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公开(公告)号：EP2912278A1
公开(公告)日：2015-09-02
申请号：EP13849387.9
申请日：2013-10-21
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.
CPC分类号： F01D5/16 , F01D5/005 , F01D5/141 , F01D9/04 , F05D2240/122 , F05D2260/81 , G01M13/00 , Y10T29/49318
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.
摘要翻译： 在具有多个叶片和涡轮叶片的涡轮喷嘴组件中影响涡轮叶片耐久性的激励振幅的减小包括：识别涡轮喷嘴组件的涡轮叶片设计; 对涡轮叶片设计中的至少一个涡轮叶片进行模态模型分析; 通过确保每个涡轮机叶片在运转速度范围内不受来自叶片上游流动的气动激励而减小空气动力学冲击; 识别关于喷嘴叶片的叶片固有频率; 以及修改至少一个叶片的后缘以减小激励振幅。
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公开(公告)号：EP1825117A2
公开(公告)日：2007-08-29
申请号：EP04822101.4
申请日：2004-12-01
CPC分类号： F02K3/06 , F02C3/113 , F02C7/36 , F04D25/04 , F05D2260/40311
摘要： A gas turbine engine (10) provides a differential gear system (58) coupling the turbine (20) to the bypass fan (14) and the compressor (16). In this manner, the power/speed split between the bypass fan and the compressor can be optimized under all conditions. In the example shown, the turbine drives a sun gear (74), which drives a planet carrier (78) and a ring gear (80) in a differential manner. One of the planet carrier and the ring gear is coupled to the bypass fan, while the other is coupled to the compressor.
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