径向来流畸变对燃气轮机压气机叶片颤振特性的影响研究  

Influence of Radial Inflow Distortion on Flutter Characteristics of Gas Turbine Compressor Blades

作　　者：刘玉鹏 李云珠 罗宇轩 谢永慧[1] 张荻 LIU Yupeng;LI Yunzhu;LUO Yuxuan;XIE Yonghui;ZHANG Di(State Key Laboratory for Strength and Vibration of Mechanical Structures,School of Energy and Power Engineering,Xi'an Jiaotong University,Xi'an 710049,China;Beijing Aerospace Propulsion Institute,Beijing 100070,China;MOE Key Laboratory of Thermo-fluid Science and Engineering,School of Energy and Power Engineering,Xi'an Jiaotong University,Xi'an 710049,China)

机构地区：[1]西安交通大学能源与动力工程学院,复杂服役环境重大装备结构强度与寿命全国重点实验室,西安710049 [2]北京航天动力研究所,北京100070 [3]西安交通大学能源与动力工程学院,热流科学与工程教育部重点实验室,西安710049

出　　处：《动力工程学报》2024年第9期1361-1369,共9页Journal of Chinese Society of Power Engineering

基　　金：国家科技重大专项资助项目(J2019-IV-0022-0090)。

摘　　要：为分析来流畸变对燃气轮机压气机颤振特性的影响,建立了径向畸变的入口来流总压模型,基于影响系数法研究了不同相位角和不同畸变强度的径向来流总压畸变对压气机流场特征及气弹稳定性的影响。结果表明:相位角为90°和180°的径向来流总压畸变会使危险工况下的气动阻尼最小值有所增大,气弹稳定性提升;相位角为180°的径向来流总压畸变可以在所有叶间相位角下提高压气机的气弹稳定性;相位角为0°和270°的径向来流总压畸变均会提高压气机发生颤振的风险,需要尽量避免。In order to analyze the influence of inflow distortion on flutter characteristics of gas turbine compressors,an inlet total pressure model with radial distortion was established.Based on the influence coefficient method,the effects of radial inflow total pressure distortion with different phases and distortion intensities on the flow field characteristics and aeroelastic stability of compressors were studied.Results show that the radial inflow total pressure distortion with phase angles of 90°and 180°will increase the minimum value of aerodynamic damping under dangerous conditions,and the aeroelastic stability is improved.The radial inflow total pressure distortion with phase angle of 180°can improve the aeroelastic stability of the compressor at all inter blade phase angles.However,the radial inflow total pressure distortion with phase angles of 0°and 270°will increase the risk of compressor flutter,which should be avoided.

关 键 词：燃气轮机 压气机 径向来流畸变 颤振 影响系数法 气动阻尼 

分 类 号：V231[航空宇航科学与技术—航空宇航推进理论与工程]