US6070404A
Expired / Lapsed
US
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Gaseous fuel compression and control method
Assignee: Capstone Green Energy Corp
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Filing: 1998-05-27
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Granted: 2000-06-06
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Expires: 2018-05-27
Abstract
Abstract A gaseous fuel compression and control system is disclosed which utilizes a 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.
Inventors
- 👤 Robert W. Bosley
- 👤 Edward C. Edelman
- 👤 Ronald F. Miller
Bibliographic Details
Application Number
—
Jurisdiction
US
Data Source
google_patents
Last Synchronized
2026-10-29 02:46
CPC Classifications
F; F04; F04D; F04D25/00; F04D25/02; F04D25/06; F01; F01D; F01D15/00; F01D15/10; F01D5/00; F01D5/02; F01D5/04; F02; F02C; F02C3/00; F02C3/20; F02C3/22; F02C7/00; F02C7/22; F02C7/236; F02C9/00; F02C9/26; F02C9/30; F04D23/00; F04D23/008; F04D27/00; F04D27/02
Claims Analysis
Total Claims: 18
Claim 1
Independent Claim
167 words
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; 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 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.
Claim 2
Independent Claim
167 words
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; 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 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.
Claim 3
Independent Claim
180 words
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.
Claim 4
Independent Claim
180 words
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.
Claim 5
Independent Claim
143 words
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.
Claim 6
Independent Claim
143 words
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.
Claim 7
Dependent Claim
29 words
The method of gaseous fuel compression and control of claim 3 wherein the turbogenerator temperature established based on the power load requirements of the turbogenerator is turbogenerator combustion temperature.
Claim 8
Dependent Claim
31 words
The method of gaseous fuel compression and control of claim 3 wherein the turbogenerator temperature established based on the power load requirements of the turbogenerator is turbogenerator turbine exhaust gas temperature.
Claim 9
Dependent Claim
34 words
The method of gaseous fuel compression and control of claim 3 wherein the helical flow compressor/turbine is commanded to produce the established gaseous fuel pressure by controlling the torque of the helical flow compressor/turbine.
Claim 10
Dependent Claim
34 words
The method of gaseous fuel compression and control of claim 3 wherein the helical flow compressor/turbine is commanded to produce the established gaseous fuel pressure by controlling the speed of the helical flow compressor/turbine.
Claim 11
Dependent Claim
52 words
The method of gaseous fuel compression and control of claim 3 wherein the turbogenerator temperature established based on the power load requirements of the turbogenerator is turbogenerator combustion temperature, and the helical flow compressor/turbine is commanded to produce the established gaseous fuel pressure by controlling the torque of the helical flow compressor/turbine.
Claim 12
Dependent Claim
52 words
The method of gaseous fuel compression and control of claim 3 wherein the turbogenerator temperature established based on the power load requirements of the turbogenerator is turbogenerator combustion temperature, and the helical flow compressor/turbine is commanded to produce the established gaseous fuel pressure by controlling the speed of the helical flow compressor/turbine.
Claim 13
Dependent Claim
54 words
The method of gaseous fuel compression and control of claim 3 wherein the turbogenerator temperature established based on the power load requirements of the turbogenerator is turbogenerator turbine exhaust gas temperature, and the helical flow compressor/turbine is commanded to produce the established gaseous fuel pressure by controlling the torque of the helical flow compressor/turbine.
Claim 14
Dependent Claim
54 words
The method of gaseous fuel compression and control of claim 3 wherein the turbogenerator temperature established based on the power load requirements of the turbogenerator is turbogenerator turbine exhaust gas temperature, and the helical flow compressor/turbine is commanded to produce the established gaseous fuel pressure by controlling the speed of the helical flow compressor/turbine.
Claim 15
Independent Claim
214 words
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.
Claim 16
Independent Claim
214 words
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.
Claim 17
Independent Claim
231 words
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.
Claim 18
Independent Claim
231 words
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.
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USPTO Annuity & Maintenance Windows
| Annuity Stage | Window Opens | Payment Deadline | Surcharge Period Until | Estimated Fee | Status |
|---|---|---|---|---|---|
| 3.5 Years (Year 4) | 2003-06-06 | 2003-12-06 | 2004-06-06 | $2000.00 | Window Closed / Lapsed |
| 7.5 Years (Year 8) | 2007-06-06 | 2007-12-06 | 2008-06-06 | $3760.00 | Window Closed / Lapsed |
| 11.5 Years (Year 12) | 2011-06-06 | 2011-12-06 | 2012-06-06 | $7700.00 | Window Closed / Lapsed |