Influence of the Initial Position of the Controllable Speed Casing on the Tip Flow of High-Load Compressor Stage

展开
  • Merchant Marine College, Shanghai Maritime University, Shanghai 201306, China

网络出版日期: 2026-01-05

基金资助

The authors would like to thank the Key Project of the National Nature Science Foundation of China (Grant No. 52236005) and the Key Project of the Center for Basic Science of Aeroengine and Gas Turbine (Grant No. P2022-B-II-007-001) for funding this work.

版权

Science Press, Institute of Engineering Thermophysics, CAS and Springer-Verlag GmbH Germany, part of Springer Nature 2025

Influence of the Initial Position of the Controllable Speed Casing on the Tip Flow of High-Load Compressor Stage

Expand
  • Merchant Marine College, Shanghai Maritime University, Shanghai 201306, China

Online published: 2026-01-05

Supported by

The authors would like to thank the Key Project of the National Nature Science Foundation of China (Grant No. 52236005) and the Key Project of the Center for Basic Science of Aeroengine and Gas Turbine (Grant No. P2022-B-II-007-001) for funding this work.

Copyright

Science Press, Institute of Engineering Thermophysics, CAS and Springer-Verlag GmbH Germany, part of Springer Nature 2025

摘要

可控转速机匣是一种新型的机匣处理技术,将原始的全固定式机匣设计为可转动环段和固定环段两个部分。可转动环段的起始位置是影响可控转速机匣作用范围的重要参数之一。本研究探讨了可转动环段的终止位置固定在转子叶顶尾缘位置时,起始位置的变化对压气机气动性能和流动稳定性的影响。结果表明:当可转动环段的起始位置处于叶顶尾缘附近时,可控转速机匣通过改善尾缘附近的二次流,实现微弱扩稳。然而,当起始位置与叶尖泄漏涡和诱导涡破裂区域重合时,可控转速机匣会对起始位置上游的流动产生扰动,造成低能流体的堵塞面积增加,诱发压气机的提前失速。当起始位置处于转子叶顶前缘位置时,可控转速机匣可以有效改善叶顶泄漏流动,并促进泄漏涡远离相邻叶片压力面,削弱了叶顶通道的堵塞效应,从而显著提升了压气机的流动稳定性。此时,可控转速机匣可使压气机稳定工作裕度最大提升45.11%。

本文引用格式

WU Wanyang, HU Yi, ZHAO Ao, ZHONG Jingjun . Influence of the Initial Position of the Controllable Speed Casing on the Tip Flow of High-Load Compressor Stage[J]. 热科学学报, 2026 , 35(1) : 50 -61 . DOI: 10.1007/s11630-025-2213-3

Abstract

Controllable speed casing (CSC) represents an innovative development in casing treatment technology, wherein the traditional stationary casing is reconfigured into two components: a rotatable ring and a stationary ring. Initial position (IP) of the rotatable ring is a critical parameter affecting the operational effectiveness of CSC. This study investigates the influence of varying IP of the rotatable ring on the aerodynamic performance and flow stability of a high-load compressor stage, with terminal position (TP) fixed at the rotor tip trailing edge. The results reveal that positioning the rotatable ring near the rotor tip trailing edge leads to moderate improvements in stability by controlling the secondary flow at the trailing edge. However, when IP coincides with the region where the tip leakage vortex and induced vortex breakdown, CSC disrupts the upstream flow, increasing the blockage of low-energy fluid, thereby precipitating an early stall in the compressor. Conversely, positioning IP at the rotor leading edge enables CSC to effectively manage tip leakage flow, facilitating the deflection of the tip leakage vortex away from the adjacent blade pressure surface. This adjustment mitigates the blocking effect within the blade tip passage, thereby significantly enhancing the compressor’s flow stability. Under these optimal conditions, CSC achieves a substantial 45.11% improvement in stable operating margin of the compressor.

参考文献

[1] Zheng X.Q., Li Z.H., Blade-end treatment to improve the performance of axial compressors: An overview. Progress in Aerospace Sciences, 2017, 88(1): 1–14.
[2] Si C.X., Wu Z.H., Simplified numerical models of the unsteady tip leakage flow in compressor. Journal of Thermal Science, 2023, 32(6): 2386–2399.
[3] Vo H.D., Cameron J.D., Morris S.C., Control of short length-scale rotating stall inception on a high-speed axial compressor with plasma actuation. ASME Turbo Expo 2008: Power for Land, Sea, and Air, Berlin, Germany, 2008, 6: 533–542.
[4] Benini E., Biollo R., Ponza R., Efficiency enhancement in transonic compressor rotor blades using synthetic jets: a numerical investigation. Applied Energy, 2011, 88(3): 953–962.
[5] Fietzke B., Mihalyovics J., King R., et al., Binary repetitive model predictive active flow control applied to an annular compressor stator cascade with periodic disturbances. Journal of Engineering for Gas Turbines and Power, 2022, 144 (1): 011029.
[6] Spence S.W.T., O'Neill J.W., Cunningham G., An investigation of the flow field through a variable geometry turbine stator with vane endwall clearance. Proceedings of the Institution of Mechanical Engineers Part A: Journal of Power and Energy, 2006, 220(12): 899–910.
[7] Zhong J.J., Wu W.Y., Han S.B., Research progress of tip winglet technology in compressor. Journal of Thermal Science, 2021, 30(1): 18–31.
[8] Zhao A., Wu W.Y., Hu Y., et al., Influence of the chordwise distribution of tip winglets on the stability of a high-load compressor stage. Physics of Fluids, 2023, 35(10): 104111.
[9] Wang N.F., Liu C., Jiang D.X., Prediction of transient vibration response of dual-rotor-blade-casing system with blade off. Proceedings of the Institution of Mechanical Engineers Part G: Journal of Aerospace Engineering, 2019, 233(11): 5164–5176.
[10] Wu G.H., Zheng L.J., Wu K.Q., Numerical analysis and PIV measurements of tip vortex in an axial rotor with skewed-swept blade at its leading edge. Journal of Thermal Science, 2004, 13(1): 16–23.
[11] Koch C.C., Experimental evaluation of outer case blowing or bleeding of single stage axial-flow compressor. NASA CR-54592, 1970.
[12] Oscarson R.P., Wright D.L., Experimental evaluation of a honeycomb rotor shroud configuration to improve the stall margin of a 0.5 hub-hip ratio single stage compressor, NASA CR-72809, 1970.
[13] Osborn W.M., Lewis G.W., Heidelberg L.J., Effect of porous casing treatment on stall limit and on overall performance of an axial-flow compressor rotor, NASA TND-6537, 1970.
[14] Houghton T., Day I., Enhancing the stability of the subsonic compressors using casing grooves. Journal of Turbomachinery-Transactions of the ASME, 2012, 113(4): 021007.
[15] Zhu J., Chu W., Lu X., Design and experimental investigations of a new type of casing treatment for an axial flow compressor. Proceedings of the Institution of Mechanical Engineers Part A: Journal of Power and Energy, 2006, 220(5): 207–215.
[16] Wilke I., Kau H.P., A numerical investigation of the flow mechanisms in a HPC front stage with axial slots. ASME Turbo Expo 2003, collocated with the 2003 International Joint Power Generation Conference, Atlanta, Georgia, USA, 2003, 6: 465‒477.
[17] Hah C., The inner workings of axial casing grooves in a one and a half stage axial compressor with a large rotor tip gap: Changes in stall margin and efficiency. Journal of Turbomachinery, 2019, 141(1): 011001.
[18] Zhang H.G., Liu W.H., Wang E.H., et al., Mechanism investigation of enhancing the stability of an axial flow rotor by blade angle slots. Proceedings of the Institution of Mechanical Engineers Part G: Journal of Aerospace Engineering, 2019, 233(10): 4750–4764.
[19] Kumar S.S., Alone D.B., Timmaiah S.M., et al., Aerodynamic behavior of a transonic axial flow compressor stage with self-recirculating casing treatment. Aerospace Science and Technology, 2021, 112(5): 106587.
[20] Vuong T.D., Kim K.Y., Dinh C.T., Recirculation-groove coupled casing treatment for a transonic axial compressor, Aerospace Science and Technology, 2021, 111(3): 106556.
[21] Sun D.K., Nie C.Q., Liu X.H., et al., Further investigation on transonic compressor stall margin enhancement with stall precursor-suppressed casing treatment. Journal of Turbomachinery-Transactions of the ASME, 2016, 138(2): 021001.
[22] Zhong J.J., Wu W.Y., A rotatable inner endwall casing for compressor rotor, China, Patent ZL201910069085.1, 2023.12.
[23] Hu Y., Wu W.Y., Zhao A., et al., Influence of the rotation characteristics of the controllable speed casing on the flow stability of a high-load compressor stage. Aerospace Science and Technology, 2023, 141(10): 108575.
[24] Wu W.Y., Zhao J.Y., Zhong J.J., Influence of the rotating direction and speed of controllable speed casing on the flow stability of a transonic compressor rotor under design condition. Aerospace Science and Technology, 2023, 126(7): 107630.
[25] Zhong J.J., Hu Y., Zhao A., et al., Influence of the terminal position of the rotatable ring of controllable speed casing on the flow stability of a high-load compressor stage. ASME Turbo Expo 2024: Turbomachinery Technical Conference and Exposition, London, United Kingdom, 2024.
DOI: 10.1115/GT2024-123009.
[26] Kan X.X., Suo L.C., Lei H.D., et al., Shock wave spectrum forming around the compound five-hole probe and its influence on pneumatic parameters acquisition during subsonic to supersonic flow. Journal of Thermal Science, 2024, 33(6): 2019–2031.
[27] Hunt J.C.R., Wray A.A., Moin P., Eddies, stream, and convergence zones in turbulent flows, Center for Turbulence Research Report CTR-S88, 1988.
[28] Zhao A., Wu W.Y., Hu Y., et al., Influence of the chordwise distribution of tip winglets on the stability of a high-load compressor stage. Physics of Fluids, 2023, 35(10): 104111.
文章导航

/