Accession Number:

ADA025500

Title:

High Temperature Thermocouple System for Advanced Aircraft Turbine Engines

Descriptive Note:

Final technical rept. 1 Aug 1974-31 Dec 1975

Corporate Author:

ENGELHARD MINERALS AND CHEMICALS CORP EDISON NJ RESEARCH AND DEVELOPMENT DEPT

Personal Author(s):

Report Date:

1975-12-31

Pagination or Media Count:

109.0

Abstract:

This is a final report covering the development of a temperature measuring system for the very high temperature gas streams found in advanced jet engines. The measurement system is a thermocouple probe assembly suitable for interfacing to the Detroit Diesel-Allison GMA 200 Joint Technology Demonstration Engine. Average temperatures of the order of 2600-2700F 1425-1480C will have to be measured and it is anticipated that hot spots to 3000F 1650C will be encountered. This study covered the selection of an optimum thermocouple Pt- 40 Rh vs. Pt-0.6 ThO2 compatible compensating extension lead wire base metal usable to around 750C in air Nichrome vs. EA 9R-682 high temperature resisting sheath and shield tube material Pt-0.6 ThO2 crushable MgO insulation design of a temperature probe using the optimum materials and vibration testing at 1450C of one of the finished probes. The selected probe passed the high temperature vibration test successfully.

Subject Categories:

  • Laminates and Composite Materials
  • Metallurgy and Metallography
  • Test Facilities, Equipment and Methods
  • Jet and Gas Turbine Engines

Distribution Statement:

APPROVED FOR PUBLIC RELEASE