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Performance of a Model Rich Burn-quick Mix-lean Burn Combustor at Elevated Temperature and PressureAs interest in pollutant emission from stationary and aero-engine gas turbines increases, combustor engineers must consider various configurations. One configuration of increasing interest is the staged, rich burn - quick mix - lean burn (RQL) combustor. This report summarizes an investigation conducted in a recently developed high pressure gas turbine combustor facility. The model RQL combustor was plenum fed and modular in design. The fuel used for this study is Jet-A which was injected from a simplex atomizer. Emission (CO2, CO, O2, UHC, NOx) measurements were obtained using a stationary exit plane water-cooled probe and a traversing water-cooled probe which sampled from the rich zone exit and the lean zone entrance. The RQL combustor was operated at inlet temperatures ranging from 367 to 700 K, pressures ranging from 200 to 1000 kPa, and combustor reference velocities ranging from 10 to 20 m/s. Variations were also made in the rich zone and lean zone equivalence ratios. Several significant trends were observed. NOx production increased with reaction temperature, lean zone equivalence ratio and residence time and decreased with increased rich zone equivalence ratio. NOx production in the model RQL combustor increased to the 0.4 power with increased pressure. This correlation, compared to those obtained for non-staged combustors (0.5 to 0.7), suggests a reduced dependence on NOx on pressure for staged combustors. Emissions profiles suggest that rich zone mixing is not uniform and that the rich zone contributes on the order of 16 percent to the total NOx produced.
Document ID
20030013952
Document Type
Contractor Report (CR)
Authors
Peterson, Christopher O. (California Univ. Irvine, CA United States)
Sowa, William A. (California Univ. Irvine, CA United States)
Samuelsen, G. S. (California Univ. Irvine, CA United States)
Date Acquired
September 7, 2013
Publication Date
December 1, 2002
Subject Category
Aircraft Propulsion and Power
Report/Patent Number
E-13663
NASA/CR-2002-211992
NAS 1.26:211992
Funding Number(s)
CONTRACT_GRANT: NAG3-1110
PROJECT: RTOP 714-02-08
Distribution Limits
Public
Copyright
Work of the US Gov. Public Use Permitted.

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