Effect of Operating Variables on Pollutant Emissions from Aircraft Turbine Engine Combustors

  • J. S. Grobman


The purpose of this paper is to review NASA-Lewis combustor research aimed at reducing exhaust emissions from jet aircraft engines. Experimental results of tests performed on both conventional and experimental combustors over a range of inlet total pressure, inlet total temperature, reference velocity, and fuel-air ratio are presented to demonstrate the effect of operating variables on pollutant emissions. Combustor design techniques to reduce emissions are discussed. Improving fuel atomization by using an air-assist fuel nozzle has been shown to significantly reduce hydrocarbon (HC) and carbon monoxide (CO) emissions during idle. A short-length annular swirl-can combustor has demonstrated a significant reduction in nitric oxide (NO) emissions compared to a conventional combustor operating at similar conditions. The use of diffuser wall bleed to provide variable control of combustor airflow distribution may enable the achievement of reduced emissions without compromising combustor performance.


Combustion Efficiency Reference Velocity Primary Zone Emission Index Fuel Atomization 


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Copyright information

© Springer Science+Business Media New York 1972

Authors and Affiliations

  • J. S. Grobman
    • 1
  1. 1.NASA — Lewis Research CenterClevelandUSA

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