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179 条记录 (耗时 0.018 秒)

    Aircraft engine
    144.
    发明授权
    Aircraft engine 有权

    公开(公告)号：US11692454B2

    公开(公告)日：2023-07-04

    申请号：US17453501

    申请日：2021-11-04

    申请人： ROLLS-ROYCE plc

    发明人： Benjamin Mohankumar ,  Mark J. Wilson ,  Cesare A. Hall

    IPC分类号： F01D15/12 ,  F02C7/04 ,  F01D25/24 ,  F02K3/068

    CPC分类号： F01D15/12 ,  F01D25/24 ,  F02C7/04 ,  F02K3/068 ,  F05D2220/32 ,  F05D2260/4031

    摘要： An aircraft engine comprising a fan, the fan having a diameter D and including a plurality of fan blades, the fan blades having a sweep metric Stip, each fan blade having a leading edge, and a forward-most portion on the leading edge of each fan blade being in a first reference plane. The aircraft engine further comprises a nacelle, comprising an intake portion forward of the fan, a forward edge on the intake portion being in a second reference plane, wherein the intake portion has a length L measured along an axis of the aircraft engine between the first reference plane and the second reference plane, the aircraft engine having a cruise design point condition Mrel, wherein Mrel is between 0.4 and 0.93, L/D is between 0.2 and 0.45 and Stip is from −1 to 0.1.

    TIP TURBINE ENGINE COMPOSITE TAILCONE
    147.
    发明申请
    TIP TURBINE ENGINE COMPOSITE TAILCONE 审中-公开

    公开(公告)号：US20180106194A1

    公开(公告)日：2018-04-19

    申请号：US15784629

    申请日：2017-10-16

    申请人： UNITED TECHNOLOGIES CORPORATION

    发明人： Brian Merry ,  Gabriel L. Suciu ,  James W. Norris

    IPC分类号： F02C3/073 ,  F02K3/068 ,  F02K1/04

    CPC分类号： F02C3/073 ,  F02K1/04 ,  F02K3/068 ,  F05D2300/603 ,  F05D2300/614 ,  Y02T50/672 ,  Y10T29/49346

    摘要： A non-metallic tailcone in a tip turbine engine includes a tapered wall structure disposed about a central axis. The non-metallic tailcone is fastened to a structural frame in the aft portion of the tip turbine engine. The tip turbine engine produces a first temperature gas stream from a first output source and a second temperature gas stream from a second output source. The second temperature gas stream is a lower temperature than the first temperature gas stream. The second temperature gas stream is discharged at an inner diameter of the tip turbine engine over an outer surface of the tailcone. Discharging the cooler second temperature gas stream at the inner diameter allows a non-metallic to be used to form the tailcone.

    Particle separator for tip turbine engine
    149.
    发明授权
    Particle separator for tip turbine engine 有权
    尖端涡轮发动机的颗粒分离器

    公开(公告)号：US09003759B2

    公开(公告)日：2015-04-14

    申请号：US11719799

    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： F02G3/00 ,  F02C7/052 ,  F01D5/02 ,  F02C3/073 ,  F02C7/05 ,  F02K3/068

    CPC分类号： F02C7/052 ,  F01D5/022 ,  F02C3/073 ,  F02C7/05 ,  F02K3/068 ,  F05D2250/71

    摘要： A particle separator (20) for a tip turbine engine (10) includes a generally conical inclined leading surface (24) leading to a maximum radius (25) and a tapered trailing surface (56) having a radius at all points therealong less than the maximum radius (25). The trailing surface (56) of the particle separator (20) is tapered and/or curved radially inwardly away from the maximum radius (25). Air flowing toward the core airflow inlet is first diverted radially outwardly by the inclined leading surface (24) of the particle separator (20) to the maximum radius (25) of the particle separator (20). The air then follows the trailing surface (56) radially inwardly to flow axially into the core airflow inlet. While the air can follow the contours of the particle separator (20) around the maximum radius (25) and into the core airflow inlet, any particles, such as dirt, will have more inertia and will pass radially outwardly of the core airflow inlet through the bypass fan.

    摘要翻译： 用于尖端涡轮发动机（10）的颗粒分离器（20）包括通向圆锥形的倾斜前导表面（24），其导致最大半径（25）和锥形后表面（56），所述锥形后表面在所有点处具有小于 最大半径（25）。 颗粒分离器（20）的后表面（56）从最大半径（25）向内径向向内渐缩和/或弯曲。 首先通过颗粒分离器（20）的倾斜引导表面（24）向颗粒分离器（20）的最大半径（25）径向向外转向空气流向核心气流入口。 然后空气径向向内跟随后表面（56），从而轴向流入核心气流入口。 当空气可以沿着最大半径（25）和颗粒气流入口跟随颗粒分离器（20）的轮廓时，任何颗粒（例如污物）将具有更大的惯性并且将通过核心气流入口的径向向外通过 旁路风扇。

    Counter-rotating gearbox for tip turbine engine
    150.
    发明授权
    Counter-rotating gearbox for tip turbine engine 有权
    尖端涡轮发动机的反向旋转变速箱

    公开(公告)号：US08950171B2

    公开(公告)日：2015-02-10

    申请号：US13089450

    申请日：2011-04-19

    申请人： Gabriel Suciu ,  Brian Merry ,  Michael E. McCune

    发明人： Gabriel Suciu ,  Brian Merry ,  Michael E. McCune

    IPC分类号： B63H11/00 ,  F02C3/073 ,  F02C3/107 ,  F02C3/08 ,  F02K3/068 ,  F02C7/36 ,  F04D25/04 ,  F16H48/10

    CPC分类号： F02C3/08 ,  F02C3/073 ,  F02C3/107 ,  F02C7/36 ,  F02K3/068 ,  F04D25/045 ,  F05D2260/40311 ,  F16H48/10

    摘要： A tip turbine engine provides an axial compressor rotor that is counter-rotated relative to a fan. A planetary gearset couples rotation of a fan to an axial compressor rotor, such that the axial compressor rotor is driven by rotation of the fan in a rotational direction opposite that of the fan. By counter-rotating the axial compressor rotor, a final stage of compressor vanes between the final stage of compressor blades and inlets to the hollow fan blades of the fan are eliminated. As a result, the length of the axial compressor and the overall length of the tip turbine engine are decreased.

    摘要翻译： 尖端涡轮发动机提供相对于风扇反向旋转的轴向压缩机转子。 行星齿轮组将风扇的旋转耦合到轴向压缩机转子，使得轴向压缩机转子通过风扇沿与风扇相反的旋转方向的旋转来驱动。 通过逆向旋转轴向压缩机转子，消除了在压缩机叶片的最后阶段和到风扇的中空风扇叶片的入口之间的压缩机叶片的最后阶段。 结果，轴流压缩机的长度和末端涡轮发动机的总长度减小。