发明名称 |
REDUCTION OF EQUALLY SPACED TURBINE NOZZLE VANE EXCITATION |
摘要 |
A reduction in excitation amplitudes affecting turbine blade durability in a turbine nozzle assembly having a plurality of vanes and turbine blades, includes: identifying a turbine blade design of the turbine nozzle assembly; performing a modal model analysis of at least one of the turbine blades in the turbine blade design; reducing aerodynamic impact by ensuring that each of the turbine blades is free of aero-excitation from an upstream flow at the vanes in an operating speed range; identifying blade natural frequencies with respect to the nozzle vanes; and modifying a trailing edge of at least one of the vanes to reduce the excitation amplitudes. |
申请公布号 |
US2014112760(A1) |
申请公布日期 |
2014.04.24 |
申请号 |
US201213658184 |
申请日期 |
2012.10.23 |
申请人 |
UNITED TECHNOLOGIES CORPORATION;UNITED TECHNOLOGIES CORPORATION |
发明人 |
DUONG LOC QUANG;HU XIAOLAN;YANG GAO;FALCONER STEVEN R.;GORDON RALPH E.;GARCIA JESUS A.;SAPIRO DAN G.;KAUL ULRIKE;JOHNSON GREGORY G.;FISHLER BENJAMIN E. |
分类号 |
F01D5/16;B23P6/00;F01D5/00;G01M13/00 |
主分类号 |
F01D5/16 |
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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