Vk. Garg, ADIABATIC EFFECTIVENESS AND HEAT-TRANSFER COEFFICIENT ON A FILM-COOLED ROTATING BLADE, Numerical heat transfer. Part A, Applications, 32(8), 1997, pp. 811-830
A three dimensional Navier-Stokes code has been used to compute the ad
iabatic effectiveness and heat transfer coefficient on a rotatingfilm-
cooled turbine blade. The blade chosen is the United Technologies Rese
arch Center (UTRC) rotor with five film-cooling rows containing 83 hol
es, including three rows on the shower head with 49 holes, covering ab
out 86% of the blade span. The mainstream is akin to that under real e
ngine conditions with stagnation temperature 1900 K and stagnation pre
ssure 3 MPa. The blade speed is taken to be 5200 rpm. The adiabatic ef
fectiveness is higher for a rotating blade as compared to that for a s
tationary blade. Also, the direction of coolant injection from the sho
wer-head holes considerably affects the effectiveness and heat transfe
r coefficient values on both the pressure and suction surfaces. In all
cases the heat transfer coefficient and adiabatic effectiveness me hi
ghly three-dimensional in the vicinity of holes but tend to become two
-dimensional far downstream.