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Flight Evaluation of Helicopter Gas Turbine Engines PUBLIC ACCESS

[+] Author Affiliations
J. F. Bortkiewicz

Rolls Royce Ltd., Leavesden, Watford, Herts, England

Paper No. 70-GT-38, pp. V01AT01A039; 11 pages
doi:10.1115/70-GT-38
From:
  • ASME 1970 International Gas Turbine Conference and Products Show
  • Volume 1A: General
  • Brussels, Belgium, May 24–28, 1970
  • Conference Sponsors: International Gas Turbine Institute
  • ISBN: 978-0-7918-7985-6
  • Copyright © 1970 by ASME

abstract

Five distinct phases of flight testing are outlined: initial flight evaluation, engine-helicopter integration, intensive flying, environmental tests and continuation development after introduction of engines into service. Areas of evaluation are listed and ultimate objectives specified. Since many areas of flight evaluation are common with fixed wing subsonic aircraft, emphasis is laid primarily on matching of the engine characteristics to the helicopter dynamic system. The paper is concluded with a statement of prerequisites of “ideal” engines and their control systems for helicopters.

Copyright © 1970 by ASME
Topics: Gas turbines , Flight
This article is only available in the PDF format.

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