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针对航空发动机加力燃烧室的冷却,采用横向波纹隔热屏结构和全气膜冷却相结合的高效冷却方式,利用CFD软件,计算分析了吹风比、波长、波幅等结构、气动参数对气膜冷却效率以及热侧换热系数的影响规律。结果表明:随着吹风比的增加,平均绝热冷却效率变大,当吹风比M>2.0后,绝热冷效不再随着吹风比的增加而进一步增大,存在最佳吹风比M=2.0;波长和波幅的变化对平均气膜冷却效率的影响很小,但是对对流换热系数有很大的影响,对流换热系数随着波长的增大而降低,随着波幅的增大而升高;此外,对流换热系数随吹风比的增大而升高,在气膜均匀覆盖后趋于定值。
Aiming at the cooling of the afterburner in aeroengine, the structure of the wind blowing ratio, wavelength and amplitude is calculated and analyzed by the CFD software with the high efficient cooling method combined transverse corrugated heat shield structure and all-film cooling. Cooling efficiency and hot side heat transfer coefficient. The results show that with the increase of blowing ratio, the average adiabatic cooling efficiency becomes larger. When the blowing ratio M> 2.0, the adiabatic cooling efficiency no longer increases with blowing ratio increasing, and the optimum blowing ratio M = 2.0. The changes of wavelength and amplitude have little effect on the average film cooling efficiency, but have a great influence on the convective heat transfer coefficient. The convection heat transfer coefficient decreases with the increase of the wavelength and increases with the increase of the amplitude ; In addition, the convective heat transfer coefficient increases with the blowing ratio increases, after the uniform coverage of the gas film tends to set value.