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公开(公告)号：DE69928200D1
公开(公告)日：2005-12-15
申请号：DE69928200
申请日：1999-08-12
Applicant: UNITED TECHNOLOGIES CORP
Inventor： BREWER KEITH S , OLSEN DAVID R , CHAPLIN GARY F
Abstract: The present invention relates to a thermally compliant liner (50) for a gas turbine engine. The liner includes an outer wall (100), an inner wall (110) spaced radially inwardly from the outer wall leaving a duct (112) therebetween. A plurality of stiffeners (120) are disposed in the duct (114). The stiffeners (120) include a flexible medial portion (128) which accommodates differential rates of thermal growth between the outer and inner walls (100,110). The stiffeners (120) also include radially extending portions (124) which in conjunction with the medial portion (128), minimize buckling of the liner due to pressure differentials.
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公开(公告)号：CA1115640A
公开(公告)日：1982-01-05
申请号：CA336132
申请日：1979-09-21
Applicant: UNITED TECHNOLOGIES CORP
Inventor： CHAPLIN GARY F
Abstract: TURBINE SEAL AND VANE DAMPER A seal member for a gas turbine engine is disclosed. Various construction details which increase sealing effectiveness and which enable the damping of vibrations in a plurality of vanes are developed. The seal member is disposed between the engine case and a plurality of stator vanes. The seal member has a flexible center section which is compressed in the installed position.
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公开(公告)号：DE3917937A1
公开(公告)日：1989-12-07
申请号：DE3917937
申请日：1989-06-01
Applicant: UNITED TECHNOLOGIES CORP
Inventor： CHAPLIN GARY F , PANNONE JOHN L , WEISSE MICHAEL A
Abstract: A stator vane assembly 30 for a rotary machine is disclosed. The stator vane assembly includes an array of stator vanes 44 and an inner air seal 46. Various construction details which damp vibrational stresses in the vanes are developed. In one embodiment, the stator vanes slidably engage the inner air seal. The inner air seal is urged radially into sliding contact with the vanes at the inner ends 52 of the vanes by a resilient device such as a radial spring member 70. In one detailed embodiment, the stator vane has at least two airfoils 55b,c which are circumferentially spaced at their inner ends leaving a circumferential gap therebetween.
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Patent Agency Ranking
公开(公告)号：CA1163928A
公开(公告)日：1984-03-20
申请号：CA386143
申请日：1981-09-17
Applicant: UNITED TECHNOLOGIES CORP
Inventor： CHAPLIN GARY F
Abstract: A flanged joint (20) having a seal ring (38) is disclosed. The flanged joint includes two cylindrical case structures (24,26). The seal ring is disposed in a groove (40) formed between two outwardly convergent sidewalls (32,34). The seal ring has a wedge-shaped cross section (48) and may operate with a higher coefficient of thermal expansion than the adjacent case structure or at a higher temperature than the adjacent case structure.
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公开(公告)号：DE3917937C2
公开(公告)日：1998-12-03
申请号：DE3917937
申请日：1989-06-01
Applicant: UNITED TECHNOLOGIES CORP
Inventor： CHAPLIN GARY F , PANNONE JOHN L , WEISSE MICHAEL A
Abstract: A stator vane assembly 30 for a rotary machine is disclosed. The stator vane assembly includes an array of stator vanes 44 and an inner air seal 46. Various construction details which damp vibrational stresses in the vanes are developed. In one embodiment, the stator vanes slidably engage the inner air seal. The inner air seal is urged radially into sliding contact with the vanes at the inner ends 52 of the vanes by a resilient device such as a radial spring member 70. In one detailed embodiment, the stator vane has at least two airfoils 55b,c which are circumferentially spaced at their inner ends leaving a circumferential gap therebetween.
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公开(公告)号：CA1117023A
公开(公告)日：1982-01-26
申请号：CA336686
申请日：1979-09-28
Applicant: UNITED TECHNOLOGIES CORP
Inventor： CHAPLIN GARY F , DETOLLA FRANCIS L , GRIFFIN JAMES G
Abstract: OUTER AIR SEAL SUPPORT STRUCTURE A support structure for an outer air seal of a gas turbine engine is disclosed. Various construction details which improve the sealing effectiveness of the outer air seal are developed. The outer air seal is held in close proximity to the rotor blades by the circumferentially adjacent support segments.
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公开(公告)号：DE69928200T2
公开(公告)日：2006-07-13
申请号：DE69928200
申请日：1999-08-12
Applicant: UNITED TECHNOLOGIES CORP HARTF
Inventor： BREWER KEITH S , OLSEN DAVID R , CHAPLIN GARY F
Abstract: The present invention relates to a thermally compliant liner (50) for a gas turbine engine. The liner includes an outer wall (100), an inner wall (110) spaced radially inwardly from the outer wall leaving a duct (112) therebetween. A plurality of stiffeners (120) are disposed in the duct (114). The stiffeners (120) include a flexible medial portion (128) which accommodates differential rates of thermal growth between the outer and inner walls (100,110). The stiffeners (120) also include radially extending portions (124) which in conjunction with the medial portion (128), minimize buckling of the liner due to pressure differentials.
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公开(公告)号：FR2632357A1
公开(公告)日：1989-12-08
申请号：FR8907339
申请日：1989-06-02
Applicant: UNITED TECHNOLOGIES CORP
Inventor： CHAPLIN GARY F , PANNONE JOHN L , WEISSE MICHAEL A
Abstract: A stator vane assembly 30 for a rotary machine is disclosed. The stator vane assembly includes an array of stator vanes 44 and an inner air seal 46. Various construction details which damp vibrational stresses in the vanes are developed. In one embodiment, the stator vanes slidably engage the inner air seal. The inner air seal is urged radially into sliding contact with the vanes at the inner ends 52 of the vanes by a resilient device such as a radial spring member 70. In one detailed embodiment, the stator vane has at least two airfoils 55b,c which are circumferentially spaced at their inner ends leaving a circumferential gap therebetween.
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