Accession Number:

AD0651103

Title:

SMALL GAS TURBINE ENGINE COMPONENT TECHNOLOGY, HIGH-TEMPERATURE TURBINE MATERIALS RESEARCH

Descriptive Note:

Final rept., 1 May 1964-31 Aug 1965

Corporate Author:

BOEING CO SEATTLE WA TURBINE DIV

Report Date:

1966-12-01

Pagination or Media Count:

169.0

Abstract:

The report describes research conducted on two new material systems macrolaminate metal-ceramic composites and dispersion-strengthened nickel base alloys to determine their potential for future use, without special cooling, in the turbine section of an advanced small gas turbine engine, operating at a turbine inlet temperature of 2300F. Although the research showed that the targeted high-temperature material properties could not be achieved with the macrolaminate composites or the dispersion-strengthened alloys, it was felt that these types of materials could be developed to increase turbine inlet temperatures to about 2100F. However, it was recognized that this gain would not be sufficient in view of improvements being made with other new material systems.

Subject Categories:

  • Laminates and Composite Materials
  • Metallurgy and Metallography
  • Jet and Gas Turbine Engines

Distribution Statement:

APPROVED FOR PUBLIC RELEASE