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Nonintrusive Flowfield, Temperature and Species Measurements on a Generic Aeroengine Combustor at Elevated Pressures

[+] Author Affiliations
Christoph Hassa, Chris Willert, Michael Fischer, Guido Stockhausen, Ingo Röhle

German Aerospace Center, Cologne, Germany

Wolfgang Meier, Lorin Wehr, Peter Kutne

German Aerospace Center, Stuttgart, Germany

Paper No. GT2006-90213, pp. 173-182; 10 pages
doi:10.1115/GT2006-90213
From:
  • ASME Turbo Expo 2006: Power for Land, Sea, and Air
  • Volume 1: Combustion and Fuels, Education
  • Barcelona, Spain, May 8–11, 2006
  • Conference Sponsors: International Gas Turbine Institute
  • ISBN: 0-7918-4236-3 | eISBN: 0-7918-3774-2
  • Copyright © 2006 by ASME

abstract

A generic combustor was built, that gives wide optical access at higher pressure and shares typical features with aero engine combustors. A comprehensive data set for validation of RANS and LES codes was generated at isothermal as well as combusting conditions at 2 and 10 bars with 650 K preheat using natural gas as fuel. The velocity field was measured using LDA (Laser Doppler Anemometry) and DGV (Doppler Global Velocimetry) as well as PIV (Particle Image Velocimetry). Temperature data were acquired using CARS (Coherent Anti stokes Raman Scattering) and SRS (Spontaneous Raman Scattering). Major species concentrations as well as the mixture fraction in the primary zone of the combustor were also measured using SRS. Mean and RMS values of the temperature measured by CARS in the secondary zone illustrate the influence of the jet impingement on the unsteady mixing of the jets with the swirling primary air.

Copyright © 2006 by ASME

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