Axial flow turbine nozzle
    1.
    发明公开
    Axial flow turbine nozzle 失效
    轴流式涡轮喷嘴

    公开(公告)号:EP0058532A3

    公开(公告)日:1983-04-27

    申请号:EP82300699

    申请日:1982-02-12

    IPC分类号: F01D09/04 F01D11/00 F02C07/00

    CPC分类号: F01D9/04

    摘要: In an axial flow turbine, such as an exhaust gas turbine, in order to prevent the driving gas from escaping through the slits (9) formed in an outer nozzle ring (8) of integral type construction, which divide said ring into several segments so as to facilitate differential thermal expansion, and thus by-passing the regular flow of the gas through the nozzle structure, filler metals (15) are located in the slits. Preferably, the radial depth of the filler metals is shorter than the slits, and they are fixed e.g. by fixing bolts (17) and tongues (16) provided on the filler metals, so as not to protrude beyond the inner diameter of the outer nozzle ring.

    Gas turbine engine assembly
    2.
    发明公开
    Gas turbine engine assembly 失效
    气体涡轮发动机总成

    公开(公告)号:EP0213055A3

    公开(公告)日:1988-10-19

    申请号:EP86630115

    申请日:1986-07-28

    发明人: Prario, Aldo

    IPC分类号: F01D09/04 F01D11/08 F01D25/24

    摘要: Annular, circumferentially segmented components (42, 44) of a gas turbine engine are secured to a support structure (40) by C-shaped couplings (104, 104a) which prevent movement of the components (42, 44) in a radial and circumferential direction. The coupling (104, 104a) has spaced apart legs (106,106a,108,108)which trap the component (42) and support structure (40) there­between, and a key (116) between the legs (106, 106a, 108, 108a) which engages a keyway formed by cooperating slots (102a, 78a) in the component (42) and support structure (40).

    A stator vane assembly for a turbine machine
    3.
    发明公开
    A stator vane assembly for a turbine machine 失效
    涡轮机定子风机组件

    公开(公告)号:EP0079216A3

    公开(公告)日:1983-11-16

    申请号:EP82305901

    申请日:1982-11-05

    IPC分类号: F01D09/04 F02K03/06 F02C07/05

    摘要: An annular inlet stator vane assembly (18) positioned upstream of the bypass and core flow passages (24, 26) of a turbofan jet engine is provided with energy-absorbing bendable vanes (38) which are fixedly secured to a radially outer support shroud (42) and extend through radial slots (96,98) in an inner shroud (40). The radially inner ends of the vanes (38) are releasably secured to the inner shroud (40) by specially designed deformable retaining clips (102, 124) which are welded both to the inner ends of the vanes (38) and to the shroud (40). These features of the vane assembly (18) cooperate to limit the circumferential extent of inlet vane damage in the event of ingestion into the engine of foreign bodies such as birds, and to help to prevent damaged parts of the vane assembly from being drawn through the core passage of the engine or blocking surch core passage.

    Clearance control for turbine blade tips
    5.
    发明公开
    Clearance control for turbine blade tips 失效
    涡轮叶片的间隙控制

    公开(公告)号:EP0103260A3

    公开(公告)日:1984-09-26

    申请号:EP83108779

    申请日:1983-09-06

    申请人: HITACHI, LTD.

    IPC分类号: F01D11/08 F01D09/04

    CPC分类号: F01D11/18 F01D9/041

    摘要: A turbine comprising a casing in which are disposed a turbine rotor assembly which provides a plurality of turbine blades and a guide vane assembly which provides a plurality of guide vane segments, and there being shrouds spaced from turbine blade tips. To control the clearance between the turbine blade tips and the shrouds at a small value by simple structure, the guide vane segments are made movable freely in the radial direction and inside parts of the guide vane segments are fixed to a stationary member.