Development of a new lean burning combustor with fuel film evaporation for a micro gas turbine
Development of a new lean burning combustor with fuel film evaporation for a micro gas turbine
复制标题
开发用于微型燃气轮机的具有燃料膜蒸发的新型贫燃燃烧器
DOI：
10.1016/s0894-1777(02)00239-x
复制
发表时间：
2003
影响因子：
3.2
通讯作者：
A. Schulz
中科院分区：
文献类型：
--
作者：
O. Liedtke;A. Schulz
介绍了一种用于微型燃气涡轮机的新型贫油预混预汽化燃烧器。由于所选择的热力循环条件引起的低压和低燃烧器入口温度，液体燃料在热表面上蒸发，因为压缩机空气温度对于燃料液滴喷雾的强烈蒸发来说太低。该概念基于热燃烧气体沿着蒸发器管的外表面的反向流动。管内表面上的液体燃料膜被从热燃烧气体通过管壁传递的热量蒸发。燃烧室壁是由陶瓷内衬、柔性层和金属外壳组成的多层组件。这种设计允许建立几乎绝热的燃烧。燃烧室的设计过程得到了等温流和反应流的全面数值研究的支持。燃烧器的涡流，提供火焰稳定，详细描述。已经进行了第一次实验测试。测量的废气污染物浓度符合国际标准，并证明了新燃烧室的巨大潜力。
The present paper describes a new burner for a micro gas turbine utilizing the lean premixed pre-vaporized combustion. Due to low pressure and low combustor inlet temperature, caused by the thermodynamic cycle conditions chosen, the liquid fuel is evaporated on a hot surface since compressor air temperature is too low for an intense evaporation of a fuel droplet spray. The concept is based on the reverse flow of hot combustion gases along the outer surface of an evaporator tube. The liquid fuel film on the inner surface of the tube is evaporated by heat transferred from the hot combustion gases through the tube wall. The combustor wall is a multi-layered assembly consisting of a ceramic inner liner, a compliant layer, and the outer metal casing. This design allows almost adiabatic combustion to be established. The design process of the combustor is supported by comprehensive numerical studies of the isothermal and reacting flow. The vortex flow of the burner, which provides for flame stabilization, is described in detail. First experimental tests have been conducted. Measured pollutant concentrations of the exhaust gases meet international standards and demonstrate the great potential of the new combustor.