发明名称 |
Turbine nozzle support |
摘要 |
A gas turbine nozzle includes a plurality of nozzle segments having a pair of nozzle vanes supported by inner and outer shroud segments. Each inner shroud segment includes a circumferential retention slot and a radial retention slot in generally circumferential alignment and an interlocking tab and slot arrangement at the respective ends to provide engagement between adjacent flange segments. A 360 degree retention ring includes a plurality of circumferential retention tabs and radial retention tabs to engage respective ones of the plurality of flange segments to secure the nozzle segments in a circumferential ring about the outlet of a gas turbine combustor.
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申请公布号 |
US5343694(A) |
申请公布日期 |
1994.09.06 |
申请号 |
US19930059863 |
申请日期 |
1993.05.10 |
申请人 |
GENERAL ELECTRIC COMPANY |
发明人 |
TOBORG, STEVEN M.;SCHONEWALD, ROGER W. |
分类号 |
F01D9/02;F01D9/04;F01D11/00;F02C7/20;(IPC1-7):F02C7/20 |
主分类号 |
F01D9/02 |
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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