Coupled heat transfer characterisitcs of stepped cooling channel of liquid oxygen/methane rocket engine
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摘要: 为了研究液氧甲烷发动机再生冷却通道中跨临界甲烷的流动和传热特性,以及冷却通道较大幅度的突扩突缩对冷却效果的影响,采用整场直接耦合的方法对推力室三维耦合传热进行了数值模拟,考虑了燃气的非平衡流动.通过计算得到了推力室三维温度场和流场.计算结果表明:由于喉部截面附近存在较强的二次流,燃气侧壁面温度的最大值出现在喉部上游.由于突扩突缩处存在较强的旋涡运动,冷却剂的湍流强度增强,冷却剂侧表面传热系数显著提高,燃气侧壁面温度出现局部极小值,同时也产生了较大的局部损失.由于铜内衬热阻比镍外套热阻小得多,从燃烧室进入的大部分热量在冷却通道底面和侧面被冷却剂吸收.冷却通道底面的温度和热流密度沿程变化比顶面更剧烈.Abstract: To study the flow and heat transfer characteristics of transcritical methane in regenerative cooling channel of liquid oxygen/methane rocket engine, and acquire the influence of large-scale sudden expansion and sudden contraction of cooling channel on cooling effect, the three-dimensional coupled heat transfer of thrust chamber was simulated with the whole field direct coupling approach, and the flow of hot gas with non-equilibrium chemical reactions was considered in simulation. Through computation, the three-dimensional temperature field and flow field of thrust chamber were obtained. The computational results show that the maximum value of hot gas side wall temperature appears upstream the throat, because powerful secondary flow exists near the throat section. Due to strong vortices in sudden expansion and sudden contraction sections, the turbulence intensity of coolant is enhanced, the heat transfer coefficient of coolant side wall is significantly increased, the local minimum value of hot gas side wall temperature and large local loss are generated. Most of heat from combustor is absorbed by coolant on the bottom surface and side surface inside the cooling channel, because thermal resistance of copper liner is much smaller than that of nickel jacket. The axial variation of temperature and heat flux on bottom surface is more violent than that on top surface.
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