TECHNICAL PAPERS: Gas Turbines: Combustion and Fuels

Investigation of Two Advanced Cooling Mixing Concepts for a Rich Quench Lean Combustor

[+] Author and Article Information
O. Diers, J. Koopman, M. Fischer, C. Hassa

German Aerospace Center, Institute of Propulsion Technology, 51170 Köln, Germany

J. Eng. Gas Turbines Power 124(4), 784-791 (Sep 24, 2002) (8 pages) doi:10.1115/1.1473823 History: Received December 01, 2000; Revised March 01, 2001; Online September 24, 2002
Copyright © 2002 by ASME
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Side view of combustor first configuration
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Side view of second configuration
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Measurement planes and upper side of first configuration, axial plane positions in mm behind the nozzle exit
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Measurement planes and lower side of liner second configuration, axial plane positions in mm behind the nozzle exit
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TFN, RFTN, NO, and combustion efficiency average of measurement of planes at x=48, 78, 95, and 108 mm
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Interpolated vector plot of measured velocities in nozzle center area
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Thermocouple temperatures in nozzle center plane
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Calculated temperature distribution of first configuration
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Mass and arithmetically averaged EI_TFN for several primary zone air fuel ratios (AFR)
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Axial development of nitrogen emission indices (upper: EI_TFN, middle: EI_RTFN, lower: EI_NO), calculated with molecular weight of NO2 for a primary zone AFR of 8.4
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Interpolated velocity vectors, axial velocity as gray scale, histograms with axial velocities in nozzle area (upper: position over primary zone cooling air orifice, lower: position over secondary air inlet hole)
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Flame tube boundary and mixing hold configuration for modified mixing hold design




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