Abstract: The stable operating ranges of the fan/compressor, combustor and turbine of the aero-engine directly determine the performance and stability of the engine. While pursuing high aerodynamic performance, high turbine temperature and low emission, the aerodynamic, aeroelastic and combustion stability problems of the main components become particularly prominent. It is of great theoretical and engineering values to develop rapid and accurate stability assessment methods and stability control techniques and incorporate them into the engine design process. This paper gives a review of the research progress of a variety of semi-analytical models developed based on the small perturbation method and the eigenvalue theory. These methods can effectively evaluate the fan/compressor aerodynamic instability and predict the flutter and main/afterburner combustor thermal instability in the design phase. On this basis, the further stability control design can be conducted to save the cost of experiments and simulations.

Key words: eigenvalue theory, aero-engine, small perturbation method, flow stability, combustion stability, aeroelastic stability