Numerical Simulation of the Rotating Stall Feature on a Single Stage Transonic Compressor
-
摘要: 为了研究多排跨声轴流压气机旋转失速先兆的表现形式与失速演化规律，基于自主研发的CFD软件ASPAC，通过发展动态重叠网格技术，流量出口边界条件以及节流阀边界条件，对单级跨声速压气机NASA Stage 35由近失速状态到完全失速状态的过程进行了模拟.结果表明，发展的数值模拟方法能准确地模拟多排压气机的旋转失速发展过程；均匀进气条件下，随着NASA Stage 35向失速状态逼近，某些动叶压力面前缘出现了叶顶间隙流溢流现象，促使压气机进入旋转失速状态；在失速先兆阶段，周向非均匀流动开始出现并沿压气机周向传播；当完全失速时，失速团充分发展并连续地沿周向旋转，结构几乎不随时间变化.Abstract: To study the characteristics of stall inception and stall development in multi-row transonic axial compressor, taking NASA Stage 35 as an example, the development from near stall to fully developed stall was simulated. The simulation was conducted based on the in-house code ASPAC. The dynamic overlapped grid technique, mass flow boundary at the outlet, throttle valve boundary condition were used. The simulation result indicates that: the developed simulation technique can predict the development process of rotating stall correctly. Under the condition of uniform inlet flow, as the flow approaches to stall condition, the blade tip leakage occurs on the leading edge of pressure surface for some rotors, which leads to the rotating stall of the compressor. Under the condition of stall inception, circumferential non-uniform flow occurs and propagates circumferentially. When the rotating stall is fully developed, the adverse flow occurs on the pressure surface of stator and is mainly adjacent to the stall cells in the rotor, meanwhile the flow structure in the stall region nearly does not change with time.
-
图 6 失速发展过程的入口流量变化(细节图)
Figure 6. Variation of inlet mass flow during stall development(details)
图 7 失速发展过程的流量-出口静压特性图
Figure 7. Variation of mass flow-outlet static pressure during stall development
图 8 失速发展过程的流量-总压比特性图
Figure 8. Variation of mass flow-total pressure ratio during stall development
图 9 不同叶片通道机匣处的静压变化
Figure 9. Variation of static pressure on the shroud in different blade passages
图 10 95%叶高的相对Mach数分布及流线示意
Figure 10. Distributions of relative Mach number and streamline at 95% span
图 11 转动到第4.5圈时的轴向Mach数等值面(Ma=-0.1, 静压着色)
Figure 11. Iso-surface of axial Mach number at 4.5th revolution(Ma=-0.1, colored by static pressure)
图 12 转动到第12.65圈时的轴向Mach数等值面(Ma=-0.1, 静压着色)
Figure 12. Iso-surface of axial Mach number at 12.65th revolution(Ma=-0.1, colored by static pressure)
图 13 转动到第26.7圈时的轴向Mach数等值面(Ma=-0.1, 静压着色)
Figure 13. Iso-surface of axial Mach number at 26.7th revolution(Ma=-0.1, colored by static pressure)
图 14 转动到第26.7圈时95%叶高的熵分布
Figure 14. Distribution of entropy at 95% span at 26.7th revolution
表 1 NASA Stage 35的设计参数
Table 1. Design parameters of NASA Stage 35
rotor wheel speed/RPM rotor tip speed/(m/s) hub-tip ratio rotor aspect ratio stator aspect ratio number of rotor blades number of stator blades -17 188.7 454.456 0.7 1.19 1.26 36 46 
下载: 导出CSV
表 2 数值模拟结果与实验结果误差
Table 2. Differences between simulation and experiment
physical mass flow/choke flow TURBO ASPAC 1 15.0% 18.1% 0.995 05 2.6% 7.9% 0.980 65 4.3% 7.4% 0.956 78 4.4% 5.6% 0.924 69 2.7% 3.6% 0.902 27 2.2% 2.6%
下载: 导出CSV
-
[1] Day I, Morris S, et al. Spike-type compressor stall inception, detection, and control[J]. Annual Review of Fluid Mechanics, 2010, 42: 275-300. doi: 10.1146/annurev-fluid-121108-145603 [2] 钟勇健, 腾金芳, 徐玺, 等. 跨声速轴流压气机失速边界预测方法[J]. 航空动力学报, 2014, 29(8): 1838-1845. https://www.cnki.com.cn/Article/CJFDTOTAL-HKDI201408012.htmZhong Y J, Teng J F, Xu X, et al. Prediction method of stall margin in axial-flow transonic compressor[J]. Journal of Aerospace Power, 2014, 29(8): 1838-1845(in Chinese). https://www.cnki.com.cn/Article/CJFDTOTAL-HKDI201408012.htm [3] 屠宝锋. 风扇/压气机动态失速过程和多尺度非定常气动稳定性研究[D]. 南京: 南京航空航天大学, 2009.Tu B F. Dynamic stall inception and multi-scale unsteady aerodynamic stability investigation of fan/compressor[D]. Nanjing: Nanjing University of Aeronautics and Astronautics, 2009(in Chinese). [4] 郭晋, 胡骏, 屠宝锋. 多级轴流压气机彻体力模型——理论方法及简化应用[J]. 航空动力学报, 2018, 33(8): 1954-1963. https://www.cnki.com.cn/Article/CJFDTOTAL-HKDI201808019.htmGuo J, Hu J, Tu B F. Body force model for multistage axial compressor-theoretical method and simplified application[J]. Journal of Aerospace Power, 2018, 33(8): 1954-1963(in Chinese). https://www.cnki.com.cn/Article/CJFDTOTAL-HKDI201808019.htm [5] 禹世奇. 压气机近失速状态流场非定常特性研究[D]. 南京: 南京航空航天大学, 2012.Yu S Q. Unsteady analysis of axial flow compressor at near stall conditions[D]. Nanjing: Nanjing University of Aeronautics and Astronautics, 2012(in Chinese). [6] 鞠鹏飞, 宁方飞. 跨声压气机近失速流动特征的数值模拟研究[J]. 推进技术, 2016, 37(6): 1055-1064. https://www.cnki.com.cn/Article/CJFDTOTAL-TJJS201606008.htmJu P F, Ning F F. Numerical study of near-stall flow feature on transonic compressor[J]. Journal of Propulsion Technology, 2016, 37(6): 1055-1064(in Chinese). https://www.cnki.com.cn/Article/CJFDTOTAL-TJJS201606008.htm [7] 贺象, 银越千, 黄生勤, 等. 低速轴流压气机旋转失速演化机制研究[J]. 航空发动机, 2016, 42(5): 81-86. https://www.cnki.com.cn/Article/CJFDTOTAL-HKFJ201605015.htmHe X, Yin Y Q, Huang S Q, et al. Investigation on the rotating stall in a low-speed axial compressor[J]. Aeroengine, 2016, 42(5): 81-86(in Chinese). https://www.cnki.com.cn/Article/CJFDTOTAL-HKFJ201605015.htm [8] 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, 26(10): 2330-2338. https://www.cnki.com.cn/Article/CJFDTOTAL-HKDI201110023.htmLi Q P, Wu Y H, Chu W L, et al. Full-annulus simulations on axial compressor rotor at near stall condition[J]. Journal of Aerospace Power, 2011, 26(10): 2330-2338(in Chinese). https://www.cnki.com.cn/Article/CJFDTOTAL-HKDI201110023.htm [9] 吴艳辉, 王晓, 稂仿玉, 等. 单级轴流压气机失速起始的数值模拟[J]. 航空动力学报, 2014, 29(1): 125-132. https://www.cnki.com.cn/Article/CJFDTOTAL-HKDI201401017.htmWu Y H, Wang X, Lang F Y, et al. Numerical simulation of stall inception in single-stage axial-flow compressor[J]. Journal of Aerospace Power, 2014, 29(1): 125-132(in Chinese). https://www.cnki.com.cn/Article/CJFDTOTAL-HKDI201401017.htm [10] Menon S, Schmidt D P. Conservative interpolation on unstructured polyhedral meshes: an extension of the supermesh approach to cell-centered finite-volume variables[J]. Computer Methods in Applied Mechanics and Engineering, 2011, 200(41/44): 2797-2804. http://www.sciencedirect.com/science/article/pii/S0045782511001666 [11] 徐春光, 董海波, 刘君. 基于单元相交的混合网格精确守恒插值方法[J]. 爆炸与冲击, 2016, 36(3): 305-312. https://www.cnki.com.cn/Article/CJFDTOTAL-BZCJ201603003.htmXu C G, Dong H B, Liu J. An accurate conservative interpolation method for the mixed grid based on the intersection of grid cells[J]. Explosion and Shock Waves, 2016, 36(3): 305-312(in Chinese). https://www.cnki.com.cn/Article/CJFDTOTAL-BZCJ201603003.htm [12] 崔鹏程, 唐静, 李彬, 等. 基于超网格的重叠网格守恒插值方法[J]. 航空学报, 2018, 39(3): 121569. https://www.cnki.com.cn/Article/CJFDTOTAL-HKXB201803003.htmCui P C, Tang J, Li B, et al. A conservative interpolation method for overset mesh via super mesh[J]. Acta Aeronautica et Astronautica Sinica, 2018, 39(3): 121569(in Chinese). https://www.cnki.com.cn/Article/CJFDTOTAL-HKXB201803003.htm [13] Reid L, Moore R D. Performance of single-stage axial-flow transonic compressor with rotor and stator aspect ratios of 1.19 and 1.26, respectively, and with design pressure ratio of 1.82[R]. NASA TP-1338, 1978. [14] 王子维, 范召林, 江雄, 等. 用于多级压气机非定常流动的谐波平衡方法研究[J]. 推进技术, 2017, 38(11): 2512-2521. https://www.cnki.com.cn/Article/CJFDTOTAL-TJJS201711014.htmWang Z W, Fan Z L, Jiang X, et al. Investigation on harmonic balance method for simulation of unsteady flow in the multi-stage compressor[J]. Journal of Propulsion Technology, 2017, 38(11): 2512-2521(in Chinese). https://www.cnki.com.cn/Article/CJFDTOTAL-TJJS201711014.htm [15] Herrick G P, Hathaway M D, Chen J P. Unsteady full annulus simulations of a transonic axial compressor stage[R]. AIAA 2009-1059, 2009. -
点击查看大图
计量
- 文章访问数: 70
- HTML全文浏览量: 13
- PDF下载量: 9
- 被引次数: 0
邮件订阅
RSS