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Soot loading in a generic gas turbine combustorVariation in soot loading along the centerline of a generic gas turbine combustor was experimentally investigated. The 12.7-cm dia burner consisted of six sheet-metal louvers. Soot loading along the burner length was quantified by acquiring measurements first at the exit of the full-length combustor and then at upstream stations by sequential removal of liner louvers to shorten the burner length. Alteration of the flow field approaching removed louvers, maintaining a constant liner pressure drop. Burner exhaust flow was sampled at the burner centerline to determine soot mass concentration and smoke number. Characteristic particle size and number density, transmissivity of the exhaust flow, and local radiation from luminous soot particles in the exhaust flow were determined by optical techniques. Four test fuels were burned at three fuel-air ratios to determine fuel chemical property and flow temperature influences. Data were acquired at two combustor pressures. Particulate concentration data indicated a strong oxidation mechanism in the combustor secondary zone, though the oxidation was significantly affected by flow temperature. Soot production was directly related to fuel smoke point. Less soot production and lower secondary-zone oxidation rates were observed at reduced combustor pressure.
Document ID
19870035270
Acquisition Source
Legacy CDMS
Document Type
Conference Paper
Authors
Eckerle, W. A.
(Clarkson University Potsdam, NY, United States)
Rosfjord, T. J.
(United Technologies Research Center East Hartford, CT, United States)
Date Acquired
August 13, 2013
Publication Date
January 1, 1987
Subject Category
Aircraft Propulsion And Power
Report/Patent Number
AIAA PAPER 87-0297
Accession Number
87A22544
Funding Number(s)
CONTRACT_GRANT: NAS3-24223
Distribution Limits
Public
Copyright
Other

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