基于富油燃烧/快速淬熄/贫油燃烧技术的高温升燃烧室设计  

Design of High Temperature Rise Combustor Based on Technology of Rich-Burn/Quick-Quench/Lean-Burn

作　　者：陈坚 董清清 薛九天 CHEN Jian;DONG Qingqing;XUE Jiutian(School of Aerospace Engineering,Guizhou Institute of Technology,Guiyang 550025,China;Key Laboratory of Aero engine Thermal Management and Intelligent Manufacturing in Higher Education Institutions of Guizhou Province,Guiyang 550025,China)

机构地区：[1]贵州理工学院航空航天工程学院,贵州贵阳550025 [2]贵州省高等学校航空发动机热管理与智能制造重点实验室,贵州贵阳550025

出　　处：《机械与电子》2024年第6期3-9,共7页Machinery & Electronics

基　　金：国家自然科学基金资助项目(52166006);贵州省科学技术基金(黔科合基础ZK[2021]一般279);贵州省教育厅高等学校科学研究项目(黔教技[2022]268号)。

摘　　要：随着现代燃烧室不断向高温升及低排放方向发展,传统的燃烧组织方法已经不足以满足日益发展的燃烧室设计要求。为此,将RQL燃烧技术运用到高温升燃烧室设计中,首先依据给定的基本设计参数,完成了基于RQL燃烧技术的高温升燃烧室气动方案设计,获得合理的流量分配方案。随后在后续试验要求基础上,完成包括燃烧室主体、头部进气段、射流孔进气腔体、射流孔板、距离调节模块和排气段等各部件的结构方案设计。最后采用数值仿真的方法对燃烧室设计方案进行了验证,仿真结果表明,当量比的沿程变化基本在设计指标范围内,燃烧室的设计方案符合要求。With the continuous development of modern combustor towards high temperature rise and low emissions,traditional combustion organizations are no longer sufficient to meet the increasingly evolving requirements of combustor design.RQL technology is applied to design of high temperature rise combustor.Firstly,based on the given basic design parameters,the aerodynamic scheme design of the high temperature rise combustor based on RQL was completed,and a reasonable flow distribution scheme was obtained.Then,based on the requirements of subsequent experiments,the structural design of various components including the combustor main body,head intake section,jet holes intake chamber,jets orifice plate,distance adjustment module,exhaust section,etc.were completed.Finally,simulation was used to validate the combustor design scheme.The simulation results showed that the variation of equivalence ratio along the combustor was basically within the design index range,and the design scheme meet the requirements.

关 键 词：航空发动机 高温升燃烧室 RQL技术 气动设计 结构设计 

分 类 号：V231.3[航空宇航科学与技术—航空宇航推进理论与工程]