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Effect of wire mesh casing treatment on axial compressor performance and stability

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In this paper,a kind of Wire Mesh Casing Treatment(WMCT)is proposed to improve the stable operating range of the compressor.In contrast to the traditional circumferential groove,as for WMCT,a layer of wire mesh is laid on the surface of the circumferential groove.Parametric studies were conducted on the low-speed axial flow compressor,including the groove width,axial location,and mesh count.The optimum axial location for WMCT is related to its groove width.A higher wire mesh count results in a smaller compressor stall margin improvement.Steady simula-tions were carried out to study the effect of WMCT on the flow structure of the compressor.The wire mesh in the WMCT has a certain flow resistance,which restricts the flow into and out of the groove.Due to the WMCT,the flow parameter in the tip region of the rotor is less sensitive to changes in the operating conditions of the compressor.The WMCT causes the rotor tip blade loading to shift backward,inhibiting the formation of spill forward of the leakage flow,and thus improving the stability of the compressor.The flow resistance on the groove surface is a new degree-of-freedom for the casing treatment designer.

Axial compressorWire mesh casing treatmentTip clearance flowStall marginBlade loading

Ming ZHANG、Jiaming ZHANG、Jiahao HU、Xu DONG、Dakun SUN、Xiaofeng SUN

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School of Energy and Power Engineering,Beihang University,Beijing 100191,China

Beihang Hangzhou Innovation Institute Yuhang,Hangzhou 310023,China

National Key Laboratory of Science and Technology on Aero-Engine Aero-Thermodynamics,Beihang University,Beijing 100191,China

国家自然科学基金国家自然科学基金Science Center for Gas Turbine Project,ChinaScience Center for Gas Turbine Project,ChinaScience Center for Gas Turbine Project,China国家科技重大专项Key Laboratory of Pre-Research Management Centre,China

52325602U2241276P2022-A-Ⅱ-002-001P2022-C-Ⅱ-001-001P2022-C-Ⅱ-003-0012017-Ⅱ-0005-00186142702200101

2024

10.1016/j.cja.2023.11.009

中国航空学报(英文版)
中国航空学会

中国航空学报(英文版)

CSTPCDEI
影响因子：0.847
ISSN：1000-9361
年,卷(期)：2024.37(3)
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