摘要
设计了一种以天然气为燃料的微型燃气轮机燃烧室,并对燃烧室的燃烧性能进行了试验测试。所设计的燃烧室为单级旋流器+主燃孔的折流式单管燃烧室,采用L型燃气导管实现气流在燃烧室内的180°转角;燃料喷嘴为多孔式,2排孔的喷射角度分别为120°和90°;通过掺混孔和燃气导管冷却孔相互配合的方式来满足燃烧室出口温度场的要求。测试结果表明:在设计点燃烧室的冷、热态压力恢复系数分别为0.955、0.940;点火燃空比为0.005~0.007,具有较好的点火特性;对贫油熄火特性影响较大的因素是燃烧室入口温度,当大气温度由?30 ℃升至30 ℃时,贫油熄火燃空比由0.002 6降低至0.002 3;排放及燃烧效率未能达到要求,尤其是CO排放较高,体积分数达到300×10–6;燃烧室出口温度分布的热点指标低于0.15,满足要求,但空气流量分配不合理导致火焰筒局部温度过高。
A micro gas turbine combustor using natural gas as fuel was designed, and its combustion characteristics were tested. The combustor is baffled type single-tube combustion chamber with single stage swirler + primary combustion hole. The gas flow in the combustor can realize a 180° turn by applying an L-type gas conduit. The fuel nozzle is a porous type, and the injection angle of the two rows of holes is 120° and 90°. The requirements of temperature field at outlet of the combustion chamber can be satisfied by the mutual cooperation between the mixing holes and gas conduit cooling holes. The test results show that, the pressure recovery coefficient was 0.955 and 0.940 for cool and heat condition, respectively. Better ignition characteristics can be obtained when the ignition fuel/air ratio was 0.005~0.007. The main factor affecting the lean burnout characteristics was the combustor entrance temperature, the lean blowout fuel/air ratio decreased from 0.002 6 to0.002 3 when the atmospheric temperature increased from-30 ℃ to 30 ℃. The emission and combustion efficiency failed to meet the requirements, especially the CO emission volume concentration reached 300×10^-6,which was high. The pattern factor of the temperature distribution at the outlet of the combustion chamber was below 0.15, which met the requirements, but the unreasonable air flow distribution caused local high temperature on the flame tube.
作者
刘爱虢
陈思
李昱泽
翁一武
曾文
刘凯
LIU Aiguo;CHEN Si;LI Yuze;WENG Yiwu;ZENG Wen;LIU Kai(Liaoning Key Laboratory of Advanced Testing Technology for Aeronautical Propulsion System, Shenyang Aerospace University, Shenyang 110136, China;School of Mechanical and Power Engineering, Shanghai Jiao Tong University, Shanghai 200240, China)
出处
《热力发电》
CAS
北大核心
2019年第6期71-78,共8页
Thermal Power Generation
基金
航空科学基金(20170354001)
辽宁省自然科学基金(20180550358)~~
关键词
微型燃气轮机
燃烧室
排放特性
试验测试
热点指标
燃烧效率
micro-gas turbine
combustor
emission characteristics
test
pattern factor
combustion efficiency
