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72 条记录 (耗时 0.025 秒)

    Turbine coolant supply system
    31.
    发明授权
    Turbine coolant supply system 有权
    涡轮冷却液供应系统

    公开(公告)号：US09091173B2

    公开(公告)日：2015-07-28

    申请号：US13485579

    申请日：2012-05-31

    申请人： John H. Mosley ,  Ioannis Alvanos ,  Phililp S. Stripinis ,  Douglas Paul Freiberg ,  Hector M. Pinero ,  John J. O'Connor ,  Jon Pietrobon

    发明人： John H. Mosley ,  Ioannis Alvanos ,  Phililp S. Stripinis ,  Douglas Paul Freiberg ,  Hector M. Pinero ,  John J. O'Connor ,  Jon Pietrobon

    IPC分类号： F01D5/08 ,  F01D25/12

    CPC分类号： F01D5/082 ,  F01D25/12

    摘要： A gas turbine engine configured to rotate in a circumferential direction about an axis extending through a center of the gas turbine engine comprises a turbine stage. The turbine stage comprises a disk, a plurality of blades and a mini-disk. The disk comprises an outer diameter edge having slots, an inner diameter bore surrounding the axis, a forward face, and an aft face. The plurality of blades is coupled to the slots. The mini-disk is coupled to the aft face of the rotor to define a cooling plenum therebetween in order to direct cooling air to the slots. In one embodiment of the invention, the cooling plenum is connected to a radially inner compressor bleed air inlet through all rotating components so that cooling air passes against the inner diameter bore.

    摘要翻译： 构造成围绕延伸穿过燃气涡轮发动机的中心的轴线在圆周方向上旋转的燃气涡轮发动机包括涡轮级。 涡轮级包括盘，多个叶片和小型盘。 盘包括具有槽的外径边缘，围绕轴线的内径孔，前表面和后表面。 多个叶片耦合到槽。 微型盘联接到转子的后表面以在其间限定冷却室，以便将冷却空气引导到狭槽。 在本发明的一个实施例中，冷却气室通过所有旋转部件连接到径向内部的压缩机排放空气入口，使得冷却空气抵靠内径孔。

    TURBINE COOLANT SUPPLY SYSTEM
    36.
    发明申请
    TURBINE COOLANT SUPPLY SYSTEM 有权
    涡轮冷却液供应系统

    公开(公告)号：US20130323010A1

    公开(公告)日：2013-12-05

    申请号：US13485579

    申请日：2012-05-31

    申请人： John H. Mosley ,  Ioannis Alvanos ,  Phililp S. Stripinis ,  Douglas Paul Freiberg ,  Hector M. Pinero ,  John J. O'Connor ,  Jon Pietrobon

    发明人： John H. Mosley ,  Ioannis Alvanos ,  Phililp S. Stripinis ,  Douglas Paul Freiberg ,  Hector M. Pinero ,  John J. O'Connor ,  Jon Pietrobon

    IPC分类号： F01D5/18

    CPC分类号： F01D5/082 ,  F01D25/12

    摘要： A gas turbine engine configured to rotate in a circumferential direction about an axis extending through a center of the gas turbine engine comprises a turbine stage. The turbine stage comprises a disk, a plurality of blades and a mini-disk. The disk comprises an outer diameter edge having slots, an inner diameter bore surrounding the axis, a forward face, and an aft face. The plurality of blades is coupled to the slots. The mini-disk is coupled to the aft face of the rotor to define a cooling plenum therebetween in order to direct cooling air to the slots. In one embodiment of the invention, the cooling plenum is connected to a radially inner compressor bleed air inlet through all rotating components so that cooling air passes against the inner diameter bore.

    摘要翻译： 构造成围绕延伸穿过燃气涡轮发动机的中心的轴线在圆周方向上旋转的燃气涡轮发动机包括涡轮级。 涡轮级包括盘，多个叶片和小型盘。 盘包括具有槽的外径边缘，围绕轴线的内径孔，前表面和后表面。 多个叶片耦合到槽。 微型盘联接到转子的后表面以在其间限定冷却室，以便将冷却空气引导到狭槽。 在本发明的一个实施例中，冷却气室通过所有旋转部件连接到径向内部的压缩机排放空气入口，使得冷却空气抵靠内径孔。

    BUFFER COOLING SYSTEM PROVIDING GAS TURBINE ENGINE ARCHITECTURE COOLING
    37.
    发明申请
    BUFFER COOLING SYSTEM PROVIDING GAS TURBINE ENGINE ARCHITECTURE COOLING 有权
    缓冲器冷却系统提供气体涡轮发动机结构冷却

    公开(公告)号：US20130219918A1

    公开(公告)日：2013-08-29

    申请号：US13405502

    申请日：2012-02-27

    申请人： Gabriel L. Suciu ,  Ioannis Alvanos ,  Camelia Galos

    发明人： Gabriel L. Suciu ,  Ioannis Alvanos ,  Camelia Galos

    IPC分类号： F02C6/08 ,  F02C3/00

    CPC分类号： F01D5/081 ,  F02C6/08 ,  F02C7/06 ,  F02C7/185

    摘要： A gas turbine engine includes a buffer cooling system having a first heat exchanger, a first passageway, a second passageway and a third passageway. The first heat exchanger exchanges heat with a bleed airflow to provide a conditioned airflow. The first passageway communicates a first portion of the conditioned airflow to a high pressure compressor of the gas turbine engine, the second passageway communicates a second portion of the conditioned airflow to a high pressure turbine of the gas turbine engine, and the third passageway communicates a third portion of the conditioned airflow to a low pressure turbine of the gas turbine engine.

    摘要翻译： 燃气涡轮发动机包括具有第一热交换器，第一通道，第二通道和第三通道的缓冲冷却系统。 第一热交换器与放气气流交换热量以提供调节气流。 第一通道将调节气流的第一部分与燃气涡轮发动机的高压压缩机连通，第二通道将调节气流的第二部分连通到燃气涡轮发动机的高压涡轮机，并且第三通道 调节气流的第三部分到燃气涡轮发动机的低压涡轮机。

    Turbine cooling air sealing
    38.
    发明授权
    Turbine cooling air sealing 有权
    涡轮冷却空气密封

    公开(公告)号：US08517666B2

    公开(公告)日：2013-08-27

    申请号：US11224613

    申请日：2005-09-12

    申请人： Ioannis Alvanos ,  Rajendra K. Agrawal ,  Hector M. Pinero

    发明人： Ioannis Alvanos ,  Rajendra K. Agrawal ,  Hector M. Pinero

    IPC分类号： F01D5/08 ,  F01D5/18

    CPC分类号： F01D5/081 ,  F01D11/001 ,  F01D25/12 ,  F02C7/18 ,  F02C7/28

    摘要： A turbine engine section has a stationary vane stage and a rotating blade stage. The blade stage is spaced from the vane stage to form an annular chamber therebetween. A manifold delivers a pressurized fluid to the chamber. An outer diameter (OD) sealing system restricts leakage of the pressurized fluid from the chamber. An inner diameter (ID) sealing system restricts leakage of the pressurized fluid from the chamber. A flow guide extends radially between the inner diameter sealing system and the manifold. The flow guide bisects the chamber to form a stationary chamber portion and a rotating chamber portion, the rotating chamber portion at least partially along a disk of the first blade stage.

    摘要翻译： 涡轮发动机部分具有静止叶片台和旋转叶片台。 叶片台与叶片台间隔开以在它们之间形成环形室。 歧管将加压流体输送到腔室。 外径（OD）密封系统限制加压流体从腔室泄漏。 内径（ID）密封系统限制加压流体从腔室泄漏。 流动引导件在内径密封系统和歧管之间径向延伸。 流动导向装置将室平分成一个固定室部分和一个旋转室部分，旋转室部分至少部分地沿着第一叶片台的圆盘。