重型燃气轮机压气机叶片气动弹性稳定性初期预判  

Preliminary Aeroelastic Stability Design for Heavy Duty Gas Turbine Compressor Blade

作　　者：张正秋[1] 蒋洪德[1] 

机构地区：[1]清华大学热能工程系,北京100084

出　　处：《燃气涡轮试验与研究》2013年第2期18-23,共6页Gas Turbine Experiment and Research

摘　　要：通过求解雷诺平均N-S方程并采用影响系数法,对某重型燃气轮机压气机叶片三个基本正交模态的叶片绕流问题进行了研究;同时结合有限元分析和稳定性参数分析,对压气机叶片气动弹性稳定性进行了初期预判。结果表明:以振型为判断标准的稳定性参数图,可作为压气机设计中气动弹性稳定性的预判工具;本文所述颤振稳定性初期预判方法,可为重型燃气轮机压气机气动弹性稳定性初期设计提供技术支持。Numerical simulation of 3-D unsteady viscous flow around oscillating compressor blades was carried out in the influence coefficient domain by resolving Reynolds average N-S equation. Combined with the FEM analysis and stability parameter analysis （Tie-Dye method）, the aeroelastic stability analysis for compressor was done. The main results indicate that the stability parameter estimated on the basis of oscilla- tion mode could be a pre-evaluation tool for aeroelastic stability design of compressor. And the method pro- vides technical support for the preliminary aeroelastic stability design of heavy duty gas turbine compressor.

关 键 词：气动弹性 重型燃气轮机 压气机 稳定性参数 振荡叶栅 影响系数法 

分 类 号：V231.9[航空宇航科学与技术—航空宇航推进理论与工程]