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    DAMPER AND SEAL OF TURBINE BLADE
    1.
    发明专利
    DAMPER AND SEAL OF TURBINE BLADE 失效

    公开(公告)号：JPH1082301A

    公开(公告)日：1998-03-31

    申请号：JP17138497

    申请日：1997-06-27

    Applicant: UNITED TECHNOLOGIES CORP

    Inventor： GONSOR MICHAEL ,  KELLY III SANFORD E ,  HOUSTON DAVID P

    IPC: F01D5/10 ,  F01D5/22 ,  F01D5/26 ,  F01D5/30 ,  F01D11/00 ,  F16F7/00 ,  F16F15/02

    Abstract: PROBLEM TO BE SOLVED: To provide a damper that is able to damp the extent of vibration by means of being yet smoother. SOLUTION: A damper 40 for a turbine blade of a gas turbine engine is provided with a body part 50, and further it is provided with at least one extension end 52 working in noncontact with the radial inner end of two adjacent blade platforms 28, and installed to strengthen the damping performance of this damper 40 and the radial support of a seal 2. This seal 42 to be related for the turbine engine is provided with a support part and a seal part 48, and further it is also provided with a locator, being joined with a locking structure of the blade, and to hold the seal 42 at a proper axial position in regard to the radial inner surface of the adjacent platform. This seal 42 may have a projection to check the setting of the damper and the seal to the blade in the case where they are set up in an inappropriate position, in order to prevent any improper assembly in addition.

    INTEGRATED DAMPER/SEAL OF TURBINE BLADE
    2.
    发明专利
    INTEGRATED DAMPER/SEAL OF TURBINE BLADE 失效

    公开(公告)号：JPH10196305A

    公开(公告)日：1998-07-28

    申请号：JP35432497

    申请日：1997-12-24

    Applicant: UNITED TECHNOLOGIES CORP

    Inventor： HOUSTON DAVID P ,  PELLAND NATALIE A ,  GONSOR MICHAEL ,  AIREY DAVID

    IPC: F01D5/26 ,  F01D5/30 ,  F01D11/00

    Abstract: PROBLEM TO BE SOLVED: To improve a vibration damping and seal effect of a platform extending inside in the radial direction by having a certain angle from a lengthwise directional shaft by providing a seal part extending inside in the radial direction by having a certain angle from a plane of a damper part to contact with an adjacent blade platform. SOLUTION: A turbine rotor blade 13 has aerofoil 22 to receive kinetic energy from a gas flow 24, and this extends from a radial directional outside surface 26 of a platform 28. The blade 13 also has a pair of platform support parts 36 and 38, a neck 40 and a bottom part 42 having a fir-tree-shaped cross section, and an integrated damper/seal joining body 46 is arranged under a radial directional inside surface 30 of the platform 28. The joining body 46 is composed of a damper part 48 and a seal part 50, and the damper part 48 has rigidity, and is arranged to reduce vibration between blades 13, and the seal part 50 is formed so as to extend inside in the radial direction from an end part of the damper part 48 by having a certain angle.

    7.
    发明专利
    未知

    公开(公告)号：DE69328786T2

    公开(公告)日：2000-10-26

    申请号：DE69328786

    申请日：1993-11-09

    Applicant: UNITED TECHNOLOGIES CORP

    Inventor： CHLUS A ,  GONSOR MICHAEL ,  HOUSTON P ,  KUDRA D

    IPC: F01D5/26 ,  F01D5/22 ,  F01D11/00

    Abstract: An integrated damper and windage cover 52 has a windage cover portion 56 cantilevered at the upstream end, free of contact with the blade platform 24, 32. The contact portion 54 is rigid and bears against the underside of the blade platform 24, spanning blade platform clearance 50.

    10.
    发明专利
    未知

    公开(公告)号：DE69328786D1

    公开(公告)日：2000-07-06

    申请号：DE69328786

    申请日：1993-11-09

    Applicant: UNITED TECHNOLOGIES CORP

    Inventor： CHLUS A ,  GONSOR MICHAEL ,  HOUSTON P ,  KUDRA D

    IPC: F01D5/26 ,  F01D5/22 ,  F01D11/00

    Abstract: An integrated damper and windage cover 52 has a windage cover portion 56 cantilevered at the upstream end, free of contact with the blade platform 24, 32. The contact portion 54 is rigid and bears against the underside of the blade platform 24, spanning blade platform clearance 50.

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