液体火箭发动机推力室冷却通道流动与传热数值研究

Numerical investigation of heat transfer and fluid flow in cooling channel of H_2/O_2 liquid rocket engine thrust chamber

采用气固耦合算法对液体火箭发动机推力室再生冷却通道的流动与传热过程进行了三维湍流流动与传热数值模拟,冷却工质为氢气,其密度、导热系数、动力粘度随着温度和压力而变化。应用大涡模拟及标准k-ε双方程模型两种湍流模型分别进行数值模拟,详细揭示了再生冷却通道固体区和流体区内的速度场和温度场,并在不同的计算网格数目下对两种湍流模型的计算结果进行了对比。结果表明,在相同的网格条件下,标准k-ε双方程模型与实验数据的吻合精度比大涡模拟模型更好,且满足工程计算精度。随着网格数的增加,大涡模拟的计算精度逐渐得到改善。

Turbulent fluid flow and heat transfer in a regenerative-cooling channel of H2/O2 liquid rocket engine were numerically investigated by solving three-dimensional elliptical Navier-Stokes equations and the gas-solid coupled arithmetic was adopted. The coolant was hydrogen, whose thermal properties such as thermal conductivity, density, dynamical viscidity, etc were varied with both temperature and pressure. Large Eddy Simulation and standard k-ε turbulent model were used to simulate temperature and velocity distribution in fluid and solid region of regenerative-cooling channel. The simulation results of two turbulent models were compared with experiment data at different calculation grids. It is shown that under the same grids, the result obtained by standard k-ε turbulent model agrees better with the experimental data than that by Large Eddy Simulation （LES） , which is also satisfied with engineering precision. With the increase of calculation grids, the calculation precision of LES is gradually enhanced.