The Prediction of Surge Margins During Gas Turbine Transients

6Citations
Citations of this article
5Readers
Mendeley users who have this article in their library.
Get full text

Abstract

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.

Cite

CITATION STYLE

APA

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

Register to see more suggestions

Mendeley helps you to discover research relevant for your work.

Already have an account?

Save time finding and organizing research with Mendeley

Sign up for free