| 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 |
| 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 |
| Numerical Calculation and Experimental Verification of Rotor-tip-clearance Effects on High-Load Compressor Performance |
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| DOI： |
| 中文关键词: 转子叶尖间隙 高负荷压气机 泄漏流 数值计算 试验验证 航空发动机 |
| 英文关键词:rotor-tip-clearance high-load compressor leakage flow numerical calculation experimental verification aeroengine |
| 基金项目:航空动力基础研究项目资助 |
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| 中文摘要: |
| 为了研究高负荷压气机转子叶尖间隙对压气机性能的影响，采用数值模拟软件NUMECA对某4级压气机和其中的1个
典型级进行了不同间隙的计算。计算结果表明：当间隙超过叶高的0.52%后，叶尖流场出现堵塞，喘点压比衰减速度开始加剧，直
至5.24%性能衰减速度逐渐减弱；在多级环境中，4级压气机间隙增大叶高的0.5%，喘点压比降低了约0.6%～4.3%，间隙增大的叶
排作功能力降低是压气机喘点总压比降低的主要原因，其中前2级间隙增大对总性能影响较大。同时，通过4级压气机试验验证
了间隙对性能的影响，验证结果表明：间隙增大叶高的0.78%后，4级压气机喘点压比和峰值效率分别降低了1.4%和0.4%，在
65%～88%叶高时的压比和效率的性能衰减较为明显。 |
| 英文摘要: |
| 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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