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    Reverse core gear turbofan
    3.
    发明授权
    Reverse core gear turbofan 有权
    反转式核心齿轮涡轮风扇

    公开(公告)号：US09239004B2

    公开(公告)日：2016-01-19

    申请号：US13431048

    申请日：2012-03-27

    Applicant: Daniel Bernard Kupratis ,  Francis R. Moon

    Inventor： Daniel Bernard Kupratis ,  Francis R. Moon

    IPC: F02C7/36 ,  F02K3/065 ,  F02C6/02 ,  F02C3/10 ,  F02C3/107

    CPC classification number: F02C6/02 ,  F01D17/141 ,  F02C3/05 ,  F02C3/10 ,  F02C3/107 ,  F02C3/13 ,  F02C3/145 ,  F02C7/36 ,  F02C9/18 ,  F02K3/06 ,  F02K3/065 ,  F02K3/075 ,  F05D2220/32 ,  F05D2220/323 ,  F05D2250/36 ,  F05D2260/4023 ,  F05D2260/4031 ,  F05D2270/053

    Abstract: A gas turbine engine has a fan at an axially outer location. The fan rotates about an axis of rotation. The fan delivers air into an outer bypass duct, and across a booster fan positioned radially inwardly of the outer bypass duct. The booster fan delivers air into a radially middle duct, and across a cold turbine into a radially inner core duct being directed into a compressor. From the compressor, air flows axially in a direction back toward the fan through a combustor section, and across an exhaust of the turbine section as directed into the middle duct. A gear reduction drives the fan from a fan drive turbine section. A method is also disclosed.

    Abstract translation: 燃气涡轮发动机在轴向外部位置具有风扇。 风扇围绕旋转轴旋转。 风扇将空气输送到外部旁路管道中，并且跨过位于外部旁路管道的径向内侧的增压风扇。 增压器风扇将空气输送到径向中间的管道中，并且将冷却涡轮机横穿进入压缩机的径向内部芯管道。 从压缩机，空气沿着朝向风扇的方向通过燃烧器部分轴向流动，并且沿着涡轮机部分的排气指向中间管道。 齿轮减速器从风扇驱动涡轮机部分驱动风扇。 还公开了一种方法。

    Transition duct for use in a turbine engine and method of assembly
    4.
    发明授权
    Transition duct for use in a turbine engine and method of assembly 有权
    用于涡轮发动机的过渡管和组装方法

    公开(公告)号：US09222437B2

    公开(公告)日：2015-12-29

    申请号：US13624543

    申请日：2012-09-21

    Applicant: General Electric Company

    Inventor： Joseph Machnaim ,  Brian David Keith ,  Scott Michael Carson

    IPC: F04D29/54 ,  F02K3/065 ,  B23P11/00 ,  F01D9/02

    CPC classification number: F02K3/065 ,  B23P11/00 ,  F01D9/02 ,  F04D29/547 ,  Y10T29/49323

    Abstract: A transition duct for use in a turbine engine is provided. The transition duct includes a radially inner wall and a radially outer wall positioned about the radially inner wall defining a flow passage therebetween. The radially outer wall extends and is contoured from an upstream end to a downstream end of the transition duct. As such, the slope of the radially outer wall increases from the upstream end to a predetermined axial location and decreases from the predetermined axial location to the downstream end.

    Abstract translation: 提供了一种用于涡轮发动机的过渡管道。 过渡管道包括径向内壁和围绕径向内壁定位在其间的流动通道定位的径向外壁。 径向外壁从过渡管道的上游端延伸到下游端。 这样，径向外壁的斜面从上游端增加到预定的轴向位置，并从预定的轴向位置减小到下游端。

    TRANSITION DUCT FOR USE IN A TURBINE ENGINE AND METHOD OF ASSEMBLY
    5.
    发明申请
    TRANSITION DUCT FOR USE IN A TURBINE ENGINE AND METHOD OF ASSEMBLY 有权
    涡轮发动机中使用的过渡管和组装方法

    公开(公告)号：US20140086739A1

    公开(公告)日：2014-03-27

    申请号：US13624543

    申请日：2012-09-21

    Applicant: GENERAL ELECTRIC COMPANY

    Inventor： Joseph Machnaim ,  Brian David Keith ,  Scott Michael Carson

    IPC: F02K3/065 ,  B23P11/00 ,  F04D29/54

    CPC classification number: F02K3/065 ,  B23P11/00 ,  F01D9/02 ,  F04D29/547 ,  Y10T29/49323

    Abstract: A transition duct for use in a turbine engine is provided. The transition duct includes a radially inner wall and a radially outer wall positioned about the radially inner wall defining a flow passage therebetween. The radially outer wall extends and is contoured from an upstream end to a downstream end of the transition duct. As such, the slope of the radially outer wall increases from the upstream end to a predetermined axial location and decreases from the predetermined axial location to the downstream end.

    Abstract translation: 提供了一种用于涡轮发动机的过渡管道。 过渡管道包括径向内壁和围绕径向内壁定位在其间的流动通道定位的径向外壁。 径向外壁从过渡管道的上游端延伸到下游端。 这样，径向外壁的斜面从上游端增加到预定的轴向位置，并从预定的轴向位置减小到下游端。

    Gas turbine engines
    6.
    发明授权
    Gas turbine engines 失效
    燃气涡轮发动机

    公开(公告)号：US5383332A

    公开(公告)日：1995-01-24

    申请号：US68479

    申请日：1987-06-19

    Applicant: Robert G. Angel

    Inventor： Robert G. Angel

    IPC: F02K1/00 ,  F02K3/065 ,  F02K3/075

    CPC classification number: F02K3/065 ,  F02K1/004 ,  F02K3/075

    Abstract: A variable cycle gas turbine bypass engine includes a first fan 1 located at an inlet to the engine so as to provide air to a compressor 2 driven by a turbine 11 and to a bypass duct 13 surrounding the compressor housing. A second fan 5 located in the bypass duct 13 is driven by a free turbine 12. A controllable area auxiliary air intake 4 and bypass duct blocker doors 3 are located between the first and second fans 1, 5. Control means are effective for selectably operating the bypass duct blocker doors 3 and the auxiliary air intake 4 to vary in operation the bypass ratio of the engine. Thus in conventional wing-borne flight, the intake 4 is closed and the bypass duct 13 is unobstructed, and the combined exhausts from the bypass duct 13 and the turbines 10, 11 and 12 pass to a tailpipe 14, which has a vectorable nozzle 8, to produce forward thrust. In jet-borne flight, however, the doors 3 block the bypass duct 13, the auxiliary air intake 4 is opened to admit air to the second fan 5, and a vectorable nozzle 9 with associated blocker doors 3a and the nozzle 8 are operated by the control means respectively to receive air from the first fan 1 and the exhausts from the second fan 5 and the turbines 10, 11 and 12.

    Abstract translation: 可变循环燃气轮机旁路发动机包括位于发动机入口处的第一风扇1，以向由涡轮11驱动的压缩机2和围绕压缩机壳体的旁路管道13提供空气。 位于旁通管道13中的第二风扇5由自由涡轮12驱动。可控区域辅助进气口4和旁通管道阻塞门3位于第一和第二风扇1,5之间。控制装置对于可选择地操作是有效的 旁通管道阻塞门3和辅助进气口4在操作中改变发动机的旁路比。 因此，在常规翼型飞行中，进气口4关闭，旁通管道13不受阻碍，并且来自旁通管道13和涡轮机10,11和12的组合排气通过尾管14，尾管14具有可向量的喷嘴8 ，产生向前推力。 然而，在喷气式飞行中，门3阻挡旁路管道13，辅助进气口4打开以允许空气进入第二风扇5，并且具有相关联的阻挡门3a和喷嘴8的可向导管9由 所述控制装置分别接收来自所述第一风扇1的空气和来自所述第二风扇5和所述涡轮机10,11和12的排气。

    High by-pass ratio turbojet engine with counterrotating upstream and downstream fans
    7.
    发明授权
    High by-pass ratio turbojet engine with counterrotating upstream and downstream fans 失效
    高旁路比例涡轮发动机，配有上下游和下游风机

    公开(公告)号：US5058379A

    公开(公告)日：1991-10-22

    申请号：US504839

    申请日：1990-04-05

    Applicant: Alain M. J. Lardellier

    Inventor： Alain M. J. Lardellier

    IPC: F02C3/067 ,  F02C3/073 ,  F02K3/065 ,  F02K3/072 ,  F02K3/077

    CPC classification number: F02K3/077 ,  F02K3/065 ,  F02K3/072

    Abstract: A turbojet bypass engine includes an upstream fan of a conventional type also a downstream fan arranged to rotate in the opposite direction to the upstream fan and driven by a free turbine interleaved with the low pressure turbine which drives the upstream fan. The two fans are supplied by separpate overlapping and inverleaved air flow paths which are formed largely within the nacelle structure of the engine, giving the nacelle an ovoide shape which allows such engines with a high bypass ratio to be mounted below the wings of an aircraft.

    Abstract translation: 涡轮喷气旁路发动机包括常规类型的上游风扇和下游风扇，其布置成沿与上游风扇相反的方向旋转，并由与驱动上游风扇的低压涡轮机交错的自由涡轮机驱动。 这两个风扇由主要在发动机的机舱结构内形成的分离的重叠和倒车的空气流动路径供应，使得机舱具有允许具有高旁路比的这种发动机安装在飞行器的机翼下方的向外的形状。

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