This paper describes how allowance for the thermal effects of non-adiabatic flow, altered boundary layer development, changes in tip clearances and changes in seal clearances have been incorporated into a general gas turbine transient program. This program has been applied to a two-spool bypass engine. Revised predictions of surge margins in three common tn"ns Lents have been obtained. When the eneine undergoes a 'cold' acceleration, the thermal effects on the trajectory and on the surge line give a much increased proportion of unused surge margin in the H.P.Co. pressor, as compared to adiabatic predictions. In a 'hot' a,;celeration this iITprovement is considerably reduced.
CITATION STYLE
Maccallum, N. R. L., & Pilidis, P. (1985). The Prediction of Surge Margins During Gas Turbine Transients. In Proceedings of the ASME Turbo Expo (Vol. 1-A). American Society of Mechanical Engineers (ASME). https://doi.org/10.1115/85-GT-208
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