涡轮机壅塞式燃烧室燃烧数值仿真  

Numerical Simulation about Combustion Performance of Choked Combustor of Turbine

作　　者：乔宏 赵卫兵 马晓励 师海潮 

机构地区：[1]中国船舶重工集团第705研究所,陕西西安710075

出　　处：《鱼雷技术》2011年第1期48-54,共7页Torpedo Technology

摘　　要：为了研究涡轮机燃烧室的实现形式并通过仿真验证其工作性能,提出了一种既能实现三组元推进剂稳定燃烧,又能满足涡轮机在低工况时较低进气压力要求的新型壅塞式燃烧室方案,并基于计算燃烧动力学方法对该燃烧室方案的工作特性进行了数值仿真。仿真结果表明,在多种工况条件下,燃烧室三组元推进剂燃烧完全,三组元中的水完全蒸发,燃烧室流场分布合理,喷嘴环前压力满足涡轮机进气要求。该方案及仿真结果可供三组元推进剂涡轮机燃烧室工程研制参考。In order to study the form of turbine combustor and verify its performance,a new choked combustor scheme which is suitable for tri-propellant and matches the lower gas inlet pressure of a turbine under low operating condition was proposed.The combustion characteristics of scheme under multi-operating conditions were simulated based on computational combustion dynamics.Simulation results show that the tri-propellant burns completely,the water vapor-izes entirely,the flow field in the combustor is satisfactory,and the front pressure of the nozzle ring meets the require-ment of the turbo-pressure.This new choked combustor with its simulation results may benefit the design of turbine combustors with tri-propellant.

关 键 词：涡轮机 燃烧室 计算燃烧动力学 三组元推进剂 数值仿真 

分 类 号：TJ630.32[兵器科学与技术—武器系统与运用工程]