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US 5,850,733 AGranted
Gaseous fuel compression and control system and method
AssigneeCapstone Turbine Corporation
InventorsRobert W. Bosley, Edward C. Edelman, Ronald F. Miller
Life of this patent
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Abstract
A gaseous fuel compression and control system is disclosed which utilizes one or more helical flow compressor/turbine integrated with a permanent magnet motor/generator and driven by a torque controlling inverter to compress or expand gaseous fuels, precisely control fuel pressure and flow, and precisely control the operations (speed, combustion temperature and output power) of a gaseous fuel fired turbogenerator.
Claims20
A gaseous fuel compression and control system, comprising:
- a turbogenerator set including a turbogenerator and turbogenerator power controller, said turbogenerator including a compressor, a turbine, a combustor with a plurality of gaseous fuel nozzles and a plurality of air inlets, a recuperator, and a permanent magnet motor/generator;
- a first helical flow compressor/turbine;
- a first motor operably associated with said first helical flow compressor/turbine to drive said first helical flow compressor/turbine;
- a first helical flow compressor/turbine motor inverter drive operably associated with said first helical flow compressor/turbine motor to provide electrical power to said first helical flow compressor/turbine motor and receive operational data from said first helical flow compressor/turbine motor;
- a second helical flow compressor/turbine;
- a second motor operably associated with said second helical flow compressor/turbine to drive said second helical flow compressor/turbine;
- and
- a second helical flow compressor/turbine motor inverter drive operably associated with said second helical flow compressor/turbine motor to provide electrical power to said second helical flow compressor/turbine motor and receive operational data from said second helical flow compressor/turbine motor;
- said first helical flow compressor/turbine receiving gaseous fuel and supplying intermediately pressurized gaseous fuel to the second helical flow compressor/turbine and said second helical flow compressor/turbine supplying pressurized gaseous fuel to the gaseous fuel nozzles of said turbogenerator combustor, said turbogenerator compressor/turbine supplying compressed combustion air to said air inlets of said turbogenerator combustor,
- said first and said second helical flow compressor/turbine motor inverter drives also operably associated with said turbogenerator power controller to receive control signals from said turbogenerator power controller, said turbogenerator power controller also receiving operational data from said helical flow compressor/turbine motor inverter and turbogenerator parameter signals from said turbogenerator.
7 more elements
Dependencies are inferred from the claim text.