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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


Gas turbine-heated high-temperature battery

Siemens Aktiengesellschaft

Gas turbine-heated high-temperature battery

Liner attaching scheme

United Technologies

Liner attaching scheme

Date/App# patent app List of recent Gas Turbine-related patents
01/22/15
20150025814
 Method and system for real time dry low nitrogen oxide (dln) and diffusion combustion monitoring patent thumbnailnew patent Method and system for real time dry low nitrogen oxide (dln) and diffusion combustion monitoring
A system and method for monitoring and diagnosing anomalies in a diffusion or dry low nox combustion system of a gas turbine, the method including storing a plurality rule sets specific to a temperature spread of the gas turbine exhaust. The method further including determining an anomaly in the performance of the gas turbine using at least one of a swirl angle of the exhaust flow, a health of a plurality of flame detectors of the gas turbine, and a transfer of the gas turbine from a first mode of operation to a second lower nox mode of operation, and recommending to an operator of the gas turbine a set of corrective actions to correct the anomaly..
Nuovo Pignone Srl
01/22/15
20150023800
 Gas turbine arrangement alleviating stresses at turbine discs and corresponding gas turbine patent thumbnailnew patent Gas turbine arrangement alleviating stresses at turbine discs and corresponding gas turbine
A turbine arrangement is provided, particularly a gas turbine arrangement, having at least one rotor blade and a turbine disc, the rotor blade having a root portion, the turbine disc having at least one slot in which the root portion of the rotor blade is secured. The slot has a plurality of opposite pairs of slot lobes and a plurality of opposite pairs of slot fillets, and a slot bottom of the slot.
Siemens Aktiengesellschaft
01/22/15
20150023780
 Liner attaching scheme patent thumbnailnew patent Liner attaching scheme
A gas turbine engine includes a liner disposed around a flowpath. The liner has a forward end, a radially outer surface, and a radially inner surface.
United Technologies Corporation
01/22/15
20150023778
 Micro gas turbine system with a pipe-shaped recuperator patent thumbnailnew patent Micro gas turbine system with a pipe-shaped recuperator
A micro gas turbine system (1) having an annular recuperator (9) for heat transfer from an exhaust gas flow (13) to an intake air flow (8). The exhaust gas flow (13) flows through radial inlets (18) into the recuperator (9) and/or out of the recuperator (9) through radial outlets (19)..
Babcock Borsig Steinmuller Gmbh
01/22/15
20150023776
 Fluid cooling arrangement for a gas turbine engine and method patent thumbnailnew patent Fluid cooling arrangement for a gas turbine engine and method
A fluid cooling arrangement in a gas turbine engine for aerospace propulsion includes an inner structure. Also included is an outer structure disposed radially outwardly of the inner structure, the outer structure and the inner structure defining a bypass flow path.
Hamilton Sundstrand Corporation
01/22/15
20150022655
 Apparatus and method using a linear array of optical sensors for imaging a rotating component of a gas turbine engine patent thumbnailnew patent Apparatus and method using a linear array of optical sensors for imaging a rotating component of a gas turbine engine
Apparatus and method using a linear array (22) of optical sensors (24) for imaging a rotating component (12) of a gas turbine engine. A viewing probe (16) may include the linear array of optical sensors disposed in the probe to acquire image data that may be made up of a series of line scans capturing views of the component passing within a field of view of the probe.
01/22/15
20150021860
 Leaf seal patent thumbnailnew patent Leaf seal
There is disclosed a leaf seal (131) for effecting a seal between first (134) and second 1) coaxial components arranged for relative rotation about a common axis. The seal is particularly suited for use in a gas turbine engine, and has: an annular pack (50) of stacked leaves (132) mountable to said first component (134) at root portions (140) of the leaves distal to the second component (51) and extending towards the second component (51) such that end edges(136) of the leaves (132) are proximal to the second component (51); and a plurality of seal elements (52) which cooperate to define an annulus extending around a surface (137) of the second component (51).
Rolls-royce Plc
01/22/15
20150021031
 Electric and fired steam generation systems patent thumbnailnew patent Electric and fired steam generation systems
Methods and systems relate to steam assisted oil recovery utilizing a fired boiler and an electric boiler, which may be disposed closer to an injection well than the fired boiler. A gas turbine produces electricity supplied to the electric boiler and flue gas exhaust that may input into the fired boiler.
Conocophillips Company
01/22/15
20150020531
 Gas turbine-heated high-temperature battery patent thumbnailnew patent Gas turbine-heated high-temperature battery
A power plant system is provided having a high temperature battery, supplied with fluid via at least one supply line, for storing and releasing electrical energy, a gas turbine for generating electrical energy, and a heat exchanger which is designed to extract thermal energy from the exhaust stream of the gas turbine and transfer said thermal energy to the fluid, which fluid can be supplied after heat transfer to the high temperature battery via the at least one supply line.. .
Siemens Aktiengesellschaft
01/22/15
20150020530
 Gas turbine emissions control system and method patent thumbnailnew patent Gas turbine emissions control system and method
Embodiments of the present disclosure are directed towards a system including a gas turbine engine, a selective catalytic reduction system, and a control system configured to regulate operation of the selective catalytic reduction system based at least partially on preset variations in an emissions compound of exhaust gases produced by the gas turbine engine.. .
General Electric Company
01/22/15
20150020529
new patent

Gas turbine emissions control system and method


Embodiments of the present disclosure are directed towards a system including a gas turbine engine configured to produce exhaust gas, a selective catalytic reduction system configured to produce processed exhaust gas from the exhaust gas, and a control system. The control system includes a first controller configured to regulate operation of the selective catalytic reduction system, a second controller configured to regulate operation of the gas turbine engine, and an optimizer configured to coordinate operation of the first controller and the second controller to simultaneously maximize a first level of an emissions compound in the exhaust gas and regulate injection of a reductant into the selective catalytic reduction system to reduce a second level of the emissions compound in the processed exhaust gas to a first desired level of the emissions compound in the processed exhaust gas..
General Electric Company
01/22/15
20150020528
new patent

Fuel manifold and fuel injector arrangement for a combustion chamber


A fuel manifold and fuel injector arrangement for a gas turbine engine combustion chamber includes an annular combustion chamber casing arranged around the combustion chamber. Circumferentially spaced fuel injectors supply fuel into the combustion chamber and a fuel manifold supplies fuel to each of the fuel injectors.
Rolls-royce Plc
01/22/15
20150020500
new patent

Micro gas turbine system havnig an annular recuperator


A micro gas turbine system (16) having an annular recuperator (24). The recuperator (24) serves to transfer heat from an exhaust stream (27) of the turbine (17) to an air stream (23) compressed by a compressor (19).
Babcock Borsig Steinmuller Gmbh
01/22/15
20150020499
new patent

Control valve control method and control device, and power generating plant utilizing same


A gas turbine plant including a gas turbine and a compressor is provided with a steam turbine plant including a steam turbine and a condenser, and, an exhaust heat recovery boiler. Steam from the exhaust heat recovery boiler is directly flown to the condenser of the steam turbine plant through a bypass control valve.
Kabushiki Kaisha Toshiba
01/22/15
20150020498
new patent

Cooling cover for gas turbine damping resonator


A cover (54, 54a-b) enclosing with clearance (65) an acoustic damping resonator (24) on a working gas path liner (22) of a gas turbine component (28). The cover includes a coolant inlet chamber (56, 56b) with a top wall (58, 58b) that is closer to the liner than a top wall (32) of the resonator, and extends upstream from the resonator relative to the working gas flow (48).
01/22/15
20150020497
new patent

Gas turbine facility


A gas turbine facility 10 of an embodiment has a combustor 20 combusting fuel and oxidant, a turbine 21 rotated by combustion gas exhausted from the combustor 20, and a pipe 41 guiding a part of the combustion gas exhausted from the turbine 21 to a pipe 42 supplying the oxidant. Further, the gas turbine facility 10 has a pipe 43 guiding mixed gas constituted of the oxidant and the combustion gas to the combustor 20, a pipe 45 guiding another part of the combustion gas to the combustor 20 as working fluid of the turbine, and a pipe 40 exhausting a remaining part of the combustion gas to an outside..
Kabushiki Kaisha Toshiba
01/15/15
20150019104

Gas turbine engine controller with event trigger


A feedback control system is provided and includes a controller to control an operation of a motive element in accordance with current and previous measured states. The controller includes a servo, a processor and an event trigger controller.
General Electric Company
01/15/15
20150017324

Method of applying a nanocrystalline coating to a gas turbine engine component


A method of applying a nanocrystalline metal coating to a titanium or titanium alloy blade of a gas turbine engine is described. The method includes selecting an intermediate bond coat from the group consisting of nickel, nickel alloy, p, b, tl and combinations thereof, and applying the intermediate bond coat to at least a portion of the blade.
Pratt & Whitney Canada Corp.
01/15/15
20150017003

Gas turbine engine shrouded blade


A gas turbine engine bladed component, such as a turbine blade, is shown as including a shroud located above a blade portion and a stiffener located above the shroud. The stiffener is generally located in a central interior region of the shroud and includes a raised portion that extends above a top surface of the shroud.
Rolls-royce Corporation
01/15/15
20150017002

Composite gas turbine engine blade having multiple airfoils


An apparatus includes a composite gas turbine engine multi-airfoil blade that includes first and second circumferentially spaced adjacent composite airfoils coupled together via a common composite attachment. The common attachment does not employ a fastener.
Rolls-royce Corporation
01/15/15
20150016986

Gas turbine compressor stator vane assembly


A stator vane assembly for a compressor of a gas turbine, in particular of an aircraft engine, including a plurality of stator vanes whose airfoil sections form a stagger angle with an axis of rotation of the compressor, which stagger angle varies along a duct height of the stator vane assembly. Along the duct height from the inside to the outside, the stagger angle increases to a local maximum in a second section adjoining a first, radially innermost section, and decreases to an outer local minimum in a third section adjoining this second section and, along the duct height from the inside to the outside, the stagger angle decreases from the initial value to an inner local minimum in the first, radially innermost section and/or increases from the outer local minimum to a final value in a fourth, radially outermost section adjoining the third section..
Mtu Aero Engines Ag
01/15/15
20150016985

Gas turbine stage


A gas turbine stage including a rotor blade array having a plurality of rotor blades and an adjacent stator vane array having a plurality of stator vanes which have leading edges facing the rotor blade array. In a first radial position of a rear face of the rotor blade array, a minimum axial gap is formed between this rear face and an opposite first contact region a stator vane leading edges, and in a second radial position of the rear face different from the first position, the minimum axial gap is formed between the rear face and an opposite second contact region.
Mtu Aero Engines Ag
01/15/15
20150016983

Subsonic shock strut


A gas turbine engine strut is disclosed as having a will forebody positioned upstream of a point of maximum thickness and an aft body positioned downstream of the point of maximum thickness. The aft body includes a discontinuity in a curvature distribution which provides for a “subsonic shock.” the discontinuity in curvature distribution can include in inflection point that marks a transition from a curvature associated with an upstream portion of the aft body to a second curvature associated with a downstream portion of the aft body.
Rolls-royce Corporation
01/15/15
20150016982

Exhaust diffuser for a gas turbine


An exhaust diffuser for a gas turbine includes an annular duct. A row of struts is arranged in the duct.
Alstom Technology Ltd
01/15/15
20150016974

Method of producing an insulation element and insulation element for a housing of an aero engine


The invention relates to a process for producing an insulation element (12), which can be arranged radially above at least one guide vane (14) in a housing (10) of a thermal gas turbine. The insulation element (12) is produced from a solid body (24) provided with a metallic shell (26), the solid body (24) consisting at least partially of a ceramic material.
Mtu Aero Engines Ag
01/15/15
20150016971

Compartmentalization of cooling air flow in a structure comprising a cmc component


A structure in a gas turbine engine comprises a spar and a cmc component adjoining the spar and separated from the spar by a cavity supplied by cooling air. At least one rope seal is installed in the cavity within a groove made in the spar to thus compartmentalize the cavity and control the flow of cooling air..
Rolls-royce North American Technologies, Inc.
01/15/15
20150016964

Gas turbine engine and operations


An improved gas turbine engine is adapted to include an inlet flow control arrangement disposed in an inlet passage at least between a filter member and a row of variable inlet guide vanes (vigv), and adjacent the filter member, to enable pressure loss in the inlet passage and supply reduced amount of inlet air to a compressor to enable the reduction of power output of the gas turbine engine at a low load condition.. .
Alstom Technology Ltd
01/15/15
20150016956

Compliant intermediate component of a gas turbine engine


One aspect of present application provides an intermediate structure in a gas turbine engine. The intermediate structure is positioned between a first component and another component.
Rolls-royce Corporation
01/15/15
20150016949

Tip clearance control method


A method of controlling tip clearance of rotor blades from a surrounding casing in a gas turbine engine. The method comprising the steps of performing a first run of the gas turbine engine, shutting down the gas turbine engine and starting the gas turbine engine for a second run.
Rolls-royce Plc
01/15/15
20150016946

Blade clearance control for gas turbine engine


An apparatus and method for controlling a clearance between the blades of a turbomachinery component and flow forming surface are disclosed herein, and includes controlling the clearance by moving the surface axially relative to the turbomachinery component. In one embodiment the apparatus includes an impeller rotatable about a first axis, a shroud encircling the impeller, and a first ring encircling the first axis.
Rolls-royce North American Technologies, Inc.
01/15/15
20150016945

Liner for gas turbine engine


An embodiment of a gas turbine engine having a liner and casing is disclosed. The liner is disposed between the casing and a rotatable turbomachinery component.
Rolls-royce Corporation
01/15/15
20150016944

Cooled gas turbine engine component


A gas turbine component having a cooling passage is disclosed. In one form, the passage is oriented as a turned passage capable of reversing direction of flow, such as a turned cooling hole.
Rolls-royce North American Technologies, Inc.
01/15/15
20150013852

Method for manufacturing components made of single crystal (sx) or directionally solidified (ds) nickelbase superalloys


The invention relates to a method for manufacturing a component, especially of a gas turbine, made of a single crystal (sx) or directionally solidified (ds) nickelbase superalloy, including a heat treatment and a machining and/or mechanical treatment step. The ductility of the component is improved by doing the machining and/or mechanical treatment step prior to said heat treatment and a solution heat treatment of the component is done prior to the machining/mechanical treatment step..
Alstom Technology Ltd
01/15/15
20150013440

Method and system for diagnostic rules for heavy duty gas turbines


A method for monitoring and diagnosing anomalies in auxiliary systems of a gas turbine implemented using a computer device coupled to a user interface and a memory device, the method including storing a plurality rule sets in the memory device, the rule sets relative to the auxiliary systems of the gas turbine, 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 parameters associated with the auxiliary systems of the gas turbine, receiving real-time and historical data inputs from a condition monitoring system associated with the gas turbine, the data inputs relating to process parameters associated with the auxiliary systems of the gas turbine, and estimating values for at least some of the parameters associated with the auxiliary systems of the gas turbine using the received inputs.. .
Nuovo Pignone Sri
01/15/15
20150013345

Gas turbine shroud cooling


A shroud segment for a casing of gas turbine includes a body configured for attachment to the casing proximate a localized critical process location within the casing. The body has a leading edge, a trailing edge, and two side edges.
General Electric Company
01/15/15
20150013344

Tube


The present disclosure relates generally to the field of tubes for carrying fluids. More specifically, the present disclosure relates to a tube having an oval shaped cross-section.
United Technologies Corporation
01/15/15
20150013343

Method and device for safely operating a gas turbine plant


A method and a device are disclosed for the safe operation of a gas turbine plant, whose operation is both controlled by at least one process controller, which at least triggers and/or influences operationally relevant processes of the gas turbine plant, and is also monitored by a separate protection unit that is operated independently of the process controller on the basis of at least one first limit value for a safety-relevant operating parameter, wherein the gas turbine plant is subjected to an emergency switch-off once the at least one first limit value is exceeded. In that in the case of a defined transient operating state of the gas turbine plant that can be detected by the protection unit, the at least one first limit value of the safety-relevant operating parameter is raised to a second limit value, wherein the gas turbine plant is protected by an emergency switch-off of the gas turbine plant once said second limit value is exceeded.
Alstom Technology Ltd
01/15/15
20150013342

Air flow conditioner for fuel injector of gas turbine engine


A fuel injector for a gas turbine engine is provided. The fuel injector includes a central body, an air inlet duct, a mixing duct, a swirler, and a flow conditioner.
Solar Turbines Inc.
01/15/15
20150013341

Exhaust mixer with offset lobes


An exhaust mixer for a gas turbine engine where each outer lobe has at the downstream end a circumferential offset in a direction corresponding to that of the swirl component of the flow entering the mixer. The mixer has a crest line having at least a downstream portion curved with respect with respect to a circumferential direction of the mixer and/or a center line at the downstream end tilted with respect to a radial line extending to the tip of the outer lobe to define the circumferential offset.
Pratt & Whitney Canada Corp.
01/15/15
20150013340

Gas turbine engine combustor liner


A gas turbine engine variable porosity combustor liner has a laminated alloy structure. The laminated alloy structure has combustion chamber facing holes on one side and cooling plenum facing holes on a radially opposite side.
Rolls-royce Corporation
01/15/15
20150013339

Mixing arrangement for mixing a fuel with a stream of oxygen containing gas


The invention relates to a mixing arrangement for mixing a fuel with a stream of oxygen containing gas flowing along an axis in an axial channel, especially in the second combustor of a gas turbine with sequential combustion. The mixing is improved and the mixing length reduced by said mixing arrangement comprising an injector with at least one injector ring, which is passed by said stream of gas inside and outside..
Alstom Technology Ltd
01/15/15
20150013306

Hybrid gas turbine propulsion system


A hybrid aerodynamic thrust system as a prime mover for aircraft or other high-speed vehicles. An arrangement of dual thrust resources to alternately accommodate low and high airspeed regimes.
01/15/15
20150013143

Method and system for attaching a piece of equipment to a structure made from composite material


A method of placing a fastener plate on a structure made of composite material, the structure being obtained by a technique of injecting resin under a vacuum, the technique including placing a fiber preform in a closed mold, injecting a thermosetting resin into the mold, and polymerizing the resin prior to cooling. The method includes mounting a metal fastener plate against a wall of the mold before putting the fiber preform into place, the fastener plate coming into contact with one of faces of the fiber preform while the fiber preform is being put into place in the mold, and the resin becoming deposited between the fastener plate and the fiber preform while the resin is being injected into the mold.
Snecma
01/15/15
20150013126

Device for recontouring a gas turbine blade


Wherein the machining unit (4) can be displaced perpendicularly to the machining direction (8).. .
01/08/15
20150010385

Gas turbine with high-pressure turbine cooling system


The present invention relates to a gas turbine with a turbine stator wheel, which is fitted with stator vanes and includes a ring segment-shaped vane root, where the stator vanes are designed hollow and have a vane interior which can be supplied with cooling air, where a ring-shaped sealing element of an inter-stage seal is arranged radially on the inside, relative to an engine axis, on the vane root, where in the vane root at least one outflow duct is provided, characterized in that between the vane root and the sealing element an annular space extending substantially in the axial direction is formed, into which the outflow duct issues and which discharges into the area of the inter-stage seal.. .
Rolls-royce Deutschland Ltd & Co Kg
01/08/15
20150008772

Integrated gas turbine engine accessories


An permanent magnet alternator stator assembly for an integrated air turbine starter and permanent magnet alternator assembly has a permanent magnet alternator stator winding assembly attached to a mounting structure. A quick electrical connector electrically connects to the stator winding assembly and is attached to the mounting structure.
Hamilton Sundstrand Corporation


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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This listing is a sample listing of patent applications related to Gas Turbine for is only meant as a recent sample of applications filed, not a comprehensive history. There may be associated servicemarks and trademarks related to these patents. Please check with patent attorney if you need further assistance or plan to use for business purposes. This patent data is also published to the public by the USPTO and available for free on their website. Note that there may be alternative spellings for Gas Turbine with additional patents listed. Browse our RSS directory or Search for other possible listings.
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