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A Steady-State Radial Inlet Pressure Distortion Index for Axial-Flow Compressors FREE

[+] Author Affiliations
D. F. Brunda, J. F. Boytos

Naval Air Propulsion Test Center, Trenton, NJ

Paper No. 72-GT-109, pp. V001T01A107; 10 pages
doi:10.1115/72-GT-109
From:
  • ASME 1972 International Gas Turbine and Fluids Engineering Conference and Products Show
  • ASME 1972 International Gas Turbine and Fluids Engineering Conference and Products Show
  • San Francisco, California, USA, March 26–30, 1972
  • Conference Sponsors: International Gas Turbine Institute
  • ISBN: 978-0-7918-7981-8
  • Copyright © 1972 by ASME

abstract

A radial inlet pressure distortion index is derived using a mathematical compressor model, the two-dimensional continuity equation and the expression for radial velocity upstream of a low hub-tip ratio, multi-stage compressor. These expressions are combined with two conditions required for inlet flow similarity at compressor stall; namely, constant rotor angle of attack and constant ratio of mixing time to air residence time in the blade passage. The theory was tested on a twin-spool turbojet engine at sea level static conditions.

Copyright © 1972 by ASME
This article is only available in the PDF format.

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