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首页> 外文期刊>Advances in Mechanical Engineering >Numerical Analysis of Supersonic Film Cooling in Supersonic Flow in Hypersonic Inlet with Isolator
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Numerical Analysis of Supersonic Film Cooling in Supersonic Flow in Hypersonic Inlet with Isolator

机译：带隔离器的超音速入口超音速流中超音速薄膜冷却的数值分析

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摘要

Supersonic film cooling is an efficient method to cool the engine with extremely high heat load. In order to study supersonic film cooling in a real advanced engine, a two-dimensional model of the hypersonic inlet in a scramjet engine with supersonic film cooling in the isolator is built and validated through experimental data. The simulation results show that the cooling effect under different coolant injection angles does not show clear differences; a small injection angle can ensure both the cooling effect and good aerodynamic performances (e.g., flow coefficient) of the hypersonic inlet. Under selected coolant injection angle and inlet Mach number, the cooling efficiency increases along with the injection Mach number of the coolant flow, only causing a little total pressure loss in the isolator. Along with the increase of the inlet Mach number of the hypersonic inlet, the cooling efficiency does not present a monotonic change because of the complex shock waves. However, the wall temperature shows a monotonic increase when the inlet Mach number increases. The mass flow rate of coolant flow should be increased to cool the engine more efficiently according to the mass flow rate of the main stream when the inlet Mach number increases.
机译：超音速薄膜冷却是一种以极高的热负荷冷却发动机的有效方法。为了研究真正先进发动机中的超音速薄膜冷却，建立了超音速进气口的二维模型，该超音速进气口在隔离器中具有超音速薄膜冷却，并通过实验数据进行了验证。仿真结果表明，在不同的冷却液喷射角下，冷却效果没有明显的差异。小的喷射角可以确保高超声速进气口的冷却效果和良好的空气动力学性能（例如流量系数）。在选定的冷却剂喷射角和入口马赫数下，冷却效率随冷却剂流的喷射马赫数一起增加，仅在隔离器中造成很小的总压力损失。随着高超声速入口的入口马赫数的增加，由于复杂的冲击波，冷却效率不会呈现单调变化。但是，当入口马赫数增加时，壁温显示出单调增加。当入口马赫数增加时，应根据主流的质量流量增加冷却剂流量的质量流量，以更有效地冷却发动机。

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