进口预旋对预压缩叶栅性能影响研究

推进技术 ›› 2017, Vol. 38 ›› Issue (12): 2725-2733.

进口预旋对预压缩叶栅性能影响研究

郝颜,邱名,江雄,王子维

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,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:郝颜，男，硕士生，研究实习员，研究领域为热机气动热力学。
基金资助:
国家自然科学基金(11572339)；中国空气动力研究与发展中心风雷青年创新基金(FLYIF20160008)。

Investgation of Inlet Pre-Swirl Influence on Performance in Precompression Cascade

Computational Aerodynamics Institute，China Aerodynamics Research and Development Center， Mianyang 621000，China,Computational Aerodynamics Institute，China Aerodynamics Research and Development Center， Mianyang 621000，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： 进口预旋对改善叶间匹配、提高压气机效率和抗畸变能力有着重要影响。基于课题组自主研发的RANS方程解算器，以ARL-SL19，SM-1.5预压缩叶栅为研究对象，采用数值模拟和理论分析相结合的方式探讨进口预旋对预压缩叶栅的性能影响。结果表明:叶栅进口引入正预旋，叶栅流动处于溢流状态，来流相对马赫数由1.50降为1.43，叶栅前缘脱体激波表现为一道槽道正激波和一道向远上游延伸的外伸激波，此时叶栅流动损失较大；叶栅进口引入负预旋，叶栅流动始终处于起动状态，随着进口负预旋的增大，来流相对马赫数增加，叶栅流动损失增大。无论进口处存在正预旋还是负预旋，叶栅流动始终遵循唯一进气角原理；当预压缩超声速叶栅处于溢流状态时，可通过减小正预旋或引入进口负预旋的方式使其起动。

关键词: 进口预旋；超声速叶栅；预压缩叶型；起动状态；溢流状态

Abstract: Inlet pre-swirl has important influence on improving the matching between the blades and improving the efficiency of compressor and the ability of resisting distortion. Based on in-house RANS solver ， it is discussed that the influence of inlet pre-swirl on precompression blade profile cascade by CFD solving and theoretical analysis. Cascade ARL-sl19 and Cascade SM-1.5 were the object of study. The results show that under the circumstance of inlet positive pre-swirl， supersonic cascade works in overflow state， inlet relative Mach number turns from 1.50 to 1.43， and the shock wave structure appears as a normal shock and a detached shock wave to the far upstream， it cause a high loss. Under the circumstance of inlet negative pre-swirl， supersonic cascade works in starting state always， with the inflow angle increasing， relative Mach number and the loss increase. However， wherever in positive pre-swirl or in negative pre-swirl， cascade works in unique incidence.When the precompression supersonic cascade is in the overflow state， it can be started by reducing the positive pre-swirl or introducing the negative pre-swirl.

Key words: Inlet pre-swirl；Supersonic cascade；Precompression blade profile；Starting state；Overflow state

郝颜,邱名,江雄,王子维. 进口预旋对预压缩叶栅性能影响研究[J]. 推进技术, 2017, 38(12): 2725-2733.

HAO Yan,QIU Ming,JIANG Xiong,WANG Zi-wei. Investgation of Inlet Pre-Swirl Influence on Performance in Precompression Cascade[J]. Journal of Propulsion Technology, 2017, 38(12): 2725-2733.

参考文献

[1] 季鹤鸣. 航空动力百年回顾(四)[J]. 航空发动机, 2003, 29(4): 55-58.
[2] Kantrowitz A, Donaldson C. Preliminary lnvestigation of Supersonic Diffusers[R]. NACA ACR-L5D20, 1945.
[3] Ullman G N, Hartmann Melvin J, Tysl E R. Experimental Investigation of a 16-inch Impulse-Type Supereonic Compressor Rotor [R]. NACA RM E51G19, 1951.
[4] Klapproth J F, Ullman G N, Tysl E R. Performance of an Impulse-Type Supersonic Compressor with Stators [R]. NACA RM52B22, 1952
[5] Lieblein S, Lewis G W, Sandercock D M. Experimental Investigation of an Axial-Flow Compressor Inlet Stage Operating at Transonic Relative Inlet Mach Number I– Overall Performance of Stage with Transonic Rotor and Subsonic Stators up to Rotor Relative Inlet Mach Number of 1.1[R]. NACA RM-E52A24, 1952.
[6] Keenan M J, Harley K G, Bogardus G A. Experimental Evaluation of Transonic Stators, Data and Performance Report, Multiple-Circular-Arc Stator[R]. NASA CR-54621/PWA-3260, 1968.
[7] Wennerstrom A J, Frost G R. Design of a 1500 ft/sec, Transonic, High-Through-Flow, Single-Stage Axial Flow Compressor with Low Hub/Tip Ratio[R]. AFAPL-TR-76-59/ADB-016386, 1976.
[8] Wennerstrom A J, Hearsey R M. The Design of an Axial Compressor Stage for a Total Pressure Ratio of 3 to 1 [R]. AD-727001, 1971.
[9] Wennerstrom A J, Frost G R, Derose R D. Test of an Axial Compressor Stage Design for a Total Pressure Ratio of 3 to 1[R]. AD-778844, 1974.
[10] Fleeter S, Holtman R L, Mcclure R B, et al. Experimental Investigation of a Supersonic Compressor Cascade[R]. ARL-75-0208, 1975.
[11] Tweedt D L, Schreiber H A, Starken H. Experimental Investigation of the Performance of a Supersonic Compressor Cascade[R]. NACA-TM-100879, 1988.
[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] 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.
[14] Levine P. The Two Dimensional Inflow Conditions for a Supersonic Compressor with Curved Blades[R]. WADC TR 55-387, 1956.
[15] Levine P. Two-Dimensional Inflow Conditions for a Supersonic Compressor with Curved Blades[J]. Journal of Applied Mechanics, 1957, 24(2):165-169.
[16] York R E, Woodard W S. Supersonic Compressor Cascades-an Analysis of the Entrance Region Flow Field Contain Detached [J]. Journal of Engineering for Power, 1976, 98(2): 247-257.
[17] 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.
[18] 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.)
[19] 肖翔. 对转冲压压气机冲压叶轮内部流动分析研究[D]. 北京:中国科学院研究生院, 2007.
[20] 肖敏, 刘波, 程荣辉. 轴流压气机超音叶片新设计技术研究[J]. 航空动力学报, 2002, 17(1): 83-86.
[21] Frost G R, Hearsey R M, Wennerstrom A J. A Computer Program for the Specification of Axial Compressor Airfoils[R]. AD0756879/ARL 72-0171, 1972.
[22] Knight M J, Bridgnorth. Variable Camber Stator Vane[P]. US: 5314301, 1994-05-24.
[23] 楚武利, 申凯. 可调进口导叶和叶片角向缝处理机匣相互作用的实验研究及机理分析[J]. 推进技术, 2014, 35(9). (CHU Wu-li, SHEN Kai. Experiment Investigation and Mechanism Analysis of Interaction of Variable Inlet Guide Vanes and Axial Skewed Slots Casing Treatment[J]. Journal of Propulsion Technology, 2014, 35(9).)
[24] 刘波, 张国臣, 巫骁雄. 可调弯度进口导叶在对转压气机中的应用[J]. 航空动力学报, 2015, 30(5):1184-1191.
[25] 赵斌, 刘宝杰. 进口预旋对高负荷跨声风扇性能的影响分析[J]. 航空动力学报, 2011, 26(3): 642-648.
[26] 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.
[27] 孙小磊, 扈延林, 杜建一, 等. 来流气流角变化对冲压叶栅性能的影响[J]. 工程热物理学报, 2010, 31:1484-1487.
[28] 牟斌, 肖中云, 周铸, 等. 直升机旋翼悬停流场的粘性数值模拟[J]. 空气动力学学报, 2009, 27(5): 582-585.　　　　　　　　　　　　　*　收稿日期:2016-08-23；修订日期:2016-10-10。基金项目:国家自然科学基金(11572339)；中国空气动力研究与发展中心风雷青年创新基金(FLYIF20160008)。作者简介:郝颜,男,硕士生,研究实习员,研究领域为热机气动热力学。E-mail: cardchaoyan@qq.com(编辑:史亚红)