高马赫数超声压气机转子叶型优化设计

推进技术 ›› 2016, Vol. 37 ›› Issue (10): 1826-1838.

高马赫数超声压气机转子叶型优化设计

邱名¹,马率¹,周正贵²,张传海¹,王子维¹

中国空气动力研究与发展中心计算空气动力研究所，四川绵阳 621000,中国空气动力研究与发展中心计算空气动力研究所，四川绵阳 621000,南京航空航天大学能源与动力学院，江苏南京 210016,中国空气动力研究与发展中心计算空气动力研究所，四川绵阳 621000,中国空气动力研究与发展中心计算空气动力研究所，四川绵阳 621000

发布日期:2021-08-15
作者简介:邱名，男，博士，研究实习员，研究领域为叶轮机气体动力学。E-mail: qiu_ming_abc@163.com 通讯作者:周正贵，男，博士，教授，博士生导师，研究领域为叶轮机气体动力学。
基金资助:
国家自然科学基金(11572339)。

High Mach Number Supersonic Compressor Rotor Blade

Computational Aerodynamics Institute，China Aerodynamics Research and Development Center， Mianyang 621000，China,Computational Aerodynamics Institute，China Aerodynamics Research and Development Center， Mianyang 621000，China,College of Energy and Power Engineering，Nanjing University of Aeronautics and Astronautics，Nanjing 210016，China,Computational Aerodynamics Institute，China Aerodynamics Research and Development Center， Mianyang 621000，China and Computational Aerodynamics Institute，China Aerodynamics Research and Development Center， Mianyang 621000，China

Published:2021-08-15

摘要/Abstract

摘要： 为进一步提高压气机叶尖轮缘速度和增压比，将唯一进气角原理和数值最优化技术用于叶型设计，获得两个高马赫数、高压比、低损失的“S”形超声压气机叶型。首先根据压气机流动机理，提出超声压气机叶栅的性能指标；然后通过吸力面叠加厚度的方式生成初始叶型，保证叶栅的来流马赫数和唯一进气角；最后采用基于修改量的叶型参数化方法，以给定总压比为约束条件，以总压损失系数最小为目标对初始叶型优化。设计结果表明:在设计点，叶栅1和叶栅2的总压损失系数分别为0.119和0.158；在高来流马赫数条件下，超声叶栅需采用大稠度设计才能实现多道斜激波加一道正激波增压；在叶型吸力面前端构造一个斜坡也可增加叶栅通道内的斜激波数量；平直的吸力面后段有利于削弱激波对附面层干扰，将平直吸力面后段与钝尾缘(或翘尾缘)相结合可有效抑制附面层分离，减小尾迹区。

关键词: 超声叶栅；平面叶栅；预压缩叶型；优化设计；唯一进气角

Abstract: To achieve higher blade tip speed and single stage pressure-ratio in compressor，the unique incidence principle and numerical optimization technology are used to design blade airfoil. And two “S” shape supersonic cascades with high inlet Mach number，high pressure-ratio and high efficiency were obtained. Firstly，the design target is proposed，according to compressor flow mechanism. Then，the initial airfoils，whose inlet Mach number and flow angle equal with design value，were generated through overlaying thickness to suction side curve. At last，genetic algorithm and the blade airfoil parameterization method based on modifying quantity were used to optimize the initial airfoil. The optimization object is the minimal total pressure loss coefficient. The restriction condition is that total pressure-ratio equals to design value. The results show that，the total pressure loss coefficient is 0.119 at designing point for cascade 1，and 0.158 for cascade 2. Supersonic cascade may achieve multi-shock pressurization only if solidity was high，in the case of high inlet Mach number. The number of oblique shock increases，if a slope existed in the front of suction side. The straight suction rear segment can inhibit the shock wave/boundary layer interaction，and can even weaken separation when it is combined with blunt trailing edge(or the warped trailing edge).

Key words: Supersonic cascade；Plane cascade；Pre-compression blade airfoil；Optimization design；Unique incidence

邱名,马率,周正贵,张传海,王子维. 高马赫数超声压气机转子叶型优化设计[J]. 推进技术, 2016, 37(10): 1826-1838.

QIU Ming¹,MA Shuai¹,ZHOU Zheng-gui²,ZHANG Chuan-hai¹,WANG Zi-wei¹. High Mach Number Supersonic Compressor Rotor Blade[J]. Journal of Propulsion Technology, 2016, 37(10): 1826-1838.

参考文献

[1] Kantrowitz A. The Supersonic Axial-Flow Compressor [R]. NACA-Report 974, NACA-ACR-L6D02, 1946.
[2] Erwin J R, Wright L C, Kantrowitz A. Investigation of an Experimental Supersonic Axial-Flow Compressor [R]. NACA-RM-L6J01b, 1947.
[3] Ritter W K, Johnson I A. Performance of 24-inch Supersonic Axial-Flow Compressor in Air I: Performance of Compressor Rotor at Design Tip Speed of 1600 Feet Per Second[R]. NACA-RM-E7L10, 1948
[4] Ullman G N, Hartmann M J, Tysl E R. Experimental Investigation of a 16-inch Impulse-Type Supersonic Compressor Rotor[R]. NACA-RM-E51G19, 1951.
[5] Klapproth J F, Ullman G N, Tysl E R. Performance of an Impulse-Type Supersonic Compressor with Stators [R]. NACA-RM-52B22, 1952.
[6] Levine P. The Two Dimensional Inflow Conditions for a Supersonic Compressor with Curved Blades[R]. WADC TR 55-387, 1956.
[7] Levine P. Two-Dimensional Inflow Conditions for a Supersonic Compressor with Curved Blades[J]. Journal of Applied Mechanics, 1957, 24(2): 165-169.
[8] Lichtfuss H J, Starken H. Supersonic Cascade Flow [J]. Progress in Aerospace Science, 1974, 15: 37-149.
[9] Starken H, Zhong Yongxing, Schreiber H A. Mass Flow Limitations of Supersonic Blade Rows Due to Leading Edge Blockage[R]. ASME 84-GT-233.
[10] 程家纲. 超跨声速扩压叶栅未启动堵塞工况计算[J].力学学报, 1979, (4): 315-322.
[11] 邱名, 周正贵, 刘龙龙, 等. 超声压气机叶型设计方法[J]. 航空学报, 2013, 34: 1-12.
[12] Graham R C, Klapproth J F, Barina F J. Investigation of Off-Design Performance of Shock-in-Rotor Type Supersonic Blading[R]. NACA-RM-E51C22, 1951.
[13] Schreiber H A. Experimental Investigations on Shock Losses of Transonic and Supersonic Compressor Cascades[R]. AGARD-CP-401/AD-A183996, 1987.
[14] Schreiber H A, Starken H. An Investigation of a Strong Shock-Wave Turbulent Boundary Layer Interaction in a Supersonic Compressor Cascade[J]. Journal of Turbomachinery, 1992, 114(3): 494-503.
[15] Küsters B, Schreiber H A. Compressor Cascade Flow with Strong Shock-Wave/Boundary-Layer Interaction [J]. AIAA Journal, 1998, 36(11): 2072-2078.
[16] 刘龙龙, 周正贵, 邱名. 超音叶栅激波结构研究及叶型优化设计[J]. 推进技术, 2013, 34(8): 1050-1055. (LIU Long-long, ZHOU Zheng-gui, QIU Ming. Studies of Shock Structure in Supersonic Cascade and Profile Optimization Design[J]. Journal of Propulsion Technology, 2013, 34(8): 1050-1055.)
[17] 孙波, 张堃元. Busemann进气道起动问题初步研究[J]. 推进技术, 2006, 27(2): 128-131. (SUN Bo, ZHANG Kun-yuan. Preliminary Investigation on Busemann Inlet Starting Characteristics[J]. Journal of Propulsion Technology, 2006, 27(2): 128-131.)
[18] 袁化成, 梁德旺. 高超声速进气道再起动特性分析[J]. 推进技术, 2006, 27(5): 390-398. (YUAN Hua-cheng, LIANG De-wang. Analysis of Characteristics of Restart Performance for a Hypersonic Inlet[J]. Journal of Propulsion Technology, 2006, 27(5): 390-398.)
[19] 邱名. 高级压比轴流压气机转子通道内激波组织研究[D]. 南京:南京航空航天大学, 2014.
[20] Fleeter s, Holtman R L, Mcclure R B, et al. Experimental Investigation of a Supersonic Compressor Cascade[R]. ARL-75-0208, 1975.
[21] Tweedt D L, Schreiber H A, Starken H. Experimental Investigation of the Performance of a Supersonic Compressor Cascade[R]. NACA-TM-100879, 1988.
[22] Leonard O. Design Method for Subsonic and Transonic Cascade with Prescribed Mach Number Distribution[J]. Journal of Turbomachinery, 1992, 114(3): 553-559.
[23] 曹志鹏, 兰发祥, 夏天, 等. 高负荷风扇转子叶片反问题设计[J]. 燃气涡轮试验与研究, 2012, 25(2):1-6.
[24] 杜磊, 宁方飞. 低速叶型气动反问题设计方法[J]. 航空学报, 2011, 32(7): 1180-1187.
[25] Sanger N L. The Use of Optimization Techniques to Design Controlled Diffusion Compressor Balding[J]. ASME Journal Eng.Power, 1983, 105(2): 256-265.
[26] Oyama A, Liou M S. High-Fidelity Swept and Leaned Rotor Blade Design Optimization using Evolutionary Algorithm[R]. AIAA 2003-4091.
[27] Benini E, Toffolo A. For Axial Flow Compressors Using Evolutionary Computation[J]. Journal of Propulsion and Power, 2002, 18(3): 544-554.
[28] Benini E. Three-Dimensional Multi-Objective Design Optimization of a Transonic Compressor Rotor [J]. Journal of Propulsion and Power, 2004, 20(3): 559-565.
[29] 周正贵, 邱名, 徐夏, 等. 压气机/风扇二维叶型自动优化设计[J], 航空学报, 2011, 32(11): 1987-1997.
[30] 邱名, 周正贵. 优化方法在轴流压气机转子叶片气动设计中的应用[J]. 南京航空航天大学学报, 2013, 45(1): 75-81.
[31] Wennerstrom AJ, Frost GR. Design of a 1500ft/sec, Transonic, High-Through-Flow, Single-Stage Axial Flow Compressor with Low Hub/Tip Ratio[R]. AFAPL-TR-76-59/ADB-016386.
[32] Strazisar A J, Wood J R, Hathaway M D, et al. Laser Anemometer Measurements in a Transonic Axial-Flow Fan Rotor [R]. NASA TP-2879, 1989.
[33] Lonnie Reid, Moore R D. Design and Overall Performance of Four Highly Loaded, High-Speed Inlet Stages for an Advanced, High-Pressure-Ratio Core Compressor[R]. NASA TP-1337, 1978.
[34] 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.
[35] Rabe D, Hoying D. Application of Sweep to Improve the Efficiency of a Transonic Fan: PartⅡ-Performance and Laser Test Result [R]. AIAA 91-2544.
[36] 陈懋章. 风扇/压气机技术发展和对今后工作的建议[J]. 航空动力学报, 2002, 17(1): 1-15.　　　　　　　　　　　　　*　收稿日期:2015-05-31；修订日期:2015-08-10。基金项目:国家自然科学基金(11572339)。作者简介:邱名 ,男,博士,研究实习员,研究领域为叶轮机气体动力学。E-mail: qiu_ming_abc@163.com通讯作者:周正贵 ,男,博士,教授,博士生导师,研究领域为叶轮机气体动力学。E-mail: zzgon@nuaa.edu.cn(编辑:张荣莉)