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143 条记录 (耗时 0.015 秒)

    Counter-vortex paired film cooling hole design
    21.
    发明申请
    Counter-vortex paired film cooling hole design 审中-公开
    逆流成对薄膜冷却孔设计

    公开(公告)号：US20090304494A1

    公开(公告)日：2009-12-10

    申请号：US12157115

    申请日：2008-06-06

    申请人： Christopher W. Strock ,  Paul M. Lutjen

    发明人： Christopher W. Strock ,  Paul M. Lutjen

    IPC分类号： F01D5/18

    CPC分类号： F23R3/04 ,  F01D5/186 ,  F05D2240/121 ,  F05D2240/303 ,  F05D2250/11 ,  F05D2250/12 ,  F05D2250/141 ,  F05D2250/25 ,  F05D2260/2212 ,  F23R2900/03042

    摘要： An apparatus for use in a gas turbine engine includes a wall defining an exterior face, a first film cooling passage extending through the wall for providing film cooling to the exterior face of the wall, and a second film cooling passage extending through the wall adjacent to the first film cooling passage for providing film cooling to the exterior face of the wall. The first film passage includes a first vortex-generating structure for inducing a vortex in a first rotational direction in a cooling fluid passing therethrough, and the second film passage includes a second vortex-generating structure for inducing a vortex in a second rotational direction in a cooling fluid passing therethrough. The first and second rotational directions are substantially opposite one another.

    摘要翻译： 用于燃气涡轮发动机的装置包括限定外表面的壁，延伸穿过壁的第一膜冷却通道，用于向壁的外表面提供膜冷却;以及第二膜冷却通道，其延伸穿过邻近壁的壁 第一膜冷却通道，用于向壁的外表面提供膜冷却。 第一膜通道包括用于在通过其中的冷却流体中沿第一旋转方向诱导涡流的第一涡流产生结构，并且第二膜通道包括用于在第二旋转方向上引入涡流的第二涡流产生结构 冷却液通过其中。 第一和第二旋转方向基本上彼此相对。

    Gas turbine blade shroud
    22.
    发明授权
    Gas turbine blade shroud 有权
    燃气轮机叶片护罩

    公开(公告)号：US07628587B2

    公开(公告)日：2009-12-08

    申请号：US11589262

    申请日：2006-10-30

    申请人： Jose Anguisola McFeat ,  Ingolf Schulz ,  Dirk Wilhelm

    发明人： Jose Anguisola McFeat ,  Ingolf Schulz ,  Dirk Wilhelm

    IPC分类号： B63H1/16

    CPC分类号： F01D5/141 ,  B33Y80/00 ,  F01D5/225 ,  F05D2230/90 ,  F05D2240/80 ,  F05D2250/12 ,  F05D2250/13 ,  F05D2250/141

    摘要： A gas turbine blade shroud includes a platform and one or more fins extending toward a stator and side rails that extend radially toward the stator and along the edge of the platform. The increased wall thickness in the side regions of the blade shroud effects an increase in stiffness and a decrease in deformation during turbine operation. Due to a localised increase in wall thickness the mass of the blade shroud can be minimized such that mechanical loading is not significantly increased. The side rails can improve a lining up of adjacent blades and decrease a probability of hot gas leakage into the cavity between blade shroud and stator. The side rails have profile shapes that can be optimised in view of stiffness and mechanical loading and are suitable for casting. The blade shroud with side rails can have an improved life time.

    摘要翻译： 燃气轮机叶片护罩包括平台和朝向定子延伸的一个或多个翅片和沿着定子并沿着平台的边缘径向延伸的侧轨道。 在叶片护罩的侧部区域中增加的壁厚在涡轮机操作期间增加刚度和变形减小。 由于壁厚的局部增加，叶片护罩的质量可以最小化，使得机械负载不会显着增加。 侧轨可以改善相邻叶片的排列，并降低热气体泄漏到叶片护罩和定子之间的空腔的可能性。 侧轨具有可根据刚度和机械载荷优化的轮廓形状，并且适合于铸造。 具有侧轨的刀片护罩可以具有改善的寿命。

    Compliant plate seals for turbomachinery
    23.
    发明授权
    Compliant plate seals for turbomachinery 有权
    符合涡轮机械的板式密封件

    公开(公告)号：US07419164B2

    公开(公告)日：2008-09-02

    申请号：US11504061

    申请日：2006-08-15

    申请人： Shorya Awtar ,  Norman Arnold Turnquist

    发明人： Shorya Awtar ,  Norman Arnold Turnquist

    IPC分类号： F16J15/447

    CPC分类号： F16J15/3292 ,  F01D11/003 ,  F01D11/02 ,  F05D2250/12 ,  F05D2250/13 ,  F05D2250/70 ,  Y10T29/4932

    摘要： A shaft seal serves to reduce leakage between a rotating shaft and a static shell. The shaft seal includes a plurality of compliant plate members, each having a root and a tip. The compliant plate members are secured to the static shell at their root in facing relation. The tips of the compliant plate members define a sealing ring between the static shell and the rotating shaft. An axial flow resistance member is disposed within the compliant plate members and serves as a barrier to axial leakage flow between the compliant plate members.

    摘要翻译： 轴密封件用于减少旋转轴和静态外壳之间的泄漏。 轴封包括多个柔性板构件，每个具有根部和尖端。 柔性板构件在其根部处以面对关系固定到静态壳体上。 柔性板构件的尖端在静态壳和旋转轴之间限定密封环。 轴向阻力构件设置在柔性板构件内并用作在柔性板构件之间的轴向泄漏流动的障碍。

    Film cooled slotted wall
    25.
    发明授权
    Film cooled slotted wall 失效
    薄膜冷却开槽墙

    公开(公告)号：US5660525A

    公开(公告)日：1997-08-26

    申请号：US94998

    申请日：1993-07-23

    申请人： Ching-Pang Lee ,  Ronald Scott Bunker ,  Nesim Abuaf ,  Steven Joseph Brzozowski

    发明人： Ching-Pang Lee ,  Ronald Scott Bunker ,  Nesim Abuaf ,  Steven Joseph Brzozowski

    IPC分类号： F01D5/18

    CPC分类号： F01D5/186 ,  F05D2250/12 ,  F05D2250/121 ,  F05D2260/202

    摘要： A wall adapted for use in a gas turbine engine between a first and a hotter second fluid includes a first side over which is flowable the first fluid, and an opposite second side over which is flowable the second fluid. An elongate slot extends inwardly from the second side and is disposed in flow communication with a plurality of longitudinally spaced apart holes extending inwardly from the first side. The holes are disposed at a compound angle relative to the second side for discharging the first fluid obliquely into the slot and at a shallow discharge angle from the slot along the second side. The holes are also disposed in converging pairs to impinge together in the slot the first fluid channeled therethrough. In a preferred embodiment, the slot has an aft surface including a plurality of longitudinally spaced apart grooves extending from the holes to the wall second side.

    摘要翻译： 适于在第一和第二热液体之间的燃气涡轮发动机中使用的壁包括可流过第一流体的第一侧和可流动第二流体的相对的第二侧。 细长狭槽从第二侧向内延伸，并且设置成与从第一侧向内延伸的多个纵向间隔开的孔流动连通。 孔以相对于第二侧的复合角度设置，用于将第一流体倾斜地排放到槽中，并且沿着沿着第二侧的槽沿浅放电角排放。 这些孔也以会聚对设置，以将槽中的第一流体冲入其中。 在优选实施例中，槽具有包括从孔延伸到壁第二侧的多个纵向间隔开的槽的后表面。

    Convergent-divergent film coolant passage
    26.
    发明授权
    Convergent-divergent film coolant passage 失效
    会聚发散薄膜冷却液通道

    公开(公告)号：US4705455A

    公开(公告)日：1987-11-10

    申请号：US81209285

    申请日：1985-12-23

    申请人： UNITED TECHNOLOGIES CORP

    发明人： SAHM MICHAEL K ,  MILANO ROBERT

    IPC分类号： F01D5/18 ,  F01D9/02

    CPC分类号： F01D5/186 ,  F05D2250/12 ,  F05D2250/121 ,  F05D2250/323 ,  F05D2250/324 ,  Y02T50/673 ,  Y02T50/676

    摘要： A coolant passage through a wall to be cooled, such as the wall of a hollow airfoil, is shaped and oriented to eject coolant fluid therefrom within the boundary layer of hot gases flowing over the surface to film cool the wall downstream of the outlet. The passage includes a metering portion near its inlet, followed by a diffusing portion and nozzle portion. The nozzle portion, adjacent the outlet, simultaneously diverges and converges in mutually perpendicular directions to produce a more uniform coolant velocity profile, which results in increased coolant area coverage and improved cooling effectiveness.

    摘要翻译： 通过待冷却的壁（例如中空翼片的壁）的冷却剂通道被成形并定向成在其流过表面的热气体的边界层内从其中排出冷却剂流体，以将出口下游的壁冷却。 通道包括在其入口附近的计量部分，随后是扩散部分和喷嘴部分。 邻近出口的喷嘴部分同时沿相互垂直的方向发散并收敛，以产生更均匀的冷却剂速度分布，这导致冷却剂面积的增加和冷却效率的提高。

    Articulating slider for nacelle
    27.
    发明授权
    Articulating slider for nacelle 有权

    公开(公告)号：US11754019B2

    公开(公告)日：2023-09-12

    申请号：US17554067

    申请日：2021-12-17

    申请人： ROHR, INC.

    发明人： Jihad Ramlaoui

    IPC分类号： F02K1/72 ,  B64D29/06

    CPC分类号： F02K1/72 ,  F05D2250/12 ,  F05D2250/34 ,  F05D2260/50

    摘要： A thrust reverser may comprise translating sleeve panel. A first articulating slider and a second articulating slider may be located at a circumferential end of the translating sleeve panel. Each of the first articulating slider and the second articulating slider may include a slider bar and a slider ball. The slider ball may be attached to the translating sleeve panel and located in a spherical opening defined by the slider bar.