The present disclosure describes a micro gas turbine flameless heater, in which the heat is generated by burning fuel in a gas turbine engine, and the heater output air mixture is generated by transferring the heat in the gas turbine exhaust to the cold air drawn from the ambient environment. The pr
The present disclosure describes a micro gas turbine flameless heater, in which the heat is generated by burning fuel in a gas turbine engine, and the heater output air mixture is generated by transferring the heat in the gas turbine exhaust to the cold air drawn from the ambient environment. The present disclosure also describes component geometries and system layout for a gas turbine power generation unit that is designed for simple assembly, disassembly, and component replacement. The present disclosure also allows for quick removal of the rotating components of the gas turbine engine in order to reduce assembly and maintenance time. Furthermore, the present disclosure describes features that help to maintain safe operating temperatures for the bearings and structures of the gas turbine engine power turbine. Lastly, the present disclosure describes features of a fuel capture system that allow the injection of wellhead gas, which typically is a mixture of gaseous and liquid fuels, into the combustion chamber, and also describes methods of incorporating afterburners in the gas turbine engine, such that the gas turbine engine system can use wellhead gas to power equipment and reduce emissions from flaring in oil and gas applications.
대표청구항▼
1. A gas turbine heater comprising: i) a gas turbine engine comprising: a shaft,a compressor configured to rotate about the shaft, and to accept ambient air through a compressor inlet, and to pressurize the air;a combustion chamber in fluid communication with an outlet of the compressor, the combust
1. A gas turbine heater comprising: i) a gas turbine engine comprising: a shaft,a compressor configured to rotate about the shaft, and to accept ambient air through a compressor inlet, and to pressurize the air;a combustion chamber in fluid communication with an outlet of the compressor, the combustion chamber being configured to receive combustible fuel from a fuel source and to receive air from the outlet of the compressor, such that an air-fuel mixture is created inside the combustion chamber;an igniter, at least a portion of which is positioned inside the combustion chamber, the igniter being configured to ignite the air-fuel mixture inside the combustion chamber, thereby generating pressurized, heated air in the combustion chamber; anda turbine in fluid communication with an outlet of the combustion chamber, the turbine being configured to rotate about the shaft and extract shaft power from the pressurized, heated air received from the combustion chamber outlet, thereby providing shaft power to drive the compressor;ii) a fan configured to draw ambient air;iii) a gas turbine air starter configured to provide air for starting the gas turbine engine;iv) an electric generator configured to generate electric energy to power the air starter and the fan;v) an enclosure configured such that within the enclosure, exhaust gas exiting a turbine outlet mixes with the ambient air drawn by the fan to create a stream of heated air;vi.) a heater outlet through which the stream of heated air is directed out of the enclosure; andvii) a controller configured to control fan power of the fan to create a desired temperature of the stream of heated air at the gas turbine heater outlet. 2. The gas turbine heater of claim 1, further comprising a fuel manifold that comprises: i) a pressure regulator configured to control pressure of combustible fuel supplied to the combustion chamber,ii) an ignition fuel flow passage establishing fluid communication between the fuel source and the combustion chamber, and the ignition fuel flow passage comprises: an ignition fuel orifice configured for restricting flow of combustible fuel into the combustion chamber during an ignition event; andan ignition fuel valve configured for controlling the flow of combustible fuel into the ignition fuel orifice during an ignition event; andiii) a second fuel flow passage establishing fluid communication between the fuel source and the combustion chamber, and the second fuel flow passage comprises a fuel valve configured for controlling the flow of additional combustible fuel into the combustion chamber. 3. The gas turbine heater of claim 1, wherein the controller is configured to receive one or more input signals indicative of engine performance metrics, and to generate one or more output signals that control the air starter and the fan. 4. The gas turbine heater of claim 1, wherein the compressor and turbine of the gas turbine engine are components of a turbocharger. 5. The gas turbine heater of claim 1, wherein the enclosure houses: a) the gas turbine engine, wherein the gas turbine engine is configured such that the gas turbine exhaust flows into the enclosure, andb) the fan, andwherein the enclosure further comprises: i) a first air inlet port in fluid communication with the fan, wherein the fan is configured to draw ambient air in through the first air inlet port and pump ambient air into the enclosure, andii) a second air inlet port in fluid communication with a compressor inlet, wherein the compressor of the gas turbine engine is configured to draw ambient air into the gas turbine engine through the second air inlet port. 6. The gas turbine heater of claim 1, wherein the enclosure houses the gas turbine engine and the fan, and the enclosure further comprises: i) an air inlet port in fluid communication with the fan inlet, and the fan is configured to draw ambient air through the air inlet port;ii) a first duct having an inlet in fluid communication with the fan outlet, and the duct is configured to receive ambient air drawn by the fan;iii) an air inlet port in fluid communication with the compressor inlet, and the compressor is configured to draw ambient air through the air inlet port into the gas turbine engine;iv) a second duct having an inlet in fluid communication with the turbine outlet and being configured to receive gas turbine exhaust; andv) a mixing chamber comprising: a first inlet configured to receive ambient air from the first duct; anda second inlet configured to receive gas turbine exhaust from the second duct;such that the ambient air and the gas turbine exhaust mix inside the mixing chamber to create warm air, and the warm air exits the mixing chamber through the heater outlet. 7. The gas turbine heater of claim 1 further comprising an inlet flow diverter, and the inlet flow diverter comprises: i) an outlet port in fluid communication with the compressor inlet,ii) a first inlet port configured for receiving air from the air starter, andiii) a second inlet port having a controllable valve configured to open or close to control fluid communication between the compressor inlet and the ambient air,and the gas turbine heater being configured such that during gas turbine engine startup, the valve can be configured in a closed position to force substantially all of the ambient air drawn by the air starter into the compressor, and during steady state gas turbine engine operation, the valve can be configured in an open position to allow the compressor to draw in air from the ambient. 8. The gas turbine heater of claim 1, in which the electric generator is a component of a standalone motor-generator set that is not powered by the gas turbine engine. 9. The gas turbine heater of claim 1, wherein the ambient air drawn by the fan is heated by 180 degrees F. 10. The gas turbine heater of claim 1, wherein the controller is configured to control fuel flow to the combustion chamber to create a desired temperature of the stream of heated air at the gas turbine heater outlet.
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