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    SEAL STRUCTURE
    96.
    发明申请
    SEAL STRUCTURE 审中-公开

    公开(公告)号：US20170284218A1

    公开(公告)日：2017-10-05

    申请号：US15507436

    申请日：2015-07-07

    Applicant: MITSUBISHI HITACHI POWER SYSTEMS, LTD.

    Inventor： Takahiro KONDO ,  Shinya HASHIMOTO ,  Kenta TANIGUCHI

    IPC: F01D11/14 ,  F01D11/10 ,  F02C7/24 ,  F01D11/00

    Abstract: A seal structure includes: a first member and a second member disposed so as to face a combustion gas flow passage; a third member disposed on the outer side of the combustion gas flow passage; a heat-resistant coating formed on at least one of a first end face and a second end face, on the side of the face closer to the combustion gas flow passage; and a contact part disposed in the first end face and the second end face, further on the outer side than the heat-resistant coating. When the first member and the second member move relatively toward each other, the contact part restricts the relative movement by coming in contact in a state where a clearance is left between the heat-resistant coating and the face facing the heat-resistant coating.

    SUPPORT ASSEMBLY FOR A GAS TURBINE ENGINE
    98.
    发明申请
    SUPPORT ASSEMBLY FOR A GAS TURBINE ENGINE 有权
    燃气涡轮发动机支撑组件

    公开(公告)号：US20160341061A1

    公开(公告)日：2016-11-24

    申请号：US14715844

    申请日：2015-05-19

    Applicant: United Technologies Corporation

    Inventor： Andrew S. Miller ,  Peter Balawajder

    IPC: F01D11/14 ,  F01D25/28

    CPC classification number: F01D11/14 ,  F01D11/18 ,  F01D25/28 ,  F05D2220/32 ,  F05D2270/305

    Abstract: A support assembly for a gas turbine engine includes a control ring that extends about a circumferential axis. A plurality of first supports has a cavity that receives the control ring. A plurality of cover plates are attached to the first plurality of supports and enclose the cavity.

    Abstract translation: 用于燃气涡轮发动机的支撑组件包括围绕圆周轴线延伸的控制环。 多个第一支撑件具有接收控制环的空腔。 多个盖板附接到第一多个支撑件并且包围空腔。

    Compressor tip clearance control and gas turbine engine
    99.
    发明授权
    Compressor tip clearance control and gas turbine engine 有权
    压缩机顶端间隙控制和燃气轮机

    公开(公告)号：US09458855B2

    公开(公告)日：2016-10-04

    申请号：US13334607

    申请日：2011-12-22

    Applicant: Douglas David Dierksmeier ,  Steven Lester Grant ,  James Christopher Muskat

    Inventor： Douglas David Dierksmeier ,  Steven Lester Grant ,  James Christopher Muskat

    IPC: F04D29/58 ,  F01D25/14 ,  F02C6/08 ,  F04D29/16 ,  F01D11/24 ,  F01D11/14 ,  F01D11/20

    CPC classification number: F04D29/164 ,  F01D11/14 ,  F01D11/20 ,  F01D11/24 ,  F01D25/14 ,  F02C6/08 ,  F05D2240/11 ,  F05D2260/201 ,  Y02T50/676

    Abstract: A unique compressor includes a rotating compressor blade having a blade tip; a compressor case having a blade track disposed opposite the blade tip; and a tip clearance control system including a fluid impingement structure. This structure has a plurality of openings to impinge a fluid received from a diffuser onto the compressor case. The tip clearance control system is configured to control a clearance between the blade tip and the blade track by impinging the fluid onto the compressor case and modulating the same with a valve in fluid communication with the diffuser. A further form includes a unique gas turbine engine having a compressor with a compressor blade tip, a compressor case disposed opposite the blade tip, and a fluid impingement structure having openings to impinge a fluid onto the case. Also included are other apparatuses, systems, devices, hardware, methods, and combinations for compressor blade tip clearance control.

    Abstract translation: 独特的压缩机包括具有叶片尖端的旋转压缩机叶片; 压缩机壳体，其具有与叶片尖端相对设置的叶片轨道; 以及包括流体冲击结构的顶端间隙控制系统。 该结构具有多个开口以将从扩散器接收的流体冲击到压缩机壳体上。 顶端间隙控制系统构造成通过将流体冲击到压缩机壳体上并通过与扩散器流体连通的阀来调节其而控制叶片尖端和叶片轨道之间的间隙。 另外的形式包括具有压缩机的独特的燃气涡轮发动机，其具有压缩机叶片尖端，与叶片尖端相对设置的压缩机壳体和具有将流体冲击到壳体上的开口的流体冲击结构。 还包括用于压缩机叶片顶端间隙控制的其他装置，系统，装置，硬件，方法和组合。

    EXPANSION TURBINE
    100.
    发明申请
    EXPANSION TURBINE 审中-公开
    膨胀涡轮机

    公开(公告)号：US20160237841A1

    公开(公告)日：2016-08-18

    申请号：US15027201

    申请日：2014-09-11

    Applicant: EXERGY S.P.A.

    Inventor： Claudio SPADACINI ,  Dario RIZZI

    IPC: F01D11/14 ,  F01D25/24 ,  F01K7/16 ,  F01D5/04 ,  F01D9/04

    CPC classification number: F01D11/14 ,  F01D1/06 ,  F01D5/04 ,  F01D9/041 ,  F01D11/003 ,  F01D25/24 ,  F01K7/16 ,  F05D2230/70 ,  F05D2230/72 ,  F05D2240/55 ,  F05D2240/60

    Abstract: An expansion turbine including: a stator, a rotor facing the stator, a short pipe, a shaft rotatably mounted in the short pipe and removably connected to the rotor. The shaft is extractable from the short pipe from the side opposite said rotor. The turbine includes devices removably connecting the rotor to the shaft having a handling portion at a rotor front face. A front static seal, between the rotor and stator, at a radially inner position with respect to an expansion volume between the stator and rotor. The front static seal is mobile between a first position at which a passage is cleared between the stator and the rotor in fluid communication with the expansion volume, and a second position which seals the passage and isolates the expansion volume from a space for access to said handling portion. The front static seal may variable geometry and be an inflatable gasket.

    Abstract translation: 一种膨胀涡轮，包括：定子，面向定子的转子，短管，可旋转地安装在短管中并可拆卸地连接到转子的轴。 轴可从短管从与转子相对的一侧抽出。 涡轮机包括可移除地将转子连接到轴上的装置，该转轴在转子正面具有处理部分。 在转子和定子之间的相对于定子和转子之间的膨胀体积的径向内部位置处的前静态密封件。 前静态密封件在第一位置和第二位置之间是可移动的，第一位置在定子和与膨胀容积流体连通的转子之间清除通道，第二位置密封通道并将膨胀体积与用于进入所述膨胀容积的空间隔离 处理部分。 前静电密封件可以具有可变的几何形状，并且是可充气垫圈。

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