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Experimental Analysis of Altitude Relight Under Realistic Conditions Using Laser and High-Speed Video Techniques

[+] Author Affiliations
T. Mosbach, R. Sadanandan, W. Meier

Deutsches Zentrum f. Luft- u. Raumfahrt (DLR), Stuttgart, Germany

R. Eggels

Rolls-Royce Deutschland, Blankenfelde-Mahlow, Germany

Paper No. GT2010-22625, pp. 523-532; 10 pages
  • ASME Turbo Expo 2010: Power for Land, Sea, and Air
  • Volume 2: Combustion, Fuels and Emissions, Parts A and B
  • Glasgow, UK, June 14–18, 2010
  • Conference Sponsors: International Gas Turbine Institute
  • ISBN: 978-0-7918-4397-0 | eISBN: 978-0-7918-3872-3
  • Copyright © 2010 by ASME


The altitude relight performance of a lean fuel injector and combustor was investigated at the altitude relight test rig at the Rolls-Royce Strategic Research Centre (SRC) in Derby. The studies were performed for different mass flow rates of air and kerosene, a combustor temperature and pressure of 278 K and 0.5 bar, respectively. Good optical access to the combustion chamber enabled the application of optical and laser measuring techniques. High-speed video imaging in the UV and visible wavelength range at a frame rate of 3.5 kHz was used to visualize the temporal development of the flame kernel. The observed differences between the UV and visible flame emissions demonstrate the different origins of the luminosity, i.e. OH* chemiluminescence and soot radiation. Further, laser-induced fluorescence of kerosene and OH radicals was applied at a frame rate of 5 Hz to visualize the fuel distribution and regions of hot and reacting mixtures. For two exemplary flames with different mass flow rates and fuel-to-air ratios, the steady burning flames after successful ignition are characterized in this paper by the distributions of kerosene, OH*, OH and soot luminosity. An example of the flame kernel development for a successful ignition is given by an image sequence from a high-speed video recording of the chemiluminescence. The importance of the upstream movement of the flame kernel as a condition preceding successful flame stabilization is identified.

Copyright © 2010 by ASME



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