摘要
为了更好更快地计算喷管性能,采用特征线法加附面层修正的方式开发了一种二维喷管化学动力流场计算程序,针对某液氧甲烷发动机计算了不同设计参数对应的喷管流场,研究了不同设计参数对喷管效率的影响,设计参数包括推力、室压、喷管面积比和喷管出口角等。计算喷管效率时考虑了几何损失、附面层损失、化学动力损失。结果表明使用程序计算能够准确快速获得工程上重视的设计指标,大大提高了仿真效率,可用于喷管型面优化。
In order to better and faster calculate nozzle performance,a program for calculating the chemical dynamic flow field of two dimensional nozzles is developed by using the method of characteristic and boundary layer correction.The nozzle field corresponding to different for a liquid oxymethane engine,and the influence of different design parameters on nozzle efficiency are studied,the design parameters include thrust,chamber pressure,nozzle area ratio and nozzle outlet angle,etc.Geometric loss,boundary layer loss and chemical dynamic loss are considered in the calculation of nozzle efficiency.The results show that the program can obtain the number important for engineer quickly and accurately,improve the simulation efficiency greatly,and can be used to optimize the nozzle contour.
作者
刘阳旻
田原
LIU Yangmin;TIAN Yuan(Beijing Aerospace Propulsion Institute,Beijing,100076)
关键词
液氧甲烷发动机
数值仿真
喷管效率
特征线法
附面层修正
liquid oxygen methane engine
numerical simulation
nozzle efficiencies
method of characteristic
boundary layer correction
