[1]陈 坚,董清清,等.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[J].机械与电子,2024,42(06):3-9.
　CHEN Jian,DONG Qingqing,et al.Design of High Temperature Rise Combustor Based on Technology of Rich Burn / Quick Quench / Lean Burn[J].Machinery & Electronics,2024,42(06):3-9.
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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()
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《机械与电子》[ISSN:1001-2257/CN:52-1052/TH]

卷:
42
期数:
2024年06期
页码:
3-9
栏目:
研究与设计
出版日期:
2024-06-28

文章信息/Info

Title:
Design of High Temperature Rise Combustor Based on Technology of Rich Burn / Quick Quench / Lean Burn
文章编号:
1001-2257 ( 2024 ) 06-0003-07
作者:
陈 坚 1 ; 2 ; 董清清 1 ;  2 ; 薛九天 1 ; 2
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
Author(s):
CHEN Jian1 ;  2 ;  DONG Qingqing1 ;  2 ; XUE Jiutian1 ; 2
( 1.School of Aerospace Engineering , Guizhou Institute of Technology , Guiyang 550025 , China ; 2.Key Laboratory of Aero-engine Thermal Management and Intelligent Manufacturing in Higher Education Institutions of Guizhou Province , Guiyang 550025 , China )
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
Keywords:
aero-engine ;  high temperature rise combustor ;  RQL ;  aerodynamic design ;  structure design
分类号:
V231.3
文献标志码:
A
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。
Abstract:
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.

参考文献/References:

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备注/Memo

备注/Memo:
收稿日期: 2023-12-28
基金项目: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)
作者简介:陈 坚 ( 1984- ),男,贵州安顺人,副教授,研究方向为航空发动机喷雾燃烧、低排放燃烧技术。
更新日期/Last Update: 2024-07-01