弱化激波涡轮叶栅研究
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摘要
激波问题严重影响超/跨音涡轮气动性能、冷却特性和结构完整性,因而,弱化激波设计是高负荷涡轮研究的热点之一。针对这一问题,本文以两个典型超/跨音涡轮叶栅为例,以伴随方法寻优为手段,给定流量和出口气流角约束,在不同工况点下进行优化,并对比研究变工况特性、流动特征和造型参数,探索弱化激波涡轮叶栅设计技术及规律。
The shock waves have serious impacts on the aerodynamic performance,cooling characteristics and integrity of structure of supersonic/transonic turbines.Hence,the nozzle/blade design with weakened shock wave is one of the research hotspots of highly-loaded turbine.The paper focuses on this aspect.Two typical Russia supersonic/transonic turbine cascades under different design conditions are selected as examples.By using the adjoint method with the constraints of mass flow rate and outflow angle to find the best geometry parameters for the optimum aerodynamic performance at three different back pressures respectively.Their performance,flow characteristics and geometric parameters are compared to explore the design technology and rules of the turbine cascades with reduced shock wave.
The shock waves have serious impacts on the aerodynamic performance,cooling characteristics and integrity of structure of supersonic/transonic turbines.Hence,the nozzle/blade design with weakened shock wave is one of the research hotspots of highly-loaded turbine.The paper focuses on this aspect.Two typical Russia supersonic/transonic turbine cascades under different design conditions are selected as examples.By using the adjoint method with the constraints of mass flow rate and outflow angle to find the best geometry parameters for the optimum aerodynamic performance at three different back pressures respectively.Their performance,flow characteristics and geometric parameters are compared to explore the design technology and rules of the turbine cascades with reduced shock wave.
引文
[1]Sieverding C H,Stanislas M,Snoek J.The Base Pressure Problem in Transonic Cascades[R].ASME Paper.1983,No.83-GT-50
[2]Denton J D.The Trailing Edge Loss of Transonic Turbine Blades[J].Journal of turbomachinery,1990,112(2):277-285
[3]Laumert B.Investigation of Unsteady Aerodynamic Blade Excitation Mechanisms in a Transonic Turbine Stage Part I:Phenomenological Identification and Classification[J].Journal of Turbomachinery,2002,124(3):410-418
[4]Paul W,ASRC/RTT,NASA Glenn Research Center.NASA/GE Highly-Loaded Turbine Research Program[R].AIAA Turbine Engine Testing Working Group(TETWoG)Meeting,2008
[5]#12
[6]Senoo S.Development of Design Method for Supersonic Turbine Aerofoils near the Tip of Long Blades in Steam Turbine,Part I:Overall Configuration[R].ASME paper,GT2012-68218,2012
[7]Li W W,Tian Y,Yi W L,et al.Study on AdjointBased Optimization Method for Multi-Stage Turbomachinery[J].Journal of Thermal Science,2011,20(5):398-405
[8]李伟伟.面向叶轮机气动形状精细设计的伴随方法及其应用研究[J].中国科学院大学,2011,20(5):398-405Li W W.Turbomachinerv Aerodynamic Shape Optimization Approach Using Adjoint Method and Its Applications for Blade Detail Design[J].Chinese Academy of Sciences,2011,20(5):398-405
[9]马伟涛,季路成.超跨音涡轮激波演化及损失模型的研究[C]//中国工程热物理学会会议论文,2014,No.142157Ma W T,Ji L C.Study on the Evolution of Shock in Supersonic/Transonic Turbine and its Loss Model[C]//China Society of Engineering Thermophysics Conference,2014,No.142157
[2]Denton J D.The Trailing Edge Loss of Transonic Turbine Blades[J].Journal of turbomachinery,1990,112(2):277-285
[3]Laumert B.Investigation of Unsteady Aerodynamic Blade Excitation Mechanisms in a Transonic Turbine Stage Part I:Phenomenological Identification and Classification[J].Journal of Turbomachinery,2002,124(3):410-418
[4]Paul W,ASRC/RTT,NASA Glenn Research Center.NASA/GE Highly-Loaded Turbine Research Program[R].AIAA Turbine Engine Testing Working Group(TETWoG)Meeting,2008
[5]#12
[6]Senoo S.Development of Design Method for Supersonic Turbine Aerofoils near the Tip of Long Blades in Steam Turbine,Part I:Overall Configuration[R].ASME paper,GT2012-68218,2012
[7]Li W W,Tian Y,Yi W L,et al.Study on AdjointBased Optimization Method for Multi-Stage Turbomachinery[J].Journal of Thermal Science,2011,20(5):398-405
[8]李伟伟.面向叶轮机气动形状精细设计的伴随方法及其应用研究[J].中国科学院大学,2011,20(5):398-405Li W W.Turbomachinerv Aerodynamic Shape Optimization Approach Using Adjoint Method and Its Applications for Blade Detail Design[J].Chinese Academy of Sciences,2011,20(5):398-405
[9]马伟涛,季路成.超跨音涡轮激波演化及损失模型的研究[C]//中国工程热物理学会会议论文,2014,No.142157Ma W T,Ji L C.Study on the Evolution of Shock in Supersonic/Transonic Turbine and its Loss Model[C]//China Society of Engineering Thermophysics Conference,2014,No.142157