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 State and Performance Correction

作　　者：周安宇 孟德君 赵清伟 陈雷 史文斌 高海洋 ZHOU An-yu;MENG De-jun;ZHAO Qing-wei;CHEN Lei;SHI Wen-bin;GAO Hai-yang(AECC Shenyang Engine Research Institute,Shenyang 110015,China)

机构地区：[1]中国航发沈阳发动机研究所,沈阳110015

出　　处：《航空发动机》2024年第6期54-59,共6页Aeroengine

基　　金：航空动力基础研究项目资助。

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T1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T1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。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 T1 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 T1,the hot state tip clearance of the compressor decreases,and the flow rate,pressure ratio,maximum efficiency,and surge margin increase approximately linearly.

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 

分 类 号：V231.3[航空宇航科学与技术—航空宇航推进理论与工程]