高温升多旋流燃烧室的数值分析  

Numerical Analysis of High Temperature Rise Combustor with a Multi-swirler

作　　者：罗卫东[1] 李锋[1] 高贤智 高伟伟[1] 

机构地区：[1]北京航空航天大学能源与动力工程学院,北京100191 [2]上海电气燃气轮机有限公司,上海200240

出　　处：《航空发动机》2015年第2期17-21,共5页Aeroengine

基　　金：国家自然科学基金(50476005)资助

摘　　要：为了探索高推重比航空发动机可能用到的燃烧组织方式,基于燃烧室空气分级技术,对高温升多旋流燃烧室展开研究。在保证与某型单环腔燃烧室(SAC)扩压器尺寸、外机匣最大直径及燃烧室出口尺寸和边界条件等相同的基础上,对设计模型进行3维数值模拟,并与现有的单环腔燃烧室数值模拟结果和试验结果进行对比分析。研究结果表明:在设计油气比为0.037的情况下,采用多旋流的设计方案,温升达到1153 K,出口温度分布系数达到0.170,同时可获得理想的性能参数,满足高温升燃烧室的设计指标。In order to explore the possible combustion method of high thrust-to-weight ratio aeroengine,the high temperature rise combustor with the use of a multi-swirler was investigated based on the combustion chamber air classification technology. A three- dimensional numerical simulation on the design model was conducted on the basis of insuring the same diffuser size, the same biggest diameter of the outer casing and the combustion chamber, the same boundary conditions with those of a certain existing type of single annular combustor （SAC）, and compared with the existing SAC through the results of numerical simulation. The results demonstrated that the temperature rise reaches 1153 K, the pattern factor reaches 0.170, meet the desired performance parameters and satisfied the high temperature rise combustor design requirement under the condition of fuel and air ratio is 0.037.

关 键 词：高温升 多旋流燃烧室 空气分级 多级旋流器 数值模拟 航空发动机 

分 类 号：V231.12[航空宇航科学与技术—航空宇航推进理论与工程]