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A 2000-HP Military Vehicle Gas Turbine: A Study of Significant Thermodynamic and Mechanical Parameters PUBLIC ACCESS

[+] Author Affiliations
A. F. Carter

Northern Research and Engineering Corporation, Cambridge, MA

Paper No. 68-GT-52, pp. V001T01A052; 10 pages
doi:10.1115/68-GT-52
From:
  • 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

abstract

During a study of possible gas turbine cycles for a 2000-hp unit for tank propulsion, it has been established that the level of achievable specific fuel consumption (sfc) is principally determined by the combustor inlet temperature. If a regenerative cycle is selected, a particular value of combustor inlet temperature (and hence sfc) can be produced by an extremely large number of combinations of compressor pressure ratio, turbine inlet temperature, and heat exchanger effectiveness. This paper outlines the overall design considerations which led to the selection of a relatively low pressure ratio engine in which the turbine inlet temperature was sufficiently low that blade cooling was not necessary.

Copyright © 1968 by ASME
This article is only available in the PDF format.

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