Accession Number:

ADA285423

Title:

Design of Thermocouple Probes for Measurement of Rocket Exhaust Plume Temperatures

Descriptive Note:

Technical rept.

Corporate Author:

DEFENCE SCIENCE AND TECHNOLOGY ORGANISATION VICTORIA (AUSTRALIA) AERONAUTICAL AND MARITIME RESEARCH LAB

Personal Author(s):

Report Date:

1994-06-01

Pagination or Media Count:

41.0

Abstract:

This paper summarises a literature survey on high temperature measurement and describes the design of probes used in plume measurements. There were no cases reported of measurements in extreme environments such as exist in solid rocket exhausts, but there were a number of thermocouple designs which had been used under less extreme conditions and which could be further developed. Tungsten-rheniumW-Rh thermocouples had the combined properties of strength at high temperatures, high thermoelectric emf, and resistance to chemical attack. A shielded probe was required, both to protect the thermocouple junction, and to minimise radiative heat losses. After some experimentation, a twin shielded design made from molybdenum gave acceptable results. Corrections for thermal conduction losses were made based on a method obtained from the literature. Radiation losses were minimised with this probe design, and corrections for these losses were too complex and unreliable to be included. Rocket Plume Temperature, Thermocouple, High Temperature.

Subject Categories:

  • Inorganic Chemistry
  • Acoustics
  • Combustion and Ignition

Distribution Statement:

APPROVED FOR PUBLIC RELEASE