초록 ▼

A gas turbine electric powerplant, preferably driven by an aeroderivative turbine engine of split shaft design. The gas turbine engine is coupled to a speed reducer, which is in turn coupled to an electric generator. An engine mount is provided that ensures that the gas turbine engine will remain i

A gas turbine electric powerplant, preferably driven by an aeroderivative turbine engine of split shaft design. The gas turbine engine is coupled to a speed reducer, which is in turn coupled to an electric generator. An engine mount is provided that ensures that the gas turbine engine will remain in proper alignment with the speed reducer and generator, even during the thermal expansion or contraction thereof. Preferably, the components comprising the powerplant are mounted to a common, transportable base, so that the powerplant can be delivered to various locations. An overspeed control system is provided for ensuring that a runaway condition of the gas turbine engine does not occur should the gas turbine engine become disconnected from the speed reducer or generator. Sensors are used to monitor multiple operating conditions of the powerplant. A microprocessor-based control system communicates with the sensors, and is further adapted to activate the overspeed control system if an overspeed condition is detected.

대표청구항 ▼

What is claimed is: 1. A gas turbine electric powerplant, comprising: an aeroderivative split-shaft gas turbine engine; an engine mounting system for affixing said gas turbine engine to a mounting surface, said engine mounting system comprising: a mounting frame substantially encircling a portion o

What is claimed is: 1. A gas turbine electric powerplant, comprising: an aeroderivative split-shaft gas turbine engine; an engine mounting system for affixing said gas turbine engine to a mounting surface, said engine mounting system comprising: a mounting frame substantially encircling a portion of said gas turbine engine; a plurality of mounting shafts affixed to and spaced about the circumference of said gas turbine engine; and a plurality of linear bearings affixed to said mounting frame, each linear bearing provided to receive a corresponding one of said mounting shafts; a speed reducer coupled to an output shaft of said gas turbine engine, said speed reducer having an output shaft that rotates at a slower speed than said output shaft of said gas turbine engine; an electric generator coupled to said output shaft of said speed reducer, said electric generator selected to provide a predetermined electric power output when driven by said gas turbine engine; a fuel valve for metering a supply of fuel to said gas turbine engine; a cooling system for providing cooling fluid to said speed reducer and said gas turbine engine, said cooling system having at least one cooling pump and at least one cooling fluid reservoir; a turbine engine overspeed control system, said system adapted to slow or shut down said turbine engine if an overspeed condition thereof is detected; sensors placed at various locations on said gas turbine electric powerplant, said sensors for monitoring and reporting on a plurality of conditions selected from the group consisting of turbine speed, turbine engine exhaust gas temperature, turbine engine inlet temperature, turbine engine oil temperature and pressure, gearbox oil temperature and pressure, gearbox output shaft speed, generator output voltage, fuel flow rate, and inlet guide vane position; and a microprocessor-based control system for receiving signals from said sensors and controlling said gas turbine electric powerplant, said microprocessor-based control system further adapted to detect an overspeed condition of said gas turbine engine and to activate said turbine engine overspeed control system in response thereto. 2. The gas turbine electric powerplant of claim 1, further comprising a transportable mounting base for receiving the components comprising said gas turbine electric powerplant. 3. The gas turbine electric powerplant of claim 1, wherein the components comprising said gas turbine electric powerplant are mounted to a non-transportable base. 4. The gas turbine electric powerplant of claim 3, wherein said non-transportable base is a concrete floor. 5. The gas turbine electric powerplant of claim 1, wherein said powerplant operates on a liquid fuel selected from the group consisting of gasoline, diesel fuel, jet fuel, kerosene and isopropyl alcohol. 6. The gas turbine electric powerplant of claim 1, wherein said powerplant operates on a gaseous fuel selected from the group consisting of hydrogen, natural gas, propane, isopropane and butane. 7. The gas turbine electric powerplant according to claims 5 or 6, wherein the thermal energy output of said fuel is at least about 600 BTU per cubic foot. 8. The gas turbine electric powerplant of claim 1, wherein said fuel valve has an integrated microprocessor in electrical communication with said microprocessor-based control system. 9. The gas turbine electric powerplant of claim 1, wherein said turbine engine overspeed control system includes a compression relief system, said compression relief system adapted, upon occurrence of an overspeed condition of said gas turbine engine, to draw operating air away from a combustion section of said gas turbine engine, and to direct said air to the atmosphere or to a collecting device. 10. The gas turbine electric powerplant of claim 1, wherein said turbine engine overspeed control system includes an air directing system, said air directing system adapted, upon occurrence of an overspeed condition of said gas turbine engine, to deoptimize an angle that air enters a compressor section of said gas turbine engine. 11. The gas turbine electric powerplant of claim 1, further comprising an alternator for powering said at least one cooling fluid pump, said alternator driven by a belt and pulley, said pulley located on a coupling connecting said gearbox and said electric generator. 12. The gas turbine electric powerplant of claim 1, wherein said cooling system utilizes a separate cooling loop for cooling each of said speed reducer and said turbine engine, each cooling loop having a cooling pump connected to a cooling fluid reservoir. 13. The gas turbine electric powerplant of claim 12, further comprising a heat exchanger in each cooling loop for assisting in reducing the temperature of said cooling fluid. 14. The gas turbine electric powerplant of claim 13, further comprising a cooling fan located on each of said heat exchangers, said cooling fan in electrical communication with said microprocessor-based control system. 15. The gas turbine electric powerplant of claim 1, wherein said output shaft rotational speed of said speed reducer is about 1,800 revolutions per minute. 16. The gas turbine electric powerplant of claim 15, wherein said electric generator produces approximately 1.2 MW of power when driven by said output shaft of said speed reducer. 17. A transportable gas turbine electric powerplant, comprising: a common base for receiving the components comprising said gas turbine electric powerplant; an aeroderivative split-shaft gas turbine engine; an engine mounting system for affixing said gas turbine engine to a mounting surface, said engine mounting system comprising: a mounting frame substantially encircling a portion of said gas turbine engine and connected to said common base; a plurality of mounting shafts affixed to the circumference of said gas turbine engine and substantially uniformly spaced; and a plurality of linear bearings affixed to said mounting frame, each linear bearing provided to receive a corresponding one of said mounting shafts; a speed reducer coupled to an output shaft of said gas turbine engine, said speed reducer adapted to provide an output speed of approximately 1,800 revolutions per minute at substantially normal gas turbine engine operating speed; a permanent magnet generator coupled to an output shaft of said speed reducer, said generator adapted to provide about 1.2 MW of 3-phase, 480 volt AC power when driven at approximately 1,800 revolutions per minute; a fuel valve for metering a supply of fuel to said gas turbine engine; a cooling system for providing cooling fluid to said speed reducer and said gas turbine engine, said cooling system having at least one cooling pump and at least one cooling fluid reservoir; an alternator for powering said at least one cooling fluid pump, said alternator driven by a belt and pulley, said pulley located on a coupling connecting said gearbox and said permanent magnet generator; a compression relief system installed on said gas turbine engine, said compression relief system adapted, upon occurrence of an overspeed condition of said gas turbine engine, to draw air away from an inlet portion of a combustion section of said gas turbine engine; an air directing system installed on said gas turbine engine, said air directing system adapted, upon occurrence of an overspeed condition of said gas turbine engine, to deoptimize an angle that air impinges a set of inlet guide vanes located approximate a first stage of a compressor section of said gas turbine engine; sensors placed at various locations on said transportable gas turbine electric powerplant, said sensors for monitoring and reporting on a plurality of conditions selected from the group consisting of turbine speed, turbine engine exhaust gas temperature, turbine engine inlet temperature, turbine engine oil temperature and pressure, gearbox oil temperature and pressure, gearbox output shaft speed, generator output voltage, fuel flow rate, and inlet guide vane position; and a microprocessor-based control system for receiving signals from said sensors and controlling said transportable gas turbine electric powerplant, said microprocessor-based control system further adapted to detect an overspeed condition of said gas turbine engine and to activate said compression relief and said air directing systems in response thereto. 18. The transportable gas turbine electric powerplant of claim 17, wherein said powerplant operates on a liquid fuel selected from the group consisting of gasoline, diesel fuel, jet fuel, kerosene and isopropyl alcohol. 19. The transportable gas turbine electric powerplant of claim 17, wherein said powerplant operates on a gaseous fuel selected from the group consisting of hydrogen, natural gas, propane, isopropane and butane. 20. The transportable gas turbine electric powerplant according to claims 18 or 19, wherein the thermal energy output of said fuel is at least about 600 BTU per cubic foot. 21. The transportable gas turbine electric powerplant of claim 17, wherein said fuel valve has an integrated microprocessor in electrical communication with said microprocessor-based control system. 22. The transportable gas turbine electric powerplant of claim 17, wherein said cooling system utilizes a separate cooling loop for cooling each of said speed reducer and said turbine engine, each cooling loop having a cooling pump connected to a cooling fluid reservoir. 23. The transportable gas turbine electric powerplant of claim 22, further comprising a heat exchanger in each cooling loop for assisting in reducing the temperature of said cooling fluid. 24. The transportable gas turbine electric powerplant of claim 23, further comprising a cooling fan located on each of said heat exchangers, said cooling fan in electrical communication with said microprocessor-based control system. 25. The transportable gas turbine electric powerplant of claim 17, further comprising an operator interface for interacting with said microprocessor-based control system.