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    Counter rotating turbine with reversing speed reduction assembly
    5.
    发明授权
    Counter rotating turbine with reversing speed reduction assembly 有权

    公开(公告)号：US10815881B2

    公开(公告)日：2020-10-27

    申请号：US15709651

    申请日：2017-09-20

    申请人： General Electric Company

    发明人： Jeffrey Donald Clements ,  Darek Tomasz Zatorski ,  Alan Roy Stuart

    IPC分类号： F02C3/067 ,  F02K3/072 ,  F01D5/14 ,  F01D5/03 ,  F01D1/26 ,  F02K3/068 ,  F02C3/107 ,  F02C7/36

    摘要： The present disclosure is directed to a gas turbine engine including a turbine section including a first rotating component interdigitated along a longitudinal direction with a second rotating component. The first rotating component and the second rotating component are each coupled to a speed reduction assembly in counter-rotating arrangement. The first rotating component comprising an outer shroud and a plurality of outer shroud airfoils extended inward along a radial direction from the outer shroud. A connecting member couples the outer shroud to a radially extended first rotor. The second rotating component comprising an inner shroud and a plurality of inner shroud airfoils extended outward along the radial direction from the inner shroud, the plurality of inner shroud airfoils in alternating arrangement along the longitudinal direction with the plurality of outer shroud airfoils. The gas turbine engine defines a radius per unit thrust defined by a maximum radius at the turbine section over a maximum thrust output between approximately 0.0004 to approximately 0.0010 inches per pound thrust.

    ELONGATED GEARED TURBOFAN WITH HIGH BYPASS RATIO
    7.
    发明申请
    ELONGATED GEARED TURBOFAN WITH HIGH BYPASS RATIO 审中-公开

    公开(公告)号：US20190271269A1

    公开(公告)日：2019-09-05

    申请号：US16407505

    申请日：2019-05-09

    申请人： United Technologies Corporation

    发明人： Frederick M. Schwarz ,  Robert E. Malecki

    IPC分类号： F02C7/36 ,  B64D33/02 ,  F02K3/06 ,  F02K3/068 ,  F02C3/10

    摘要： A propulsion system includes a fan, a gear, a turbine configured to drive the gear to, in turn, drive the fan. The turbine has an exit point, and a diameter (Dt) is defined at the exit point. A nacelle surrounds a core engine housing. The fan is configured to deliver air into a bypass duct defined between the nacelle and the core engine housing. A core engine exhaust nozzle is provided downstream of the exit point. A downstream most point of the core engine exhaust nozzle is defined at a distance from the exit point. A ratio of the distance to the diameter is greater than or equal to about 0.90.

    AXIAL COMPRESSOR FOR TIP TURBINE ENGINE
    9.
    发明申请
    AXIAL COMPRESSOR FOR TIP TURBINE ENGINE 有权
    TIP涡轮发动机轴流式压缩机

    公开(公告)号：US20090148292A1

    公开(公告)日：2009-06-11

    申请号：US11719317

    申请日：2004-12-01

    申请人： Gabriel Suciu ,  Gary D. Roberge ,  Brian Merry

    发明人： Gabriel Suciu ,  Gary D. Roberge ,  Brian Merry

    IPC分类号： F02C3/073 ,  F02C7/36 ,  F02C3/107 ,  F02K3/068

    CPC分类号： F02C3/107 ,  F02C3/073 ,  F02C7/36 ,  F02K3/068 ,  F05D2260/40311

    摘要： A tip turbine engine (10) according to the present invention provides at least one gear (90) coupling rotation of a bypass fan (24) to an axial compressor (22), such that the axial compressor (22) is driven by rotation of the fan (24) at a rate different from than the rate of the fan. In one embodiment, the rate of rotation of the axial compressor (22) is increased relative to a rate of rotation of the fan (24). By increasing the rotation rate, the compression provided by the axial compressor is increased, while the number of stages of the axial compressor blades may be reduced. As a result, the length of the axial compressor and the overall length of the tip turbine engine are decreased.

    摘要翻译： 根据本发明的顶端涡轮发动机（10）提供将旁路风扇（24）的旋转耦合到轴向压缩机（22）的至少一个齿轮（90），使得轴向压缩机（22）由 风扇（24）的速度与风扇的速率不同。 在一个实施例中，轴向压缩机（22）的旋转速率相对于风扇（24）的旋转速率增加。 通过提高旋转速度，由轴流式压缩机提供的压缩增加，同时可减小轴向压缩机叶片的级数。 结果，轴流压缩机的长度和末端涡轮发动机的总长度减小。