基于环形燃烧室结构的燃气发生器设计与仿真  

Design and Numerical Simulation of Gas Generator Based on Annular Combustor Structure

作　　者：赵芳 史煜[2] 王海锋[1,2] 任泽斌[1,2] 李先锋[2] 罗智锋 ZHAO Fang;SHI Yu;WANG Haifeng;REN Zebin;LI Xianfeng;LUO Zhifeng(State Key Laboratory of Aerodynamics,China Aerodynamics Research and Development Center,Mianyang 621000,China;Facility Design and Instrumentation Institute,China Aerodynamics Research&Development Center,Mianyang 621000,China;Aecc Sichuan Gas Turbine Research Establishment,Mianyang 621000,China)

机构地区：[1]中国空气动力研究与发展中心空气动力学国家重点实验室,四川绵阳621000 [2]中国空气动力研究与发展中心设备设计与测试技术研究所,四川绵阳621000 [3]中国航发四川燃气涡轮研究院,四川绵阳621000

出　　处：《现代防御技术》2023年第5期126-133,共8页Modern Defence Technology

基　　金：国家高技术研究发展计划。

摘　　要：为有效解决高能化学激光器压力恢复系统无法实现小型化及机动性能等问题,提出了以高温气源替代常温空气作为引射气源的方案,并设计了一种基于航空发动机环形燃烧室结构的空气/酒精燃气发生器。采用CFD计算软件开展了燃气发生器的流场仿真计算,获取了燃气发生器冷态及燃烧工况下的速度、压力与温度场,并将部分仿真计算结果与理论计算及试验值进行了对比。研究表明:燃气发生器设计合理,扩压器及二股腔道转接处无气流分离,帽罩处无溢流现象;主燃区回流区明显,且尺度适中,有利于组织燃烧,并有效指导了高能电火装置的位置布局;空气流量配比合理,主燃孔及掺混孔的射流深度满足燃烧及掺混要求;燃烧室总压恢复系数达到96.7%,燃烧效率实现98.4%,实现了高效燃烧;此外,相同工况下的理论计算值及试验结果验证了数值计算方法的合理可行性。A scheme of employing high-temperature gas source instead of normal-temperature air as the ejection gas source is proposed,and an air/alcohol gas generator based on aeroengine annular combustor structure is designed to meet the miniaturization and maneuverability of a high-energy chemical laser pressure recovery system.Meanwhile,CFD software is adopted to simulate the flow field of gas generator,and obtain the velocity,pressure,and temperature fields of gas generator in cold and combustion conditions.Some simulation results are compared with theoretical calculation and experimental values.The research shows that the design of the gas generator is reasonable,and there is no air flow separation at the diffuser and the junction of the two-channel cavity,without overflow at the cap.The recirculating zone of the main combustion zone is obvious with moderate scale,which is conducive to combustion organization and guides the location layout of high-energy electric fire devices.The air flow ratio is reasonable,and the jet depth of the main combustion hole and mixing hole meets the combustion and mixing requirements.The total pressure recovery coefficient of the combustion combustor reaches 96.7%with the combustion efficiency of 98.4%,which realizes efficient combustion.Additionally,the theoretical calculated values and experimental results in the same working conditions verify the rationality and feasibility of the numerical simulation method.

关 键 词：压力恢复系统 引射气源 航空发动机 环形燃烧室 燃气发生器 

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] TK223.2[动力工程及工程热物理—动力机械及工程] TP391.9[自动化与计算机技术—计算机应用技术]