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Gas turbine combustor stabilization by heat recirculationThe feasibility of heat recirculation for stabilization of lean mixtures and emission reduction has been studied in detail for a typical aircraft gas turbine combustor. Thermodynamic calculations have indicated temperature and heat recirculation rates for operation of the combustor over a range of combustion zone equivalence ratios and for varying modes of desired engine operation. Calculations indicate the feasibility of stabilizing the combustion zone at equivalence ratios as low as 0.2 with achievable heat recirculation rates. Detailed chemical kinetic calculations suggest that combustor heat release is maintained with reaction completion substantially before the NO forming reactions, even though CO is rapidly oxidized in this same region.
Document ID
19750061616
Acquisition Source
Legacy CDMS
Document Type
Conference Paper
Authors
Ganji, A.
Short, J.
Branch, M. C.
Oppenheim, A. K.
(California, University Berkeley, Calif., United States)
Date Acquired
August 8, 2013
Publication Date
September 1, 1975
Subject Category
Aircraft Propulsion And Power
Report/Patent Number
AIAA PAPER 75-1304
Accession Number
75A45688
Funding Number(s)
CONTRACT_GRANT: NSG-3028
Distribution Limits
Public
Copyright
Other

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