Patent ID: 6070404
Filing Date: 2000-06-06
Classification: F01D,F02C,F04D

Abstract:
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 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; andcommanding 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 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.