起动机驱动过程中微型燃气轮机燃烧室变工况燃烧特性  

Off-design Combustion Performance Under Starter-Driven Process for a Micro-gas Turbine Combustor

作　　者：邢畅[1] 邱朋华[1] 刘栗[1] 王辉[1] 沈闻凯 吕亚锦 孙静怡 秦裕琨[1] XING Chang;QIU Penghua;LIU Li;WANG Hui;SHEN Wenkai;LV Yajin;SUN Jingyi;QIN Yukun(School of Energy Science and Engineering, Harbin Institute of Technology, Harbin 150001, Heilongjiang Province, China)

机构地区：[1]哈尔滨工业大学能源科学与工程学院

出　　处：《中国电机工程学报》2018年第8期2367-2375,共9页Proceedings of the CSEE

基　　金：国家科技支撑计划项目(2012BAA11B02);国家自然科学基金委创新研究群体项目(51421063)~~

摘　　要：针对起动机驱动过程,基于由单级离心压气机、贫预混旋流燃烧室、单级向心涡轮和空冷变频起动机/发电机组成的单轴微型燃气轮机样机,进行了整机实验研究,以获得燃烧室在该运行过程中的变工况燃烧特性变化趋势。研究表明：由于燃烧室内燃气温度较低,NO生成量近似为零,CO2排放浓度与燃烧效率随转速增加的变化趋势基本一致,而与CO排放浓度变化趋势正好相反。由于燃烧室出口平均温度主要受燃烧室进口空气温度、燃烧效率和当量比的影响,因此在起动机驱动过程中,燃烧室出口平均温度呈现与三者波动不一致的趋势。随着起动机转速增加,燃烧室总压恢复系数由于热阻损失和流动损失增加而减小。燃料化学反应过程不仅会影响压气机背压,并导致燃烧室进口空气温度和总压增大,而且会促使燃烧室进出口总压波动变大。燃烧室设计流阻系数在文中所涉及的运行参数和燃烧室无量纲结构参数条件下取值为35,可以满足燃烧室设计要求。In order to investigate the trends of off-design combustion performance under starter-driven process for a micro-gas turbine（MGT） combustor, the overall performance experiment of the MGT prototype was employed. The MGT prototype was designed on single shaft mode and includes a single stage centrifugal compressor, a lean premixed swirling combustor, a single stage centripetal turbine and an air-cooling frequency conversion starter/generator. The results indicate that： due to the relatively low temperature of the flue gas, NO formation is approximately zero. As the starter speed（n） increases, the trend of CO2 mass concentration is almost consistent with the combustion efficiency（η） trend, but opposite to that of CO mass concentration. The mean outlet temperature is mainly affected by inlet air temperature（T3）, ηand equivalence ratio, thus its fluctuation trend is different from these three under the starter-driven process. The total pressure recover factor of the combustor has a drop with the rising n due to the increasing thermal resistance and flow losses. The chemical reaction process of fuel can not only have an influence on the compressor back pressure, which leads to the rising T3 and inlet total pressure of the combustor, but also cause the obvious fluctuations in inlet and outlet total pressures of the combustor. Based on the operation conditions and non-dimensional structure sizes of the combustor in the current research, the flow resistance coefficient of 35 is satisfied for the design requirement of the combustor.

关 键 词：微型燃气轮机 贫预混旋流燃烧室 起动机驱动过程 变工况燃烧特性 天然气 

分 类 号：V231[航空宇航科学与技术—航空宇航推进理论与工程] TK477[动力工程及工程热物理—动力机械及工程]