Entries |
Document | Title | Date |
20080209910 | METHOD OF STARTING A GAS TURBINE HELICOPTER ENGINE, A FUEL FEED CIRCUIT FOR SUCH AN ENGINE, AND AN ENGINE HAVING SUCH A CIRCUIT - At least one of the main injectors of the engine, forming a starter main injector, is fed directly by the pressurized feed pipe, while a head loss is imposed between the pressurized feed pipe and the other main injectors. Ignition is caused to take place at the starter main injector, and after ignition, said head loss imposed between the feed pipe and the other main injectors is eliminated so that all of the main injectors are fed with fuel at substantially the same pressure, without any imposed head loss. | 09-04-2008 |
20080229757 | Methods and systems for output variance and facilitation of maintenance of multiple gas turbine plants - A method of operating a power generation system is provided. The system includes a first gas turbine engine that uses at least one of a primary fuel and a secondary fuel, and at least one second gas turbine engine that operates using at least one of a primary and secondary fuel. The method includes supplying primary fuel to at least one of the first and second engines from a common fuel source coupled to the first and second engines, and selectively operating the first engine between a first operational position and a second operational position. The first engine using only secondary fuel in the first operational position and operates using only primary fuel in the second operational position. The method includes supplying the second engine with primary fuel from the common fuel source without flaring the primary fuel. | 09-25-2008 |
20090013696 | Gas turbine engine mixing duct and method to start the engine - A combustion chamber device having a field static pressure gradient adapted to expel a flame kernel or hot spot from a fuel-air mixing duct. The swirling flow passing through an annular mixing duct is turned from a radial direction to an axial direction before entering the combustion chamber. An ignition source located within the fuel-air mixing duct can then be used to start the combustion process in the gas turbine. | 01-15-2009 |
20090120098 | GAS TURBINE ENGINE COMPRISING A STARTER IN THE AUXILIARY GEAR BOX - A gas turbine engine incorporating a starter mounted on the gear box | 05-14-2009 |
20090260367 | Multi-Compressor String With Multiple Variable Speed Fluid Drives - Starter arrangement for high power rotating equipment strings with multiple compressors driven by a single turbine or motor includes multiple variable fluid drive torque converters (CSTCs) to start the compressors in a pressurized start. The string can use a single CSTC for each compressor or a single CSTC for more than one compressor with at least two CSTCs for a given string. The starting procedure is sequential. After the turbine or motor is started and brought up to speed, successive CSTCs are operated from zero to lock-up speed sequentially to start each compressor or group of compressors in turn. In order to cool the working fluid of the CSTCs, a single heat exchanger is provided and the working fluid of each CSTC in turn is circulated through the heat exchanger as they are sequentially started. At lock-up speed, the CSTC is locked up, the working fluid is drained, and the working fluid of the active CSTC is isolated from the heat exchanger and the next succeeding CSTC in the start sequence is in turn, filled with the working fluid and connected to the heat exchanger. At full start, with all compressors operating at full speed, no working fluid is present in the CSTCs, and no working fluid is circulated through the heat exchangers from the locked-up CSTCs. A single heat exchanger may also be used for multiple strings, each having multiple CSTCs for multiple compressors. The starter arrangement is useful in high compressor load strings for LNG refrigeration service. | 10-22-2009 |
20090314002 | BI-MODAL TURBINE ASSEMBLY AND STARTER / DRIVE TURBINE SYSTEM EMPLOYING THE SAME - A bi-modal turbine assembly is provided for use in conjunction with a gas turbine engine. In one embodiment, the bi-modal turbine assembly includes a housing assembly having a flow passage therethrough, a turbine wheel rotatably mounted in the housing assembly and positioned so as to be driven by pressurized air flowing through the flow passage, an output shaft rotatably mounted in the housing assembly, and first and second gear trains disposed in the housing assembly. A switching device is also disposed in the housing assembly and configured to mechanically couple: (i) the first gear train between the turbine wheel and the output shaft in a first operational mode, and (ii) the second gear train between the turbine wheel and the output shaft in a second operational mode. | 12-24-2009 |
20090314003 | 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 | 12-24-2009 |
20100043444 | STARTING TURBINE ENGINES - A method for implementing a system and a device for enhancing the starting process of a turbine engine by use of at least one solid mass of oxidizing-species-releasing material, ORM, selected as a solid oxidizer, or SO, and/or as an oxidizing-species-releasing burning substance, or ORBS. The ORM is introduced into the combustion chamber of the turbine engine and the starting process of the turbine engine is initiated, by help of the igniter and in association with the mass of ORM, to enhance the starting process. In operation, an ORM selected as an SO releases gaseous oxygen when heated to decompose, while an ORM chosen as an ORBS discharges oxidizing species when ignited to burn. An ORM such as an SO or an ORBS may operate alone or in various combinations of both. The ORM is configured to release a predetermined mass flow rate of oxidizing species or of gaseous oxygen. | 02-25-2010 |
20100107648 | Method and System for Starting a Turboshaft Engine by Cold Weather - According to the invention, when starting a turboshaft engine ( | 05-06-2010 |
20100126179 | METHOD FOR THE START-UP OF A GAS TURBINE - A method is described for the start-up of a gas turbine comprising the phases of effecting a preliminary purging cycle of the discharge duct ( | 05-27-2010 |
20100162721 | APPARATUS FOR STARTING A STEAM TURBINE AGAINST RATED PRESSURE - An external steam turbine main steam startup control valve bypass loop is provided to facilitate a full pressure combined cycle rapid response/fast start powerplant. The main steam startup bypass control loop particularly includes a main steam startup bypass control valve, which allows for the implementation of high efficiency, low pressure drop main steam control valve that otherwise would not be able to handle the severe throttling duty during a full pressure steam turbine startup and enhances the controllability of the steam turbine allowing for the high fidelity controls necessary to minimize steam turbine rotor stresses. | 07-01-2010 |
20100170262 | AIRCRAFT POWER AND THERMAL MANAGEMENT SYSTEM WITH ELECTRIC CO-GENERATION - A power and thermal management system includes an integrated power package which receives bleed air, communicates conditioned air to an environmental control air distribution system and selectively communicates electrical power with an electrical distribution system. | 07-08-2010 |
20100180604 | METHOD FOR STARTING PREMIXED COMBUSTION IN COMBUSTOR FOR TWO-SHAFT GAS TURBINE - A two-shaft gas turbine is capable of starting premixed combustion without extinguishing a flame. The two-shaft gas turbine includes a combustor and a gas generator controller. The combustor has a premix burner that includes combustion regions in which premixed combustion is to be carried out individually. The gas generator controller controls the combustor. In a method for starting the premixed combustion in the combustor, the gas generator controller selects at least one of the combustion regions in which the premixed combustion is to be carried out, on the basis of a fuel-air ratio, and starts premix combustion in the selected combustion region or separately in each of the selected combustion regions. Further, as the fuel-air ratio is increased, the controller increases the number of the selected region in which the premixed combustion is carried out. | 07-22-2010 |
20100212326 | POWERPLANT AND A METHOD OF DRIVING A MECHANICAL SYSTEM VIA SAID POWERPLANT - A powerplant ( | 08-26-2010 |
20100281877 | SINGLE SHAFT COMBINED CYCLE POWER PLANT START-UP METHOD AN SINGLE SHAFT COMBINED CYCLE POWER PLANT - In a start-up method of a single shaft combined cycle power plant, during a time period from when the gas turbine is started up to when rotation speed of the gas turbine reaches a rotation speed allowing self-sustained operation using the combustion gas, auxiliary steam from the start-up boiler is fed to the low-pressure steam turbine via the low-pressure turbine steam supply pipe by controlling valve opening degree of the auxiliary steam flow control valve. The low-pressure steam turbine generates a drive force. Speed-up control is performed in a unified manner for the gas turbine, the high-pressure steam turbine, the low-pressure steam turbine, and the power generator. | 11-11-2010 |
20100287948 | UNLOADED SPEED CONTROL FOR AVAILABILITY IMPROVEMENTS TO HEAVY FUEL FIRED GAS TURBINES - Control of gas turbine speed and acceleration during unloaded rotation may limit stresses on components and facilitate timely operational performance. Operation of a torque converter driving a gas turbine shaft from a starter motor provides control over acceleration and speed of the gas turbine shaft. Hydraulic coupling between the input and output of the torque converter is adjusted by draining and refilling the working fluid in a body of the torque converter to control acceleration and speed of the rotor shaft during a first speed range. Vane positioning within the torque converter may be alternated between discrete speed settings to control acceleration and speed of the rotor shaft during a second speed range. A turbine control system with an acceleration schedule may provide control signals for these functions. | 11-18-2010 |
20100293960 | Gas Turbine Engine Starting Method and Control Device - A method of starting a gas turbine engine by use of a start sequence is provided. Turbine speed and fuel delivery are coordinated so as to provide a fuel/air mixture at an ignition device allowing a successful ignition. If a successful ignition has not occurred by end of the start sequence the gas turbine engine is purged and the start sequence is repeated after the purging of the gas turbine engine. | 11-25-2010 |
20100293961 | GAS TURBINE STARTING WITH STEPPING SPEED CONTROL - The system and method of the present invention provides stepping speed control of a gas turbine engine to reliably light-off a gas turbine engine. During starting, the speed of the gas turbine engine is incremented by stepped amounts through the light-off window from a minimum speed value to a maximum speed value, with the speed of the gas turbine dwelling at each stepped value for a period of time before incrementing the speed of the engine to the next stepped level. If the gas turbine engine is stepped through the entire light-off window without success, the controller decreases the speed of the gas turbine engine to the minimum value and begins the process again. The process continues until successful light-off is initiated or until the light-off window is traversed a certain number of times, after which the start process is aborted. | 11-25-2010 |
20100319357 | DEVICE AND A METHOD FOR STARTING A TURBINE ENGINE FITTED TO A HELICOPTER, MAKING USE OF AN ELECTRICAL ENERGY SOURCE THAT INCLUDES DISCHARGE BOOSTER MEMBERS - The invention provides a device and a method for starting at least one turbine engine ( | 12-23-2010 |
20100326085 | LIGHTWEIGHT START SYSTEM FOR A GAS TURBINE ENGINE - A start system for an engine package with a high spool includes a power source which generates air. A nozzle system in fluid communication with the power source, the nozzle system operable to direct air toward the high spool to spin-up the high spool. | 12-30-2010 |
20100326086 | METHOD AND SYSTEM FOR ENHANCING START OF A TURBINE ENGINE, AND IGNITION MODULE - A method, a system, and a product for enhancing the start of a turbine engine by providing a replaceable ignition module including a solid combustible substance, that when ignited, or a solid oxidizer substance, that when heated, releases hot gases rich in oxidizing species. The module includes a solid substance(s) appropriately selected as: a solid-propellant grain (SPG) and a solid oxidizer (SO); or an oxygen-rich burning substance (OBSS); or a solid-propellant to grain and an oxygen-rich burning substance; or an oxygen-rich burning solid substance and a solid oxidizer. The replaceable module further contains an initiator for the initiation of the solid combustible substance, or solid-propellant grain by an initiation command (IC). The hot gases released by the ignition module start and enhance the combustion process of the air-and-fuel mixture by successive fuel heating and vaporization, followed by ignition. | 12-30-2010 |
20110041511 | Gas turbine engine - A bypass turbofan gas turbine engine is started by means of electric starter motor mounted directly about a downstream end or upstream of the low pressure spool of the engine. This causes air to be driven by a fan through a bypass duct around the engine casing. Closures close to substantially seal an outlet of the bypass duct, and the air is directed into a combustion chamber of the engine and through the turbines, causing the high pressure spool to pick up speed for starting. | 02-24-2011 |
20110061396 | Relighting a Turbofan Engine - The method and apparatus for in-flight relighting of a turbofan engine involve in one aspect selectively controlling an accessory drag load on one or more windmilling rotors to permit control of the windmill speed to an optimum value for relight conditions. | 03-17-2011 |
20110094241 | GAS TURBINE STARTING PROCESS - A starting process for a gas turbine ( | 04-28-2011 |
20110138818 | GAS TURBINE AND OPERATING METHOD THEREOF - Provided is a gas turbine capable of achieving high-speed startup of the gas turbine through quick operation control of an ACC system during startup of the gas turbine, improving the cooling efficiency of turbine stationary components, and quickly carrying out an operation required for cat back prevention during shutdown of the gas turbine. Included are a pressurizing device ( | 06-16-2011 |
20110146290 | METHOD OF STARTING A TURBOMACHINE - The present invention has the technical effect of reducing the start-up time associated with starting a powerplant machine. An embodiment of the present invention provides a method of starting a powerplant machine, such as, but not limiting of, a turbomachine. An embodiment of the method of the present invention provides a new philosophy for starting a turbomachine. This new philosophy involves testing the turbomachine systems before the start-up process begins. | 06-23-2011 |
20110146291 | METHOD FOR STARTING A TURBOMACHINE - Embodiments of the present invention employ a closed loop controls philosophy, which actively controls the starting means of a powerplant machine, throughout the start-up process. Here, the present invention may provide a method for adjusting a nominal operating schedule of the starting means, which may have the form of a Load Commutated Inverter (LCI). Embodiments of the method may adjust the nominal operating schedule based, in part, on an operating parameter, which is associated with the gas turbine | 06-23-2011 |
20110146292 | METHOD FOR STARTING A TURBOMACHINE - Embodiments of the present invention employ a closed loop controls philosophy that actively determines the air-to-fuel ratio of turbomachine throughout the start-up process. This closed loop controls philosophy provides many benefits. This philosophy performs the ignition process while the turbomachine is operating at a purge speed and eliminates the associated coast down period. Reduces or eliminates the warm-up timer. The philosophy may also increase the acceleration rate of the turbomachine to the primary operating speed. These benefits may reduce the overall start-up time of the turbomachine. | 06-23-2011 |
20110146293 | METHOD FOR CONNECTING A STARTING MEANS TO A TURBOMACHINE - An embodiment of the present invention provides a method of starting a powerplant machine, such as, but not limiting of, a turbomachine set to operate in a Fast Start mode. The turbomachine may include, but is not limited to, a steam turbine, a heavy-duty gas turbine, an aero-derivative gas turbine, and the like. An embodiment of the method of the present invention provides a new philosophy for controlling a starting system associated with the turbomachine. An embodiment of the present invention may be applied to a powerplant having multiple turbomachines and a starting system having multiple starting means, which may include at least one LCI system. Here, an embodiment of the present invention may eliminate the manual process of preparing and integrating a desired turbomachine with a desired starting means. | 06-23-2011 |
20110179802 | SYSTEM AND METHOD FOR GAS TURBINE STARTUP CONTROL - A system and method for startup control of a gas turbine is disclosed. The system and method includes defining a target startup time for the startup of the gas turbine and determining a remaining time to achieve the target startup time. The system and method includes monitoring at least one parameter associated with the startup and determining a first operating point for the parameter. The system and method adjusts the first operating point for the parameter to a second operating point based at least in part on the remaining time for the startup. The system and method controls an effector based on the second operating point for the parameter. | 07-28-2011 |
20110185744 | METHOD AND APPARATUS FOR COMBINED CYCLE POWER PLANT STARTUP - A combined cycle power plant startup system is provided. The system includes a steam turbine, a HRSG, a condenser, and a bypass system. The steam turbine may include a turbine section. The HRSG may be operably connected to the steam turbine for providing steam to the steam turbine. The HRSG may include a reheater. The bypass system may be configured to adjust the steam pressure downstream of the reheater by routing steam downstream of the reheater to the condenser. The bypass system may include at least one bypass line, at least one control valve operably connected to the at least one bypass line, a pressure gauge configured to monitor the steam pressure downstream of the reheater, and a controller configured to communicate with the pressure gauge and operate the at least one control valve. | 08-04-2011 |
20110185745 | EMERGENCY POWER ENGINE RESTART SYSTEM - An engine starting apparatus and method may allow for two methods of engine start where only one engine gearbox accessory pad exists off the aircraft engine. A gearbox lubricating apparatus may also be provided to lubricate the gearbox at altitude without added complexity. Two engine starting inputs (for example, one input for ground start and one input for in-flight engine start) are provided while avoiding complex gearbox designs. Clutches may also be used to prevent the starter gearbox from continuous operation (rotation) after the engine has started. Apparatus and methods are also provided for improving the air-fuel combustion of the hot-gas turbine start input (for in-flight engine start) to minimize the build-up of solid carbon (soot) in and around the combustor and turbine nozzle flow passages. | 08-04-2011 |
20110239657 | CONTROL APPARATUS FOR GAS TURBINE AND START UP METHOD FOR GAS TURBINE - An electronic control apparatus which is applied to a gas turbine is provided. The electronic control apparatus includes a cylindrical combustor in which air compressed by a compressor is supplied, a plurality of fuel injection valves aligned in a circumferential direction in the combustor which are capable of injecting fuel into the combustor, and an ignition plug provided in the combustor which is capable of igniting a fuel-air mixture within the combustor. The electronic control apparatus controls the operation of the plurality of fuel injection valves so that when the gas turbine is started up, fuel injection opening times of the #6 and #12 fuel injection valves which are positioned far from the ignition plug are later than fuel injection opening times of the #1 and #7 fuel injection valves which are positioned close to the ignition plug. | 10-06-2011 |
20110259016 | METHOD OF STARTING A GAS TURBINE ENGINE - A method of starting a gas turbine engine includes maintaining the gas turbine engine at the dwelling speed after light-off until a predetermined magnitude of combustor warm-up is determined then increasing the speed of the starter motor to accelerate the gas turbine engine after the predetermined magnitude of combustor warm-up is achieved. | 10-27-2011 |
20110289934 | Gas Turbine Startup Control - A method for gas turbine start-up can include placing a static starter in a torque control mode, sending a torque reference to the static starter to establish a startup torque for the gas turbine, setting current set points for the static starter and modulating a current output to achieve the startup torque. | 12-01-2011 |
20110296843 | POSITIVE DISPLACEMENT POWER EXTRACTION COMPENSATION DEVICE - A positive displacement power extraction compensation device is used to start and control the operation of engines. The device includes a positive displacement fixed vane compressor having a rotor connected with a drive shaft, a combustor connected with the compressor and a positive displacement power extraction device also having a rotor connected with a drive shaft. The compressor and power extraction devices are configured to displace unequal volumes of air at a given speed, so that combustion gases from the combustor exert less force on the compressor drive shaft as on the power extraction device drive shaft. | 12-08-2011 |
20120000204 | MULTI-SPOOL INTERCOOLED RECUPERATED GAS TURBINE - A method and apparatus are disclosed for a multi-spool gas turbine power plant which utilizes motor/generator devices on two or more spools for starting the gas turbine and for power extraction after starting. Methods are disclosed for controlling engine responsiveness under changing load and/or ambient air conditions; providing a momentary power boost when required; providing some engine braking when needed; providing over-speed protection for the free power turbine when load is rapidly lowered or disconnected; charging an energy storage system; and restoring the compressors and/or turbines toward their operating lines when surge or choking limits are approached. | 01-05-2012 |
20120006035 | TURBINE RIM CUTTER FOR AIR TURBINE STARTER - An air turbine starter includes an air turbine starter rotor rotatably located at a central axis. The rotor includes a plurality of aerodynamic surfaces extending from a platform. At least one cutting element is located in the air turbine starter such that travel of the rotor along the central axis during operation of the air turbine starter results in removal of the platform and aerodynamic surfaces from the rotor via contact between the at least one cutting element and the rotor. | 01-12-2012 |
20120017602 | SYSTEMS AND METHODS FOR CONTROLLING THE STARTUP OF A GAS TURBINE - Systems and methods for controlling the startup of a gas turbine are described. A gas discharge component may be configured to discharge gas from a compressor component associated with the gas turbine. A fuel control component may be configured to control a fuel flow provided to a combustor component associated with the gas turbine. A drive component may be configured to supply a rotational force to a shaft associated with the gas turbine. At least one control device may be configured to (i) direct the gas discharge component to discharge gas from the compressor component, (ii) direct the fuel control component to adjust the fuel flow, and (iii) direct the drive component to rotate the shaft. | 01-26-2012 |
20120023966 | POWER PLANT START-UP METHOD - Ambient air is compressed into a compressed ambient gas flow and delivered to a turbine combustor. At least one of an exhaust port, a bypass conduit, or an extraction conduit is opened to vent the power plant. A turbine shaft is rotated at an ignition speed and a fuel stream is delivered to the turbine combustor for mixing with the compressed ambient gas flow to form a combustible mixture. The combustible mixture is burned and forms a recirculated gas flow that drives the turbine. The recirculated gas flow is recirculated using the recirculation loop. The turbine is operated at a target operating speed and then reaches substantially stoichiometric combustion. At least a portion of the recirculated gas flow is extracted using an extraction conduit that is fluidly connected to the turbine compressor. | 02-02-2012 |
20120031104 | TURBINE ENGINE - A turbine engine is disclosed herein. The turbine engine includes a starter/generator operable to deliver rotational power in a first mode of operation and to generate electrical power in a second mode of operation. The turbine engine also includes an accessory gear box mechanically coupled to the starter/generator. The turbine engine also includes a shaft mechanically coupled to the accessory gear box such that the accessory gear box is operably disposed between the shaft and the starter/generator. The turbine engine also includes a clutch operably disposed between the accessory gear box and the starter generator. The clutch is operable to slip in and out of full engagement in response to a first predetermined level of torque between the starter/generator and the accessory gear box. | 02-09-2012 |
20120042658 | Fuel supply system for gas turbine combustor and fuel supply method for gas turbine combustor - A consumption amount of high-calorific gas such as coke oven gas (COG) during operation of a gas turbine is reduced, halt of the gas turbine due to clogging of a pilot system, a malfunction of a compressor which compresses high-calorific gas is prevented, and reliability of the gas turbine is improved. When operation of the gas turbine ( | 02-23-2012 |
20120144839 | METHOD FOR STARTING A COMBINED CYCLE POWER PLANT - A method for starting a combined cycle power plant ( | 06-14-2012 |
20120159960 | TURBOMACHINE DRIVE ARRANGEMENT - An example arrangement for driving a turbomachine includes an input shaft that is configured to rotate a rotor of the turbomachine through a hydraulic log and gear differential rotatable coupled to the input shaft. A motor-generator is rotatably coupled to the differential. The motor-generator has a motor mode of operation and a generator mode of operation. The motor-generator is configured to drive the input shaft through the hydraulic log and differential when the motor-generator is in the motor mode of operation. The input shaft is configured to drive the motor-generator through the hydraulic log and differential when the motor-generator is in the generator mode of operation. | 06-28-2012 |
20120167584 | CONTROLLING BLADE TIP CLEARANCES IN A TURBINE ENGINE - A turbine engine including a controller controlling clearance between tips of moving blades of a high-pressure turbine and an outer casing surrounding the blades, by cooling the outer casing by the impact of air taken from a high-pressure compressor stage of the engine, and by electric heating of top and bottom portions of the outer casing. | 07-05-2012 |
20120174594 | TURBOMACHINE FUEL DELIVERY METHOD AND ASSEMBLY - An example method of fuel delivery to a turbomachine includes reaching a light-off speed of a turbomachine and delivering fuel to a combustor of the turbomachine at a first rate. The method also increases the rate of the delivery. The combustor achieves light-off at a fuel flow rate on or in-between the first rate and a second rate that is greater than the first rate. An example turbomachine fuel delivery assembly includes a fuel delivery component and a controller configured to adjust the fuel pump to increase a rate of fuel delivery from a fuel supply to a combustor of a turbomachine. | 07-12-2012 |
20120312025 | METHOD AND SYSTEMS FOR ADAPTIVE IGNITION ENERGY - A method and systems for an engine igniter excitation system includes an energy storage device, a first adaptive comparator configured to control the storage of an amount of energy in the energy storage device wherein the amount of energy is determined using at least one of an environmental parameter of the engine and a process parameter of the engine. The system also includes a second adaptive comparator communicatively coupled to the energy storage device wherein the second adaptive comparator is configured to control a rate of energy delivery to the energy storage device using at least one of an environmental parameter of the engine and a process parameter of the engine. The system also includes an igniter configured to generate a spark based on the amount of stored energy and the rate of energy delivery. | 12-13-2012 |
20120324905 | APU FUEL SYSTEM AND METHOD - A control disclosed herein for providing fuel to an auxiliary power unit (“APU”) includes a constant speed electrical motor, a first pump driven by the motor; and, a second pump driven by the motor wherein the electric motor, the first pump and the second pump provide fuel at sufficient pressure/flow capacity to run the APU. | 12-27-2012 |
20130000317 | MECHANISM FOR TURBINE ENGINE START FROM LOW SPOOL - A gas turbine engine includes a high spool, a low spool mechanically connected to a fan, a gear system, an actuator, and a starter. The gear system is actuable to engage and disengage the low spool to and from the high spool. The actuator is connected to the gear system for selectively engaging and disengaging the gear system. The starter is connected to the low spool and can drive rotation of the high spool through the low spool when the gear system is engaged. | 01-03-2013 |
20130008173 | POWER GENERATION ASSEMBLY AND METHOD - A method of starting a gas turbine cycle including a gas turbine and a heat recovery steam generator, the method including: heating water in a steam cycle with a base load heat source; powering one or more steam turbines with steam from said steam cycle; and diverting a portion of the steam from the steam cycle to the gas turbine cycle. Also disclosed is a power generation assembly connectable to a base load heat source arranged to heat water in a steam cycle and power a steam turbine, the power generation assembly including: a gas turbine cycle including a gas turbine and a heat recovery steam generator; and diverting apparatus configured to selectively divert a portion of steam from the steam cycle to the gas turbine cycle on start up of the gas turbine. | 01-10-2013 |
20130031912 | GAS TURBINE START ARCHITECTURE - A gas turbine starting architecture is used to start a gas turbine engine having at least a first spool. The architecture includes an electric power distribution bus, a motor, a compressor, a pneumatic distribution circuit, an air turbine starter, and a first tower shaft. The motor converts electric power provided by the electric power distribution bus to mechanical power. In turn, the mechanical power provided by the motor is converted to pneumatic power by the compressor for provision to a pneumatic distribution circuit. The air turbine starter converts pneumatic power from the pneumatic distribution circuit to mechanical power is provided via the first tower shaft to the at least one spool on the gas turbine engine. | 02-07-2013 |
20130042625 | MICROMIXER HEAT SHIELD - A combustor includes a combustor wall defining a combustion zone and a fuel nozzle. The fuel nozzle includes a forward face, an aft face downstream from the forward face and adjacent to the combustion zone, a plurality of mixing tubes extending between the forward face and the aft face, an outer sleeve positioned radially outward of the plurality of mixing tubes, a heat shield positioned radially inward of the outer sleeve, and a baffle plate between the forward face and the aft face. At least one of the plurality of mixing tubes includes a sidewall that includes an injection opening defined therethrough. The baffle plate is oriented to channel fuel between the plurality of mixing tubes and between the baffle plate and the aft face prior to the fuel being channeled through the injection opening. | 02-21-2013 |
20130086919 | STARTING OF AIRCRAFT ENGINE - A multi-engine system | 04-11-2013 |
20130111919 | GAS TURBINE ENGINE WITH STRUCTURE FOR DIRECTING COMPRESSED AIR ON A BLADE RING - The present invention comprises a gas turbine engine and a process for operating a gas turbine engine. A fluid structure receives compressed air from a compressor and extends toward a stationary blade ring in a turbine to discharge the compressed air directly against a surface of the blade ring such that the compressed air impinges on the blade ring surface. The compressed air then passes through at least one opening in the stationary blade ring and into cooling passages of a corresponding row of vanes. | 05-09-2013 |
20130167550 | METHOD FOR MEETING A PURGE FLOW REQUIREMENT FOR A POWER PLANT AND A POWER PLANT HAVING A PURGE CONTROL SYSTEM - A method of delivering a purge flow through a gas turbomachine includes generating a purge flow, guiding the purge flow through at least one of a combustor assembly and a turbine portion of the gas turbomachine, determining a cumulative purge volume passing through the one of the combustor assembly and the turbine portion of the gas turbomachine to determine a predetermined purge volume, and discontinuing the purge flow once the predetermined purge volume has passed through the one of the combustor assembly and the turbine portion of the gas turbomachine. | 07-04-2013 |
20130199201 | MAIN ENGINE START BY MEANS OF AN AIRCRAFT AIR CONDITIONING SYSTEM - An air conditioning system in an aircraft is provided. The system comprises at least one air cycle air-conditioning pack with a compressor comprising a bleed air outlet and with a compressed-air line connected to the bleed air connection, which compressed-air line is connectable to a starter turbine for a main engine. With the use of air from a compressor of an air conditioning pack it is not necessary to switch off the air conditioning pack; bleed air removal from the auxiliary power units becomes obsolete; and, since there is no unnecessary discharge of compressed air from a bleed air system, noise pollution on the ground is reduced. | 08-08-2013 |
20130219911 | COMBUSTION SYSTEM FOR A GAS TURBINE ENGINE AND METHOD FOR DIRECTING FUEL FLOW WITHIN THE SAME - Disclosed is a combustion system for a gas turbine engine, which includes a combustor and a plurality of fuel injector nozzles within the combustor. The plurality of fuel injector nozzles include at least one start nozzle and at least of run nozzle, wherein each of the plurality of fuel injector nozzles is a single-circuit fuel injector nozzle. The combustion system further includes a fuel flow directing system to selectively deliver fuel flow to each of the at least one start nozzle and at least one run nozzle, wherein the fuel flow directing system is configured to deliver preferential flow of fuel to the at least one start nozzle during an engine start-up procedure and is further configured to deliver an equalized flow both of the at least one start nozzle and the at least one run nozzle as a total engine fuel flow is near or above an idle setting. | 08-29-2013 |
20130227959 | METHOD OF ACCELERATION CONTROL DURING APU STARTING - A method for controlling fuel flow to a gas turbine engine during starting includes monitoring acceleration of the gas turbine engine to determine actual acceleration value, and calculating a fuel flow rate for a setpoint acceleration using the actual acceleration value as a factor. The method further includes commanding the calculated fuel flow for the setpoint acceleration to the gas turbine engine. | 09-05-2013 |
20130239580 | HIGH ALTITUDE START OF A GAS TURBINE ENGINE USING FUEL PULSING AND STARTER TOGGLING - A system for starting a gas turbine engine includes an engine controller and a fuel controller. The engine controller varies the engine speed between a minimum start speed and a maximum start speed until light-off of the engine occurs. The fuel controller operates a fuel command to vary fuel provided to a combustion chamber of the engine until light-off of the engine occurs. | 09-19-2013 |
20130247579 | METHOD OF STARTUP CONTROL FOR A GAS TURBINE SYSTEM OPERATING IN A FIRED DECELERATION SHUTDOWN PROCESS MODE - A method of startup control for a gas turbine system that is operating in a fired deceleration shutdown process mode is provided. The method includes determining whether the combustor flame is in a lit state. Also included is increasing a fuel flow to the gas turbine system if the combustor is determined to be in the lit state. Further included is initiating a starter system to the gas turbine system. | 09-26-2013 |
20130291551 | METHOD FOR STARTING A TURBOMACHINE - A method of starting a turbine engine, including a re-try performed if a main injector has not ignited when a shaft has reached a first predetermined speed value, the re-try including: a stopping during which a starter and the ignitor device are stopped; a second ignition during which fuel is injected into the combustion chamber, the ignitor device being actuated, the second ignition being performed when a speed of rotation of the shaft reaches a second predetermined speed value; and a second starting during which the starter is actuated once more to drive the shaft in rotation. | 11-07-2013 |
20140000277 | METHOD TO START UP AND MANAGE A COMBINED CYCLE THERMAL PLANT FOR ENERGY PRODUCTION AND RELATIVE PLANT | 01-02-2014 |
20140020401 | METHOD FOR CONDITIONING A POWER SUPPLY FOR STARTING A JET ENGINE - Method for conditioning a power supply for starting a jet engine having an electrical starting system with an auxiliary power unit in parallel with a DC power supply. | 01-23-2014 |
20140047847 | METHOD TO START UP A COMBINED CYCLE THERMAL PLANT FOR ENERGY PRODUCTION FROM AN OFF-STATE TO AN OPERATIONAL STATE - To start a combined cycle thermal plant for energy-production from an off-state to an operational state, once the minimum warm-up time of the steam turbine (ST) having been set, as well as the pressure of the warm-up steam, it is necessary to determine the steam optimum temperature to avoid stressing or straining the mechanical parts of the turbine itself. | 02-20-2014 |
20140060072 | METHOD OF STARTING A GAS TURBINE SYSTEM - A method of starting a gas turbine system is provided. The method includes approximating a temperature of at least one turbine system component. Also included is selectively determining a flow rate for a fuel to be delivered to a combustor for combustion therein, wherein the flow rate is dependent upon the temperature of the at least one turbine system component. Further included is delivering the fuel to the combustor at the flow rate selectively determined. | 03-06-2014 |
20140096533 | Bearing chamber venting system for an aircraft engine and method for providing a required pressure ratio at bearing chamber seals of an air-sealed bearing chamber - A bearing chamber venting system for an aircraft engine includes at least one bearing chamber air-sealed by sealing air via bearing chamber seals, a vent line connected to the bearing chamber, via which an oil/air mixture present in the bearing chamber is vented out, and an oil separator connected to the vent line. An oil return line is connected to the oil separator via which oil separated from the mixture is discharged. An air outlet line is connected to the oil separator, via which cleaned air is passed to the environment. An air ejector is arranged in the air outlet line to eject gas supplied to the air ejector into the air outlet line at a speed which is greater than the speed of the air flowing in the air outlet line and passed to the environment out of the oil separator. | 04-10-2014 |
20140123673 | A METHOD OF STARTING A TURBOMACHINE WHILE REDUCING THERMAL UNBALANCE - A method of starting a turbomachine, performed by an electronic unit, the turbomachine including a gas turbine engine including at least one rotor and a starter to drive the rotor in rotation, the method including: receiving an order to start the turbomachine, and executing in response to receiving the order to start: a primary acceleration during which the starter is operated to increase speed of rotation of the rotor; a thermal homogenization during which the starter is operated to keep the speed of rotation of the rotor constant or to decrease it until a predetermined condition is satisfied; after the predetermined condition is true, a secondary acceleration in which the starter is operated to increase the speed of rotation of the rotor; and an ignition in which ignition of the engine is ordered. | 05-08-2014 |
20140130508 | Powerplant and related control system and method - A hydrogen fueled powerplant including an internal combustion engine that drives a motor-generator, and has a two-stage turbocharger, for an aircraft. A control system controls the operation of the motor-generator to maintain the engine at a speed selected based on controlling the engine equivalence ratio. The control system controls an afterburner, an intercooler and an aftercooler to maximize powerplant efficiency. The afterburner also adds power to the turbochargers during high-altitude restarts. The turbochargers also include motor-generators that extract excess power from the exhaust. | 05-15-2014 |
20140150446 | BATTERY CURRENT REGULATION - Embodiments are directed to an engine of an aircraft, a starter generator configured to receive power to cause the engine to start and to provide electrical power to at least one load, and a battery system comprising: a battery, and at least one of a controller and a regulator configured to limit an in-rush current to the battery following the starting of the engine. | 06-05-2014 |
20140150447 | LOAD RAMP AND START-UP SYSTEM FOR COMBINED CYCLE POWER PLANT AND METHOD OF OPERATION - The disclosure includes a load ramp system for a heat recovery steam generator (HRSG) of a combined cycle power plant and a method of increasing the rate of the load ramp process of a gas turbine system of the combined cycle power plant. In one embodiment, the load ramp system for the HRSG of the combined cycle power plant includes a conduit in fluid communication with a supercharger positioned upstream of a compressor of a gas turbine system in the combined cycle power plant. The conduit of the load ramp system is configured to direct a portion of supercharged air for use in cooling the HRSG during a load ramp process of the gas turbine system in the combined cycle power plant. | 06-05-2014 |
20140165586 | TURBINE START METHOD - A method of starting an engine includes the steps of starting a fuel supply pump, opening a fuel solenoid to allow fuel flow to a combustor to at least partially begin, and beginning to operate a starter motor to drive a shaft associated with the engine. Then an ignitor is excited to spark in the combustor. An engine is also disclosed. | 06-19-2014 |
20140208766 | Waste Heat Recovery Fuel Gas Heater Control Method and Algorithm - A method of operating a fuel heating system is provided. The method includes performing pre-ignition diagnostic checks on a plurality of components of the fuel heating system, wherein at least one inlet damper and at least one outlet damper of an exhaust flow circuit are each in a closed position. The method also includes purging the fuel heating system of unburned hydrocarbons. The method further includes operating the fuel heating system in a normal operating condition. The method yet further includes operating the fuel heating system in a cool down condition, wherein the at least one inlet damper is in the closed position. | 07-31-2014 |
20140238038 | GAS TURBINE VARIABLE FOCUS LASER IGNITION - A laser ignition system for a gas turbine engine includes a combustion chamber. The system comprises a laser source for generating a continuous laser beam during an ignition process of the combustion chamber; and a dynamic laser focus apparatus positioned outside of the combustion chamber and focusing the laser beam into a continuously varying focal point to generate a laser kernel moving within a spray of air/fuel mixture injected into the combustion chamber. | 08-28-2014 |
20140238039 | SYSTEM AND METHOD FOR OPERATING A POWER PLANT - A system including a fuel-supply system including, an auxiliary-fuel-gas compressor configured to compress a fuel for use by a gas-turbine system, an expander configured to generate power by expanding an oxidant from the gas-turbine system, and a motor/generator configured to function in a motor mode and in a generator mode, wherein the motor/generator drives fuel compression with the auxiliary fuel-gas compressor in the motor mode, and the motor/generator generates power in the generator mode as the expander uses oxidant from the gas-turbine system to drive the motor/generator | 08-28-2014 |
20140238040 | COMBINED CYCLE POWER PLANT - A combined cycle engine is used to provide power to a vehicle. In one form the combined cycle engine includes two engines coupled through a gearbox. The engines can include a gas turbine engine, reciprocating engine, and a rotary engine. In one embodiment the combined cycle engine includes a gas turbine engine coupled to a gearbox along with either a reciprocating or rotary engine also coupled to the gearbox. One or more clutches can be provided to selectively couple the gas turbine engine and the reciprocating or rotary engine to the vehicle through the gearbox. In one embodiment the diesel engine can provide power to the vehicle during an idle condition and then also provide power to the gas turbine engine to assist the starting of the gas turbine engine. | 08-28-2014 |
20140250909 | Series Battery Start Controller - A series battery start controller for starting an aircraft turbine engine and method thereof is provided, wherein the battery series start controller connects two batteries in series when an aircraft engine starter is engaged to provide a higher voltage to start the aircraft engine and to provide adequate operational voltage to aircraft engine instruments and other aircraft electrical systems, and wherein the battery series start controller reconnects the batteries in parallel when the electrical load drawn by the starting aircraft engine decreases and the supplied voltage to the aircraft rises to a predetermined threshold. | 09-11-2014 |
20140250910 | THERMAL STRESS REDUCTION IN AIRCRAFT MOTOR CONTROLLERS - A thermal stress reduction method includes ramping an electric power generator to start an aircraft engine, for a time period associated with the aircraft engine start sequence toggling a three-level inverter switch array to a three-level pulse width modulation mode, determining if a first time interval in the three-level pulse width modulation mode exceeded a predetermined three-level pulse width modulation mode interval, in response to the first time interval exceeding the three-level pulse width modulation mode interval, toggling the three-level inverter switch array to a two-level pulse width modulation mode, determining if a second time interval in the two-level pulse width modulation mode exceeded a predetermined two-level pulse width modulation mode interval and in response to the second time interval exceeding the two-level pulse width modulation mode interval, toggling the three-level inverter switch array to the three-level pulse width modulation mode. | 09-11-2014 |
20140260306 | ENGINE STARTING SYSTEM USING STORED ENERGY - There is described a method for and system for starting at least one engine from a twin engine installation. The starting system comprises a first engine arrangement comprising a first electric machine having a single rotor dual stator configuration, a first dual channel power control unit coupled to the first electric machine, and a first dual channel full authority digital engine control (FADEC) coupled to the first dual channel power control unit; a second engine arrangement comprising a second electric machine having a single rotor dual stator configuration, a second dual channel power control unit coupled to the second electric machine, and a second dual channel full authority digital engine control (FADEC) coupled to the second dual channel power control unit; an energy storage unit coupled to the first engine arrangement and the second engine arrangement and having at least a first super-capacitor and a second super-capacitor; and a DC to DC converter configured to receive a first voltage level from a power source, increase the first voltage level to a second voltage level, and charge the first super-capacitor and the second super-capacitor to the second voltage level. | 09-18-2014 |
20140298820 | GAS TURBINE ENGINE AND METHOD FOR STARTING SAME - A starting method for a gas turbine engine includes a primary warming step of warming up the gas turbine engine while a constant primary warm-up rotation speed is maintained by an inverter motor and a secondary warming step of warming up the gas turbine engine while a constant secondary warm-up rotation speed is maintained by further increasing the speed of the inverter motor. The primary warming step terminates when an electric power required by the inverter motor attains a predetermined preset electric power value. The preset electric power value is so chosen as to decrease as the intake air temperature is low. | 10-09-2014 |
20140298821 | GAS TURBINE ENGINE PROVIDED WITH HEAT EXCHANGER, AND METHOD FOR STARTING SAME - A method of starting a gas turbine engine includes a primary warming step of warming a heat exchanger ( | 10-09-2014 |
20140305132 | METHOD FOR STARTING UP A GAS AND STEAM TURBINE SYSTEM - A method for starting a gas and steam turbine system which includes a gas turbine system which includes at least one gas turbine, in addition to at least one steam turbine system which includes at least one steam turbine and at least one steam system is provided. Heat produced by the working fluid and which is released in the gas turbine is guided to the steam system in order to produce steam which drives the steam turbine. During starting, the gas turbine is started prior to the steam turbine and the steam turbine is started in the presence of the first steam in the system and is impinged upon by said steam. | 10-16-2014 |
20140373552 | METHOD AND SYSTEM FOR STARTING UP AN AIRCRAFT TURBOMACHINE BY REAL-TIME REGULATION OF AIR FLOW - The start-up system comprises a control loop, which regulates in real time the opening of a valve of an air feed of a start-up turbine based on the current measured speed of rotation of a rotor of the turbomachine and a predetermined speed value, said start-up turbine being capable of turning the rotor of the turbomachine for the purpose of the start-up. | 12-25-2014 |
20140373553 | METHOD AND SYSTEM FOR STARTING UP AN AIRCRAFT TURBOMACHINE - A start-up system including a control system controlling a partial opening of an air intake valve of a start-up turbine during a first phase of the start-up. The start-up turbine is capable of turning a rotor of the turbomachine for the purpose of the start-up, so as to prevent the rotor from encountering critical frequencies of the turbomachine | 12-25-2014 |
20150033753 | RELIGHTING A TURBOFAN ENGINE - The method and apparatus for in-flight relighting of a turbofan engine involve in one aspect selectively controlling an accessory drag load on one or more windmilling rotors to permit control of the windmill speed to an optimum value for relight conditions. | 02-05-2015 |
20150033754 | RELIGHTING A TURBOFAN ENGINE - The method and apparatus for in-flight relighting of a turbofan engine involve in one aspect selectively controlling an accessory drag load on one or more windmilling rotors to permit control of the windmill speed to an optimum value for relight conditions. | 02-05-2015 |
20150059353 | Gas Turbine Combustion System - The present invention provides a gas turbine combustion system capable of minimizing unburned content of a gas fuel under all load conditions from partial load to rated load. | 03-05-2015 |
20150308347 | METHOD TO CONTROL ELECTRIC STARTER GENERATOR FOR GAS TURBINE ENGINES - A gas turbine engine starting system including an electric start generator (ESG) free of temperature sensors and configured to provide torque to a gas turbine engine. A fuel metering module is configured to provide a quantity of fuel to the gas turbine engine, and an electronic control system (ECS). The ESG includes a plurality of subcomponents. The ECS is configured to predict a future temperature of the ESG, predict that at an ongoing start or an uninitiated start will be unsuccessful, and provide the prediction that at an ongoing start or an uninitiated start will be unsuccessful to an operator. The prediction of the future temperature of the ESG is based on a plurality of historical ESG thermal trending information and an input ambient temperature. The prediction that at an ongoing start or an uninitiated start will be unsuccessful is based on the future temperature of the ESG. | 10-29-2015 |
20150315973 | SYSTEM FOR DETECTING A FLASHBACK AND MITIGATING DAMAGE FROM THE FLASHBACK TO A COMBUSTION SYSTEM - A system is provided for detecting and mitigating damage from flashback in a combustion system. The combustion system includes an injector and a combustor. The system includes a supply line coupled to the combustor. The supply line defines an end configured to face with the combustor. The end is provided with a fusible component that is configured to melt in the event of a flashback and release an extinguishing agent into the combustor. | 11-05-2015 |
20150377140 | METHOD AND SYSTEM FOR STARTUP OF GAS TURBINE SYSTEM DRIVE TRAINS WITH EXHAUST GAS RECIRCULATION - In one embodiment, a system includes a drive train starter system. The drive train starter system includes a generator mechanically coupled to a drive train of a gas turbine system and an exciter system electrically coupled to the generator and configured to provide a magnetic field. The drive train starter system additionally includes a load commutated inverter (LCI) electrically coupled to the generator and configured to provide electrical power to the generator and a controller communicatively coupled to the generator, the exciter system, and the LCI. The controller is configured to start up the drive train via the LCI and the generator up to less than a drive train operating speed, wherein the generator is converting electricity into mechanical motion; drive the drive train via a gas turbine up to the drive train operating speed; and to drive the drive train via the generator at the drive train operating speed. | 12-31-2015 |
20150377142 | LOW SPOOL STARTER SYSTEM FOR GAS TURBINE ENGINE - A gas turbine engine comprises a first compressor, a second compressor, a starter generator and a clutch. The starter generator is coupled to the first compressor. The clutch selectively couples the second compressor and the first compressor. The clutch is disposed between a first shaft and a second shaft to engage the first shaft with the second shaft at rest. A flyweight system is engaged with the clutch mechanism to permit freewheeling of the first shaft relative to the second shaft when subject to rotational motion beyond a threshold speed. A method for starting a gas turbine engine comprises engaging a low pressure compressor with a high pressure compressor utilizing a clutch, rotating the low pressure compressor and the high pressure compressor utilizing a starter generator coupled to the low pressure compressor, igniting the gas turbine engine, and disengaging the clutch at an operational speed of the gas turbine engine. | 12-31-2015 |
20160023773 | HYBRID ELECTRIC PULSED-POWER PROPULSION SYSTEM FOR AIRCRAFT - A propulsion system has a gas turbine engine optimized to operate at a single operating condition corresponding to a maximum continuous power output of the gas turbine engine, an electric motor system, an electric machine rotatably attached to the gas turbine engine and electrically connected to the electric motor system, and an energy storage system having bi-directional electrical connections with the electric motor system and the electric machine. A method of operating the propulsion system including operating the gas turbine engine for a first period of time to provide electric power to the electric motor system and to recharge the energy storage system, turning off the gas turbine for a second period of time, and discharging the energy storage system to operate the electric motor system during the second period of time. | 01-28-2016 |
20160025011 | SERIES BATTERY START CONTROLLER - A series battery start controller for starting an aircraft turbine engine and method thereof is provided, wherein the battery series start controller connects two batteries in series when an aircraft engine starter is engaged to provide a higher voltage to start the aircraft engine and to provide adequate operational voltage to aircraft engine instruments and other aircraft electrical systems, and wherein the battery series start controller reconnects the batteries in parallel when the electrical load drawn by the starting aircraft engine decreases and the supplied voltage to the aircraft rises to a predetermined threshold. | 01-28-2016 |
20160053690 | In Flight Restart System and Method for Free Turbine Engine - There is described a method and system for in-flight start of an engine. The method comprises rotating a propeller; generating electrical power at an electric generator embedded inside a propeller hub from rotation of the propeller; transmitting the electrical power from the electric generator to an engine starter mounted on a core of the engine via an electric power link; and driving the engine with the engine starter to a sufficient speed while providing fuel to a combustor to light the engine to achieve self-sustaining operation of the engine. | 02-25-2016 |
20160123232 | METHOD AND SYSTEM FOR TURBINE ENGINE TEMPERATURE REGULATION - A method of starting a turbine engine using turbine temperature gradient regulation and a turbine engine temperature management system are provided. The system includes a temperature sensor, a modulating fuel flow valve, and a temperature controller. The temperature controller is configured to limit a rate of change of the fuel flow to the turbine engine to less than a predetermined maximum rate of change of the fuel flow that will reduce a rate of change of the temperature and maintain a positive rate of change of a rotational speed of the turbine engine and limit a rate of the fuel flow to greater than a predetermined minimum rate of the fuel flow that maintains a positive rate of change of temperature and a positive rate of change of the rotational speed of the turbine engine. | 05-05-2016 |
20160138475 | METHOD OF STARTING A GAS TURBINE ENGINE - A gas turbine engine comprises a compressor driven by a shaft, and a reference starting schedule, the compressor having a reference stability boundary, with the reference starting schedule defining a reference working line. A method of starting the gas turbine engine is described in which the method comprises the steps of:
| 05-19-2016 |
20160146110 | OPTIMIZATION OF COLD STARTS IN THERMAL POWER STATIONS, IN PARTICULAR IN STEAM-ELECTRIC POWER PLANTS OR IN COMBINED CYCLE POWER PLANTS (CCPPS) - A thermal power plant, in particular to a steam-electric power plant or a combined cycle power plant (CCPP), and a method for operating a thermal power plant is adapted to accelerate, or to technically and/or economically optimize the start-up of the thermal power plant, in particular to accelerate/optimize a cold-start phase of the thermal power station. The thermal power plant has an auxiliary energy store integrated into the power plant. The store, during the start-up of the thermal power plant, delivers energy for heating/pre-heating components and/or media of the thermal power plant, or supplies an electrical power distribution network. | 05-26-2016 |
20170233089 | SYSTEM AND METHOD FOR STARTING THE ENGINES OF A TWIN-ENGINE AIRCRAFT | 08-17-2017 |
20170234230 | BOWED ROTOR START USING DIRECT TEMPERATURE MEASUREMENT | 08-17-2017 |
20170234236 | BOWED ROTOR START USING A VARIABLE POSITION STARTER VALVE | 08-17-2017 |
20170234237 | GAS TURBINE ENGINE MOTORING VARIABLE FREQUENCY GENERATOR SYSTEM FOR BOWED ROTOR ENGINE STARTS | 08-17-2017 |
20170234238 | GAS TURBINE ENGINE BOWED ROTOR AVOIDANCE SYSTEM | 08-17-2017 |
20180022463 | PRE-START MOTORING SYNCHRONIZATION FOR MULTIPLE ENGINES | 01-25-2018 |
20180022465 | ALTERNATING STARTER USE DURING MULTI-ENGINE MOTORING | 01-25-2018 |
20180023413 | MULTI-ENGINE COORDINATION DURING GAS TURBINE ENGINE MOTORING | 01-25-2018 |
20180023479 | AIR SUPPLY CONTROL DURING MOTORING OF A GAS TURBINE ENGINE | 01-25-2018 |