Feasibility Demonstration of a Small Fluid-Cooled Turbine at 2300F 690034
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.
