Research on the flow and heat transfer performance of variable geometry high-pressure turbine blade tip area of gas turbine

Abstract Carrying out the research of geometric turbine region flow and heat transfer research, and optimizing the configuration of the end zone is of great significance to improve turbine performance. In response to the complex second flow and heat transfer caused by the interval space of geometric turbine blades, this article starts from the perspective of reducing the pneumatic loss of the end zone and improving the heat transfer. The numerical method is used to study the adjustment of the turbine non-uniform import conditions, which can be adjusted. Studies have found that the configuration of the static leaf end zone weakens the cross-speed flow and leakage flow of the interval space of the rear end. At the same time, the coverage of the cooling gas on the wall surface of the end zone is also reduced. The separation of front side of the interval space is separated, and the average heat transfer coefficient of the wall surface is reduced, which has the best air thermal performance.