高温涡轮叶片三种内冷通道冷却性能的实验研究

EXPERIMENTAL INVESTIGATION ON THE COOLING PERFORMANCE OF THREE GAS TURBINE BLADE INTERNAL PASSAGES

本文用实验方法研究了高温涡轮叶片三种内冷通道的压力分布、冷热态流阻及局部换热系数分布．叶片前部分别采用径向光滑通道、集中冲击冷却和分散冲击冷却三种结构，叶片后部则分别采用三排φ3扰流柱和五排φ2扰流柱稠密布置两种结构．对这三种结构进行了冷却性能比较，提出了该类冷却通道的最佳结构．

In this paper three gas turbine blade internal cooling passages were experimentallyinvestigated. The distributions of air flow pressure drop and heat transfer coefficient, flowresistance in three passages with or without heating were determined. The front of testturbine blades has three cooling madels, they are radial smooth passages, impinging coolingon lending edge and full impinging cooling in all blade front part, respectively. In therear of the blade cooling passages is wedged pin-finned channel, there is three pin-fin rowwith diameter 3mm or five pin-fin rows with diameter 2 mm, respectively. Comparingtheir thermal performance of three cooling models, the optimal cooling structure has beensuggested.