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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 fuel nozzle leak detection pressure test tool and method for leak detection

Gas turbine fuel nozzle leak detection pressure test tool and method for leak detection

Thermal management system for gas turbine engine

United Technologies

Thermal management system for gas turbine engine

Thermal management system for gas turbine engine

General Electric

Apparatus and method for servicing gas turbine engines

Date/App# patent app List of recent Gas Turbine-related patents
02/26/15
20150056073
 Method and system for cooling rotor blade angelwings patent thumbnailnew patent Method and system for cooling rotor blade angelwings
A system for cooling an angelwing coupled to a rotor blade in a gas turbine engine is provided. An angelwing coupled to a shank of a rotor blade includes at least one cooling passage extending from at least one inlet opening coupled in flow communication with a gas turbine engine inner wheelspace to at least one outlet opening coupled in flow communication with a gas turbine engine outer rotor/stator cavity.
General Electric Company
02/26/15
20150054939
 Internal inspection of machinery by stitched surface imaging patent thumbnailnew patent Internal inspection of machinery by stitched surface imaging
A method of generating a comprehensive image (87) of interior surfaces (78, 80) of machine components such as a gas turbine combustor basket (59) and transition duct (34) by digitally stitching together multiple photographs (82) thereof, and analyzing the comprehensive image by contouring (91, 95a-b) of colors and shadings thereon, and quantifying and tracking aspects of the contours (a, b, c) over time for indications of degradation (89) of the interior surfaces. A scope (58) may be inserted into a port (56) in the combustor with a camera (72, 74) in a rotatable end (70) of the scope for obtaining a circumferential set (84) of photos at each axial position along a length of the combustor and transition duct.
Siemens Energy, Inc.
02/26/15
20150053750
 High temperature brazing fixture and  manufacture patent thumbnailnew patent High temperature brazing fixture and manufacture
A high temperature brazing fixture and method of manufacture for a gas turbine component made of a superalloy is disclosed herein. The high temperature brazing fixture includes a first and second frame member, a support member, and positioning member, all of which are made from the superalloy and fastened together using tab and tab lock couplings.
Solar Turbines Incorporated
02/26/15
20150052980
 Gas turbine fuel nozzle leak detection pressure test tool and  leak detection patent thumbnailnew patent Gas turbine fuel nozzle leak detection pressure test tool and leak detection
Internally shielded fuel passage orifices in nozzle rocket swirler airfoils are sealed with the pressure test tool. Pinch clamps on the test tool are introduced into the fuel nozzle rocket swirler.
02/26/15
20150052910
 Apparatus and  servicing gas turbine engines patent thumbnailnew patent Apparatus and servicing gas turbine engines
The present disclosure relates to an apparatus having an elongated body configured to be inserted into a tubular structure extending between a first combustor and a second combustor of a gas turbine engine. A movable arm may be positioned proximate to a first end of the elongated body, and the movable arm may be configured to engage a surface of the first combustor when the elongated body is placed within the tubular structure.
General Electric Company
02/26/15
20150052908
 Bleed duct assembly for a gas turbine engine patent thumbnailnew patent Bleed duct assembly for a gas turbine engine
A bypass duct has a support unit comprising a pair of aerofoils arranged as an “a” frame. A bleed duct assembly is provided on the radially inner wall of the bypass duct annulus and the aerofoils project from the surface and extend across the annulus between the inner wall and an outer wall of the annulus.
Rolls-royce Deutschland Ltd & Co Kg
02/26/15
20150052907
 Thermal management system for gas turbine engine patent thumbnailnew patent Thermal management system for gas turbine engine
A method of thermal management for a gas turbine engine comprising selectively positioning a valve to communicate a bypass flow into either an environmental control system (ecs) pre-cooler or an air oil cooler (aoc) “peaker” through a common inlet.. .
United Technologies Corporation
02/26/15
20150052905
 Pulse width modulation for control of late lean liquid injection velocity patent thumbnailnew patent Pulse width modulation for control of late lean liquid injection velocity
Systems and methods for pulse-width modulation of late lean liquid injection velocity can be provided by certain embodiments of the disclosure. In one embodiment, a gas turbine combustor utilizing a late lean injection scheme can be provided, wherein the combustor can include a combustor liner and a transition piece.
General Electric Company
02/26/15
20150052904
 Method for controlling a gas turbine group patent thumbnailnew patent Method for controlling a gas turbine group
The invention relates to a method for controlling a gas turbine group including, a first combustion chamber, a first turbine connected, a second combustion chamber, a second turbine, and a load. The method includes: measuring a temperature tat1 at an outlet of the first turbine; determining a ratio s1r of a fuel mass flow feeding a pilot flame of the first combustion chamber to a total fuel mass flow feeding the first combustion chamber based upon the measured temperature tat1 in accordance with a predetermined mapping table between ratio s1r and temperature tat1; adopting the larger one between the determined ratio s1r and a predetermined booster ratio s1r to be used in the controlling fuel flow feeding the first combustion chamber of the gas turbine group.
Alstom Technology Ltd.
02/26/15
20150052899
 Airblast fuel injector patent thumbnailnew patent Airblast fuel injector
An airblast fuel injector for a gas turbine engine fuel spray nozzle has, in order from radially inner to outer, a coaxial arrangement of an inner air swirler passage, an annular fuel passage, an annular outer air swirler passage, and an annular shroud air swirler passage. The injector further has an annular shroud having an inner surface profile.
Rolls-royce Plc
02/26/15
20150052897
new patent

Method of recovering energy in a steam-cooled gas turbine


A method of recovering heat energy from a cooling medium used to cool hot gas path components in a turbine engine includes cooling one or more hot gas path components with the cooling medium; supplying spent cooling medium used to cool the one or more hot gas path components to a heat exchanger; supplying air (e.g., compressor discharge air) to the heat exchanger so as to be in heat exchange relationship with the spent cooling medium and thereby add heat to the compressor discharge air; and supplying the air heated in the heat exchanger to at least one combustor.. .
General Electric Company
02/26/15
20150052872
new patent

Thermal isolating service tubes and assemblies thereof for gas turbine engines


Thermal isolating service tubes and assemblies thereof for gas turbine engines are provided. The thermal isolating service tube comprises an inner tubular member defining a fluid passage and at least one outer tubular member disposed about the inner tubular member.
Honeywell International Inc.
02/26/15
20150052749
new patent

Method of fabricating integrally bladed rotor using surface positioning in relation to surface priority


A method of fabricating an integrally bladed rotor for gas turbine engines according to one aspect includes a step of positioning a blade on a hub in a joining procedure by using a priority surface of the blade as a reference surface. The priority surface is determined in relation to importance of surface functionality of the blades during engine operation.
Pratt & Whitney Canada Corp.
02/19/15
20150051626

Rotational atherectomy device with electric motor


An atherectomy device is disclosed, which is rotationally driven by an electric motor. In some designs, the device includes features unavailable on gas turbine-driven systems, such as the storing in memory of low/medium/high preset rotation speeds for particular models of handle, calculations of the amount of saline left in the iv and associated warnings when it gets sufficiently low, and automatic adjustment of the iv pump rate to a predetermined or calculated level when the rotational speed of the motor is changed.
Cardiovascular Systems, Inc.
02/19/15
20150051040

Oil baffle for gas turbine fan drive gear system


An epicyclic gear train component includes spaced apart walls with circumferentially spaced mounts that interconnect the walls. The mounts provide circumferentially spaced apart apertures between the mounts at an outer circumference of the walls.
United Technologies Corporation
02/19/15
20150050511

Intermetallic wear-resistant layer for titanium materials


Disclosed is a process for producing a wear-resistant layer, in particular on components of gas turbines or aero engines. The process comprises providing a component with a titanium material on at least part of a surface on which the wear-resistant layer is to be produced, applying a solder formed from a cobalt base material to the titanium material, soldering the solder to the titanium material by applying heat and producing at least one diffusion zone between solder and titanium material which comprises intermetallic phases..
Mtu Aero Engines Ag
02/19/15
20150050158

Gas turbine engine component including a compliant layer


A blade for a gas turbine engine comprises a blade portion having a first end and a second end and an engagement portion including a first surface coupled to the second end of the blade portion and a second surface coupled to the second end of the blade portion, the first and second surfaces arranged to extend divergently away from one another. The engagement portion is adapted for coupling to a wheel included in a gas turbine engine wheel..
Rolls-royce North American Technologies, Inc.
02/19/15
20150050151

Annulus filler


An annulus filler is provided for mounting to a rotor disc of a gas turbine engine and bridging the gap between two adjacent blades attached to the rotor disc, the annulus filler has an outer lid which defines an airflow surface for air being drawn through the engine, the lid having a leading edge and a trailing edge in an axial airflow direction. The annulus filler further has a support arrangement which is connectable to the rotor disc.
Rolls-royce Plc
02/19/15
20150050150

Annulus filler


An annulus filler, mounted to a rotor disc of a gas turbine engine and bridging the gap between two adjacent blades attached to the rotor disc, is disclosed. The annulus filler, formed from a polymer matrix composite material, includes an outer lid, defining an airflow surface for air drawn through the engine in an axial airflow direction, and a support structure, connectable to the rotor disc, to support the rear of the lid on the rotor disc.
Rolls-royce Plc
02/19/15
20150050140

Intake arrangement in gas turbine power plant


An improved intake arrangement, for a compressor having a compressor blading, includes a manifold divided by a barrier into two sections, to convey, from one section, a flue gas stream, and, from other section, an air stream. Further, the intake arrangement includes a converging section configured to the manifold and extends convergingly to the compressor defining an inlet to the compressor blading.
Alstom Technology Ltd
02/19/15
20150050127

Air with integral spring for a gas turbine engine exhaust drive


A seal assembly for an exhaust duct section of a gas turbine engine includes a multiple of springs that axially extend from a split hoop opposite a seal surface.. .
United Technologies Corporation
02/19/15
20150050123

Switched reluctance, fully superconducting, integrated ring turbine motor, generator gas turbine, engine stage (ssrgts)


A superconducting integrated ring turbine motor generator gas turbine engine stage of the present invention includes a combination of turbine vanes, rotors and blisk assemblies that prevent temperatures during operation from interfering with the extraction or control of power generation processes. The engine stage includes a ring having an evenly spaced array of aerodynamic vanes affixed on the inside or outside of the ring.
02/19/15
20150047368

Systems and methods for controlling gas turbines


Embodiments of the disclosure relate to systems and methods for controlling a gas turbine. In one embodiment, a method can be provided.
General Electric Company
02/19/15
20150047366

Operation of gas turbine power plant with carbon dioxide separation


The invention relates to a method for operating a gas turbine power plant, including a gas turbine, a hrsg following the gas turbine, an exhaust gas blower, and a carbon dioxide separation plant which separates the carbon dioxide contained in the exhaust gases and discharges it to a carbon dioxide outlet, the gas turbine, hrsg, exhaust gas blower, and carbon dioxide separation plant being connected by means of exhaust gas lines. According to the method a trip of the gas turbine power plant includes the steps of: stopping the fuel supply, switching off the exhaust gas blower, and controlling the opening angle of a vigv at a position bigger or equal to a position required to keep a pressure in the exhaust gas lines between the hrsg and the exhaust gas blower above a minimum required pressure.
Alstom Technology Ltd
02/19/15
20150047365

Sequential combustion with dilution gas mixer


The invention refers to a sequential combustor arrangement including a first burner, a first combustion chamber, a dilution burner for admixing a dilution gas and a second fuel via a dilution-gas-fuel-admixer to the first combustor combustion products. The dilution-gas-fuel-admixer has at least one streamlined body which is arranged in the dilution burner for introducing the at least one second fuel into the dilution burner through at least one fuel nozzle, and which has a streamlined cross-sectional profile and which extends with a longitudinal direction perpendicularly or at an inclination to a main flow direction prevailing in the dilution burner.
Alstom Technology Ltd
02/19/15
20150047363

High frequency-stabilized combustion in aircraft gas turbines


A gas turbine includes a combustion chamber and a microwave source to produce microwave radiation. The gas turbine is arranged to guide the microwave radiation into a cavity of the combustion chamber.
Eads Deutschland Gmbh
02/19/15
20150047361

Nozzle with multi-tube fuel passageway for gas turbine engines


A pilot fuel nozzle for a combustor includes an igniter forming a central body extending along a longitudinal center of the nozzle. A nozzle tip includes a plurality of circumferentially spaced fuel passages and a plurality of circumferentially spaced air passages extending to an outer side of the nozzle tip.
Siemens Aktiengesellschaft
02/19/15
20150047359

Axial flow machine cooling system


This invention concerns a system for cooling components in a gas turbine engine, the gas turbine engine including a compressor for driving a primary gas flow to a combustor and a turbine arranged to be driven by combustion gases from the combustor, wherein the system includes: an annular cooling flow passage arranged for fluid communication between the compressor and the turbine, the flow passage having a first inlet arranged to receive gas from the primary gas flow downstream of compressor, and a second inlet located upstream of the first inlet, wherein the annular cooling flow passage has at least one internal wall for guiding airflow from the first inlet towards the airflow from the second inlet, the airflow from the first and second inlets coalesce within the annular flow passage prior to passing along the passage in a direction from the compressor to the turbine.. .
Rolls-royce Plc
02/19/15
20150047357

Damper for combustion oscillation damping in a gas turbine


With the solution of the present invention, the damper used to damping combustion oscillation may prevent hot gas ingestion during normal operations by uniquely determining the dimensions of the neck connecting the resonator cavity and the combustion chamber.. .
02/19/15
20150047315

Gas turbine engine flow duct having integrated heat exchanger


A gas turbine engine flow duct comprising a flow duct disposed along an engine centerline of the gas turbine engine and defining a stream flow passage, and first and second rows of heat exchangers disposed along the engine centerline of the gas turbine engine and integrated in the flow duct in fluid communication with the stream flow passage of the flow duct.. .
Rolls-royce North American Technologies, Inc.
02/19/15
20150047314

Intake arrangement in gas turbine power plant


An intake arrangement for a compressor in a gas turbine power plant includes at least a passageway having an elongated portion, and a circular portion at an end of the elongated portion. The circular portion may be arranged in proximity to the compressor at around a compressor inlet.
Alstom Technology Ltd.
02/19/15
20150047313

Combustor of a gas turbine with pressure drop optimized liner cooling


A design for an effectively cooling a liner of a gas turbine combustor by means of convective cooling is disclosed.. .
Alstom Technology Ltd
02/19/15
20150047191

Method for balancing and assembling a turbine rotor


A method for balancing and assembling a turbine rotor 2 including at least one turbine disk 3 and a compressor rotor 15 of a gas turbine. A front cover disk 6 is fastened by connections 10 to the turbine disk 3, and the turbine disk 3 is balanced together with the cover disk 6.
Rolls-royce Deutschland Ltd & Co Kg
02/12/15
20150046126

Gas turbine engine rotor assembly optimization


A method for optimizing a rotor assembly for a gas turbine engine is disclosed. The rotor assembly includes rotating parts including a first journal and one or more rotor disks.
Solar Turbines Incorporated
02/12/15
20150044056

Airfoil with leading edge reinforcement


A leading edge member for a composite vane of a gas turbine engine. The leading edge member includes a first leg and a second leg.
Rolls-royce Corporation
02/12/15
20150044054

Composite retention feature


A retention feature for use in a gas turbine engine is disclosed herein. The retention feature includes a ceramic post, an insert, and a braze layer coupling the insert to the ceramic post.
Rolls-royce Corporation
02/12/15
20150044050

Composite blade with an integral blade tip shroud and forming the same


A gas turbine engine airflow member including a blade core portion, a shroud tip portion extending from the blade core portion, and an airfoil portion formed exteriorly to the blade core portion, where the blade core portion and the shroud tip portion are constructed as a first unitary structure and the airfoil portion is constructed as a second structure. A method of forming a gas turbine engine component is also disclosed..
Rolls-royce Corporation
02/12/15
20150044049

Dovetail retention system for blade tracks


A turbine shroud for a gas turbine engine includes a metallic support ring and a ceramic blade track. The blade track is formed from a plurality of blade track segments including dovetail posts.
Rolls-royce Corporation
02/12/15
20150044046

Manufacturing strut shield collar of gas turbine exhaust diffuser


A method for casting a collar (44, 46) for a heat shield (36) of a strut (32) in a gas turbine exhaust section (20). A casting geometry (60, 70) is defined with extra wall thickness (56, 68) in an area of wall curvature (53, 54), which provides a flow path beyond a final geometry of the collar to facilitate a flow of molten metal in the mold (63, 64).
02/12/15
20150044044

Turbine shroud


A turbine shroud for a gas turbine engine includes an annular metallic carrier, a ceramic blade track, and a cross-key connection formed between the annular metallic carrier and the ceramic blade track. The cross-key connection is formed between the annular metallic carrier and the ceramic blade track to locate the ceramic blade track relative to the annular metallic carrier.
Rolls-royce Corporation
02/12/15
20150044041

Crack resistant turbine vane and vane containment cap attachment


A gas turbine vane containment cap is attached to an inboard surface of the vane inner shroud by penetrating flat weld filler, formed in a root gap between the cap and inner shroud. A semi-circular bead weld filler is formed outboard the penetrating weld filler closer to the vane exterior.
Siemens Energy, Inc.
02/12/15
20150044035

High porosity abradable coating


An abradable coating for a gas turbine engine includes a bond coat, an intermediate layer, and a porous layer. The bond coat includes a metal coating and a thickness from 0.152 millimeters to 0.229 millimeters.
Solar Turbines Incorporated
02/12/15
20150044029

Aerofoil


An aerofoil component of a gas turbine engine has an aerofoil portion which spans, in use, a working gas annulus of the engine. The aerofoil portion has a pressure side outer wall and a suction side outer wall, each extending from the leading edge to the trailing edge of the aerofoil portion.
Rolls-royce Plc
02/12/15
20150044028

Low pressure ratio fan engine having a dimensional relationship between inlet and fan size


According to an example embodiment, a gas turbine engine assembly includes, among other things, a fan that has a plurality of fan blades. A diameter of the fan has a dimension d that is based on a dimension of the fan blades.
United Technologies Corporation
02/12/15
20150042023

Hybrid part made from monolithic ceramic skin and cmc core


A hybrid part for use in a gas turbine engine has a platform and an attachment feature. The platform and an exterior portion of the attachment feature are formed from a monolithic ceramic material.
United Technologies 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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