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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
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.
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Patent Agency Ranking
公开(公告)号：JPH10196309A
公开(公告)日：1998-07-28
申请号：JP35432597
申请日：1997-12-24
Applicant: UNITED TECHNOLOGIES CORP
Inventor： AIREY DAVID , PELLAND NATALIE A , HOUSTON DAVID P
Abstract: PROBLEM TO BE SOLVED: To provide a turbine blade platform seal device. SOLUTION: A seal for the turbine blade 13 of a gas turbine engine is clearly shown. The seal is provided with a seal part having two small parts, and the small parts are longitudinally offset with each other. Adjoining turbine plates 13 having an inside platform 28 surface offset in a longitudinal direction are sealed together by the seal. The offset between the seal small parts approximately corresponds to an offset amount between the inside surfaces of the platform 28.
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公开(公告)号：DE69728508T2
公开(公告)日：2004-08-12
申请号：DE69728508
申请日：1997-12-23
Applicant: UNITED TECHNOLOGIES CORP
Inventor： HOUSTON DAVID P , AIREY DAVID , PELLAND NATALIE A
Abstract: A seal for a turbine blade in a gas turbine engine has a sealing portion 72 with two subportions 80,82, where the subportions 80,82 are longitudinally offset from one another, so that the seal may provide sealing for adjacent turbine blades having longitudinally offset inner platform surfaces.
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公开(公告)号：DE69732613D1
公开(公告)日：2005-04-07
申请号：DE69732613
申请日：1997-12-23
Applicant: UNITED TECHNOLOGIES CORP
Inventor： HOUSTON DAVID P , GONSOR MICHAEL , PELLAND NATALI A , AIREY DAVID
Abstract: An integral damper and seal 46 for a turbine blade in a gas turbine engine includes a damper portion 54 which contacts the platform and at least one sealing portion 56, angled radially inward from the damper portion, which makes contact with and seals against the platform.
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公开(公告)号：DE69728508D1
公开(公告)日：2004-05-13
申请号：DE69728508
申请日：1997-12-23
Applicant: UNITED TECHNOLOGIES CORP
Inventor： HOUSTON DAVID P , AIREY DAVID , PELLAND NATALIE A
Abstract: A seal for a turbine blade in a gas turbine engine has a sealing portion 72 with two subportions 80,82, where the subportions 80,82 are longitudinally offset from one another, so that the seal may provide sealing for adjacent turbine blades having longitudinally offset inner platform surfaces.
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公开(公告)号：DE69732613T2
公开(公告)日：2005-07-21
申请号：DE69732613
申请日：1997-12-23
Applicant: UNITED TECHNOLOGIES CORP
Inventor： HOUSTON DAVID P , GONSOR MICHAEL , PELLAND NATALI A , AIREY DAVID
Abstract: An integral damper and seal 46 for a turbine blade in a gas turbine engine includes a damper portion 54 which contacts the platform and at least one sealing portion 56, angled radially inward from the damper portion, which makes contact with and seals against the platform.
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