Feasibility Demonstration of a Small Fluid-Cooled Turbine at 2300F

This paper presents the results of an investigation directed toward the design and demonstration of a fluid-cooled turbine for an advanced small gas turbine. The primary objective was to advance and demonstrate high turbine inlet temperature technology utilizing a thermosiphon cooling system concept for a small gas turbine engine to the level that will provide a potential for doubling the specific horsepower relative to current small aircraft propulsion engines.