液体火箭发动机推力室再生冷却流动与传热计算研究

Calculation Study on Flow and Heat Transfer of Regenerative Cooling in Liquid Rocket Engine Thrust Chamber

关键词:  液体火箭发动机  再生冷却  准二维模型  三维模型  数值模拟

Key words:  Liquid rocket engine  Regenerative cooling  Quasi two-dimensional model  Three-dimensional model  Numerical simulation

摘要:

为了研究液体火箭发动机推力室再生冷却流动与传热的快速仿真方法，建立了推力室再生冷却的准二维模型，对航天飞机主发动机开展了再生冷却流动与传热计算仿真研究，对比分析了再生冷却准二维模型和三维模型的仿真计算结果。研究表明，两种计算模型均可较好地预测推力室燃气及再生冷却剂的流动和传热。三维模型计算精度高，但计算用时较长。计算得到的航天飞机主发动机的燃气侧壁面最高热流密度为162.2MW/m²，最高壁温为1159.7K，冷却剂温升为244.0K，压降为8.5MPa。准二维模型计算结果精度略有降低，但计算时间较三维模型减小了90%。四个参数与三维模型计算结果的差异分别为0.3%，4.4%，8.6%和4.5%，在可接受范围内。本文的准二维模型计算时间短，适用于液体火箭发动机再生冷却结构的方案筛选和优化设计，三维模型计算精度高，适用于设计完成后的校核计算。

Abstract:

To study the rapid simulation method of the regenerative cooling flow and heat transfer of the liquid rocket engine thrust chamber， a quasi-two-dimensional model of the regenerative cooling in thrust chamber was established. A numerical simulation of the regenerative cooling flow and heat transfer in the space shuttle main engine was carried out. The results of regenerative cooling quasi-two-dimensional model and three-dimensional model were compared and analyzed. Research shows that both the two calculation models can predict the flow and heat transfer of gas and regenerative coolant in the thrust chamber. Three-dimensional model numerical simulation has higher accuracy but takes more time， and the maximum heat flux on gas side wall is 162.2MW/m²， the maximum wall temperature is 1159.7K， the coolant temperature rise is 244.0K， and the pressure drop is 8.5MPa. The accuracy of the results of quasi-two-dimensional model is slightly reduced， but the calculation time is reduced by 90% compared with that of three-dimensional model. The differences of the four parameters from the calculation results of the three-dimensional model are 0.3%， 4.4%， 8.6% and 4.5%， which are within the acceptable range. The quasi-two-dimensional model in this paper takes less calculation time and is more suitable for the project selection and the optimal design of the regenerative cooling structure of the liquid rocket engine. The three-dimensional model has higher calculation accuracy and is more suitable for the verification calculation after the design.