可控扩散叶型全3维黏性反问题设计方法
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摘要
为了快速有效地完成叶片造型,提高压气机气动性能,以全3维黏性反问题设计方法为基础,研究了全新的可控扩散叶型设计方法。基于黎曼不变量守恒建立了吸力和压力面型线与其对应静压分布之间的关系,通过给定叶片表面静压分布,求解吸力和压力面型线坐标几何参数。为了验证方法的有效性,以NASA Stage 35静子叶片为设计算例,通过全3维数值模拟得到其流场参数分布,进而采用可控扩散叶型的设计思路,对NASA Stage 35静子叶片表面的静压分布进行修改,以修改后的静压分布作为目标进行反问题设计计算,最终设计出满足设计要求的叶片几何型线。改型后的静子叶片通道内流场很好地实现了可控扩散叶型的流动结构,叶片总体气动性能得到提升,验证了可控扩散叶型全3维反问题设计方法的准确性和有效性。
In order to complete the airfoil modeling quickly and effectively and improve the aerodynamic performance of compressor,a new design method of controlled diffusion airfoil was studied based on the full three-dimensional viscous inverse design method. The relationship between suction and pressure profile and its corresponding static pressure distributions was established based on Riemann invariant conservation. The geometric parameters of the vane profile coordinates of suction and pressure were solved by given the static pressure distributions on the vane surface. In order to verify the validity of the method,the flow field parameter distributions of NASA Stage35 stator vane was obtained by the full three-dimensional numerical simulation. And then,the static pressure distributions on the surface of NASA Stage 35 stator vane was modified by using the design idea of controlled diffusion airfoil. With the modified static pressure distributions as the target,the inverse design calculation was carried out. Finally,the geometric profile of the vane was designed to meet the design requirements. The flow structure of the controlled diffusion airfoil is realized commendably by flow field in the channel of the modified stator vane. The overall aerodynamic performance of the blade is improved. The accuracy and validity of the inverse design method are verified for the fully three-dimensional controlled diffusion airfoil.
In order to complete the airfoil modeling quickly and effectively and improve the aerodynamic performance of compressor,a new design method of controlled diffusion airfoil was studied based on the full three-dimensional viscous inverse design method. The relationship between suction and pressure profile and its corresponding static pressure distributions was established based on Riemann invariant conservation. The geometric parameters of the vane profile coordinates of suction and pressure were solved by given the static pressure distributions on the vane surface. In order to verify the validity of the method,the flow field parameter distributions of NASA Stage35 stator vane was obtained by the full three-dimensional numerical simulation. And then,the static pressure distributions on the surface of NASA Stage 35 stator vane was modified by using the design idea of controlled diffusion airfoil. With the modified static pressure distributions as the target,the inverse design calculation was carried out. Finally,the geometric profile of the vane was designed to meet the design requirements. The flow structure of the controlled diffusion airfoil is realized commendably by flow field in the channel of the modified stator vane. The overall aerodynamic performance of the blade is improved. The accuracy and validity of the inverse design method are verified for the fully three-dimensional controlled diffusion airfoil.
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]Dang T.Inverse methods for turbomachine blades using shock-capturing techniques[C]//Asme International Gas Turbine&Aeroengine Congress&Exposition.1994.
[3]Medd A J,Dang T Q,Larosiliere L M.3D Inverse design loading strategy for transonic axial compressor blading[R].ASME2003-GT-38501.
[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]Hield P.Semi-inverse design applied to an eight stage transonic axial flow compressor[R].ASME 2008-GT-50430.
[6]van Rooij,Meed A.Reformulation of a three-dimensional inverse design method for application in a high-fidelity CFD environment[R].ASME 2012-GT-69891.
[7]王正明,贾希诚.正反问题数值解法相结合3维叶片的优化设计[J].工程热物理学报,2000,21(5):567-569.WANG Zhengming,Jia Xicheng.Optimum design of three-dimensional blades by combination of numerical methods for solving direct and inverse problems[J].Journal of Engineering Thermophysics,2000,21(5):567-569.(in Chinese)
[8]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.
[9]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.ZHOU Xinhai,ZHU Fangyuan.Finite volume method to solve the inverse problem for transonic flows in cascades[J].Journal of Engineering Thermophysics,1985,6(4):331-335.(in Chinese)
[10]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 Dazhong,JIANG Zikang.Numerical solution on viscous inverse problem for transonic compressor cascades[J].Journal of Propulsion Technology,1999,20(4):57-60.(in Chinese)
[11]Ning F F.MAP:A CFD package for turbomachinery flow simulation and aerodynamic design optimization[R].ASME2014-GT-26515.
[12]Sanz J M.Automated design of controlled-diffusion blades[J].Journal of Turbomachinery,1988,110(4):540-544.
[13]Sanz J M.Lewis inverse design code(LINDES)[R].NASA-TP-76,1987.
[14]Gelder T F,Schmidt J F,Suder K L,et al.Design and performance of controlled-diffusion stator compared with original double-circular-arc stator[R].NASA-TM-100141,1989.
[15]Sanger N L,Shreeve R P.Comparison of calculated and experimental cascade performance for controlled-diffusion compressor stator blading[J].Journal of Turbomachinery,1986,108:43.
[16]刘波,周新海,严汝群.轴流压气机可控扩散叶型的数值优化设计[J].航空动力学报,1991,6(1):9-12,89.LIU Bo,ZHOU Xinhai,YAN Ruqun.Numerical optimization program for designing controlled diffusion compressor blading[J].Journal of Aerospace Power,1991,6(1):9-12,89.(inChinese)
[17]钟兢军,王会社,王仲奇.多级压气机中可控扩散叶型研究的进展与展望(第一部分):可控扩散叶型的设计与发展[J].航空动力学报,2001,16(3):205-211.ZHONG Jingjun,WANG Huishe,WANG Zhongqi.Development and prospect of controlled diffusion airfoils for multistage compressor-PartⅠ:design and development of controlled diffusion airfoils[J].Journal of Aerospace Power,2001,16(3):205-211.(in Chinese)
[18]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.LIU Zhaowei,WU Hu,TANG Xiaoyi.Optimization of transonic axial compressor using multi-row inverse method[J].Journal of Northwestern Polytechnical University,2016,34(1):118-124.(in Chinese)
[19]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(7):1491-1498.LIU Zhaowei,WU Hu.Axial compressor inverse design method based on the conservation of Riemann invariant[J].Journal of Propulsion Technology,2017(7):1491-1498.(in Chinese)
[2]Dang T.Inverse methods for turbomachine blades using shock-capturing techniques[C]//Asme International Gas Turbine&Aeroengine Congress&Exposition.1994.
[3]Medd A J,Dang T Q,Larosiliere L M.3D Inverse design loading strategy for transonic axial compressor blading[R].ASME2003-GT-38501.
[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]Hield P.Semi-inverse design applied to an eight stage transonic axial flow compressor[R].ASME 2008-GT-50430.
[6]van Rooij,Meed A.Reformulation of a three-dimensional inverse design method for application in a high-fidelity CFD environment[R].ASME 2012-GT-69891.
[7]王正明,贾希诚.正反问题数值解法相结合3维叶片的优化设计[J].工程热物理学报,2000,21(5):567-569.WANG Zhengming,Jia Xicheng.Optimum design of three-dimensional blades by combination of numerical methods for solving direct and inverse problems[J].Journal of Engineering Thermophysics,2000,21(5):567-569.(in Chinese)
[8]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.
[9]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.ZHOU Xinhai,ZHU Fangyuan.Finite volume method to solve the inverse problem for transonic flows in cascades[J].Journal of Engineering Thermophysics,1985,6(4):331-335.(in Chinese)
[10]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 Dazhong,JIANG Zikang.Numerical solution on viscous inverse problem for transonic compressor cascades[J].Journal of Propulsion Technology,1999,20(4):57-60.(in Chinese)
[11]Ning F F.MAP:A CFD package for turbomachinery flow simulation and aerodynamic design optimization[R].ASME2014-GT-26515.
[12]Sanz J M.Automated design of controlled-diffusion blades[J].Journal of Turbomachinery,1988,110(4):540-544.
[13]Sanz J M.Lewis inverse design code(LINDES)[R].NASA-TP-76,1987.
[14]Gelder T F,Schmidt J F,Suder K L,et al.Design and performance of controlled-diffusion stator compared with original double-circular-arc stator[R].NASA-TM-100141,1989.
[15]Sanger N L,Shreeve R P.Comparison of calculated and experimental cascade performance for controlled-diffusion compressor stator blading[J].Journal of Turbomachinery,1986,108:43.
[16]刘波,周新海,严汝群.轴流压气机可控扩散叶型的数值优化设计[J].航空动力学报,1991,6(1):9-12,89.LIU Bo,ZHOU Xinhai,YAN Ruqun.Numerical optimization program for designing controlled diffusion compressor blading[J].Journal of Aerospace Power,1991,6(1):9-12,89.(inChinese)
[17]钟兢军,王会社,王仲奇.多级压气机中可控扩散叶型研究的进展与展望(第一部分):可控扩散叶型的设计与发展[J].航空动力学报,2001,16(3):205-211.ZHONG Jingjun,WANG Huishe,WANG Zhongqi.Development and prospect of controlled diffusion airfoils for multistage compressor-PartⅠ:design and development of controlled diffusion airfoils[J].Journal of Aerospace Power,2001,16(3):205-211.(in Chinese)
[18]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.LIU Zhaowei,WU Hu,TANG Xiaoyi.Optimization of transonic axial compressor using multi-row inverse method[J].Journal of Northwestern Polytechnical University,2016,34(1):118-124.(in Chinese)
[19]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(7):1491-1498.LIU Zhaowei,WU Hu.Axial compressor inverse design method based on the conservation of Riemann invariant[J].Journal of Propulsion Technology,2017(7):1491-1498.(in Chinese)