某型F级轴向分级燃烧室的全温全压试验研究

Experimental Study of a Certain Type of F-class Axial Staged Combustion Chamber Under Full Temperature and Full Pressure

在全温全压条件下对自主研发的F级燃气轮机轴向分级燃烧室进行了燃烧试验研究,以探究设计点工况下燃烧室的压力损失、出口温度分布、火焰筒壁面温度、污染物排放、燃烧效率和热声稳定性等燃烧性能。结果表明:在设计点工况下,燃烧室总压损失系数为5.4%;燃烧室出口温度分布系数为0.06,燃烧室出口径向温度分布系数为0.03;燃烧室火焰筒壁面温度低于850℃;NO_(x)摩尔分数维持在1.9×10^(-5),CO和未燃碳氢(UHC)排放基本为0,燃烧效率维持在99.99%以上;压力脉动各特征频率对应幅值均低于3 kPa,表明燃烧室热声状态稳定。

The axial staged combustion chamber of the self-developed F-class gas turbine was studied under full temperature and full pressure condition.In order to explore the combustion performance of the combustion chamber under the working conditions of the design point,such as pressure loss,outlet temperature distribution,wall temperature,pollutant discharge,combustion efficiency and thermoacoustic stability,etc.Results show that,the total pressure loss coefficient of the combustion chamber is 5.4%at the design point.The outlet temperature distribution factor and radial temperature distribution factor are 0.06 and 0.03,respectively.And the wall temperature of the flame barrel in the combustion chamber is below 850℃.The mole fraction of NO_(x)is maintained 1.9×10^(-5),while the emissions of CO and unburned hydrocarbon(UHC)are basically zero.The combustion efficiency is maintained above 99.99%.The amplitude of dynamic pressure spectrum is below 3 kPa,which indicates the thermoacoustic state of the combustor is stable.