Design Problems of a Regenerative Turboprop Aircraft Engine

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Abstract
The military and industry have long recognized the potential of the regenerative-cycle gas turbine. Only recently has the “state-of-the-art” in regenerators and other lightweight turbine-engine components made it feasible to apply regeneration to aircraft engines. In applying regeneration to the aircraft gas turbine certain unique engine-design problems are encountered, such as: (a) Configuration and arrangement of lightweight, high effectiveness regenerator; (b) combustion system with side entry air; (c) turbine cooling at high inlet temperatures; (d) compressor operating flexibility; (e) control system for optimum engine response and operational flexibility; (f) configuration and arrangement of propeller and reduction gear.

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