Abstract: In a method for operating a gas turbine plant (10) with a compressor (11) for the compression of combustion air sucked in from the surroundings, with a combustion chamber (15) for generating hot gas by the combustion of a fuel with compressed combustion air, and with a turbine (12), in which the hot gas from the combustion chamber (15) is expanded so as to perform work, temperatures and pressures are measured at various points in the gas turbine plant (10), and a combustion chamber exit temperature is derived from the measured temperatures and pressures and used for controlling the gas turbine plant (10). Improved temperature determination is achieved in that the composition of the gas, in particular the water content in the exhaust gas of the turbine (12), is determined, and in that the specific water content in the exhaust gas of the turbine (12) is taken into account in deriving the combustion chamber exit temperature.

Abstract: A gas turbine combustion system for a turbine engine is disclosed. The gas turbine combustion system may include a plurality of combustor baskets positioned circumferentially about a longitudinal axis of the turbine engine, at least one firing nozzle extending into each of the plurality of combustor baskets and a fuel delivery system in communication with each of the at least one firing nozzles and in communication with at least one fuel source. Each combustor basket may include a fuel flow control device of the fuel delivery system inline with each of the at least one firing nozzles in that combustor basket such that fuel flow to some of the combustor baskets can be shut off while fuel flow to firing nozzles in other combustor baskets remains unobstructed, thereby permitting some combustor baskets to remain non-fired while other combustor baskets are firing to reduce CO emissions.

Abstract: A device for detecting breakage of a gas turbine engine shaft and for reducing the rotational speed of the turbine includes a rotor of a turbine or of a first stage turbine driving the shaft. The rotor has a turbine disk with a rim. A stator that the rotor rotates inside or a nozzle guide vanes assembly of the first turbine stage is provided. A temperature sensor is positioned on the stator or on the nozzle guide vanes assembly, immediately downstream of the rim. The sensor is located to sense temperature on a portion of the stator that contacts the rotor, or on a portion of the nozzle guide vanes assembly that contacts the first stage rotor, in the event of shaft breakage. An engine fuel control member connects to the sensor and can interrupt fuel supply to the engine, when the sensor emits a signal above a predetermined threshold.

Abstract: The present invention provides a reformed-fuel-burning gas turbine system that constantly generates good-quality reformed fuel even when heavy fuel has a different composition. The reformed-fuel-burning gas turbine system according to the present invention comprises a heavy oil heater; a water heater; a reformer vessel for mixing high-temperature, high-pressure water with high-temperature, high-pressure heavy oil to cause a hydrothermal reaction and producing reformed fuel from heavy oil; and a gas turbine which operates on the reformed fuel.

Abstract: A lean blowout protection system and method is provided that facilitates improved lean blowout protection while providing effective control of turbine engine speed. The lean blowout protection system and method selectively and gradually biases the lean blowout (LBO) schedule based on current engine data. This facilitates improved lean blowout protection while providing effective control of turbine engine speed and temperature.

Abstract: A flexible and automatic system and method for blending an inexpensive secondary gas with a primary gas fuel for operation of a Dry Low NOx gas turbine. The secondary gas may be a gas fuel such as hydrogen, ethane, butane, propane and liquefied natural gas or an inert gas. Combustion dynamics are avoided by controlling the blended fuel within a permissible range for a Modified Wobbe Index. Combustion dynamics and gas turbine exhaust emissions may also be monitored to maintain safe combustion with the blended fuel. A gas turbine control system may adjust the blend and temperature of the primary gas fuel and the secondary gas to promote desired combustion.

Abstract: A system for driving a fuel pump in a turbine engine is disclosed. The system includes an electric motor and a fluid flow assistance unit controlled by a control valve. In the system, the control valve is a regulator valve the opening of which is controlled as a function of information representative of the speed of the pump, and/or the speed of the turbine engine, and/or the flow rate of fuel delivered to the turbine engine. As a result, operating safety of the turbine engine can be increased in the event of the electric motor failing or of its electricity generator failing, and the weight/size/cost ratios of the drive system are improved.

Abstract: In an apparatus for controlling a flow rate of fuel to be supplied to a combustion chamber of a gas turbine engine having a turbine rotated by combustion gas injected from the combustion chamber and a compressor for compressing air to be supplied to the combustion chamber, a first fuel flow rate at starting of the engine is calculated based on at least the detected output pressure of the compressor. In addition, a second fuel flow rate at starting of the engine is calculated based on at least the detected temperature of the inflowing air, the exhaust gas temperature and the rotational speed of the compressor, one of the first and second fuel flow rates is selected based on the detected exhaust gas temperature and operation of a fuel metering valve is controlled based on the selected fuel flow rate, thereby enabling to prevent white smoke at engine starting even when the engine is in the unstable range where the exhaust gas temperature is low.

Abstract: In an overspeed protection apparatus for a gas turbine engine having a turbine rotated by combustion gas injected from a combustion chamber to drive a compressor, a fuel shutoff valve to shut off fuel to be supplied to the engine and a controller controlling operation of the fuel shutoff valve based on a turbine rotational speed to protect the turbine from overspeed, an outlet pressure of the compressor is detected and compared with a threshold value when a shutoff command is outputted, and the fuel shutoff valve is determined to be failed when the detected pressure is not less than the threshold value, thereby enabling to promptly detect the fuel shutoff valve failure without additional installing sensor, thereby enhancing the reliability

Abstract: A combined power generation unit includes a gasification unit with a gasification furnace that is used to produce fuel gas, and a gas turbine that uses the fuel gas to generate power. To produce the fuel gas required in the combined power generation unit according to a required power load, a feed-forward control of the gasification unit is performed. Also, a dead time compensator compensates for a lag and a dead time occurring while the fuel gas is fed from the gasification unit to the combined power generation unit. The gasification unit is operated using a zero flare process. The dead time compensator delays the power load required in the combined power generation unit on the basis of the lag and the dead time of the gasification unit so that the combined power generation unit is operated while a follow-up is performed with a predetermined delay.

Abstract: A system and method for operating an integrated gasification combined cycle (IGCC) gas turbine system that utilizes the fuel stream as a means of controlling the operation of the IGCC to achieve a target output and efficiency. The methods and systems enable the IGCC to be operated at reduced output, but without a corresponding drop in efficiency as compared to prior art gas turbine systems. Conversely, the IGCC may be operated at higher outputs. The methods and systems achieve the target output and efficiency by adjusting the chemical potential energy, sensible energy, or both of a fuel stream entering the combustion turbine. The chemical potential energy and sensible energy may be manually or automatically controlled.

Abstract: A system includes a turbine combustor fuel nozzle. The turbine combustor fuel nozzle includes a swirl vane. The turbine combustor fuel nozzle also includes an injection hole configured to inject fluid in a downstream region of the swirl vane. The injection of fluid in a downstream region of the swirl vane may be in response to detection of a condition indicative of a flame inside the turbine combustor fuel nozzle.

Abstract: A method of starting a turbine engine at a first engine speed value which is lower than a second engine speed value designed for a normal engine starting operation, comprises varying a fuel flow into a combustor of the engine to start the engine in repeatedly alternating speed acceleration and deceleration cycles in order to create an engine speed augmentation in each of the speed acceleration and deceleration cycles, thereby achieving the second engine speed value while preventing the engine from being overheated, and then beginning the normal engine starting operation.

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 fuel system includes first and second drive assemblies that are independently drivable relative to one another. The second drive assembly has a speed that is selectively controlled based upon a desired fuel flow. A non-positive displacement pump is driven by the first drive assembly. The non-positive displacement pump provides a desired fuel pressure for the fuel system. A positive displacement pump is driven by the second drive assembly. The positive displacement pump meters a desired volume in response to the speed of the second drive assembly in a first rotational direction. The fuel flows from the pumps and passes through a bypass valve that acts as a minimum pressure shut-off valve. During shut-down of the first drive assembly, the bypass valve is opened by a solenoid and the rotational direction of the second drive assembly is reversed to a second rotational direction to evacuate fuel from the system with the positive displacement pump and return the fuel to the fuel tank.

Abstract: An auto-tune controller and tuning process implemented thereby for measuring and tuning the combustion dynamics and emissions of a GT engine, relative to predetermined upper limits, are provided. Initially, the tuning process includes monitoring the combustion dynamics of a plurality of combustors and emissions for a plurality of conditions. Upon determination that one or more of the conditions exceeds a predetermined upper limit, a fuel flow split to a fuel circuit on all of the combustors on the engine is adjusted by a predetermined amount. The control system continues to monitor the combustion dynamics and to recursively adjust the fuel flow split by the predetermined amount until the combustion dynamics and/or emissions are operating within a prescribed range of the GT engine.

Abstract: A direct metering fuel supply system includes a plurality of axial gap motors, a fixed displacement, variable speed positive displacement piston pump, and a gas turbine engine control. Each axial gap motor is configured to be selectively energized and is operable, upon being energized, to supply a drive torque at a drive speed. The fixed displacement, variable speed positive displacement piston pump is coupled to each of the axial gap motors to receive the drive torque selectively supplied therefrom and is operable, upon receipt of the drive torque, to supply fuel at a flow rate dependent on the drive speed. The gas turbine engine control is adapted to receive fuel flow commands and is operable, in response to the fuel flow commands, to energize one of the plurality of axial gap motors.

Abstract: A dual-pump fuel system for use with a gas turbine engine comprises a fuel metering system, a mechanical fuel pump, an electric fuel pump and an engine controller. The fuel metering system is configured to dispense fuel flow to the engine based on operational needs of the gas turbine engine. The mechanical fuel pump is configured to deliver fuel to the metering system dependent on operational speeds of the engine. The electric fuel pump is configured to deliver fuel directly to the engine independent of operation of the engine. The engine controller is connected to the metering system and the electric fuel pump and is configured to cause the electric fuel pump to deliver fuel to the engine to start and operate the engine until the engine operates the mechanical fuel pump to deliver fuel to the metering system sufficient to sustain operation of the engine.

Abstract: A system allows a user to manually manipulate fuel flow to a gas turbine engine during a loss of power to the fuel supply system fuel metering unit. The fuel metering unit includes a fuel metering valve, a metering valve actuator, a fail-fixed valve, a flow increase valve, and a flow decrease valve. The fuel metering unit is configured such that, upon electrical power interruption to the metering valve actuator, the fail-fixed valve shifts and provides a hydraulic lock on the fuel metering valve, to thereby maintain its position. The flow increase and flow decrease valves are powered from a power source that is independent of that used to power the fuel metering unit and, when appropriately energized will allow movement of the fuel metering valve.

Abstract: A gasification unit provided with a gasification furnace 23 to produce fuel gas production is provided. A combined power generation unit 25 which generates power by rotating a gas turbine and a steam turbine using fuel gas produced in the gasification unit is provided. The combined power generation unit 25 is made operable while fuel change over between fuel gas and an auxiliary fuel as the fuel. A control system is provided in which the degree of opening of a control valve 37 for a flare stack 28 provided in a fuel gas feed line is controlled depending upon the pressure of the fuel gas from the gasification unit when fuel change over from the fuel gas to the auxiliary fuel so as to allow the fuel gas supplied to the combined power generation unit 25 to gradually flare from a flare stack 28 until a flared status that total amount of the fuel gas is reached.

Abstract: In a gas turbine engine control system having a first valve for regulating the flow rate of fuel in premixed combustion and a second valve for regulating that in diffusion combustion, when the combustion mode is switched from one mode to the other mode, whichever of the first and second valves is associated with the other combustion mew is opened to supply the amount of fuel required for conducting the other combustion mode and, the opening of the valve associated with the one combustion mode is gradually decreased, while that of the other combustion mode is gradually increased, thereby maintaining the total amount of fuel supplied to the engine constant, after elapse of a predetermined period. At the time of switching the combustion mode, therefore, the total amount of fuel supplied to the engine can be accurately controlled to a desired value to minimize engine speed fluctuation.

Abstract: An object is to reduce a fluctuation in the gas-turbine output in a nozzle switching period. In the nozzle switching period during which a first nozzle group that has been used is switched to a second nozzle group that is going to be used, the amounts of fuel supplied through the first nozzle group and the second nozzle group are adjusted by using at least one adjustment parameter registered in advance, the adjustment parameter registered in advance is updated according to the operating condition of the gas turbine, and the updated adjustment parameter is registered as an adjustment parameter to be used next.

Abstract: A method of monitoring the health of a gas turbine engine 10 comprising a fuel system 30 having a fuel metering valve 36 and a fuel pump 40 for supplying fuel to a combustor apparatus 15. The method comprising the steps of: monitoring the fuel metering valve percentage open, detecting and sending a warning message when the fuel metering valve percentage open is at 97% or greater and within a predetermined time from when the first percentage open is at 97% or greater, replacing the fuel pump 40. In this way scheduling of servicing and replacement of the fuel pump may be made without disruption to the aircraft operator particularly where the operator has a fleet of aircraft.

Abstract: A technique is provided for operating a gas turbine engine that has a combustor with a primary stage and one or more other stages and a first compressor providing an air flow to the combustor. This technique includes driving a variable load device with the rotating shaft of the gas turbine engine and sensing pressure of the air flow and an engine speed. In response to a decrease in loading of the engine by the variable load device: selectively bleeding the air flow as a function of the engine speed and regulating temperature in the primary stage of the combustor as a function of a ratio between fuel flow provided to primary stage and the pressure to prevent engine flame out. In one form, the combustor is arranged as a dry load emissions type and the variable load device includes an electric power generator.

Abstract: The present invention provides a fuel system for an engine including a water supply source for providing water and a fuel supply source for providing fuel. A centrifugal pump is fluidly connected to the water and fuel supply sources, respectively at water and fuel inputs. The pump receives the water and the fuel from the inputs and produces a homogeneous mixture without using other pumps or mixing devices. A metering device is arranged between the pump and one of the supply sources, preferably the water supply source, to produce the desired ratio of water and fuel. The speed of the pump is varied to deliver the desired total volume and pressure of fuel and water to the engine through the pump output. The water metering device may be closed to deliver only fuel to the engine during special conditions such as engine startup and rapid load dumps. Operation of the system is simplified because only one pump and metering device is used.

Abstract: A method and system for controlling combustion in a gas turbine engine (10) includes reducing an overall fuel flow provided to a stage (22) of burners (e.g. 34, 35) of the gas turbine engine until reaching a predetermined dynamic operating condition of the first burner of the stage. The method also includes maintaining, while continuing to reduce the overall fuel flow (e.g. 30), a first portion (e.g. 36), of the overall fuel flow delivered to the first burner at a maintenance level so that the predetermined dynamic operating condition of the first burner is maintained.

Abstract: A pump arrangement and method of regulating pressure of a pump arrangement are provided. The pump arrangement includes an actuation pump, a pressure regulating valve, and a control valve. The actuation pump has an actuation pump outlet providing an actuation pump discharge flow. The actuation pump discharge flow is piped to opposite sides of a regulator valve member that selectively adjusts an amount of fluid that is bled from the actuation pump outlet such that the actuation pump outlet pressure is used to regulate the actuation pump discharge pressure. The actuation pump discharge flow is separated into first and second portions to provide opposing forces on the regulator valve member. The control valve is operably interposed between the actuation pump outlet and the valve member to selectively adjusts the amount of biasing applied by the second portion of the actuation pump discharge flow on the regulator valve member.

Abstract: Systems, devices, and methods for controlling a fuel supply for a turbine or other engine using direct and/or indirect indications of power output and optionally one or more secondary control parameters.

Abstract: A method for determining sensor locations in a gas turbine engine is provided. The said method includes providing a turbine rear frame including a radially inner surface, a radially outer surface and a plurality of circumferentially-spaced struts extending between the inner and outer surfaces, wherein a strut sector is defined between each pair of circumferentially-adjacent struts, providing a plurality of fuel nozzles that are each aligned with a strut sector, selecting one of the plurality of fuel nozzles as a primary index nozzle and positioning each of a plurality of sensors relative to one of the plurality of nozzles using a corresponding positioning angle such that each of the plurality of sensors coincides with a gas flow temperature distribution profile between each pair of circumferentially-spaced nozzles.

Abstract: A metering valve assembly is provided for metering a fluid. The metering valve assembly includes a position sensor, metering valve, and a thermal compensation mechanism. The metering valve includes a valve housing having a flow passage therethrough, and a valve element movably mounted within the valve housing. The thermal compensation mechanism is coupled between the position sensor and the valve element and configured to adjust the displacement of the position sensor relative to the valve element as a function of fluid temperature.

Abstract: A method for controlling the rate of transfer between operation with gas and liquid fuel types to minimize the time in undesirable operational mode, thereby preventing excessive wear and damage to gas turbine hardware. The method includes completing a fuel prefill for the oncoming fuel type through the fuel system and determining if a total fuel demand for the oncoming fuel type is greater than a predetermined flow rate for the oncoming fuel type. The method also includes selecting a fuel transfer rate and transferring from the offgoing fuel type to the oncoming fuel type at the selected fuel transfer rate. Further, the method includes determining if the offgoing fuel flowrate has decreased below a predetermined flow rate for the offgoing fuel type, selecting a final fuel transfer rate and completing the transfer from offgoing fuel type to oncoming fuel type at a selected final fuel transfer rate.

Abstract: A system and method for accurately supplying fuel flow to a gas turbine engine from a fuel metering pump regardless of variations in operating conditions of the fuel metering pump. The system determines an updated flow characteristic curve for an electrically powered positive displacement pump that is configured to supply fluid via a valve that is configured to open at a predetermined fluid inlet pressure. Electrical current is supplied to the pump to thereby cause the pump to supply the fluid to the valve. The electrical current supplied to the pump is monitored to determine when the valve opens, and one or more points on the updated flow characteristic curve are determined based on the determination of when the valve opens.

Abstract: A method for reducing or eliminating oscillations in a gas turbine fuel control system includes utilizing an engine model to regulate a gas supply pressure for a gas turbine, sensing the pressure of gas actually supplied, and applying integral state feedback plus gas supply pressure feedforward combined with integral plus state feedback to the engine model to control and reduce gas fuel supply variations.

Abstract: A gas turbine engine is provided and includes a combustor having a first interior in which a first fuel supplied thereto by a fuel circuit is combustible, a turbine, a transition zone, including a second interior in which a second fuel supplied thereto by the fuel circuit and the products of the combustion of the first fuel are combustible, a plurality of fuel injectors, which are structurally supported by the transition zone and coupled to the fuel circuit, and which are configured to supply the second fuel to the second interior in any one of a single axial stage, multiple axial stages, a single axial circumferential stage and multiple axial circumferential stages, and a control system coupled to the fuel circuit and configured to control relative amounts of the first and second fuels supplied by the fuel circuit to the first and second interiors.

Abstract: A flexible and automatic system and method for blending an inexpensive secondary gas with a primary gas fuel for operation of a Dry Low NOx gas turbine. The secondary gas may be a gas fuel such as hydrogen, ethane, butane, propane and liquefied natural gas or an inert gas. Combustion dynamics are avoided by controlling the blended fuel within a permissible range for a Modified Wobbe Index. Combustion dynamics and gas turbine exhaust emissions may also be monitored to maintain safe combustion with the blended fuel. A gas turbine control system may adjust the blend and temperature of the primary gas fuel and the secondary gas to promote desired combustion.

Abstract: A gas turbine engine combustion system includes a plurality of fuel injectors circumferentially disposed around a combustor in a one to one fuel supply relationship with a plurality of fuel nozzle valves, and an electronic controller for controlling the fuel nozzle valves to eliminate and/or reduce hot streaking in response to sensed hot streak conditions. The fuel nozzle valves may be modulating valves. The electronic controller may be used to individually control the fuel nozzle valves. The hot streak conditions may be sensed with temperature sensors such as temperature sensors operably mounted in the combustor. A program in the electronic controller may be used for determining broken or malfunctioning sensors by calculating a combustor temperature and comparing it to measured temperatures from the sensors and comparing the measured fuel pressures in the individual fuel nozzle circuits with the simulated or calculated fuel pressures.

Abstract: A turbine engine fuel supply system includes a priority flow line, a plurality of secondary fuel loads, a fluid-powered metering pump, a mechanically-driven fuel pump, and an electric machine. The fluid-powered metering pump, upon receiving fuel at its fuel inlet, rotates at a rotational speed, discharges the fuel from its fuel outlet at a flow rate dependent on the rotational speed, and supplies a first drive torque. The mechanically-driven fuel pump receives a second drive torque and, in response, draws fuel into its fuel inlet and discharges the fuel from its outlet to the fluid-powered metering pump fuel inlet to drive the fluid-powered metering fuel pump. The electric machine receives the first drive torque from the fluid-powered metering pump and generates electrical power.

Abstract: A fuel-flow-rate control device, a power generation system, and a fuel-flow-rate control method which can prevent overshooting of a gas turbine output (gas turbine inlet temperature) and which can improve power generation efficiency are provided. The fuel-flow-rate control device includes a computing portion for obtaining a state quantity relating to operating conditions and temperature conditions of a gas turbine as an input signal and computing a fuel-flow-rate command for controlling a fuel flow rate supplied to a combustor based on the above input signal, and a second selection circuit for setting the above fuel-flow-rate command to be not more than a fuel-flow-rate upper limit. The fuel-flow-rate upper limit is a fuel flow rate at which the gas turbine inlet temperature is set to be not more than a predetermined upper temperature limit.

Abstract: It is known that overshoot in fuel flow rate as a result of compensating for engine heat soak effects can create transient over values in desired thrust parameters. These over values may be displayed and/or utilised in other engine control systems, and although transient may create problems within the engine and apprehension with a user. By adjusting the normally calculated fuel flow rate to a fuel regulator by the introduction of a fuel flow adjustment dependent upon a variable which is related to heat soak effects it is possible to reduce the extent of overshoot as well as the transient time period of that overshoot to ongoing operational state. The variable used may be direct or indirect and will generally utilise a temperature sensor within the engine and/or other engine control procedures which may be extrapolated from such sensor values to provide a variable for heat soak compensation.

Abstract: A fuel delivery and control system is provided including a dual pump fluid circuit configuration comprising a fixed positive displacement pump sized to supply the main engine burn flow ranging from above windmill through cruise, a positive displacement actuation pump including a variable pressure regulator, wherein the actuation pump is sized to supply fluid to engine actuators, valves and other hydraulically operated engine components and a pump flow sharing system interconnecting the two pumps. The combined flow from the two pumps is sufficient to meet the engine flow demand for windmill relight and maximum flow conditions. During cruise or normal operating conditions, the pumps operate in completely isolated flow circuits, minimizing recirculation and therefore heat input into the fuel supply system.

Abstract: A fuel delivery and control system is provided including a dual pump fluid circuit configuration comprising a fixed positive displacement pump sized to supply the main engine burn flow ranging from above windmill through cruise and a variable displacement pump sized to supply fluid to engine actuators, valves and other hydraulically operated engine components with a pump flow sharing system interconnecting the two pumps. The combined flow from the two pumps is sufficient to meet the engine flow demand for windmill relight and maximum flow conditions. During cruise or normal operating conditions, the pumps operate in completely isolated flow circuits, minimizing recirculation and therefore heat input into the fuel supply system.

Abstract: A method for controlling a dynamic response of a fuel control valve in a gas turbine fuel control system is provided. The method includes regulating a fuel supply pressure for a gas turbine using a component model, sensing a pressure of a fuel supply to the gas turbine, and applying a proportional plus integral control algorithm combined with a gas supply pressure feedforward signal to a pressure command signal controlling the fuel control valve to increase a system response in rejecting a pressure disturbance and increase a disturbance rejection bandwidth of a fuel control valve response.

Abstract: A method of operating a gas turbine is provided, wherein the gas turbine engine is coupled to an electrical grid operating at a standardized grid frequency value, and the gas turbine includes a combustor coupled in flow communication with a plurality of independent fuel circuits and a compressor. The method includes determining a deviation of a grid frequency from the standardized grid frequency value and adjusting fuel flow from a portion of the plurality of fuel circuits while maintaining a substantially constant air flow from the compressor to facilitate controlling a fuel to compressor discharge pressure ratio such that a combustor state does not lag changes in airflow when the combustor responds to the grid frequency deviation.

Abstract: A gas turbine, in particular a gas turbine aircraft engine, including a fuel supply device and a control device, wherein at least parts of the control device, in particular of an engine control device, are integrated into the fuel supply device.

Abstract: A system and method for controlling the fuel flow rate in a direct metering fuel control system to compensate for actuator flow. The system includes a fuel metering pump that supplies fuel to a fluid-operated actuator and to a gas turbine engine combustor and determines, using a generated model of the fuel metering pump and/or the fluid-operated actuator, fuel flow rate needed by the gas turbine engine and/or the actuator fuel flow rate needed by the fluid-operated actuator. The fuel flow rate of the fuel metering pump is controlled based on the determined actuator fuel flow rate and the determined engine fuel flow rate.

Abstract: A flow equalizing override assembly is provided for use in conjunction with a gas turbine engine (GTE) and a fuel divider system. In one embodiment, the flow equalizing override assembly includes a housing assembly, a fuel divider (FD) valve, a remotely-actuatable valve, and a controller. The FD valve includes: (i) a piston slidably disposed within the housing assembly and movable between a default position and a flow equalizing position, and (ii) a control chamber defined by the piston and the housing assembly. The remotely-actuatable valve is fluidly coupled to the control chamber and is configured to selectively adjust the fuel pressure therein. The controller is configured to command the remotely-actuatable valve to adjust the pressure within the control chamber such that the piston moves from the default position to the flow equalizing position after ignition of the GTE.

Abstract: Methods and systems for delivering fuel in a gas turbine engine are provided. The system includes a plurality of can annular combustors that includes at least a first set of combustors of the plurality of can annular combustors and at least a second set of combustors of the plurality of can annular combustors wherein each set of combustors is supplied by a separately controllable respective fuel delivery system. The method includes supplying fuel at a first fuel schedule to the first set of combustors and supplying fuel at a second fuel schedule to the second set of combustors during a first mode of operation wherein the second fuel schedule is different than the first fuel schedule, and supplying fuel at the second fuel schedule to the first and second sets of combustors during a second mode of operation.

Abstract: In one aspect, power generation is accomplished by capturing off-gas from a wellhead of an oil producing well, sensing a change in pressure from which a change in available off-gas can be determined, and adjusting a torque supplied by a prime mover to a generator responsive to the change in available off-gas to vary an amount of electricity generated by the generator.

Abstract: A method is provided for supplying a liquid fuel to a gas-turbine engine, e.g. aviation engine. It includes selective fuel delivery through several fuel delivery lines for different engine operating modes based on a required engine power, providing, e.g. feeding the engine operating at minimal power with base or traditional for this type of engine fuel through a base fuel delivery line; in other operating modes the fuel is fed to the engine either through conditioned fuel delivery line with preliminary conditioning of base fuel or through both said fuel delivery lines simultaneously with mixing both fuel flows directly before entering an engine combustion chamber, e.g., in a line connecting intake manifold for the base fuel and each individual fuel injector. An engine, e.g. gas-turbine engine, operating on a liquid or gaseous fuel wherein additional injector nozzles are provided to add a third component—an incombustible evaporative liquid, e.g. water—to the combustion of the fuel mixed with air.

Abstract: A fuel modulation system usable in can-annular combustor systems of turbine engines for more efficiently managing fuel flow to reduce the amount of NOx while maintaining appropriate combustor flame temperatures. The fuel modulation system controls individual inline modulation valves in cooperation with a overall stage control valve to bring a turbine engine through the startup phase and to maintain operating conditions at a load set point while reducing NOx variability between baskets by using individual combustor dynamic pressure measurements. The fuel modulation system may be managed such that individual inline modulation valves remain within a predetermined range of positions relative to a nominal position to reduce NOx variability.