Abstract: Systems and methods for supplying fuel to a gas turbine are described. A fuel may be received, and one or more parameters associated with the received fuel may be determined. Based at least in part upon the determined one or more parameters, a desired pressure for removing one or more liquids from the fuel utilizing a separator may be calculated. The operation of a pressure changing device may then be controlled in order to achieve the desired pressure. In certain embodiments, the operations of the method may be performed by a controller that includes one or more computers.

Abstract: A method for operating a gas turbine engine fuel system with a fuel control valve is disclosed. The method includes metering fuel through the fuel control valve with an effective flow area versus command data set. The method also includes detecting that a change in an effective flow area of the fuel control valve has occurred. The method further includes modifying the effective flow area versus command data set to reflect the detected change in the effective flow area of the fuel control valve.

Abstract: A method for controlling a gas turbine engine fuel control valve during low flow conditions includes positioning the fuel control valve in an operating position. The method also includes determining a fuel control valve flow sensor flow rate while in the operating position and determining a corrected effective flow area (“Cda”) of the fuel control valve. The method further includes generating Cda versus command data with the corrected Cda and the operating position and inserting the generated Cda versus command data into the nominal Cda versus command data set when nominal Cda versus command data is not known at the operating position.

Abstract: A fuel system for an aircraft comprises a boost pump, a main fuel pump and a motive pump. The boost pump receives fuel from a storage unit. The main fuel pump receives fuel from the boost pump and delivers fuel to a distribution system. The motive fuel pump receives fuel from the boost pump, routes fuel through the storage unit, and delivers fuel to an actuator.

Abstract: A method for purging fuel from a fuel system of a gas turbine engine on shutdown of the engine comprises, in one aspect, terminating a fuel supply to the fuel system and using the residual compressed air to create a reversed pressure differential in the fuel system relative to a forward pressure differential of the fuel system used to maintain fuel supply for engine operation, and under the reversed pressure differential substantially purging the fuel remaining in the system therefrom to a fuel source.

Abstract: A system includes a gas turbine engine having a combustor, and a fuel blending system. The fuel blending system further includes a first fuel supply configured to supply a first fuel, a second fuel supply configured to supply a second fuel, a first fuel circuit, a second fuel circuit, and a controller. The first fuel circuit may be configured to blend the first fuel and the second fuel to form a first to form a first fuel mixture. The second fuel circuit may be configured to blend the first fuel and the second fuel to form a second fuel mixture. The controller may be configured to regulate blending of the first fuel mixture and the second fuel mixture based on a measured operating parameter of the combustor.

Abstract: A method of controlling operation of a pressure gain combustor comprises: determining a fuel injector duty cycle and a combustion frequency that meets a target load set point and a target fill fraction of the combustor; determining a fuel supply pressure setting, a fuel injector timing setting and an ignition timing setting that achieves the determined fuel injector duty cycle and combustion frequency; and sending a fuel supply pressure control signal with the fuel supply pressure setting to a fuel pressurizing means of the combustor, a fuel injector control signal with the fuel injector timing setting to a fuel injector of the combustor, and an ignition timing control signal with the ignition timing setting to an ignition assembly of the combustor.

Abstract: The present invention provides a plasma arc torch that can be used for lean combustion. The plasma arc torch includes a cylindrical vessel, an electrode housing connected to the first end of the cylindrical vessel such that a first electrode is (a) aligned with a longitudinal axis of the cylindrical vessel, and (b) extends into the cylindrical vessel, a linear actuator connected to the first electrode to adjust a position of the first electrode, a hollow electrode nozzle connected to the second end of the cylindrical vessel such that the center line of the hollow electrode nozzle is aligned with the longitudinal axis of the cylindrical vessel, and wherein the tangential inlet and the tangential outlet create a vortex within the cylindrical vessel, and the first electrode and the hollow electrode nozzle create a plasma that discharges through the hollow electrode nozzle.

Abstract: Gas turbine, computer readable medium, and method for controlling an operating point of the gas turbine that includes a compressor, a combustor and a turbine is provided. The method includes determining a turbine pressure ratio, calculating a primary to lean-lean mode transfer threshold reference curve as a function of the turbine pressure ratio, determining at a first time when an exhaust temperature associated with the operating point is higher than an exhaust temperature of the primary to lean-lean mode transfer threshold reference curve for the same turbine pressure ratio, and changing, after a predetermined time after the first time, a split fuel quantity from a first value to a second value if the exhaust temperature associated with the operating point remains higher than the exhaust temperature of the primary to lean-lean mode transfer threshold reference curve.

Abstract: The system for mitigating an overspeeding condition of a turbine engine can include a sensor for measuring an actual speed of a gas generator turbine of the turbine engine and a processor for deriving a delta, the delta being a comparison between the actual speed of the gas generator turbine and a predicted gas generator turbine speed. The system is configured for detecting the overspeeding condition when delta is higher than a predetermined threshold. A method of detecting an overspeeding condition during operation of a turbine engine can include measuring an actual speed of a gas generator turbine, then evaluating a delta between the actual speed of the gas generator turbine and a predicted speed of the gas generator turbine, then comparing the delta to a threshold value.

Abstract: A system includes a controller configured to control a semi-closed power cycle system. The controller is configured to receive at least one of a first signal indicative of an oxygen concentration within a first gas flow through a primary compressor, a second signal indicative of power output by the semi-closed power cycle system, a third signal indicative of a temperature of a second gas flow through a turbine, and a fourth signal indicative of a mass flow balance within the semi-closed power cycle system. The controller is also configured to adjust at least one of the first gas flow through the primary compressor, a fuel flow into a combustor, a fraction of the first gas flow extracted from the primary compressor, and an air flow through a feed compressor based on the at least one of the first signal, the second signal, the third signal, and the fourth signal.

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 fuel supply system for a gas turbine engine has a first pump for delivering fuel to a first use on a gas turbine engine, and a second pump for delivering fuel to a second use on the gas turbine engine. A valve allows flow from the first pump to be delivered to the first use, but also routes some flow from the first pump to supplement fuel flow from the second pump until a pressure downstream of the second pump increases. The valve then allows flow from the second pump to flow to the first use to supplement the flow from the first pump.

Abstract: In a method for the low-CO emissions part load operation of a gas turbine with sequential combustion, the air ratio (?) of the operative burners (9) of the second combustor (15) is kept below a maximum air ratio (?max) at part load In order to reduce the maximum air ratio (?), a series of modifications in the operating concept of the gas turbine are carried out individually or in combination. One modification is an opening of the row of variable compressor inlet guide vanes (14) before engaging the second combustor (15). For engaging the second combustor, the row of variable compressor inlet guide vanes (14) is quickly closed and fuel is introduced in a synchronized manner into the burner (9) of the second combustor (15). A further modification is the deactivating of individual burners (9) at part load.

Abstract: A fuel system comprises a first, variable displacement fuel pump operable to supply fuel through a metering valve to an engine, a control servo operable to control the operation of the first pump, a pressure drop control valve (PDCV) responsive to a pressure drop across the metering valve, a second fuel pump, and a spill valve movable between an open position in which substantially all of the fuel supplied by the second fuel pump is returned to an inlet side thereof, and a closed position, or partially closed position, wherein a proportion of the fuel supplied by the second pump is delivered to the engine.

Abstract: The disclosure relates to a method for operating a gas turbine plant which is supplied with a fuel gas via a compressor station. The compressor station includes a compressor which compresses the fuel gas which is fed via a gas feed line and delivers it via at least one control valve to a combustion chamber of the gas turbine plant. A bypass system is arranged in parallel to the compressor via which fuel gas can be directed in a switchable manner past the compressor to the at least one control valve. An energy-saving operation can be achieved in a simple manner by continuously measuring the fuel gas pressure at the outlet of the at least one control valve. A minimum fuel gas pressure, which is desired (e.g., necessary) for operation of the gas turbine, at the inlet of the at least one control valve is determined from the measured pressure values in each case.

Abstract: Provided is a fuel flow control method of a gas turbine combustor provided in a humid air gas turbine, by which method NOx generation in the gas turbine combustor is restricted before and after the starting of humidification and combustion stability is made excellent.

Abstract: Fuel control arrangements for gas turbine engines generally comprise an injector and a fuel control valve. Typically the fuel control valve is controlled in terms of fuel demand through fuel pressure presented to the valve. Fuel demand may vary and in such circumstances stagnation of fuel adjacent to the valve may cause degradation of the fuel and therefore spurious operational performance. By providing a dedicated working fluid, and typically hydraulic, pressure to the valve a variable aperture port can be displaced to alter the fuel flow configuration within the valve. In such circumstances different fuel valve conditions can be generated by altering the available area of aperture in the port to divert or present fuel to the injector between and across first or primary fuel paths and second or pilot fuel paths as required. Thus more flexibility with regard to fuel presentation to the injector is achieved as well as consistency with respect to avoiding fuel degradation as fuel demand varies.

Abstract: Provided is a gas turbine control device that is used in a generating facility including a gas turbine and a generator for generating power when at least rotational power of the gas turbine is transmitted, the gas turbine control device including a first control section for obtaining a first fuel control command for causing generator output to follow a generator output set value decided based on a demand load, where the first control section has a feedback control section (60), and the feedback control section (60) includes a subtraction section (62) for calculating a deviation of the generator output with respect to the generator output set value, a PI control section (64) provided in a later stage of control than the subtraction section (62), and a peak suppression section (66) for suppressing a peak in amplitude characteristics of the generator or a utility grid including the generator.

Abstract: A direct metering fuel supply system includes a fuel pump, a burn flow fuel line, a servo flow fuel line, and a servo regulator. The fuel pump is adapted receive pump commands representative of a commanded fuel flow rate and is configured, in response to the pump commands, to discharge fuel at the commanded fuel flow rate. The burn flow fuel line is in fluid communication with the pump to receive a first portion of the fuel discharged therefrom. The servo flow fuel line is in fluid communication with the pump to receive a second portion of the fuel discharged therefrom. The servo regulator is mounted on the servo flow fuel line and configured to maintain fuel flow rate in the servo flow fuel line at a substantially constant fuel flow rate regardless of fuel flow rate in the burn flow fuel line.

Abstract: A staging valve arrangement is described that comprises an arrangement of electrically driven staging valves that are located, in use, in the high temperature core zone of an engine. Each staging valve may comprise a housing having an inlet, a pilot flow outlet and a mains flow outlet, a valve member movable between a closed position in which the mains flow outlet is closed and an open position in which the mains flow outlet is open, a motor operable to drive the valve member for movement, and a cooling arrangement.

Abstract: A method of sensing a reduction in fuel screen area in a fuel system. The method includes detecting an engine shutdown, initiating an electronic engine control (EEC) built in test, shifting a metering valve from a first position to a second position, determining a travel time of the metering valve, and sensing a reduction in fuel screen area based on the travel time of the metering valve.

Abstract: A fuel metering unit (FMU) comprising a metering valve operable to control the supply of fuel to a delivery chamber of a pressure raising valve (PRV), the PRV including a valve member movable under the influence of the pressure within the delivery chamber between a closed position and an open position in which fuel is able to flow from the delivery chamber to an outlet port, and a push piston movable under the influence of the pressure within a control chamber to urge the valve member towards its open position, wherein the control chamber communicates with a valve control port.

Abstract: The system for mitigating an overspeeding condition of a turbine engine can include a sensor for measuring an actual speed of a gas generator turbine of the turbine engine and a processor for deriving a delta, the delta being a comparison between the actual speed of the gas generator turbine and a predicted gas generator turbine speed. The system is configured for detecting the overspeeding condition when delta is higher than a predetermined threshold. A method of detecting an overspeeding condition during operation of a turbine engine can include measuring an actual speed of a gas generator turbine, then evaluating a delta between the actual speed of the gas generator turbine and a predicted speed of the gas generator turbine, then comparing the delta to a threshold value.

Abstract: In one embodiment, a gas turbine system includes a controller configured to receive fuel composition information related to a fuel used for combustion in a turbine combustor; receive oxidant composition information related to an oxidant used for combustion in the turbine combustor; receive oxidant flow information related to a flow of the oxidant to the turbine combustor; determine a stoichiometric fuel-to-oxidant ratio based at least on the fuel composition information and the oxidant composition information; and generate a control signal for input to a fuel flow control system configured to control a flow of the fuel to the turbine combustor based on the oxidant flow information, a target equivalence ratio, and the stoichiometric fuel-to-oxidant ratio to enable combustion at the target equivalence ratio in the presence of an exhaust diluent within the turbine combustor.

Abstract: A fuel control method for a gas turbine with a combustor being formed of at least two groups of a pluralities of main nozzles for supplying fuel, and that supplies fuel from the main nozzles of all groups upon ignition of the combustor (S1), and supplies fuel from three main nozzles of a group A during subsequent acceleration of the gas turbine (S3). Because fuel is injected from a small number of the main nozzles during acceleration, the fuel flow rate per one main nozzle is increased, thereby increasing the fuel-air ratio (fuel flow rate/air flow rate) in a combustion region and improving the combustion characteristics. Accordingly, the generation of carbon monoxide and unburned hydrocarbon is reduced, whereby no bypass valve is required and manufacturing costs are reduced.

Abstract: A gas turbine control device having a gas turbine control unit for the gas turbine operation control that computes adjustment increments regarding at least one of the airflow rate into the combustor and the pilot ratio, and makes revisions to the actuating variables comprising the airflow rate and the pilot ratio so that the actuating variables are contrasted with the status signals and the variables are modified toward initial design conditions. The gas turbine control unit resets the revisions made to the actuating variables in a case where the level of the combustion vibration is restrained below the predetermined control criterion for a predetermined time span, and the gas turbine is operated under the control settings of the initial design stage.

Abstract: A gas turbine engine is provided and includes a combustor having a first interior in which a first fuel is combustible, the first fuel including natural gas and/or a blend of natural gas and alternate gas receivable by a fuel circuit from an external source, a turbine, a transition zone, including a second interior in which a second fuel, the second fuel including an unblended supply of the alternate gas receivable by the fuel circuit from the external source, and the products of the combustion of the first fuel are combustible, and 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.

Abstract: A control apparatus for controlling a compressor driven by a driving unit generating driving power by a gas turbine and an electric motor includes: a temperature detection section for detecting an exhaust gas temperature of the gas turbine; and a control section for generating a motor torque instruction value for the electric motor based on the detected exhaust gas temperature. Such a control apparatus can realize a control so as not to distribute a load on the electric motor when the exhaust gas temperature of the gas turbine is low and a driving power is low. As a result, the operation efficiency can be enhanced.

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: Control and regulation system of a combustion unit (10) of the type comprising a combustion chamber (11) and a catalyst (40), the control and regulation system comprising: -an acquisition device of signals proportional to functioning parameters characteristic of the functioning state of the combustion unit (10), an electronic data processing unit (30) connected to the signal acquisition device from which it receives signals, a control and regulation program associated with said electronic data processing unit (30), a first fuel distribution valve (20), a second air distribution valve (21), a data base associated with said electronic data processing unit (30), the electronic data processing unit (30) receives signals from the signal acquisition device, processes them and regulates the opening of the first valve (20) and second valve (21) to minimize the polluting emissions of CO and Nox of the combustion unit (10).

Abstract: A method and a system for identifying failures in an aeroengine. The system includes: a mechanism defining a set of standardized indicators representative of operation of the aeroengine; a mechanism constructing an anomaly vector representative of a behavior of the engine as a function of the set of standardized indicators; a mechanism selecting in an event of an anomaly being revealed by the anomaly vector a subset of reference vectors having directions belonging to a determined neighborhood of a direction of the anomaly vector, the subset of reference vectors being selected from a set of reference vectors associated with failures of the aeroengine and determined using criteria established by experts; and a mechanism identifying failures associated with the subset of reference vectors.

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: A method for controlling a turbine engine generator set is disclosed. The method comprises: sensing an operating parameter indicative of a load increase on the turbine engine generator set; operating the turbine engine generator set in a first mode when the sensed operating parameter is within a predetermined range; and operating the turbine engine generator set in a second mode when the sensed operating parameter is outside the predetermined range. The second mode provides a rate of adjustment of operation of the turbine engine generator set that is greater than a rate of adjustment during the first mode.

Abstract: A device and system for monitoring and controlling the flow media through a flow circuit, for example, the flow of coolant through a coolant circuit of a turbine engine fuel system, measures flow rates at the supply and return sides of the circuit and compares the measured flow rates against a threshold flow rate difference to detect the presence of a flow leak condition. Upon detecting a leak condition, the controller automatically operates a flow control valve to shut off flow to the flow circuit for repair of the leak or other low flow condition. The controller can also include components for measuring the temperate of the flow media at one or both of the supply and return sides of the circuit. The measured temperature signals can be processed to detect a high or low temperature condition. Upon detecting a low temperature condition, the controller automatically reduces the flow rate of the flow media until the condition has been corrected.

Abstract: A gas turbine system includes a compressor, a fuel source, a combustor, and a turbine. The compressor is configured to compress air. The fuel source is configured to supply fuel to a plurality of fuel manifolds. The combustor is configured to receive the air from the compressor, to receive the fuel from the plurality of fuel manifolds, and to combust the air and the fuel into combustion products. The turbine is configured to extract work from the combustion products. A fuel control valve is disposed within each of the plurality of fuel manifolds and is configured to throttle the fuel to the combustor when the gas turbine system is operating in an electrical island mode.

Abstract: Systems and methods for controlling fuel flow within a machine are provided. A plurality of fuel types provided to the machine and a plurality of fuel circuits associated with the machine may be identified, each of the plurality of fuel circuits adapted to be provided with one or more of the plurality of fuel types. A fuel flow parameter for calculating fuel flow may be identified, and a respective fuel flow for each of the one or more fuel types provided to each of the plurality of fuel circuits may be calculated based at least in part on the identified fuel flow parameter. Based at least in part on the calculation of the respective fuel flows, operation of one or more fuel flow control devices providing fuel to the plurality of fuel circuits may be controlled.

Abstract: A method for actively controlling fuel flow from a fuel pump to a mixer assembly of a gas turbine engine combustor, where the mixer assembly includes a pilot mixer and a main mixer. The pilot mixer further includes an annular pilot housing having a hollow interior, a primary fuel injector mounted in the pilot housing and adapted for dispensing droplets of fuel to the hollow interior of the pilot housing, a plurality of axial swirlers positioned upstream from the primary fuel injector. The fuel flow control apparatus further includes: at least one sensor for detecting dynamic pressure in the combustor; a fuel nozzle; and, a system for controlling fuel flow supplied by the fuel nozzle through the valves. The fuel nozzle includes: a feed strip with a plurality of circuits for providing fuel to the pilot mixer and the main mixer; and, a plurality of valves associated with the fuel nozzle and in flow communication with the feed strip thereof.

Abstract: A fuel delivery system for use, for example in a gas turbine engine system, includes a fuel metering unit including a main fuel inlet. The fuel metering unit includes fuel pressure and temperature sensors. A cavitating venturi is in fluid communication with the main fuel inlet and includes venturi characteristics such as throat diameter. A fuel nozzle is in fluid communication with the venturi for delivering fuel to the gas turbine engine. A controller is connected to the pressure temperature sensors and is operable to calculate a flow rate of fuel through the nozzle based upon the signals from the pressure and temperature sensors and the fuel and venturi characteristics. A variable cavitating venturi may be arranged within the throat to vary the area and adjust the flow rate through the venturi. The cavitating venturi can also be used at the fuel nozzle to further simplify the fuel delivery system.

Abstract: A fuel valve for a gas turbine engine includes a passageway configured to direct a fuel to the engine and a flow restriction positioned in the passageway. The fuel valve may also include a first pressure sensor coupled to the passageway upstream of the restriction through an upstream port, and a second pressure sensor coupled to the passageway downstream of the restriction through a downstream port. The fuel valve may further include a third pressure sensor coupled to the upstream port through a first branch port, and a fourth pressure sensor coupled to the downstream port through a second branch port.

Abstract: A fuel metering system for supplying fuel to load includes a variable displacement piston pump having an adjustable hanger that is movable to a plurality of positions. The variable displacement piston pump is configured to receive a drive torque and, upon receipt of the drive torque, to supply fuel to the plurality of loads at a flow rate dependent on the position of the adjustable hanger. A hanger actuator is coupled to receive hanger position commands and is operable, in response thereto, to move the adjustable hanger to the commanded position.

Abstract: Disclosed is a system for suppressing vibration and noise mitigation in structures such as blades in turbomachinery. The system includes flexible piezoelectric patches which are secured on or imbedded in turbomachinery blades which, in one embodiment, comprises eight (8) fan blades. The system further includes a capacitor plate coupler and a power transfer apparatus, which may both be arranged into one assembly, that respectively transfer data and power. Each of the capacitive plate coupler and power transfer apparatus is configured so that one part is attached to a fixed member while another part is attached to a rotatable member with an air gap therebetween. The system still further includes a processor that has 16 channels, eight of which serve as sensor channels, and the remaining eight, serving as actuation channels. The processor collects and analyzes the sensor signals and, in turn, outputs corrective signals for vibration/noise suppression of the turbine blades.

Abstract: The present combustor of gas turbine engine includes: a fuel injection unit including a fuel spray part to spray a fuel so that a diffusion combustion region is formed in a combustion chamber, and a pre-mixture supply part to supply a pre-mixture of a fuel and an air so that a pre-mixture combustion region is formed in the combustion chamber; and a fuel supply unit to supply the fuel to the fuel spray part and pre-mixture supply part. The fuel supply unit includes: a pilot fuel passage and a main fuel passage to supply the fuel to the fuel spray part and the pre-mixture supply part, respectively; an assembled fuel passage to supply the fuel to the pilot and main fuel passages; and a fuel distributor disposed at a branch point where the assembled fuel passage is connected to both the pilot and main fuel passages. The fuel distributor is configured to automatically control amounts of the fuel to be distributed to the pilot fuel passage and to the main fuel passage in accordance with the fuel pressure.

Abstract: A pressure regulating valve assembly includes a pressure regulating valve sleeve and a pressure regulating valve spool. The pressure regulating valve sleeve includes a first window set and a second window set. The pressure regulating valve spool includes a first cylindrical portion, a second cylindrical portion, and a third cylindrical portion formed between the first and second cylindrical portions. The pressure regulating valve spool also includes an angled bucket formed on the first cylindrical portion having a high gain portion of a first width, a low gain portion of a second width, and a ratio of the first width to the second width between 1.44 and 1.47. The pressure regulating valve spool further includes an angled outlet surface. The angled bucket is configured to align with the first window set and the angled outlet surface is configured to align with the second window set.

Abstract: A controller receives a power-level command representative of a level of power to be transmitted by a single-spool turboshaft engine to a controllable load. A torque command determined responsive to a measure of inlet pressure, from a control schedule responsive to the power-level command, is representative of a level of torque to be transmitted by an element to drive the controllable load. Under some operating conditions, a rotational speed command provides for at least nearly minimizing a measure of associated fuel consumption when the transmitted torque is regulated to the level corresponding to the torque command by controlling one of the controllable load and a fuel flow to the engine, and the other of the controllable load and the fuel flow to the engine is controlled so as to regulate an associated rotational speed to a level corresponding to the rotational speed command.

Abstract: A fuel supply device includes a fuel supply pipe receiving fuel at a non-regulated pressure delivered by a pump, a device for measuring the flow rate of fuel in the pipe, a first controlled variable-restriction valve mounted in the supply pipe, a control system connected to the flow rate measurement device and to the first valve to control the valve to deliver fuel to the engine at a desired flow rate under normal operating conditions of the engine, a second controlled variable-restriction valve mounted in the supply pipe in series with the first valve, and a control for controlling the second valve to enable the engine to be supplied with fuel at an adjustable, reduced flow rate in response to detecting over-speed or over-thrust of the engine.

Abstract: A fuel control system (100) for supplying metered fuel flow to a gas turbine engine is disclosed that includes a variable delivery fuel pump (116) for outputting a fuel flow that includes a burn fuel flow for the gas turbine engine and a surplus fuel flow recirculated back to an inlet (124) of the variable delivery fuel pump (116) and a pump control (148, 158, 122) for controlling the output of the variable delivery fuel pump to maintain the surplus fuel flow at a substantially constant rate. A method of controlling a fuel system (100) is also disclosed.

Abstract: A power generation plant comprises a plant control device (600) including two switchable control modes, i.e., a gas-turbine load control mode (7a) and a steam-turbine load control mode (7b). When the control is performed with the gas-turbine load control mode (7a), a fuel valve (104a) is controlled based on a load of a whole generator set (100), and a steam regulating valve (203a) is controlled based on an exhaust pressure of a steam turbine (202a). When the control is performed with the steam-turbine load control mode (7b), the fuel valve (104a) is controlled such that a valve opening degree thereof is maintained constant, and the steam regulating valve (203a) is controlled based on a load of the whole generator set (100).

Abstract: A system comprises a pressure raising valve having a valve member movable within a bore between a closed position and an open position in which fuel supplied to the pressure raising valve from a metering valve, in use, is delivered to an engine manifold, the valve member being urged towards its closed position by the fuel pressure within a control chamber, the pressure raising valve including a low pressure port which communicates with the control chamber when the valve member is in its closed position, the valve member closing the low pressure port upon movement thereof away from its closed position beyond a predetermined distance.

Abstract: Embodiments for controlling a gas turbine engine to minimize combustion dynamics and emissions are disclosed. Methods and an apparatus are provided for controlling the gas turbine engine where a compressor inlet temperature is measured and a turbine reference temperature is calculated in real-time and utilized to determine the most-efficient fuel splits and operating conditions for each of the fuel circuits. The fuel flow for the fuel circuits are then adjusted according to the identified fuel split.