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Investigations Relating to the Effects of Various Internal Geometries on the Effectiveness of an Aero-Engine Intake Thermal Anti-Icing System FREE

[+] Author Affiliations
S. J. Riley

Rolls-Royce plc, Derby, UK

E. H. James

Loughborough University of Technology, Leicestershire, UK

Paper No. 94-GT-276, pp. V004T09A042; 8 pages
doi:10.1115/94-GT-276
From:
  • ASME 1994 International Gas Turbine and Aeroengine Congress and Exposition
  • Volume 4: Heat Transfer; Electric Power; Industrial and Cogeneration
  • The Hague, Netherlands, June 13–16, 1994
  • Conference Sponsors: International Gas Turbine Institute
  • ISBN: 978-0-7918-7886-6
  • Copyright © 1994 by ASME

abstract

Various nose cowl internal geometry designs have been investigated in a study relating to the effect of hot air mass flows in the prevention of ice formation on the external nose cowl (lipskin) surfaces of aero-engine intakes. Significant differences in the lipskin surface temperature levels were observed as the internal, hot, anti-icing air distribution geometry was altered. A double-skinned arrangement (in which the hot air was closely confined to the region requiring protection against ice formation) was observed to be particularly advantageous in this respect. The effectiveness of this design was matched however by a conventional “piccolo” pipe distribution system whilst the remaining two internal Builds investigated were found to be not as effective. In evaluating the benefits that accrue from a particular design, factors such as weight, cost, reliability, maintenance and in-service experience must also be considered.

Copyright © 1994 by ASME
This article is only available in the PDF format.

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