Small Gas Turbine Combustor Experimental Study--Compliant Metal/Ceramic Liner and Performance Evaluation

Abstract

Combustor research relating to the development of fuel efficient small gas turbine engines capable of meeting future commercial and military aviation needs is currently underway at NASA Lewis. As part of this combustor research, a basic reverse-flow combustor has been used to investigate advanced liner wall cooling techniques. Liner temperature, performance, and exhaust emissions of the experimental combustor utilizing compliant metal/ceramic liners were determined and compared with three previously reported combustors that featured: (1) splash film-cooled liner walls; (2) transpiration cooled liner walls; and (3) counterflow film cooled panels.

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Document Details

Document Type
Technical Report
Publication Date
Jun 01, 1986
Accession Number
ADA170907

Entities

People

  • Carl T. Norgren
  • Waldo A. Acosta

Organizations

  • National Aeronautics and Space Administration

Tags

DTIC Thesaurus Topics

  • Army Aviation
  • Carbon Monoxide
  • Ceramic Materials
  • Ceramic Matrix Composites
  • Chemistry
  • Combustion
  • Dielectric Gases
  • Exhaust Gases
  • Films
  • Fuel Air Ratio
  • Gas Turbines
  • Heat Transfer
  • Materials
  • Mechanical Properties
  • Pressure Measurement
  • Secondary Flow
  • Turbines

Fields of Study

  • Physics

Readers

  • Combustion and Flow Dynamics.
  • Internal Combustion Engine (ICE) Technology.
  • Technical Research and Report Writing.