DESIGN AND FABRICATION ASPECTS OF TRANSPIRATION AIR COOLED BLADES FOR 2500°F TURBINE OPERATION 640393
The improvements in performance in turbojet and turboprop engines by increasing the maximum cycle temperature through the use of transpiration air cooled turbine blades for operation at 2500°F cycle temperature are presented. The fabrication aspects of a transpiration air cooled blade are discussed. Initial test results are presented demonstrating the feasibility of the transpiration air cooled blade concept for advanced aircraft turbine engines.
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