Influence of inlet guide vane angle on flow instability of hub instability compressor
-
摘要:
以一台航空高速压气机为研究对象,通过加装进口导叶调整压气机进气预旋角,采集失稳过程中的动态压力信号,观察不同导叶角度、流动失稳演化过程。结果表明:在负导叶角情况下,压气机由转子叶尖突尖波引起失稳;在零导叶角及较小的正导叶角情况下,由静子叶根区域的局部喘振诱发失稳;在较大的正导叶角情况下,静子叶根在节流过程中首先出现局部失稳,进一步节流导致叶尖旋转失速团出现,压气机完全失稳。分析认为,导叶角的增加通过降低反力度,调整了转静间的负荷分配,从而引起了失速初始扰动发生上述“转子突尖波-静子局部喘振-静子局部失稳”的转变。
Abstract:A high-speed aero-compressor with different instability precursors was taken as the research object. The inlet guide vane was installed to manipulate the compressor inlet pre-swirl angle. Several dynamic pressure transducers were arranged to measure the whole instability evolutions. The instability precursor and the evolutions were observed under different inlet guide vane angles. The results showed that at negative inlet guide vane angle, the compressor instability was caused by the spike in the rotor tip region. At zero inlet guide vane angle and small positive inlet guide vane angle, the instability was induced by the partial surge in the stator hub region. Under the condition of large positive inlet guide vane angle, local instability occurred at stator hub first in the process of throttling, and led to complete compressor instability with further throttling in form of rotating stall cells at the tip. The analysis showed that the increase of the inlet guide vane angle adjusted the load distribution between the rotor and the stator by reducing the degree of reaction, thus causing the instability precursors to change from “spike at rotor- partial surge at stator-local instability at stator” as described above.
-
表 1 跨声速轴流压气机主要设计参数
Table 1. Main design parameters of the transonic axial compressor
设计参数 数值 转速/(r/min) 22000 压比 1.6 绝热效率 0.84 质量流量/(kg/s) 13.5 转子叶片数 17 转子叶尖马赫数 1.21 轮毂比 0.565 展弦比 0.956 第1排静子叶片数 29 第2排静子叶片数 29 -
[1] EMMONS H W,PEARSON C E,GRANT H P. Compressor surge and stall propagation[J]. Transactions of the ASME,1955,77(4): 455-469. [2] DAY I J. Stall inception in axial flow compressors[J]. Journal of Turbomachinery,1993,115(1): 1-9. doi: 10.1115/1.2929209 [3] DAY I J,FREEMAN C. The unstable behavior of low and high-speed compressors[J]. Journal of Turbomachinery,1994,116(2): 194-201. doi: 10.1115/1.2928353 [4] MAILACH R,SAUER H,VOGELER K.The periodical interaction of the tip clearance flow in the blade rows of axial compressors[R].ASME Paper 2001-GT-0299,2001. [5] RICK D,AHMET S,PHILIP K,et al. Prediction of surge in a turbocharger compression system vs.measurements[J]. International Journal of Engines,2011,4(2): 2181-2192. [6] CAMP T R,DAY I J. A study of spike and modal stall phenomena in a low-speed axial compressor[J]. Journal of Turbomachinery,1998,120(3): 393-401. doi: 10.1115/1.2841730 [7] HAH C,SCHULZE R,WAGNER S,et al.Numerical and experimental study for short wavelength stall inception in a low-speed axial compressor[R].Florence,Italy:the 14th International Symposium on Air Breathing Engines,1999. [8] PULLAN G,YOUNG A M,DAY I J,et al. Origins and structure of spike-type rotating stall[J]. Journal of Turbomachinery,2015,137(5): 051007.1-051007.11. [9] WEICHERT S,DAY I J. Detailed measurements of spike formation in an axial compressor[J]. Journal of Turbomachinery,2014,136(5): 051006.1-051006.9. [10] MAILACH R,LEHMAN I,VOGELER KAND. Rotating instabilities in an axial compressor originating from the fluctuating blade tip vortex[J]. Journal of Turbomachinery,2001,123(3): 453-460. doi: 10.1115/1.1370160 [11] DODDS J,VAHDATI M. Rotating stall observations in a high speed compressor: Part ⅱ numerical study[J]. Journal of Turbomachinery,2015,137(5): 1-10. [12] LI Q S,PAN T Y,SUN T L,et al. Experimental investigations on instability evolution in a transonic compressor at different rotor speeds[J]. Journal of Mechanical Engineering Science,2015,229(18): 3378-3391. doi: 10.1177/0954406215573779 [13] 潘天宇,贺雷,王正鹤,等.局部喘振频率特性及估算方法[J].航空动力学报, 2015,30(11):2666-2672.PAN Tianyu,HE Lei,WANG Zhenghe,et al. Study on the frequency of partial surge and a frequency prediction method[J].Journal of Areospace Power,2015,30(11):2666-2672.(in Chinese) [14] 潘天宇,孙太璐,李志平,等. 局部喘振的发生机理[J]. 航空动力学报,2016,31(4): 877-885. doi: 10.13224/j.cnki.jasp.2016.04.014PAN Tianyu,SUN Tailu,LI Zhiping,et al. Occurrence mechanism of partial surge[J]. Journal of Areospace Power,2016,31(4): 877-885. (in Chinese) doi: 10.13224/j.cnki.jasp.2016.04.014 [15] PAN T Y,LI Q S,LI Z P,et al. Effects of radial loading distribution on partial-surge-initiated instability in a transonic axial flow compressor[J]. Journal of Turbomachinery,2017,139(10): 101010.1-101010.13. [16] DAY I J. Axial compressor performance during surge[J]. Journal of Propulsion and Power,1994,10(3): 329-336. doi: 10.2514/3.23760 [17] NIE C Q,An experimental investigation on different radial loading distribution and patterns of stall inception in a single-stage low-speed axial compressor[R].ASME Paper GT2003-38090,2003.