Abstract
Abstract : An evaluation test of a typical transpiration cooled turbine blade was performed on the combustion chamber sector rig, prior to engine testing, in order to evaluate the coolant requirements of high temperature operation. The results obtained demonstrate the ability of the blades to operate in an environment of turbine inlet temperatures of 2500 F and higher. Cascade tests were conducted to determine the contamination effects of JP-4 exhaust products on porous blade airfoils. Full scale engine tests of transpiration cooled turbine rotor and stator blades were successful up to average turbine inlet temperatures just under 2200 F. Inspection of the undamaged portions of rotor blades, indicate that operation at average turbine inlet temperatures of 2500 F is possible. Cooling air flow to the rotor blades was 4% as prescribed in the design (2500 F) requirements which test results showed was more than sufficient as overcooling was evident on some areas of the blades. With the prescribed cooling air flows the designed maximum skin and strut temperatures of 1600 F and 1200 F, respectively, were not exceeded as indicated by material conditions observed after full scale engine testing.
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