2015/04/29 by Chao Zhou
Engineering · #Fluid Dynamics and Turbulent Flows #Heat Transfer Mechanisms #Turbomachinery Performance and Optimization
paper · doi:10.2514/1.b35392
openalex publication_date 2015/04/29 · openalex created_date 2025/10/10 · openalex updated_date 2026/07/28
Transonic high-pressure turbines are promising candidates for future aircraft engines. Recent studies in transonic turbine cascades showed that shock waves appeared over the uncooled flat tip, which affects its heat transfer. However, the effects of coolant injection on the thermal performance of transonic cooled tips are not clear. The current study aims to understand the thermal performance of a cooled flat tip and a cooled cavity tip in a transonic turbine cascade. The effects of tip film cooling are studied at five coolant pressure ratios (which are the stagnation pressure ratios of the coolant inlet and the cascade inlet) from 0.8 to 1.2. The flow physics over the tip, the heat transfer coefficient, the film-cooling effectiveness, and the heat flux of the tip are investigated. The effects of relative endwall motion are considered.