Compressor stall mitigation

A method for operating a hybrid-electric propulsion system of an aircraft, the hybrid-electric propulsion system comprising a gas turbine engine having a compressor, an electric machine coupled to the compressor, and an engine controller, the method comprising:

• sensing data indicative of pressures within the compressor of the gas turbine engine with a plurality of high-frequency sensors arranged at different axial locations of the compressor and capable of sensing data at frequencies from 500 hertz to 10 kilohertz;
• monitoring the plurality of high-frequency sensors to determine a location within the compressor in which conditions are within a threshold of a stall limit for the compressor based at least in part on the sensed data indicative of the pressures within the compressor of the gas turbine engine;
• selecting a torque profile that includes an amount of torque and a frequency of torque to match the location within the compressor in which conditions are within the threshold of the stall limit;
• and
• modifying a torque of the compressor according to the selected torque profile using the electric machine in response to determining the location within the compressor to reduce a risk of compressor stall;
• wherein modifying the torque of the compressor using the electric machine comprises modifying the torque of the compressor using the electric machine within an amount of time less than 0.5 seconds from determining conditions within the compressor are within the threshold of the stall limit for the compressor.