IGTC-62 Heat Transfer in Turbo-Machinery(Session B-6 BLADE COOLING I)

Bayley F.J.

This paper describes recent research concerned with heat transfer in the gas turbine, concentrating upon processes in machinery rather than the no less important combustion system. Studies of the conditions associated with turbine blading, especially those determining the local convective coefficients between the hot mainstream gas and the blade outer surfaces are considered in the first part of the paper. The remainder reports research upon the increasingly crucial problems of heat transfer to turbine and compressor discs. Attention is first given to the rotor-stator system, commonly found in turbines. Phenomena in this region are critical to disc life through their determination of the mean and transient metal temperatures which are set not only by the prevailing heat transfer conditions but also by the extent of ingress of mainstream gas to the 'wheel-space'. A geometry also found in machinery, especially compressors, involves cavities between two corotating discs, from which a wide range of unusual flow regimes are reported. Finally long cavities, or hollow shafts, are shown to reveal another class of novel flows.

IGTC-62 Heat Transfer in Turbo-Machinery(Session B-6 BLADE COOLING I)

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