轴流压气机叶片准三维自动优化设计

推进技术 ›› 2014, Vol. 35 ›› Issue (4): 485-491.

轴流压气机叶片准三维自动优化设计

安志强^1,2,周正贵¹,张益豪¹

南京航空航天大学能源与动力学院,江苏南京 210016;南京航空航天大学能源与动力学院,江苏南京 210016;南京航空航天大学能源与动力学院,江苏南京 210016

发布日期:2021-08-15
作者简介:安志强(1989—),男,硕士生,研究领域为叶轮机气体动力学。 E-mail:azq0206@gmail.com

Axial Compressor Blade Automatic Optimization Design Based on a Quasi Three-Dimensional Approach

College of Energy and Power, Nanjing University of Aeronautics and Astronautics, Nanjing 210016, China;College of Energy and Power, Nanjing University of Aeronautics and Astronautics, Nanjing 210016, China;College of Energy and Power, Nanjing University of Aeronautics and Astronautics, Nanjing 210016, China

Published:2021-08-15

摘要/Abstract

摘要： 为提高轴流压气机叶片气动设计效果,将叶片准三维设计方法与叶型自动优化技术相结合,构建轴流压气机叶片准三维自动优化设计平台。在叶片三维数值计算结果中提取总压损失系数径向分布,反馈到S₂流面计算程序,替代原有的基于试验数据的损失模型,重新进行通流设计,提高S₂流面流场计算精度；S₁流面叶型设计采用并行遗传算法与叶轮机CFD方法相结合的叶型自动优化方法,以数值寻优代替叶型气动外形的人工调整,减小对设计经验的依赖。运用设计平台,对一设计流量6.3kg/s,设计压比2.07的轴流压气机第一级转子进行气动设计,得到径向三维叶片,设计点流量、总压比均接近设计目标,等熵效率接近90%,失速裕度达15.5%,结果令人满意。采用三维优化方法进一步进行叶片积叠线弯、掠设计,在失速点到设计点的稳定工作范围内效率均得到了1%的提升。 

关键词: 准三维设计;S₁流面叶型;优化设计;S₂损失模型;轴流压气机 

Abstract: For improving the effectiveness of axial compressor blade aerodynamic design, an axial compressor blade aerodynamic optimization design process based on the quasi three-dimensional approach is developed, which combines blade quasi three-dimensional approach with profile automatic optimization technique. Radial distribution of loss data from blade three dimensional calculation is fed back to S₂ flow surface calculation, for replacing the original loss model based on the test data. With through-flow redesign, more precise calculation on S_2flow surfaces is developed. Automatic optimization design method based on parallel genetic algorithm and turbine CFD is applied to blade profile design on S_1flow surface. Replacing artificial modulation of blade aerodynamic profiles with process of numerical optimization, the optimization method reduces the dependence of artificial experience. A radial stacking rotor blade of axial compressor first stages is designed using the design process above. With total pressure ratio objective of 2.07and mass flow-rate objective of 6.3kg/s, rotor designed shows isentropic efficiency about 90%, and reaches stall margin of 15.5%. The proximity of objectives from throughflow design is satisfactory,too. Sweeping-bending design is conducted with 3D numerical optimization, which shows that the efficiency increase by 1% from the stall point to the working point.

Key words: Quasi three-dimenslonal design；Blade profile on S_1flow surface；Optimization design；Loss model of S_2flow surface；Axial compressor

安志强,周正贵,张益豪. 轴流压气机叶片准三维自动优化设计[J]. 推进技术, 2014, 35(4): 485-491.

AN Zhi-qiang^1,2, ZHOU Zheng-gui¹, ZHANG Yi-hao¹. Axial Compressor Blade Automatic Optimization Design Based on a Quasi Three-Dimensional Approach[J]. Journal of Propulsion Technology, 2014, 35(4): 485-491.

参考文献

[1] 陈懋章.中国航空发动机高压压气机发展的几个问题[J].航空发动机, 2006,2(2):5-11.
[2] Gallimore S J.Axial Flow Compressor Design[J].Proceedings of the Institution of Mechanical Engineers, 1999,3(C):437-449.
[3] Neubert R J,Hobbs D E,Weingold H D.Application of Sweep to Improve the Efficiency of a Transonic Fan:Part Ⅰ- Design[R].AIAA 90-1915.
[4] Rabe D, Hoying D, Ko S.Application of Sweep to Improve the Efficiency of a Transonic Fan:Part Ⅱ- Performance and Laser Test Results[R].AIAA 91-2544.
[5] Rhie C M, Zacharias R M, Hobbs D E, et al.Advanced Transonic Fan Design Procedure Based on a Navier-Stokes Method[J].Trans.Journal of Turbomachinery, 1994,6(2):291-297.
[6] Brandvik T, Pullan G.An Accelerated 3D Navier– Stokes Solver for Flows in Turbomachines[R].ASME 2009-GT-60052.
[7] Rhie C M,Glexner A J, Spear D A, et al.Development and Application of a Multistage Navier-Stokes Flow Solver:Part Ⅰ- Multistage modeling using bodyforces and deterministic stresses[J].Trans.Journal of Turbomachinery, 1998,0(2):205-214.
[8] LeJambre C R, Zacharias R M, Biederman B P, et al.Development and Application of a Multistage Navier-Stokes Flow Solver:Part Ⅱ- Application to a High-Pressure Compressor Design[J].Trans.Journal of Turbomachinery, 1998,0(2):215-223.
[9] 周正贵.压气机/风扇叶片自动优化设计的研究现状和关键技术[J].航空学报, 2008,9(2):257-266.
[10] 周正贵, 邱名, 徐夏.压气机/风扇二维叶型自动优化设计[J].航空学报, 2011,2(11):1987-1997.
[11] Oyama A, Liou M S, Obayashi S.High-Fidelity Swept and Leaned Rotor Blade Design Optimization Using Evolutionary Algorithm[R].AIAA 2003-4091.
[12] Akira Oyama, Meng-Sing Liou, Shigeru Obayashi.Transonic Axial-Flow Blade Optimization:Evolutionary Algorithms/Three-Dimensional Navier- Stokes Solver[J].Journal of Propulsion and Power, 2004,0(4):612-619.
[13] 周正贵, 胡骏.H型叶栅通道流计算网格的改进[J].推进技术, 2003,4(5):436-439.(ZHOU Zheng-gui, HU Jun.Improvement of H-Type Grid for Compressor Cascade Flow Calculation[J].Journal of Propulsion Technology, 2003,4(5):436-439.)
[14] 李清鹏, 吴艳辉, 楚武利, 等.轴流压气机转子近失速工况全通道数值模拟[J].航空动力学报, 2011,6(10):2330-2338.
[15] 金东海, 桂幸民.某涡扇发动机多级高负荷风扇/压气机气动性能数值模拟[J].航空动力学报, 2011,6(5):1059-1065.
[16] 汪光文, 周正贵, 胡骏.基于优化算法的压气机叶片气动设计[J].航空动力学报, 2008,3(7):1218-1224.
[17] 周正贵.高压声速压气机叶片优化设计[J].推进技术, 2004,5(1):58-61.(ZHOU Zheng-gui.Optimization of High Subsonic Axial Compressor Blades[J].Journal of Propulsion Technology, 2004,5(1):58-61.)