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Small gas-turbine combustor study: Fuel injector evaluationAs part of a continuing effort at the Lewis Research Center to improve performance, emissions, and reliability of turbine machinery, an investigation of fuel injection technique and effect of fuel type on small gas turbine combustors was undertaken. Performance and pollutant emission levels are documented over a range of simulated flight conditions for a reverse flow combustor configuration using simplex pressure-atomizing, spill-flow return, and splash cone airblast injectors. A parametric evaluation of the effect of increased combustor loading with each of the fuel injector types was obtained. Jet A and an experimental referee broad specification fuel were used to determine the effect of fuel type.
Document ID
19810017610
Acquisition Source
Legacy CDMS
Document Type
Conference Paper
Authors
Norgren, C. T. (NASA Lewis Research Center Cleveland, OH, United States)
Riddlebaugh, S. M. (NASA Lewis Research Center Cleveland, OH, United States)
Date Acquired
September 4, 2013
Publication Date
January 1, 1981
Subject Category
Aircraft Propulsion And Power
Report/Patent Number
NASA-TM-82641
E-891
Report Number: NASA-TM-82641
Report Number: E-891
Meeting Information
Meeting: Joint Propulsion Conf.,
Location: Colorado Springs, CO
Country: United States
Start Date: July 27, 1981
End Date: July 29, 1981
Sponsors: ASME, AIAA, SAE
Accession Number
81N26146
Funding Number(s)
PROJECT: RTOP 505-32-32
Distribution Limits
Public
Copyright
Work of the US Gov. Public Use Permitted.

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