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Techniques for Enhancing Durability and Equivalence Ratio Control in a Rich-Lean, Three-Stage, Ground Power Gas Turbine Combustor FREE

[+] Author Affiliations
Donald F. Schultz

National Aeronautics and Space Administration, Lewis Research Center, Cleveland, OH

Paper No. 82-JPGC-GT-17, pp. V001T01A017; 8 pages
doi:10.1115/82-JPGC-GT-17
From:
  • 1982 Joint Power Generation Conference: GT Papers
  • 1982 Joint Power Generation Conference: GT Papers
  • Denver, Colorado, USA, October 17–21, 1982
  • Conference Sponsors: International Gas Turbine Institute
  • ISBN: 978-0-7918-7937-5
  • Copyright © 1982 by ASME

abstract

This effort summarizes the work performed under Task IV, Sector Rig Tests of the CRT - Critical Research and Support Technology Program, a Department of Energy funded project. The rig tests of a can-type combustor were performed to demonstrate two advanced ground power engine combustor concepts: steam cooled rich-burn combustor primary zones for enhanced durability; and variable combustor geometry for three stage combustion equivalence ratio control. Both concepts proved to be highly successful in achieving their desired objectives. The steam cooling reduced peak liner temperatures to less than 800 K. This offers the potential of both long life and reduced use of strategic materials for liner fabrication. Three degrees of variable geometry were successfully implemented to control airflow distribution within the combustor. One was a variable blade angle axial flow air swirler to control primary airflow while the other two consisted of rotating bands to control secondary and tertiary or dilution air flow.

Copyright © 1982 by ASME
This article is only available in the PDF format.

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