发明名称 |
Damper configured turbine blade |
摘要 |
A turbine rotor blade includes a hollow airfoil joined to a platform and dovetail. A main flow channel extends longitudinally in span through the blade and is bound chordally by opposite partitions transversely bridging opposite sidewalls of the airfoil. A damper rib and transversely opposite damper pad are arranged together in a plurality of pairs spaced longitudinally apart in the airfoil and chordally positioned intermediate to the partitions to provide unobstructed forward and aft portions of the flow channel for channeling a coolant therethrough. The damper ribs and pads are configured to receive a wire damper through the channel to locally dampen vibration while minimizing obstruction of the coolant flow therethrough.
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申请公布号 |
US7736124(B2) |
申请公布日期 |
2010.06.15 |
申请号 |
US20070733252 |
申请日期 |
2007.04.10 |
申请人 |
GENERAL ELECTRIC COMPANY |
发明人 |
BAUER RANDALL CHARLES;GARAY GREGORY TERRENCE;WEAVER MATTHEW MARK;BAILEY JAMES ROBERT;BUSBEY BRUCE CLARK |
分类号 |
F01D5/26 |
主分类号 |
F01D5/26 |
代理机构 |
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代理人 |
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主权项 |
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地址 |
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