推力室槽道式冷却通道尺寸优化设计方法

OPTIMAL DESIGN METHOD FOR CHANNEL SIZE OF THRUST CHAMBER COOLING PASSAGE

新一代液氧 /烃类推进剂液体火箭发动机将采用高燃烧室压力方案 ,这时推力室冷却成为一项关键技术问题。本文构造了一个槽道式再生冷却通道几何尺寸的优化设计方法 ,其优化目标是使通过冷却通道的冷却剂的压力损失最小。典型的计算、实验表明 ,采用优化设计方法可使冷却压力损失减少 50 % ,即采用优化设计有利于高室压推力室冷却问题的解决。

High combustion chamber pressure engine scheme is to be used in new generation of liquid rocket engine with propellant LOX/hydrocarbon.For this kind of engine thrust chamber cooling is one of key technical problems.An optimal design method for geometric size of regenerative cooling channel is provided.The minimum of cooling pressure loss has been taken as an optimal objective.The results of a typical calculation show t hat the cooling pressure loss may be decreased 50% by using the optimal method.