SMALL GAS TURBINE ENGINE COMPONENT TECHNOLOGY - TURBINE. VOLUME I. PHASE I SUMMARY REPORT
CURTISS-WRIGHT CORP WOOD-RIDGE NJ
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The report describes the aerodynamic, thermal, and mechanical design and analysis, fabrication, and experimental evaluation of a transpiration cooled, single stage axial-flow turbine component capable of operation at 2500F average inlet temperature. Combustor design and development and test rig design are described, as well as stator vane hot thermal and cold aerodynamic cascade testing. The objective of the program was to advance and demonstrate high turbine inlet technology for use in a gas generator with a compressor pressure ratio of 8 to 10 and an airflow of 4 pounds per second. Additional objectives included turbine work of 140 Btu per pound of airflow at a high level of turbine efficiency. Phase I report presents the design and analysis. It was concluded that the advanced technology incorporated in the turbine design relative to blade cooling and turbine mechanical integrity are practical and can be applied to the design of advanced small gas turbines.
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