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Gas Turbine patents



      
           
This page is updated frequently with new Gas Turbine-related patent applications. Subscribe to the Gas Turbine RSS feed to automatically get the update: related Gas RSS feeds. RSS updates for this page: Gas Turbine RSS RSS


Method for operating a combined-cycle power plant with cogeneration, and a combined-cycle power plant for carrying out…

Alstom Technology Ltd

Method for operating a combined-cycle power plant with cogeneration, and a combined-cycle power plant for carrying out…

Gas turbine casing load sharing mechanism

General Electric

Gas turbine casing load sharing mechanism

Gas turbine casing load sharing mechanism

Alstom Technology

Carrier ring

Date/App# patent app List of recent Gas Turbine-related patents
03/26/15
20150086381
 Internally cooled airfoil patent thumbnailnew patent Internally cooled airfoil
An internally cooled airfoil for a gas turbine engine has a hollow airfoil body including pressure and suction sidewalls defining a cooling passage therebetween. A combination of pedestal and trip-strips are used in the cooling passage to enhance heat transfer while minimizing the coolant pressure drop across these features..
Pratt & Whitney Canada Corp.
03/26/15
20150086361
 Axial rotor portion and turbine rotor blade for a gas turbine patent thumbnailnew patent Axial rotor portion and turbine rotor blade for a gas turbine
A turbine rotor blade is provided with a blade root, platform adjoining it, and turbine blade on that side of the platform which faces away from the blade root, with at least one opening for feeding coolant into the turbine rotor blade interior on an underside of the blade root, which opening merges into a coolant duct. An axial rotor section for a rotor is provided, having an outer circumferential surface adjoining two end-side first side surfaces with rotor blade holding grooves distributed over the circumference and extending along an axial direction, wherein a turbine rotor blade is arranged in every holding groove, wherein a multiplicity of sealing elements are at the side of a side surface of the rotor section, and lie opposite the end sides of blade roots to form a gap.
Siemens Aktiengesellschaft
03/26/15
20150086352
 Gas turbine engine inlet assembly and  making same patent thumbnailnew patent Gas turbine engine inlet assembly and making same
A method of fabricating an inlet assembly for a gas turbine engine, the method including defining an intake duct of the inlet assembly between first and second space apart inlet case portions, locating at least one strut across the intake duct, each strut having a proximal end made integral to the first inlet case portion and an opposed distal end engaged in a respective strut-receiving aperture defined through the second inlet case portion, while maintaining the distal end of each strut in the respective strut-receiving aperture, adjusting the relative position of the first inlet case portion and the second inlet case portion until a predetermined throat dimension of the intake duct is obtained, and locking the adjusted relative position by attaching the second inlet case portion to each strut. An inlet assembly and gas turbine engine with inlet assembly as also disclosed..
Pratt & Whitney Canada Corp.
03/26/15
20150086339
 Diffuser with strut-induced vortex mixing patent thumbnailnew patent Diffuser with strut-induced vortex mixing
A gas turbine engine includes inner and outer shrouds forming an annular gas path, and a plurality of struts connecting the inner shroud to the outer shroud. Airfoil shaped shields surround the struts, and each of the shields include a main body having an upstream leading edge defining a chordal axis extending in a downstream axial direction from the leading edge toward a downstream end of the shield.
03/26/15
20150086334
 Centrifugal compressor provided with a marker for measuring wear and a  monitoring wear using said marker patent thumbnailnew patent Centrifugal compressor provided with a marker for measuring wear and a monitoring wear using said marker
A device and method for precise measurement of erosion of compressors, without removing an engine, and with easy positioning. A centrifugal compressor of a gas turbine with a radial air inlet includes an impeller including blades and a casing for an air stream to flow in the blades of the impeller.
Turbomeca
03/26/15
20150086330
 Gas turbine casing load sharing mechanism patent thumbnailnew patent Gas turbine casing load sharing mechanism
A turbine system is provided having a first turbine casing and a second turbine casing, the first and second turbine casings together defining an inner wall. The turbine system further includes a first attachment flange extending from a surface of the first turbine casing within the inner wall and a second attachment flange extending from a surface of the second turbine casing within the inner wall.
General Electric Company
03/26/15
20150083169
 System for washing an aero gas turbine engine patent thumbnailnew patent System for washing an aero gas turbine engine
A wash system includes a wash unit associated with a mobile unit for providing wash fluid, one or more nozzles for streamline injecting wash fluid provided by the wash unit directly into an engine inlet, and an articulating arm for use in positioning the one or more nozzles. The wash unit is physically spaced from a surface of the engine inlet cowling during a washing process.
Ecoservices, Llc
03/26/15
20150083165
 Suspensions of inorganic cleaning agents patent thumbnailnew patent Suspensions of inorganic cleaning agents
Methods for on-line cleaning hot parts of a gas turbine during its operation are provided. A cleaning agent composition is injected into a hot gas path of the gas turbine, and includes a liquid carrier and a descaling material suspending in the liquid carrier.
General Electric Company
03/26/15
20150082808
 Gas turbine engines with turbine airfoil cooling patent thumbnailnew patent Gas turbine engines with turbine airfoil cooling
An airfoil for a gas turbine engine is provided. The airfoil includes a body with a leading edge, a trailing edge, a first side wall extending between the leading edge and the trailing edge, and a second side wall extending between the leading edge and the trailing edge.
Honeywell International Inc.
03/26/15
20150082807
 Carrier ring patent thumbnailnew patent Carrier ring
The invention relates to a carrier ring for a high-pressure gas turbine of a gas turbine plant, which has a high-pressure combustion chamber upstream of the high-pressure gas turbine, a compressor upstream of the high-pressure combustion chamber, a low-pressure combustion chamber downstream of the high-pressure gas turbine, a low-pressure gas turbine downstream of the low-pressure combustion chamber, and a rotor that carries rotor blades for the compressor, for the high-pressure gas turbine, and for the low-pressure gas turbine. The carrier ring carries guide blades and/or heat shields of the high-pressure gas turbine and can be fastened to the high-pressure combustion chamber.
Alstom Technology Ltd.
03/26/15
20150082803
new patent

Method for operating a combined-cycle power plant with cogeneration, and a combined-cycle power plant for carrying out the method


The invention relates to a method for operation of a combined-cycle power plant with cogeneration, in which method combustion air is inducted in at least one gas turbine, and in which method the exhaust gas emerging from the at least one turbine is passed through a heat recovery steam generator (hrsg) in order to generate steam. The electricity production can be decoupled from the steam production in order to restrict the electricity production while the heat provided by steam extraction remains at a constant level.
Alstom Technology Ltd
03/26/15
20150082801
new patent

Gas turbine and method to operate the gas turbine


It is proposed a gas turbine and a method to operate the gas turbine. A fluid is supplied to the gas turbine by means of fluid paths.
Alstom Technology Ltd.
03/26/15
20150082798
new patent

Component for attaching to a wall


A tile for attaching to a wall of a gas turbine engine. The tile has a main body.
Rolls-royce Plc
03/26/15
20150082796
new patent

Burner


A burner of a gas turbine extending along an axis is provided having in axial order: a swirler section, mixing section, outlet section, and main combustion zone. The swirler section has swirler vanes to swirl a stream of fuel and oxygen containing gas entering therein in a circumferential direction.
Siemens Aktiengesellschaft
03/26/15
20150082795
new patent

Internally cooled transition duct aft frame


An aft frame for a transition duct of a gas turbine combustor includes a main body having an outer rail, an inner rail, a first side rail circumferentially separated from an opposing second side rail, a forward portion, an aft portion and an outer surface. An inlet port extends through the outer surface and an exhaust port extends through the forward portion.
General Electric Company
03/26/15
20150082794
new patent

Apparatus for acoustic damping and operational control of damping, cooling, and emissions in a gas turbine engine


Acoustic damping resonators (60, 62, 76, 78) formed in pockets (32) between reinforcing ribs (30) in a grid of ribs on the outer surface of a wall (74) surrounding a combustion gas flow path (18). Each resonator has a perforated cover plate (64a-c) spanning between sides formed by the ribs (30).
03/26/15
20150082770
new patent

Dual-fuel burning gas turbine combustor


A dual-fuel burning gas turbine combustor having a diffusive combustion burner to burn a liquid fuel and a gaseous fuel placed at the axis of the gas turbine combustor and a plurality of pre-mixing combustion burners to burn a liquid fuel and a gaseous fuel placed on an outer circumferential side of the diffusive combustion burner, each pre-mixing combustion burner having a liquid fuel nozzle, a plurality of gaseous fuel spray holes, a plurality of air holes, and a pre-mixing chamber to mix gaseous fuel and air, wherein each pre-mixing combustion burner has a double pipe sleeve at a connected portion between end cover and the pre-mixing combustion burner, and the double pipe sleeve has an inner sleeve having a gaseous fuel flow path, an outer sleeve positioned on an outer circumferential side of the inner sleeve, and a circular spacing formed between the inner sleeve and the outer sleeve.. .
Mitsubishi Hitachi Power Systems, Ltd.
03/26/15
20150082768
new patent

Systems and methods for facilitating substantially uniform ventilation airflow inside an engine enclosure of a gas turbine engine


A diffuser assembly for a ventilation system is disclosed herein. The diffuser assembly may include a boundary defining an interior of the diffuser assembly.
General Electric Company
03/26/15
20150082767
new patent

Passive cooling system for control valve actuators


The present application provides a passive control valve actuator cooling system to provide a flow of cooling air to a control valve actuator used with a gas turbine engine. The passive control valve actuator cooling system may include a turbine enclosure with a negative pressure therein, a radiation shield with a number of radiation shield outlets and the control valve actuator positioned therein, and a cooling air line extending from outside of the turbine enclosure to the radiation shield such that the negative pressure within the turbine enclosure pulls the flow of cooling air into and through the radiation shield so as to cool the control valve actuator..
General Electric Company
03/19/15
20150081121

System and controlling operation of a gas turbine based power plant


A system for controlling a gas turbine power plant includes a plurality of sensors configured to transmit signals indicative of one or more operating parameters of the gas turbine, and a control system in electronic communication with each sensor. The control system is configured to compute cumulative wear for one or more hardware components of the gas turbine based at least in part on the signals.
General Electric Company
03/19/15
20150078915

Piloted nut


The present disclosure relates generally to a piloted nut. The piloted nut may be used on a tie-shaft to apply an axial load to a rotor.
United Technologies Corporation
03/19/15
20150078908

Gas turbine engine for aircraft engine


A gas turbine stator for aircraft engines has a blade array with a plurality of blades constituted by a series of first blades and a series of second blades with different geometries; the array is formed by a plurality of sectors, each having an inner portion, an outer portion, at least one first blade and a least one second blade, and each defined by a body made in one piece; a single first blade is alternated with a single second blade for the entire circumference of the stator.. .
03/19/15
20150078905

Turbine rotor for an exhaust gas turbine and producing the turbine rotor


A turbine rotor for an exhaust gas turbine has a turbine rotor wheel made of a highly heat-resistant metal alloy and a rotor shaft made of steel. A rotor wheel hub and a rotor shaft end are connected to each other in a metallurgical bond by way of a solder connection.
Continental Automotive Gmbh
03/19/15
20150078901

Threaded shank, connection assembly and gas turbine engine for improved fatigue life of threads


A threaded shank for engaging with a threaded further component is provided herein, the further component having a cylindrical first thread with a uniform first thread pitch and a uniform first thread angle, the threaded shank including a second thread with a uniform second thread pitch and a uniform second thread angle and including a third thread with a uniform third thread pitch and a uniform third thread angle along an axial expanse of the third thread. The first thread angle and the second thread angle and the third thread angle being substantially identical, the first thread pitch and the second thread pitch and the third thread pitch being substantially identical, wherein the second thread and the third thread are spaced apart axially by a thread-free region, a second thread helix and a third thread helix have an axial offset to one another..
Siemens Aktiengesellschaft
03/19/15
20150078887

Disc shaft center adjusting mechanism in gas turbine


In a disc axis adjusting mechanism in a gas turbine, the gas turbine has an exhaust gas diffuser provided between a casing wall and a bearing case which are connected to a downstream side of a turbine, a plurality of struts provided at intervals in a circumferential direction, and strut covers coupling an outer diffuser and an inner diffuser of the exhaust gas diffuser so as to cover the struts, and the mechanism comprises: a plurality of air introduction holes formed in the casing wall so as to allow the interior and exterior of the wall to communicate with each other; a sensor unit configured to detect a parameter corresponding to the thermal elongation of each of the struts; and a flow rate adjustor configured to adjust the flow rate of air flowing through each of the air introduction holes based on a detection value detected by the sensor unit.. .
Mitsubishi Heavy Industries, Ltd.
03/19/15
20150076352

Infrared spectrometer measurement of droplets collected from an oil mist in a breather pipe of a gas turbine


A method for analysing a droplet fraction of an oil mist sample of a gas turbine is provided. A collecting device collects the oil mist sample, wherein the collecting device is arranged within a breather pipe which is coupled to the gas turbine such that oil mist is flowing through the breather pipe.
Siemens Aktiengesellschaft
03/19/15
20150076251

System for injecting fuel in a gas turbine combustor


A combustion system uses a fuel nozzle with an inner wall having a fuel inlet in fluid communication with a fuel outlet in a fuel cartridge. The inner wall defines a mounting location for inserting the fuel cartridge.
General Electric Company
03/19/15
20150075178

Gas turbine engines with turbine rotor blades having improved platform edges


A turbine rotor blade is provided. The turbine rotor blade includes a root, a platform coupled to the root, and an airfoil extending from the platform.
Honeywell International Inc.
03/19/15
20150075176

Connecting gas turbine engine annular members


A gas turbine engine assembly includes first and second annular members having different first and second thermal expansion coefficients connected together with dual arm v brackets. Brackets include first and second arms angularly spaced apart from a bracket centerline and extending axially away from bracket bases attached to a first one of the first and second annular members.
General Electric Company
03/19/15
20150075174

Combustor and fuel supply and converting fuel nozzle for advanced humid air turbine


A fuel control device and method of a gas turbine combustor, for advanced humid air turbines, in which plural combustion units comprising plural fuel nozzles for supplying fuel and plural air nozzles for supplying air for combustion are provided. A part of the plural combustion units are more excellent in flame stabilizing performance than the other combustion units.
Mitsubishi Hitachi Power Systems, Ltd.
03/19/15
20150075170

Method and system for augmenting the detection reliability of secondary flame detectors in a gas turbine


Systems and methods for operating a gas turbine combustion system by generating a flame detection signal are provided. A set of modeled parameters expected when there is a flame in a secondary combustion zone is calculated.
General Electric Company
03/19/15
20150075133

Gas turbine engine system that uses organic medium


A gas turbine engine system is provided which achieves high efficiency while using sunlight as a heat source. In a gas turbine engine system including: a compressor configured to compress a first working medium; a heater configured to heat the compressed first working medium by an external heat source; a turbine configured to output power from the first working medium; and an intermediate cooler provided at the compressor and configured to cool the first working medium compressed by a low-pressure compression part of the compressor and supply the first working medium to a high-pressure compression part of the compressor, an organic rankine cycle engine using, as a second working medium, an organic substance which is a cooling medium of the intermediate cooler is provided..
Kawasaki Jukogyo Kabushiki Kaisha
03/19/15
20150075131

Exhaust collector with curved side panel


An exhaust collector for a gas turbine engine is disclosed. The exhaust collector includes a front panel, a rear panel, and a side panel.
Solar Turbines Incorporated
03/12/15
20150071777

Turbine guide wheel


A turbine stator wheel of a gas turbine with a plurality of stator vanes spaced apart around the circumference is provided. Two adjacent stator vanes form a passage each between the suction side of the one stator vane and the pressure side of the other stator vane starting from the vane trailing edge, which includes a constant passage portion in which the passage has a substantially constant passage cross-section.
Rolls-royce Deutschland Ltd & Co Kg
03/12/15
20150071772

Method for producing and restoring ceramic heat insulation coatings in gas turbines and associated gas turbine


Through the use of different ceramic heat insulation coatings (7, 13) on turbine blades, it is possible to produce or restore different configurations of gas turbines, which are then optimized for a respective baseload operation application or peak load operation application. Differences in the sprayed-on heat insulation coatings (7, 13) can be generated by means of a different material composition of the powder, for example zirconium oxide, by means of a different number of layers (10), by means of different coating thicknesses and/or by means of different porosities..
Siemens Aktiengesellschaft
03/12/15
20150071769

Method for disassembly and assembly of a rotor of a gas turbine


A method for disassembly of a rotor, in particular the front rotor of a gas turbine with a housing and a channel which diverges in a direction of flow and in which the rotor is arranged, is disclosed. An embodiment of the method includes axially displacing an outer sealing ring that is radially opposite the rotor, and whose minimum inside diameter is smaller than the maximum outside diameter of the rotor, against the direction of flow.
Mtu Aero Engines Ag
03/12/15
20150071764

Turbocompound bearing for attaching a turbocompound system to an internal combustion engine


A turbocompound bearing for attaching a turbocompound system to an internal combustion engine comprises an exhaust gas turbine having a turbine shaft mounted in a turbine bearing housing, a hydrodynamic clutch having a clutch shaft mounted in a clutch bearing housing, and having a connector for attachment of the internal combustion engine. The invention is characterized in that the connector is formed by a plate-shaped base support which has at least one first centering surface on which the clutch bearing housing is oriented, and the plate-shaped base support and/or the clutch bearing housing has at least one second centering surface on which the turbine bearing housing is oriented..
Voith Patent Gmbh
03/12/15
20150071761

Sealing arrangement for a nozzle guide vane and gas turbine


A nozzle guide vane support arrangement including a platform portion of a nozzle guide vane at a trailing edge is provided, the platform portion having a platform wall including a first platform wall portion and a second platform wall portion. A working fluid interaction surface and a cooling surface at least partly limit an inner cavity of the platform portion in which a cooling fluid is leadable.
Siemens Aktiengesellschaft
03/12/15
20150069763

Load cover


A load cover for a coupling between a rotor of a gas turbine engine and a generator is provided. The load cover includes a guard which is disposed about the rotor and a baffle disposed around the guard to form an annulus of circumferentially increasing area.
General Electric Company
03/12/15
20150069148

Integrated heat shield


A fuel injector for a gas turbine engine includes a nozzle tip assembly having a substantially monolithically formed nozzle body. The nozzle body has an annular outlet chamber for issuing a spray from the nozzle tip.
Delavan Inc
03/12/15
20150068294

Flame monitoring of a gas turbine combustor using multiple dynamic pressure sensors in multiple combustors


The state of a flame in a subject combustor of a gas turbine engine is acoustically monitored using a dynamic pressure sensor within the subject combustor and one or more additional sensors in nearby combustors. Dynamic pressure sensor output signals from the sensors are cross correlated to identify acoustic oscillations generated by a flame in the subject combustor and received by the sensors.
Siemens Energy, Inc.
03/12/15
20150068217

Inlet bleed heat system and related a compact gas turbine inlet


An inlet system for a gas turbine includes an inlet air duct; a silencer disposed in the inlet air duct, the silencer including a plurality of panels with spaces between the panels; and a conduit with orifices disposed to inject inlet bleed heat into each of the spaces. A method of conditioning inlet air for a gas turbine includes flowing air through spaces between panels of a silencer in an inlet air duct of the gas turbine, and injecting inlet bleed heat through orifices and into each of the spaces..
General Electric Company
03/12/15
20150068215

Two-shaft gas turbine


The 2-shaft gas turbine having a gas generator and a power turbine includes: means for measuring control parameters of the compressor; and a controller configured to set, in accordance with the degree of the degradation of the compressor efficiency computed from the measured control parameters, a target speed of the gas generator at a level lower than a target speed in a state where degradation of the compressor efficiency has not occurred, and to control the rotating speed of the gas generator on the basis of a difference between the target speed thus set and an actual rotating speed.. .
03/12/15
20150068214

Low thermal mass joint


A gas turbine engine includes a tangential on-board injector (tobi) fluidly connected to a compressor section. A diffuser case structurally supports a combustor section and the tangential on-board injector via at least one low thermal mass joint..
United Technologies Corporation
03/12/15
20150068213

Method of cooling a gas turbine engine


A method of cooling a gas turbine engine is provided. The method includes removing a load from the gas turbine engine.
General Electric Company
03/12/15
20150068211

Radial midframe baffle for can-annular combustor arrangement having tangentially oriented combustor cans


A can-annular gas turbine engine combustion arrangement (10), including: a combustor can (12) comprising a combustor inlet (38) and a combustor outlet circumferentially and axially offset from the combustor inlet; an outer casing (24) defining a plenum (22) in which the combustor can is disposed; and baffles (70) configured to divide the plenum into radial sectors (72) and configured to inhibit circumferential motion of compressed air (16) within the plenum.. .
03/12/15
20150068210

Tube fed tangential on-board injector for gas turbine engine


A tangential on-board injector assembly for a gas turbine engine includes an annular housing including a plenum. A plurality of discrete tubes is fluidly connected to the plenum and is configured to provide a cooling fluid to the annular housing..
United Technologies Corporation
03/05/15
20150066418

Method and system for advising operator action


A system and computer-implemented method for monitoring and diagnosing anomalies in a wheel-space of a gas turbine is implemented using a computer device coupled to a user interface and a memory device and includes storing a plurality rule sets in the memory device, the rule sets relative to the wheel-space, the rule sets including at least one rule expressed as a relational expression of a real-time data output relative to a real-time data input, the relational expression being specific to a temperature of the wheel-space. The method also includes receiving real-time and historical data inputs from a condition monitoring system associated with the gas turbine, the data inputs relating to sources providing heat to the wheel-space and estimating a wheel-space temperature value using the inputs relating to a temperature of the wheel-space..
Nuovo Pignone Srl


Popular terms: [SEARCH]

Gas Turbine topics: Gas Turbine, Gas Turbine Engine, Internal Combustion Engine, Distributed, Combustion, Uv Radiation, Exhaust Gas, Circulation, Downstream

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