多级轴流压气机反问题级间气动匹配设计方法
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摘要
为提高多级轴流压气机气动性能,采用轴流压气机叶片全三维粘性反问题求解方法,对多级轴流压气机反问题级间气动匹配设计方法进行了研究。以压气机级出口旋流角为设计目标,叶片表面载荷分布为设计对象,通过动量矩守恒方程,建立起叶片出口旋流角与叶片表面载荷分布的关系,从而实现计算过程中载荷的自动调整,修正气流在叶片出口旋流角分布。为了让压气机每一级都工作在设计给定的进口条件下,对上游级静子叶片进行反问题改型设计,使得其出口旋流角分布满足设计给定值。为了验证方法的有效性,采用四级高压压气机作为算例,对其初始设计进行反问题匹配改型设计。通过计算,修正了三个级间位置的旋流角分布,改善了下游级进口工作条件。气流在改型后压气机内部流动更加符合设计意图,级与级之间流动匹配更好。与原型相比,总压比和绝热效率分别提高了2.8%和1.3%,验证了方法的有效性。
In order to improve the performance of multistage axial compressor,a new aerodynamic matching design method for multistage axial compressor is developed based on the three-dimensional viscous inverse method. The swirl of the compressor stage exit is chosen as the design objective and the design variable is the blade pressure loading distribution on the blade surface. The relationship between blade exit swirl and blade surface pressure loading distribution is established based on the angular momentum conservation. The blade pressure loading is automatically adjusted during the computation process to modify the blade exit swirl. In order to ensure that each stage of compressor is working under the specified inlet operation condition,the stator of upstream stage is redesigned using the inverse design method. The exit swirl of upstream stage is adjusted to satisfy the design value. In order to validate the effectiveness of present method,an aerodynamic matching design using inverse method is carried out on a 4 stage high-pressure axial compressor original design configuration,which is used as the test case. The exit swirl on three axial positions between stages is modified to improve the inlet operation condition of downstream stage. The flow in the compressor blade passage satisfies the design intent and matches better between stages. Compared with original design,the total pressure ratio and adiabatic efficiency of compressor is improved by 2.8% and 1.3%,which demonstrated the effectiveness and accuracy of present method.
In order to improve the performance of multistage axial compressor,a new aerodynamic matching design method for multistage axial compressor is developed based on the three-dimensional viscous inverse method. The swirl of the compressor stage exit is chosen as the design objective and the design variable is the blade pressure loading distribution on the blade surface. The relationship between blade exit swirl and blade surface pressure loading distribution is established based on the angular momentum conservation. The blade pressure loading is automatically adjusted during the computation process to modify the blade exit swirl. In order to ensure that each stage of compressor is working under the specified inlet operation condition,the stator of upstream stage is redesigned using the inverse design method. The exit swirl of upstream stage is adjusted to satisfy the design value. In order to validate the effectiveness of present method,an aerodynamic matching design using inverse method is carried out on a 4 stage high-pressure axial compressor original design configuration,which is used as the test case. The exit swirl on three axial positions between stages is modified to improve the inlet operation condition of downstream stage. The flow in the compressor blade passage satisfies the design intent and matches better between stages. Compared with original design,the total pressure ratio and adiabatic efficiency of compressor is improved by 2.8% and 1.3%,which demonstrated the effectiveness and accuracy of present method.
引文
[1]DANG T Q.A Fully Three-Dimensional Inverse Method for Turbomachinery Blading in Transonic Flows[J].ASME Journal of Turbomachinery,1993,115(2):354-361.
[2]QIU X W,DANG T Q.3D Inverse Method for Turbomachine Blading with Splitter Blades[R].ASME 2000-GT-0526.
[3]Mileshin P C,Van Rooij,Dang T Q,et al.Enhanced Blade Row Matching Capabilities via 3D Multistage Inverse Design and Pressure Loading Manager[R].ASME GT 2008-50539.
[4]Ahmadi M,Ghaly W.Aerodynamic Inverse Design of Turbomachinery Cascades Using a Finite Volume Method on Unstructured Meshes[J].Inverse Problems in Science and Engineering,1998,6(4):281-298.
[5]Van Rooij,Meed A.Reformulation of a Three-Dimensional Inverse Design Method for Application in a HighFidelity CFD Environment[R].ASME GT 2012-69891.
[6]周新海,朱方元.求解叶栅跨音速流动反问题的有限体积方法[J].工程热物理学报,1985,6(4):331-335.
[7]杨策,老大中,蒋滋康.求解跨声速压气机叶栅粘性流动反问题的数值解[J].推进技术,1999,20(4):57-60.(YANG Ce,LAO Da-zhong,JIANG Zi-kang.Numerical Solution on Viscous Inverse Problem for Transonic Compressor Cascades[J].Journal of Propulsion Technology,1999,20(4):57-60.)
[8]王正明,贾希诚.正反问题数值解法相结合三维叶片的优化设计[J].工程热物理学报,2000,21(5):567-569.
[9]WANG Z M,CAI R X.A Three-Dimensional Inverse Method Using Navier-Stokes Equation for Turbomachinery Blading[J].Inverse Problems in Engineering,2000,8:529-551.
[10]朱阳历.叶轮机械叶片全三维反问题优化设计方法研究[D].北京:中国科学院研究生院,2012.
[11]杨金广.叶轮机械全三维粘性反方法设计技术研究[D].西安:西北工业大学,2013.
[12]Ning F F.MAP:A CFD Package for Turbomachinery Flow Simulation and Aerodynamic Design Optimization[R].ASME GT 2014-26515.
[13]Jameson A,Schmidt W,Turkel E.Numerical Solution of the Euler Equations by Finite Volume Methods UsingRunge Kutta Time Stepping Schemes[J].AIAA Journal,1981,1259(11):2004-4325.
[14]杨金广,吴虎.改进的Baldwin-Lomax湍流模型及其在叶轮机械中的应用[J].工程热物理学报,2014,35(3):451-455.
[15]刘昭威,吴虎.基于黎曼不变量守恒的轴流压气机反问题设计方法[J].推进技术,2017,38(9).(LIU Zhao-wei,WU Hu.Axial Compressor Inverse Design Method Based on the Conservation of Riemann Invariant[J].Journal of Propulsion Technology,2017,38(9).)
[16]刘昭威,吴虎,唐晓毅.改进的反问题边界条件在叶轮机械中的应用[J].工程热物理学报,2015,36(10):1-5.
[17]刘昭威,吴虎,唐晓毅.跨声速轴流压气机转子反问题优化方法[J].推进技术,2015,36(9):1310-1316.(LIU Zhao-wei,WU Hu,TANG Xiao-yi.Optimization of Transonic Axial Compressor Rotor Using Improved Inverse Method[J].Journal of Propulsion Technology,2015,36(9):1310-1316.)
[18]刘昭威,吴虎,唐晓毅.基于反问题设计方法的叶栅激波损失控制[J].推进技术,2014,35(6):766-773.(LIU Zhao-wei,WU Hu,TANG Xiao-yi.Shock Wave Loss Control of Cascades Using Inverse Method[J].Journal of Propulsion Technology,2014,35(6):766-773.)
[19]刘昭威,吴虎,唐晓毅.跨声速轴流压气机多叶排反问题优化方法[J].西北工业大学学报,2016,34(1):118-124.
[20]杨金广,刘振德,邵伏永,等.基于渗透边界条件的三维粘性叶轮机械气动设计反方法应用研究[J].推进技术,2015,36(5):688-695.(YANG Jin-guang,LIU Zhen-de,SHAO Fu-yong,et al.A Study of Applications of 3D Viscous Inverse Method Based on Transpiration Boundary Conditions for Turbomachinery Aerodynamic Design[J].Journal of Propulsion Technology,2015,36(5):688-695.)
[2]QIU X W,DANG T Q.3D Inverse Method for Turbomachine Blading with Splitter Blades[R].ASME 2000-GT-0526.
[3]Mileshin P C,Van Rooij,Dang T Q,et al.Enhanced Blade Row Matching Capabilities via 3D Multistage Inverse Design and Pressure Loading Manager[R].ASME GT 2008-50539.
[4]Ahmadi M,Ghaly W.Aerodynamic Inverse Design of Turbomachinery Cascades Using a Finite Volume Method on Unstructured Meshes[J].Inverse Problems in Science and Engineering,1998,6(4):281-298.
[5]Van Rooij,Meed A.Reformulation of a Three-Dimensional Inverse Design Method for Application in a HighFidelity CFD Environment[R].ASME GT 2012-69891.
[6]周新海,朱方元.求解叶栅跨音速流动反问题的有限体积方法[J].工程热物理学报,1985,6(4):331-335.
[7]杨策,老大中,蒋滋康.求解跨声速压气机叶栅粘性流动反问题的数值解[J].推进技术,1999,20(4):57-60.(YANG Ce,LAO Da-zhong,JIANG Zi-kang.Numerical Solution on Viscous Inverse Problem for Transonic Compressor Cascades[J].Journal of Propulsion Technology,1999,20(4):57-60.)
[8]王正明,贾希诚.正反问题数值解法相结合三维叶片的优化设计[J].工程热物理学报,2000,21(5):567-569.
[9]WANG Z M,CAI R X.A Three-Dimensional Inverse Method Using Navier-Stokes Equation for Turbomachinery Blading[J].Inverse Problems in Engineering,2000,8:529-551.
[10]朱阳历.叶轮机械叶片全三维反问题优化设计方法研究[D].北京:中国科学院研究生院,2012.
[11]杨金广.叶轮机械全三维粘性反方法设计技术研究[D].西安:西北工业大学,2013.
[12]Ning F F.MAP:A CFD Package for Turbomachinery Flow Simulation and Aerodynamic Design Optimization[R].ASME GT 2014-26515.
[13]Jameson A,Schmidt W,Turkel E.Numerical Solution of the Euler Equations by Finite Volume Methods UsingRunge Kutta Time Stepping Schemes[J].AIAA Journal,1981,1259(11):2004-4325.
[14]杨金广,吴虎.改进的Baldwin-Lomax湍流模型及其在叶轮机械中的应用[J].工程热物理学报,2014,35(3):451-455.
[15]刘昭威,吴虎.基于黎曼不变量守恒的轴流压气机反问题设计方法[J].推进技术,2017,38(9).(LIU Zhao-wei,WU Hu.Axial Compressor Inverse Design Method Based on the Conservation of Riemann Invariant[J].Journal of Propulsion Technology,2017,38(9).)
[16]刘昭威,吴虎,唐晓毅.改进的反问题边界条件在叶轮机械中的应用[J].工程热物理学报,2015,36(10):1-5.
[17]刘昭威,吴虎,唐晓毅.跨声速轴流压气机转子反问题优化方法[J].推进技术,2015,36(9):1310-1316.(LIU Zhao-wei,WU Hu,TANG Xiao-yi.Optimization of Transonic Axial Compressor Rotor Using Improved Inverse Method[J].Journal of Propulsion Technology,2015,36(9):1310-1316.)
[18]刘昭威,吴虎,唐晓毅.基于反问题设计方法的叶栅激波损失控制[J].推进技术,2014,35(6):766-773.(LIU Zhao-wei,WU Hu,TANG Xiao-yi.Shock Wave Loss Control of Cascades Using Inverse Method[J].Journal of Propulsion Technology,2014,35(6):766-773.)
[19]刘昭威,吴虎,唐晓毅.跨声速轴流压气机多叶排反问题优化方法[J].西北工业大学学报,2016,34(1):118-124.
[20]杨金广,刘振德,邵伏永,等.基于渗透边界条件的三维粘性叶轮机械气动设计反方法应用研究[J].推进技术,2015,36(5):688-695.(YANG Jin-guang,LIU Zhen-de,SHAO Fu-yong,et al.A Study of Applications of 3D Viscous Inverse Method Based on Transpiration Boundary Conditions for Turbomachinery Aerodynamic Design[J].Journal of Propulsion Technology,2015,36(5):688-695.)