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对液体火箭发动机燃烧室液膜-再生复合冷却进行了数值计算,针对液膜-燃气流场区多组分、轴对称Navier-Stokes(N-S)方程和再生冷却区单组分N-S方程进行求解,并使用k-ε方程求解湍流流动.对文献中的某液氧/煤油火箭发动机燃烧室进行了数值模拟,该模型的计算结果能够与文献中的计算结果较好地吻合.计算结果表明:①液膜-再生复合冷却能有效地减少壁面热流密度和降低壁面温度,且其形成的冷气边区覆盖了整个燃烧室及喷管壁面;②再生冷却液入口质量流量越大,复合冷却作用越明显,壁面温度越低;③随再生冷却液质量流量的不同其温升在450～600K之间,且质量流量越大,再生冷却液的温升越小.④壁面煤油的质量分数不断下降,在喷管出口壁面处达到最低值,但含有煤油的区域不断变大.
The liquid film-reclaimed composite cooling of a liquid rocket engine combustor is numerically calculated. The multi-component, axial symmetric Navier-Stokes (NS) equations and single-component NS equations in the regenerative cooling zone are solved for the liquid film- And the k-ε equation is used to solve the turbulent flow. Numerical simulations of a liquid oxygen / kerosene rocket engine combustor in the literature are carried out and the results of the model are in good agreement with those in the literature. The calculation results show that: ① Liquid film-reclaimed composite cooling can effectively reduce the wall heat flux density and reduce the wall temperature, and the formation of the air-conditioning marginal zone covers the entire combustion chamber and nozzle wall; ② regenerative coolant inlet mass flow rate, the more obvious cooling effect, The lower the temperature of the wall surface; (3) the temperature rise with the mass flow of regenerative coolant between 450 ~ 600K, and the greater the mass flow, the smaller the temperature rise of the regenerative coolant. (4) The mass fraction of kerosene on the wall continues to decline, The pipe exit wall surface reached the lowest value, but the area containing kerosene is getting larger.