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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


Power generation system and method of operating power generation system

Mitsubishi Hitachi Power Systems

Power generation system and method of operating power generation system

Component of a gas turbine engine and method of detecting a crack therein

Pratt & Whitney Canada Corp.

Component of a gas turbine engine and method of detecting a crack therein

Component of a gas turbine engine and method of detecting a crack therein

General Electric

On-line monitoring of hot gas path components of a gas turbine


Date/App# patent app List of recent Gas Turbine-related patents
08/27/15
20150244296 
 Electrical power generator for a gas turbine engine patent thumbnailElectrical power generator for a gas turbine engine
An aircraft electrical power generation system includes an ac generator having a rotor including a plurality of electromagnetic rotor-windings and stator including plurality of electrical stator-windings. The rotor mechanically coupled to a shaft of a gas turbine engine by transmission-system.
Rolls-royce Plc


08/27/15
20150244007 
 Power generation system and  operating power generation system patent thumbnailPower generation system and operating power generation system
A power generation system includes a fuel cell, a gas turbine, a first compressed air supply line that supplies the air from a compressor to a combustor, a second compressed air supply line that supplies compressed air from the compressor to the fuel cell, a compressed air circulating line that supplies exhausted air from the fuel cell to the combustor, a detection unit that detects ease of flow of compressed air in the fuel cell, an adjustment unit that adjusts balance between ease of flow of the compressed air in the first compressed air supply line and ease of flow of the compressed air in the second compressed air supply line.. .
Mitsubishi Hitachi Power Systems, Ltd.


08/27/15
20150241309 
 Component of a gas turbine engine and  detecting a crack therein patent thumbnailComponent of a gas turbine engine and detecting a crack therein
A component of a gas turbine engine comprises a substrate, a corrosion resistant top layer, and an intermediate corrodible layer disposed between the corrosion resistant top layer and the substrate. When corroding, the intermediate layer has a color contrasting with a color of the top layer.
Pratt & Whitney Canada Corp.


08/27/15
20150241308 
 On-line monitoring of hot gas path components of a gas turbine patent thumbnailOn-line monitoring of hot gas path components of a gas turbine
Systems and methods for on-line monitoring of hot gas path components of a gas turbine are provided. According to one embodiment of the disclosure, a system may include a camera operable to monitor one or more hot gas path components of the gas turbine and a processor communicatively coupled to the camera.
General Electric Company


08/27/15
20150241067 
 Fastened joint for a tangential on board injector patent thumbnailFastened joint for a tangential on board injector
A combustor assembly for a gas turbine engine includes a combustor shell, a tobi, a case, and a joint for securing the combustor shell, tobi and case together. The joint has a combustor flange integral to the combustor shell.
United Technologies Corporation


08/27/15
20150241066 
 System and  control of combustion dynamics in combustion system patent thumbnailSystem and control of combustion dynamics in combustion system
A system includes a gas turbine engine that includes a first combustor and a second combustor. The first combustor includes a first oxidant flow path and a first perforated structure comprising a first plurality of oxidant ports, wherein the first perforated structure is disposed in the first oxidant flow path.
General Electric Company


08/27/15
20150241061 
 Heat shield with a supporting structure and  cooling the supporting structure patent thumbnailHeat shield with a supporting structure and cooling the supporting structure
A heat shield of a gas turbine: a supporting structure (16), to which heat shield tiles are fastened releasably by tile holders (2, 2a, 2b); the heat shield permits cooling of the supporting structure. Each tile has a cold side facing the supporting structure (16) and an opposite hot side that can be acted upon with a hot medium; each tile holder (2, 2a, 2b) has a holding section (3) for fastening to a heat shield tile and a fastening section (4) for fastening to the supporting structure (16).
Siemens Aktiengesellschaft


08/27/15
20150240745 
 Angled reverse core gas turbine engine with widened nozzle patent thumbnailAngled reverse core gas turbine engine with widened nozzle
A propulsion system for an aircraft includes a furcated nozzle that has at least a first duct that extends from a first propulsor to a first trailing end duct opening and a second duct that extends from a second propulsor to a second trailing end duct opening.. .
United Technologies Corporation


08/27/15
20150240726 
 Model-based feed forward approach to coordinated air-fuel control on a gas turbine patent thumbnailModel-based feed forward approach to coordinated air-fuel control on a gas turbine
Presented herein are turbine machines, turbine control systems, methods, and computer-readable storage devices for controlling turbines including a compressor, a combustion system, and a turbine section comprising a turbine operating at an initial turbine output while using initial parameter values for the respective control parameters of the turbine. The techniques involve, for respective selected control parameters, selecting an adjustment of the initial parameter value of the selected control parameter, and predicting a predicted turbine output of the turbine operated using the adjustment of the selected control parameter and the initial parameter values for other control parameters; comparing the predicted turbine outputs for the adjustments of the respective control parameters to select, from the control parameters, a target control parameter having a target adjustment that results in the target turbine output; and operating the turbine with the target adjustment of the target control parameter..
General Electric Company


08/27/15
20150240725 
 Gas turbine engine with forward moment arm patent thumbnailGas turbine engine with forward moment arm
A gas turbine engine includes a plurality of fan blades rotatable about an axis, wherein each of the plurality of fan blades includes a leading edge. The gas turbine engine also includes turbine section includes an aft most turbine blade having a trailing edge and a geared architecture driven by the turbine section for rotating the plurality of fan blades about the axis.
United Technologies Corporation


08/27/15
20150240724 

Combustor seal mistake-proofing for a gas turbine engine


A combustor seal for use between a downstream end of a combustor and a turbine vane includes a seal body and a plurality of seal alignment features. The plurality of seal alignment features projects from the seal body.
United Technologies Corporation


08/27/15
20150240723 

Bore basket for a gas powered turbine


A bore basket for a gas turbine engine includes two cylinders that guide a cooling flow through a bore opening. The cylinder's define an axially aligned gap that further directs fluid flow..
United Technologies Corporation


08/27/15
20150240722 

Single phase micro/mini channel heat exchangers for gas turbine intercooling


A gas turbine engine heat exchange system including a first multi-width channel heat exchanger (mwchx) configured to transfer heat between a first air stream and a heat transfer fluid. The first mwchx includes a first plurality of air-passage mini-channels configured to allow passage of the first air stream therethrough, where each air-passage channel has an air-channel width and an air-channel length greater than the air-channel width.
Rolls-royce North American Technologies, Inc.


08/27/15
20150240721 

Aircraft components with porous portion and methods of making


A component including a porous portion which may be permeable or impermeable to air, and a method for making. In one example, the component is a cooled wall segment for a gas turbine engine, including a body defining a contact surface configured to be in contact with circulating hot gas and an outer surface configured to be in contact with cooling air.
Pratt & Whitney Canada Corp.


08/27/15
20150240720 

Inlet air filter arrangement, inlet air filter cartridge, and equipment for supporting inlet air filter cartridges for a gas turbine or a combustion turbine


An inlet air filter arrangement for a gas turbine or a combustion turbine includes a housing with an inlet side and an outlet side separated by a planar tubesheet including multiple tubesheet openings. Each multiple cylindrical filter cartridge includes a symmetry axis, an open end, and a closed end.
Amec Foster Wheeler North America Corp.


08/27/15
20150240719 

Gas turbine efficiency and regulation speed improvements using supplementary air system continuous and storage systems and methods of using the same


The present invention discloses a novel apparatus and methods for augmenting the power of a gas turbine engine, improving gas turbine engine operation, and reducing the response time necessary to meet changing demands of a power plant. Improvements in power augmentation and engine operation include additional heated compressed air injection from a power augmentation system and a motor-generator in selective operation with the power augmentation system..
Powerphase Llc


08/27/15
20150240717 

Increasing combustibility of low btu natural gas


A system and methods for increasing a combustibility of a low btu natural gas are provided herein. The method includes increasing the adiabatic flame temperature of the low btu natural gas using heavy hydrocarbons, wherein the heavy hydrocarbons include compounds with a carbon number of at least two.

08/27/15
20150240713 

Aero boost - gas turbine energy supplementing systems and efficient inlet cooling and heating, and methods of making and using the same


The invention relates generally to electrical power systems, including generating capacity of a gas turbine, and more specifically to pressurized air injection that is useful for providing additional electrical power during periods of peak electrical power demand from a gas turbine system power plant, as well as to inlet heating to allow increased engine turn down during periods of reduced electrical demand.. .
Powerphase Llc


08/27/15
20150240712 

Mid-turbine duct for geared gas turbine engine


A mid-turbine vaned duct comprises a duct upstream end to abut a downstream end of an upstream turbine rotor. A duct downstream end abuts an upstream end of a downstream turbine rotor.
United Technologies Corporation


08/27/15
20150240662 

Case assembly for a gas turbine engine


A case for a gas turbine engine includes an integrated hpc diffuser case operable to contain a combustor section and a portion of a high pressure compressor.. .
United Technologies Corporation


08/27/15
20150240661 

Repair or remanufacture of liner panels for a gas turbine engine


A method of remanufacturing a liner panel for a gas turbine engine includes removing a bushing from a damaged component; and molding the bushing with a material charge. A liner panel for a gas turbine engine includes a forward fan exit case liner panel with a donor bushing from a damaged forward fan exit case liner panel.
United Technologies Corporation


08/27/15
20150240660 

Buffer airflow to bearing compartment


A seal support and duct assembly of a gas turbine engine includes a seal support housing disposed about a central axis, a duct housing attached to the seal support housing, the duct housing and the seal support housing defining the seal support and duct assembly, an outer annular cavity, an inlet that supplies the outer annular cavity with cooling buffer air, an inner annular cavity disposed radially inward of the outer annular cavity, a first plurality of outlets that provide the cooling buffer air from the outer annular cavity to the inner annular cavity, and a second plurality of outlets that provide the cooling buffer air from the inner annular cavity to an area surrounding a bearing compartment.. .
United Technologies Corporation


08/27/15
20150240658 

Carbon nanotubes for increasing vibration damping in polymer matrix composite containment cases for aircraft engines


A gas turbine engine has a fan section having a fan with a plurality of fan blades and a containment case surrounding the fan blades. The containment case is formed from a polymer matrix material containing carbon, glass and aramid fibers, and carbon nanotubes for improving vibration damping..
United Technologies Corporation


08/27/15
20150240656 

Exhaust gas turbine and controlling the turbine


In an exhaust gas turbine with a guide section for the exhaust gas turbine comprising a flow-through duct for conducting exhaust gas through the exhaust gas guide section, wherein the flow-through duct includes a wheel chamber in which a turbine wheel is rotatably supported and wherein, downstream of the wheel chamber, the flow-through duct has an outlet portion and upstream of the wheel chamber, the flow-through duct has an inlet portion with a bypass duct being formed in the exhaust gas guide section for by-passing the wheel chamber, the by-pass duct forms an annular opening adjacent the turbine wheel for directing by-pass exhaust gas into the exhaust gas outlet portion in an annular flow pattern along the outlet portion duct wall.. .
Ihi Charging Systems International Gmbh


08/27/15
20150240644 

Thermal shields for gas turbine rotor


A turbomachine including a rotor having an axis and a plurality of disks positioned adjacent to each other in the axial direction, each disk including opposing axially facing surfaces and a circumferentially extending radially facing surface located between the axially facing surfaces. At least one row of blades is positioned on each of the disks, and the blades include an airfoil extending radially outward from the disk a non-segmented circumferentially continuous ring structure includes an outer rim defining a thermal barrier extending axially in overlapping relation over a portion of the radially facing surface of at least one disk, and extending to a location adjacent to a blade on the disk a compliant element is located between a radially inner circumferential portion of the ring structure and a flange structure that extends axially from an axially facing surface of the disk.
Siemens Energy, Inc.


08/27/15
20150239568 

Pylon shape with geared turbofan for structural stiffness


A gas turbine includes a mounting structure for mounting the engine to a pylon. A propulsor section includes a fan having a fan diameter.
United Technologies Corporation


08/27/15
20150239033 

Clipping tool


The present disclosure provides a clipping tool for clipping flash from a component e.g. A gas turbine aerofoil body.
Rolls-royce Plc


08/27/15
20150239010 

Method of forming an abradable coating for a gas turbine engine


A method of forming an abradable coating on a gas turbine engine component comprising, in sequence: placing dry lubricant particles and trapping particles in a channel having a spraying end and containing a gas; causing at least one shockwave in the gas to travel in the channel toward the spraying end, the at least one shockwave causing the dry lubricant particles and the trapping particles to travel in the channel with it, the at least one shockwave reducing interparticle spacing and increasing particles density; directing a resulting flow of the dry lubricant particles and the trapping particles from the spraying end at a supersonic velocity to impact the component; and then plastically deforming the trapping particles upon impacting the component with the resulting flow thereby trapping the dry lubricant particles with the deformed trapping particles onto the component to provide the abradable coating.. .
Pratt & Whitney Canada Corp.


08/20/15
20150233789 

Method and system for predicting the serviceable life of a component


The remaining serviceable life of a critical rotating component of a gas turbine engine can be predicted using a remote detection component. The remote detection component is inspected to determine whether a crack has formed at a dedicated crack-initiation feature.
Rolls-royce Plc


08/20/15
20150233582 

Gas flow path for a gas turbine engine


A duct arrangement in a can annular gas turbine engine. The gas turbine engine has a gas delivery structure for delivering gases from a plurality of combustors to an annular chamber that extends circumferentially and is oriented concentric to a gas turbine engine longitudinal axis for delivering the gas flow to a first row of blades a gas flow path is formed by the duct arrangement between a respective combustor and the annular chamber for conveying gases from each combustor to the first row of turbine blades the duct arrangement includes at least one straight section having a centerline that is misaligned with a centerline of the combustor..
Siemens Energy, Inc.


08/20/15
20150233581 

Fuel manifold for a gas turbine engine


A pigtail assembly of a fuel supply manifold assembly for a gas turbine engine, includes a first coupling assembly defined along a first axis; a second coupling assembly defined along a second axis, the second axis is parallel to the first axis; a first conduit between the first coupling assembly and the second coupling assembly; a third coupling assembly that defines a third axis, the third axis is non-parallel to the second axis; and a second conduit between the second coupling assembly and the third coupling assembly.. .
United Technologies Corporation


08/20/15
20150233580 

Gas turbine combustion acoustic damping system


A gas turbine may include a rotatable shaft, a compressor disposed about the rotatable shaft and configured to output compressed air, and a combustor disposed about the rotatable shaft. The combustor may be configured to receive the compressed air and output high temperature compressed gas.
Dresser-rand Company


08/20/15
20150233323 

Gas turbine engine airfoil


A gas turbine engine includes a fan section, a compressor section and a turbine section, one of which includes an airfoil. The airfoil includes pressure and suction sides extending in a radial direction from a 0% span position at an inner flow path location to a 100% span position at an airfoil tip.
United Technologies Corporation


08/20/15
20150233303 

Method for setting a gear ratio of a fan drive gear system of a gas turbine engine


A gas turbine engine includes a fan section that includes a fan rotatable about an axis of rotation of the gas turbine engine. A speed reduction device is connected to the fan.
United Technologies Corporation


08/20/15
20150233302 

Operability geared turbofan engine including compressor section variable guide vanes


A gas turbine engine has a fan which includes a plurality of fan blades that are rotatable about an axis, and a compressor section, where the combustor section includes a first compressor and a second compressor aft of the first compressor. At least one first variable guide vane controls operation of the first compressor and at least one second variable guide vane controls operation of the second compressor.
United Technologies Corporation


08/20/15
20150233301 

Method for setting a gear ratio of a fan drive gear system of a gas turbine engine


A gas turbine engine includes a fan section including a fan rotatable about an axis of rotation of the gas turbine engine. A speed reduction device is in communication with the fan.
United Technologies Corporation


08/20/15
20150233300 

Geared gas turbine engine accessory gearbox


A gas turbine engine includes a gearbox. The gearbox includes a housing at a forward part of a core compartment of a gas turbine engine.
United Technologies Corporation


08/20/15
20150233298 

Reduction in jet flap interaction noise with geared turbine engine


A turbine engine system mounted on an aircraft wing includes a gas turbine engine having a spool, a turbine coupled with the spool, a fan coupled to be rotated about an axis through the spool, and a gear assembly coupled between the fan and spool such that rotation of the spool results in rotation of the fan at a different speed than the spool. The gas turbine engine is operable to discharge a jet plume that interacts with a flap of the aircraft wing.
United Technologies Corporation


08/20/15
20150233297 

Fuel manifold fitting with integral support for a gas turbine engine


A manifold fitting for a gas turbine engine includes a manifold tee including a first manifold port, a second manifold port and a pigtail port. A support extends from the manifold tee.
United Technologies Corporation


08/20/15
20150233296 

Gas turbine energy supplementing systems and heating systems, and methods of making and using the same


Electrical power systems, including generating capacity of a gas turbine, where additional electrical power is generated utilizing a separately fueled system during periods of peak electrical power demand.. .

08/20/15
20150233295 

Split-zone flow metering t-tube


A gas turbine engine includes a core engine that has a compressor section, a combustor section and a turbine section. A thermal management system is configured to receive a cooling stream.
United Technologies Corporation


08/20/15
20150233293 

Annular spring for a bearing assembly of a gas turbine engine


An annular spring for a bearing assembly of gas turbine engine is provided. The annular spring includes a multiple of ligaments between an inner support and an outer support..
United Technologies Corporation


08/20/15
20150233264 

Retention of damping media


An example method of assembling a particle damped gas turbine engine component according to an exemplary aspect of the present disclosure includes, among other things, holding damping media within a cavity of a gas turbine engine component using magnetic force.. .
United Technologies Corporation


08/20/15
20150233262 

Gas turbine engine


A fan containment system for fitment around an array of radially extending fan blades mounted on a hub in an axial gas turbine engine, including: a fan case having an annular casing element for encircling an array of fan blades and an annular fan track liner lining a radially inner side of the casing element, including a first fan track liner panel positioned circumferentially adjacent a second fan track liner panel. An engagement arrangement engages the first fan track liner panel to the second, extending along at least a portion of adjacent sides of the liner panels, and is configured and the liner panels are shaped such that axial movement of the first fan track liner panel by a distance less than the length of the engagement arrangement, being measured in a direction parallel to the adjacent sides of the liner panels, disengages the first liner panel from the second..
Rolls-royce Plc


08/20/15
20150233261 

Machine cavity seal


There is disclosed a seal assembly (32) for a machine such as a gas turbine engine. The seal assembly has a support structure (38) to which a resiliently deformable seal member (34) is mounted.
Rolls-royce Plc


08/20/15
20150233259 

Fan blade tall dovetail for individually bladed rotors


A blade has an airfoil extending radially outwardly of a dovetail. The dovetail has edges that will be at circumferential sides of the blade when the blade is mounted within a rotor.
United Technologies Corporation


08/20/15
20150233258 

Turbine bucket and balancing a tip shroud of a turbine bucket


The present application and the resultant patent provide a turbine bucket for a gas turbine engine. The turbine bucket may include an airfoil, a tip shroud positioned radially outward from the airfoil, and a seal rail positioned radially outward from the tip shroud and extending in a generally tangential direction from a first end to a second end of the tip shroud.
General Electric Company


08/20/15
20150233256 

Novel architectures for ultra low thermal conductivity thermal barrier coatings with improved erosion and impact properties


A thermal barrier coating system for metal components in a gas turbine engine having an ultra low thermal conductivity and high erosion resistance, comprising an oxidation-resistant bond coat formed from an aluminum rich material such as mcraly and a thermal insulating ceramic layer over the bond coat comprising a zirconium or hafnium oxide lattice structure (zro2 or hfo2) and an oxide stabilizer compound comprising one or more of the compounds ytterbium oxide (yb2o3), yttria oxide (y2o3), hafnium oxide (hfo2), lanthanum oxide (la2o3), tantalum oxide (ta2o5) or zirconium oxide (zro2). The invention includes a new method of forming the ceramic-based thermal barrier coatings using a liquid-based suspension containing microparticles comprised of at least one of the above compounds ranging in size between about 0.1 and 5 microns.
General Electric Company


08/20/15
20150233252 

Gas turbine engine airfoil


An airfoil of a turbine engine includes pressure and suction sides that extend in a radial direction from a 0% span position at an inner flow path location to a 100% span position at an airfoil tip. The airfoil has a relationship between a tangential stacking offset and a span position that is at least a third order polynomial curve that includes at least one positive and negative slope.
United Technologies Corporation


08/20/15
20150233251 

Gas turbine engine airfoil


An airfoil for a turbine engine includes pressure and suction sides that extend in a radial direction from a 0% span position at an inner flow path location to a 100% span position at an airfoil tip. The airfoil has a relationship between a stacking offset and a span position that is at least a third order polynomial curve that includes at least one positive and negative slope.
United Technologies Corporation


08/20/15
20150233250 

Gas turbine engine airfoil


An airfoil of a turbine engine includes, pressure and suction sides extending in a radial direction from a 0% span to a 100% span position. The airfoil has a relationship between a gap/chord ratio and span position that defines a curve with a gap/chord ratio of less than 0.80 from 80% span to 100% span..
United Technologies Corporation


08/13/15
20150227677 

Gas turbine engine with first turbine vane clocking


A gas turbine engine design process includes the steps of determining the location of a hot streak downstream of a combustor nozzle, and determining whether it would be most beneficial to have the hot streak initially impact a pressure side of a first static turbine vane or whether it would be more beneficial to have it impact a suction side. A location is designed for the first static turbine vane such that the hot streak will impact the more beneficial side of the first static turbine vane..
United Technologies Corporation


08/13/15
20150227121 

Method for controlling and/or regulating a technical system in a computer-assisted manner


A computer-implemented method for controlling and/or regulating a technical system, in which actions to be carried out on the technical system are first of all determined using an action selection rule which was determined through the learning of a data-driven model and, in particular, a neural network. On the basis of these actions a numerical optimization searches for actions which are better than the original actions according to an optimization criterion.
Siemens Aktiegesellschaft


08/13/15
20150226436 

Flashback detection in gas turbine engines using distributed sensing


A distributed sensing system for detecting a flashback condition in a combustor for a gas turbine engine the distributed sensing system includes one or more strategically positioned fiber optic cables provided upstream of the combustion area in the combustor. The distributed sensing system employs rayleigh backscattering and swept-wavelength interferometry to measure temperature and reliably identify the location of the flashback condition the fiber optic cable is specially fabricated to have a high temperature resistance suitable for those temperatures existing during flashback conditions.
Siemens Energy, Inc.


08/13/15
20150226433 

Gas turbine engine combustors with effusion and impingement cooling and methods for manufacturing the same using additive manufacturing techniques


Disclosed in various exemplary embodiments are turbine engine combustors with effusion and impingement cooling and methods for manufacturing the same. In one exemplary embodiment, disclosed is a combustor for a turbine engine that includes an annular liner portion including a first metering hole positioned on a cold side annular surface of the annular liner portion and an impingement chamber positioned in the annular liner.
Honeywell International Inc.


08/13/15
20150226231 

Fan blade removal panel


A fan section of a gas turbine engine is disclosed. The fan section may comprise a fan having a hub and a plurality of blades extending radially from the hub.
United Technologies Corporation


08/13/15
20150226133 

Gas turbine load control system


A gas turbine system includes a combustor configured to combust an oxidant and a fuel in the presence of an exhaust gas diluent to produce combustion products, an oxidant supply path fluidly coupled to the combustor and configured to flow the oxidant to the combustor at an oxidant flow rate, and a turbine configured to extract work from the combustion products to produce an exhaust gas used to generate the exhaust gas diluent. The turbine causes a shaft of the gas turbine system to rotate when the work is extracted from the combustion products.
General Electric Company


08/13/15
20150226132 

Gas turbine engine ring seal


A seal assembly for a gas turbine engine includes an engine static structure. First and second members fluidly separate cavities from one another.
United Technologies Corporation


08/13/15
20150226131 

Combustor seal system for a gas turbine engine


A system for providing a seal between a combustor and a turbine vane. The system includes a flange configured to extend radially from the combustor, and a seal.
United Technologies Corporation


08/13/15
20150226130 

Gas turbine engine including vane structure and seal to control fluid leakage


A gas turbine engine includes a core engine, a fan coupled to be driven by the core engine, a first case structure around the core engine and a second case structure around the fan. The first case structure and the second case structure define a bypass passage there between.
United Technologies Corporation


08/13/15
20150226129 

Method for detecting hazardous gas concentrations within a gas turbine enclosure


A method for detecting hazardous gas concentration from an exhaust duct of a gas turbine enclosure includes aggregating multiple exhaust air samples collected via a first and a second plurality of sampling ports disposed within the exhaust duct to provide first and second aggregated exhaust air samples to primary and secondary sensors disposed outside of the exhaust duct. The method further includes sensing hazardous gas concentrations within the first and second aggregated exhaust air samples, where the primary and secondary sensors communicate signals that are indicative of the hazardous gas concentrations and functionality of the primary and secondary sensors to a computing device.
General Electric Company


08/13/15
20150226128 

Hazardous gas detection system for a gas turbine enclosure


A hazardous gas detection system includes a first and second plurality of air sampling ports in fluid communication with an exhaust duct of a gas turbine enclosure. The first and second plurality of air sampling ports is fluidly connected to a first and second outlet orifice respectfully.
General Electric Company


08/13/15
20150226125 

Combined high pressure turbine case and turbine intermediate case


A disclosed gas turbine engine includes a compressor section, a combustor section, a first turbine section and a second turbine section. An outer case structure for the gas turbine engine includes a single-piece case structure with a turbine case portion and a transition case portion.
United Technologies Corporation


08/13/15
20150226124 

Gas turbine


In a gas turbine of the invention, a first blade ring portion to which first vanes are attached and a second blade ring portion to which second vanes are attached are integrally formed to form an integrated blade ring. A second upstream pressing member is arranged on the upstream side of a second upstream isolation ring which attaches a first ring segment and a second vane stage which is arranged on the downstream side of the first ring segment to the integrated blade ring.
Mitsubishi Heavy Industries, Ltd.


08/13/15
20150226123 

Gas turbine engine buffer cooling system


A gas turbine engine according to an exemplary aspect of the present disclosure includes, among other things, a heat exchanger configured to exchange heat with a bleed airflow to provide a conditioned airflow. A bearing compartment is in fluid communication with the heat exchanger, and a first passageway communicates the conditioned airflow to the bearing compartment.
United Technologies Corporation


08/13/15
20150226122 

Sequential combustion with dilution gas mixer


The invention refers to a sequential combustor arrangement including a first burner, a first combustion chamber, a mixer for admixing a dilution gas to the hot gases leaving the first combustion chamber during operation, a second burner, and a second combustion chamber arranged sequentially in a fluid flow connection. The mixer includes a plurality of injection pipes pointing inwards from the side walls of the mixer for admixing the dilution gas to cool the hot flue gases leaving the first combustion chamber with a low pressure drop.
Alstom Technology Ltd


08/13/15
20150226119 

Sunlight-utilizing gas turbine power generation system provided with hydrogen-generating unit


A power generation system having a gas turbine engine that utilizes sunlight, includes a compressor configured to compress an air which is a working medium, a solar heater configured to heat the air compressed by the compressor, utilizing sunlight as a heat source, a hydrogen combustor configured to burn the air compressed by the compressor utilizing hydrogen as a fuel, a turbine configured to output a motive power from a high-temperature gas heated by at least one of the solar heater and the hydrogen combustor, a power generator configured to be driven by the turbine, and at least one hydrogen-generating unit configured to generate hydrogen by utilizing an output of the turbine or exhaust heat from the turbine to decompose a water, and supply the hydrogen so generated to the hydrogen combustor.. .
Kawasaki Jukogyo Kabushiki Kaisha


08/13/15
20150226118 

Oxygen transport membrane reactor based generating electric power


A carbon capture enabled system and method for generating electric power and/or fuel from methane containing sources using oxygen transport membranes by first converting the methane containing feed gas into a high pressure synthesis gas. Then, in one configuration the synthesis gas is combusted in oxy-combustion mode in oxygen transport membranes based boiler reactor operating at a pressure at least twice that of ambient pressure and the heat generated heats steam in thermally coupled steam generation tubes within the boiler reactor; the steam is expanded in steam turbine to generate power; and the carbon dioxide rich effluent leaving the boiler reactor is processed to isolate carbon.

08/13/15
20150226117 

Gas turbine engine with distributed fans


A gas generator has at least one compressor rotor, at least one gas generator turbine rotor and a combustion section. A fan drive turbine is positioned downstream of a path of the products of combustion having passed over the at least one gas generator turbine rotor.
United Technologies Corporation


08/13/15
20150226116 

Fan drive gear system module and inlet guide vane coupling mechanism


A connection assembly for securing a fan drive gear system module within a gas turbine engine includes first and second members removably secured to one another by radially extending fasteners.. .
United Technologies Corporation


08/13/15
20150226092 

Method for operating a combined cycle power plant


A method for operating a combined cycle power plant is disclosed, which has a gas turbine installation and a water-steam cycle connected to the gas turbine installation by a waste heat steam generator and has at least one steam turbine, the gas turbine installation includes a compressor, a combustion chamber, and a turbine. To cool the turbine, air compressed at the compressor is removed, cooled in at least one cooler flowed through by water, thus generating steam, and introduced into the turbine.
Alstom Technology Ltd.


08/13/15
20150226090 

Gas and steam turbine system having feed-water partial-flow degasser


A method for operating a gas and steam turbine system, in which, in an associated waste-heat steam generator, the heat contained in the expanded working medium of an associated gas turbine is utilized for the generation of steam for an associated steam turbine with at least one low-pressure part and one high-pressure part, the low-pressure part being assigned in the waste-heat steam generator a low-pressure stage with a low-pressure drum, gases dissolved in the water or steam being degassed essentially of steam for the low-pressure part from the low-pressure drum, and, to regulate degassing, steam production in the low-pressure drum being varied in that heat is displaced inside the waste-heat steam generator, the heat in the waste-heat steam generator being displaced in that less heat is extracted from the working medium in a medium-pressure stage or high-pressure stage of the gas and steam turbine system.. .
Siemens Aktiengesellschaft


08/13/15
20150226085 

Baffle with flow augmentation feature


One exemplary embodiment of this disclosure relates to a component for a gas turbine engine. The component includes a baffle provided in an internal cavity of the component.
United Technologies Corporation


08/13/15
20150226084 

Method of fabricating a composite material casing for a gas turbine engine, and a casing obtained thereby


A method of fabricating a composite material casing for a gas turbine engine, the method including making an outer shroud including a platform and a flange, making an inner shroud of smaller diameter than the outer shroud and including a platform and a flange, making a plurality of casing arms, each including a blade that is terminated at each radial end by a respective platform, arranging a plurality of openings in the respective platforms of the shrouds, each opening serving to receive a platform of a casing arm, and assembling the casing arms with the outer shroud and with the inner shroud by inserting the platforms of the casing arms in the openings of the shrouds. A composite material casing is obtained by such a method..
Herakles


08/13/15
20150226083 

Ceramic centerbody and making


A ceramic centerbody (120) for an aircraft gas turbine engine. The ceramic centerbody (120) comprises an interlaced fiber structure having fibers oriented in a substantially transverse directions and a ceramic matrix surrounding the ceramic fiber structure.
General Electric Company


08/13/15
20150226073 

Turbine vane arrangement


A guide vane arrangement of a gas turbine and a method of manufacturing a guide vane arrangement of a gas turbine are provided herein. The guide vane arrangement includes a first guide vane device including a first radially inner platform and a first number of first airfoils, and a second guide vane device including a second radially inner platform and a second number of second airfoils.
Siemens Aktiengesellschaft


08/13/15
20150226070 

Shrouded blade for a gas turbine engine


A turbine blade for a gas turbine engine comprises a platform, a blade root, an airfoil portion defining pressure and suction sides, and a shroud provided at a tip of the airfoil portion opposite to the blade root. The shroud includes a body having a radially outer face opposite to the airfoil portion, upstream and downstream generally parallel fins extending outwardly from the outer face, and two ribs extending outwardly from the outer face.
Pratt & Whitney Canada Corp.




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