| 魏 崃，尹 松，郭海宁，高 山.转子叶尖间隙对高负荷压气机性能影响的数值计算和试验验证[J].航空发动机,2023,49(6):14-18 |
| Numerical Calculation and Experimental Verification of Rotor-tip-clearance Effects on High-Load Compressor Performance |
| DOI： |
| Key Words:rotor-tip-clearance high-load compressor leakage flow numerical calculation experimental verification aeroengine |
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| Abstract:In order to analyze the effect of rotor-tip-clearance on the performance of high-load compressors, simulations of a four-
stage compressors and one typical stage with different clearance were calculated by NUMECA. The calculation results show that when clear?
ance exceeds 0.52% span, tip flow blockage emerges, and the attenuation rate of the surge-point pressure ratio begins to intensify until the
tip clearance reaches 5.24% span, the performance attenuation rate gradually weakens; In the multi-stage environment, with a 0.5% span
tip clearance increase, the total pressure ratio reduces about 0.6% to 4.3%. The working capacity decrease of the blade row with increased
clearance is the main reason for the decrease of the surge-point total pressure ratio, with the clearance increases of the first two stages hav?
ing more significant impact on the overall performance. Meanwhile, the influence of the clearance on performance was verified by the four-
stage compressor experiments. The verification results show that if the clearance increases 0.78% span, the surge-point total pressure ratio
and peak efficiency of the four-stage compressor are reduced by 1.4%，0.4% respectively, with the performance degradation of the pressure
ratio and efficiency more significant at 65% to 88% spanwise position of the blade. |
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