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RESEARCH PAPERS

Unsteady Total Temperature Measurements Downstream of a High-Pressure Turbine

[+] Author and Article Information
D. R. Buttsworth, T. V. Jones

Deparment of Engineering Science, University of Oxford, Parks Road, Oxford, United Kingdom

K. S. Chana

DRA Pyestock, Farnborough, United Kingdom

J. Turbomach 120(4), 760-767 (Oct 01, 1998) (8 pages) doi:10.1115/1.2841787 History: Received February 01, 1997; Online January 29, 2008

Abstract

An experimental technique for the measurement of flow total temperature in a turbine facility is demonstrated. Two thin film heat transfer gases located at the stagnation point of fused quartz substrates are operated at different temperatures in order to determine the flow total temperature. With this technique, no assumptions regarding the magnitude of the convective heat transfer coefficient are made. Thus, the probe can operate successfully in unsteady compressible flows of arbitrary composition and high free-stream turbulence levels without a heat transfer law calibration. The operation of the total temperature probe is first demonstrated using a small wind tunnel facility. Based on results from the small wind tunnel tests, it appears that the probe total temperature measurements are accurate to within ±1 K. Experiments using the probe downstream of a high-pressure turbine stage are than described. Both high and low-frequency components of the flow total temperature can be accurately resolved with the present technique. The probe measures a time-averaged flow total temperature that is in good agreement with thermocouple measurements made downstream of the rotor. Frequencies as high as 182 kHz have been detected in the spectral analysis of the heat flux signals from the total probe. Through comparison with fast-response aerodynamic probe measurements, it is demonstrated that the current measurement location, the total temperature fluctuations arise mainly due to the isentropic extraction of work by the turbine. The present total temperature probe is demonstrated to be an accurate, robust, fast-response device that is suitable for operation in a turbomachinery environment.

Copyright © 1998 by The American Society of Mechanical Engineers
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