The current demands for high performance gas turbine engines can be reached by raising combustion temperatures to increase power output. Predicting the performance of a combustor is quite challenging, particularly the turbulence levels that are generated as a result of injection from high momentum dilution jets. Prior to predicting reactions in a combustor, it is imperative that these turbulence levels can be accurately predicted. The measurements presented in this paper are of flow and thermal fields produced in a large-scale combustor simulator, which is representative of an aeroengine. Three-component laser Doppler velocimeter measurements were made to quantify the velocity field while a rake of thermocouples was used to quantify the thermal field. The results indicate large penetration depths for the high momentum dilution jets, which result in a highly turbulent flow field. As these dilution jets interact with the mainstream flow, kidney-shaped thermal fields result due to counter-rotating vortices that develop.
Flow and Thermal Field Measurements in a Combustor Simulator Relevant to a Gas Turbine Aeroengine
Contributed by the International Gas Turbine Institute (IGTI) of THE AMERICAN SOCIETY OF MECHANICAL ENGINEERS for publication in the ASME JOURNAL OF ENGINEERING FOR GAS TURBINES AND POWER. Paper presented at the International Gas Turbine and Aeroengine Congress and Exhibition, Atlanta, GA, June 16–19, 2003, Paper No. 2003-GT-38254. Manuscript received by IGTI, October 2002, final revision, March 2003. Associate Editor: H. R. Simmons.
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Vakil , S. S., and Thole, K. A. (April 15, 2005). "Flow and Thermal Field Measurements in a Combustor Simulator Relevant to a Gas Turbine Aeroengine ." ASME. J. Eng. Gas Turbines Power. April 2005; 127(2): 257–267. https://doi.org/10.1115/1.1806455
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