| 周安宇，孟德君，赵清伟，陈 雷，史文斌，高海洋.进口总温对整机状态高压压气机特性影响及特性修正[J].航空发动机,2024,50(6):54-59 |
| 进口总温对整机状态高压压气机特性影响及特性修正 |
| Influence of Inlet Temperature on Performance of High-Pressure Compressor under Whole Engine Stateand Performance Correction |
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| DOI： |
| 中文关键词: 进口总温 叶尖间隙 变形量模型 压气机性能 特性修正 高压压气机 航空发动机 |
| 英文关键词:inlet total temperature tip clearance deformation model compressor performance performance correction high-
pressure compressor aeroengine |
| 基金项目:航空动力基础研究项目资助 |
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| 摘要点击次数: 159 |
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| 中文摘要: |
| 为准确评估高压压气机在整机状态不同进口总温下的特性，以满足更精确的发动机整机性能匹配和分析，开展了双转
子发动机进口总温T 1 的变化对高压压气机工作性能影响的有限元计算。通过有限元计算结果分析评估部件状态与整机状态转子
各部分的变形量占比，完成热态间隙计算。结合压气机部件试验的间隙测试结果评估有限元计算的准确性，构建了满足工程精度
的整机状态压气机转子变形量模型。采用多元线性回归分析方法建立变形量与压气机特征参数的方程，确定发动机进口总温与
压气机转子变形量的变化关系，并结合压气机不同间隙状态下的试验结果分析转子叶尖热态间隙对压气机性能影响的规律，构建
整机状态高压压气机的特性修正模型。结果表明：随着T 1 的升高，压气机的热态间隙减小，流量、压比、最高效率和喘振裕度近似
呈线性提高。最终获取不同进口总温下整机状态高压压气机的气动参数变化规律与修正特性。 |
| 英文摘要: |
| To accurately evaluate the performance of high-pressure compressors under different inlet total temperatures under whole
engine state and to meet more accurate engine performance matching and analysis requirements, finite element calculations were carried
out on the impact of the variation of the inlet total temperatures T 1 of a twin-spool engine on the performance of the high-pressure compres?
sor. Based on the finite element calculation results, the deformation ratio of each part of the rotors in the component state and the whole
engine state were evaluated and analyzed, and the hot state tip clearance calculation was completed. Based on the tip clearance results of
the compressor component test, the accuracy of the finite element calculations was evaluated and a deformation model of the compressor
rotor in the whole engine state that meets the engineering accuracy requirement was constructed. Multiple linear regression analysis method
was used to establish correlations between the deformation and the compressor performance parameters, to determine the relationship
between the engine inlet total temperature and the compressor rotor deformation. Based on compressor test results under different tip clear?
ance conditions, the influence law of rotor hot state tip clearance on compressor performance was analyzed, and the performance correction
model of the high-pressure compressor under the whole engine state was constructed. Finally, the variation laws of the aerodynamic
parameters and the corrected high-pressure compressor performance under different inlet total temperatures were obtained. The results
show that with the increase of T 1 , the hot state tip clearance of the compressor decreases, and the flow rate, pressure ratio, maximum
efficiency, and surge margin increase approximately linearly. |
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