航空发动机燃烧室设计研发体系  

Design and Development System of Aeroengine Combustor

作　　者：索建秦[1] 梁红侠[1] 黎明[1] 金如山[1] SUO Jian-qin;LIANG Hong-xia;LI Ming;JIN Ru-shan(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,西安710072

出　　处：《航空发动机》2021年第3期29-34,共6页Aeroengine

基　　金：国家科技重大专项(2017-III-0002-0026)资助。

摘　　要：针对国内设计体系建设和完善的迫切需要,提出了航空发动机燃烧室全寿命周期的设计研发体系。将燃烧室设计研发分为5个阶段:概念性预先研究阶段、方案论证选择阶段、技术研发阶段、发动机型号研发阶段和售后服务及改进阶段。叙述了每个阶段的主要任务,说明了燃烧室研发特点,尤其是强调燃烧室研发要以试验研究工作为主,仿真无法替代试验。对比分析了先进燃烧室与传统燃烧室在设计和研发上的差异,最显著的是燃烧组织不同,导致燃烧试验方面的不同,尤其要重视单头部单管燃烧室试验研发。In view of the urgent need of the domestic design system construction and perfection,the whole life cycle design and development system of aeroengine combustor was put forward.The design and development of combustion chamber were divided into five stages:conceptional preliminary research,determination of design configuration,technology development,engine combustor development,post-sales service and improvements.The main tasks of each stage were described and the characteristics of combustor development were explained,especially the combustor development should be based on test research,and simulation could not replace the test.The difference between the advanced combustor and the traditional combustor was compared and analyzed.The most significant difference was that the combustion structure was different,which led to the difference of combustion test,especially the development of single flame tube combustor should be paid more attention to.

关 键 词：燃烧室 航空发动机 燃气轮机 设计体系 研发体系 

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]