High Temperature Thermocouple System for Advanced Aircraft Turbine Engines

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.

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Document Details

Document Type
Technical Report
Publication Date
Dec 31, 1975
Accession Number
ADA025500

Entities

People

  • D. A. Toenshoff
  • E. D. Zysk

Tags

Communities of Interest

  • Advanced Electronics
  • Air Platforms
  • Sensors

DTIC Thesaurus Topics

  • Advanced Materials
  • Air Force
  • Base Metal
  • Ceramic Materials
  • Chemistry
  • Fabrication
  • Gas Turbines
  • Lead Wires
  • Manufacturing
  • Materials
  • Measurement
  • Mechanical Properties
  • Military Aircraft
  • Plastic Explosives
  • Procurement
  • Test Equipment
  • Turbines

Fields of Study

  • Physics

Readers

  • Aerospace Engineering
  • Metallurgy
  • Thermal Physics or Thermal Science.

Technology Areas

  • Microelectronics
  • Microelectronics - Microelectromechanical Systems