Abstract:
The effect of coolant-to-freestream velocity ratios on film cooling adiabatic effectiveness has been presented. These measurements were taken under high free-stream turbulence intensity (12%) conditions, representative of operating gas turbine engines. Coolant is supplied to the film cooling hole by means of circular pipe with length to diameter ratio of 7.0. The geometry has a single film cooling hole with 35°-inclined streamwise injection. The film cooling flow is supplied at the temperature of 500 k and free stream flow is supplied at 1175 k. GAMBIT is used for geometry drawing and mesh generation, while FLUENT 6.2 is used for solving flow problem. Ten coolant-to-freestream velocity ratios ranging from 0.1 to 1.0 with an increment of 0.1 have been investigated. The results document the effect of velocity ratios on film cooling adiabatic effectiveness.
Page(s):
174-185
DOI:
DOI not available
Published:
Journal: Proceedings 5th International Bhurban Conference on Applied Sciences and Technology , Volume: 0, Issue: 0, Year: 2007