An investigation is being conducted to determine experimentally the effectiveness of air-cooling several configurations of turbine blades in a turbojet engine. The results obtained with the second, blade configuration, a hollow blade shell with 15 fins inserted, are presented.nThe turbine of a production turbojet engine was modified for this investigation by replacing two of the original blades that were dia-metrically opposite one another with hollow air-cooled blades that had 15 fins inserted in the hollow blade shell. The air-cooled blades were instrumented so that the radial temperature distribution near the trail-ing edge and the peripheral temperature distribution approximately one-third of the spanwise distance from the blade base could be determined. Investigation of the cooled-blade temperature distribution was made over a range of cooling-air flows from 0.005 to about 0.125 pound per second per blade. The engine speed was varied from 4000 to 10,000 rpm and the combustion-gas-flow rate from 20.4 to 62.9 pounds per second.
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