摘要
核心机试验进气范围宽,从常温常压状态到加温加压进气状态,进行进气温度和压力调节的同时给核心机带来大量的过渡态工作过程,对核心机气动稳定性提出了较高的需求,通过压气机进口可调静子叶片角度(α2)的调节可以有效提升稳定裕度,需要设计出合理的压气机α2规律来保证核心机的试验安全。为了研究压气机进口可调静子叶片角度控制规律,以整机大量试验数据为基础,以发动机相似原理为理论依据,分别在核心机稳态、加速和减速等不同状态下开展核心机与整机压气机进口可调静子叶片角度控制规律对比研究。结果表明:最终确定的压气机α2稳态规律与整机的n2R25-α2控制规律相同,遵循在加速过程中稳态基础上偏关2°、在减速过程中稳态基础上偏关5.5°的控制规律,确保压气机在试验过程有较好的稳定裕度,保证试验安全。
The core engine test has a wide air inlet range.While adjusting the air inlet temperature and pressure from normal tempera�ture and pressure to heated and pressurized air inlet,it brings a large number of transition working processes to the core engine,which puts forward a high demand for the aerodynamic stability of the core engine.The stability margin could be effectively improved by adjusting the compressor inlet variable stator vanes angle(α2).It was necessary to design a reasonable compressorα2 rules to ensure the test safety of core engine.In order to investigate the control law of compressor inlet variable stator vanes angle,based on a large number of whole engine test data and the engine similarity principle,a comparative study on the control law of compressor inlet variable stator vanes angle of the core engine and the whole engine was carried out under different states such as steady state,acceleration and deceleration of the core en⁃gine.The results show that the final compressorα2 steady state law is the same as the n2R25-α2 control law of the whole engine.The control law of turning off 2°on the basis of steady state in the acceleration process and 5.5°on the basis of steady state in the deceleration process ensures that the compressor has a good stability margin in the test process and ensures the test safety.
作者
王赫
杨纯辉
韩文俊
王晨
WANG He;YANG Chun-hui;HAN Wen-jun;WANG Chen(AECC Shenyang Engine Research Institute,Shenyang 110015,China;Air Force Equipment Department Second Military Representative Office in Shenyang,Shenyang 110043,China)
出处
《航空发动机》
北大核心
2022年第3期20-24,共5页
Aeroengine
基金
航空动力基础研究项目资助。
作者简介
王赫(1989),男,硕士,工程师,从事航空发动机总体性能设计工作。E-mail:wanghe_200806@126.com。
