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Having power output control

Subclass of:

060 - Power plants

060390010 - COMBUSTION PRODUCTS USED AS MOTIVE FLUID

060772000 - Process

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DocumentTitleDate
20130074512INLET FLUID FLOW AND IMPINGEMENT ANGLE CONTROL - A compressor of a gas turbine system comprises a fluid flow control device and an impingement angle control device downstream of the fluid flow control device. The fluid flow control device controls a fluid flow rate of fluid entering an inlet of the compressor, and the impingement angle control device controls an impingement angle of the fluid flowing to rotor blades in the compressor. The fluid flow control device and the impingement angle control device are independently operable.03-28-2013
20120174592METHOD FOR OPERATING A GAS TURBINE - A method for operating a gas turbine includes supplying fuel via at least one control valve regulated using an open-loop control system based on a predetermined load setpoint value. A valve stroke control command (s07-12-2012
20130074513METHOD OF ESTIMATING THE MAXIMUM POWER GENERATION CAPACITY AND FOR CONTROLLING A SPECIFIED POWER RESERVE OF A SINGLE CYCLE OR COMBINED CYCLE GAS TURBINE POWER PLANT, AND A POWER GENERATING SYSTEM FOR USE WITH SAID METHOD - An estimation unit can estimate, on a real-time basis, a maximum power generation capacity of a single cycle or combined cycle gas turbine power plant. For example, the actual power output and the maximum power generation capacity can be calculated relying on a mathematical process model. Subsequently, the calculated actual power output can be compared with the measured power output yielding a model-estimation error. Based on the model-estimation error, a correction signal can be deduced, to correct the calculated maximum power generation capacity. A controller can maintain a specified power reserve. The controller can use an estimate of the maximum power generation capacity as a reference, subtract a load offset, and apply the resulting signal as upper limit of the load set-point.03-28-2013
20100031667METHOD FOR OPERATING A POWER PLANT - A method is provided for operating a power station (02-11-2010
20090044542APPARATUS AND METHOD FOR MONITORING COMPRESSOR CLEARANCE AND CONTROLLING A GAS TURBINE - A gas turbine including a compressor, the gas turbine including a sensor for measuring a clearance of blades in the compressor; and a controller for receiving clearance information and using the information to control the gas turbine for prevention of at least one of a surge and rubbing of the blades.02-19-2009
20100005808TWIN-SHAFT GAS TURBINE - A twin-shaft gas turbine 01-14-2010
20130086917APPARATUS FOR HEAD END DIRECT AIR INJECTION WITH ENHANCED MIXING CAPABILITIES - 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.04-11-2013
20100269515GAS TURBINE CONTROL METHOD AND GAS TURBINE POWER GENERATING APPARATUS - An object is to reduce a fluctuation in the gas-turbine output in a nozzle switching period. In the nozzle switching period during which a first nozzle group that has been used is switched to a second nozzle group that is going to be used, the amounts of fuel supplied through the first nozzle group and the second nozzle group are adjusted by using at least one adjustment parameter registered in advance, the adjustment parameter registered in advance is updated according to the operating condition of the gas turbine, and the updated adjustment parameter is registered as an adjustment parameter to be used next.10-28-2010
20130067927SYSTEM AND METHOD FOR CONTROLLING COMBUSTION INSTABILITIES IN GAS TURBINE SYSTEMS - A gas turbine system and a method for controlling combustion instability in a combustion section of a gas turbine system are disclosed. The gas turbine system includes a compressor section, a turbine section connected to the compressor section, and a combustor section connected to the compressor section and the turbine section. The combustor section includes a plurality of combustors. The combustor section further includes at least one igniter for igniting a fuel-air mixture within each of the plurality of combustors into a hot gas. The gas turbine system further includes a control system for controlling a velocity of the hot gas in at least one of the plurality of combustors by controlling an operating parameter of the fuel-air mixture.03-21-2013
20130061596FUEL GAS PRESSURE CONTROL SYSTEM AND METHOD FOR REDUCING GAS TURBINE FUEL SUPPLY PRESSURE REQUIREMENTS - A method is provided for modifying a fuel control system for a gas turbine having a standard unloading sequence and a pre-defined minimum inlet pressure requirement associated with the standard unloading sequence to allow the gas turbine to operate over an increased range of fuel supply pressure. The method includes modifying the fuel control system by inputting a modified unloading sequence onto a computing system operatively associated with the fuel control system, the modified unloading sequence comprising a series of operating modes, mode transfers, or a combination thereof that is different than the standard unloading sequence; and modifying the fuel control system by inputting a new defined minimum inlet pressure requirement for the modified unloading sequence onto the computing system, the new defined minimum inlet pressure requirement being less than the pre-defined minimum inlet pressure requirement thereby reducing a fuel supply pressure trip point for the gas turbine.03-14-2013
20100089067ADAPTIVE PERFORMANCE MODEL AND METHODS FOR SYSTEM MAINTENANCE - A system includes a correction factor module that receives modeled data generated from a simulation model and measured data, that determines a difference between the modeled data and the measured data, and that applies a filter to the difference to determine a correction value; and a performance monitoring module that analyzes the correction value, and that generates a component alert based on the analysis.04-15-2010
20120234014FLOW CONTROL SYSTEM AND METHOD FOR CONTROLLING TWO POSITIVE DISPLACEMENT PUMPS - A fuel flow system for a gas turbine engine includes a first pump, a second pump, a bypass loop, an integrating bypass valve and a pilot valve. The first pump connects to an actuator and a metering valve. The second pump connects to the metering valve and is arranged in parallel with the first pump. The bypass loop recycles fuel flow from the first pump and the second pump to inlets of the first pump and second pump integrating bypass valve includes first and second windows. The first window regulates fuel from the first pump through the bypass loop and the second window that regulates fuel from the second pump through the bypass loop. The pilot valve controls the size of the first and second windows.09-20-2012
20120090330METHOD OF OPERATING AN ELECTRONIC ENGINE CONTROL (EEC) TO COMPENSATE FOR SPEED CHANGES - A method of operating an electronic engine control to compensate for speed changes. The method includes receiving a fuel flow request, sensing actual engine rotor speed, calculating a fuel flow correction factor, establishing a final fuel flow request based on the fuel flow correction factor, and adjusting the actual set point of the MV to compensate for the actual engine rotor speed.04-19-2012
20100199679GAS TURBINE ENGINE VALVE - A gas turbine engine valve is disclosed. In one form the valve includes two inlets in fluid communication with an outlet. The valve can include a spool having two lands capable of selectively closing either of the two inlets. The valve can include energy storage devices that initially position the spool within a valve housing. A temperature motor is provided to position the spool based upon a temperature of a mixture of working fluid from the two inlets. A working fluid flowing into the first inlet can be in fluid communication with a second end of the valve; and a working fluid flowing into the second inlet can be in fluid communication with a first end of the valve. A relatively high pressure condition at one or the other of the inlets can be used to alter a position of the valve.08-12-2010
20120285174Systems and Methods for Optimized Gas Turbine Shutdown - The present application and the resultant patent provide a gas turbine engine. The gas turbine engine may include a compressor for compressing a flow of air, a combustor for combusting the flow of air and a flow of fuel to create a flow of combustion gases, a turbine driven by the flow of combustion gases, a rotor driven by the turbine and driving the compressor, a rotor speed sensor, and a gas turbine shut down controller. The gas turbine shut down controller varies the flow of fuel to the combustor based upon a rotational speed of the rotor as determined by a dynamic target trajectory schedule.11-15-2012
20110126547TWIN-SHAFT GAS TURBINE - A twin-shaft gas turbine 06-02-2011
20110197593GAS TURBINE AND METHOD FOR ITS OPERATION - A gas turbine and method are disclosed by which the gas turbine can be safely operated at nominal speed with reduced margin to a surge limit of a compressor. The gas turbine, via a directly driven generator which generates alternating current with an operating frequency and which is connected in a frequency-coupled manner to an electricity grid, can deliver electric power to this grid. In the case of an underfrequency event the compressor of the gas turbine is unloaded by controlled, fast closing of the variable compressor guide vanes (VGV) and as a result maintains a sufficient margin to the surge limit of the compressor.08-18-2011
20090301096Gas Turbine Engine and Method for Reducing Turbine Engine Combustor Gaseous Emission - The invention relates to turbine engines used in aeronautics, but also for industrial and marine turbine engines. To reduce turbine engine combustor gaseous emissions at given combustor sizes or to reduce combustor sizes at given combustor gaseous emissions, the invention proposes the injection of hydrogen into the combustor in response to a power output level. According to a preferred embodiment, gaseous hydrogen is always injected at low-power operations and switched off at mid-power and high-power operations.12-10-2009
20120023963POWER PLANT AND METHOD OF OPERATION - At least one main air compressor makes a compressed ambient gas flow. The compressed ambient gas flow is delivered to both master and slave turbine combustors at a pressure that is greater than or substantially equal to an output pressure delivered to each turbine combustor from each turbine compressor as at least a first portion of a recirculated gas flow. A fuel stream is delivered to each turbine combustor, and combustible mixtures are formed and burned, forming the recirculated gas flows. A master and slave turbine power are produced, and each is substantially equal to at least a power required to rotate each turbine compressor. At least a portion of the recirculated gas flow is recirculated through recirculation loops. At least a second portion of the recirculated gas flow bypasses the combustors or an excess portion of each recirculated gas flow is vented or both.02-02-2012
20120023962POWER PLANT AND METHOD OF OPERATION - At least one main air compressor makes a compressed ambient gas flow. The compressed ambient gas flow is delivered to a turbine combustor at a pressure that is greater than or substantially equal to an output pressure delivered to the turbine combustor from a turbine compressor as at least a first portion of a recirculated gas flow. A fuel stream is delivered to the turbine combustor, and a combustible mixture is formed and burned, forming the recirculated gas flow. A turbine power is produced that is substantially equal to at least a power required to rotate the turbine compressor. At least a portion of the recirculated gas flow is recirculated through a recirculation loop. An excess portion of the recirculated gas flow is vented or a portion of the recirculated gas flow bypasses the turbine combustor or both.02-02-2012
20110167831ADAPTIVE CORE ENGINE - A gas turbine engine having an adaptive core capable of maintaining a substantially constant core pressure ratio while having a variable flow rate is disclosed. In one aspect, the adaptive core comprises a front block compressor and a rear block compressor.07-14-2011
20090277183PRIMARY FREQUENCY REGULATION METHOD THROUGH JOINT CONTROL IN COMBINED CYCLE TURBINES - A method for providing Asymmetric Joint Control for Primary Frequency Regulation (PFR) in combined cycle power generation plants, said plant comprising at least one gas turbine and at least one steam turbine is provided. The method may comprise the use of the spinning energy existing in the high pressure steam to rapidly supply additional power to the steam turbine for PFR service when required by the grid, within the time frame established as a requirement to participate in the PFR service,. In some embodiments, PFR control can be carried out jointly in the whole combined cycle plant and the distribution of spinning reserve energy can be asymmetric.11-12-2009
20110203290CONTROL METHOD AND CONTROL DEVICE FOR EXHAUST HEAT RECOVERY SYSTEM FOR MARINE VESSEL - Disclosed are a control method and a control device for an exhaust heat recovery system which are capable of preventing an onboard supply power outage in response to a sharp change in the load of the main drive machine. For an exhaust heat recovery system for which a portion of the exhaust gas generated by the ship's main drive machine is supplied to a gas turbine and the amount of heat of the exhaust gas exhausted by the gas turbine is conducted to an exhaust gas economizer, this control method and control device: obtain an estimated or calculated current reserve amount of heat (Q), which is based on the heat energy detection signal of the exhaust gas economizer; obtain, based on the operation state of an auxiliary electrical generator and on the onboard power demand, a reference amount of heat (Q08-25-2011
20100275610POWER GENERATION PLANT AND CONTROL METHOD THEREOF - A power generation plant comprises a plant control device (11-04-2010
20100275609HYBRID WOBBE CONTROL DURING RAPID RESPONSE STARTUP - According to one aspect, the subject application involves a method of controlling a transition of a gas turbine. The method includes receiving a request of the gas turbine to drive an increased load. The increased load is greater than a load being driven by the gas turbine when the request is received. The method further includes determining that a temperature of a fuel to be ignited within a combustor of the gas turbine is less than a target temperature of the fuel to be introduced into the combustor for driving the increased load. Responsive to this determination, the method also includes controlling introduction of an additive into the combustor of the gas turbine when the temperature of the fuel is less than the target temperature to establish a suitable Wobbe Index of a fuel combination to promote a substantially continuous transition of the gas turbine to drive the increased load, wherein the fuel combination includes the fuel and the additive.11-04-2010
20110265487Dynamically Auto-Tuning a Gas Turbine Engine - Tuning processes implemented by an auto-tune controller are provided for measuring and adjusting the combustion dynamics and the emission composition of a gas turbine (GT) engine via a tuning process. Initially, the tuning process includes monitoring parameters, such as combustion dynamics and emission composition. Upon determining that one or more of the monitored parameters exceed a critical value, these “out-of-tune” parameters are compared to a scanning order table. Upon comparison, the first out-of-tune parameter that is matched within the scanning order table is addressed. The first out-of-tune parameter is then plotted as overlaid slopes on respective graphs, where the graph represents a fuel-flow split. Typically, the slopes are plotted as a particular out-of-tune parameter against a particular fuel-flow split. The slopes for each graph are considered together by taking into account the combined impact on each out-of-tune parameter when a fuel-flow split is selected for adjustment.11-03-2011
20080276620METHOD OF OPERATING A GAS TURBINE ENGINE - A method of operating a gas turbine engine having a rotatable turbine shaft with an electric machine mounted to the shaft. The method includes providing supplemental acceleration and/or deceleration of the turbine shaft of the gas turbine engine through the use of the electric machine operated as an electric motor and/or an electric generator, in order to avoid an undesirable engine speed range during engine operation.11-13-2008
20100139286BURNER AND FUEL SUPPLY FOR A GAS TURBINE - 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.06-10-2010
20110219779LOW EMISSION COMBUSTION SYSTEMS AND METHODS FOR GAS TURBINE ENGINES - A combustion system for a gas turbine engine is provided. The system includes a forward liner; an aft liner; a combustion chamber formed by the forward liner and the aft liner, the combustion chamber defining a lean combustion zone and a pilot combustion zone; a premixing zone coupled to the combustion chamber; a pilot fuel injector coupled to the combustion chamber and configured to deliver a first flow of fuel to the pilot combustion zone; and a slinger unit configured to deliver a second flow of fuel to the premixing zone such that the second flow of fuel is mixed with air in the premixing zone and directed into the lean combustion zone of the combustion chamber.09-15-2011
20090173078Methods and Systems for Providing Real-Time Comparison with an Alternate Control Strategy for a Turbine - A method for controlling and modeling a turbine is provided. The method may include modeling the turbine by a primary adaptive turbine model that includes at least one primary operating parameter and modeling the turbine by an alternate adaptive turbine model that includes at least one alternate operating parameter. The method may also include determining a first output value from the primary adaptive turbine model that corresponds at least in part to the operation of the turbine based on a primary control strategy and adjusting the alternate operating parameter or parameters based on an alternate control strategy and based at least in part on the first output value. The method may further include determining comparison data based at least in part on a comparison between the primary control strategy and the alternate control strategy.07-09-2009
20090025396Parallel 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.01-29-2009
20090249792OPERATION OF A GAS TURBINE - Provided is a control method for a gas turbine plant having a first and a second combustors in series, such that combustion gases produced in the first combustor flows into the second combustor. The second combustor having a fuel lance with internal partitions, for injecting at least one fuel and a gas having a mixture of inert gas and support air into the second combustor. The partitions enable the gas to carry, and/or veil, at least one of the fuels as the fuel exits the lance. A variable of the second combustor is measured and the inert gas to support air mixture varies in response to variations of the variable so as to at least partially compensate for the operational effects of the variable on the operation of the second combustor.10-08-2009
20100162720GAS TURBINE ENGINE - A gas turbine engine is provided having a variety of forms and features. The gas turbine engine can include a compressor having movable vanes. In one form of operation the compressor can close down the vanes to a relatively low flow capacity position and the compressor can be operated at a higher speed, whereupon the vanes can be repositioned and the gas turbine engine operated at a different condition. The gas turbine engine can include a turbine having movable vanes. In one form of operation the turbine can change the vane positions to a relatively low torque position and the engine operated at a higher fuel flow condition, whereupon the vanes can be repositioned and the gas turbine engine operated at a different condition. The gas turbine engine can have a heater that adds heat to a flow stream, a motor that provides energy to a shaft, and an external load.07-01-2010
20100162719GAS TURBINE ENGINE - A gas turbine engine is provided having a variety of forms and features. The gas turbine engine can include a compressor having movable vanes. In one form of operation the compressor can close down the vanes to a relatively low flow capacity position and the compressor can be operated at a higher speed, whereupon the vanes can be repositioned and the gas turbine engine operated at a different condition. The gas turbine engine can include a turbine having movable vanes. In one form of operation the turbine can change the vane positions to a relatively low torque position and the engine operated at a higher fuel flow condition, whereupon the vanes can be repositioned and the gas turbine engine operated at a different condition. The gas turbine engine can have a heater that adds heat to a flow stream, a motor that provides energy to a shaft, and an external load.07-01-2010
20130213049SYSTEM AND METHOD FOR HIGH EFFICIENCY POWER GENERATION USING A CARBON DIOXIDE CIRCULATING WORKING FLUID - The present invention provides methods and system for power generation using a high efficiency combustor in combination with a CO08-22-2013
20100162718SYSTEMS, APPARATUSES, AND METHODS OF GAS TURBINE ENGINE CONTROL - One embodiment according to the present invention is a unique system for gas turbine engine control. Other embodiments include unique apparatuses, systems, devices, and methods relating to gas turbine engines. Further embodiments, forms, objects, features, advantages, aspects, and benefits of the present invention shall become apparent from the following description and drawings.07-01-2010
20120102968METHOD FOR CONTROLLING A GAS TURBINE AND GAS TURBINE FOR IMPLEMENTING THE METHOD - A method for controlling a gas turbine, including during transient operating states, and such a gas turbine are provided. The gas turbine includes a compressor for compressing inducted combustion air, a combustion chamber for generating hot gas by combusting a fuel with the aid of the compressed combustion air, and a multistage turbine for expanding the generated hot gas and performing work. The controlling of the gais turbine is carried out in accordance with the hot gas temperature which is derived from a plurality of other measured operating variables of the gas turbine. A reliable controlling of the gas turbine is achieved, even during rapid changes, by pressure measurements being gathered exclusively at different points of the gas turbine for derivation of the hot gas temperature.05-03-2012
20100257866METHOD FOR COMPUTER-SUPPORTED CONTROL AND/OR REGULATION OF A TECHNICAL SYSTEM - A method for computer-supported control and/or regulation of a technical system is provided. In the method a reinforcing learning method and an artificial neuronal network are used. In a preferred embodiment, parallel feed-forward networks are connected together such that the global architecture meets an optimal criterion. The network thus approximates the observed benefits as predictor for the expected benefits. In this manner, actual observations are used in an optimal manner to determine a quality function. The quality function obtained intrinsically from the network provides the optimal action selection rule for the given control problem. The method may be applied to any technical system for regulation or control. A preferred field of application is the regulation or control of turbines, in particular a gas turbine.10-14-2010
20100251727Engine brake for part load CO reduction - Aspects of the invention relate to a system and method for operating a turbine engine assembly. The turbine engine assembly has a turbine engine having a compressor section, a combustor section and a turbine section. The combustor section has a lower T_PZ limit and the turbine engine has a design load. The assembly further includes at least one air bleed line from the compressor and at least one valve for controlling air flow through the bleed line. Control structure is provided for opening the valve to allow bleed air to flow through the bleed line when an operating load is less than the design load. The flow rate through the bleed line is increased as the operating load is decreased, reducing the power delivered by the turbine assembly while maintaining the T_PZ above a lower T_PZ limit. A method for operating a turbine engine assembly is also disclosed.10-07-2010
20100242489Systems, Methods, and Apparatus for Modifying Power Output and Efficiency of a Combined Cycle Power Plant - Embodiments of the invention can provide systems, methods, and an apparatus for modifying the power output and efficiency of a combined cycle power plant. According to one embodiment where a combined cycle power plant includes a compressor, a gas turbine, a combustor, and a heat recovery steam generator, excess air from the compressor can be extracted and expanded to generate power. The expanded air can then be mixed with at least one combustible fuel to generate a heated combustion product. The heated combustion product can be mixed with exhaust gas from the gas turbine to increase the temperature of the exhaust gas prior to introduction to the heat recovery steam generator. This increase in temperature of the exhaust gas from the gas turbine provides additional energy for generating steam and power and improves performance of the heat recovery steam generator.09-30-2010
20100251726Turbine engine transient power extraction system and method - A power extraction system for a gas turbine engine comprises a low spool generator, a high spool generator and a power controller. The low spool generator extracts power from a low spool of the gas turbine engine, and the high spool generator extracts power from a high spool of the gas turbine engine. The power controller receives power extracted by the low spool generator and the high spool generator and distributes the received power to provide an uninterrupted steady state power supply and a transient power supply larger than what is available individually from the low and high spool generators. In another embodiment of the invention, the power extraction system includes an engine controller that operates in conjunction with the power controller to increase inertia energy of the low spool and high spool to increase electric power supply, while engine excursion is reduced and consistent engine thrust is maintained.10-07-2010
20100000223METHOD OF TAKING OFF AUXILIARY POWER FROM AN AIRPLANE TURBOJET, AND A TURBOJET FITTED TO IMPLEMENT SUCH A METHOD - Producing the electrical power need for equipment on board an airplane. Auxiliary power is taken off by means of a shaft driven by the high pressure turbine and, when idling, the efficiency of the low pressure turbine is degraded so as to enable the high pressure turbine to operate at a speed that is sufficient for delivering the required auxiliary power.01-07-2010
20090288420METHOD FOR OPERATING A GAS TURBINE - A method for operating a gas turbine comprising a compressor, a combustion chamber and a turbine is to allow a particularly safe and reliable operation of the gas turbine. Furthermore, a gas turbine and gas and steam turbine plant, which are especially suitable for carrying out the method, are disclosed. For this purpose, the compressor discharge pressure is used as a control variable.11-26-2009
20100293959Method for Operating a Gas Turbine Engine, Power Supplying Device for Conducting such Method and Aircraft using such Method - A power supply device or system for aeronautics, having a hydrocarbon supply for supplying an engine with hydrocarbon fuel and a hydrogen supply having a fuel reformer for producing hydrogen from hydrocarbon fuel from said hydrocarbon supply. The hydrogen supply is connected to a hydrogen-powered fuel cell for producing electric power and to a hydrogen injecting system for injection of hydrogen into a combustion chamber of the engine. Further, the invention relates to an aircraft having an engine that can be supplied by that power supplying device or system, and to a method for operating said engine.11-25-2010
20100300108STABILIZING A GAS TURBINE ENGINE VIA INCREMENTAL TUNING - An auto-tune controller and tuning process implemented thereby for measuring and tuning the combustion dynamics and emissions of a GT engine, relative to predetermined upper limits, are provided. Initially, the tuning process includes monitoring the combustion dynamics of a plurality of combustors and emissions for a plurality of conditions. Upon determination that one or more of the conditions exceeds a predetermined upper limit, a fuel flow split to a fuel circuit on all of the combustors on the engine is adjusted by a predetermined amount. The control system continues to monitor the combustion dynamics and to recursively adjust the fuel flow split by the predetermined amount until the combustion dynamics and/or emissions are operating within a prescribed range of the GT engine.12-02-2010
20130139518MULTIPLE TURBOSHAFT ENGINE CONTROL METHOD AND SYSTEM FOR HELICOPTERS - Electric power from the low spool of a turboshaft engine is transferred to drive the compressor of an other turboshaft engine. This is used to assist in maintaining the other turboshaft idling while a single engine provides flight power or to increase acceleration for instance.06-06-2013
20130139519MULTI-SPOOL INTERCOOLED RECUPERATED GAS TURBINE - 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.06-06-2013
20100313572OPTICAL INTERROGATION SENSORS FOR COMBUSTION CONTROL - Certain embodiments of the invention may include systems and methods for providing optical interrogation sensors for combustion control. According to an example embodiment of the invention, a method for controlling combustion parameters associated with a gas turbine combustor is provided. The method can include providing an optical path through the gas turbine combustor, propagating light along the optical path, measuring absorption of the light within the gas turbine combustor, and controlling at least one of the combustion parameters based at least in part on the measured absorption.12-16-2010
20110030381GAS TURBINE ENGINE ROTARY INJECTION SYSTEM AND METHOD - A rotary injector (02-10-2011
20110016876METHOD FOR THE CONTROL OF GAS TURBINE ENGINES - A method for operating a gas turbine engine system under baseload and/or a high part load conditions is disclosed, the gas turbine engine system includes a gas turbine engine with at least one compressor with at least one row of adjustable variable vanes for control of the inlet air mass flow; at least one combustor; at least one turbine. A control system is provided, which, on the basis of and as a function of at least one measured temperature value measured upstream of the compressor or a measurable quantity directly functionally related thereto, controls the position of the variable vanes such that at least one measured pressure value varying with the angular position of the variable vanes is at a predefined target pressure which is a function of said first temperature.01-27-2011
20090320492CONTROL SYSTEM FOR GAS TURBINE IN MATERIAL TREATMENT UNIT - 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.12-31-2009
20110173988ADAPTIVE FAIL-FIXED SYSTEM FOR FADEC CONTROLLED GAS TURBINE ENGINES - A gas turbine engine control system includes a module operable to fail-fix the gas turbine engine to one of a multiple of pre-determined modes in response to failure of an automatic control.07-21-2011
20090320493METHOD FOR PRIMARY CONTROL OF A COMBINED GAS AND STEAM TURBINE ARRANGEMENT - A method for primary regulation of a combined gas and steam turbine installation in network operation, wherein the combined gas and steam turbine installation includes a gas turbine and a steam turbine arranged along at least one shaft includes operating at least one steam turbine actuating valve on a restricted basis along a working steam supply line to at least one pressure stage of the steam turbine so as to provide a steady-state steam turbine reserve power, wherein the at least one steam turbine actuating valve is changed to a less restricted state if a network frequency decreases so as to require network frequency support.12-31-2009
20110056210SURGE MARGIN REGULATION - The present invention relates to control of engine variable of a gas turbine engine to regulate the surge margins of at least two compressors. A controller (03-10-2011
20090301097Method and Device for Regulating the Operating Line of a Gas Turbine Combustion Chamber - A regulating device for regulating the course of a gas turbine plant has at least one sensor for sensing a measurement variable and for outputting a measurement signal which represents the measurement variable; at least one adjusting system for influencing air and/or fuel supply to a combustion chamber of the gas turbine plant on the basis of a correcting variable; and a regulator connected to the at least one sensor so as to receive the measurement variable and to the at least one adjusting system for outputting the correcting variable, the regulator being designed to determine the correcting variable on the basis of the measurement variable received and its deviation from a pilot variable. At least one sensor is designed to sense the variation in time of at least one burner or combustion chamber parameter as measurement variable.12-10-2009
20100018215PILOT FUEL INJECTION FOR A WAVE ROTOR ENGINE - Apparatus and methods for combustion of fuel. Some embodiments of the inventions include a fuel nozzle which injects fuel into a combustion channel of a wave rotor combustor or a pulse detonation combustor In some embodiments the combustion process includes a backward-propagating detonation wave within a substantially closed channel which compresses discrete quantities of combustible and noncombustible mixture. Yet other embodiments include a precombustion chamber integrated into the wave rotor, the outlet stator or both.01-28-2010
20100175385Method for Increasing Turndown Capability in an Electric Power Generation System - A method of operating an electric power generation system (07-15-2010
20100319356CONTROL APPARATUS AND CONTROL METHOD FOR COMPRESSOR - A control apparatus for controlling a compressor driven by a driving unit generating driving power by a gas turbine and an electric motor includes: a temperature detection section for detecting an exhaust gas temperature of the gas turbine; and a control section for generating a motor torque instruction value for the electric motor based on the detected exhaust gas temperature. Such a control apparatus can realize a control so as not to distribute a load on the electric motor when the exhaust gas temperature of the gas turbine is low and a driving power is low. As a result, the operation efficiency can be enhanced.12-23-2010
20110154828GAS TURBINE, METHOD OF CONTROLLING AIR SUPPLY AND COMPUTER PROGRAM PRODUCT FOR CONTROLLING AIR SUPPLY - The present invention provides a gas turbine capable of reducing energy consumption while suppressing a so-called cat back phenomenon. The gas turbine includes a combustor-accommodating chamber casing for accommodating therein a combustor which burns fuel and air compressed by a compressor to generate combustion gas and which injects the combustion gas to a turbine. The gas turbine also includes a first air supply passage and a second air supply passage on an upper portion of the combustor-accommodating chamber casing in the vertical direction. The first air supply passage discharges air toward the compressor in the combustor-accommodating chamber casing. The second air supply passage discharges air in a direction different from that of the first air supply passage.06-30-2011
20120204570Load Control Device and Method for Controlling the Load of an Engine - The present invention relates to a load control device for an engine and to a method for controlling the load. The load control device comprises a compressor for compressing air in an intake system of the engine; an exhaust gas line for discharging an exhaust gas mass flow from the engine; a turbine that is driven by an exhaust gas mass flow supplied by the exhaust gas line and that drives the compressor; a bypass line that branches off the exhaust gas line upstream of the turbine, wherein a first valve is disposed in the bypass line for controlling the mass flow in the bypass line; and an active cooling device that is disposed upstream of the valve.08-16-2012
20120011855OPERATION OF A COMBUSTOR APPARATUS IN A GAS TURBINE ENGINE - 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.01-19-2012
20120060505ADAPTIVE CONTROL FOR A GAS TURBINE ENGINE - A method for controlling a gas turbine engine includes: generating model parameter data as a function of prediction error data, which model parameter data includes at least one model parameter that accounts for off-nominal operation of the engine; at least partially compensating an on-board model for the prediction error data using the model parameter data; generating model term data using the on-board model, wherein the on-board model includes at least one model term that accounts for the off-nominal operation of the engine; respectively updating one or more model parameters and one or more model terms of a model-based control algorithm with the model parameter data and model term data; and generating one or more effector signals using the model-based control algorithm.03-15-2012
20110094238MODEL-BASED COORDINATED AIR-FUEL CONTROL FOR A GAS TURBINE - 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.04-28-2011
20120210725NON-FLAME-OUT TEST FOR THE COMBUSTION CHAMBER OF A TURBINE ENGINE - A method for ground control of proper operation of an aeronautical turbine engine for a plane. A test includes carrying out, on the operating turbine engine and from a predetermined speed, a quick reduction in fuel flow according to a programmed decrease to evaluate flame-out resistance of the combustion chamber of the turbine engine during a quick inflight deceleration maneuver of the speed thereof.08-23-2012
20120102967Method and system for preventing combustion instabilities during transient operations - A method and system for preventing or reducing the risk of combustion instabilities in a gas turbine includes utilizing a turbine controller computer processor to compare predetermined and stored stable combustion characteristics, including rate of change of the characteristics, with actual operating combustion characteristics. If the actual operating combustion characteristics are divergent from stable combustion characteristics then the controller modifies one or more gas turbine operating parameters which most rapidly stabilize the operation of the gas turbine.05-03-2012
20100287945METHOD FOR OPERATING A GAS TURBINE PLANT WITH A COMPRESSOR STATION FOR GASEOUS FUEL - The disclosure relates to a method for operating a gas turbine plant which is supplied with a fuel gas via a compressor station. The compressor station includes a compressor which compresses the fuel gas which is fed via a gas feed line and delivers it via at least one control valve to a combustion chamber of the gas turbine plant. A bypass system is arranged in parallel to the compressor via which fuel gas can be directed in a switchable manner past the compressor to the at least one control valve. An energy-saving operation can be achieved in a simple manner by continuously measuring the fuel gas pressure at the outlet of the at least one control valve. A minimum fuel gas pressure, which is desired (e.g., necessary) for operation of the gas turbine, at the inlet of the at least one control valve is determined from the measured pressure values in each case. The compressor station can be switched over to bypass operation when the fuel gas pressure which reaches the inlet of the at least one control valve via the bypass system is greater than or equal to the minimum fuel gas pressure.11-18-2010
20100175384Optical Flame Holding And Flashback Detection - Optical flame holding and flashback detection systems and methods are provided. Exemplary embodiments include a combustor including a combustor housing defining a combustion chamber having combustion zones, flame detectors disposed on the combustor housing and in optical communication with the combustion chamber, wherein each of the flame detectors is configured to detect an optical property related to one or more of the combustion zones.07-15-2010
20120247119ACTIVE PATTERN FACTOR CONTROL FOR GAS TURBINE ENGINES - A method of actively controlling pattern factor in a gas turbine engine includes the steps of issuing fuel into a combustion chamber of a gas turbine engine through one or more circumferentially disposed fuel injectors, determining an initial circumferential pattern factor in the combustion chamber, and adjusting fuel flow through one or more selected fuel injectors based on the initial circumferential pattern factor, to yield a modified circumferential pattern factor in the combustion chamber. The step of determining the circumferential pattern factor can include the steps of detecting a chemiluminescent signature within the combustor, correlating the chemiluminescent signature to an equivalence ratio, and computing the initial circumferential pattern factor based on the equivalence ratio. Alternatively, the step of determining the circumferential pattern factor can include the steps of measuring temperatures at a plurality of circumferential positions at the combustor exit and computing the initial circumferential pattern factor based on the measured temperatures.10-04-2012
20120167581Method of controlling a combined-cycle system in single-shaft configuration, and combined-cycle system in single-shaft configuration - A combined-cycle system includes a compressor, a gas turbine, a steam turbine, and an electric generator, which are coupled to the same shaft. A method of controlling the system envisages detecting a current compression ratio of the compressor, calculating a normalized compression ratio on the basis of the current compression ratio, and determining a load condition of the gas turbine on the basis of the normalized compression ratio. Moreover, a setpoint is selected, for at least one operating quantity of the gas turbine, and regulating signals are applied to actuators of the gas turbine so that the operating quantity of the gas turbine tends to reach the setpoint.07-05-2012
20120247118COMBUSTOR CROSSFIRE TUBE - The present application and the resultant patent provide a combustor for mixing a flow of air and a flow of fuel. The combustor may include an air path for the flow of air, a number of fuel injectors positioned in the air path for the flow of fuel, and a crossfire tube positioned within the air path upstream of the fuel injectors. The crossfire tube may include a number of purge holes positioned on a downstream side thereof to reduce a wake in the flow of air caused by the crossfire tube in the air path.10-04-2012
20110120136METHOD OF OPERATING A TURBOFAN ENGINE COWL ASSEMBLY - An inner core cowl baffle assembly for a turbofan engine assembly is provided. The engine assembly includes a core gas turbine engine, a core cowl which circumscribes the core gas turbine engine, a nacelle positioned radially outward from the core cowl, and a fan nozzle duct defined between the core cowl and the nacelle. The inner core cowl baffle assembly includes an inner core cowl baffle, and an actuator assembly configured to vary the throat area of the fan nozzle duct by selectively repositioning the inner core cowl baffle with respect to the core cowl.05-26-2011
20110265486COMBUSTION SYSTEM WITH VARIABLE PRESSURE DIFFERENTIAL FOR ADDITIONAL TURNDOWN CAPABILITY OF A GAS TURINE ENGINE - A turbine engine assembly for a generator including a turbine engine having a compressor section, a combustor section and a turbine section, and the turbine engine having a base load. The combustor section includes a combustor and a combustor shell. A flow control device is located in a flow path between the combustor shell and an inlet to the combustor. The flow control device effects an increase in a pressure drop of shell air flowing from the combustor shell to the combustor. A controller is provided for operating the flow control device to change a pressure drop across the flow control device, wherein an increase in the pressure drop across the flow control device results in a corresponding reduction in mass flow through the combustor for effecting a reduction in power output from the turbine engine during a reduction in an operating load to less than the base load.11-03-2011
20120279229METHOD FOR PROTECTING A GAS TURBINE ENGINE AGAINST HIGH DYNAMICAL PROCESS VALUES AND GAS TURBINE ENGINE FOR CONDUCTING THE METHOD - A method can protect a gas turbine engine (11-08-2012
20120279230EXHAUST TEMPERATURE BASED THRESHOLD FOR CONTROL METHOD AND TURBINE - Gas turbine and method for controlling an operating point of the gas turbine that includes a compressor, a combustor and at least a turbine. The method includes calculating an exhaust temperature reference curve of the turbine as a function of a turbine pressure ratio; determining whether condition IGV11-08-2012
20100199680GAS TURBINE CONTROL METHOD AND DEVICE - 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. A gas turbine control device comprises a frequency analyzing means for analyzing the frequencies inside the combustor of a gas turbine, a state grasping means for grasping the combustion state in the gas turbine on the basis of a state signal representing the result of the analysis by frequency band, the amount of operation process including a ratio between the air flow rate and pilot fuel in the gas turbine, the atmosphere state, and the load amount, a combustion characteristic grasping means for grasping the characteristic of the combustion vibration, and a control section for calculating a correction value of at least either the air flow rate supplied to the combustor or the pilot ratio from the grasped combustion vibration characteristic and the grasped combustion state each time the degree of the combustion vibration exceeds a predetermined control value, correcting the initial design values of the air flow rate and the pilot ratio predetermined correspondingly to the amount of operation process and the state signal, and thereby driving the gas turbine. The control section resets the correction of the initial design values when the degree of combustion vibration of the gas turbine is below the predetermined control value for a given period of time and operates the gas turbine using the initial design values.08-12-2010
20130019606GAS TURBINE ENGINE SPEED CONTROL SYSTEM AND METHOD DURING MAXIMUM FUEL FLOW - 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.01-24-2013
20130019607EXHASUST TEMPERATURE VERSUS TURBINE PRESSURE RATIO BASED TURBINE CONTROL METHOD AND DEVICE - Gas turbine, software and method for controlling an operating point of the gas turbine that includes a compressor, a combustor and at least a turbine is provided. The method includes determining a turbine exhaust pressure at an exhaust of the turbine; measuring a compressor pressure discharge at the compressor; determining a turbine pressure ratio based on the turbine exhaust pressure and the compressor pressure discharge; calculating an exhaust temperature at the exhaust of the turbine as a function of the turbine pressure ratio; identifying a reference exhaust temperature curve in a plane defined by the exhaust temperature and the turbine pressure ratio; and controlling the gas turbine to maintain the operating point on the reference exhaust temperature curve.01-24-2013
20130167549COMPRESSOR GUIDE VANE AND PILOT CONTROL FOR GAS TURBINE ENGINE - A method of controlling a turbine engine. The method may include adjusting a position of a plurality of guide vanes of a compressor. The adjusting the position of the plurality of guide vanes may be a function of a compressor temperature signal. The method may further include adjusting a quantity of fuel delivered to a combustor via a pilot assembly. The adjusting of the quantity of fuel may be a function of a temperature difference resulting from the adjusting a position of the plurality of guide vanes.07-04-2013
20110232294METHODS AND SYSTEMS FOR MITIGATING DISTORTION OF GAS TURBINE SHAFT - Methods and systems for mitigating distortion of a shaft of a gas turbine engine are provided. One method comprises at least one step of applying intermittent rotary power to a shaft of a gas turbine engine. The step of applying intermittent power to the shaft is performed during a period where conditions of temperature differential in the engine exist capable of distorting the shaft. The methods and systems shorten the time needed to start a gas turbine engine in such a way that bowing of a shaft is not a significant problem.09-29-2011
20110232295METHOD FOR OPERATION OF AN INTEGRATED SOLAR COMBINED-CYCLE POWER STATION, AND A SOLAR COMBINED-CYCLE POWER STATION FOR CARRYING OUT THIS METHOD - A method is provided for operation of an integrated solar combined-cycle power station. The power station includes a water/steam circuit having a steam turbine and a heat recovery steam generator through which hot exhaust gases from a gas turbine flow. The water/steam circuit is additionally supplied with heat from a solar array. In such a method, an optimum cost-benefit relationship is achieved in that the water/steam circuit is designed only for the full load on the gas turbine, and in that, when feeding additional power from the solar array into the water/steam circuit, the load on the gas turbine is reduced, on the basis of the power additionally fed in from the solar array, to such an extent that the total output power of the integrated solar combined-cycle power station remains substantially constant.09-29-2011
20130199196SYSTEM AND METHOD FOR GAS TURBINE PART LOAD EFFICIENCY IMPROVEMENT - In one embodiment of the present disclosure, a gas turbine system for part load efficiency improvement is described. The system includes a gas turbine having a compressor which receives inlet-air. An evaporative cooler system using heated fluid heats the inlet-air before the inlet-air flows to the compressor. Heating the inlet-air reduces an output of the gas turbine and extends the turndown range.08-08-2013
20130199197DEVICE AND A METHOD FOR REGULATING A TURBINE ENGINE, AND AN AIRCRAFT - A regulator device (08-08-2013
20130199198METHOD OF AUTOMATICALLY REGULATING AN AIRCRAFT POWER PLANT, A DEVICE, AND AN AIRCRAFT - A method of automatically regulating a power plant (08-08-2013
20100000222Controlling a gas turbine engine with a transient load - A technique is provided for operating a gas turbine engine that has a combustor with a primary stage and one or more other stages and a first compressor providing an air flow to the combustor. This technique includes driving a variable load device with the rotating shaft of the gas turbine engine and sensing pressure of the air flow and an engine speed. In response to a decrease in loading of the engine by the variable load device: selectively bleeding the air flow as a function of the engine speed and regulating temperature in the primary stage of the combustor as a function of a ratio between fuel flow provided to primary stage and the pressure to prevent engine flame out. In one form, the combustor is arranged as a dry load emissions type and the variable load device includes an electric power generator.01-07-2010
20130174567Automatic Engine Noise Reduction - A method of reducing engine noise for an engine under little or low load conditions includes the steps of: establishing an engine idle speed for the engine when the engine has less than a predetermined minimum level of load; measuring the level of load on the engine; measuring the speed of the engine; and reducing the speed of the engine to the engine idle speed if the measured level of load on the engine is less than the predetermined minimum level of load and the measured speed of the engine is greater than the engine idle speed.07-11-2013
20130091856CONTROL SYSTEM AND METHODS FOR CONTROLLING THE OPERATION OF POWER GENERATION SYSTEMS - A control system is provided. The control system includes at least one sensor positioned within a turbine engine, wherein the sensor is configured to detect at least one first operating parameter within the turbine engine. A controller is coupled to the sensor and the controller is configured to receive at least one second operating parameter of the turbine engine. The controller is also configured to control a flow of a fluid to a rotor assembly within the turbine engine such that the fluid is distributed substantially uniformly within the rotor assembly and at least one of the first operating parameter and the second operating parameter is less than at least one threshold value.04-18-2013
20130091855SYSTEM FOR USE IN CONTROLLING THE OPERATION OF POWER GENERATION SYSTEMS - A control system is provided. The control system includes at least one sensor that is positioned within a turbine engine and is configured to detect at least one first operating parameter therein. A controller is coupled to the sensor. The controller is configured to receive at least one second operating parameter of the turbine engine. Moreover, the controller is configured to control a flow of a fluid to a rotor assembly within the turbine engine such that at least one of the first operating parameter and the second operating parameter is less than at least one threshold value.04-18-2013
20130111917APPARATUS FOR AIRCRAFT WITH HIGH PEAK POWER EQUIPMENT - An apparatus is provided for supplying electrical power and cooling for an aircraft. The apparatus includes a cooling turbine coupled to a shaft, a compressor coupled to the shaft, and including an input for receiving engine bleed air or ambient air, and an output for discharging compressed air, a flywheel coupled to the shaft, a power turbine coupled to the shaft, and a starter generator coupled to the shaft between the compressor and the power turbine.05-09-2013
20130111916SYSTEM FOR OPERATING A POWER PLANT - A system for operating a power plant is provided and includes a grid configured to generate a normal load and an abnormal load, a turbomachine configured to provide power to the grid in accordance with the normal load by firing at normal temperatures and in accordance with the abnormal load by firing at higher-than-normal temperatures, a cooling system disposed to cool components of the turbomachine with fluid supplied by an external reservoir and a controller configured to identify when the grid generates the abnormal load and to responsively operate the cooling system.05-09-2013
20130111915SYSTEM FOR OPTIMIZING POWER USAGE FROM DAMAGED FAN BLADES - An aircraft jet engine system includes at least one gas turbine engine having a fan including a rotor and a plurality of fan blades. A sensor system in the fan section senses information about the operation of the blades and provides feedback on the condition of each blade to a control. The control is programmed to take in the sensed information and identify a safe operating range for the gas turbine engine based upon damage information developed from the sensed information with regard to each of the blades. An aircraft jet engine system incorporating a plurality of gas turbine engines wherein safe operating ranges are developed for each of the gas turbine engines is also disclosed as is a method of operating an aircraft jet engine system.05-09-2013
20130098054Method for Operating a Gas Turbine - In a method for operating a gas turbine (04-25-2013
20130098053SYSTEMS AND METHODS FOR USE IN OPERATING TURBINE ENGINES - A control system for use with a turbine engine that is configured to operate at a rated power output is provided. The control system includes a computing device that includes a processor that is programmed to calculate an amount of fluid to be supplied for combustion in the turbine engine. The processor is also programmed to designate at least one nozzle of a plurality of nozzles to receive the fluid. Moreover, the control system includes at least one control valve coupled to the computing device. The control valve is configured to receive at least one control parameter from the computing device for use in modulating the amount of the fluid to be channeled to the nozzle such that the rated power output is generated while emission levels are maintained below a predefined emissions threshold level.04-25-2013
20130125557METHOD AND APPARATUS FOR OPTIMIZING THE OPERATION OF A TURBINE SYSTEM UNDER FLEXIBLE LOADS - A gas turbine system includes a compressor protection subsystem; a hibernation mode subsystem; and a control subsystem that controls the compressor subsystem and the hibernation subsystem. At partial loads on the turbine system, the compressor protection subsystem maintains an air flow through a compressor at an airflow coefficient for the partial load above a minimum flow rate coefficient where aeromechanical stresses occur in the compressor. The air fuel ratio in a combustor is maintained where exhaust gas emission components from the turbine are maintained below a predetermined component emission level while operating at partial loads.05-23-2013
20130125556FUEL-AIR MIXTURE DISTRIBUTION FOR GAS TURBINE ENGINE COMBUSTORS - A method of noise control from a combustor of a gas turbine engine includes selectively forming a plurality of local circumferential zones with different fuel-air ratios within the combustor.05-23-2013
20130133332SYSTEMS AND METHODS FOR CHANGING A SPEED OF A COMPRESSOR BOOST STAGE IN A GAS TURBINE - Systems and methods for changing a speed ratio between a compressor boost stage (05-30-2013
20130152597SYSTEM AND METHOD FOR FLAME STABILIZATION - A system and method for flame stabilization is provided that forestalls incipient lean blow out by improving flame stabilization. A combustor profile is selected that maintains desired levels of power output while minimizing or eliminating overboard air bleed and minimizing emissions. The selected combustor profile maintains average shaft power in a range of from approximately 50% up to full power while eliminating overboard air bleed in maintaining such power settings. Embodiments allow for a combustor to operate with acceptable emissions at lower flame temperature. Because the combustor can operate at lower bulk flame temperatures during part power operation, the usage of inefficient overboard bleed can be reduced or even eliminated.06-20-2013
20130180259SYSTEM AND METHOD FOR GENERATING POWER USING A SUPERCRITICAL FLUID - A dual cycle system for generating shaft power using a supercritical fluid and a fossil fuel. The first cycle is an open, air breathing Brayton cycle. The second cycle is a closed, supercritical fluid Brayton cycle. After compression of air in the first cycle, the compressed air flows through a first cross cycle heat exchanger through which the supercritical fluid from the second cycle flows after it has been compressed and then expanded in a turbine. In the first cross cycle heat exchanger, the compressed air is heated and the expanded supercritical fluid is cooled. Prior to expansion in a turbine, the compressed supercritical fluid flows through a second cross cycle heat exchanger through which also flows combustion gas, produced by burning a fossil fuel in the compressed air in the first cycle. In the second cross cycle heat exchanger, the combustion gas is cooled and the compressed supercritical fluid is heated.07-18-2013
20110308256Control 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.12-22-2011
20120017600Combustor Control Method and Combustor Controller - 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. An ignition/extinction control unit of the combustor control device calculates the combustion air flow supplied to the combustors based on the open position of compressor inlet guide vanes attached to the gas generator turbine, revolution speed of the gas generator turbine and compressor inlet temperature, calculates the flow of fuel supplied to the combustors based on revolution speed of the power turbine, and calculates the fuel-air ratio in real time as flame reference based on the calculated combustion air flow and fuel flow.01-26-2012

Patent applications in class Having power output control