passage for directing a bypass gas flow. An exhaust mixer communicating with the core passage and the outer annular passage has an upstream end, a downstream end and an annular wall extending therebetween. A plurality of protrusions extend axially from a downstream end of the annular wall to form a jagged trailing edge of the exhaust mixer. Each of the plurality of protrusions extend separately from the downstream end of the annular wall from the other of the plurality of protrusions. At least one of the plurality of protrusions is twisted about a protrusion axis extending through the at least one of the plurality of protrusions, the protrusion axis parallel to the central axis.

    EXHAUST MIXER WITH PROTRUSIONS
    13.
    发明公开
    EXHAUST MIXER WITH PROTRUSIONS 审中-公开

    公开(公告)号：US20240229740A1

    公开(公告)日：2024-07-11

    申请号：US18152326

    申请日：2023-01-10

    Applicant: PRATT & WHITNEY CANADA CORP.

    Inventor： Metin Ilbay YARAS ,  Mark CUNNINGHAM ,  Raja RAMAMURTHY

    IPC: F02K1/48 ,  F02K3/02

    CPC classification number: F02K1/48 ,  F02K3/025 ,  F05D2240/126 ,  F05D2250/18 ,  F05D2260/606

    Abstract: An exhaust mixer assembly for a gas turbine engine includes a core passage extending along a central engine axis for directing a core gas flow. An outer annular passage coaxially surrounds the core passage for directing a bypass gas flow. An exhaust mixer communicating with the core passage and outer annular passages has an upstream end, a downstream end and an annular wall extending therebetween. The annular wall defines a mixing plane at a trailing edge thereof at the downstream end at which the core and bypass gas flows are mixed. The annular wall has a radially inner surface and a radially outer surface. A plurality of protrusions are disposed on and extend laterally along and radially from at the radially inner surface and/or the radially outer surface. The plurality of protrusions are arranged one alongside another on the radially inner surface and/or the radially outer surface.

    GAS TURBINE ENGINE EJECTOR
    14.
    发明申请
    GAS TURBINE ENGINE EJECTOR 审中-公开

    公开(公告)号：US20200025132A1

    公开(公告)日：2020-01-23

    申请号：US16226717

    申请日：2018-12-20

    Applicant: PRATT & WHITNEY CANADA CORP.

    Inventor： Guorong YAN ,  Mark CUNNINGHAM ,  Franco DI PAOLA

    IPC: F02K1/38 ,  F02K1/34 ,  F02K1/48 ,  F02C3/10

    Abstract: An ejector comprises a primary nozzle having an annular wall forming part of an outer boundary of an exhaust portion of a primary flow path of a gas turbine engine. The annular wall has a downstream end defining a plurality of circumferentially distributed lobes. The ejector further comprises a secondary nozzle having an annular wall disposed about the primary nozzle, the primary nozzle and the secondary nozzle defining a secondary flow passage therebetween for channeling a secondary flow. The secondary nozzle defines a mixing zone downstream of an exit of the primary nozzle. A flow guide ring is mounted to the primary nozzle lobes. The ring has an aerodynamic surface extending from a leading edge to a trailing edge respectively disposed upstream and downstream of the exit of the primary nozzle. The aerodynamic surface of the ring is oriented to guide the high velocity primary flow into the mixing zone.

    GAS TURBINE ENGINE EJECTOR
    16.
    发明申请
    GAS TURBINE ENGINE EJECTOR 审中-公开
    气体涡轮发动机

    公开(公告)号：US20160032865A1

    公开(公告)日：2016-02-04

    申请号：US14514770

    申请日：2014-10-15

    Applicant: Pratt & Whitney Canada Corp.

    Inventor： Guorong YAN ,  Mark CUNNINGHAM ,  Franco DI PAOLA

    IPC: F02K1/38

    CPC classification number: F02K1/386 ,  F02C3/10 ,  F02K1/34 ,  F02K1/48 ,  F05D2220/324 ,  F05D2250/232 ,  F05D2250/61 ,  F05D2260/601

    Abstract: An ejector comprises a primary nozzle having an annular wall forming part of an outer boundary of an exhaust portion of a primary flow path of a gas turbine engine. The annular wall has a downstream end defining a plurality of circumferentially distributed lobes. The ejector further comprises a secondary nozzle having an annular wall disposed about the primary nozzle, the primary nozzle and the secondary nozzle defining a secondary flow passage therebetween for channeling a secondary flow. The secondary nozzle defines a mixing zone downstream of an exit of the primary nozzle. A flow guide ring is mounted to the primary nozzle lobes. The ring has an aerodynamic surface extending from a leading edge to a trailing edge respectively disposed upstream and downstream of the exit of the primary nozzle. The aerodynamic surface of the ring is oriented to guide the high velocity primary flow into the mixing zone.

    Abstract translation: 喷射器包括具有形成燃气涡轮发动机的主流路的排气部分的外边界的一部分的环形壁的主喷嘴。 环形壁具有限定多个周向分布的凸角的下游端。 喷射器还包括二次喷嘴，其具有围绕主喷嘴设置的环形壁，主喷嘴和次喷嘴在其间限定用于引导二次流的二次流动通道。 次级喷嘴限定了主喷嘴出口下游的混合区域。 流动引导环安装到主喷嘴孔。 环具有从前缘延伸到分别设置在主喷嘴的出口的上游和下游的后缘的空气动力学表面。 环的空气动力学表面被定向以将高速一次流引导到混合区中。

    Exhaust Mixer with Offset Lobes
    17.
    发明申请
    Exhaust Mixer with Offset Lobes 审中-公开
    排气混合器与偏移Lobes

    公开(公告)号：US20150013341A1

    公开(公告)日：2015-01-15

    申请号：US13937587

    申请日：2013-07-09

    Applicant: Pratt & Whitney Canada Corp.

    Inventor： Mark CUNNINGHAM ,  Remo MARINI ,  Sami GIRGIS ,  Mohammad Reza KAMESHKI ,  Raja RAMAMURTHY

    IPC: F01D25/30

    CPC classification number: F01D25/30 ,  F02K1/386 ,  F02K1/48 ,  F05D2250/314 ,  F05D2250/37 ,  F05D2250/71 ,  Y02T50/672

    Abstract: An exhaust mixer for a gas turbine engine where each outer lobe has at the downstream end a circumferential offset in a direction corresponding to that of the swirl component of the flow entering the mixer. The mixer has a crest line having at least a downstream portion curved with respect with respect to a circumferential direction of the mixer and/or a center line at the downstream end tilted with respect to a radial line extending to the tip of the outer lobe to define the circumferential offset. A method of mixing a core flow and a bypass flow surrounding the core flow with an annular mixer is also provided.

    Abstract translation: 一种用于燃气涡轮发动机的排气混合器，其中每个外瓣在下游端具有与进入混合器的流的漩涡分量的方向对应的方向的周向偏移。 混合器具有至少一个相对于混合器的圆周方向弯曲的下游部分和/或下游端的中心线相对于延伸到外凸缘尖端的径向线倾斜的顶部线， 定义圆周偏移。 还提供了使用环形混合器混合芯流和围绕芯流的旁路的方法。

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