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Design Problems of a Regenerative Turboprop Aircraft Engine PUBLIC ACCESS

[+] Author Affiliations
R. E. Cutler, Esten W. Spears, Jr.

General Motors Corporation, Indianapolis, IN

Paper No. 64-GTP-13, pp. V001T01A013; 10 pages
doi:10.1115/64-GTP-13
From:
  • ASME 1964 Gas Turbine Conference and Products Show
  • ASME 1964 Gas Turbine Conference and Products Show
  • Houston, Texas, USA, March 1–5, 1964
  • Conference Sponsors: International Gas Turbine Institute
  • ISBN: 978-0-7918-7991-7
  • Copyright © 1964 by ASME

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.

Copyright © 1964 by ASME
This article is only available in the PDF format.

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