基于反方法的高负荷涡轮动叶激波控制
|
摘要
为控制高负荷涡轮叶栅中的激波、改善涡轮叶栅流动状况,针对E3涡轮第二级动叶中间叶高叶型,通过修改叶型吸力面压力分布进行了弱化激波S1流面反方法研究,并基于反设计叶型,对涡轮整级性能进行了三维数值计算分析。S1流面求解器选取MISES程序,应用Mixed模式反方法对叶型表面压力分布进行修改,并在反设计过程中临时"冻结"边界层来提高计算鲁棒性,加速收敛。结果表明,S1流面反设计叶型变薄,喉道位置前移,叶栅通道内激波强度明显削弱,叶型尾迹损失明显降低;涡轮整级环境下,反设计叶型使低背压工况下的等熵效率提高了约0.55%,涡轮出口激波强度显著降低,高效运行区拓宽,变工况性能较原始涡轮得到优化,验证了本文反方法的可行性。
In order to control the shock wave and improve the flow conditions of highly-loaded turbine cascades,an inverse method study on S1 stream surface was conducted to weaken the shock wave strength using the blade profile at the mid-span of the second stage rotor blade of E3 turbine. This was realized by adjusting the pressure distribution on the blade suction side. Meanwhile,three dimensional numerical simulation was carried out to analyze the performance of the turbine stage with the inverse-designed blade. The MISES code was chosen to solve the flow field on S1 stream surface,and the pressure distribution was modified through‘mixed-inverse'mode. A temporarily‘frozen'boundary layer scheme was employed to enhance the robustness and accelerate the convergence of the inverse design process. Results indicated that the blade thickness got thinner and the throat position moved forward compared to the original geometry. The shock wave strength was reduced significantly,as well as the wake loss. In addition,under the stage environment,compared to the original turbine,the isentropic efficiency at low back pressure condition increased approximately by 0.55%,and the shock wave intensity at the turbine exit was reduced greatly. The back pressure interval with high efficiency was extended and the off-design performance was improved. These results verified the feasibility of the developed inverse method.
In order to control the shock wave and improve the flow conditions of highly-loaded turbine cascades,an inverse method study on S1 stream surface was conducted to weaken the shock wave strength using the blade profile at the mid-span of the second stage rotor blade of E3 turbine. This was realized by adjusting the pressure distribution on the blade suction side. Meanwhile,three dimensional numerical simulation was carried out to analyze the performance of the turbine stage with the inverse-designed blade. The MISES code was chosen to solve the flow field on S1 stream surface,and the pressure distribution was modified through‘mixed-inverse'mode. A temporarily‘frozen'boundary layer scheme was employed to enhance the robustness and accelerate the convergence of the inverse design process. Results indicated that the blade thickness got thinner and the throat position moved forward compared to the original geometry. The shock wave strength was reduced significantly,as well as the wake loss. In addition,under the stage environment,compared to the original turbine,the isentropic efficiency at low back pressure condition increased approximately by 0.55%,and the shock wave intensity at the turbine exit was reduced greatly. The back pressure interval with high efficiency was extended and the off-design performance was improved. These results verified the feasibility of the developed inverse method.
引文
[1]Denton J D,Xu L.The Trailing Edge Loss of Transonic Turbine Blades[R].ASME 2009-GT-59679.
[2]Paul W G.NASA/GE Highly-Loaded Turbine Research Program[C].Ohio:AIAA Turbine Engine Testing Working Group(TETWo G)Meeting,2008.
[3]Vito L,Braembussche R A,Deconinck H.A Novel Two Dimensional Viscous Inverse Design Method Turbomachinery Blading[R].ASME 2002-GT-30617.
[4]余佳,马伟涛,季路成.弱化激波涡轮叶栅研究[J].工程热物理学报,2015,36(12):2585-2588.
[5]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.)
[6]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.)
[7]Timko L P.Energy Efficient Engine High Pressure Turbine Component Test Performance Report[R].NASA CR-168289.
[8]Behr T.Control of Rotor Tip Leakage and Secondary Flow by Casing Air Injection in Unshrouded Axial Turbine[D].Swiss:Swiss Federal Institute of Technology Zurich,2007.
[9]Drela M.Two-Dimensional Transonic Aerodynamic Design and Analysis Using the Euler Equations[D].Cambridge:Massachusetts Institute of Technology,1995.
[10]Drela M,Youngren H.A User's Guide to MISES 2.63[M].USA:MIT Aerospace Computational Design Laboratory,2008.
[11]赵学成,耿苗,杨金广,等.叶轮机械气动设计的反方法发展综述[J].战术导弹技术,2013,(4):64-69.
[12]Bent P.A Simple Inverse Cascade Design Method[R].ASME 2006-GT-68575.
[13]Dang T.Inverse Method for Turbomachine Blades Using Shock-Capturing Techniques[R].AIAA 95-2465.
[14]Drela M,Michael B G.Viscous-Inviscid Analysis of Transonic and Low Reynolds Number Airfoils[J].AIAA Journal,1987,25(10):1347-1355.
[15]Philip L A,P E,Harika S K.Validation of MISES 2-D Boundary Layer Code for High Pressure Turbine Aerodynamic Design[R].ASME 2007-GT-28123.
[2]Paul W G.NASA/GE Highly-Loaded Turbine Research Program[C].Ohio:AIAA Turbine Engine Testing Working Group(TETWo G)Meeting,2008.
[3]Vito L,Braembussche R A,Deconinck H.A Novel Two Dimensional Viscous Inverse Design Method Turbomachinery Blading[R].ASME 2002-GT-30617.
[4]余佳,马伟涛,季路成.弱化激波涡轮叶栅研究[J].工程热物理学报,2015,36(12):2585-2588.
[5]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.)
[6]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.)
[7]Timko L P.Energy Efficient Engine High Pressure Turbine Component Test Performance Report[R].NASA CR-168289.
[8]Behr T.Control of Rotor Tip Leakage and Secondary Flow by Casing Air Injection in Unshrouded Axial Turbine[D].Swiss:Swiss Federal Institute of Technology Zurich,2007.
[9]Drela M.Two-Dimensional Transonic Aerodynamic Design and Analysis Using the Euler Equations[D].Cambridge:Massachusetts Institute of Technology,1995.
[10]Drela M,Youngren H.A User's Guide to MISES 2.63[M].USA:MIT Aerospace Computational Design Laboratory,2008.
[11]赵学成,耿苗,杨金广,等.叶轮机械气动设计的反方法发展综述[J].战术导弹技术,2013,(4):64-69.
[12]Bent P.A Simple Inverse Cascade Design Method[R].ASME 2006-GT-68575.
[13]Dang T.Inverse Method for Turbomachine Blades Using Shock-Capturing Techniques[R].AIAA 95-2465.
[14]Drela M,Michael B G.Viscous-Inviscid Analysis of Transonic and Low Reynolds Number Airfoils[J].AIAA Journal,1987,25(10):1347-1355.
[15]Philip L A,P E,Harika S K.Validation of MISES 2-D Boundary Layer Code for High Pressure Turbine Aerodynamic Design[R].ASME 2007-GT-28123.