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Analytical Investigation of the Rules of Component Matching in Turbojet Engines PUBLIC ACCESS

[+] Author Affiliations
Dao-Zhi Liu

Beijing University of Aeronautics and Astronautics, Beijing, P. R. China

Paper No. 91-GT-170, pp. V001T01A065; 5 pages
doi:10.1115/91-GT-170
From:
  • ASME 1991 International Gas Turbine and Aeroengine Congress and Exposition
  • Volume 1: Turbomachinery
  • Orlando, Florida, USA, June 3–6, 1991
  • Conference Sponsors: International Gas Turbine Institute
  • ISBN: 978-0-7918-7898-9
  • Copyright © 1991 by ASME

abstract

In turbojet engines, phenomena under off–design conditions are related to the variations of incidence angles at different compressor stages. In the present paper, analytical formulae about the off–design incidence variations of inlet and exit compressor stages are derived. Using these fomulae, the detailed rules about engine parameter variations under off–design conditions are obtained; a series of phenomena about engine performance for low and high pressure ratio engines, engines with axial, centrifugal and combined compressors, as well as single–shaft and two–spool engines can then be explained systematically, their physical essence will be revealed clearly; and a variety of new situations and problems about engine off–design behavior can be predicted in advance.

Copyright © 1991 by ASME
Topics: Engines , Turbojets
This article is only available in the PDF format.

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