Gaseous fuel compression and control method

A method of gaseous fuel compression and control for a turbogenerator having a combustor supplied with gaseous fuel by a pair of helical flow compressor/turbine permanent magnet motor/generators in series separate from the turbogenerator, the method comprising the steps of:

• establishing the turbogenerator speed required based upon the power load requirements of the turbogenerator;
• establishing the turbogenerator combustion temperature or turbine exhaust gas temperature based on the power load requirements of the turbogenerator;
• establishing the gaseous fuel pressure requirements to produce the established turbogenerator speed and established temperature;
• and
• commanding the pair of helical flow compressor/turbine permanent magnet motor/generators in series to produce the established gaseous fuel pressure by controlling the torque or speed of the individual helical flow compressor/turbine permanent magnet motor/generators,
• said helical flow compressor/turbine permanent magnet motor/generators functioning as turbines when the pressure of the gaseous fuel supplied is greater than that needed by the turbogenerator combustor, and functioning as compressors when the pressure of the gaseous fuel supplied is less than that needed by the turbogenerator combustor, with a smooth transition between turbine and compressor functions.

A method of gaseous fuel compression and control for a turbogenerator supplied with gaseous fuel by a helical flow compressor/turbine driven by a separate permanent magnet motor/generator, comprising the steps of:

• establishing the turbogenerator speed required based upon the power load requirements of the turbogenerator;
• establishing a turbogenerator temperature based on the power load requirements of the turbogenerator;
• establishing the gaseous fuel pressure requirements to produce the established turbogenerator speed and established turbogenerator temperature;
• and
• commanding the helical flow compressor/turbine to produce the established gaseous fuel pressure,
• said helical flow compressor/turbine functioning as a turbine when the pressure of the gaseous fuel supplied is greater than that needed by the turbogenerator combustor, and functioning as a compressor when the pressure of the gaseous fuel supplied is less than that needed by the turbogenerator combustor, with a smooth transition between turbine and compressor functions.

A method of gaseous fuel compression and control for a turbogenerator having a combustor supplied with gaseous fuel by a helical flow compressor/turbine driven by a permanent magnet motor/generator, said turbogenerator having a rotational speed, a torque, a power load, a combustion temperature, a turbine exhaust gas temperature, and a gaseous fuel pressure requirement, and said helical flow compressor/turbine having a rotational speed and a torque, the method comprising the steps of:

• establishing the turbogenerator speed required based upon the power load requirements of the turbogenerator;
• establishing the turbogenerator combustion temperature or turbine exhaust gas temperature based on the power load requirements of the turbogenerator;
• establishing the gaseous fuel pressure requirements to produce the established turbogenerator speed and established temperature;
• and
• commanding the helical flow compressor/turbine to produce the established gaseous fuel pressure by controlling the torque or speed of the helical flow compressor/turbine,
• said permanent magnet motor/generator driving said helical flow compressor/turbine distinct from said turbogenerator, and said helical flow compressor/turbine functioning as a turbine when the pressure of the gaseous fuel supplied is greater than that needed by the turbogenerator combustor, and functioning as a compressor when the pressure of the gaseous fuel supplied is less than that needed by the turbogenerator combustor, with a smooth transition between turbine and compressor functions.

A method of gaseous fuel compression and control for a turbogenerator having a combustor supplied with gaseous fuel by a pair of helical flow compressor/turbine permanent magnet motor/generators in series, said turbogenerator having a rotational speed, a torque, a power load, a combustion temperature, a turbine exhaust gas temperature, and a gaseous fuel pressure requirement, and each of said pair of helical flow compressor/turbine permanent magnet motor/generators having a rotational speed and a torque, the method comprising the steps of:

• establishing the turbogenerator speed required based upon the power load requirements of the turbogenerator;
• establishing the turbogenerator combustion temperature or turbine exhaust gas temperature based on the power load requirements of the turbogenerator;
• establishing the gaseous fuel pressure requirements to produce the established turbogenerator speed and established temperature;
• and
• commanding the pair of helical flow compressor/turbine permanent magnet motor/generators in series to produce the established gaseous fuel pressure by controlling the torque or speed of the individual helical flow compressor/turbine permanent magnet motor/generators,
• said permanent magnet motor/generators driving said helical flow compressor/turbines distinct from said turbogenerator, and said helical flow compressor/turbines functioning as turbines when the pressure of the gaseous fuel supplied is greater than that needed by the turbogenerator combustor, and functioning as compressors when the pressure of the gaseous fuel supplied is less than that needed by the turbogenerator combustor, with a smooth transition between turbine and compressor functions.