Measurements of gas turbine combustor and engine augmentor tube sooting characteristics
Young, Mark F
Grafton, Thomas A
Netzer, David W
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An experimental investigation was conducted to determine the changes in soot mean diameter across the combustor and exhaust nozzle of a T63 gas turbine engine, and across an exhaust augmentor tube. D32 within the combustor varied between 0.16 and 0.25 microns, depending upon fuel composition. Data correlation was most successful in this location using an index of refraction of 1.95 -0.66i with sigma = 1.5. In the aft can location (ahead of the exhaust nozzle) D32 was between 0.35 and 0.45 microns, depending upon the fuel-air ratio. Increasing fuel-air ratios decreased D32, also in agreement with the results presented in reference 1. Using NAPC 9 high aromatic fuel, D32 increased across the exhaust nozzle (0.35 to 1.2 microns) and across the augmentor tube (1.2 to 1.5 = 1.9 microns). Malvern data were in good agreement with the results obtained using larger scattering angles. Keywords: Optical sizing of sootGas turbine combustorsExhaust augmentor tubes. (JES)
RightsThis publication is a work of the U.S. Government as defined in Title 17, United States Code, Section 101. Copyright protection is not available for this work in the United States.
NPS Report NumberNPS-67-88-002
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