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Inlet-Fan Flow Field Computation FREE

[+] Author Affiliations
Mark D. Matwey, Barry S. Seidel

University of Delaware, Newark, DE

Charles A. Farrell, Jr.

NASA Lewis Research Center, Cleveland, OH

Paper No. 83-GT-41, pp. V001T01A019; 7 pages
doi:10.1115/83-GT-41
From:
  • ASME 1983 International Gas Turbine Conference and Exhibit
  • Volume 1: Turbomachinery
  • Phoenix, Arizona, USA, March 27–31, 1983
  • Conference Sponsors: International Gas Turbine Institute
  • ISBN: 978-0-7918-7951-1
  • Copyright © 1983 by ASME

abstract

The flow field of a tilt-nacelle inlet-fan combination used for V/STOL aircraft is studied. Under certain flight conditions the inlet is subjected to high angles of attack and/or yaw. This produces a non-uniform or distorted flow field at the fan-face that can lead to large blade stresses. This paper presents an analytical approach to the coupled inlet-fan problem. The nacelle is modelled by a distribution of source panels and the fan by a distribution of radial vortices. A modified actuator disc with losses and a quasi-steady rotor response is used to derive the boundary condition at the fan-face. An example of the calculation is shown.

Copyright © 1983 by ASME
This article is only available in the PDF format.

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