对涡旋流影响压气机转子性能和稳定性的研究

推进技术 ›› 2016, Vol. 37 ›› Issue (4): 640-645.

对涡旋流影响压气机转子性能和稳定性的研究

屠宝锋^1,2,胡骏^1,2,张凯¹

南京航空航天大学能源与动力学院，江苏省航空动力系统重点实验室，江苏南京 210016; 先进航空发动机协同创新中心，北京 100191,南京航空航天大学能源与动力学院，江苏省航空动力系统重点实验室，江苏南京 210016; 先进航空发动机协同创新中心，北京 100191,南京航空航天大学能源与动力学院，江苏省航空动力系统重点实验室，江苏南京 210016

发布日期:2021-08-15
作者简介:屠宝锋，男，博士，讲师，研究领域为风扇/压气机气动稳定性。
基金资助:
南京航空航天大学青年科技创新基金(NS2014021)。

Effects of Twin Swirl on Performance and

Nanjing University of Aeronautics and Astronautics，Jiangsu Province Key Laboratory of Aerospace Power Systems，Nanjing 210016，China; Collaborative Innovation Center of Advanced Aero-Engine，Beijing 100191，China,Nanjing University of Aeronautics and Astronautics，Jiangsu Province Key Laboratory of Aerospace Power Systems，Nanjing 210016，China; Collaborative Innovation Center of Advanced Aero-Engine，Beijing 100191，China and Nanjing University of Aeronautics and Astronautics，Jiangsu Province Key Laboratory of Aerospace Power Systems，Nanjing 210016，China

Published:2021-08-15

摘要/Abstract

摘要： 为研究对涡旋流影响跨声速轴流压气机性能和稳定性的机理，设计了一种叶片式旋流发生器，并对旋流发生器和跨声速单转子进行了联合数值模拟研究。计算结果表明旋流发生器叶片数越少，对涡强度越低；对涡旋流导致压气机总压比、峰值效率、稳定工作范围和堵塞边界流量减小，失速边界流量增大，对涡强度等于60°时峰值效率和堵塞边界流量分别降低1.11%和2.12%，失速边界流量增加4.17%；对涡中的同向涡导致叶尖进口攻角增加，进口相对马赫数减小；反向涡使叶尖进口攻角降低，进口相对马赫数增大；对涡前缘的轴向速度偏低，造成叶尖进口攻角大幅增加，叶尖泄漏流堵塞严重；由于叶尖泄漏流在叶片前缘溢流导致失稳。

关键词: 压气机；跨声速；对涡；效率；稳定性

Abstract: In order to investigate the effects of twin swirl on performance and stability of transonic axial compressor，blade swirl generator was designed and simulated with a transonic single rotor. The results show that the intensity of twin swirl can be decreased by reducing blade number. Total pressure ratio，maximum efficiency，stable operating range and choke mass flow are decreased by twin swirl，and mass flow at stall boundary increases greatly. Maximum efficiency and choke mass flow decrease by 1.11% and 2.12% respectively，and mass flow at stall boundary increases by 4.17% as swirl intensity equals to 60°. Co-rotating swirl drives increase in attack angle and causes loss in relative Mach number at tip regions. On the contrary，counter rotating swirl decreases attack angle and increases relative Mach number at tip areas. Axial velocity at leading edge of twin swirl is lower than other regions，which makes attack angle increase and tip leakage block more serious. Leading edge spillage of tip leakage flow leads to instability.

Key words: Compressor；Transonic；Twin swirl；Efficiency；Stability

屠宝锋,胡骏,张凯. 对涡旋流影响压气机转子性能和稳定性的研究[J]. 推进技术, 2016, 37(4): 640-645.

TU Bao-feng^1,2,HU Jun^1,2,ZHANG Kai¹. Effects of Twin Swirl on Performance and[J]. Journal of Propulsion Technology, 2016, 37(4): 640-645.

参考文献

[1] Schmid N R, Leinhos D C, Fottner L. Steady Performance Measurements of a Turbofan Engine with Inlet Distortions Containing Co-and Counter-Rotating Swirl from an Intake Diffuser for Hypersonic Flight [R]. ASME 2000-GT-0011.
[2] Fottner L, Genssler H P, Meyer W. Development of Intake Swirl Generators for Turbo Jet Engine Testing [C]. Munich: Engine Response to Distorted Inflow Conditions, 1987.
[3] Cousins W T. History Philosophy Physics and Future Directions of Aircraft Propulsion System/Inlet Integration [R]. ASME 2004-GT-54210.
[4] Sheoran Y, Bouldin B. A Versatile Design of a Controlled Swirl Distortion Generator for Testing Gas Turbine Engines [R]. ASME GT2008-50657.
[5] Sheoran Y, Bouldin B, Krishnan P M. Advancements in the Design of an Adaptable Swirl Distortion Generator for Testing Gas Turbine Engines [R]. ASME GT2009-59146.
[6] Sheoran Y, Bouldin B, Krishnan P M. Compressor Performance and Operability in Swirl Distortion[J]. Journal of Turbomachinery, 2012, 134: 041008-1-13.
[7] Castaneda J, Mehdi A, Cugno D, et al. A Preliminary Numerical CFD Analysis of Transonic Compressor Rotors when Subjected to Inlet Swirl Distortion[R]. ASME GT2011-46560.
[8] Cousins W T, Miller R E, Dalton K E. Distortion Tolerance of the T800-LHT-800 Turboshaft Engine[C]. Phoenix: Proceedings of the American Helicopter Society 47th Annual Forum, 1991: 1147-1155.
[9] Lotter KW, Jorg J. The Effect of Intake Flow Disturbances on APU Compressor Blade High Cycle Fatigue in the Airbus A300 [C]. Seattle: Proceedings of the 13th Congress of ICAS/AIAA, 1982: 1072-1081.
[10] Sullivan J P, Murthy S N B, Davis R, et al. S-shaped Duct Flows [R]. Office of Naval Research Contract, 1982, N-78-C-0710.
[11] 张晓飞, 姜健, 符小刚. S弯进气道旋流畸变数值模拟及特性分析[J]. 燃气涡轮试验与研究, 2012, 25(3): 21-26.
[12] Rabe A C. Effectiveness of Serpentine Inlet Duct Flow Control Scheme at Design and Off-Design Simulated Flight Conditions[D]. Blacksburg: Virginia Polytechnic Institute and State University, 2003.
[13] XIE Wengzhong, GUO Rongwei. A Ventral Diverterless High Offset S-shaped Inlet at Transonic Speeds[J]. Chinese Journal of Aeronautics, 2008, 21:207-214.
[14] 彭成一, 林峰, 张堃元. 旋流模拟器研究[J]. 航空动力学报, 1986, 1(2): 22-26.
[15] 彭成一, 马家驹, 尹军飞. 新机试飞中的进气道旋流测量[J]. 推进技术, 1994, 15(4): 8-13. (PENG Cheng-yi, MA Jia-ju, YIN Jun-fei. Measurement of Inlet Swirl in Flight [J]. Journal of Propulsion Technology, 1994, 15(4):8-13.)
[16] 姜健, 屈霁云, 史建邦. 进气道旋流发生器的设计与数值模拟[J]. 燃气涡轮试验与研究, 2008, 21(1):43-46.
[17] 邓小宝, 姜健, 屈雯云, 等. 进气道旋流模拟及测量的风动试验研究[J]. 燃气涡轮试验与研究, 2009, 22(4): 51-56.
[18] 叶飞, 张堃元, 姜健, 等. 进气道旋流模拟及测量的实验研究[J]. 推进技术, 2009, 30(3): 297-301. (YE Fei, ZHANG Kun-yuan, JIANG Jian, et al. Experimental Investigation on Simulation and Measurement for Intake Swirl[J]. Journal of Propulsion Technology, 2009, 30(3): 297-301.)　　　　　　　　　　　　　*　收稿日期:2014-11-21；修订日期:2015-01-20。基金项目:南京航空航天大学青年科技创新基金(NS2014021)。作者简介:屠宝锋,男,博士,讲师,研究领域为风扇/压气机气动稳定性。E-mail: tubaofeng@126.com(编辑:朱立影)