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LES Predictions of Noise Emissions From a Low-Bypass Ratio Military Gas Turbine Engine

[+] Author Affiliations
N. Sinha, J. Erwin, C. Kannepalli, S. Arunajatesan

Combustion Research & Flow Technology, Inc. (CRAFT Tech), Pipersville, PA

Paper No. GT2010-22191, pp. 47-56; 10 pages
  • ASME Turbo Expo 2010: Power for Land, Sea, and Air
  • Volume 1: Aircraft Engine; Ceramics; Coal, Biomass and Alternative Fuels; Education; Electric Power; Manufacturing Materials and Metallurgy
  • Glasgow, UK, June 14–18, 2010
  • Conference Sponsors: International Gas Turbine Institute
  • ISBN: 978-0-7918-4396-3 | eISBN: 978-0-7918-3872-3
  • Copyright © 2010 by ASME


A practical framework for predicting jet structure and noise from military aircraft is described, which is developmental and has been examined for some fundamental jet flow problems. The framework currently utilizes RANS methodology for geometrically complex internal propulsive flowpaths and LES methodology for the jet structure downstream of the nozzle exit. Temporal data from the LES solution is stored on a flared-cylindrical surface surrounding the jet, to be used for noise propagation to the farfield. Earlier applications of RANS methodology combined with the use of analogy-based jet noise codes proved inadequate due to the inability of the noise codes to treat complex 3D flows such as those associated with multiple nozzles and/or with varied jet noise reduction concepts. Restricting the use of LES (or RANS/LES) methodology to free shear flows remedies the severe grid resolution issues that would be encountered with utilization of LES for modeling internal propulsive flows. The issue of “adequately” initiating the LES solution from a RANS solution profile just downstream of the nozzle exit has been the focus of our exploratory studies, and is clearly more complex than standard procedures such as recycling and rescaling techniques used for simple wall bounded flows. Approaches examined are discussed and unified RANS / LES solutions for several flows are described. The application of this framework to more complex flows requires no fundamental modifications as will also be discussed.

Copyright © 2010 by ASME



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