Abstract: A power generation system and method in which a fuel gas is introduced into a combustor and at least a portion of the fuel gas is combusted in the combustor, producing an exhaust gas having no appreciable available oxygen. The exhaust gas is introduced as a working fluid into a gas turbine, thereby generating power. Cooling of the power generation system is accomplished using a cooling fluid selected from the group consisting of synthesis gas, natural gas, natural gas/steam mixture, flue gas, flue gas/steam mixture, and mixtures thereof.

Abstract: A fuel delivery system includes a fuel stabilization unit that removes dissolved oxygen from liquid fuel to increase the temperature at which the liquid fuel can be elevated without substantial formation of insoluble products. At least a portion of the fuel with reduced amounts of dissolved oxygen is vaporized prior to entering a combustion device to improve mixing and combustor performance.

Abstract: A method and apparatus for improved gas turbine efficiency and augmented power output employs a combustion turbine for electrical or mechanical power generation system in a simple or combined power generation cycle which contains air-to-fuel heat exchanger. The heat exchanger cools down portion of hot compressor discharge air utilized for cooling of hot gas turbine components, such as vanes and blades. Colder component cooling air allows for higher combustor firing temperatures thereby improving gas turbine efficiency and allowing for augmented power output. Simultaneously the heat exchanger pre-heats natural gas utilized for driving the gas turbine unit prior to entering a combustor of the gas turbine, which also allows for significant improvement of the cycle efficiency.

Abstract: A method for heating a fluid in a turbine engine is provided. The method includes channeling an exhaust flow through an exhaust duct of the turbine engine and coupling a panel to the exhaust duct. The panel includes a first wall and an opposite second wall that is spaced a distance from the first wall such that at least one passageway is defined within the panel. The fluid is supplied to the at least one passageway through an inlet defined at a first end of the passageway, such that heat is transferred from the exhaust flow to the fluid flowing through the panel. The fluid is injected into the turbine engine.

Abstract: A fuel system includes a fuel deoxygenator for removing oxygen from a liquid fuel. A vaporizer is in fluid communication with the fuel deoxygenator. The vaporizer vaporizes at least a portion of the liquid fuel to produce vaporized fuel. At least a portion of the vaporized fuel pre-mixes with oxidizer to reduce formation of undesirable emissions.

Abstract: In certain embodiments, a system includes a fuel heater. The fuel heater includes a first heat exchanger configured to receive compressed air from a compressor and to transfer heat from the compressed air to a cooled intermediate heat transfer media to generate a heated intermediate heat transfer media. The fuel heater also includes a second heat exchanger configured to receive the heated intermediate heat transfer media from the first heat exchanger and to transfer heat from the heated intermediate heat transfer media to a fuel. The first heat exchanger is configured to receive the cooled intermediate heat transfer media from the second heat exchanger.

Abstract: A combustion turbine engine that includes: a compressor; a combustor that receives fuel from a fuel line; a turbine; a heat exchange portion comprising a portion of the fuel line in heat transfer relationship with a heat source for heating the fuel; a rapid heating value meter disposed to test the heating value of the fuel that is configured to provide heating value test results within approximately 1 minute; a cold leg bypass comprising a fuel line that bypasses the heat exchange portion, the cold leg bypass being connected to the fuel line at an upstream fork and at a fuel mixing junction; and valves for controlling the fuel being directed through the heat exchange portion and the fuel being direct through the cold leg bypass; wherein the length of fuel line between the fuel mixing junction and the combustor is less than 20 meters.

Abstract: A method of controlling a combustion turbine engine, wherein the engine includes: a fuel line including a heat exchange portion; a heating value meter; a cold leg bypass comprising an alternate fuel line that bypasses the heat exchange portion, the cold leg bypass being connected to the fuel line at an upstream fork and at a fuel mixing junction, the fuel mixing junction being positioned such that a length of fuel line between it and the inlet to the combustor is short; and valves for controlling the amount of fuel being directed through the heat exchange portion; the method comprising: measuring the heating value of the fuel; determining a target fuel temperature range based on the heating value and a target Modified Wobbe Index range; and controlling the fuel that bypasses the heat exchange portion such that the temperature of the fuel is within the target temperature range.

Abstract: In certain embodiments, a system includes a fuel heater. The fuel heater includes a first heat exchanger configured to receive compressed air from a compressor and to transfer heat from the compressed air to feedwater. The fuel heater also includes a second heat exchanger configured to receive heated feedwater from the first heat exchanger and to transfer heat from the heated feedwater to a fuel.

Abstract: A gas turbine engine fuel system includes a fuel tank for storing fuel, a heat exchanger through which the fuel from the fuel tank can pass, a fuel pump located downstream from the heat exchanger for pumping the fuel, a fuel metering unit for metering the fuel pumped by the fuel pump, an additive tank for storing a fuel additive, an additive delivery subsystem for mixing the fuel additive with the fuel at or before the heat exchanger to generate a fuel and fuel additive mixture, and a combustor located downstream of the fuel metering unit where the fuel and fuel additive mixture is delivered for combustion. The fuel additive comprises a fuel stabilizer for reducing fuel coking.

Abstract: A waste heat utilization system and associated methods for preheating fuel for a turbine engine component. The turbine engine component includes at least one heat generating source. The system includes structure for applying heat from the at least one heat generating source to relatively cold fuel for the turbine engine component to preheat the fuel prior to ignition.

Abstract: The present invention relates to the processing of biomass, particularly but not exclusively poultry litter, to generate energy. A method is presented for generating power from biomass comprising a gasification process (44) involving the gasification of biomass to produce a combustible fuel gas and a power generation process (49) involving combustion of the combustible fuel gas to produce a combustion exhaust gas which is fed to a power generator (49) to generate power and a generator exhaust gas. The method further comprises placing compressed air (1) in thermal contact with the generator exhaust gas (47) to facilitate heat transfer between the compressed air and the generator exhaust gas, and feeding a first portion of compressed air that has thermally contacted the generator exhaust gas to the gasification process to assist in gasification of further biomass.

Abstract: A gas turbine engine that includes a compressor, a combustion stage, a turbine assembly, a fuel gas feed system for supplying fuel gas to a combustion stage of the gas turbine, an integrated fuel gas characterization system, and a buffer tank is disclosed. The integrated fuel gas characterization system may determine the heating value of the fuel and adjust either the airflow to the compressor or the fuel gas flow to the combustor to maintain a design fuel-to-air ratio.

Abstract: A system and method for recovering heat from dirty gaseous fuel (syngas), wherein the pressure of clean fuel gas is elevated to a pressure higher than that of the dirty syngas and then the pressurized clean fuel gas is fed to a heat recovery unit for heat exchange with the dirty syngas. Consequently, in the event of a leak in the heat recovery unit, the flow is from the clean fuel side to the dirty syngas side, thereby avoiding the possibility of contamination of the clean fuel gas.

Abstract: A method and system for heating fuel for a gas turbine engine by using excess heat energy in the engine exhaust gas to heat the fuel and returning the cooled exhaust gas back to the engine exhaust gas stream upstream of an emissions sensor is disclosed. The method and system comprises providing a heat exchanger having an exhaust gas passage and a fuel passage, extracting high temperature exhaust gas from the engine exhaust gas stream and passing the high temperature exhaust gas through the exhaust gas passage. Fuel is passed through the fuel passage where excess heat energy in the high temperature exhaust gas is used to heat the fuel. The temperature of the heated fuel is controlled by controlling the flow of the high temperature exhaust gas through the exhaust gas passage.

Abstract: The invention relates to an open-cooled component for a gas turbine having an outer wall which is subjected to hot gas and which at least partly defines a first cavity for a first medium and in which through-openings are arranged, which through-openings open into the cavity on the one side and into the hot-gas space on the other side, and having at least one second cavity for admixing a second medium, this second cavity being fluidically connected to the through-openings. In order to specify a component for a gas turbine with which flashback and spontaneous ignition during feeding of fuel into the cooling air can be reduced, it is proposed that the second cavity be formed by supply passages which are provided in the outer wall and are connected via transverse passages (4) to the through-openings designed as through-bores, so that the two media cannot be mixed until inside the through-bores.

Abstract: An apparatus, a system and a method by which fuel gas to drive a heat source is heated are provided. The apparatus includes a first gas passage by which at least a portion of the fuel gas is transported from an inlet to an outlet, the outlet being fluidly coupled to the heat source, a plurality of heat pipes in thermal communication, at respective first ends thereof, with the portion of the fuel gas transported by the first gas passage, and a heating element, fluidly coupled to the heat source to receive exhaust of the heat source, through which respective second ends of the heat pipes extend to be in position to be heated by the exhaust.

Abstract: A method for operating a firing system with a combustion chamber, in which a fuel is preheated and is supplied in the preheated state for combustion in the combustion chamber. The preheated temperature of the fuel is set higher for a part load of the firing system than with a basic load. In addition, the preheated temperature of the fuel is set using a variable obtained from the combustion in particular a load of the firing system. A firing system is also provided.

Abstract: A fuel heating system for fuel usable in a turbine engine. The fuel heating system may include at least one fuel heating chamber in communication with an exhaust stack of a turbine engine. The fuel heating chamber may be configured to allow exhaust gases to flow through the at least one fuel heating chamber. The fuel heating system may also include at least one conduit positioned in the fuel heating chamber. The conduit may be configured to receive fuel from a fuel source at a first temperature, allow the fuel to flow through the conduit, and exhaust the fuel at a second temperature that is higher than the first temperature.

Abstract: A secondary combustion system for a stage one turbine nozzle. The secondary combustion system may include a supply tube extending into the stage one nozzle, a number of injectors extending from the supply tube to an outer surface of the stage one nozzle, and an air gap surrounding each of the number of injectors.

Abstract: An LNG (liquefied natural gas) power plant has a heating/cooling device. The heating/cooling device is controlled by a command generated by a temperature control device. The temperature control device receives a heating value and a temperature of the fuel gas. The heating value of the fuel gas introduced to a gas turbine power generation unit from an LNG vaporization facility is detected by a heating value detector. The temperature of the fuel gas is detected by a temperature detector. A target temperature calculator installed in the temperature control device calculates a target temperature based on the heating value. A command generator installed in the temperature control device generates the command by comparing the target temperature and the fuel temperature.

Abstract: A combustor includes two upstream parts of fuel supply system supplying gaseous fuels of two types having different heating values from each other, a three-way fuel transfer valve merging the two upstream parts of fuel supply system with each other, a plurality of gaseous fuel supply subsystems supplying a combustion chamber with the gaseous fuels supplied through the three-way fuel transfer valve and branched, and a plurality of burners injecting, corresponding to each of the gaseous fuel supply subsystems, the gaseous fuel supplied from the gaseous fuel supply subsystem into the combustion chamber.

Abstract: The invention relates to a gas turbine, for energy generation, with a compressor, arranged coaxially to a rotor, mounted such as to rotate, for the compression of an inlet gaseous fluid, at least partly serving for combustion of a fuel in a subsequent annular combustion chamber, with generation of a hot working medium, with an annular diffuser arranged coaxially to the rotor, between the compressor and the annular combustion chamber, for distribution and deflection of the fluid, whereby a part of the fluid is diverted as cooling fluid for the turbine stages after the combustion chamber, by means of a dividing element, arranged in the fluid flow.

Abstract: A gas turbine engine is piloted with a pilot flow of fuel delivered to a combustor as a liquid. A first additional flow of the fuel is also delivered to the combustor as a liquid. A second additional flow of the fuel is vaporized and delivered to the combustor as a vapor. A fuel injector may have passageways associated with each of the three flows.

Abstract: A turbine engine is disclosed. The turbine engine may have a first compressor configured to pressurize inlet air, and a second compressor configured to further pressurize the inlet air. The turbine engine may also have a cooling circuit fluidly located to cool the inlet air after the inlet air is pressurized by the first compressor and before the inlet air is further pressurized by the second compressor. The cooling circuit may have a first heat exchanger configured to transfer heat from the inlet air to a fuel of the engine, and a second heat exchanger configured to transfer heat from exhaust of the engine to the fuel of the engine.

Abstract: A fuel system includes a fuel deoxygenator for removing oxygen from a liquid fuel. A vaporizer is in fluid communication with the fuel deoxygenator. The vaporizer vaporizes at least a portion of the liquid fuel to produce vaporized fuel. At least a portion of the vaporized fuel pre-mixes with oxidizer to reduce formation of undesirable emissions.

Abstract: A mixture of air and fuel is received into a reaction chamber of a gas turbine system. The fuel is oxidized in the reaction chamber, and a maximum temperature of the mixture in the reaction chamber is controlled to be substantially at or below an inlet temperature of a turbine of the gas turbine system. The oxidation of the fuel is initiated by raising the temperature of the mixture to or above an auto-ignition temperature of the fuel. In some cases, the reaction chamber may be provided without a fuel oxidation catalyst material.

Abstract: In a fluid system for a gas turbine engine, oil is supplied from an oil tank (10) by a constant displacement pump (12) to lubricate engine components (18). The oil is supplied to the components (18) via a heat exchanger (16) in which oil and fuel are placed in direct heat exchange relationship. The flow of oil to the components (18) is controlled by recirculating a proportion of the oil flow through a bypass (20). The bypass (20) regulates the flow of oil to the components (18) so that the amount of heat transferred to the fuel in the heat exchanger (16) is controlled. At low engine powers a greater proportion of the oil flows through the bypass (20) to reduce the oil flow to the components (18). This reduces the heat transferred to the fuel in the heat exchanger (16) and so prevents overheating of the fuel.

Abstract: A method for operating a gas turbine engine including a compressor, a combustor, and a turbine, coupled together in serial flow arrangement, and a fuel heating system including a heat exchanger and an economizer. The method includes channeling fuel through the heat exchanger, channeling a working fluid through the heat exchanger to facilitate regulating the operating temperature of the fuel and the operating temperature of the working fluid, and channeling the fuel and the working fluid into the gas turbine engine combustor to facilitate increasing a fuel efficiency of the gas turbine engine.

Abstract: A method of generating electricity in synthesis gas in which a fuel is combusted in a gas turbine to generate the electricity that at least about 60 percent by volume is derived from a source independent of the synthesis gas. The synthesis gas is produced by reacting a hydrocarbon stream, by for example, partial oxidation, autothermal reforming or steam methane reforming. After the synthesis gas stream is cooled, heat is transferred from the heated synthesis gas stream to the fuel prior to combustion in the gas turbine. All or at least a portion of the heat is transferred at a temperature no greater than about 500° F. and at a flow ratio of the fuel to the gas turbine to the synthesis gas stream from at least about 1.5. The heating of the fuel to the gas turbine lowers fuel consumption and thereby the total expenses involved in generating electricity and syngas.

Abstract: A guanidine based fuel delivery system and method of powering a combustion engine or furnace may be operable to supplying a guanidine-based composition consisting substantially of water, ethanol and guanidine into a reactor chamber. Guanidine and water of the guanidine-based composition may react in the reactor chamber to produce ammonia and carbon dioxide. The products from the reactor chamber may be delivered to a combustion chamber of the combustion based energy conversion system and combusted therein.

Abstract: A gas turbine engine is provided with a first heat exchanger associated with a cooling air flow to deliver cooling air to a turbine section. A second heat exchanger is associated with a fuel supply line for delivering fuel into a combustion section. An intermediate fluid cools air at the first heat exchanger and heats fuel at the second heat exchanger.

Abstract: A gas turbine engine is provided comprising a compressor, a fuel supply apparatus, a combustor, and a turbine. The fuel supply apparatus comprises a fuel source, a cooling apparatus including a heat exchanger and structure for defining a first path for fuel to travel from the fuel source to the heat exchanger and a second path for fuel to travel away from the heat exchanger. The combustor functions to receive the compressed air from the compressor and the fuel from the heat exchanger, combine the air and fuel to create an air/fuel mixture and ignite the air/fuel mixture to create combustion products. The cooling apparatus further comprises structure coupled to and extending between the heat exchanger and at least one of a plurality vanes in the turbine for circulating a coolant fluid through at least one vane and the heat exchanger. In another embodiment, pipe supply structure extends from a fuel source through an end section of a turbine casing.

Abstract: A gas turbine engine having a longitudinal centerline axis therethrough, including: a fan section at a forward end of the gas turbine engine including at least a first fan blade row connected to a first drive shaft; a booster compressor positioned downstream of and in at least partial flow communication with the fan section including a plurality of stages, each stage including a stationary compressor blade row and a rotating compressor blade row connected to a drive shaft and interdigitated with the stationary compressor blade row; a core system positioned downstream of the booster compressor, the core system further comprising a combustion system for producing pulses of gas having increased pressure and temperature from a fluid flow provided to an inlet thereof so as to produce a working fluid at an outlet; a low pressure turbine positioned downstream of and in flow communication with the core system, the low pressure turbine being utilized to power the first drive shaft; and, a system for cooling the combus

Abstract: A method and device of this invention includes a fuel deoxygenator and a heating device for removing dissolved oxygen from fuel and then heating that fuel to a temperature above the temperature that would otherwise produce undesirable insoluble materials from a hydrocarbon fuel. The temperature of the fuel and the amount of dissolved oxygen that is removed from the fuel are adjusted according to the combustion process and optimization of desired combustion characteristics.

Abstract: A gas turbine engine is piloted with a pilot flow of fuel delivered to a combustor as a liquid. A first additional flow of the fuel is also delivered to the combustor as a liquid. A second additional flow of the fuel is vaporized and delivered to the combustor as a vapor. A fuel injector may have passageways associated with each of the three flows.

Abstract: An apparatus for producing power from a source of liquid fuel. The apparatus includes at least one capillary flow passage, the at least one capillary flow passage having an inlet end and an outlet end, the inlet end in fluid communication with the source of liquid fuel, a heat source arranged along the at least one capillary flow passage, the heat source operable to heat the liquid fuel in the at least one capillary flow passage to a level sufficient to change at least a portion thereof from a liquid state to a vapor state and deliver a stream of substantially vaporized fuel from the outlet end of the at least one capillary flow passage, a combustion chamber for combusting the stream of substantially vaporized fuel and air, the combustion chamber in communication with the outlet end of the at least one capillary flow passage and a conversion device operable to convert heat released by combustion in the combustion chamber into mechanical or electrical power.

Abstract: A fuel heating system for fuel usable in a turbine engine. The fuel heating system may include at least one fuel heating chamber in communication with an exhaust stack of a turbine engine. The fuel heating chamber may be configured to allow exhaust gases to flow through the at least one fuel heating chamber. The fuel heating system may also include at least one conduit positioned in the fuel heating chamber. The conduit may be configured to receive fuel from a fuel source at a first temperature, allow the fuel to flow through the conduit, and exhaust the fuel at a second temperature that is higher than the first temperature.

Abstract: In a fluid system for a gas turbine engine, oil is supplied from an oil tank (10) by a constant displacement pump (12) to lubricate engine components (18). The oil is supplied to the components (18) via a heat exchanger (16) in which oil and fuel are placed in direct heat exchange relationship. The flow of oil to the components (18) is controlled by recirculating a proportion of the oil flow through a bypass (20). The bypass (20) regulates the flow of oil to the components (18) so that the amount of heat transferred to the fuel in the heat exchanger (16) is controlled. At low engine powers a greater proportion of the oil flows through the bypass (20) to reduce the oil flow to the components (18). This reduces the heat transferred to the fuel in the heat exchanger (16) and so prevents overheating of the fuel.

Abstract: A method for operating a gas turbine engine includes channeling compressed airflow discharged from a first compressor through an intercooler having a cooling medium flowing therethrough, channeling a working fluid through the intercooler to facilitate increasing an operating temperature of the working fluid, and channeling the discharged working fluid to a combustor to facilitate increasing an operating efficiency of the gas turbine engine.

Abstract: An apparatus for supplying inlet gas 29 and fuel 17 to a gas turbine engine 10, the apparatus comprising: a heat exchanger 28 for transferring thermal energy from the inlet gas 29 to a fuel 17 for the gas turbine engine 10, the heat exchanger 28 comprising a first input for receiving fuel 17, a second input for receiving inlet gas 29, a first output for providing inlet gas 31 after heat exchange to the gas turbine engine 10 and a second output for providing fuel 33 after heat exchange to the gas turbine engine 10.

Abstract: A cooling system for a gas turbine engine includes a fuel deoxygenator for increasing the cooling capacity of the fuel. The fuel deoxygenator removes dissolved gases from the fuel to prevent the formation of insoluble deposits. The prevention of insoluble deposits increases the usable cooling capacity of the fuel. The increased cooling capacity of the deoxygenated fuel provides a greater heat sink for cooling air used to protect engine components. The improved cooling capacity of the cooling air provides for increased engine operating temperatures that improves overall engine efficiency.

Abstract: Apparatus for maintaining the temperature of a component of a gas turbine engine below a predetermined maximum working temperature comprises a reservoir for a cooling fluid having a boiling point below the working temperature and in which the component is immersed or with which it is in contact. At least two heat exchangers are associated with the reservoir and operable to effect condensation of vaporised cooling fluid and return of same to the reservoir. Preferably the apparatus is a closed system incorporating three heat exchangers respectively adapted to effect heat exchange with engine fuel, compressed air derived from a fan or low pressure compressor of the engine and ambient air. Means may advantageously be provided to ensure return of condensed cooling fluid to the reservoir when the attitude of the reservoir is altered as a result of aircraft maneuvers.

Abstract: A gas turbine plant comprises an air compressor, gas turbine including at least one high temperature section, a driven equipment, which are operatively connected in series, a gas turbine combustor arranged between the air compressor and the gas turbine, a fuel system disposed for supplying a fuel to the gas turbine combustor, and a heat exchange section for heating the fuel from the fuel by means of a high pressure air as a heating medium fed from the air compressor.

Abstract: A premixer for a combustor to entrain a selected volume of fuel in an oxidizer to be combusted to heat the oxidizer. The combustor is for a gas powered turbine which employs the hypergolic or high energy air stream which will allow a fuel to be combusted in the absence of an additional ignition source. A heat exchanger and a catalyst combusts a first portion of fuel in air without the production of undesired chemical species. The catalyst is employed to lower the combustion temperature of the fuel to substantially eliminate selected chemical species. The fuel premixed in the air then encounters the catalyst and the fuel is combusted to increase the temperature of the air to an auto-ignition temperature so that no other ignition source is needed to combust additional fuel added later.

Abstract: A gas turbine plant comprises an air compressor, gas turbine including at least one high temperature section, a driven equipment, which are operatively connected in series, a gas turbine combustor arranged between the air compressor and the gas turbine, a fuel system disposed for supplying a fuel to the gas turbine combustor, and a heat exchange section for heating the fuel from the fuel by means of a high pressure air as a heating medium fed from the air compressor.

Abstract: Apparatus for maintaining the temperature of a component of a gas turbine engine below a predetermined maximum working temperature comprises a reservoir for a cooling fluid having a boiling point below the working temperature and in which the component is immersed or with which it is in contact. At least two heat exchangers are associated with the reservoir and operable to effect condensation of vaporized cooling fluid and return of same to the reservoir. Preferably the apparatus is a closed system incorporating three heat exchangers respectively adapted to effect heat exchange with engine fuel, compressed air derived from a fan or low pressure compressor of the engine and ambient air. Means may advantageously be provided to ensure return of condensed cooling fluid to the reservoir when the attitude of the reservoir is altered as a result of aircraft maneuvers.

Abstract: A device is for preheating combustibles in combined gas and steam turbine installations. The device includes at least one steam generator for heating, evaporating and superheating feed water, which has a feed water preheater, an evaporator and a superheater. At least part of the heated feed water is used for preheating combustibles in a combustible preheater, which can be supplied with feed water of a predetermined temperature by a feed water supply line. Once the combustible has been heated, the cooled feed water can be drained using a feed water drain line. The device is configured so that it can be used in different gas turbine installations and its heating capacity can be rapidly and cost-effectively adapted to predetermined combustible preheating requirements. To achieve this, the combustible is preheated in stages, which can be activated individually as required and through which the combustible can successively pass.

Abstract: An energy storage gas-turbine electric power generating system includes a liquid air storage tank for storing liquid air, a vaporizing facility for vaporizing the liquid air stored in the liquid air storage tank, a combustor for generating a combusted gas by combusting the air vaporized by the vaporizing facility and a fuel, a gas turbine driven by the combusted gas generated in the combustor, and a gas-turbine generator connected to the gas turbine for generating electric power. The system further includes a pressurizing unit for pressurizing the liquid air stored in the liquid air storage tank up to a pressure higher than a pressure of air supplied to the combustor to supply the liquid air to the vaporizing facility, an expansion turbine driven by expanding the air vaporized by the vaporizing facility and an expansion-turbine generator connected to the expansion turbine for generating electric power.

Abstract: A fuel conditioning system for a turbine plant may include an inlet fuel module followed by a turbine fuel module for each turbine, the modules being monitored and controlled by a programmable logic controller. The inlet fuel module may include a metering station, an inlet pressure control station, an inlet scrubber station, and an inlet coalescing filter station. Each turbine fuel module has a turbine pressure control station, a turbine super-heater station, and a turbine coalescing filter station. The fuel conditioning system may also include a trip transient mitigation system and a latent fuel venting system. The programmable logic controller collects data from all of the stations and systems as well as the turbine and then uses self-correcting algorithms to control the stations and systems. The programmable logic controller also stores the data collected and transmits the data to an off-site storage and verification center.