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Aero-Thermal Computations With Experimental Comparison Applied to Aircraft Engine Nacelle Compartment

[+] Author Affiliations
Morgan Balland

Snecma Moteurs, Moissy Cramayel, France

Olivier Verseux, Marie-Josephe Esteve

Airbus France, Toulouse Cedex, France

Paper No. GT2005-68995, pp. 1217-1225; 9 pages
doi:10.1115/GT2005-68995
From:
  • ASME Turbo Expo 2005: Power for Land, Sea, and Air
  • Volume 3: Turbo Expo 2005, Parts A and B
  • Reno, Nevada, USA, June 6–9, 2005
  • Conference Sponsors: International Gas Turbine Institute
  • ISBN: 0-7918-4726-8 | eISBN: 0-7918-3754-8
  • Copyright © 2005 by ASME

abstract

A joint Airbus & Snecma study on aero-thermal methodology applied to nacelle compartment is presented. Both partners have used their own simulation tools and compared their results with a real engine configuration to highlight the temperature heterogeneities on the engine casing and characterize equipment thermal fields. From the CFD, the structure of the flow has been consolidated in a cavity without equipments. The impact of equipment items on flow behavior has been studied in a second step. From a thermal aspect, the weight of both radiative and convective transfers has been estimated. Comparisons with engine thermocouple data show that the difference on average metal temperatures per station is less than 10% whereas the temperature gradient are underestimated in a range of [10–30]°C.

Copyright © 2005 by ASME

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