Numerical analysis of compressor blade flutter in modern gas turbine engines

Authors

V. Vedeneev - Lomonosov Moscow State University, Russia
M. Kolotnikov, P. Makarov - Gas-turbine Engineering Research and Production Center "Salut", Russia

Abstract

Blade flutter of the modern gas turbine engines is turning into one of the main issues that engine designers have to face. Today there is no general method for a reliable prediction of compressor blade flutter and flutter suppression in a wide range of engine operating regimes, especially at the engine design phase. Engine designers use internal criteria of their companies and approaches based on their own experience in engine design and refinement. In this paper we describe development of numerical method and present results of flutter onset prediction based on energy method. Analysis is limited by the condition of unstalled air flow through the blade passage, which is typical for compressor operating regimes. The problem is solved in the 3-D formulation. The developed method is applied to flutter prediction of real compressor blade wheels of a modern gas turbine engine; results are verified by compressor and full engine test data. It is shown that the prediction of flutter onset is rather reliable. Influence of numerical parameters and modeling features on flutter prediction is studied.