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燃气轮机一级静叶冷却结构非常复杂,要提高燃气轮机的设计水平,在现有的结构和设计的基础上,需要进行更加精细化的设计,需要对多种设计因素进行综合考虑,挖掘现有结构的冷却潜力。本文采用数值计算方法,研究了叶栅环境下,冲击衬套的使用对于一级静叶气膜孔流量分配和气膜冷却效率的影响。结果表明,冲击衬套会影响气膜孔的流量分配,而流量分配是传热的基础。同时,冲击腔会改善气膜孔内的流动,在流量不变的条件下提升气膜冷却效率。
Gas turbine first stage vane cooling structure is very complex, to improve the gas turbine design level, based on the existing structure and design, the need for more refined design, the need for a variety of design factors into consideration, mining the existing structure The cooling potential. In this paper, the numerical calculation method is used to study the influence of the use of impact bushing on the flow distribution and the film cooling efficiency of the first stage vane. The results show that the impact liner affects the flow distribution of the film holes, and the flow distribution is the basis of heat transfer. At the same time, the impact cavity will improve the flow in the film hole, and enhance the film cooling efficiency under the same flow rate.