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Parametric test results of a swirl-can combustorPollutant levels of oxides of nitrogen, unburned hydrocarbons, and carbon monoxide were measured for three models of an experimental, annular swirl can combustor. The combustor was 1.067 meters in outer diameter, incorporated 120 modules, and was specifically designed for elevated exit temperature performance. Test conditions included combustor inlet temperatures of 589, 756 and 839 K, inlet pressures of 3 to 6.4 atmospheres, reference velocities of 21 to 38 meters per second and combustor equivalence ratios, based on total combustor flows of 0.206 to 1.028. Maximum oxides of nitrogen emission index values occurred at an equivalence ratio of 0.7 with lower values measured for both higher and lower equivalence ratios. Oxides of nitrogen concentrations, to the 0.7 level with 756 K inlet air, were correlated for the three models by a combined parameter consisting of measured flow and geometric parameters. Effects of the individual parameters comprising the correlation are also presented.
Document ID
19730016070
Acquisition Source
Legacy CDMS
Document Type
Conference Paper
Authors
Niedzwiecki, R. W.
(NASA Lewis Research Center Cleveland, OH, United States)
Jones, R. E.
(NASA Lewis Research Center Cleveland, OH, United States)
Date Acquired
September 2, 2013
Publication Date
January 1, 1973
Subject Category
Propulsion Systems
Report/Patent Number
E-7501
NASA-TM-X-68247
Report Number: E-7501
Report Number: NASA-TM-X-68247
Meeting Information
Meeting: Natl. Meeting
Location: Detroit, MI
Country: U.S
Start Date: June 4, 1973
End Date: June 6, 1973
Sponsors: Am. Inst. of Chem. Engr.
Accession Number
73N24797
Distribution Limits
Public
Copyright
Work of the US Gov. Public Use Permitted.
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