液体火箭发动机铣槽推力室三维壁温分布计算

采用三维有限元模型对液体火箭发动机铣槽推力室进行了壁温分布计算。边界条件按一维经验公式处理。计算中比较了不同冷却剂流量。不同铣槽肋厚及肋数对温度分布的影响，并与一维简化肋模型的计算结果进行了比较，表明三维计算的温度分布规律更加合理。在小冷却剂流量、大肋厚情况下，周向温度分布不均也很严重。设计中对壁温进行三维分析是非常必要的。而对于高密肋，一维简化肋模型具有良好的近似性。

3-D WALL TEMPERATURE DISTRIBUTION OF CHAMBER WITH MILLED GROOVES IN LIQUID PROPELLANT ROCKET ENGINE

A calculation of the wall temperature distribution in liquid propellant rocket engine chamber with milled grooves was completed by the aid of three-dimensional finite element method.The boundary conditions are treated by one-dimensional empirical model and the wall temperature distributions under the influence of different cooling flow rates and grooves have been analyzed and compared with those obtained from 1-D model.It is shown that the 3-D temperature distribution is more reasonable.The circular temperature distribution is quite uneven under the conditions of small cooling flow rate and big grooves.It is very necessary to complete 3-D wall temperature distribution analysis in designing.