Measurement of temperature in low velocity high temperature gas streams

Abstract

Many investigations have been conducted for the development of suitable devices for the measurement of gas temperature in the field of gas turbines and jet propulsion. Each of the methods developed is suitable for a certain range of temperature, and some of the methods need further development to establish their accuracy. It is intended in the present investigations to test some of the conventional devices in the temperature range of 1600癋 to 2200癋 in a low-velocity gas stream, where radiation error is predominant. The investigations were conducted on a series of shielded thermocouple probes in a test setup developed for that purpose, and the results obtained therefrom are herein reported. In addition, the thermodynamic method as developed by Clark and Rohsenow has been applied to the above range of temperatures with a suitable probe developed for that purpose. The results presented give an indication of the behavior of the various probes tested in the temperature range of 1600癋 to 2200癋.