Abstract: A pollution-free propulsion engine includes a rotating arm, a hollow axle defining a fuel delivery chamber, and hydrogen and oxygen sources. The rotating arm is formed with a detonation chamber, an opening and two tubular ducts therebetween. The axle is inserted into the opening. A pair of holes is formed in the axle to establish paths of fluid communication from the fuel delivery chamber through the ducts and into the detonation chamber as the rotating arm turns. The hydrogen source comprises a thin palladium binding layer deposited onto an aluminum sheet. Hydrogen molecules that are trapped in the binding layer are released, and the hydrogen is fed into the delivery chamber, through one duct and into the detonation chamber. At the same time, oxygen is delivered into the detonation chamber through the other duct, and the oxygen-hydrogen combination is detonated to release energy, which is converted into mechanical energy.

Abstract: The present invention provides a method of controlling a turbomachine having at least one fuel supply system that uses an unchoked valve. Here, the method may determine the flow characteristics of a fuel in a fuel supply system without using a flow meter. The present invention also provides a fuel supply system with a configuration comprising at least one unchoked valve. The fuel system may not require the use of a flow meter.

Abstract: A pollution-free propulsion engine includes a rotating arm, a hollow axle defining a fuel delivery chamber, and hydrogen and oxygen sources. The rotating arm is formed with a detonation chamber, an opening and two tubular ducts therebetween. The axle is inserted into the opening. A pair of holes is formed in the axle to establish paths of fluid communication from the fuel delivery chamber through the ducts and into the detonation chamber as the rotating arm turns. The hydrogen source comprises a thin palladium binding layer deposited onto an aluminum sheet. Hydrogen molecules that are trapped in the binding layer are released, and the hydrogen is fed into the delivery chamber, through one duct and into the detonation chamber. At the same time, oxygen is delivered into the detonation chamber through the other duct, and the oxygen-hydrogen combination is detonated to release energy, which is converted into mechanical energy.

Abstract: A method for utilizing landfill gas is disclosed herein. The method includes the step of collecting landfill gas. The method also includes the step of fueling a turbine engine that is at least part of a power generation system with the landfill gas to generate power. The method also includes the step of cooling one or more components of the power generation system with the landfill gas prior to the fueling step. A power generation system capable of practicing the method is also disclosed. A landfill gas utilization system capable of practicing the method is also disclosed.

Abstract: In a turbine engine hydrogen is injected into the combustor in response to a power output level of the turbine engine. In a preferred embodiment, gaseous hydrogen is always injected at low-power operations and switched off at mid-power and high-power operations.

Abstract: Methods and systems for controlling a dynamic response in a gas turbine fuel control system are provided. The control system includes a component model adapted to regulate a fuel supply pressure for a gas turbine, a pressure sensor adapted to sense a pressure of fuel supplied to the gas turbine, and a feedback module including integral plus state feedback, the feedback module adapted to provide a positive feedback reference signal to the component model such that a response time of the gas turbine fuel control system to changes in fuel pressure is facilitated being reduced.

Abstract: There is described a method for operation of a burner, whereby a fuel is supplied to the burner, sprayed into the combustion air, mixed with the combustion air to give a fuel/air mixture and burnt in a combustion chamber. With regard to a combustion particularly low in pollutants and, in order to reduce the nitrogen oxide emissions with relation to achieving a given nitrogen oxide emission level, a change in parameters characterizing the fuel is determined. Such a parameter may, for example, be the Wobbe index. There is further described a device for carrying out said method, comprising a fuel treatment device, with an analytical device for the analysis of the current fuel composition and a monitoring and control system.

Abstract: A method and a device are described for monitoring an exhaust gas turbocharger of an internal combustion engine, which allow a diagnosis of the oil supply to an exhaust gas turbocharger. In at least one operating state of the internal combustion engine, a variable that is characteristic for the rotational speed of the exhaust gas turbocharger is ascertained. A variable that is characteristic for the rotational speed of the exhaust gas turbocharger is ascertained in the at least one operating state of the internal combustion engine. An operating state which is characterized by a change in the exhaust gas mass flow, which is linked to a change in the variable that is characteristic for the rotational speed of the exhaust gas turbocharger within a predefined tolerance range, is selected as the at least one operating state.

Abstract: A natural gas production well secondary purpose turbine electric power generator system includes: a.) a natural gas production well from an underground or underwater natural gas well production field that produces natural gas at the surface at an elevated pressure of at least 500 psi and at least 200 psi in excess of desired pressure delivered to gas processing or gas distribution lines; b.) a natural gas valving subsystem connected to said well; and, c.) a power generating turbine subsystem, including at least one gas driven turbine located in at least one of said well and said gas valving subsystem.

Abstract: The carbon-free gas turbine is a power-producing turbine driven by the combustion of hydrocarbon fuels with oxygen. The carbon-free gas turbine includes at least one combustor for combusting gaseous fuel with oxygen. The at least one combustor includes a housing containing at least one oxygen transport reactor. The oxygen transport reactor includes an outer wall and an inner cylindrical ion transport membrane. The membrane receives pressurized air and separates gaseous oxygen therefrom, transporting the oxygen into a central region thereof for combustion with the gaseous hydrocarbon fuel, producing gaseous carbon dioxide and water vapor. A first turbine is driven by the gaseous carbon dioxide and water vapor produced by the at least one combustor and drives a first compressor. The first compressor provides the pressurized air supplied to the at least one combustor. A second turbine is driven by pressurized nitrogen gas resulting from the combustion.

Abstract: An operational control system of a gas turbine which is driven using mainly ammonia as fuel, wherein in a deteriorated combustibility operating region where the combustibility of ammonia deteriorates compared with the time of normal operation of the gas turbine, for example, at the time of cold startup of the gas turbine and right after startup or right before stopping operation, etc., a ratio of fossil fuel in the fuel which is fed to the gas turbine is increased over the time of normal operation. Due to this, even when using nonflammable ammonia as a main fuel, it is possible to stably start up, operate, and stop the gas turbine.

Abstract: A fuel lance for a gas turbine installation with sequential combustion, in which hot gas is produced in a first combustion chamber and expanded in a subsequent turbine, and then flows through a subsequent second combustion chamber in which the fuel lance for injecting fuel into the hot gas is arranged. The fuel lance has a lance section which extends in the flow direction of the hot gas and includes at least an outer tube which is arranged concentrically to a lance axis, and a center tube which is concentrically arranged in the outer tube and in which the fuel is guided to the lance tip and is injected through first injection openings in the region of the lance tip into the hot gas. The fuel lance is modified for operation with syngas by the first injection openings being arranged directly on the lance tip, and by the first injection openings being oriented so that the fuel jets which emerge from them include an acute angle with the lance axis.

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, and an integrated fuel gas characterization system. The integrated fuel gas feed system can include a buffer tank. The integrated fuel gas characterization system for determining the amount of energy provided by the fuel prior to combustion of the fuel in the combustion stage. The integrated fuel gas characterization system minimizes megawatt swings by adjusting the operating parameters of the gas turbine engine based on the rate of change in fuel gas energy content. The integrated fuel gas characterization system also provides improved turbine engine start-up reliability by tuning the turbine engine operating parameters using fuel gas energy content measurements obtained prior to actual start-up.

Abstract: A power plant, including a compressor, in which inlet air is compressed for combustion operations, is provided and includes a separation unit, which receives and removes nitrogen from an air supply, and a system, coupled to the separation unit and an inlet disposed upstream from and in fluid communication with the compressor, which receives the nitrogen from the separation unit and delivers the nitrogen to the inlet.

Abstract: A method and apparatus are described for controlling the combustion in a gas turbine. The method includes measuring, with one or two calorimeters, the temperature, calorific value and relative density of a gaseous fuel in order to determine the Wobbe index, comparing the Wobbe index value measured with a predefined Wobbe index value for the gaseous fuel and regulating the temperature of the gaseous fuel with at least one heat exchanger in order to reach the predefined Wobbe index value. The method may also include using a second gaseous fuel, having a different Wobbe index from the gaseous fuel, or a fuel obtained by mixing the gaseous fuel and the second gaseous fuel, according to arbitrary proportions and variable with time.

Abstract: The invention relates to gas turbine plants which can be used for gas turbine locomotives and mobile and stationary power plants and which use cryogenic gas fuel. The oil systems of a gas turbine engine and of actuating units are designed in the form of individual adjustable flow circuits each of which comprises fuel-oil heat exchangers, the cooling medium of which his in the form of a cryogenic gas fuel, a delivery pump and an oil tank. The cooling cavities of the fuel/oil heat exchangers are connected, at the inputs thereof, to a fuel supply and adjusting device and to a fuel heater, which is arranged, at the outputs thereof, in the sleeve of the gas turbine engine. Said invention makes it possible to design a low-consumption gas turbine plant provided with a small-sized oil-cooling and fuel-heating system.

Abstract: A fuel processor (10) comprises a supply of natural gas (12) and a compressor (14), which compresses the natural gas and supplies the natural gas to a partial oxidation reactor (16). A supply of oxygen (20) supplies the oxygen to the partial oxidation reactor (16). The partial oxidation reactor (16) partially reacts the natural gas and the oxygen to form a mixture comprising hydrogen and carbon dioxide. The partial oxidation reactor (16) supplies the mixture of hydrogen and carbon dioxide to a turbine (20). The turbine (20) is arranged to drive the compressor (14). The turbine (20) expands and cools the mixture of hydrogen and carbon dioxide and supplies the mixture of hydrogen and carbon dioxide to a fuel cell stack (22) requiring hydrogen and/or carbon dioxide.

Abstract: A gas turbine uses a first fuel at full load and an improved emission behavior is achieved by operating the gas turbine (11) at partial load with a second fuel, which has a richer mix of higher-value hydrocarbons (C2+) with 2 and more carbon atoms per molecule like ethane (C2H6) and propane (C3H8).

Abstract: Methods and systems for controlling a dynamic response in a gas turbine fuel control system are provided. The control system includes a component model adapted to regulate a fuel supply pressure for a gas turbine, a pressure sensor adapted to sense a pressure of fuel supplied to the gas turbine, and a feedback module including integral plus state feedback, the feedback module adapted to provide a positive feedback reference signal to the component model such that a response time of the gas turbine fuel control system to changes in fuel pressure is facilitated being reduced.

Abstract: A fuel supply system and method thereof that utilizes an off-gas in addition to the primary fuel to lower the emissions of a gas turbine combustion system is disclosed. The fuel supply system apparatus comprises a fuel gas supply conduit and an off-gas supply conduit in fluid communication with the fuel gas supply conduit such that the flow of an off-gas to the fuel gas supply conduit can be regulated as required by the operator to the desired fuel nozzle(s). The fuel gas supply preferably operates with natural gas and the off-gas supply preferably comprises the constituents hydrogen and methane.

Abstract: A combustion control device for a gas turbine is capable of determining respective fuel flow rate control valve position command values based on fuel ratios. The combustion control device for a gas turbine is configured to calculate fuel flow rate command values for respective types of fuel gas based on a total fuel flow rate command value and fuel gas ratios, to calculate fuel gas flow rates based on the fuel flow rate command values and on a function of the fuel flow rate command value and the fuel gas flow rate, to calculate Cv values of the respective fuel flow rate control valves in accordance with a Cv value calculation formula based on the fuel gas flow rates, a fuel gas temperature, and front and back pressures of the respective fuel flow rate control valves, and to calculate respective fuel flow rate control valve position command values based on the Cv values and on a function between the Cv value and apertures of the fuel flow rate control valves.

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 trapped vortex combustor. The trapped vortex combustor is configured for receiving a lean premixed gaseous fuel and oxidant stream, where the fuel includes hydrogen gas. The trapped vortex combustor is configured to receive the lean premixed fuel and oxidant stream at a velocity which significantly exceeds combustion flame speed in a selected lean premixed fuel and oxidant mixture. The combustor is configured to operate at relatively high bulk fluid velocities while maintaining stable combustion, and low NOx emissions. The combustor is useful in gas turbines in a process of burning synfuels, as it offers the opportunity to avoid use of diluent gas to reduce combustion temperatures. The combustor also offers the possibility of avoiding the use of selected catalytic reaction units for removal of oxides of nitrogen from combustion gases exiting a gas turbine.

Abstract: The plant includes a gaseous fuel processing apparatus for pre-processing natural gas (gaseous fuel) produced in the gas field, a liquid fuel processing apparatus for pre-processing liquid fuel obtained during the extraction and refining process of the natural gas, and a gas turbine. The gas turbine includes a compressor for generating compressed air, a combustor for mixing the compressed air from the compressor with one or both of the gaseous fuel pre-processed by the gaseous fuel processing apparatus and the liquid fuel pre-processed by the liquid fuel processing apparatus, and for burning a gas mixture, and a turbine for driving a generator by combustion gases supplied from the combustor.

Abstract: Methods and systems for operating a gas turbine engine system include an electrical generator configured to provide electrical energy to a load, a gas turbine engine including at least one combustor that includes a plurality of fuel injection points configured to inject a fuel into the combustor at a plurality of different locations wherein the combustor configured to combust the fuel and the gas turbine engine is rotatably coupled to the generator through a shaft. The gas turbine engine system includes a control system including a plurality of sensors positioned about the gas turbine engine system and configured to measure at least one parameter associated with the sensor, a processor programmed to receive a signal indicative of a heating value of the fuel, and automatically control a fuel split between the fuel injection points on the combustor using the determined heating value.

Abstract: A system and method to reduce the gas fuel supply pressure requirements of a gas turbine, which results in an increased operability range and a reduction in gas turbine trips. According to the method, the gas turbine is allowed to start and operate at supply pressures determined as a function of ambient conditions and gas turbine compressor pressure ratio. This increases the operability window, and reduces or eliminates the need for gas fuel compressors.

Abstract: A method for operating a gas turbine (2), in particular in a power plant, includes operating the gas turbine (2) with natural gas. In order to adapt the gas turbine operation to different natural gas qualities, a concentration of C2+ is measured in the natural gas during gas turbine (2) operation. The gas turbine (2) then is operated based on the current concentration of C2+.

Abstract: Various embodiments of a fuel-control system and associated methods for regulating the administration of a fuel to a fuel consuming device are disclosed. In one aspect, the fuel consuming device is a gas turbine receiving fuel through a feeder conduit from first and second sources of gas. According to one method, natural gas fuel is delivered from said first and second sources into said surge tank via first and second conduits, each conduit having pressure-control valves and sensors. The natural gas is delivered to the turbine from the surge tank via a feeder conduit. Pressure measurements are taken by the sensors for the first and second conduits, which are sent to a controller. The controller is then used to manipulate the valves to supply the turbine with fuel.

Abstract: A gas-turbine power generating installation capable of effectively utilizing gases produced in overage gas fields, etc. and a method of operating the installation are provided. The gas-turbine power generating installation is installed in the vicinity of an outrage gas field or an oil field. In the installation, air compressed by a compressor is introduced to a combustor for combustion after being mixed with fuel, a gas turbine is driven by generated combustion gas, and a power generator is driven by motive power obtained from a rotary shaft of the gas turbine. A boosting compressor is driven by the motive power obtained from the rotary shaft of the gas turbine, whereby natural gas or accompanying gas is boosted in pressure and supplied as fuel to the combustor. The gas turbine generates electric power by using natural gas produced in the outrage gas field or accompanying gas produced in the oil field, and the generated electric power is supplied to a consuming site.

Abstract: Provided is a compressor control unit with a high response ability to changes of gas condition of a compressor (compressor suction temperature, pressure, gas specific gravity, pressure ratio of suction pressure and discharge pressure). In the control unit for a compressor that supplies gas into a gas turbine through a header tank, an inlet gas condition is measured and a load command value from a gas turbine controller is corrected to be increased or decreased corresponding to the measured inlet gas condition.

Abstract: This invention relates to the injection of compressible gaseous fuel directly into the combustion chamber of a reciprocating piston-type internal combustion engine. In particular, the invention provides apparatus and methods for low-pressure, high-speed direct injection of compressed natural gas into a combustion chamber of an engine. Using the present invention, relatively low intake pressures of about 50 to about 150 PSIG yield high-speed (sonic and supersonic) gas flow through the diverging nozzle portion for injection into the combustion chamber. Preferably, the gas reaches supersonic velocity, approaching Mach 1.5 to 2.5.

Abstract: A system comprising a compressor (10) having an inlet stream (25) and an outlet stream (26), a pre-heater (12) having a process inlet stream (29) and a process outlet stream (31), a catalytic combustor (13) having an inlet stream (32) and an outlet stream (33) and containing an catalyst, and a turbine (14) having an inlet stream (34) and an outlet stream (35), wherein, the outlet stream (26) of the compressor(10) is connected to the process inlet stream (29) of the pre-heater (12), the process outlet stream (31) of the pre-heater (12) is connected to the inlet stream (32) of the catalytic combustor (13). The outlet stream (33) of the catalytic combustor (13) is connected to the inlet stream (34) of the turbine (14). During operation of the system, the inlet stream (25) of the compressor (10) has a substantially constant and low concentration of fuel.

Abstract: A gas turbine cycle that utilizes the vaporization of liquefied natural gas as an intercooler in an open loop gas turbine system. The system provides an increase in gas turbine cycle efficiencies while providing a convenient system for vaporizing liquefied natural gas. The systems and methods of the present invention permit the vaporization of liquefied natural gas using air that has been compressed in a first compressor, with the resulting cooled air being easier to compress and/or having fewer contaminants therein for compression in a second compressor. As the air is easier to compress, less energy is needed to operate the second compressor, thereby increasing the efficiency of the system. Additionally, unlike prior art systems that use water as an intercooler, no additional equipment is needed to cool the vaporized natural gas, such as cooling towers.

Abstract: Calories of a first mixed gas are predicted by calculations based on the mixed flow rate of a blast furnace gas and the mixed flow rate of a converter gas measured by flow meters, and preset blast furnace gas calories and converter gas calories; the flow rate ratio of the mixed flow rate of a coke oven gas to a gas turbine consumed fuel gas flow rate is calculated based on the predicted calories, set calories, and preset coke oven gas calories; the mixed flow rate required value of the coke oven gas is calculated based on the flow rate ratio and a gas turbine fuel gas requirement signal corresponding to the gas turbine consumed fuel gas flow rate; and the opening of a coke oven gas flow control valve provided in a fuel gas production system is controlled, based on the mixed flow rate required value, to control the mixed flow rate of the coke oven gas.

Abstract: The present invention is a fuel-control system for a turbine which includes a programmable logic controller. The controller manages utility and stored natural gas sources using a surge tank and pressure-control valve arrangement and is backed up by a hydrogen-powered fuel cell.

Abstract: The invention is directed to a method of fueling gas turbines from natural gas reserves with relatively low methane concentrations. The invention uses such reserves to generate electric power. The invention permits the use of these reserves at significantly lower cost than by producing pipeline natural gas to fuel gas turbines to generate electric power. These reserves currently generally are used only after the removal of impurities to produce pipeline natural gas quality turbine fuel. The latter current technology is capital intensive, and at current natural gas prices, economically unattractive. The process of the invention can remove the impurities from the gas from the natural gas reserve necessary for protection of the environment and leaves inert gasses in the fuel in an amount which will increase the output of a gas turbine for the generation of power by about 5 to about 20%.

Abstract: An electric power supply system capable of maintaining stable power generation or the like regardless of variation in the amount of fuel gas being supplied and variation in the gas calorie, comprises a gas engine, a gas turbine, a suction device configured to collect the generating gas, a gas separating device configured to classify the gas collected according to the calorie, a gas calorie adjusting device configured to mix gases having different calories which are supplied from the gas separating device to adjust gas calorie before supplying to the gas engine and the gas turbine, a gas amount balance monitor device configured to monitor balance between the amount of gas being consumed by the gas turbine and the gas engine in operation and the amount of gas being supplied from the gas calorie adjusting device, and a system control device configured to control operation of the gas engine, operation of the gas turbine, and operation of the gas calorie adjusting device.

Abstract: A power generating system having a liquid natural gas (LNG) vaporization circuit and an energy generating circuit. The LNG vaporization circuit includes a heat exchange assembly and a heating tower connected to the heat exchange assembly. The LNG vaporization circuit also includes a LNG vessel connected to the heat exchange assembly. The energy generating circuit includes a gas turbine connected to the heating tower along with a first electrical generator connect to the gas turbine.

Abstract: Relevant fuel-gas properties (XG) are measured on an ongoing basis while a gas turbine group is operating. The C2+alkane content of the fuel gas is of particular interest in this context, since it has a significant influence on the ignitability of the fuel gas in the combustion chamber. The operating parameters of the gas turbine group are acted on directly as a function of the measured fuel-gas properties. In particular, in the case of the example of a gas turbine group with sequential combustion, the distribution of the fuel mass flows ({dot over (m)}EV, {dot over (m)}SEV) between the combustion chambers (4, 8) of the gas turbine group is varied. Furthermore, if there is provision for inert media, such as water or steam, to be introduced, it is possible for the mass flow of inert media ({dot over (m)}ST) to be controlled as a function of the measured fuel properties.

Abstract: A fuel injection system has a fuel lance for supplying gaseous fuel to the burner of a gas turbine engine. The fuel lance includes a gas sensor that is used to monitor the concentration of the methane fuel inside the gas pilot channel of the fuel lance. The invention prevents overheating caused by the ignition of the methane fuel inside the fuel lance by monitoring the concentration of the methane fuel during the purge sequence and taking action if a critical fuel air mixture is reached.

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.

Abstract: A gas-turbine power generating installation capable of effectively utilizing gases produced in overage gas fields, etc. and a method of operating the installation are provided. The gas-turbine power generating installation is installed in the vicinity of an outrage gas field or an oil field. In the installation, air compressed by a compressor is introduced to a combustor for combustion after being mixed with fuel, a gas turbine is driven by generated combustion gas, and a power generator is driven by motive power obtained from a rotary shaft of the gas turbine. A boosting compressor is driven by the motive power obtained from the rotary shaft of the gas turbine, whereby natural gas or accompanying gas is boosted in pressure and supplied as fuel to the combustor. The gas turbine generates electric power by using natural gas produced in the outrage gas field or accompanying gas produced in the oil field, and the generated electric power is supplied to a consuming site.

Abstract: A gas fuel injector includes a first header plate, a second header plate, and a plurality of venturi tubes. The second header plate is spaced downstream from the first header plate. The plurality of venturi tubes is sealably secured to the first and second header plates. Each venturi tube of the plurality of venturi tubes is defined by a plurality of fixable components.

Abstract: A gas-turbine power generating installation capable of effectively utilizing gases produced in overage gas fields, etc. and a method of operating the installation are provided. The gas-turbine power generating installation is installed in the vicinity of an outrage gas field or an oil field. In the installation, air compressed by a compressor is introduced to a combustor for combustion after being mixed with fuel, a gas turbine is driven by generated combustion gas, and a power generator is driven by motive power obtained from a rotary shaft of the gas turbine. A boosting compressor is driven by the motive power obtained from the rotary shaft of the gas turbine, whereby natural gas or accompanying gas is boosted in pressure and supplied as fuel to the combustor. The gas turbine generates electric power by using natural gas produced in the outrage gas field or accompanying gas produced in the oil field, and the generated electric power is supplied to a consuming site.

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 method for operating a gas turbine (2), in particular in a power plant, includes operating the gas turbine (2) with natural gas. In order to adapt the gas turbine operation to different natural gas qualities, a concentration of C2+ is measured in the natural gas during gas turbine (2) operation. The gas turbine (2) then is operated based on the current concentration of C2+.

Abstract: A turbine includes a combustion chamber with deflectors generating vortices in a secondary gas flow into the combustion chamber, thereby confining the flame front from penetrating into the cold region of the chamber under variable operating conditions, simplifying cooling of the chamber walls. The turbine further includes devices for decoupling vibrations between the high- and low-speed shafts, including a loosely mounted spline coupling the high-speed shaft to the step-down system and disk dampening means coupling the step-down system to the low-speed output shaft.

Abstract: A turbine includes a combustion chamber with deflectors generating vortices in a secondary gas flow into the combustion chamber, thereby confining the flame front from penetrating into the cold region of the chamber under variable operating conditions, simplifying cooling of the chamber walls. The turbine further includes devices for decoupling vibrations between the high- and low-speed shafts, including a loosely mounted spline coupling the high-speed shaft to the step-down system and disk dampening means coupling the step-down system to the low-speed output shaft.

Abstract: Values such as a pressure for supplying fuel gas to a gas turbine, a pressure in a combustor casing of the gas turbine, an output of a generator connected to the gas turbine, and a controlled output for a flow rate control valve are detected by sensors. The detected values are input into a control device. A differential pressure across the flow rate control valve and a target value of the differential pressure are also input into the control device. The control device performs a desired arithmetic operation based on these input values to output a lift instruction for a pressure control valve.

Abstract: A gas turbine cycle that utilizes the vaporization of liquefied natural gas as a source of inlet air chilling for a gas turbine. The cycle uses regeneration for preheating of combustor air and offers the potential of gas turbine cycle efficiencies in excess of 60%. The systems and methods permit the vaporization of LNG using ambient air, with the resulting super cooled air being easier to compress and/or having fewer contaminants therein. As the air is easier to compress, less energy is needed to operate the compressor, thereby increasing the efficiency of the system. A portion of the vaporized natural gas may be used as the combustion fuel for the gas turbine system, thereby permitting multiple turbines to be operated using a single topping cycle. In alternative embodiments, the vaporization of the LNG may be used as part of a bottoming cycle to increase the efficiencies of the gas turbine system.