Effects of casing elliptical deformation on the aerodynamic stability of a transonic axial compressor rotor
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摘要:
选取跨声速压气机转子Rotor37作为研究对象，基于经过验证的数值计算方法，对设计转速条件下机匣变形所产生的影响及其作用机理进行了研究。结果表明，在理想机匣条件下，转子叶顶间隙泄漏涡的破碎是压气机失稳的直接诱因。随着机匣椭圆变形度τ的增大，压气机的稳定裕度逐渐降低；当机匣变形度τ达到最大值0.9时，其稳定裕度较理想机匣下降了4.67%，且流动失稳首先出现在最小叶顶间隙附近的叶片通道。同时，机匣变形下通道叶顶区域流动及阻塞区影响范围表现出显著周向不均匀性。一方面，前缘叶顶间隙尺寸与气流攻角的周向非均匀分布决定了各通道前缘泄漏流强度，进而影响各通道前缘泄漏阻塞区的作用范围，该阻塞区在最大叶顶间隙附近达到最大，主导该处通道失稳；另一方面，尾缘叶顶间隙尺寸和各叶片吸力面近壁面流动分离位置的周向非均匀分布分别决定了尾缘间隙泄漏流强度及近壁面流动分离程度，进而影响各通道近吸力面阻塞区的作用范围，该阻塞区在最小叶顶间隙附近通道内影响最大，导致该通道率先失稳。
Abstract:This study investigated the impact of casing deformation on the Rotor 37 transonic compressor rotor using validated numerical simulations at design speed. The results showed that under the ideal(undeformed) casing condition, the breakdown of the rotor’s tip-leakage vortex served as the direct trigger for compressor stall. As τ increased, the compressor’s stability margin steadily decreased. At maximum deformation (τ = 0.9), stall margin dropped by 4.67 % relative to the ideal casing, and flow instability first appeared in passages adjacent to the smallest tip clearance. Simultaneously, casing deformation induced pronounced circumferential variability in the flow field and blockage-zone extent within the blade-tip region. On one hand, circumferential non-uniformity in leading-edge tip clearance and local flow incidence controlled the leading-edge leakage strength in each passage, shaping blockage-zone extent. Blockage was most severe near maximum tip clearance, triggering instability in that passage. On the other hand, circumferential non-uniformity in trailing-edge tip clearance and suction-side separation location controlled the trailing-edge leakage intensity and separation-blockage severity. These factors maximize blockage near minimum tip clearance, causing the earliest instability in that passage.
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图 5 不同机匣变形度下压气机气动特性对比
Figure 5. Aerodynamic characteristics of compressors under different casing deformation degrees
图 6 不同机匣变形度下压气机综合稳定裕度对比
Figure 6. Comparison of compressor stability margins under different casing deformation levels
图 7 τ=0不同工况下压气机子午流面的周向平均熵分布
Figure 7. τ=0 Circumferentially averaged entropy on the compressor’s meridional plane under various conditions
图 8 τ=0不同工况叶顶流场结构
Figure 8. τ=0 Flow field structure at the blade tip under different operating conditions
图 9 τ=0近失稳与过失稳状态叶顶（98%叶高）损失分布
Figure 9. τ=0 Entropy contours at 98% span under near stall and post stall conditions
图 10 τ=0不同工况叶顶相对压力分布
Figure 10. τ=0 Pre distribution under various operating conditions
图 11 τ=0不同工况叶顶载荷分布
Figure 11. τ=0 Blade tip load distribution under different operating conditions
图 12 τ=0 不同工况下叶顶流向涡量分布
Figure 12. τ=0 Tip-flow vorticity distribution under various conditions
图 13 不同机匣变形度下压气机叶顶（98%叶高）损失分布
Figure 13. Compressor tip loss distribution under varying casing deformation
图 14 τ=0.9近失稳工况与τ=0同流量工况（$\dot m $=19.251 kg/s）各通道质量流率密度分布对比
Figure 14. Comparison of passage dense-flow distribution at τ=0.9 near-stall vs. τ=0 same-flow （$\dot m $=19.251 kg/s）
图 15 不同机匣变形程度下不同叶道出口质量流率密度分布
Figure 15. Dense flow distribution at the blade passage exit under different casing deformation degrees and passages
图 16 τ=0.9 通道“17”近失稳工况流动失稳震荡周期
Figure 16. τ=0.9 Unsteady flow oscillations in passage 17 near stall
图 17 τ=0.9 通道“17”和“7”过失稳状态叶顶（98%叶高）损失分布
Figure 17. Tip-loss distribution at 98% span for passages 17 and 7 under τ=0.9 post-stall
图 18 原型机匣和变形机匣下近失稳工况各叶片98%叶高的气动载荷分布
Figure 18. Aerodynamic load distribution at 98% span of each blade
图 19 各叶片通道98%叶高气流角及攻角分布
Figure 19. Radial profiles of aerodynamic angles at 98% span in multi-blade passages
图 20 τ=0.9 近失稳工况下叶片“7”、“17”间隙泄漏流形态及吸力面相对静压分布
Figure 20. Leakage pattern and suction-side relative static pressure for blades 7 & 17 at τ=0.9 near-stall
表 1 Rotor 37设计参数
参数 数值 叶片数 36 设计转速/（r/min） 17188.7 设计压比 2.106 叶尖速度/（m/s） 454.14 设计流量/（kg/s） 20.19 等熵效率 0.889 叶顶间隙高度/mm 0.356 
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[1] Dean, R. C , Jr , 1954, “The Influence of tip Clearance on Boundary –Layer Flow in a Rectilinear Casade, ”MIT Gas Turbine Laboratory Report No. 27-3. [2] Kunz R F, Lakshminarayana B, Basson A H. Investigation of tip clearance phenomena in an axial compressor cascade using Euler and navier–stokes procedures[J]. Journal of Turbomachinery, 1993, 115(3): 453-467. [3] Khalid S A, Khalsa A S, Waitz I A, et al. Endwall blockage in axial compressors[C]//Volume 1: Turbomachinery. American Society of Mechanical Engineers, 1998: V001T01A047. [4] Thomas H J. Unstable natural vibration of turbine rotors induced by the clearance flow in glands and blading[J]. Bulletin de L’ A. I. M., 1958, 71(11/12): 1039-1063. [5] Alford J S. Protecting turbomachinery from self-excited rotor whirl[J]. Journal of Engineering for Power, 1965, 87(4): 333-343. doi: 10.1115/1.3678270 [6] Morris S C, Cameron J D, Bennington M A, et al. Performance and short length-scale disturbance generation in an axial compressor with non-uniform tip clearance[C]//Volume 6: Turbomachinery, Parts A, B, and C. ASMEDC, 2008: 667-679. [7] Song S J, Cho S H. Nonuniform flow in a compressor due to asymmetric tip clearance[J]. Journal of Turbomachinery, 2000, 122(4): 751-760. doi: 10.1115/1.1308569 [8] Jüngst M, Liedtke S, Schiffer H P, et al. Aerodynamic effects in a transonic compressor with nonaxisymmetric tip clearance[C]//Volume 2A: Turbomachinery. American Society of Mechanical Engineers, 2018: V02AT45A007. [9] Kang Y S, Kang S H. Prediction of the nonuniform tip clearance effect on the axial compressor flow field[J]. Journal of Fluids Engineering, 2010, 132(5): 051110. doi: 10.1115/1.4001553 [10] 李剑雄, 陈颖秀, 侯安平. 非均匀间隙下进气畸变对风扇性能的影响[J]. 航空动力学报, 2020, 35(3): 532-539. Li Jianxiong, Chen Yingxiu, Hou Anping. Effects of inlet flow distortion on fan performance under nonuniform tip clearance[J]. Journal of Aerospace Power, 2020, 35(3): 532-539. (in Chinese doi: 10.13224/j.cnki.jasp.2020.03.009Li Jianxiong, Chen Yingxiu, Hou Anping. Effects of inlet flow distortion on fan performance under nonuniform tip clearance[J]. Journal of Aerospace Power, 2020, 35(3): 532-539. (in Chinese) doi: 10.13224/j.cnki.jasp.2020.03.009 [11] Young A M, Cao Teng, Day I J, et al. Accounting for eccentricity in compressor performance predictions[J]. Journal of Turbomachinery, 2017, 139(9): 091008. doi: 10.1115/1.4036201 [12] Cameron J D, Bennington M A, Ross M H, et al. Effects of steady tip clearance asymmetry and rotor whirl on stall inception in an axial compressor[C]//Volume 6: Turbo Expo 2007, Parts A and B. ASMEDC, 2007: 457-468. [13] 张浩浩, 朱铭敏, 羌晓青, 等. 基于喷管节流的轴流转子非轴对称间隙布局研究[J]. 工程热物理学报, 2022, 43(2): 331-340. Zhang Haohao, Zhu Mingmin, Qiang Xiaoqing, et al. Research on non-axisymmetric clearance layout of axial rotor based on nozzle throttling[J]. Journal of Engineering Thermophysics, 2022, 43(2): 331-340. (in ChineseZhang Haohao, Zhu Mingmin, Qiang Xiaoqing, et al. Research on non-axisymmetric clearance layout of axial rotor based on nozzle throttling[J]. Journal of Engineering Thermophysics, 2022, 43(2): 331-340. (in Chinese) [14] Graf M B, Wong T S, Greitzer E M, et al. Effects of nonaxisymmetric tip clearance on axial compressor performance and stability[J]. Journal of Turbomachinery, 1998, 120(4): 648-661. doi: 10.1115/1.2841774 [15] 向宏辉, 葛宁, 高杰, 等. 周向非均匀叶尖间隙对轴流压气机性能的影响[J]. 航空学报, 2018, 39(2): 61-72. Xiang Honghui, Ge Ning, Gao Jie, et al. Effect of circumferential non-uniform tip clearance on performance of axial compressor[J]. Acta Aeronautica et Astronautica Sinica, 2018, 39(2): 61-72. (in Chinese doi: 10.7527/S1000-6893.2017.121491Xiang Honghui, Ge Ning, Gao Jie, et al. Effect of circumferential non-uniform tip clearance on performance of axial compressor[J]. Acta Aeronautica et Astronautica Sinica, 2018, 39(2): 61-72. (in Chinese) doi: 10.7527/S1000-6893.2017.121491 [16] 梁武昌, 楚武利, 朱俊强, 等. 非轴对称尖部间隙对轴流压气机性能影响的实验研究[J]. 航空动力学报, 2004, 19(2): 233-236. Liang Wuchang, Chu Wuli, Zhu Junqiang, et al. Effects of asymmetric tip clearance on axial flow compressor performance[J]. Journal of Aerospace Power, 2004, 19(2): 233-236. (in Chinese doi: 10.3969/j.issn.1000-8055.2004.02.013Liang Wuchang, Chu Wuli, Zhu Junqiang, et al. Effects of asymmetric tip clearance on axial flow compressor performance[J]. Journal of Aerospace Power, 2004, 19(2): 233-236. (in Chinese) doi: 10.3969/j.issn.1000-8055.2004.02.013 [17] 孙玲. 转子尖部间隙布局对压气机性能影响的实验研究[D]. 西安: 西北工业大学, 2003. Sun Ling. Experimental investigation of layout of tip clearance effects on the performance of an axial-flow compressor[D]. Xi’an: Northwestern Polytechnical University, 2003. (in ChineseSun Ling. Experimental investigation of layout of tip clearance effects on the performance of an axial-flow compressor[D]. Xi’an: Northwestern Polytechnical University, 2003. (in Chinese) [18] di Mare L, Imregun M, Green J S. Effect of real geometry on compressor performance predictions[C]//Volume 7: Turbomachinery, Parts A and B. ASMEDC, 2009: 263-271. [19] Chen Yingxiu, Hou Anping, Zhang Mingming, et al. Effects of nonuniform tip clearance on fan performance and flow field[C]//Volume 2A: Turbomachinery. American Society of Mechanical Engineers, 2015: V02AT37A010. [20] 李紫良, 陈宇飞, 王楠, 等. 机匣椭圆变形对亚声速压气机转子气动损失特性的影响研究[J]. 航空动力学报, 2026, 41(5): 193-203. Li Ziliang, Chen Yufei, Wang Nan, et al. Influence of elliptical casing deformation on aerodynamic loss performance of subsonic compressor rotor[J]. Journal of Aerospace Power, 2026, 41(5): 193-203. (in ChineseLi Ziliang, Chen Yufei, Wang Nan, et al. Influence of elliptical casing deformation on aerodynamic loss performance of subsonic compressor rotor[J]. Journal of Aerospace Power, 2026, 41(5): 193-203. (in Chinese) [21] 陈颖秀, 侯安平, 张明明, 等. 轴流压气机机匣变形对多排转子流场特性的影响[J]. 航空学报, 2016, 37(11): 3284-3295. Chen Yingxiu, Hou Anping, Zhang Mingming, et al. Effects of casing deformation on blade rows flow field characteristics in an axialflow compressor[J]. Acta Aeronautica et Astronautica Sinica, 2016, 37(11): 3284-3295. (in Chinese doi: 10.7527/S1000-6893.2016.0010Chen Yingxiu, Hou Anping, Zhang Mingming, et al. Effects of casing deformation on blade rows flow field characteristics in an axialflow compressor[J]. Acta Aeronautica et Astronautica Sinica, 2016, 37(11): 3284-3295. (in Chinese) doi: 10.7527/S1000-6893.2016.0010 [22] 成铠, 陈云瑞, 孟凡杰, 等. 叶顶间隙非均匀对大型轴流风机性能的影响[J]. 西安交通大学学报, 2022, 56(10): 180-189. Cheng Kai, Chen Yunrui, Meng Fanjie, et al. Influence of non-uniform blade tip clearance on the performance of a large axial flow fan[J]. Journal of Xi’an Jiaotong University, 2022, 56(10): 180-189. (in Chinese doi: 10.7652/xjtuxb202210018Cheng Kai, Chen Yunrui, Meng Fanjie, et al. Influence of non-uniform blade tip clearance on the performance of a large axial flow fan[J]. Journal of Xi’an Jiaotong University, 2022, 56(10): 180-189. (in Chinese) doi: 10.7652/xjtuxb202210018 -
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