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Power Plants > Combustion Products Used As Motive Fluid > Process ProcessProcess patent applications listed are from June 2005 to current and include Date, Patent Application Number, Patent Title, Patent Abstract summary and are linked to the corresponding patent application page.01/24/08 - 20080016874 - Gas turbine floating collar arrangement A crack-resistant floating collar mounting arrangement is provided comprising a collar mounted between spaced-apart mounting flanges, the flange being fixed to a dome from an outer surface unexposed to the hot combustor temperatures. ... 12/27/07 - 20070295011 - Regenerative turbine blade and vane cooling for a tip turbine engine A fan-turbine rotor assembly (24) includes a multitude of turbine blades (34) which each define a turbine blade passage which bleed air from a diffuser section (74) to provide for regenerative cooling. Regenerative cooling airflow is communicated from the radial core airflow passage (80) through the diffuser passages (144), through ... 12/06/07 - 20070277529 - Method and system for heat recovery from dirty gaseous fuel in gasification power plants A system and method for recovering heat from dirty gaseous fuel (syngas), wherein the pressure of clean fuel gas is elevated to a pressure higher than that of the dirty syngas and then the pressurized clean fuel gas is fed to a heat recovery unit for heat exchange with the ... 11/15/07 - 20070261409 - Gas turbine floating collar A method of providing a floating collar for a gas turbine engine combustor is provided, and comprises providing an annular sheet metal blank and bending the blank to provide the floating collar with an axial extending annular collar portion, an annular flange portion extending radially from the collar portion and ... 11/15/07 - 20070261408 - Gas turbine having exhaust recirculation A gas turbine adapted to operate in a highly diluted mode comprises a compressor 3 adapted to compress oxidant 5; a combustion chamber 3 adapted to accept the compressed oxidant 7 and provide an exit means for flue gas 9; a turbine 4; and a flue gas re-circulation means 12, ... 11/08/07 - 20070256423 - Method and arrangement for expanding a primary and secondary flame in a combustor Disclosed is an arrangement for expanding an annular fluid flow and a center fluid flow, comprising a combustor including a venturi and a centerbody, the centerbody including an upstream end and a downstream end, and a venturi throat defined by the venturi and disposed upstream of 0.19 inches downstream of ... 11/08/07 - 20070256422 - Production enhancements on integrated gasification combined cycle power plants A method of using an apparatus for producing electric power or mechanical drive in which fuel gas produced in a gasifier using air as an oxidant is supplied to the gasifier by extraction from the exit of the air compressor of a gas turbine. ... 11/08/07 - 20070256421 - Gas turbine engine oil system operation A method of operating a gas turbine engine having at least one electric machine associated therewith, the engine having an oil system communicating with an electric oil pump, at least one bearing cavity of the engine and a coolant passage of the electric machine, the method comprising the step of ... 11/08/07 - 20070256420 - Methods and apparatus for assembling a low noise ejector motive nozzle A method of assembling an ejector is provided, wherein the method includes providing a motive nozzle tip having a centerline axis and including a nozzle tip edge having at least one protrusion extending through a plane substantially normal to the centerline axis. The method also includes coupling the motive nozzle ... 10/25/07 - 20070245744 - Fuel system of gas turbine engines A method for purging fuel from a fuel system of a gas turbine engine on shutdown of the engine comprises, in one aspect, terminating a fuel supply to the fuel system and using the residual compressed air to create a reversed pressure differential in the fuel system relative to a ... 10/18/07 - 20070240424 - Gas turbine engine having bypass ducts A gas turbine engine having a bypass flow in which the bypass flow includes a central bypass passage formed by a rotary shaft of the engine, and an outer bypass passage located between the casing and the combustor, where the hot gas stream from the turbine is located between the ... 10/11/07 - 20070234732 - Gas turbine engine fuel control system having a transfer valve and a shutoff valve and a common controller therefor A fuel control system for a gas turbine engine includes a metering valve for metering a flow of fuel, a throttling valve for maintaining a pressure drop across the metering valve, the throttling valve being shiftable between an open state and a shutoff state blocking an outlet of the metering ... 10/11/07 - 20070234731 - System and method for providing air to a compressor of an aircraft auxiliary gas turbine engine A system for providing air to a compressor of an auxiliary gas turbine engine of an aircraft. A system turbine has an inlet adapted to receive compressed air from the aircraft. A system compressor is mechanically coupled to the system turbine and has an inlet adapted to receive atmospheric air. ... 10/11/07 - 20070234730 - Method and apparatus for monitoring combustion instability and other performance deviations in turbine engines and like combustion systems The sensor arrangement, performance-monitored machine system, and method, utilize radiance of exhaust streams to indicate performance deviation, due to combustion instability or machine malfunction, in propulsion gas turbine engines, augmentors used on such engines, stationary power generating gas turbine engines, and other air-breathing combustion-based turbine machines and systems. Sensor operation ... 10/11/07 - 20070234729 - Methods and apparatus for cooling gas turbine engine components A method for cooling a turbine assembly component of a gas turbine engine in a combined-cycle power generation system. The method includes channeling cooling fluid that is extracted from a source external to the gas turbine engine to the turbine assembly component, and cooling the turbine assembly component using the ... 10/04/07 - 20070227155 - Gas turbine plant and method of operation In a method for operating a gas turbine plant (10) with a compressor (11) for the compression of combustion air sucked in from the surroundings, with a combustion chamber (15) for generating hot gas by the combustion of a fuel with compressed combustion air, and with a turbine (12), in ... 10/04/07 - 20070227154 - System and method for producing injection-quality steam for combustion turbine power augmentation The present invention is a combustion turbine assembly connected to a steam generator which utilizes deaerated potable water. The steam formed by the steam generator may be combined with air and injected into the combustor of the combustion turbine assembly to increase the mass flow of gas through the turbine ... 10/04/07 - 20070227153 - Flow control redistribution to mitigate high cycle fatigue The present invention provides a method operable to improve pressure recovery and/or distortion within engine inlet. This method involves providing a first fluid flow to primary jet vortex generator(s) operable to inject fluid at a first injection rate into a boundary layer of a primary fluid flow within the inlet. ... 09/27/07 - 20070220896 - Systems and methods of reducing nox emissions in gas turbine systems and internal combustion engines A gas turbine systems of reducing NOx emissions and enhancing operability comprises a compressor; a combustor disposed downstream of and in fluid communication with the compressor; a turbine assembly disposed down stream of and in fluid communication with the combustor; an oxygen-enriched gas source disposed in selective fluid communication with ... 09/27/07 - 20070220895 - Methods and apparatus for housing gas turbine engines A method for housing a gas turbine engine including an inlet portion, an engine portion, and an exhaust portion. The method includes containing at least a portion of the engine portion of the gas turbine engine within a first module, containing at least a portion of one of the inlet ... 09/20/07 - 20070214797 - Combustion dynamics monitoring A method for monitoring combustion dynamics of a can annular combustor (12) of a gas turbine engine includes monitoring respective dynamic operating conditions of cans (16) of the can annular combustor with respective dynamic operating condition sensors (20) associated with each of the cans. The method also includes grouping the ... 09/20/07 - 20070214796 - Monitoring health of a combustion dynamics sensing system A method and system (14) for monitoring a health of a combustion dynamics sensing system (10) includes monitoring respective dynamic conditions of at least two combustor cans (16) of a can annular combustor (12) of a gas turbine engine with respective dynamic condition sensors (20) associated with each of the ... 09/20/07 - 20070214795 - Continuous real time egt margin control A method and system for maintaining a limiting gas temperature in a gas turbine engine working fluid flowpath by monitoring the gas temperature and adjusting one or more parameters when the gas temperature exceeds a predetermined or a calculated temperature limit during engine operation. The parameters include one or more ... 09/06/07 - 20070204623 - High density combined cycle power plant process A process for increasing the specific output of a combined cycle power plant and providing flexibility in the power plant rating, both without a commensurate increase in the plant heat rate, is disclosed. The present invention demonstrates that the process of upgrading thermal efficiencies of combined cycles can often be ... 09/06/07 - 20070204622 - Internal fuel manifold with turned channel having a variable cross-sectional area A method of manufacturing an internal manifold of a gas turbine engine including machining an annular channel in a ring by a turning process, and varying a position of a tool bit relative to the surface of the ring as a function of a relative circumferential location of the tool ... 08/16/07 - 20070186556 - Methods and apparatus for operating a pulse detonation engine A method for operating a pulse detonation engine, wherein the method includes channeling air flow from a pulse detonation combustor into a flow mixer having an inlet portion, an outlet portion, and a body portion extending therebetween. The method also includes channeling ambient air past the flow mixer and mixing ... 08/09/07 - 20070180830 - System for reducing oil consumption in gas turbine engines A system for reducing oil usage from a sump in a gas turbine engine. Two sources of oil usage, which usage includes leakage and consumption, have been identified: (1) during idle, leakage of oil from an oil sump through seals and (2) during high-power operation, consumption of oil entrained in ... 08/09/07 - 20070180829 - Methods and apparatus for fabricating gas turbine engine combustors A method for fabricating a dome assembly for a gas turbine engine combustor includes forming an annular dome plate including a plurality of substantially circular eyelets circumferentially spaced thereon, coupling a seal plate to the dome plate at each eyelet such that an opening defined in each seal plate is ... 07/26/07 - 20070169485 - System and method for improving the heat rate of a turbine A steam cycle power plant (10) is provided that may include a steam source generating steam (40), a steam turbine (24) receiving the generated steam and discharging an exhaust steam, a condenser (44) receiving the exhaust steam and an atomizer (60) for injecting water into the exhaust steam downstream of ... 07/12/07 - 20070157620 - Method for controlling fuel splits to gas turbine combustor A method for determining a target exhaust temperature for a gas turbine including: determining a target exhaust temperature based on a compressor pressure condition; determining a temperature adjustment to the target exhaust temperature based on at least one parameter of a group of parameters consisting of specific humidity, compressor inlet ... 07/12/07 - 20070157619 - Methods and apparatus for gas turbine fuel control A method for reducing or eliminating oscillations in a gas turbine fuel control system includes utilizing an engine model to regulate a gas supply pressure for a gas turbine, sensing the pressure of gas actually supplied, and applying integral state feedback plus gas supply pressure feedforward combined with integral plus ... 07/05/07 - 20070151251 - Counterflow injection mechanism having coaxial fuel-air passages In accordance with certain embodiments, a system includes a fuel-air injection mechanism having coaxial fuel and air passages leading to fuel and air injection openings. The fuel and air injection openings are configured to reside at an off-axis position of a gas turbine combustor, and the fuel and air injection ... 07/05/07 - 20070151250 - Gas turbine combustor having counterflow injection mechanism In accordance with certain embodiments, a system includes a counterflow injection mechanism. The counterflow injection mechanism includes a fuel-air injection mechanism having fuel and air passages leading to fuel and air injection openings, wherein the fuel and air injection openings are disposed at an off-center position and a generally counterflow ... 06/21/07 - 20070137211 - Multiple turbine system with a single recuperator A turbine system is provided including a plurality of gas turbine engines, each having a compressor section for producing compressed air, a combustor section, and a turbine section yielding hot exhaust gas. A single, common recuperator section is shared by and operatively associated with the plurality of gas turbine engines. ... 06/21/07 - 20070137210 - Cooling apparatus for a gas turbine engine igniter lead A method for cooling an igniter lead is provided. The method includes coupling an assembly to the igniter lead such that a portion of the assembly rotates circumferentially around the igniter lead, and channeling cooling air through the assembly to facilitate cooling the igniter lead. ... 06/21/07 - 20070137209 - Fuel nozzle and manifold assembly connection A fuel supply assembly for a gas turbine engine including a manifold portion with a transfer conduit, a fuel nozzle with an entry conduit and disconnectable means for retaining the transfer and entry conduits in mating engagement with one another. ... 06/14/07 - 20070130953 - Local cooling hole pattern A combustor assembly includes an inner and an outer liner defining a combustion chamber. The inner and outer liner includes a plurality of cooling holes that are spaced a specified distance apart. The cooling holes include a specified inclination angle and circumferential angle. A first group of cooling holes is ... 06/14/07 - 20070130952 - Exhaust heat augmentation in a combined cycle power plant A method and system for augmenting the output of a combined cycle power plant having a base gas turbine (22) driving a generator (36) and a heat recovery steam generator (42) that recovers exhaust heat (30) from the base gas turbine (22) to drive a steam turbine (60). A complementary ... 06/07/07 - 20070125089 - Method of suppressing combustion instabilities using a resonator adopting counter-bored holes A resonator for damping pressure waves or instabilities in a system supported by acoustic energy wherein the resonator adopts the use of counter-bored openings on the downstream side of the resonator within the flow path of the system. The resonator includes a first member and a second member where the ... 06/07/07 - 20070125088 - Method and apparatus for actuating fuel trim valves in a gas turbine The gas turbines of the present invention have multiple combustion chambers, and within each chamber are multiple fuel nozzles. Each nozzle has its own fuel control valve to control the fuel flowing to the nozzles. To minimize the pressure drop through the fuel control valves, multiple manifolds are employed. Each ... 06/07/07 - 20070125087 - Gas turbine engine auxiliary component mount A mount system for an auxiliary component includes two side brackets and a top bracket for rigidly attaching an auxiliary component to an engine casing. Each side bracket defines mount segments, a deformable member and two retainer members between the mount segment. The deformable member plastically deforms during a fan-blade ... 05/10/07 - 20070101723 - Methods and apparatus for a combustion turbine nitrogen purge system A method of operating a fuel system is provided. The method includes removing fuel from at least a portion of the fuel system using a gravity drain process The method also includes channeling nitrogen into at least a portion of the fuel system to facilitate removing air and residual fuel ... 05/10/07 - 20070101722 - Open cooled component for a gas turbine, combustion chamber, and gas turbine In order to specify a component for a gas turbine with which flashback and spontaneous ignition during feeding of fuel into the cooling air can be reduced, it is proposed that the second cavity be formed by supply passages (9, 13) which are provided in the outer wall (20) and ... 05/03/07 - 20070095069 - Power generation systems and method of operating same A method for operating a power generation system including a wind turbine and a turbine assembly. The method includes operating the wind turbine, storing the energy generated by the wind turbine as compressed air, and channeling the compressed air to the turbine assembly when needed. ... 05/03/07 - 20070095068 - Methods and apparatus for operating gas turbine engines A method for operating a gas turbine engine including a compressor, a combustor, and a turbine, coupled together in serial flow arrangement, and a fuel system including a heat exchanger and an economizer. The method includes channeling fuel through the heat exchanger, channeling a working fluid through the the exchanger ... 05/03/07 - 20070095067 - Aerodynamic trip to improve acoustic transmission loss and reduce noise level for gas turbine engine A method and device for decoupling combustor attenuation and pressure fluctuation from turbine attenuation and pressure fluctuation in a gas turbine engine. The engine has: a compressor; a combustor; and a turbine, that generate a flow of hot gas from the combustor to the turbine. An aerodynamic trip is disposed ... 04/26/07 - 20070089423 - Gas turbine engine system and method of operating the same A gas turbine engine system includes an intercooler coupled between a low-pressure compressor and a high-pressure compressor and configured to cool the compressed air exiting the low-pressure compressor. Liquid natural gas or a cooled intermediate working fluid is used in the intercooler to cool the compressed air exiting the low-pressure ... 04/26/07 - 20070089422 - Multi-slot inter-turbine duct assembly for use in a turbine engine A bypass channel for use in an inter-turbine transition duct assembly of a turbine engine is connected to a suction port disposed upstream of a high-pressure turbine and at least two injection openings disposed downstream of the high-pressure turbine. The flow through the bypass channel is motivated by the natural ... 04/26/07 - 20070089421 - Assembly and method for cooling rear bearing and exhaust frame of gas turbine A propeller is mounted aft of the rear rotor supporting bearing of a gas turbine. The propeller is driven either by the rotor shaft or by the exhaust gases flowing through the exhaust frame of the turbine. The rotating propeller blows cooling air on the rear bearing. The cooling air ... 04/26/07 - 20070089420 - Gas turbine, in particular aircraft engine and method for generating electrical energy in a gas turbine A gas turbine, in particular an aircraft engine and to a method for generating electrical energy in a gas turbine is provided. The gas turbine comprises at least on engine core (18), in which a shaft (19) produces a shaft output. The turbine is equipped with means that generate electrical ... 04/19/07 - 20070084211 - Variable geometry hysteresis control for a gas turbine engine One embodiment of the present application is a gas turbine engine with a compressor that includes a variable geometry mechanism to vary working fluid flow area. A desired state of this mechanism is selected different than a current state to change the amount of flow area. The mechanism has a ... 04/19/07 - 20070084211 - Variable geometry hysteresis control for a gas turbine engine One embodiment of the present application is a gas turbine engine with a compressor that includes a variable geometry mechanism to vary working fluid flow area. A desired state of this mechanism is selected different than a current state to change the amount of flow area. The mechanism has a ... 04/19/07 - 20070084210 - Method and apparatus for performing gas turbine engine maintenance A method for performing maintenance on a gas turbine engine assembly includes unplugging a first connector from a first socket, the first connector electrically coupled to the engine control unit, the first socket electrically coupled to the hydromechanical unit, plugging a second connector into the first socket, the second connector ... 04/19/07 - 20070084210 - Method and apparatus for performing gas turbine engine maintenance A method for performing maintenance on a gas turbine engine assembly includes unplugging a first connector from a first socket, the first connector electrically coupled to the engine control unit, the first socket electrically coupled to the hydromechanical unit, plugging a second connector into the first socket, the second connector ... 04/19/07 - 20070084209 - Power generation The combustor (5) of a gas turbine (7) is supplied with coal bed methane (51), oxygen (53) and a part of the flue gas (55), predominantly CO2, produced from the gas turbine (7) and sent through a heat recovery steam generator (27), all under pressure. The heat recovery steam generator ... 04/19/07 - 20070084209 - Power generation The combustor (5) of a gas turbine (7) is supplied with coal bed methane (51), oxygen (53) and a part of the flue gas (55), predominantly CO2, produced from the gas turbine (7) and sent through a heat recovery steam generator (27), all under pressure. The heat recovery steam generator ... 04/05/07 - 20070074516 - Method of controlling bypass air split to gas turbine combustor Disclosed herein is a method for controlling a bypass air split for a gas turbine combustor, the method comprising determining a target exhaust temperature, wherein the target exhaust temperature is based on at least one parameter of a group of parameters consisting of low pressure turbine speed, high pressure turbine ... 03/29/07 - 20070068167 - Turbine exhaust catalyst In a gas turbine installation having an enclosure for passing cooling air therethrough and around the gas turbine, provision is made for a mixing of the cooling air with the exhaust gases being emitted from the gas turbine to thereby reduce the temperature thereof prior to its passing into the ... 03/22/07 - 20070062200 - Method of operating a thermal power plant, preferably a gas turbine power plant where paction limit(L) represents a pressure value which depends at least on the load set point (L) of the thermal power plant. ... 03/08/07 - 20070051108 - Method for increasing the efficiency of a gas turbine system and gas turbine system suitable therefor The aim of the invention is to increase the efficiency of a gas turbine system (1). Said aim is achieved by transferring at least one portion of the heat of the waste gases (AG) of a gas turbine (2) to a working medium of a thermodynamic circulation process, which comprises ... 03/01/07 - 20070044475 - Exhaust gas guide of a gas turbine and method for mixing the exhaust gas of the gas turbine The present invention relates to an exhaust gas guide of a gas turbine, which is situated between the gas turbine and a downstream waste heat boiler or a downstream gas diverter and which comprises a flow channel which has a cross-section expanding in at least some areas in the main ... 02/15/07 - 20070033943 - Method for operating a gas turbine as well as a gas turbine for implementing the method In a method for operating a gas turbine (11) in a combined cycle power plant (40), air, which is used to burn a syngas that is recovered from coal, is drawn in and compressed by the gas turbine (11), the compressed air is fed into a combustor (18, 19) and ... 02/15/07 - 20070033942 - Method for operating a gas turbine and a gas turbine for implementing the method In a method for operating a gas turbine (11) in a combined cycle power plant (40) air is drawn in and compressed through the gas turbine (11), the compressed air is led to a combustor (18, 19) to burn a syngas recovered from a fossil fuel, especially coal, and the ... 02/08/07 - 20070028623 - Infrared suppressor apparatus and method A method for suppressing infrared radiation from an engine of an aircraft operating in an environment includes directing hot exhaust from the aircraft engine into a lobed mixer of a single baffle infrared suppressor having a collapsible, translatable baffle to generate alternating flows of hot exhaust gas and cold air. ... 02/08/07 - 20070028622 - One-piece baffle infrared suppressor apparatus and method A method for suppressing infrared radiation from an aircraft engine includes directing hot exhaust from the aircraft engine into a lobed mixer of a single baffle infrared suppressor having a single baffle assembly to generate alternating flows of hot exhaust gas and cold air. The method further includes directing the ... 02/01/07 - 20070022757 - Infrared suppression system An InfraRed Suppression System (IRSS) includes an exhaust manifold and a high aspect ratio exhaust duct along a longitudinal length thereof. The IRSS minimizes impingement of engine exhaust onto adjacent aircraft structure by discharging the flow upwardly and/or outwardly, away from the fuselage at relatively high velocity to reduce fuselage ... 01/25/07 - 20070017226 - Generator assembly A generator assembly for a gas turbine engine. The assembly includes an electrical generator connected via a first sprag clutch to an accessory gearbox driven by the engine. The generator is also connected by a second sprag clutch to an air turbine connected to engine bleed valves which are selectively ... 01/18/07 - 20070012044 - System and method for trending exhaust gas temperature in a turbine engine A method for estimating a trend in exhaust gas temperature in a turbine engine includes sampling exhaust gas temperature and a plurality of variables associated with the exhaust gas temperature over a set of observation times for a turbine engine to acquire exhaust gas temperature data. A trend in the ... 01/11/07 - 20070006594 - Cooling system for high-speed vehicles and method of cooling high-speed vehicles A cooling system for a high-speed vehicle may comprise a combustor wall at least partially enclosing a combuster and which is cooled using a coolant circulating in a Brayton cycle. The heated coolant may be expanded in a turbine, transfer heat to a fuel within a heat exchanger, and be ... 01/11/07 - 20070006593 - Inter-turbine temperature display compensation system and method Control logic, and a method implemented by the control logic, compensates for mismatched inter turbine temperatures between two gas turbine engines and displays a biased inter turbine temperature (ITT) reading to the pilot without jeopardizing the need to be properly informed of the health of all engines and the relationship ... 01/11/07 - 20070006592 - Systems and methods for power generation with carbon dioxide isolation A power generation system and method includes a first gas turbine system comprising a first combustion chamber configured to combust a first fuel stream of primarily hydrogen that is substantially free of carbon-based fuels. The first gas turbine system also includes a first compressor configured to supply a first portion ... 01/11/07 - 20070006591 - Fuel deoxygenation for improved combustion performance A method and device of this invention includes a fuel deoxygenator and a heating device for removing dissolved oxygen from fuel and then heating that fuel to a temperature above the temperature that would otherwise produce undesirable insoluble materials from a hydrocarbon fuel. The temperature of the fuel and the ... 12/28/06 - 20060288704 - Methods and apparatus for operating gas turbine engine combustors A method facilitates assembling a gas turbine engine. The method comprises coupling a combustor including a dome assembly and a combustor liner that extends downstream from the dome assembly to a combustor casing that is positioned radially outwardly from the combustor, coupling a ring support that includes a first radial ... 12/28/06 - 20060288703 - System for detecting and compensating for aerodynamic instabilities in turbo-jet engines The present invention relates to a system for detecting aerodynamic instabilities in a jet turbine engine having a pressure transducer mounted in the engine. The pressure transducer, welded to a circuit in signal communication with a controller, is adapted to send measured pressure readings from air in a combustion chamber ... 12/21/06 - 20060283190 - Engine status detection with external microphone A method of detecting at least one engine condition of a gas turbine engine using a microphone disposed outside a region of the gas turbine engine to be monitored. The method includes receiving a signal produced by the microphone in response to audible frequencies, analyzing the signal to determine at ... 12/21/06 - 20060283189 - Axial flow sleeve for a turbine combustor and methods of introducing flow sleeve air A combustor has a flow sleeve and a flow liner defining a generally axial flow direction of compressor discharge air toward combustor burners. A casing is secured to the forward end of the flow sleeve defining an annular plenum along the interior of the flow sleeve. Openings through the flow ... 12/14/06 - 20060277916 - Method of operating an atomizing arrangement A liquid atomizing arrangement comprises: a line system, at least one pressure atomizer nozzle, at least one line for the liquid to be atomized, and at least one first actuator for setting the atomizing supply pressure and/or the liquid mass flow through the atomizing arrangement. method of operating the liquid ... 12/14/06 - 20060277915 - Gas 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 ... 11/23/06 - 20060260320 - Arrangement for controlling fluid jets injected into a fluid stream In an air mixing arrangement wherein a primary fluid is introduced through an opening in a wall to be mixed with a secondary fluid flowing along the wall surface, the opening is airfoil shaped with its leading edge being orientated at an attack angle with respect to the secondary fluid ... 11/23/06 - 20060260319 - Nox adjustment method for gas turbine combustors An embodiment may comprise a system for controlling NOx emissions from a turbine having combustion chambers. The system may comprise a center fuel flow and a plurality of outer fuel flows for each of a plurality of combustion chambers. An outer fuel flow is set to achieve a desired level ... 11/16/06 - 20060254281 - Mobile gas turbine engine and generator assembly A method for supplying power to a remote load includes coupling a gas turbine engine to a vessel that is not used to provide propulsion for the vessel, coupling a generator to the gas turbine engine, coupling an intercooler system downstream from a first compressor such that compressed air discharged ... 11/16/06 - 20060254280 - Combined cycle power plant using compressor air extraction A combined cycle power plant (100) utilizing a compressor air bleed (62) as a source of heat for generating steam in a steam generator (78) for supplying the gland seals of the steam turbine (3) and as a motive force for an air ejector (90) for evacuating the condenser (8) ... 11/16/06 - 20060254279 - Method of tuning individual combustion chambers in a turbine based on a combustion chamber stratification index A method, system and software for reducing combustion chamber to chamber variation in a multiple-combustion chamber turbine system comprising sensing dynamic combustion pressure tones emitted from combustion chambers in a multiple combustion chamber turbine and determining a combustion chamber stratification index for the combustion chambers from the dynamic combustion pressure ... 11/09/06 - 20060248895 - Magnetic gas engine and method of extracting work The present subject matter overcomes the deficiencies in the prior art by introducing or generating charged particles in an air stream and manipulating the air stream with magnetic fields operating on the charged particles. Embodiments of the present subject mater compress the air stream by accelerating charged particles with a ... 11/09/06 - 20060248894 - Fuel gas calorie control equipment and gas turbine system When CFG's are supplied to a gas tank 2, the fluctuation ratio of the gas calories of the CFG's is restrained by supplying the CFG's different time delays and mixing them. When the CFG's are mixed with BFG in a gas mixer 3, the gas flow rate of the BFG ... 11/09/06 - 20060248893 - Method and system for determining lean blow out condition for gas turbine combustion cans A method for determining a lean blow out condition for a combustor. In an exemplary embodiment, the method includes determining acoustical frequency data for the combustor, determining a combustor flame temperature based on the acoustical frequency data, determining an existing fuel/air ratio in the combustor based on the combustor flame ... 10/12/06 - 20060225428 - Dual fuel combined cycle power plant A power plant that includes two combustors in which a particulate containing fuel like coal is burned in one combustor and a non-particulate or clean fuel is burned in the other combustor, and where a heat exchanger is sued to transfer heat from the particulate combustion process to compressed air ... 10/05/06 - 20060218927 - Telemetry system A method for predicting bearing failure of a differential bearing including an inner race, an outer race, and a plurality of rolling elements positioned between the inner and outer race, the method includes coupling a measuring apparatus comprising at least one of a strain gage and an accelerometer to the ... 09/21/06 - 20060207260 - Gas-turbine power generating installation and method of operating the same A gas-turbine power generating installation capable of effectively utilizing gases produced in overage gas fields, etc. and a method of operating the installation are provided. The gas-turbine power generating installation is installed in the vicinity of an outrage gas field or an oil field. In the installation, air compressed by ... 09/21/06 - 20060207259 - Acoustic damper A combustor wall of a gas turbine engine is provided with an acoustic damper component. The component has a first metering passage, a first damping chamber, a first damping passage, a second damping chamber and a second damping passage. Air flows through the damper to be ejected into the combustion ... 09/14/06 - 20060201158 - Method and apparatus for monitoring the performance of a gas turbine system A method for monitoring performance of a gas turbine system comprises providing a plurality of combustor cans; placing a plurality of temperature sensors circumferentially around an exhaust plane of the plurality of combustor cans; operating the plurality of combustor cans while varying a plurality of gas turbine operating parameters, where ... 09/07/06 - 20060196189 - Rabbat engine An electric generator is made to produce Direct Current which is used to separate water by electrolysis into its component gases. These are fed into the turbine driving this Generator. Starting and/or acceleration use a fuel or a combination of fuels which are injected into the combustion chamber. Using off-the-shelf ... 08/31/06 - 20060191268 - Method and apparatus for cooling gas turbine fuel nozzles A method and apparatus for a nozzle of a gas turbine engine is disclosed that facilitates extending a useful life of the nozzle. The method and apparatus include an impingement baffle plate disposed at a back side of a diffusion tip of the nozzle. The method and apparatus includes the ... 08/24/06 - 20060185368 - Gas turbine system burning heavy-oil modified fuel and method of operating same A gas turbine system burning heavy-oil modified fuel and a method of operating the gas turbine system, which covers from a stage of modifying heavy oil and producing gas turbine fuel to a stage of operating a gas turbine, including startup, ordinary shutdown and emergency shutdown of the gas turbine. ... 08/24/06 - 20060185367 - Lng power plant and operation method thereof An LNG (liquefied natural gas) power plant has a heating/cooling device. The heating/cooling device is controlled by a command generated by a temperature control device. The temperature control device receives a heating value and a temperature of the fuel gas. The heating value of the fuel gas introduced to a ... 08/17/06 - 20060179845 - Extended operability aircraft fuel delivery system A fuel delivery system for a gas turbine engine includes a main fuel pump supplying fuel to a fuel-metering device. The operational flow range of the fuel system is dependent on a minimum net positive suction pressure at the main pump inlet required to prevent pump cavitation. A mixture of ... 08/10/06 - 20060174628 - Method and system for balancing bleed flows from gas turbine engines A bleed air balancing system includes a plurality of bleed air flow paths (12) each carrying bleed air from one of a plurality of gas turbine engines (10), each bleed air flow path (12) including a flow rate sensor (19), and a circuit (52, 200) outputting at least one flow ... 08/10/06 - 20060174627 - Gas turbine cycle A gas turbine cycle that utilizes the vaporization of liquefied natural gas as an intercooler in an open loop gas turbine system. The system provides an increase in gas turbine cycle efficiencies while providing a convenient system for vaporizing liquefied natural gas. The systems and methods of the present invention ... 08/03/06 - 20060168967 - Inboard radial dump venturi for combustion chamber of a gas turbine A double wall venturi chamber having a converging section, a diverging section and a cylindrical section wherein said chamber defines a venturi zone in which compressed air, fuel and combustion products flow downstream through converging section, diverging section and cylindrical section, and has a cooling gas passage between the walls ... 08/03/06 - 20060168966 - Self-purging pilot fuel injection system A gas turbine combustor having a self-purging pilot fuel injection system and method of operation thereof is disclosed. The pilot fuel injection system comprises a radial inflow swirler, a generally axially extending centerbody, and at least one fuel injection source. In operation a fluid containing at least air passes along ... 07/13/06 - 20060150632 - Gas turbine engine A gas turbine engine includes a heat exchanger for heating an airflow. The engine is arranged so that in use the heat exchanger is heated and in turn heats the airflow. ... 07/13/06 - 20060150631 - Liquid fuel recirculation system and method A recirculation system for circulating distillate during gas fuel operation so as to reduce or eliminate distillate carbon formation. The recirculation system keeps the distillate's temperature below the carbon formation limit by circulating the distillate back to a storage tank to cool the distillate due to a volume of the ... 06/29/06 - 20060137355 - Fan driven emergency generator An emergency electrical power generating apparatus for use with a turbofan engine comprises an electrical generator and a clutch assembly. The clutch connects the generator with a fan assembly of the engine only during a windmill action of the fan assembly. ... 06/29/06 - 20060137354 - Passive, high-temperature amplifier for amplifying spark signals detected in igniter in gas turbine engine A system for detecting spark in an igniter for a gas turbine engine. An igniter generates a plasma, or spark, somewhat similar to an automotive spark plug. In the invention, an inductive pick-up is positioned adjacent the igniter, to detect current pulses in the igniter, to thereby infer the presence ... 06/29/06 - 20060137353 - Systems and methods for detection of blowout precursors in combustors The present invention comprises systems and methods for detecting flame blowout precursors in combustors. The blowout precursor detection system comprises a combustor, a pressure measuring device, and blowout precursor detection unit. A combustion controller may also be used to control combustor parameters. The methods of the present invention comprise receiving ... 06/22/06 - 20060130487 - System for augmented electric power generation with distilled water output The system for augmented electric power generation with distilled water output employs a combined cycle gas turbine power generation system for electrical power generation. A multistage evaporator uses steam drawn from the steam turbine as a heating medium to power the multistage evaporator for the production of distilled water. Residual ... 06/15/06 - 20060123795 - Bearing chamber pressurization system A method and device for improved pressure balancing in a bearing chamber pressurization system for gas turbine engines employ a partition member to substantially separate first and second air-oil seals of the bearing housing. ... 06/15/06 - 20060123794 - Shroud leading edge cooling A cooling device includes a plurality of passages extending through outer platforms of turbine vane segments for directing cooling air in a choked flow condition towards a downstream turbine shroud. ... 06/15/06 - 20060123793 - Aerodynamic trip for a combustion system A apparatus and method for improving combustion by improving at least one of temperature distribution in the combustor, pressure distribution around the combustor and combustion noise level in the combustor, by redistributing air around the combustor to modify the structure of the air flow prior to entry into the combustor. ... 06/08/06 - 20060117757 - Fuel gas heating control equipment and gas turbine power generation facility provided with the fuel gas heating control equipment A fuel gas heating control equipment in accordance with the present invention is provided with a gain-determining portion 21 and a time-constant-determining portion 22 which determine values of a gain and a time constant to be used for PI calculations being performed by a PI calculation portion 14. The gain-determining ... 06/08/06 - 20060117756 - Gas turbine engine assembly and method of assembling same A method of reducing gas turbine engine distortion includes coupling a core gas turbine engine to a power turbine, coupling the power turbine to a thrust bearing support assembly through a frusto-conically shaped structural support such that the net axial thrust of the coupled core gas turbine engine and power ... 06/01/06 - 20060112697 - Stall detection and recovery system A stall detection and recovery system (10) for a gas turbine engine (1) comprises surge detection means (50 for detecting an engine surge and providing a surge detection signal (154) for indicating said engine surge. The system also includes stall detection means to provide a stall detection signal (48) relating ... 06/01/06 - 20060112696 - Efficient combined cycle power plant with co2 capture and a combustor arrangement with separate flows The invention relates to a method for inter alia to increase the energy and cost efficiency of a gas power plant or a thermal heat plant with CO2 capturing. The power plant comprises gas turbine plants (12,12′) comprising compressor units (13,13′) and turbine units (14,14′) and further comprises a combustor ... 05/25/06 - 20060107665 - Methods and systems for operating oxidizer systems A method and system for operating a gas turbine engine is provided. The system includes in serial flow arrangement, at least one compressor, a combustor, and at least one turbine. The method includes compressing atmospheric air in the gas turbine engine, channeling at least a portion of the compressed air ... 05/11/06 - 20060096292 - Method for determination of the temperature, mass-averaged over a flow cross-section, of a gas flow in a gas turbine The invention relates to a method for determination of a temperature, mass-averaged over a flow cross-section, of a gas flow in a gas turbine or the like, particularly during partial load operation of the gas turbine. The invention also relates to a control apparatus, which can be operated using the ... 05/04/06 - 20060090472 - System and method for heating an air intake of turbine engine A heating system for a turbine engine air intake region for preventing the formation of ice on the air intake region, which may be formed from the bell-mouth, one or more vanes, such as inlet guide vanes, a turbine blade assembly formed from one or more blades, such as the ... 05/04/06 - 20060090471 - Method and apparatus for identification of hot and cold chambers in a gas turbine combustor A method for identifying combustion characteristics of a plurality combustion chambers in a gas turbine, the method including: supplying fuel to the combustion chambers at a predetermined fuel rate; sensing combustion dynamic pressure in said plurality of combustion chambers and generating dynamic pressure signals representative of the dynamic pressure in ... 04/20/06 - 20060080964 - Air cooler for power plants and use of such an air cooler An air cooler for power plants comprising a pressure vessel, in which is accommodated a coaxial arrangement containing a cylindrical central tube, a helical tube bundle surrounding the central tube and a cylindrical casing surrounding the tube bundle. The central tube extends, at one end of the coaxial arrangement, into ... 04/20/06 - 20060080963 - Power generating system and method A power generating system having a liquid natural gas (LNG) vaporization circuit and an energy generating circuit. The LNG vaporization circuit includes a heat exchange assembly and a heating tower connected to the heat exchange assembly. The LNG vaporization circuit also includes a LNG vessel connected to the heat exchange ... 04/13/06 - 20060075754 - Aeroengine oil tank fire protection system A gas turbine engine comprising an oil system and a gearbox, the gearbox is driven by at least one engine shaft, the oil system comprises a pump drivingly connected to the gearbox, an oil tank connected to the pump via a supply pipe and a delivery pipe connecting the pump ... 03/30/06 - 20060064985 - Power plant and operating method A method for operating a power plant (2), which includes at least one compressor (3), at least one turbine (4), and a burner arrangement (5), involves, to enhance the power plant (2), feeding a combustion exhaust gas from a pre-burner (8) of the burner arrangement (5) to an oxygen-removal device ... 03/23/06 - 20060059919 - System and method for improving thermal efficiency of dry low emissions combustor assemblies A gas turbine engine system having improved thermal efficiency, which comprises: (1) an inlet air stream; and (2) a dry low emissions combustor assembly having an air inlet for receiving the inlet air stream, at least one bleed air port and an air outlet for discharging at least a portion ... 03/23/06 - 20060059918 - Adjusting airflow in turbine component by depositing overlay metallic coating A method for adjusting the airflow in a turbine component having a plurality of airflow holes. The method comprises the step of depositing an overlay metallic coating on the surface of the turbine component in a manner such that at least some of the airflow holes are partially filled such ... 03/23/06 - 20060059917 - Method and apparatus for detecting the presence of flame in the exhaust path of a gas turbine engine A method and apparatus for monitoring the exhaust path of a gas turbine engine for the presence of unwanted flames downstream from the main combustion chamber(s). The system is comprised of an Electro-Optics Module containing sensors and associated processing electronics as well as collection and transmitting optics, which relay the ... 03/16/06 - 20060053802 - Ignition detecting method for gas turbine A gas turbine which can detect ignition in a combustor regardless of startup conditions of the gas turbine, such as the hot startup or the cold startup. An ignition detecting method for the gas turbine comprises the steps of calculating a difference between the exhaust temperature detected at a particular ... 03/16/06 - 20060053801 - Cooling system for gas turbine engine having improved core system A gas turbine engine having a longitudinal centerline axis therethrough, including: a fan section at a forward end of the gas turbine engine including at least a first fan blade row connected to a first drive shaft; a booster compressor positioned downstream of and in at least partial flow communication ... 03/16/06 - 20060053800 - High thrust gas turbine engine with improved core system A gas turbine engine having a longitudinal centerline axis therethrough, including: a fan section at a forward end of the gas turbine engine including at least a first fan blade row connected to a first drive shaft; a booster compressor positioned downstream of and in at least partial flow communication ... 03/16/06 - 20060053799 - Recuperator and turbine support adapter for recuperated gas turbine engines A recuperator and turbine support adapter for securing a recuperator to a combustor case is provided. The recuperator and turbine support adapter comprises an outer strutted body, an inner strutted body and a thermal spring. The thermal spring allows for thermal expansion of the recuperator and turbine support adapter while ... 03/16/06 - 20060053798 - Waffled impingement effusion method A combined impingement effusion method comprises brazing or welding a waffled impingement plate to the cold back-side surface of component having effusion holes there through. The impingement plate comprises a plurality of small baffle cells to relieve the thermal stresses between the impingement plate and the component. By rigidly attaching ... 03/16/06 - 20060053797 - Combustor exit duct A combustor for a gas turbine engine includes a sheet metal combustor wall having a plurality of cooling apertures therein immediately upstream of a corner between two intersecting combustor wall portions. ... 03/09/06 - 20060048517 - Process and a plant for recycling carbon dioxide emissions from power plants into useful carbonated species A process is disclosed for recycling carbon dioxide emissions from a fossil-fuel power plant into useful carbonated species The process primarily comprises the steps of: a) burning the fossil fuel, thereby generating heat and a hot exhaust gas containing CO2; and b) converting the heat into energy. The process is ... 03/02/06 - 20060042260 - Arrangement for controlling flow of fluid to a component of a gas turbine engine An arrangement for controlling flow of fluid to a component of a gas turbine engine, the arrangement comprising: a conduit, coupled to a supply of fluid, for providing fluid to the component of the gas turbine engine; a magnetic valve for at least partially restricting the conduit and having a ... 03/02/06 - 20060042259 - Combined-cycle power plant and steam thermal power plant A combined-cycle power plant, a steam thermal power plant, and a method for operating the power plant, which are capable of effectively utilizing raw fuel produced from medium- or small-scaled gas fields and oil fields. Raw fuel produced from a gas field is separated into a gas component and a ... 03/02/06 - 20060042258 - Method of controlling a power generation system A method of controlling a gas turbine system (10) may include controlling an inlet guide vane position (98) to maintain a turbine (24) exhaust temperature at a corrected value that is a function of a compressor (12) inlet temperature and a turbine (24) normalized load. The method may include selecting ... 03/02/06 - 20060042257 - Combustor heat shield and method of cooling A heat shield for a gas turbine engine combustor includes an apparatus for providing a spiral flow to improve at least the cooling of the heat shield. ... 03/02/06 - 20060042256 - Concentric fixed dilution and variable bypass air injection for a combustor A combustor for a gas turbine includes a combustor body having an aperture and a casing enclosing the combustor body and defining a passageway therebetween for carrying compressor discharge air. There is at least one injection tube for supplying an amount of the compressor discharge air into the combustor body ... 02/23/06 - 20060037325 - Method of scavenging oil within a gas turbine engine An oil scavenge system includes a tangential scavenge scoop and a settling area adjacent thereto which separately communicate with a duct which feeds oil into an oil flow path and back to an oil sump. A shield is mounted over the settling area to at least partially shield the collecting ... 02/23/06 - 20060037324 - Water and sulfur removal from combustion turbine exhaust A combustion turbine power plant (10) incorporating a desiccating scrubber (140) for simultaneously removing water and sulfur from a flue gas (20) of the power plant (10). The desiccating scrubber (140) may include an inlet nozzle (145) for spraying an aqueous solution (142) containing a desiccant and a base into ... 02/16/06 - 20060032232 - Single shaft combined cycle power plant and its operation method According to the invention, there is provided a single shaft combined cycle power plant which can quickly switch from single operation of a gas turbine to combined operation of the gas turbine and a steam turbine, and can quickly increase output power, from low power to high power. The single ... 02/09/06 - 20060026963 - Approach to extending life of gas turbine engine Methods of increasing lifetimes of components in a gas turbine engine. Ordinarily, components are replaced after they experience a certain number of thermal cycles, or a certain operating temperature limit is exceeded. Under one form of the invention, the components are not replaced at that time, but are subjected to ... 02/02/06 - 20060021353 - Gas turbine power plant with supersonic gas compressor A gas turbine engine. The engine is based on the use of a gas turbine driven rotor having a compression ramp traveling at a local supersonic inlet velocity (based on the combination of inlet gas velocity and tangential speed of the ramp) which compresses inlet gas against a stationary sidewall. ... 02/02/06 - 20060021352 - Thermodynamic pressure generator A thermodynamic pressure generator having an oscillating valve that allows premixed fuel to enter a combustion chamber in turbulence, until it comes into contact with an annular spoiler, which converts a portion of the fuel into a Karmon vortex ring for delayed ignition. A continuous spark then ignites the remaining ... 01/26/06 - 20060016195 - Bypass and injection method and apparatus for gas turbines A bypass air injection scheme for a combustor of a gas turbine. Combustor includes a body with an inner liner and a casing enclosing the body with a passageway defined therebetween. A predetermined amount of the compressor discharge air passing through the passageway is extracted through a manifold. A conduit ... 01/19/06 - 20060010875 - Gas turbine engine bleed air power assist system and method A bleed air power assist system is coupled to a gas turbine engine that includes a high pressure turbine, a low pressure turbine, and an electrical generator driven by the high pressure turbine. The bleed air power assist system selectively bleeds air discharged from the high pressure turbine and supplies ... 01/12/06 - 20060005545 - Localized arc filament plasma actuators for noise mitigation and mixing enhancement A device for controlling fluid flow. The device includes an arc generator coupled to electrodes. The electrodes are placed adjacent a fluid flowpath such that upon being energized by the arc generator, an arc filament plasma adjacent the electrodes is formed. In turn, this plasma forms a localized high temperature, ... 01/12/06 - 20060005544 - Synchronizing stationary clutch for compression braking with a two spool gas turbine engine A synchronizing stationary clutch system for compression braking in a two spool gas turbine engine is provided by the present invention. The synchronizing stationary clutch system allows the two shafts of a two spool gas turbine engine to be reliably coupled at any given speed of either shaft. This coupling ... 01/05/06 - 20060000219 - Apparatus for observing combustion conditions in a gas turbine engine A fuel injector for a gas turbine combustor is disclosed which includes a feed arm having a flange for mounting the injector within the combustor and a fuel nozzle depending from the feed arm for injecting fuel into the combustor for combustion. An optical sensor array is operatively associated with ... 12/22/05 - 20050279100 - High area-ratio inter-turbine duct with inlet blowing A bypass channel for use in an inter-turbine transition duct of a gas turbine engine is connected to a suction port disposed upstream of a high-pressure turbine and an injection port disposed downstream of the high-pressure turbine. The flow through the bypass channel is motivated by the natural pressure difference ... 12/08/05 - 20050268615 - Method and apparatus for cooling combustor liner and transition piece of a gas turbine A method and apparatus for cooling a combustor liner and transitions piece of a gas turbine include a combustor liner with a plurality of turbulators arranged in an array axially along a length defining a length of the combustor liner and located on an outer surface thereof; a first flow ... 12/08/05 - 20050268614 - Premixing burner with impingement cooled centerbody and method of cooling centerbody A gas-air premixing burner for gas turbines includes an air swirler and an annular burner tube surrounding a bluff centerbody. The bluff body serves to stabilize the flame by defining a recirculating vortex. Cooling air is directed to impinge against the bluff face of the centerbody and the spent impingement ... 12/08/05 - 20050268613 - Method and apparatus for cooling combustor liner and transition piece of a gas turbine A method and apparatus for cooling a combustor liner and transitions piece of a gas turbine include a combustor liner with a plurality of circular ring turbulators arranged in an array axially along a length defining a length of the combustor liner and located on an outer surface thereof; a ... 12/01/05 - 20050262848 - Methods and apparatus for operating gas turbine engines A method for operating a gas turbine engine includes channeling compressed airflow discharged from a first compressor through an intercooler having a cooling medium flowing therethrough, channeling a working fluid through the intercooler to facilitate increasing an operating temperature of the working fluid, and channeling the discharged working fluid to ... 11/03/05 - 20050241317 - Apparatus and method for reducing the heat rate of a gas turbine powerplant The present invention provides an apparatus and method for reducing the pressure loss of air prior to entering a combustion system, such that, for a known combustion system having a predetermined pressure loss, the resulting fluid entering the turbine has a higher supply pressure that will result in more efficient ... 11/03/05 - 20050241316 - Uniform effusion cooling method for a can combustion chamber A dome for a combustion chamber may have a plurality of effusion holes therein to provide efficient cooling while preventing carbon formation on the dome and chamber walls of the combustion chamber. Conventional dome cooling designs, using dome louvers, for example, may become corroded and/or may allow for ingestion of ... 11/03/05 - 20050241315 - Rotary heat engine A jet-propelled rotary engine comprises a stator and a rotor operatively coupled to the stator for rotation of the rotor relative to the stator about a rotor axis. The rotor comprises at least first and second jet assemblies wherein the first jet assembly defines a first converging flow region, a ... 10/27/05 - 20050235649 - Method for operating a gas turbine A gas turbine (10) includes a compressor (12) receiving inlet air (18) and producing compressed air, a combustor (14) receiving a combustion portion (30) of the compressed air and producing a hot combustion gas (32), and a turbine (16) receiving the hot combustion gas and producing an exhaust gas (28). ... 10/27/05 - 20050235648 - Orbiting combustion nozzle engine An orbiting combustor nozzle (OCN) engine, having a rotating assembly comprising a co-rotating compressor and nozzle wheel enclosed within a non-rotating outer casing, defining a rotating combustion chamber, is disclosed. Combustion occurs in the combustion chamber in a vortex of gas that rotates at the same angular velocity as the ... 10/20/05 - 20050229602 - Forced air cooling system A forced air cooling system for an APU comprising at least an oil cooler, a plenum in fluid communication with the oil cooler, and a compressor rotated by a rotating shaft of the APU such that the compressor and rotating shaft rotate at a same speed, the rotating compressor inducing ... 10/20/05 - 20050229601 - Gas turbine engine cooling system and method Fuel supplied to a rotary fluid trap is centrifugally accelerated within a first cavity adjacent a first side of a rotor, and is then directed though a plurality of first passages extending through the rotor between and proximate to the blades, and shaped so as to at least partially conform ... 10/13/05 - 20050223712 - Vaporization of liquefied natural gas for increased efficiency in power cycles A gas turbine cycle that utilizes the vaporization of liquefied natural gas as a source of inlet air chilling for a gas turbine. The cycle uses regeneration for preheating of combustor air and offers the potential of gas turbine cycle efficiencies in excess of 60%. The systems and methods permit ... 10/13/05 - 20050223711 - Closed-loop cooling system for a hydrogen/oxygen based combustor A closed-loop cooling system is provided for a hydrogen/oxygen based combustor. A combustion reaction between hydrogen and oxygen in the combustor produces steam. The steam is used to generate work from a turbine shaft, which is used to drive a propulsion system for the underwater vessel. After the steam passes ... 10/06/05 - 20050217272 - Deoiler for a lubrication system A deoiler 26 for separating oil from air contaminated with the oil has at least one separator for separating the oil from the air and also has a source of suction for reducing air pressure at the source of the air. In an exemplary embodiment, the deoiler 26 creates the ... 09/22/05 - 20050204744 - Temperature variance reduction using variable penetration dilution jets A variable penetration dilution jet array for a single can and scroll assembly includes a plurality of differentially sized dilution openings around the circumference of the combustor can. The alternating smaller and larger openings provide for circumferential and radial mixing uniformity with the smaller openings giving shallow penetration and the ... 09/22/05 - 20050204743 - Gas turbine inlet flow straightener A radial inlet assembly comprising a radial inlet adapted to be in fluid communication with a compressor, and a restricting member covering the radial inlet and receiving a circumferentially asymmetric airflow, the restricting member partially blocking the airflow around the radial inlet, the restricting member blocking a greater portion of ... 09/08/05 - 20050193740 - Stratojet - system and method for automatically maintaining optimum oxygen content in high altitude turbojet engines The Stratojet is a method and apparatus for maintaining a desired oxygen content level at the outlet of a turbojet engine to increase speed, altitude, and thrust, and to decrease flameouts and includes delivering a second liquid oxidant dosage to the duct upstream of the compressor while repeatedly sequencing through ... 09/08/05 - 20050193739 - Model-based control systems and methods for gas turbine engines A method and system of controlling a gas turbine engine is disclosed. The engine has sensors to detect one or more parameters and actuators adapted to respond to commands. The method includes receiving data from the sensors of the engine for one or more measured or sensed parameters, estimating a ... 09/01/05 - 20050188701 - Solid propellant gas generators in power systems An emergency power system comprising a plurality of solid propellant gas generators each having a gas outlet in fluid communication with a turbine wheel rotationally disposed within a gas turbine housing, the turbine wheel being in rotational communication with an electric generator input shaft, a fluid pump input shaft, or ... 09/01/05 - 20050188700 - Pressure reduction apparatus and method A pressure reduction apparatus is disclosed. Air at high pressure and temperature may be drawn from a source such as a bleed valve of a gas turbine engine that supplies the air to an airplane interior. The air is passed to a pressure reduction vessel. The vessel has sufficient volume ... 08/25/05 - 20050183422 - Single shaft combined cycle power plant and its operation method According to the invention, there is provided a single shaft combined cycle power plant which can quickly switch from single operation of a gas turbine to combined operation of the gas turbine and a steam turbine, and can quickly increase output power, from low power to high power. The single ... 08/11/05 - 20050172633 - Start-up method for power plant A variable loading rate method of starting a plurality of gas turbines (GT1, GT2) used in a combined cycle power plant for generating electricity. A first gas turbine is started and allowed to operate at a minimum load condition. The turbine is maintained at this load level while a second ... 08/04/05 - 20050166596 - Resonator adopting counter-bored holes and method of suppressing combustion instabilities A resonator for damping pressure waves or instabilities in a system supported by acoustic energy wherein the resonator adopts the use of counter-bored openings on the downstream side of the resonator within the flow path of the system. The resonator includes a first member and a second member where the ... 07/28/05 - 20050160737 - Rotary combustor, and electrical generator comprising a combustor of this type The combustor comprises a stationary structure and at least one tubular rotor supported rotatably about an axis by the structure by means of contactless suspension devices there being formed within this rotor at least one combustion chamber having at least one orientated lateral outflow aperture for the ejection of the ... 07/28/05 - 20050160736 - Methods and apparatus for operating gas turbine engines A method for operating a gas turbine engine, including a first compressor, a second compressor, and a turbine, coupled together in serial flow arrangement. The method includes channeling compressed airflow discharged from the first compressor through an intercooler having a cooling medium flowing therethrough, operating the intercooler such that condensate ... 07/21/05 - 20050155353 - Thermal management system for an aircraft A fuel based thermal management system includes a fuel stabilization system which permits the fuel to exceed the traditional coking temperatures. High temperature components are arranged along the fuel flow path such that even at the higher operating temperatures the fuel operates as a heat sink to transfer heat from ... 07/14/05 - 20050150230 - High density combined cycle power plant process A process for increasing the specific output of a combined cycle power plant and providing flexibility in the power plant rating, both without a commensurate increase in the plant heat rate, is disclosed. The present invention demonstrates that the process of upgrading thermal efficiencies of combined cycles can often be ... 07/14/05 - 20050150229 - Method for operating a gas turbine A gas turbine includes a compressor, a combustor, a turbine, and a flow path diverting an excess portion of the compressed air produced by the compressor around the turbine. The flow path conducts the excess portion into a turbine exhaust gas flow producing a cooled exhaust gas. A method of ... 07/07/05 - 20050144956 - Vortex fuel nozzle to reduce noise levels and improve mixing A method of reducing engine noise generation by decoupling: acoustic and hydrodynamic fluctuation generated by a compressor and a fuel supply system; from acoustic and hydrodynamic fluctuation of a combustor, by: deflecting fuel jets into a fuel nozzle mixing chamber in a number of counter-rotating adjacent pairs of fuel laden ... 07/07/05 - 20050144955 - Method and apparatus for reduction of combustor dynamic pressure during operation of gas turbine engines Methods and apparatus for operating a gas turbine engine without sustained detrimental levels of dynamic pressure are provided. The engine includes a combustor. The method includes determining the combustor acoustic level amplitude, comparing the acoustic level to a predetermined upper acoustic limit, and adjusting a fuel flow distribution to the ... 06/30/05 - 20050138932 - Aircraft protection method and system In the operation of a turbojet engine of an aircraft, a method of reducing the infrared radiation in the engine's exhaust; comprising: 1) releasing infrared radiation masking material selected from the group consisting of liquid nitrogen, water, and calcined aluminum and combinations thereof into the engine's exhaust so that the ... 06/23/05 - 20050132712 - Method and apparatus for detecting compressor stall precursors A method of detecting onset of a gas turbine condition, such as compressor stall, includes receiving data indicative of an operating parameter of a compressor of the gas turbine. The method also includes performing a wavelet transformation on the data to generate wavelet transformed data. The wavelet transformation is configured ... 06/23/05 - 20050132711 - Variable turbine cooling flow system Cooling air to the blades and disks of a gas turbine may be modulated to provide a variable turbine cooling flow. A bellows may be extended by providing a high pressure compressor discharge flow to an interior of the bellows. The bellows may be compressed when the interior of the ... 06/23/05 - 20050132710 - Bifurcated oil scavenge system for a gas turbine engine An oil scavenge system includes a tangential scavenge scoop and a settling area adjacent thereto which separately communicate with a duct which feeds oil into an oil flow path and back to an oil sump. A shield is mounted over the settling area to at least partially shield the collecting ... 06/16/05 - 20050126176 - Work extraction arrangement A work extraction arrangement (10) comprises a cooling assembly (12) for cooling a gas to provide a working fluid capable of doing work. The arrangement (10) further includes storage means (14) for storing the working fluid and a turbine assembly (18) for extracting work from the working fluid. A fluid ... 06/16/05 - 20050126175 - Integrated microturbine system A microturbine for the generation of mechanical and electrical power comprising a positive displacement axial vane rotary compressor and an axial vane rotary expander. The compressor and expander are joined by a common shaft. The system further includes at least one combustor for heating a driving fluid prior to its ... 06/02/05 - 20050115246 - Outdoor microturbine engine having water and oil separator An outdoor microturbine engine assembly includes a microturbine engine supported by a base and enclosed by an enclosure. The base defines a reservoir for the collection of rain water and any oil that may leak from the engine into the reservoir. The oil will naturally float on the water in ... ### FreshPatents.com Support |