航空学报2025，Vol.46Issue(12)：113-131,19.DOI:10.7527/S1000-6893.2024.31388
新研民用涡轴发动机结冰适航试验
Icing airworthiness test on a newly developed civil turbo-shaft engine
摘要
Abstract
In this paper,the icing airworthiness test is conducted independently.A newly developed civil turbo-shaft engine is taken as the verification platform.The technical problems such as development of icing spray system and simulation of cloud spray flowfield are solved.Icing tests in icing envelope conditions are completed by using the newly constructed icing test bench.The ice formation mechanism of the intake system is revealed.The ice morphology of the engine intake system is obtained,and the impact of the flight environment on ice morphology is analyzed.The changing rules of total pressure loss,compressor efficiency,gas turbine outlet temperature and other parameters are summarized.The test results show that icing mainly occurs in the intake mesh cover of the engine,and the icing type is mainly manifested as glaze ice and rime ice.There are various forms of ice morphology,and the rime ice covers a large area,with the maximum icing thickness up to 260 mm appearing at temperature-10℃,altitude 1.2 km,and velocity 280 km/h.Icing has a significant impact on engine performance.Due to icing,the total intake pressure loss coefficient of the engine reaches up to 13.3%,the compressor efficiency value decreases by up to 10.4%,the gas temperature at gas turbine outlet increases by 41℃and the engine power decreases by 15.8%at temperature-30℃,altitude 6 km,and velocity 280 km/h.During the icing test,the engine does not show any abnormal phenom-ena such as stalling or flame-out,which fully verifies the stability and reliability of the engine under adverse icing conditions.关键词
涡轴发动机/结冰关键点/云雾参数/适航试验/发动机性能Key words
turbo-shaft engine/ice critical point/cloud spray parameter/airworthiness test/engine performance分类
航空航天引用本文复制引用
李概奇,田骏丹,吴晶峰,赵尊盛,杨洋,刘梦妮..新研民用涡轴发动机结冰适航试验[J].航空学报,2025,46(12):113-131,19.基金项目
民用涡轴发动机型号研制项目 Civil Turbo-shaft Engine Development Project （）
