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Gas turbine cycle calculations: design-point performance of turbopropeller and turboshaft engines

Par Conseil national de recherches du Canada

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DOITrouver le DOI : https://doi.org/10.4224/40003695
AuteurRechercher : 1; Rechercher : 1
Affiliation
  1. Conseil national de recherches du Canada. Division de génie mécanique
FormatTexte, Rapport technique
Description physique84 p.
Résumé
An accurate and comprehensive method for calculating the design-point performance of a broad range of turbopropturboshaft engines is described; this Report represents an extension of an earlier study dealing with turbojet-turbofan engines. Heat exchanger and interheater elements are provided so that regenerative and reheated cycles may be examined in addition to straightforward shaft power cycles. Particular emphasis is placed in this Report on a rigorous analysis of those engine components not common to the earlier study. The programme is described in sufficient detail, and is accompanied by sufficiently complete FORTRAN II source listings, that it may be applied immediately to a similar computer (IBM 1620 computer with 40,000 digit core storage memory). Copies of the programme, either in the FORTRAN II version described, or in FORTRAN IV (for an IBM 360 system) may be obtained from the authors on request.
Date de publication
Maison d’éditionNational Research Council Canada
Série
  • Aeronautical Report (National Research Council Canada. Division of Mechanical Engineering. Engine Laboratory), nº LR-448 (novembre 1965).
Langueanglais
Publications évaluées par des pairsNon
Numéro du CNRCNRCC-0008880
NRC-8880
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Identificateur de l’enregistrement314abe07-42fb-45a5-99f0-12c4d4681e4d
Enregistrement créé2025-09-05
Enregistrement modifié2025-11-03
Date de modification :