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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 three-dimensional modeling design program for the transition section of a heavy gas turbine combustor was developed. The geometric appearance was determined by three main elements: the change function of the inlet and outlet profiles, the position function of the center profile, and the inclination angle variation function along the cross section of the gas turbine. The program is concise and effective, which can realize the recurrence of the complex exterior structure in the transition section of a F-class combustion engine combustion chamber, and can meet the needs of a large range of transitional section shapes in engineering applications. Two transitions with different appearance styles are designed by the program Section, combined with a combustion chamber flame tube, cold flow numerical simulation. The results show that the shape of the transitional section has little effect on the flow in the flame tube, and the flow performance is similar in the transitional section. The flow field is reasonable and there is no significant flow loss. It shows that the transitional section modeling method is practicable. Combustion chamber design provides a reference.