633 / 2019-03-05 15:28:07

Design and Research on Labyrinth internal Cooling Structure of Nozzle guide vane

blade cooling, gas thermal coupling, labyrinth cooling, numerical simulation

全体主题 > 涡轮机

The main work of this paper is to design the cooling structure of this stage for a gas turbine. The characteristics of the flow field around the blade are discussed by means of the coupled thermal and thermal numerical simulation method, Based on the results of CFD calculation, the characteristics of heat transfer between blade and gas are discussed. In contrast to the original model and the new model, different cooling flow schemes are designed, and several contrast schemes are also designed. The results show that the maze cooling structure than the original model of cooling structure has a better cooling effect and cooling flow, impingement cooling and convective heat transfer coefficient increases with the increase of heat transfer rate becomes larger, the effect is better.