作者：刘威, 王成军, 于雷, 郑顺, 曾文

作者单位：沈阳航空航天大学航空发动机学院, 辽宁 沈阳 110136

关键词：中心分级燃烧室;值班级;主燃级;油气比;旋流器;燃烧性能

摘要：

针对中心分级燃烧室在常压下燃烧性能，分别进行不同进气温度、进气速度和油气比对值班级单独工作以及值班级与主燃级共同工作时的燃烧性能试验，获得在一定实验条件下的燃烧规律。试验结果表明：值班级单独工作时随着进气温度、进气速度增加，点火特性更好；值班级与主燃级同时工作时，进气速度的增加对燃烧的影响不大；当进气温度增加时对燃烧较好；随着油气比的增加，CO和UHC排放有所增加，出口温度增加。

Experimental investigation on combustion performance ofcentrally-staged combustor
LIU Wei, WANG Chengjun, YU Lei, ZHENG Shun, ZENG Wen
School of Aero-engine, Shenyang Aerospace University, Shenyang 110136, China
Abstract: For the combustion performance of centrally-staged combustor under normal pressure, the combustion performance experiments are performed separately in different inlet airflow temperature, inlet airflow velocity and fuel-air-ratio when pilot stage works independently and when pilot stage and primary stage work simultaneously. The combustion rule under certain experimental conditions is obtained. The experiment results show that the ignition characteristics are better with the increase of inlet airflow temperature and inlet airflow velocity when pilot stage works alone. When pilot stage works simultaneously with primary stage, the increase of the inlet airflow velocity has little effect on the combustion; the combustion is better when the inlet airflow temperature increases; the CO and UHC emissions and exit temperature increase with the increase of fuel-air-ratio.
Keywords: centrally-staged combustor;pilot stage;primary stage;fuel-air-ratio;swirler;combustion performance
2019, 45(9):149-155  收稿日期: 2018-11-07;收到修改稿日期: 2019-03-05
基金项目: 国家自然科学基金（51476106）
作者简介: 刘威(1993-),男,辽宁葫芦岛市人,硕士研究生,专业方向为航空发动机燃烧技术
参考文献
[1] BAHR D W. Technology for the design of high temperature rise combustors[J]. Journal of Propulsion and Power, 1985, 3(2):179-186.
[2] 林宇震, 许全宏, 刘高恩. 燃气轮机燃烧室[M]. 北京:国防工业出版社, 2008.
[3] 金如山. 航空燃气轮机燃烧室[M].北京:宇航出版社, 1988.
[4] MONGIA H C. Engineering aspects of complex gas turbine combustion mixers:Part I high ∆T[C]//49th AIAA Aerospace Sciences Meeting including the New Horizons Forum and Aerospace Exposition, 2011.
[5] EL-KADY A M, JENG S M, MONGIAB H C. Experimental investigation of temperature and species concentration characteristics of swirling spray combustion[C]//43rd AIAA Aerospace Sciences Meeting and Exhibit, 2005.
[6] MANSOUR A, BENJAMⅡN M. A new hybrid air blast nozzle for advanced gas turbine combustor[C]//ASME Turbo Expo 2000:Power for Land, Sea, and Air, 2000.
[7] 彭云晖, 林宇震, 许全宏, 等. 双旋流空气雾化喷嘴喷、流动和燃烧性[J]. 航空学报, 2008, 29(1):1-14
[8] 焦树建. 径向旋流器的设计方法及其燃烧特性[J]. 燃气轮机技术, 1994, 12(4):33-42
[9] DING G Y, HE X M, ZHAO Z Q, et al. Effect of dilution holes on the performance of a triple swirler combustor[J]. Chinese Journal of Aeronautics, 2014, 26(6):1421-1429
[10] 丁国玉, 何小民, 赵自强, 等. 三级轴向旋流器影响燃烧室性能的试验[J]. 航空动力学报, 2015, 30(3):686-693
[11] 张中飞, 王成军, 佟飞, 等. 旋流器结构对中心分级燃烧室贫油熄火影响数值模拟[J]. 热力发电, 2018, 47(4):70-78
[12] 王成军, 佟飞, 陈科华, 等. 高温升燃烧室贫油熄火特性数值研究[J]. 燃气涡轮试验与研究, 2016, 29(2):1-6
[13] 付忠广, 王瑞欣, 石黎, 等. 旋流器通道宽度对旋流预混燃烧特性影响数值模拟[J]. 热力发电, 2018, 47(2):63-70
[14] 肖俊峰, 王峰, 高松, 等. 进气压力对燃气轮机预混燃烧稳定性影响[J]. 热力发电, 2018, 47(4):86-91
[15] 袁怡祥, 林宇震, 刘高恩. 三旋流器头部燃烧室拓宽燃烧稳定工作范围的研究[J]. 航空动力学报, 2004, 19(1):142-147
[16] 林宇震, 刘高恩, 王华芳. 反向与同向双旋流器流场的试验研究[J]. 航空动力学报, 1995, 10(4):108-110
[17] 吴治永, 林宇震, 刘高恩, 等. 基于CFD分析改进三旋流燃烧室头部设计[J]. 推进技术, 2009, 30(5):533-537
[18] 丁国玉, 何小民, 赵自强, 等. 油气及进口参数对三级旋流器燃烧室性能的影响[J]. 航空动力学报, 2015, 30(1):53-58
[19] 李锋, 程明, 尚守堂, 等. 双环预混旋流与单双环腔燃烧室性能对比[J]. 航空动力学报, 2012, 27(8):1681-1687