Publication Date:
2019-07-13
Description:
Nitric oxide forms in the primary zone of gas turbine combustors where the burnt gas composition is close to stoichiometric and gas temperatures are highest. It has been found that combustor air inlet conditions, mean primary zone fuel-air ratio, residence time, and the uniformity of the primary zone are the most important variables affecting nitric oxide emissions. Relatively simple model of the flow in a gas turbine combustor, coupled with a rate equation for nitric oxide formation via the Zeldovich mechanism are shown to correlate the variation in measured NOx emissions. Data from a number of different combustor concepts are analyzed and shown to be in reasonable agreement with predictions. The NOx formulation model is used to assess the extent to which an advanced combustor concept, the NASA swirl can, has produced a lean well-mixed primary zone generally believed to be the best low NOx emissions burner type.
Keywords:
PROPULSION SYSTEMS
Type:
NASA-CR-132959
,
t AGARD Propulsion and Energetics Panel 41st Meeting on Atmospheric Pollution by Aircraft Engines; Apr 09, 1973 - Apr 13, 1973; London; Engl.
Format:
application/pdf
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