某重型燃气轮机燃烧室的性能试验与调试

Performance Test and Debugging of Combustor of Heavy-duty Gas Turbine

在中国一航涡轮院高压试验台上,对中国第一台具有自主知识产权的某重型燃气轮机(E级)燃烧室进行了燃用天然气的性能试验与调试,着重于燃烧室出口温度场试验与调试以及污染物排放含量试验.结果表明:设计工况下燃烧室出口周向温度分布系数为0.30,径向温度分布系数为0.13,排放污染物含量(NOx)为204 mg/m3,这些指标均超出设计要求.通过调整火焰筒掺混孔尺寸,增加预混燃烧比例,使周向温度分布系数降为0.20,达到设计要求,并使径向温度分布系数降为0.10,接近设计要求.此外,还从理论上分析了燃烧室排放超标的原因及改进方向.

The performance test and debugging of combustor of heavy-duty gas turbine （E） firing with the natural gas with the first independent intellectual property rights has been finished on high-pressure test system in Gas Turbine Institute of China Aviation Industry Corporation 1. It was focused on the test and debugging of outlet temperature field of combustor and the content of pollution emissions. Results show that, axial outlet temperature distribution coefficient of eombustor is 0.30, radial temperature distribution coefficient is 0.13, the content of pollution emissions （NOx） is 204 mg/m^3 under the design condition. All of the data exceed the design values. By adjusting the mix-holes size of chamber and increasing the fuel proportion of premixed combustion, the axial temperature distribution coefficient decreases to 0.20, which meets the design requirement; the radial temperature distribution coefficient decreases to 0. 10, which approaches to the design requirement. The reasons of NOx excessive emission and the directions to improve have Been also theoretically analyzed.