Surge recovery system and methods
A surge control system includes a rotor system with at least one compressor section and at least one turbine section operably coupled to a shaft. The surge control system also includes sensors configured to collect sensor data from the rotor system, an electric motor operably coupled to the rotor system, and a controller. The controller is operable to detect surge event from the sensor data, determine an amount of power to apply to the rotor system, and increase the amount of power provided to the rotor system to recover from the surge event.
1 . A single spool gas turbine engine comprising:
a power source;
a first compressor section;
a first turbine section;
a combustor section between the first compressor section and the first turbine section;
a first shaft operably coupling the first compressor section and the first turbine section, wherein the first compressor section, the first turbine section, and the first shaft provide a first rotor system;
a controller configured to collect or synthesize data from a sensor from at least one of the first rotor system and the combustor section;
a first electric motor disposed on a second shaft operably coupled to the first rotor system via a geared interface, the first electric motor configured to provide a power assist to the first shaft in response to a surge event in the first compressor section, wherein the controller is configured to:
detect the surge event for the first compressor section of the gas turbine engine;
determine, by a predefined multivariable table dependent on at least one of sensed engine parameters, synthesized engine parameters, or time elapsed since detecting the surge event, an amount of power to apply to the first shaft of the gas turbine engine;
increasing a power provided to the first shaft by the amount of power determined by the predefined multivariable table;
monitoring a magnitude of the power commensurate with a severity of the surge event and loss in thrust due to the increasing of the power;
adjusting the magnitude of the power commensurate with the severity of the surge event and loss in thrust due to the increasing of the power; and
increasing a stability margin of the first compressor section in response to the adjusting.
2 . The gas turbine engine of claim 1 , wherein the power source is an auxiliary power unit.
3 . The gas turbine engine of claim 2 , wherein the first electric motor is configured to act as a generator and extract power from the first shaft in response to a second surge event in the first compressor section.
4 . The gas turbine engine of claim 2 , wherein the first shaft is a high speed spool.
5 . The gas turbine engine of claim 1 , wherein the first electric motor is operable to apply torque and speed to the first rotor system to recover from the surge event of the first compressor section.
6 . The gas turbine engine of claim 1 , wherein the second shaft of the first electric motor is aligned in parallel with the first shaft.
7 . The gas turbine engine of claim 1 , wherein the second shaft of the first electric motor is parallel with the first shaft.
8 . The gas turbine engine of claim 1 , wherein the amount of power is applied in between surge cycles.
9 . The gas turbine engine of claim 1 , wherein the amount of power is applied during the surge event.