一体化加力燃烧室热态流场与特性数值研究  

Numerical study on combustion flow field and characteristics of integrated afterburner

作　　者：王治武[1] 李民强 李俊林 肖静涛 詹义民 龙好 WANG Zhiwu;LI Minqiang;LI Junlin;XIAO Jingtao;ZHAN Yimin;LONG Hao(School of Power and Energy,Northwestern Polytechnical University,Xi’an 710072,China)

机构地区：[1]西北工业大学动力与能源学院,陕西西安710072

出　　处：《推进技术》2024年第9期94-105,共12页Journal of Propulsion Technology

基　　金：国家自然科学基金(12372338);陕西省自然科学基金(2023-JC-YB-352,2022JZ-20);广东省基础与应用基础研究基金(2023A1515011663);西北工业大学硕士研究生实践创新能力培育基金(PF2023010)。

摘　　要：为满足新一代航空发动机的高推重比需求,提出一种支板与混合器一体化加力燃烧室方案,采用数值仿真方法,对比分析进口马赫数Ma (0.3~0.45),涵道比B (0.25~0.37)和不同飞行高度H(0~20 km)对加力燃烧室热态流场特性的影响。研究表明:在研究参数范围内,进口马赫数增大,壁式稳定器回流区及下游区域的燃气温度受到影响,区域内燃气温度逐渐升高,沿程径向温度不均匀性逐渐减小,总压损失增大,燃烧效率逐渐下降,但出口燃烧效率仍基本高于0.90;进口涵道比B增大,壁式稳定器下游及中心锥轴线位置的燃气温度开始下降,沿程燃气总压损失增大,燃烧效率随之升高,B从0.25增大至0.28时,燃烧效率提升较大,继续增大涵道比,燃烧效率提升较少;随着飞行高度升高,整体燃烧效率逐渐下降,在0 km和11 km飞行高度之间燃烧效率下降较少,而在20 km飞行高度时燃烧效率下降相对明显。In order to meet the high thrust-to-weight ratio requirements of the new generation of aero-engines,a scheme of integrated afterburner with strut and mixer was proposed.The numerical simulation method was used to compare and analyze the influence of inlet Mach number(0.3~0.45),bypass ratio(0.25~0.37)and different flight heights H(0~20 km)on the combustion flow field and characteristics of the afterburner.The results show that within the range of research parameters,as the inlet Mach number increases,the gas temperature in the recirculation zone and downstream area of the wall stabilizer is affected,the gas temperature in the region gradually increases,the radial temperature non-uniformity along the path gradually decreases,the total pressure loss increases,and the combustion efficiency gradually decreases,but the outlet combustion efficiency is still basically higher than 0.90.With the increase of the inlet bypass ratio,the gas temperature at the downstream of the wall stabilizer and the central cone axis begins to decrease,the total pressure loss of the gas along the path increases,and the combustion efficiency increases.When bypass ratio increases from 0.25 to 0.28,the combustion efficiency increases greatly,and continue to increase the bypass ratio,the combustion efficiency increases less.As the flight altitude increases,the overall combustion efficiency gradually decreases.The combustion efficiency decreases less between 0 km and 11 km flight altitudes,while it decreases significantly at 20 km flight altitude.

关 键 词：一体化加力燃烧室 热态流场 总压损失 燃烧效率 数值研究 

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]