航空发动机燃烧室出口温度场数值模拟研究  

Numerical Simulation of Temperature Field at the Exit of Aeroengine Combustion Chamber

作　　者：郭青青[1] 李柳 GUO Qing-qing;LI Liu(Sanya Aviation and Tourism College,Sanya 572000,China;Shenyang Liming Aero-Engine(Group)Corporation Ltd.,Shenyang 110043,China)

机构地区：[1]三亚航空旅游职业学院,三亚572000 [2]中国航发沈阳黎明航空发动机有限责任公司,沈阳110043

出　　处：《价值工程》2023年第5期115-117,共3页Value Engineering

摘　　要：针对当前现有数值模拟方法在对航空发动机燃烧室出口温度场研究分析时,存在模拟结果精度低、时间成本高的问题,提出一种新的数值模拟方法。简化燃烧室结构,分析航空发动机燃烧室性能;引入温度场有限元法,构建温度场数学模型;通过fluent软件,实现对温度场的数值模拟;利用最小二乘方法,完成对温度场的重建。通过实验验证,新的数值模拟方法可以实现对燃烧室出口温度场更高精度的模拟,且模拟的时间成本能够得到有效控制。A new numerical simulation method is proposed to solve the problems of low accuracy and high time cost of the simulation results when the current numerical simulation methods are used to study and analyze the temperature field at the exit of the aeroengine combustion chamber.The combustion chamber structure is simplified and the performance of the aeroengine combustion chamber is analyzed.The finite element method of temperature field is introduced to build the mathematical model of temperature field.The numerical simulation of temperature field is realized by fluent software.The least square method is used to reconstruct the temperature field.The experimental results show that the new numerical simulation method can achieve more accurate simulation of the combustion chamber outlet temperature field,and the time cost of simulation can be effectively controlled.

关 键 词：航空发动机 燃烧室出口 温度场 数值模拟 

分 类 号：V231.2[航空宇航科学与技术—航空宇航推进理论与工程]