Systems and methods related to control of gas trubine startup

A system comprising:

• a gas turbine comprising a compressor, a combustor, and, drivingly coupled to the compressor, a turbine, wherein the turbine includes a rotor comprising a rotor velocity and a rotor acceleration during the startup sequence;
• and
• a control system operably connected to the gas turbine for controlling an operation thereof, the control system comprising:
• a hardware processor;
• and
• a machine readable storage medium on which is stored instructions that cause the hardware processor to execute a process related to control of the gas turbine;
• wherein the process comprises:
• determining an originally scheduled startup duration for the gas turbine, the originally scheduled startup duration comprising a calculated duration for the startup sequence given:
• a) an initial rotor velocity at a beginning of the startup sequence;
• and b) a final rotor velocity at an end of the startup sequence;
• initializing the beginning of the startup sequence by applying a startup torque to the rotor;
• measuring an intermediate rotor velocity at an intermediate time within the startup sequence;
• determining a recalculated remaining startup duration, wherein the recalculated remaining startup duration comprises a duration calculated as necessary to achieve the final rotor velocity given the intermediate rotor velocity;
• determining a remaining portion of the originally scheduled startup duration based on the intermediate time, the remaining portion of the originally scheduled startup duration comprising the originally scheduled startup duration minus an elapsed portion thereof;
• calculating a time multiplier based on a comparison of the recalculated remaining startup duration to the remaining portion of the originally scheduled startup duration;
• and
• scaling the rotor acceleration per the time until the final rotor velocity is achieved by the turbine.