Abstract: A gas turbine engine is provided. The gas turbine engine includes an air inlet, a combustor, an exhaust and first and second measurement devices. A plurality of fuel supply lines is provided to the at least one combustor. The first measurement device measures an amount of a gas in the air inlet. The second measurement device measures an amount of the gas in the exhaust. A control unit varies the fuel supply in the plurality of fuel supply lines so as to control the amount of the gas in the exhaust. The variation is made in dependence upon both the measured amount of the gas in the air inlet and the measured amount of the gas in the exhaust.

Abstract: An overheating detection processing system monitors in real time and stores data samples from the different types of power plant overheating detectors. The system determines a likelihood of whether a stored detector output sample reading, alone or in combination with other readings, is indicative of monitored power plant equipment overheating. The system references previously stored information in an information storage device that associates respective types of detector sample reading levels with equipment overheating. The system also compares a combination of stored sample readings and establishes overheating determination confidence levels. The confidence levels information is combined to derive an overall confidence level of whether the power plant equipment is overheated. An overheating alarm response is initiated if an overheating condition is determined at any confidence level. Additional responses are made based on a combination of calculated confidence levels.

Abstract: A method for controlling a hybrid machine is disclosed. The hybrid machine may be equipped with a turbine engine, a generator connected in series with the turbine engine, an electrical energy storage device, and a motor drivingly connected to a power output component for the hybrid machine. A controller may receive a power demand signal, determine a power level in the electrical energy storage device, determine available inertial energy stored at least in rotating components of the turbine engine and the generator, and provide one or more control signals to selectively control powering the turbine engine to full power, selectively turn off all fuel to the turbine engine, selectively store excess energy as electrical energy by directing excess electrical energy from the generator to the electrical energy storage device, and selectively store excess energy as inertial energy.

Abstract: A control system for a gas turbine engine is disclosed. The control system may include a computer processor. The control system may also include an outer loop control module programmed into the computer processor to determine a torque request based at least in part on a real-time collective lever angle command. The control system may also include an inner loop control module programmed into the computer processor to receive the torque request from the outer loop control module, to determine fuel flow and inlet guide vane schedules based at least in part on the received torque request, and to send signals to a gas generator of the gas turbine engine in order to control the gas generator according to the determined fuel flow and inlet guide vane schedules.

Abstract: According to one aspect of the invention, a gas turbine engine includes a combustor, a fuel nozzle placed in an end of the combustor, and a passage configured to receive an air flow from a compressor discharge casing, wherein the passage directs the air flow into a chamber downstream of the nozzle, wherein a chamber pressure is lower than a compressor discharge casing pressure. The gas turbine engine also includes a flow control device configured to control the air flow from the compressor discharge casing into the passage.

Abstract: A system is provided that includes a memory storing a turbomachinery degradation model configured to model degradation of a turbomachinery over time. The system also includes a controller communicatively coupled to the memory and configured to control the turbomachinery based on a feedback signal and the turbomachinery degradation model. Moreover, the turbomachinery degradation model is configured to use a target power to derive a control parameter by estimating a modeled power of the turbomachinery, and the controller is configured to use the control parameter to control the turbomachinery.

Abstract: A method is disclosed for controlling gas turbine operation in response to lean blowout of a combustion can. The gas turbine comprises a pair of combustion cans. The method includes sensing that a first combustion can is extinguished during a full load operation of the gas turbine, adjusting a fuel ratio between the fuel nozzles in each can, delivering a richer fuel mixture to the fuel nozzles nearest to the cross-fire tubes, generating a cross-fire from the second combustion can to the first combustion can, detecting a recovery of the turbine load, and adjusting the fuel ratio to the normal balanced fuel distribution between the fuel nozzles in each can.

Abstract: In one embodiment, a system includes a turbine combustor having a combustor liner disposed about a combustion chamber, a head end upstream of the combustion chamber relative to a downstream direction of a flow of combustion gases through the combustion chamber, a flow sleeve disposed at an offset about the combustor liner to define a passage, and a barrier within the passage. The head end is configured to direct an oxidant flow and a first fuel flow toward the combustion chamber. The passage is configured to direct a gas flow toward the head end and to direct a portion of the oxidant flow toward a turbine end of the turbine combustor. The gas flow includes a substantially inert gas. The barrier is configured to block the portion of the oxidant flow toward the turbine end and to block the gas flow toward the head end within the passage.

Abstract: A reformer for use in a gas turbine engine specially configured to treat a supplemental fuel feed to the combustor that includes a reformer core containing a catalyst composition and an inlet flow channel for transporting the reformer fuel mixture, air and steam (either saturated or superheated) into a reformer core. An outlet flow channel transports the resulting reformate stream containing reformed and thermally cracked hydrocarbons and substantial amounts of hydrogen out of the reformer core for later combination with the main combustor feed. Because the catalytic partial oxidation reaction in the reformer is highly exothermic, the additional heat is transferred (and thermally integrated) using one or more heat exchange units for a first and/or second auxiliary gas turbine fuel stream that undergo thermal cracking and vaporization before combining with the reformate. The combined, hydrogen-enriched feed significantly improves combustor performance.

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: Methods and apparatus are provided for selectively controlling the rotational speed of a gas turbine engine that drives a load compressor having movable inlet guide vanes and that is coupled to receive fuel at a fuel flow rate up to a maximum fuel flow rate. The rotational speed of the gas turbine engine, and the fuel flow rate to the gas turbine engine, are both sensed. If the sensed rotational speed of the gas turbine engine is less than a predetermined value and the sensed fuel flow rate to the gas turbine engine equals or exceeds the maximum fuel flow rate, the position of the inlet guide vanes is controlled to reduce load compressor mechanical load on the gas turbine engine.

Abstract: A method is provided for operating a gas turbine in a power station in which limits of the operating concept, which provide limits for optimization of the power station operation in respect of efficiency, service life consumption, emissions and power provision to the grid system, are adapted during operation. In particular, temperature limits and compressor inlet guide vane position limits are varied as a function of the optimization aims. A gas turbine power station is also provided for carrying out the method.

Abstract: A method of transitioning from a first operating mode to a second operating in a gas turbine engine. An amount of fuel provided to a primary fuel injection system of the combustor apparatus is reduced. An amount of fuel provided to a secondary fuel/air injection system of the combustor apparatus is reduced, wherein the secondary fuel/air injection system provides fuel to a secondary combustion zone downstream from a main combustion zone. A total amount of air provided to the combustor apparatus is reduced, wherein portions of the air are provided to each of the injection systems. Upon reaching operating parameters corresponding to the second operating mode, the amount of fuel provided to the primary fuel injection system is increased, the amount of fuel provided to the secondary fuel/air injection system is reduced, and the total amount of air provided to the combustor apparatus is increased.

Abstract: The invention discloses a method for operating a gas turbine with sequential combustion, which gas turbine includes a compressor, a first combustor with a first combustion chamber and first burners, which receives compressed air from the compressor, a second combustor with a second combustion chamber and second burners, which receives hot gas from the first combustor with a predetermined second combustor inlet temperature, and a turbine, which receives hot gas from the second combustor. The CO emission for part-load operation is reduced by reducing the second combustor inlet temperature for base-load operation of the gas turbine, and increasing the second combustor inlet temperature when decreasing the gas turbine load (RLGT) from base-load to part-load.

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: Provided is a gas turbine operation control device and operation control method that are capable of suppressing turbine inlet temperature and of satisfying the demand response for shaft output. An IGV emergency fully-open flag is activated when the output of a generator is in a high load band at or above a predetermined value, and the like. When the IGV emergency fully-open flag is activated, the degree of opening of an inlet guide vane is set to a predetermined degree of opening, a temperature adjustment setting is set by switching in accordance with the degree of opening of the inlet guide vane, and an exhaust gas temperature setting value or a blade path temperature setting value of a turbine, for controlling the fuel supply amount for a combustor, is generated based on the temperature adjustment setting.

Abstract: A gas turbine engine comprises a compressor, a combustor, a turbine, and an electronic engine control system. The compressor, combustor, and turbine are arranged in flow series. The electronic engine control system is configured to estimate combustor fuel-air ratio based on a realtime model-based estimate of combustor airflow, and commands engine actuators to correct for a difference between the estimated combustor fuel-air ratio and a limit fuel-air ratio selected to avoid lean blowout.

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 for controlling a steam power plant is provided. The method includes the steps of providing a first signal showing a reduction of the current power level of the generator, generating a second signal showing a short circuit interruption as a function of the first signal, resetting the second signal after a predetermined time period and blocking the second signal for a predetermined period of time, stopping and subsequently starting the turbine as a function of the second signal, generating a third signal showing a load rejection as a function of the first signal, and permanently stopping the turbine as a function of the third signal. A device for controlling a steam power plant is also provided.

Abstract: Simple, robust and systematic solutions are provided for controlling counter-rotating open-rotor (CROR) gas turbine engines. The solutions mathematically decouple the two counter rotating rotors of a CROR engine by model-based dynamic inversion, which allows application of single-input-single-output (SISO) control concepts. The current solutions allow fuel flow to be treated as a known disturbance and rejected from the rotor speeds control. Furthermore, the current control solutions allow a simple and well-coordinated speed phase synchronizing among the four rotors on a two-engine vehicle.

Abstract: A system for tuning the operation of a gas turbine is provided based on measuring operational parameters of the turbine and directing adjustment of operational controls for various operational elements of the turbine. A controller is provided for communicating with sensors and controls within the system. The controller receiving operational data from the sensors and comparing the data to stored operational standards to determining if turbine operation conforms to the standards. The controller then communicates selected adjustment in an operational parameter of the turbine. The controller then receives additional operational data from the sensors to determine if an additional adjustment is desired or is adjustment is desired of a further selected operational parameter.

Abstract: A two-shaft gas turbine is capable of starting premixed combustion without extinguishing a flame. The two-shaft gas turbine includes a combustor and a gas generator controller. The combustor has a premix burner that includes combustion regions in which premixed combustion is to be carried out individually. The gas generator controller controls the combustor. In a method for starting the premixed combustion in the combustor, the gas generator controller selects at least one of the combustion regions in which the premixed combustion is to be carried out, on the basis of a fuel-air ratio, and starts premix combustion in the selected combustion region or separately in each of the selected combustion regions. Further, as the fuel-air ratio is increased, the controller increases the number of the selected region in which the premixed combustion is carried out.

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

Abstract: A method and apparatus are disclosed for a multi-spool gas turbine engine with a variable area turbine nozzle and a motor/alternator device on the highest pressure turbo-compressor spool for starting the gas turbine and power extraction during engine operation. During power down of the engine, the variable area turbine nozzle may be used in conjunction with power extraction to maintain a near constant combustor outlet temperature while controlling turbine inlet temperatures on the turbines downstream of the highest pressure turbine and controlling spool speed on the highest pressure turbine.

Abstract: Provided are more efficient techniques for operating gas turbine systems. In one embodiment a gas turbine system comprises an oxidant system, a fuel system, a control system, and a number of combustors adapted to receive and combust an oxidant from the oxidant system and a fuel from the fuel system to produce an exhaust gas. The gas turbine system also includes a number of oxidant-flow adjustment devices, each of which are operatively associated with one of the combustors, wherein an oxidant-flow adjustment device is configured to independently regulate an oxidant flow rate into the associated combustor. An exhaust sensor is in communication with the control system. The exhaust sensor is adapted to measure at least one parameter of the exhaust gas, and the control system is configured to independently adjust each of the oxidant-flow adjustment devices based, at least in part, on the parameter measured by the exhaust sensor.

Abstract: A method for generating electrical energy, wherein a carbonaceous fuel is gasified to a combustible gas, the combustible gas being combusted to drive an apparatus chosen from a gas turbine and a gas engine. Relatively hot exhaust gas from the apparatus is passed along a heat exchanger for removing heat from the relatively hot exhaust gas results in relatively cold exhaust gas after passing the heat exchanger. A kaolin or metakaolin-containing sorbent and a source of active free silica are introduced after the apparatus to remove mercury from the relatively hot exhaust gas, the relatively hot exhaust gas having a temperature of at least 800° C.

Abstract: A method for reducing the amount of carbon monoxide and oxygen emissions in a hydrocarbon combustor in a gas turbine engine by feeding hydrocarbon fuel and an oxidizer component into the head end of the combustor while also injecting substantially inert gas into the combustor with the fuel and oxidizer; forming a combustor exhaust stream that mixes with the recycle; cooling the combustor exhaust; detecting the amount of carbon monoxide and oxygen in the exhaust and adjusting the amount of fuel, oxidizer and inert gas feeds based on the detected amounts.

Abstract: This invention discloses systems and methods for control of a gas turbine or a gas turbine generator, where the gas turbine is connected to a dryer vessel in which gas turbine exhaust gases are used to heat treat a material in the dryer vessel. The control system comprises one or more sensors for temperature, moisture and/or flow rate in the dryer vessel and/or of the material inside, entering and/or exiting the dryer vessel and a controller responsive to the sensor for controlling the fuel and/or air flow into the gas turbine. This control system and method enables providing the appropriate heat output from the gas turbine to meet the process heat required for the desired material treatment. Optionally, the gas turbine can be a liquid fuel turbine engine, or a reciprocating engine can be substituted for the turbine engine.

Abstract: A gas turbine comprises a plurality of target exhaust temperature determination modules, the plurality of target exhaust temperature modules comprising a nitrogen oxide (NOx) compliance module configured to determine an exhaust temperature at which an exhaust of the gas turbine complies with a maximum permitted level of NOx; at least one bias module, the at least one bias module configured to apply a bias to an output of at least one of the plurality of target exhaust temperature determination modules; and a controller configured to operate the gas turbine to produce the exhaust temperature determined by the NOx compliance module.

Abstract: Compensation is provided for a fuel demand signal of a gas turbine controller during transition between operating modes. The compensation adjusts fuel demand to account for combustion efficiency differences between the starting and ending operating mode that otherwise can lead to severe swings in combustion reference temperature and lean blowout.

Abstract: A twin-shaft gas turbine 1, which has a gas generator 2 including a compressor 7, a combustor 8, and a high-pressure turbine 9, is configured to make a first control mode and a second control mode selectively useable for control of the gas generator. In addition, in the first control mode, an IGV angle in the compressor is controlled in accordance with a corrected shaft rotation speed of the gas generator, and in the second control mode, the IGV angle is controlled to maintain a constant gas generator shaft rotation speed. Furthermore, the first control mode is used to start, to stop, and to operate the turbine under fixed or lower load conditions, and that the second control mode is used under operational states other than those to which the first control mode is applied.

Abstract: A fuel controller, and associated method, provides a fuel control output signal to a fuel control actuator to control operations. The fuel controller determines the fuel control output signal based on rotational speed error. A combustion air controller provides a combustion air control output signal to a combustion air control actuator to control operations. A cross channel controller is in communication with the fuel controller and the combustion air controller. The cross channel controller provides a combustion air control modification signal to the combustion air controller. The combustion air control modification signal is determined from the fuel control output signal using an air versus fuel model. The combustion air controller determines a preliminary combustion air control signal based on an exhaust temperature error, and further determines the combustion air control output signal based on both of the preliminary combustion air control signal and the combustion air control modification signal.

Abstract: A twin-shaft gas turbine 1, which has a gas generator 2 including a compressor 7, a combustor 8, and a high-pressure turbine 9, is configured to make a first control mode and a second control mode selectively usable for control of the gas generator. In addition, in the first control mode, an IGV angle in the compressor is controlled in accordance with a corrected shaft rotation speed of the gas generator, and in the second control mode, the IGV angle is controlled to maintain a constant gas generator shaft rotation speed. Furthermore, the first control mode is used to start, to stop, and to operate the turbine under fixed or lower load conditions, and that the second control mode is used under operational states other than those to which the first control mode is applied.

Abstract: A gas turbine system including a source of gas coupled to a source of fuel wherein the gas and the fuel are combined to form a mixture of gas and fuel prior to the mixture being introduced to a fuel nozzle of the gas turbine system.

Abstract: A coordinated air-fuel controller and associated method provide a fuel controller, a combustion air controller and a steady-state air versus fuel model. The fuel controller generates a fuel control output signal and the combustion air controller generates a combustion air control output signal. The fuel controller determines a preliminary fuel control signal based on at least one of first and second loop control signals, and determines the fuel control output signal based on the preliminary fuel control signal. The steady-state air versus fuel model processes the preliminary fuel control signal to determine an expected steady-state combustion air control signal. The combustion air controller determines a preliminary combustion air control signal based on at least one of a third loop control signal and a fourth loop control signal, and determines the combustion air control output signal based on the preliminary combustion air control signal and the expected steady-state combustion air control signal.

Abstract: An internal-combustion engine receives no air from outside atmosphere and it discharges no gas into outside atmosphere. The engine receives fuel, oxygen and recycled combustion gas and its exhaust consists mostly of carbon dioxide and water vapor. Most of the gas exhausted from the engine is recycled back into the engine intake, and the remaining gas is cooled and condensed into liquid carbon dioxide and water. Discharge of greenhouse gas into environment and emission of other harmful air pollutants are eliminated.

Abstract: A fuel control device and method of a gas turbine combustor, for advanced humid air turbines, in which plural combustion units comprising plural fuel nozzles for supplying fuel and plural air nozzles for supplying air for combustion are provided. A part of the plural combustion units are more excellent in flame stabilizing performance than the other combustion units. A fuel ratio, at which fuel is fed to the part of the combustion units is set on the basis of internal temperature of the humidification tower and internal pressure of the humidification tower to control a flow ratio of the fuel fed to the plural combustion units.

Abstract: Provided are a combustor control method and a combustor controller capable of calculating the combustion air flow and the fuel flow in multi-shafts gas turbine with high precision and without the need of performing complicated calculations and thereby calculating a fuel-air ratio necessary for stable combustion control. The multi-shaft gas turbine is made up of a gas generator turbine and a power turbine. Combustors includes a diffusive combustion units and a plurality of premixed combustion units.

Abstract: Methods and systems for controlling a combustor for a gas turbine engine are provided. According to one example embodiment, a system includes an air control assembly associated with at least one air path of a combustor for a gas turbine engine. Additionally, the system also includes at least one sensor for sensing at least one operating parameter of the gas turbine engine. Further, the system also includes a controller operable to receive at least one operating parameter sensed by the at least one sensor, and further operable to selectively control an air control assembly based at least in part on the at least one operating parameter sensed by the at least one sensor.

Abstract: A gas-turbine engine receives no air from outside atmosphere. Instead, combustion gas expelled from the engine is cooled and recycled back into the engine. That gas contains no nitrogen and consists mostly of carbon dioxide and water vapor. Oxygen and fuel are added to the recycled gas, and the resulting mixture is used to perform an internal-combustion process. A small amount of the expelled combustion gas is discharged into outside environment, and the rest is recycled. Since no nitrogen is present, no nitrogen oxides are produced. The amount of other harmful exhaust emissions, including particulate matter, is greatly reduced too, since most of them are recycled back into the engine. The engine is inherently supercharged with controllable combustion-gas pressure and, in some cases, can operate without a compressor. Since the combustion gas is heavier than air, the engine can be substantially smaller than a conventional engine of equal power.

Abstract: A method and apparatus for modulating the thrust during a flight envelope of a multiple combustor chamber detonation engine using cross-combustor chamber detonation initiation are provided. The detonation combustor chambers are filled with a combustible mixture of fuel and oxidizer. The combustible mixture in one of the detonation combustor chambers is ignited by an ignition source, and the remaining detonation combustor chambers are ignited by detonation cross-firing via connectors. A controller controls the ignition source and the supply of oxidizer and fuel to the detonation combustor chambers to modulate the thrust of the engine during the flight envelope.

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: Control systems and a method for controlling a load point of a gas turbine engine are provided. A control system includes a controller that receives a temperature signal and a pressure signal associated with exhaust gases from the gas turbine engine. The controller is further configured to generate the fuel control signal. The controller is further configured to generate an actuator control signal such that flow restriction member is moved from the first operational position to the second operational position to restrict the flow path such that the exhaust gases have a temperature level within a desired turndown temperature range, the pressure level in the exhaust gases is less than a threshold pressure level, and the load point of the gas turbine engine is adjusted to toward a target load point.

Abstract: A method for using an aerodynamic stability management system is disclosed. The method includes placing at least one pressure sensor in a compressor, the at least one pressure sensor communicating with an aerodynamic stability management system controller and monitoring gas turbine engine performance using the aerodynamic stability management system controller. The controller includes a memory, an input/output interface and a processor. The method also includes defining a correlation threshold value and calculating a correlation measure using a plurality of pressure signals generated by the at least one pressure sensor and comparing the correlation measure with the correlation threshold value. When the correlation measure is less than the correlation threshold value a corrective action is implemented.

Abstract: A gas turbine control method for preventing then operation from deviating from the operating state at the ideal fuel and air flow-rates expected when the gas turbine is designed and maintaining an efficient operating state.

Abstract: Provided is a gas turbine operation control device and operation control method that are capable of suppressing turbine inlet temperature and of satisfying the demand response for shaft output. An IGV emergency fully-open flag is activated when the output of a generator is in a high load band at or above a predetermined value, and the like. When the IGV emergency fully-open flag is activated, the degree of opening of an inlet guide vane is set to a predetermined degree of opening, a temperature adjustment setting is set by switching in accordance with the degree of opening of the inlet guide vane, and an exhaust gas temperature setting value or a blade path temperature setting value of a turbine, for controlling the fuel supply amount for a combustor, is generated based on the temperature adjustment setting.

Abstract: A combustor (22) for a gas turbine (10) includes a main burner oxidizer flow path (34) delivering a first portion (32) of an oxidizer flow (e.g., 16) to a main burner (28) of the combustor and a pilot oxidizer flow path (38) delivering a second portion (36) of the oxidizer flow to a pilot (30) of the combustor. The combustor also includes a flow controller (42) disposed in the pilot oxidizer flow path for controlling an amount of the second portion delivered to the pilot.

Abstract: A pulse detonation combustor (PDC)-based hybrid engine control system includes a programmable controller directed by algorithmic software to control a rotational shaft speed of the PDC-based hybrid engine, an air inlet valve rotational speed for the PDC, and a fuel fill time period for the PDC in response to a corresponding low pressure turbine (LPT) shaft speed signal or a power difference signal based on a difference between desired power and actual power produced by the PDC-based hybrid engine and further in response to a fuel fill time signal for the PDC, such that a desired fuel fill fraction and stoichiometric ratio are maintained and further such that a mass air flowrate from an air compressor matches a mass air flowrate ingested via the PDC while the PDC-based hybrid engine is operating in an acceleration mode or a deceleration mode.

Abstract: A burner including a pressure measurement device for pressure measurement in a combustion medium inside a gas turbine is provided. The burner supplies the combustion medium in an uncombusted state to a combustion chamber of the gas turbine. The pressure measurement device includes a measuring point defining the location of the pressure measurement, wherein the measuring point is located inside the burner of the gas turbine. In addition, a gas turbine including a burner and a method for controlling a fuel supply to a burner are provided.

Abstract: Methods and apparatus are provided for detecting a flameout of an operating turbomachine that is configured to receive a controlled flow of bleed air from a bleed air source and a controlled flow of fuel from a fuel source. A value of an operational parameter within the turbomachine is detected and a determination is made as to whether it has varied by a predetermined amount. If the operational parameter has varied by the predetermined amount, a flameout confirmation test is triggered. The flameout confirmation test includes holding the controlled flow of bleed air constant, commanding an increase in turbomachine speed, and confirming that a flameout has occurred by detecting that the controlled fuel flow to the turbomachine is at a maximum fuel flow limit and that actual turbomachine speed differs from the commanded turbomachine speed by a predetermined speed error.