Accession Number:

ADA199768

Title:

Measurements of Gas Turbine Combustor and Engine Augmentor Tube Sooting Characteristics

Descriptive Note:

Final rept. Oct 1986-Sep 1987

Corporate Author:

NAVAL POSTGRADUATE SCHOOL MONTEREY CA

Report Date:

1988-07-01

Pagination or Media Count:

57.0

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.

Subject Categories:

  • Combustion and Ignition
  • Jet and Gas Turbine Engines

Distribution Statement:

APPROVED FOR PUBLIC RELEASE