Measurements of gas turbine combustor and engine augmentor tube sooting characteristics
By: M.F. Young, T.A. Grafton, H. Conner, and D.W. Netzer
Contributors: Grafton, Thomas A.; Conner, H.; Netzer, David W.; Naval Postgraduate School (U.S.). Dept. of Aeronautics and Astronautics
Publisher: Naval Postgraduate School; Available from National Technical Information Service
Published: 1988
Place of publication: Monterey, Calif; Springfield, Va
Language: eng
Number of pages: 48
Subjects: GAS TURBINES; COMBUSTORS
Other titles: NPS-67-88-002.
Description: 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)
Notes: Title from cover.

"NPS-67-88-002."

"July 1988."

AD A199 768.

Includes bibliographical references (p. 45)

aq/aq cc:9116 11/19/98