Publication:
Measurements of gas turbine combustor and engine augmentor tube sooting characteristics

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Authors
Young, Mark F
Grafton, Thomas A
Conner, H
Netzer, David W
Subjects
Optical Sizing of Soot
Gas Turbine Combustors; Exhaust Augmentor Tubes
Advisors
Date of Issue
1988-07
Date
1988-07
Publisher
Monterey, California. Naval Postgraduate School
Language
en_US
Abstract
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 soot
Gas turbine combustors
Exhaust augmentor tubes. (JES)
Type
Technical Report
Description
Series/Report No
Department
Identifiers
NPS Report Number
NPS-67-88-002
Sponsors
Prepared for: Naval Air Propulsion Center Trenton, New Jersey
Funder
Format
Citation
Distribution Statement
Rights
This 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.
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