Class / Patent application number | Description | Number of patent applications / Date published |
060390240 | Automatic | 87 |
20080250769 | System and method for augmenting turbine power output - A method and system augments shaft output of gas turbine engines that can be used in multiple modes of operation. The system comprises a washing unit capable of injecting atomized water into the gas turbine engine, thereby obtaining a release of fouling material from the at least one compressor blade; and at least one water injection unit capable of injecting atomized water into the air stream of the gas turbine engine's inlet duct or at the gas turbine, under the control of a computational fluid dynamic model, in order to increase a mass flow of said air flow, wherein the power output from said gas turbine engine can be augmented. | 10-16-2008 |
20090241506 | Gas turbine system and method - A gas turbine system and method is provided. The proposed gas turbine system includes a combustor with at least one burner. The burner has an entry for introducing a fuel into an operating medium composed of a gas containing an oxidant to facilitate combustion of the fuel. In operation, the combustion of the fuel generates a flame and a resulting combustion gas. The provided gas turbine system includes at least one oxygen sensor located downstream of the flame, and measures an oxygen concentration of the combustion gas at that location. Further, the proposed gas turbine system includes a device to determine the temperature of the flame based upon the measured oxygen concentration of the combustion gas at the location of at least one oxygen sensor. | 10-01-2009 |
20100000198 | GAS TURBINE WITH AT LEAST ONE MULTI-STAGE COMPRESSOR UNIT INCLUDING SEVERAL COMPRESSOR MODULES - A gas turbine includes at least one multi-stage compressor unit | 01-07-2010 |
20100050591 | Method for automatic closed-loop control of one or more combustion temperatures in a gas turbine installation and method for determination of the water content in the working fluid of a gas turbine instalation - The invention relates to a method for automatic closed-loop control of one or more combustion temperatures in a gas turbine installation, having the following steps: measurement of a plurality of temperatures of the working fluid of the gas turbine installation at various positions in the gas turbine installation, measurement of a plurality of pressures of the working fluid at different positions in the gas turbine installation, | 03-04-2010 |
20100064656 | ENGINES AND METHODS OF OPERATING THE SAME - Engines and methods for operating the engines are provided. The engine includes a means for limiting overspeed in flow communication with a turbine section flowpath, wherein the means for limiting overspeed is adapted to block a first portion of an airflow received along a first direction vector from flowing into an exhaust section flowpath and to redirect a second portion of the airflow received along the first direction vector or a portion of the blocked first portion of the airflow to flow along another direction vector that is closer to parallel with a longitudinal axis than the first direction vector. | 03-18-2010 |
20100269481 | SYSTEMS AND METHODS FOR PROVIDING SURGE PROTECTION TO A TURBINE COMPONENT - Systems and methods for providing surge protection to turbine components are provided. A surge protection limit may be determined for the turbine component. One or more measurements associated with operation of the turbine component may be received and provided to a cycle model executed to predict an operating condition of the turbine component. The predicted operating condition of the turbine component may be adjusted based at least in part on the received one or more measurements. The surge protection limit may be adjusted based on the adjusted predicted operating condition of the turbine component. | 10-28-2010 |
20100287905 | TURBINE ENGINE THRUST SCHEDULING - This invention relates generally to gas turbine engine thrust scheduling, and more particularly to systems and methods for smoothing thrust inputs to gas turbine engines. In one embodiment, a method for operating a gas turbine engine comprises, upon disengagement of an auto-throttle system, determining a first trim setting corresponding to a TLA setting, determining a second trim setting where the second trim setting reduces to zero during successive manual throttle lever movements, determining a third trim setting comprising a combination of the first trim setting and the second trim setting, and applying the third trim setting to the TLA setting to smoothly transition from auto-throttle to manual operation of the engine while maintaining engine thrust. | 11-18-2010 |
20100300062 | Systems and Methods for Modifying the Performance of a Gas Turbine - Embodiments of the invention can provide systems and methods for modifying the operation and/or performance of a gas turbine. According to one embodiment, a method for modifying the performance of a gas turbine comprising one or more combustors can be provided. The method can include measuring a gas exhaust temperature for the gas turbine and estimating a heat transfer rate for the gas turbine based at least in part on the gas exhaust temperature. After estimating the heat transfer rate, the method can continue by estimating a transiently accurate combustion reference temperature and using this parameter to control the one or more combustors of the gas turbine. In doing so, the performance of the gas turbine can be modified to ensure reliable and consistent operation. | 12-02-2010 |
20110000182 | Uncoupled, thermal-compressor, gas-turbine engine - The invention is for a continuous-combustion, closed-cycle, gas turbine engine with a regenerator and a displacer. It has embodiments that remove heater and cooler interior volumes during gas compression, which enable it to scale well to very large sizes. Low combustion temperatures insure very low emissions. The displacer levitated by an integral gas bearing and small clearance seal and given oscillatory translational motion by electromagnetic forces operates without surface wear. The turbine blades, subjected only to warm gases, are durable and inexpensive. Thus, this engine has a very long, continuous, maintenance-free service life. This gas turbine engine also operates without back work allowing high efficiency for both low and rated output. Pressurized encapsulation permits use of low-cost ceramics for high temperature components. The invention includes a unique monolithic ceramic heater, a compact high-capacity regenerator and a constant-power gas turbine. | 01-06-2011 |
20110056180 | GAS TURBINE CONTROL DEVICE - Occurrence of combustion vibration is prevented in a gas turbine plant by enhancing the degree of freedom in setting an airflow rate or a fuel flow rate in correspondence with a target load thereby enhancing combustion stability. A gas turbine controller comprises a first function generator ( | 03-10-2011 |
20110138766 | SYSTEM AND METHOD OF IMPROVING EMISSION PERFORMANCE OF A GAS TURBINE - A method of improving emission performance of a gas turbine is provided. The method includes recirculating a portion of an exhaust gas stream to a compressor of the gas turbine via an exhaust gas recirculating system, to reduce concentration of oxygen in a high pressure feed oxidant stream into a combustor of the gas turbine. The method further includes adding diluent to at least one of a fuel stream directed to the combustor or a low pressure feed oxidant stream directed to the compressor, to reduce concentration of oxides of nitrogen (NOx) and increase concentration of carbon dioxide in a resultant exhaust gas stream. | 06-16-2011 |
20110167780 | VARIABLE GEOMETRY HYSTERESIS CONTROL FOR A GAS TURBINE ENGINE - One embodiment of the present application is a gas turbine engine with a compressor that includes a variable geometry mechanism to vary working fluid flow area. A desired state of this mechanism is selected different than a current state to change the amount of flow area. The mechanism has a hysteresis band corresponding to a difference between increasing the flow area to reach the desired state and decreasing the flow area to reach the desired state. To control operation of the mechanism within this hysteresis band, a determination is made whether the desired state corresponds to a greater flow area or a lesser flow area relative to the current state. | 07-14-2011 |
20110185698 | FREE GAS TURBINE WITH CONSTANT TEMPERATURE-CORRECTED GAS GENERATOR SPEED - A method of controlling a speed of a gas turbine engine including a gas generator spool and a power turbine spool rotating independently from one another, including controlling a rotational speed of the gas generator spool according to a fixed relationship with respect to an outside air temperature throughout a variation of output power. | 08-04-2011 |
20110232258 | METHOD AND SYSTEM FOR TESTING AN OVERSPEED PROTECTION SYSTEM OF A POWERPLANT - Embodiments of the present invention have the technical effect of automatically testing an overspeed protection system associated with multiple powerplant machines of a powerplant. An embodiment of the present invention may automatically test the overspeed protection system while at least one of the powerplant machines is in the process of shutting down. Another embodiment of the present invention may automatically test the overspeed protection system by adjusting the speed of a shaft while at least one of the powerplant machines operates at full-speed-no-load. | 09-29-2011 |
20110232259 | METHOD AND SYSTEM FOR TESTING AN OVERSPEED PROTECTION SYSTEM OF A POWERPLANT MACHINE - Embodiments of the present invention have the technical effect of automatically testing an overspeed protection system of a powerplant machine comprising a shaft and integrated with a safety control system. An embodiment of the present invention may automatically test the overspeed protection system while the powerplant machine is in the process of shutting down. Another embodiment of the present invention may automatically test the overspeed protection system of the powerplant machine by adjusting the speed of a shaft while operating at full-speed-no-load. | 09-29-2011 |
20120096829 | SYSTEM AND METHOD FOR CONTROLLING A SEMI-CLOSED POWER CYCLE SYSTEM - 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. | 04-26-2012 |
20130025254 | CONTROLLER FOR USE WITH GAS TURBINE ENGINE - Provided is a controller for use with a gas turbine engine, which ensures a stable combustion regardless of the deterioration of the catalyst and elevated characteristics of the exhaust gas. The controller | 01-31-2013 |
20130055697 | FLUID COMPOSITION ANALYSIS MECHANISM, CALORIFIC VALUE MEASUREMENT DEVICE AND POWER PLANT - A fluid composition analysis mechanism includes a light source for configured to irradiate excitation light to a sample fluid at a measurement position; a light receiving unit arranged on an extended line of the excitation light for configured to receive and disperse Raman scattering light generated from the sample fluid irradiated with the excitation light; a Raman scattering light collection optical system arranged on an optical path for the excitation light or on the extended line of the excitation light configured to collect the Raman scattering light generated at the measurement position and to cause the condensed Raman scattering light to be incident on the light receiving unit; a calculation unit configured to calculate a composition of the sample fluid based on an output of the light receiving unit; and a light shielding member arranged on the optical path or on the extended line of the excitation light. | 03-07-2013 |
20130074471 | TURBINE COMBUSTOR AND METHOD FOR TEMPERATURE CONTROL AND DAMPING A PORTION OF A COMBUSTOR - According to one aspect of the invention, a turbine combustor includes an outer member coupled to a wall of the combustor, wherein there is at least one damping hole formed in outer member. The turbine combustor further includes at least one temperature control hole formed in the wall wherein the at least one temperature control hole is formed at an angle with respect to a line perpendicular to a hot gas path in the combustor. | 03-28-2013 |
20130104516 | METHOD OF MONITORING AN OPERATION OF A COMPRESSOR BLEED VALVE | 05-02-2013 |
20130232941 | APPARATUS FOR EXTRACTING INPUT POWER FROM THE LOW PRESSURE SPOOL OF A TURBINE ENGINE - An apparatus for powering an aircraft by generating power from a pressure spool of a turbine engine includes a speed range reduction assembly that reduces the higher speed ranges of a low pressure spool to lower speed ranges within the tolerances of the same DC or VF generators used with the high pressure spool. | 09-12-2013 |
20130255220 | DISTRIBUTED GAS TURBINE ENGINE CONTROL SYSTEM - In one embodiment, a gas turbine engine control system includes an engine controller configured to control multiple parameters associated with operation of a gas turbine engine system. The gas turbine engine control system also includes multiple remote interface units communicatively coupled to the engine controller. The remote interface unit is configured to receive an input signal from the engine controller indicative of respective target values of at least one parameter, and the remote interface unit is configured to provide closed-loop control of the at least one parameter based on the input signal and feedback signals indicative of respective measured values of the at least one parameter. | 10-03-2013 |
20140260177 | GAS TURBINE LOAD ENHANCEMENT - An automated industrial system is provided that includes a sensor system configured to monitor multiple parameters. The automated industrial system also includes a controller. The controller is configured to determine if any of the multiple parameters has surpassed a respective constraint threshold of multiple constraint thresholds. If any of the parameters has surpassed a respective constraint threshold, the controller is configured to classify a parameter of the multiple parameters which has surpassed the respective constraint threshold by the highest degree as the most constrained parameter. The controller is also configured to calculate a minimum temperature load path based on the most constrained parameter, with the minimum temperature load path configured to transition the automated industrial system from a base load to a part load via a minimum temperature load path. | 09-18-2014 |
060390260 | Oxidizer, fuel and water or steam | 1 |
20090071118 | METHOD AND SYSTEM FOR MODULATING THE MODIFIED WOBBE INDEX OF A FUEL - A method and system for modulating the Modified Wobbe Index (MWI) of a fuel is provided. A variety of industrial components, which may require a gas fuel, such as but not limiting of, a heavy-duty gas turbine; an aero-derivative gas turbine; or a boiler may utilize the method and system. The method and system may provide an industrial component comprising at least one steam injection system, wherein the at least one steam injection system injects steam into at least one fuel supply line upstream of a combustion system to modulate the MWI of at least one fuel. The method and system may also determine whether the MWI of the at least one fuel is outside of a predetermined range; and utilize the at least one steam injection system to automatically inject the steam at a flowrate for adjusting the MWI of the at least one fuel. | 03-19-2009 |
060390270 | Oxidizer and fuel | 5 |
20090158702 | METHOD FOR CONTROLLING THE LOAD VARIATIONS IN A GAS TURBINE - A method is described for controlling load variations in a gas turbine. The method comprises reducing the flow of gaseous fuel entering the combustor to a predefined minimum value, if an increase is observed in the rotation regime of said turbine above a predefined maximum value and a total reduction in the load, activating a selective feeding sequence of the burners if the turbine is operating in normal functioning or premixed flame mode, modifying the angulation of the adjustable stator vanes, in order to reduce the speed rate of the compressor, and opening one or more anti-surge valves and one or more overboard bleeds, in order to reduce the air flow at the inlet of the combustor. | 06-25-2009 |
20100107591 | TURBOMACHINE FLAMEOUT CONFIRMATION - 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. | 05-06-2010 |
20100154380 | Control system for a land-based simple cycle hybrid engine for power generation - 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. | 06-24-2010 |
20110056181 | CONTROL SYSTEMS AND METHOD FOR CONTROLLING A LOAD POINT OF A GAS TURBINE ENGINE - 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. | 03-10-2011 |
20150354467 | GAS TURBINE SYSTEM, GAS TURBINE COMBUSTOR CONTROL DEVICE, AND GAS TURBINE COMBUSTOR CONTROL METHOD - A gas turbine is provided with a combustor having a pilot nozzle, a first main nozzle, and a second main nozzle. A combustor control device has a load interruption detector which detects load interruption of the gas turbine, a pilot nozzle flow rate control unit which increases the amount of premixed fuel supplied to the pilot nozzle, based on the detection of the load interruption, a first main nozzle flow rate control unit which reduces the amount of premixed fuel supplied to the first main nozzles, based on the detection of the load interruption, and a second main nozzle flow rate control unit which reduces the amount of premixed fuel supplied to the second main nozzles to a predetermined amount, based on the detection of the load interruption, and then further reduces the amount of premixed fuel supplied after the elapse of a predetermined time. | 12-10-2015 |
060390281 | Fuel | 47 |
20080229726 | Two-Displacement Setting Variable Displacement Pump Used as Engine Over-Thrust Protection With Fuel System Thermal Benefit - A fuel delivery system ( | 09-25-2008 |
20090019830 | APPARATUS AND A METHOD FOR REGULATING THE FLOW RATE OF FUEL TO A TURBOSHAFT ENGINE IN ACCELERATION OR IN DECELERATION - Apparatus for regulating the flow rate of fuel to a turboshaft engine in acceleration or in deceleration, the engine having a free turbine and a core engine, the apparatus comprising sensors transmitting information to regulator means, said information relating: to a first speed of rotation NTL of said free turbine; to a second speed of rotation Ng of said engine's gas generator; to an internal temperature T | 01-22-2009 |
20090044513 | Method Of Mitigating Undesired Gas Turbine Transient Response Using Event Based Actions - A method of managing transient events regularly seen during gas turbine operation that may cause undesirable operation and hardware damage. During certain transient operations, a lag may be seen between reference exhaust temperature and actual turbine exhaust temperature. This lag can result in an under-fired condition within the combustion system of variable magnitude and duration. Either fuel split schedules or a control algorithm can be positioned during these transients to prevent combustion dynamics or loss of flame. Combustion dynamics are known to cause damage that may require hardware replacement. Once the transient has completed, normal control operation is resumed. | 02-19-2009 |
20090077945 | VARIABLE AMPLITUDE DOUBLE BINARY VALVE SYSTEM FOR ACTIVE FUEL CONTROL - A method of controlling combustion stability in a turbine engine having combustion stability control capability includes the steps of providing at least one pair of pulsating valves, mutually arranged in parallel with respect to fuel flow provided to a combustor of the turbine engine, detecting an amplitude and frequency of a pressure wave of at least one periodic combustion instability, selecting an amplitude, frequency and first phase shift, with respect to the pressure wave, of resultant fuel pulsations to reduce the amplitude of the pressure wave, translating the selected amplitude into a second, relative phase shift between each pulsating valve of at least one pair of pulsating valves, and commanding each pulsating valve of at least one pair of pulsating valves to operate at the selected frequency and a relative second phase shift with respect to one another, to yield a resultant fuel pulsation at the selected amplitude, frequency and first phase shift, with respect to the detected pressure wave of combustion instability. | 03-26-2009 |
20090100822 | INTEGRATED GASIFICATION COMBINED CYCLE AND THE CONTROL METHOD - A gasification unit provided with a gasification furnace | 04-23-2009 |
20090133379 | Active combustion control for a turbine engine - A combustion control system for a turbine engine is disclosed. The combustion control system includes a fuel injector having a main fuel supply and pilot fuel supply coupled to a combustor of the turbine engine. The combustion control system also includes a sensor coupled to a transfer tube. The transfer tube is fluidly coupled to the combustor, and the sensor is configured to detect a pressure pulse in the combustor. A semi-infinite coil is also coupled to the transfer tube. The combustion control system also includes a controller electrically connected to the sensor. The controller is configured to compare an amplitude of the pressure pulse within a frequency range to a threshold amplitude, and adjust the pilot fuel supply in response to the comparison. | 05-28-2009 |
20090145105 | REMOTE ENGINE FUEL CONTROL AND ELECTRONIC ENGINE CONTROL FOR TURBINE ENGINE - A controller is mounted remotely from a turbine engine and provided with an independent power source ( | 06-11-2009 |
20090173057 | GAS TURBINE POWER GENERATING MACHINE - The plant includes a gaseous fuel processing apparatus for pre-processing natural gas (gaseous fuel) produced in the gas field, a liquid fuel processing apparatus for pre-processing liquid fuel obtained during the extraction and refining process of the natural gas, and a gas turbine. The gas turbine includes a compressor for generating compressed air, a combustor for mixing the compressed air from the compressor with one or both of the gaseous fuel pre-processed by the gaseous fuel processing apparatus and the liquid fuel pre-processed by the liquid fuel processing apparatus, and for burning a gas mixture, and a turbine for driving a generator by combustion gases supplied from the combustor. | 07-09-2009 |
20090183492 | COMBUSTION LEAN-BLOWOUT PROTECTION VIA NOZZLE EQUIVALENCE RATIO CONTROL - Disclosed is a method and system for controlling a combustor of a gas turbine utilizing fuel nozzle equivalence ratio. The equivalence ratio of at least one fuel nozzle of the combustor, the combustor having at least one fuel nozzle disposed in at least one combustor can, is measured. The measured equivalence ratio is compared to a threshold value for lean blowout. The fuel flow from the at least one nozzle is modified thereby adjusting the equivalence ratio to prevent lean blowout. | 07-23-2009 |
20090193788 | METHODS AND APPARATUS FOR OPERATING GAS TURBINE ENGINE SYSTEMS - Methods and systems for operating a gas turbine engine system are provided. The system includes a fuel control system. The fuel control system includes a plurality of sensors positioned about the gas turbine engine system and configured to measure at least one parameter associated with the sensor, and a processor programmed to receive a signal from at least one of the plurality of sensors indicative of a composition of the fuel. The processor is further programmed to determine the physical properties of a fuel at an inlet to the flow control devices using a flow model and the at least one signal, determine a corresponding correction to a gas fuel flow gain using the determined physical properties, and automatically control fuel delivery as well as fuel split between the fuel injection points on the combustor using the adjusted flow gain to facilitate permitting a relatively large variation in the fuel composition for use in the gas turbine engine. | 08-06-2009 |
20090241510 | Pressure control method and system to reduce gas turbine fuel supply pressure requirements - A system and method to reduce the gas fuel supply pressure requirements of a gas turbine, which results in an increased operability range and a reduction in gas turbine trips. According to the method, the gas turbine is allowed to start and operate at supply pressures determined as a function of ambient conditions and gas turbine compressor pressure ratio. This increases the operability window, and reduces or eliminates the need for gas fuel compressors. | 10-01-2009 |
20100005776 | FUEL SUPPLY SYSTEM FOR A GAS-TURBINE ENGINE - On a fuel supply system for a gas-turbine engine with a high-pressure supply line and a fuel metering unit, the fuel distribution system connected to staged or non-staged burners includes only one single fuel line ( | 01-14-2010 |
20100018182 | REGULATING THE FLOW RATE OF FUEL TAKEN FROM A FUEL CIRCUIT OF AN AIRCRAFT PROPELLED BY AN ENGINE - The invention relates to a device for regulating the flow rate of fuel taken from a fuel circuit of an aircraft propelled by an engine. The device comprises: a positive displacement pump receiving fuel from a fuel circuit of the aircraft and delivering fuel at a flow rate that is proportional to its speed of rotation; a differential gear having a predefined transmission ratio, a first inlet mechanically coupled to the aircraft engine, a second inlet mechanically coupled to an electric motor/generator, and an outlet mechanically coupled to the positive displacement pump to drive it in rotation; and an electronic control system for regulating the speed of rotation of the electric motor/generator as a function of a setpoint value for the flow rate of fuel to be injected. | 01-28-2010 |
20100018183 | APPARATUS AND SYSTEM FOR GAS TURBINE ENGINE CONTROL - Methods and systems for controlling a dynamic response in a gas turbine fuel control system are provided. The control system includes a component model adapted to regulate a fuel supply pressure for a gas turbine, a pressure sensor adapted to sense a pressure of fuel supplied to the gas turbine, and a feedback module including integral plus state feedback, the feedback module adapted to provide a positive feedback reference signal to the component model such that a response time of the gas turbine fuel control system to changes in fuel pressure is facilitated being reduced. | 01-28-2010 |
20100037586 | Method and system for feeding a gas-turbine engine with liquid fuel - 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. | 02-18-2010 |
20100043387 | METHODS AND SYSTEMS FOR OPERATING GAS TURBINE ENGINES - 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. | 02-25-2010 |
20100064657 | Actuator flow compensated direct metering fuel control system and method - 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. | 03-18-2010 |
20100064658 | MODULAR FUEL SUPPLY DEVICE FOR A GAS TURBINE - 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. | 03-18-2010 |
20100089025 | Fuel Delivery and Control System Including a Positive Displacement Actuation Pump With a Variable Pressure Regulator Supplementing a Fixed Displacement Main Fuel Pump - 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. | 04-15-2010 |
20100089026 | Fuel Delivery and Control System Including a Variable Displacement Actuation Pump Supplementing a Fixed Displacement Main Pump - 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. | 04-15-2010 |
20100126136 | ELECTRIC POWER GENERATING TURBINE ENGINE FUEL SUPPLY SYSTEM - 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. | 05-27-2010 |
20100162678 | SYSTEM AND METHOD FOR AUTOMATIC FUEL BLENDING AND CONTROL FOR COMBUSTION GAS TURBINE - 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. | 07-01-2010 |
20100170219 | LATE LEAN INJECTION CONTROL STRATEGY - 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. | 07-08-2010 |
20100242431 | Variable Actuation Pressure System for Independent Pressure Control - 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. | 09-30-2010 |
20100293919 | DUAL-PUMP FUEL SYSTEM AND METHOD FOR STARTING A GAS TURBINE ENGINE - 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. | 11-25-2010 |
20110005189 | Active Control of Flame Holding and Flashback in Turbine Combustor Fuel Nozzle - 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. | 01-13-2011 |
20110131947 | TRIM VALVES FOR MODULATING FLUID FLOW - A trim valve includes a valve housing having an inlet section and an outlet section. A valve shaft is mounted to the valve housing to be stationary with respect thereto. The valve shaft includes an internal flow passage in fluid communication with the outlet section of the valve housing. A valve rotor is disposed inboard of the valve housing and outboard of the valve shaft for modulating flow through the valve housing. The valve rotor is mounted for rotational movement within the valve housing between a fully open position in which a flow path is defined between the inlet and outlet sections of the valve housing, and a reduced flow position in which the valve rotor at least partially blocks the flow path. An actuator is operatively connected to the valve housing to actuate the valve rotor between the fully open and reduced flow positions. | 06-09-2011 |
20110154802 | PARALLEL TURBINE FUEL CONTROL VALVES - A fuel system for a turbine, including a plurality of fuel control valves connected to the turbine and in parallel with each other; and a controller for opening each of the control valves to pass a lower controllable fuel flow through each valve, and for further opening one of the control valves in response to a control signal for controlling the turbine. | 06-30-2011 |
20110162343 | SYSTEMS AND METHODS FOR CONTROLLING FUEL FLOW WITHIN A MACHINE - 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. | 07-07-2011 |
20110167782 | SYSTEMS AND APPARATUS FOR A FUEL CONTROL ASSEMBLY FOR USE IN A GAS TURBINE ENGINE - A fuel control assembly for use in a gas turbine engine. The fuel control assembly includes a first trip device configured to selectively release a fluid pressure from a trip fluid system. At least one gas fuel control valve is coupled to the first trip device. The gas fuel control valve includes a second trip device for moving the gas fuel control valve to a safe position during a purge air operation. | 07-14-2011 |
20110239621 | Fiber optic microphones for active combustion control - Disclosed is a fuel injector for a gas turbine engine combustor that includes a fuel nozzle for injecting fuel into the gas turbine engine combustor and a fiber optic microphone operatively associated with the fuel nozzle for measuring acoustic pressure differentials within a combustion chamber of the gas turbine engine combustor. The fiber optic microphone includes a fiber bundle having at least one light transmitting fiber and one light receiving fiber; and a dynamic pressure-sensing diaphragm operatively spaced apart from a sensing end of the fiber bundle. The diaphragm has a reflective surface and is formed from a material capable of withstanding temperatures associated with flame exposure. The diaphragm is adapted and configured for deflecting in response to acoustic pressure changes within the combustion chamber. The fuel injector can further include a mechanism for measuring the temperature of the diaphragm, so as to account for changes in the material properties of the diaphragm caused by temperature changes in the combustion chamber. | 10-06-2011 |
20110247314 | COMBUSTOR EXIT TEMPERATURE PROFILE CONTROL VIA FUEL STAGING AND RELATED METHOD - A gas turbine combustor includes a combustion chamber defined by a combustor liner, the combustor liner having an upstream end cover supporting one or more nozzles arranged to supply fuel to the combustion chamber where the fuel mixes with air supplied from a compressor. A transition duct is connected between an aft end of the combustion chamber liner and a first stage turbine casing, the transition duct supplying gaseous products of combustion to the first stage turbine nozzle. One or more additional fuel injection nozzles are arranged at an aft end of the transition duct for introducing additional fuel into the transition duct upstream of the first stage turbine nozzle. | 10-13-2011 |
20110247315 | FLEXIBLE FUEL SYSTEM - An example fuel system includes a fuel sensor configured to sense at least one characteristic of a fuel provided to an engine. The fuel is selected from a plurality of different fuel types. The fuel system also includes a controller that is configured to meter the fuel in response to the at least one characteristic of the fuel. | 10-13-2011 |
20120067022 | GAS TURBINE ENGINE FUEL CONTROL THRUST CONTROL OVERRIDE SYSTEM - A gas turbine engine fuel control system is provided that includes a fuel metering valve and a thrust control valve. The fuel metering valve includes a metering valve inlet and a metering valve outlet. The metering valve inlet is adapted to receive a flow of fuel, and is configured to control the flow of fuel through the metering valve outlet. The thrust control valve is adapted to receive thrust control valve override signals and is configured, in response thereto, to move from a first position, in which flow from the metering valve is not impacted, and a second position, in which flow from the metering valve is blocked while flow through a fixed-area orifice is allowed. | 03-22-2012 |
20120090291 | INTERNAL COMBUSTION ENGINE - An internal combustion engine in which the power output is controlled by modulating at least one of the compression ratio, expansion ratio, ratio of expansion rate to compression rate, air to fuel ratio, and steam to air ratio. Continuous isobaric catalytic combustion followed by isothermal expansion and the use of separate compressor and expander devices are used. Control dynamically maximizes fuel efficiency for the given power demand conditions. Power output is controlled by modulating flame temperature and/or pressure instead of by throttling. Lean combustion, high compression ratio, exhaust heat recuperation, and high power density and fuel economy are provided. External cooling is minimized or eliminated. Insulation of the engine effectively reduces energy losses to friction. Interchangeable use of gasoline, hydrogen and ammonia at high fuel efficiency is made possible for transitional periods of fuel availabilities. An injector suitable for isothermal expansion is provided. | 04-19-2012 |
20120102914 | SYSTEMS, METHODS, AND APPARATUS FOR COMPENSATING FUEL COMPOSITION VARIATIONS IN A GAS TURBINE - Certain embodiments of the invention may include systems and methods for compensating fuel composition variations in a gas turbine. According to an example embodiment of the invention, a method is provided for compensating for fuel composition variations in a turbine. The method can include: monitoring at least one fuel parameter associated with a turbine combustor; monitoring one or more combustion dynamics characteristics associated with the turbine combustor; monitoring one or more performance and emissions characteristics associated with the turbine; estimating fuel composition based at least in part on the at least one fuel parameter, the one or more combustion dynamics characteristics, and the one or more performance and emissions characteristics, and adjusting at least one fuel parameter based at least in part on the estimated fuel composition. | 05-03-2012 |
20120186221 | INTERNAL COMBUSTION ENGINE - An internal combustion engine in which the power output is controlled by modulating at least one of the compression ratio, expansion ratio, ratio of expansion rate to compression rate, air to fuel ratio, and steam to air ratio. Continuous isobaric catalytic combustion followed by isothermal expansion and the use of separate compressor and expander devices are used. Control dynamically maximizes fuel efficiency for the given power demand conditions. Power output is controlled by modulating flame temperature and/or pressure instead of by throttling. Lean combustion, high compression ratio, exhaust heat recuperation, and high power density and fuel economy are provided. External cooling is minimized or eliminated. Insulation of the engine effectively reduces energy losses to friction. Interchangeable use of gasoline, hydrogen and ammonia at high fuel efficiency is made possible for transitional periods of fuel availabilities. An injector suitable for isothermal expansion is provided. | 07-26-2012 |
20130283763 | PRESSURE REGULATING VALVE - 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. | 10-31-2013 |
20140047815 | LOAD REJECTION FOR GAS TURBINE - 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. | 02-20-2014 |
20140123624 | GAS TURBINE COMBUSTOR CONTROL SYSTEM - 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. | 05-08-2014 |
20150315981 | FUEL SUPPLY SYSTEM - A fuel supply system includes a fuel line path configured to route a fuel to a combustion inlet region. Also included is a flow manipulation member disposed proximate the fuel line path, the flow manipulation member comprising a piezoelectric material configured to cyclically manipulate a mass flow pressure of the fuel being routed through the fuel line path. | 11-05-2015 |
20160091381 | METHOD FOR DETERMINING A FAULT WITHIN A FLOW DIVIDER - The present disclosure relates generally to a method for determining a failure of a flow divider within a fuel system, the method being performed by a controller and comprising the steps of: delivering a fuel command, calculating an expected fill time, wherein the expected fill time is indicative of the time required to fill a known fuel manifold volume, determining whether the actual fill time is greater than or equal to an expected fill time; and determining whether an actual fuel pressure value is less than or equal to an expect fuel pressure value based at least in part on at least one environmental signal. | 03-31-2016 |
20160138482 | APPLICATION OF PROBABILISTIC CONTROL IN GAS TURBINE TUNING WITH MEASUREMENT ERROR, RELATED CONTROL SYSTEMS, COMPUTER PROGRAM PRODUCTS AND METHODS - Various embodiments include a system having: at least one computing device configured to tune a set of gas turbines (GTs) by performing actions including: commanding each GT in the set of GTs to a base load level, based upon a measured ambient condition for each GT; commanding each GT in the set of GTs to adjust a respective output to match a nominal mega-watt power output value, and subsequently measuring an actual emissions value for each GT; adjusting an operating condition of each GT in the set of GTs based upon a difference between the respective measured actual emissions value and a nominal emissions value at the ambient condition; and further adjusting an operating condition of each GT in the set of GTs based upon a determined emissions measurement error. | 05-19-2016 |
20160138483 | APPLICATION OF FUEL FLOW-BASED PROBABILISTIC CONTROL IN GAS TURBINE TUNING UNDER PART LOAD, RELATED CONTROL SYSTEMS, COMPUTER PROGRAM PRODUCTS AND METHODS - Various embodiments include a system having: at least one computing device configured to tune a set of gas turbines (GTs) by performing actions including: commanding each GT in the set of GTs to a base load level, based upon a measured ambient condition for each GT; commanding each GT in the set of GTs to adjust a respective output to match a nominal mega-watt power output value, and subsequently measuring an actual fuel flow value for each GT; adjusting an operating condition of each GT in the set of GTs based upon a difference between the respective measured actual fuel flow value and a nominal fuel flow value at the ambient condition; commanding each GT in the set of GTs to a part load level, the part load level representing a fraction of the base load level, and subsequently measuring an actual fuel flow value for each GT at the part load level; and calibrating the set of GTs based upon a difference between the measured actual fuel flow value at the part load level and the measured actual fuel flow value after adjusting the output to match the nominal mega-watt power output value. | 05-19-2016 |
20160201576 | FLEXURE FOR METERING VALVE ASSEMBLY | 07-14-2016 |
060390282 | Torque sensor | 2 |
20110162344 | FUEL METERING SYSTEM ELECTRICALLY SERVOED METERING PUMP - 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. | 07-07-2011 |
20140053530 | FUEL METERING SYSTEM ELECTRICALLY SERVOED METERING PUMP - 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. | 02-27-2014 |
060794000 | Oxidizer | 8 |
20090249794 | Systems and Methods for Augmenting Power Output of a Turbine During a Transient Event - Systems and methods for augmenting power output of a turbine during a transient event are provided. A cooling substance may be provided and at least a portion of the cooling substance may be directed to a compressor inlet of the turbine for a predefined time in order to augment power output of the turbine. | 10-08-2009 |
20100162724 | Methods and Systems for Controlling a Combustor in Turbine Engines - Embodiments of 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. | 07-01-2010 |
20100223933 | System for controlling combustion dynamics and method for operating the same - A method for controlling combustion dynamics is provided. The method includes providing a flow of partially premixed, premixed, or lean premixed fuel-air into a combustion chamber. The method also includes monitoring the combustion system for combustion dynamics. The method further includes actuating a system to control and abate combustion dynamics. | 09-09-2010 |
20100307164 | SYSTEM FOR CONDITIONING THE AIRFLOW ENTERING A TURBOMACHINE - An embodiment of the present invention provides an air conditioning system (ACS) for conditioning the airstream entering an air-breathing machine, such as, but not limiting of, a gas turbine. Conditioning may be considered a process that adjusts at least one physical property of the airstream. The physical property may comprise: a wet-bulb temperature, a dry-bulb temperature, relative humidity, density, or the like. In an embodiment of the present invention, the major components of the ACS may be located in a single structure, which may be considered a module. Depending on the application of the ACS, multiple modules may be physically and/or operationally integrated on the air-breathing machine. | 12-09-2010 |
20160090915 | INLET DOOR CONTROL FOR STARTUP OF GAS TURBINE ENGINE - A gas turbine engine inlet door control system includes an actuator, an engine controller and a door controller. The actuator opens and closes an inlet door of a gas turbine engine. The engine controller determines an intermediate door position based upon one or more engine start factors. The door controller operates the actuator to open the inlet door to the intermediate door position based on the one or more engine start factors. | 03-31-2016 |
060795000 | Bleed | 3 |
20100083667 | BI-MODAL BLEED VALVE ASSEMBLY FOR GAS TURBINE ENGINE - A bi-modal bleed valve assembly is provided. In one embodiment, the bi-modal bleed valve assembly includes a housing assembly having a bleed inlet, a bleed outlet, a control servo port, and a control chamber therein. A main flow control valve is fluidly coupled to the control chamber and configured to move between an open position and a closed position to regulate fluid flow from the bleed inlet to the bleed outlet. The main flow control valve is configured to move from an open position to a closed position when the pressure within the control chamber surpasses a predetermined threshold. A switching valve is fluidly coupled between the bleed inlet, the servo control port, and the control chamber. The switching valve is configured to route fluid flow into the control chamber from: (i) the bleed inlet in an autonomous mode, and (ii) the servo control port in a servo-controlled mode. | 04-08-2010 |
20110167834 | FLOW DISCHARGE DEVICE - The present invention relates to a flow discharge device ( | 07-14-2011 |
20130167551 | TURBINE TO OPERATE AT PART-LOAD - A turbine includes a compressor to intake a fluid and to compress the fluid, a combustion chamber to heat the fluid from the compressor, a turbine section to rotate a shaft with the heated fluid from the combustion chamber, and a bypass circuit to generate a bypass flow by removing a portion of the fluid from the compressor, to heat the bypass flow, and to insert the bypass flow to the turbine section. | 07-04-2013 |
060390300 | Water or steam | 3 |
20090064653 | PARTIAL LOAD COMBUSTION CYCLES - The part load method controls delivery of diluent fluid, fuel fluid, and oxidant fluid in thermodynamic cycles using diluent, to increase the Turbine Inlet Temperature (TIT) and thermal efficiency in part load operation above that obtained by relevant art part load operation of Brayton cycles, fogged Brayton cycles, or cycles operating with some steam delivery, or with maximum steam delivery. The part load method may control the TIT at the design level by controlling one or both of liquid and/or gaseous fluid water over a range from full load to less than 45% load. This extends operation to lower operating loads while providing higher efficiencies and lower operating costs using water, steam and/or CO2 as diluents, than in simple cycle operation. | 03-12-2009 |
20090120054 | Method for operating a burner, especially a burner of a gas turbine, as well as apparatus for executing the method - There is described a method for operation of a burner, whereby a fuel is supplied to the burner, sprayed into the combustion air, mixed with the combustion air to give a fuel/air mixture and burnt in a combustion chamber. With regard to a combustion particularly low in pollutants and, in order to reduce the nitrogen oxide emissions with relation to achieving a given nitrogen oxide emission level, a change in parameters characterizing the fuel is determined. Such a parameter may, for example, be the Wobbe index. There is further described a device for carrying out said method, comprising a fuel treatment device, with an analytical device for the analysis of the current fuel composition and a monitoring and control system. | 05-14-2009 |
20110000180 | STEAM SYSTEM - An air compressor is driven by a steam engine that generates power using steam. The steam is supplied to the steam engine through a steam supply path, and the steam is exhausted through a steam exhaust path. The steam from the steam engine is supplied to a steam using device through a steam header. The usage load of the steam is monitored by a pressure sensor arranged in the steam header. The compressed air from the air compressor is supplied to a compressed air using device through a compressed air path. The usage load of the compressed air is monitored by a pressure sensor arranged on the compressed air path. The steam supply to the steam engine is controlled based on the usage load of the steam and the usage load of the compressed air. | 01-06-2011 |