Temperature measurement techniques and their application on gas turbine rotor heat transfer research

Detailed knowledge about local surface temperature and material temperature gradients of highly stressed turbine components is required for the determination of heat transfer and material stress in order to perform lifetime prediction and control. The rotor of the engine poses some particularly difficult measurement problems. In this paper the temperature measuring technique applied to the rotor system of a test gas turbine is described. Three methods are used for measuring blade surface temperatures: thermocouple technique, temperature indicating paints, and infrared pyrometry. Examinations have been made with reference to the accuracy of measurement. Some results obtained to date by application of the different techniques are presented and discussed with respect to the determination of local gas to blade heat transfer.