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以圆直管中的超声速高温燃气为主流,以常温氮气为气膜介质,用实验的方法研究了离散孔超声速气膜冷却规律,主流马赫数为2,射流马赫数分别为1,2,3.结果表明:射流流量是影响离散孔气膜冷却效果的最主要因素,提高吹风比或者增大孔径,都能显著提高气膜冷却效率;在实验工况下,冷却效率与吹风比和孔径的关系可以总结成实验关联式;射流喉部直径相同、流量相同情况下,射流马赫数对气膜冷却效果影响不大;在气膜孔附近,入射角为30°的射流比切向入射时的冷却效果差,在下流远离气膜孔位置,入射角为30°的射流冷却效果优于切向入射时.
In the straight tube of supersonic high temperature gas as the mainstream, at room temperature nitrogen as the gas film media, experimental study of the discrete hole ultrasonic film cooling law, the mainstream Mach number is 2, the jet Mach number were 1,2,3 The results show that the jet flow rate is the most important factor that affects the film cooling effect of discrete holes, and the air film cooling efficiency can be significantly improved by increasing the air blowing ratio or increasing the aperture. Under the experimental conditions, the cooling efficiency is proportional to the air blowing ratio The relation can be summed up as experimental correlation; when the jet laryngeal diameter is the same and the flow rate is the same, the jet Mach number has little effect on the film cooling effect. In the vicinity of the film hole, the jet with the incident angle of 30 ° The cooling effect is poor, downstream from the film hole position, the incident angle of 30 ° jet cooling effect is better than the tangential incidence.