液体火箭发动机推力室复合冷却流动与传热研究

Flow and Heat Transfer Investigation on Compound Cooling of Liquid Rocket Engine Thrust Chamber

关键词:  液体火箭发动机  复合冷却  再生冷却  膜冷却  超临界  数值模拟

Key words:  Liquid rocket engine  Compound cooling  Regenerative cooling  Film cooling  Supercritical  Numerical simulation

摘要:

为了预测液体火箭发动机推力室的复合冷却性能，建立了推力室再生冷却通道和超临界氢的三维仿真模型以及推力室内燃气和超临界氢膜的轴对称二维仿真模型。通过边界耦合发展了液体火箭发动机推力室复合冷却流动与传热的数值仿真方法。对航天飞机主发动机推力室内部燃气、超临界冷却膜、室壁和再生冷却剂进行了流动与传热耦合计算仿真研究。研究表明，本文的仿真方法可较好地预测推力室燃气及再生冷却剂的流动和传热，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129MW/m2，最高壁温为885K，冷却剂温升为192K，压降为8.8MPa，结果与已有数据吻合较好。本文模型和仿真方法可用于液体火箭发动机推力室冷却系统传热计算和冷却结构的优化设计。

Abstract:

To predict the compound cooling performance of the liquid rocket engine thrust chamber, the three-dimensional simulation model of regenerative cooling channel and supercritical hydrogen and the axisymmetric two-dimensional simulation model of gas and supercritical hydrogen film in thrust chamber were established. A numerical simulation method of composite cooling flow and heat transfer in liquid rocket engine thrust chamber was developed by means of boundary coupling. The flow and heat transfer of gas, supercritical film, chamber wall and regenerated coolant of space shuttle main engine thrust chamber were coupling calculated by numerical simulation. Results show that the simulation method adopted in this paper can predict the flow and heat transfer of gas and coolant well, and the maximum heat flux on the gas side wall is 129MW/m2, the maximum wall temperature is 885K, the coolant temperature rise is 192K, and the pressure drop is 8.8mpa. The results are in good agreement with the existing data. The model and simulation method in this paper can be used to calculate the flow and heat transfer and optimize the cooling structure of the liquid rocket engine thrust chamber cooling system.