This application relates to the field of aero-engine aerodynamic stability design and
simulation technology, and discloses a method for predicting the stability boundary under compressor
back pressure disturbance in a whole-engine environment. The method includes the following steps: constructing a low-dimensional lumped parameter model of the whole
system, including a rotating component excitation disk model and a stationary component cavity
piping model. By injecting time-varying unsteady heat source terms into the
combustion chamber cavity
energy equation, the pressure pulsation environment inside the
combustion chamber is simulated. While maintaining a constant rotational speed, a numerical propulsion strategy is used to gradually increase the average heat release rate to improve the
back pressure, and a set of unsteady conservation equations is used for transient solution. The aerodynamic parameter response is monitored in real time, and the
instability state is identified based on
backflow or oscillation criteria to accurately locate the surge boundary point. Finally, the dynamic stability
boundary line under
back pressure disturbance is generated by fitting across the entire rotational speed range. This invention can quantitatively evaluate the
impact of
combustion unsteady disturbances on compressor stability, providing an accurate basis for engine stability design.