Accession Number:

ADA170907

Title:

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

Descriptive Note:

Technical memo.

Corporate Author:

NATIONAL AERONAUTICS AND SPACE ADMINISTRATION CLEVELAND OH LEWIS RESEARCH CENTER

Personal Author(s):

Report Date:

1986-06-01

Pagination or Media Count:

16.0

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 metalceramic 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.

Subject Categories:

  • Jet and Gas Turbine Engines

Distribution Statement:

APPROVED FOR PUBLIC RELEASE