Problems and Solutions for Sand Environment Operation of Helicopter Gas Turbines PUBLIC ACCESS

[+] Author Affiliations
G. C. Rapp, S. H. Rosenthal

General Electric Company, Lynn, MA

Paper No. 68-GT-37, pp. V001T01A037; 16 pages
  • ASME 1968 Gas Turbine Conference and Products Show
  • ASME 1968 Gas Turbine Conference and Products Show
  • Washington, DC, USA, March 17–21, 1968
  • Conference Sponsors: International Gas Turbine Institute
  • ISBN: 978-0-7918-7987-0
  • Copyright © 1968 by ASME


This paper is of two parts: a review of the experience of the T58 in an erosive environment, and a review of the design considerations, development testing and field experience in the T64 program relative to operation in a sand environment. Combat operation of various T58-powered helicopters showed erosion to be the major cause of engine premature removals. A description is given of problems encountered and of the design improvements and maintenance procedures implemented to minimize erosion effects. Field experience and redesign effort established general guidelines applicable to future turbine engine design and installations for helicopter and V/STOL aircraft. Mechanical and aerodynamic design requirements for sand environment operation are discussed as applicable to the T64, including the test experience obtained during the development program. Results are presented of the flight test program to evaluate the effectiveness of the inertial separator installed on the Sikorsky CH-53. Relative engine conditions are reviewed and compared to SEA field experience.

Copyright © 1968 by ASME
Topics: Sands , Gas turbines
This article is only available in the PDF format.



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