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
Key words
inlet total temperature/tip clearance/deformation model/compressor performance/performance correction/high-pressure compressor/aeroengine
维普
万方数据