汽轮机调节级后过渡腔室的CFD数值研究

CFD Numerical Investigation of Turbine Governing Stage Rear Transition Chamber

汽轮机调节级进汽流具有非均匀性和非周期性,其计算较为复杂且对整个机组的运行效率有较大影响。基于此,以某超临界机组为例,对调节级、高压第一级及中间过渡腔室进行全周数值计算,并分析了汽轮机调节级后两种过渡腔室的气动性能,为提高机组运行效率奠定了基础。

Turbine governing stage has the characteristics of non-uniform and non-periodic,the calculation is complex and has a greater impact on the operating efficiency of the entire unit. Based on this,the full-scale numerical calculation of the governing stage,the first stage of high pressure and the intermediate transition chamber is carried out,taking a supercritical unit for example. The aerodynamic performance of two kinds of transition chamber after the turbine governing stage is also analyzed. It will lay the foundation to improve the operating efficiency of the unit.