重型燃气轮机燃烧室过渡段气动造型设计及性能分析

Investigation of Transition Piece Structure Design and Aerodynamic Performance in Heavy Duty Gas Turbine Combustors

开发了一套重型燃气轮机燃烧室过渡段三维造型设计程序,通过3个主要元素确定几何外型:分别为进出口型面变化函数、中心型线位置函数、沿程截面的倾斜角变化函数;造型程序简洁有效,可实现某F级燃机燃烧室过渡段复杂外型结构的复现,能够满足工程应用中较大范围的过渡段型面造型;利用该程序设计出2种外形风格不同的过渡段,结合某型燃烧室火焰筒,进行冷态流场数值模拟。结果显示过渡段外形变化对火焰筒内流动影响较小,过渡段内流动性能相似,流场合理、未出现明显流动损失现象,表明过渡段造型方法切实可行,流动性能研究为该类重型燃机燃烧室设计提供了一定的参考作用。

A design code was developed aiming at facilitating the 3-D geometric modeling process of a transition piece （TP） for can-type heavy duty gas turbine combustors. Three design parameters were introduced to fully define the spatial profile of the TP. The first parameter was applied to control the cross section transition from circle inlet to annulus-sector outlet, the second parameter was used to define the center line profile, and the last one was used to control the gradient of each section. This code has been proved being able to neatly and effectively reproduce the TP of an F-Class combustor and other shapes of transition pieces. For demonstration purpose, two sorts of transition pieces were designed by this code, and simulations were conducted combined with the same gas combustion liner. The results indicate that the difference of the TP has minor influence on the flow of combustor liner. The flow of the two cases is reasonable, without illogical total pressure loss. It is concluded that the design method is feasible and numerical simulation provides the guidance in designing of TP for heavy duty gas turbine combustors.