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Gas Turbine Engine patents



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


Enhanced mixing tube elements

General Electric

Enhanced mixing tube elements

Apparatus and process for measuring the depth of a groove in a rotor of a gas turbine engine

Apparatus and process for measuring the depth of a groove in a rotor of a gas turbine engine

Apparatus and process for measuring the depth of a groove in a rotor of a gas turbine engine

Alstom Technology Ltd

Maintenance assembly adaptable within gas turbine engine

Date/App# patent app List of recent Gas Turbine Engine-related patents
01/29/15
20150030947
 Solid oxide fuel cell system patent thumbnailnew patent Solid oxide fuel cell system
A solid oxide fuel cell system (10) comprises a solid oxide fuel cell stack (12) and a gas turbine engine (14), a compressor (24) of the gas turbine engine (14) is arranged to supply oxidant to the cathodes (22) of the solid oxide fuel cell stack (12) and a fuel supply (32) is arranged to supply fuel to the anodes (20) of the solid oxide fuel cell stack (12). A portion of the unused oxidant from the cathodes (22) of the solid oxide fuel cell stack (12) is supplied back to the cathodes (22) of the solid oxide fuel cell stack (12).
Rolls-royce Fuel Cell Systems Limited
01/29/15
20150030443
 Split damped outer shroud for gas turbine engine stator arrays patent thumbnailnew patent Split damped outer shroud for gas turbine engine stator arrays
A vane cluster includes a split damped outer shroud and an inner shroud spaced from the split damped outer shroud with a multiple of stator vane airfoils that extend between the split damped outer shroud and the inner shroud.. .
United Technologies Corporation
01/29/15
20150030432
 Trailing edge cooling arrangement for an airfoil of a gas turbine engine patent thumbnailnew patent Trailing edge cooling arrangement for an airfoil of a gas turbine engine
An airfoil (112) including an internal cooling circuit (136) to direct cooling fluid (120) through an interior of the airfoil. The airfoil also includes a trailing edge (114′) defining plugged holes (115) and cooling holes (116) along a radial direction (117).
01/29/15
20150030428
 Method for enhancing power of a gas turbine engine patent thumbnailnew patent Method for enhancing power of a gas turbine engine
A method for servicing a gas turbine engine to enhance the power output of the gas turbine engine including a control system, inlet guide vanes, and a third stage power turbine nozzle is disclosed. The control system includes an inlet guide vane module.
Solar Turbines Incorporated
01/29/15
20150028133
 Enhanced mixing tube elements patent thumbnailnew patent Enhanced mixing tube elements
The present application provides a fuel nozzle for use with a flow of air and a flow of fuel in a gas turbine engine. The fuel nozzle may include a plenum, a mixing tube element positioned within the plenum, and an enhanced mixing feature positioned within the mixing tube element so as to promote mixing of the flow of air and the flow of fuel.
General Electric Company
01/29/15
20150027811
 Maintenance assembly adaptable within gas turbine engine patent thumbnailnew patent Maintenance assembly adaptable within gas turbine engine
The maintenance assembly, for workers to perform maintenance activities within a gas turbine engine, is capable of being arranged within a cavity, generally around a combustor, accessible from a manhole of the gas turbine engine. The maintenance assembly includes a platform, and an inflatable member cooperatively configured to the platform.
Alstom Technology Ltd
01/29/15
20150027211
 Flame monitoring of a gas turbine combustor using a characteristic spectral pattern from a dynamic pressure sensor in the combustor patent thumbnailnew patent Flame monitoring of a gas turbine combustor using a characteristic spectral pattern from a dynamic pressure sensor in the combustor
The state of a flame in a gas turbine engine combustor is acoustically monitored using a dynamic pressure sensor within the combustor. A spectral pattern of a dynamic pressure sensor output signal from the sensor is compared with a characteristic frequency pattern that includes information about an acoustic pattern of the flame and information about acoustic signal canceling due to reflections within the combustor.
Siemens Energy, Inc.
01/29/15
20150027210
 Apparatus and process for measuring the depth of a groove in a rotor of a gas turbine engine patent thumbnailnew patent Apparatus and process for measuring the depth of a groove in a rotor of a gas turbine engine
An apparatus is provided for measuring a depth of a groove defined between adjacent steeples of a rotor of a turbine. The groove is adapted to receive a root of a blade.
01/29/15
20150027101
 Geared gas turbine engine architecture for enhanced efficiency patent thumbnailnew patent Geared gas turbine engine architecture for enhanced efficiency
An example gas turbine engine includes, among other things, a geared architecture rotatably coupled to the fan drive shaft, and a high pressure compressor. The gas turbine engine is configured so that a core temperature at an exit of the high-pressure compressor is approximately in a range of about 1150 to about 1350 degrees fahrenheit at take-off.
United Technologies Corporation
01/29/15
20150027100
 System for performing staging control of a multi-stage combustor patent thumbnailnew patent System for performing staging control of a multi-stage combustor
A control system is provided for performing staging control of a multi-stage combustor of a gas turbine engine. The fuel is fed to the combustor by a fuel supply system comprising: a plurality of fuel manifolds distributing fuel to respective stages of the combustor, a fuel metering valve operable to control the rate at which fuel passes to the fuel manifolds, and an actuating arrangement which splits the fuel flow from the fuel metering valve between the fuel manifolds.
Rolls-royce Controls And Data Services Limited
01/22/15
20150023780

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
20150023776

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


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


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
20150020530

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

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

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
01/15/15
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
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
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
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
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
01/08/15
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
01/08/15
20150007570

Method for manufacturing of a gas turbine engine component


The invention concerns a method for manufacturing of a gas turbine engine component (37) comprising an outer ring structure (42, 47), an inner ring structure (41), and a plurality of circumferentially spaced elements (46, 46a, 46b) extending between the inner ring structure (41) and the outer ring structure (42), wherein a primary gas channel for axial gas flow is defined between the elements (46, 46a, 46b), and wherein the component (37) has an inlet side for gas entrance and an outlet side for gas outflow. The invention is characterized in that the method comprises the step of machining a one-piece metal blank as to form a one-piece part (47) comprising: a portion (46b) of each of said elements (46), wherein said portion (46b) relates to a portion of an extension length of the elements (46) between said ring structures (41, 42); and a ring-shaped member (42) that connects said element portions (46b) and that is intended to form part of one of the ring structures.
Gkn Aerospace Sweden Ab
01/01/15
20150004000

Method for making gas turbine engine ceramic matrix composite airfoil


A method for making a gas turbine engine ceramic matrix composite airfoil is disclosed. The method includes fabricating an airfoil preform that has a slotted forward end and a continuous trailing end.
Rolls-royce North American Technologies, Inc
01/01/15
20150003989

Gas turbine engine composite vane assembly and making same


A gas turbine engine composite vane assembly and method for making same are disclosed. The method includes providing at least two gas turbine engine airfoil composite preform components.
Rolls-royce North American Technologies, Inc.
01/01/15
20150003968

Gas turbine engine with attached nosecone


A gas turbine engine includes a compressor section and a nosecone assembly. The compressor section includes an inlet guide vane assembly including an inner shroud, an outer shroud, and an inlet guide vane extending from the inner shroud to the outer shroud.
United Technologies Corporation
01/01/15
20150003963

Gas turbine engine vane end devices


A turbomachinery component of a gas turbine engine is disclosed having a number of techniques of reducing the effects of a gap flow between an airfoil member of the gas turbine engine and a wall of the gas turbine engine. The airfoil member can be a variable and in one form is a variable turbine vane.
Rolls-royce North American Technologies, Inc.
01/01/15
20150003962

Apparatus for reducing a temperature gradient of mainstream fluid downstream of an airfoil in a gas turbine engine


An apparatus (100) is presented for reducing a temperature gradient (30) of mainstream fluid (118) downstream of an airfoil (112) in a gas turbine engine (110). The apparatus includes a passage (116) in a trailing edge (114) of the airfoil having an inlet (132) and an outlet (134).
01/01/15
20150003960

Springed fan track liner


A containment system for a gas turbine engine includes a replaceable spring biased fan track assembly for use with a containment case. The fan track assembly includes a body of collapsible material that is positioned within a cavity of the fan case and a spring arrangement provides as system that is operable to perform during normal operating conditions as well as during catastrophic blade failure conditions.
Rolls-royce Corporation
01/01/15
20150003959

Gas turbine engine having configurable bypass passage


A gas turbine engine is disclosed which includes a bypass passage that in some embodiments are capable of being configured to act as a resonance space. The resonance space can be used to attenuate/accentuate/etc a noise produced elsewhere.
Rolls-royce North American Technologies Inc.
01/01/15
20150001856

Methods and systems for operating a gas turbine engine


A method of operating a gas turbine engine may include operating a starter motor to rotate a spool of the gas turbine engine; determining a torque of the starter motor during rotation of the spool; and controlling the rotation of the spool based on the torque.. .
Rolls-royce North American Technologies, Inc.
01/01/15
20150001339

Propulsion, electrical, and thermal management device for a small unmanned aerial vehicle


An aircraft is provided with a gas turbine engine having a plurality of shafts. A first shaft provides power to an electrical generator and a propeller, while a second shaft provides power to a refrigeration system.
Rolls-royce North American Technologies, Inc.
01/01/15
20150000304

Removable nosecone for a gas turbine engine


A gas turbine engine includes a nosecone assembly attached to a gas turbine engine. The nosecone assembly includes a support structure and a nosecone attached to the support structure.
United Technologies Corporation
01/01/15
20150000303

Wireless power for gas turbine engine instrumentation


A gas turbine engine includes a compressor section, a combustor section and a turbine section mounted relative to an engine static structure. A module includes instrumentation that is mounted to the engine static structure.
United Technologies Corporation
01/01/15
20150000299

System and a fuel nozzle


A system includes an oxidant compressor and a gas turbine engine turbine, which includes a turbine combustor, a turbine, and an exhaust gas compressor. The turbine combustor includes a plurality of diffusion fuel nozzles, each including a first oxidant conduit configured to inject a first oxidant through a plurality of first oxidant openings configured to impart swirling motion to the first oxidant in a first rotational direction, a first fuel conduit configured to inject a first fuel through a plurality of first fuel openings configured to impart swirling motion to the first fuel in a second rotational direction, and a second oxidant conduit configured to inject a second oxidant through a plurality of second oxidant openings configured to impart swirling motion to the second oxidant in a third rotational direction.
Exxonmobil Upstream Research Company
01/01/15
20150000292

System and exhausting combustion gases from gas turbine engines


A system includes a gas turbine engine that includes a combustor section having one or more combustors configured to generate combustion products and a turbine section having one or more turbine stages between an upstream end and a downstream end. The one or more turbine stages are driven by the combustion products.
Exxonmobil Upstream Research Company
01/01/15
20150000291

Gas turbine engine combustor heat exchanger


A gas turbine engine having a combustor is disclosed in which a heat exchanger is disposed within the combustor. The heat exchanger can take the form of a fuel/air heat exchanger.
Rolls-royce Corporation
01/01/15
20150000290

Gas turbine engine and operating thereof


A turbine system and method of operating is provided. The system includes a compressor configured to generate a compressed low-oxygen air stream and a combustor configured to receive the compressed low-oxygen air stream and to combust a fuel stream to generate a post combustion gas stream.
General Electric Company
01/01/15
20150000288

Abradable liner for a gas turbine engine


Described is an abradable component for a gas turbine engine, comprising: a base having an outboard side which receives a supply of cooling air in use and a plurality of walls on an inboard side thereof, the walls adjoining one another to provide an abradable network of open faced cells at a gas washed surface thereof; wherein at least one wall includes one or more through-holes for providing a flow of cooling air from the outboard side to the gas washed surface of the abradable network of open faced cells, when in use.. .
Rolls-royce Plc
01/01/15
20150000287

Combustor assembly including a transition inlet cone in a gas turbine engine


A combustor assembly defining a main combustion zone where fuel and air are burned to create hot combustion products includes a liner, a transition duct, and a transition inlet cone. The liner defines an interior volume including a first portion of the main combustion zone, and has an inlet and an outlet spaced from the inlet in an axial direction.
01/01/15
20150000283

Combustor apparatus in a gas turbine engine


A combustor apparatus defining a combustion zone where air and fuel are burned to create high temperature combustion products. The combustor apparatus comprises an outer wall including a fuel inlet opening for receiving a fuel feed pipe.
01/01/15
20150000089

Clamp connector


The present disclosure is applicable to all applications where two adjoining portions of material are to be joined together. A clamp connector couples the two adjoining portions of material together such that increased clamping pressure is applied in response to forces attempting to separate the two adjoining portions of material.
United Technologies Corporation
12/25/14
20140377125

Nickel-based superalloy and articles


A nickel-based superalloy composition includes from about 5 to about 7 wt % aluminum, from about 4 to about 8 wt % tantalum, from about 3 to about 8 wt % chromium, from about 3 to about 7 wt % tungsten, from 1 to about 5 wt % molybdenum, from 1.5 to about 5 wt % rhenium, from 5 to about 14 wt % cobalt, from about 0 to about 1 wt % hafnium, from about 0.01 to about 0.03 wt % carbon, from about 0.002 to about 0.006 wt % boron, and balance nickel and incidental impurities. The composition may exhibit a sustained peak low cycle fatigue life at 1800° f./45 ksi of at least about 4000 cycles.
General Electric Company
12/25/14
20140377077

Noise attenuation in rotating blades


A blade for a rotating machine, particularly for a gas turbine engine, has a leading edge and a trailing edge joined by pressure and suction surfaces. The trailing edge has a serrated form including a first periodic variation and a second periodic variation of higher frequency and lower amplitude than the first periodic variation..
Rolls-royce Plc
12/25/14
20140377075

Method for repairing a blade


A method for repairing a blade in a gas turbine engine comprises the steps of: isolating the damage on the airfoil of the blade; forming a cut back in the shape of elongated “d” shaped recess with a pair of fillets, a depth and a longitudinal axis of the “d” shaped recess having a length along the leading or trailing edge of the airfoil; and the fillets having a respective radius.. .
Pratt & Whitney Canada Corp.
12/25/14
20140377054

Nozzle film cooling with alternating compound angles


A nozzle segment for a nozzle ring of a gas turbine engine is disclosed. The nozzle segment includes a first endwall, a second endwall, and an airfoil extending between the first endwall and the second endwall.
Solar Turbines Incorporated
12/25/14
20140376590

Optical monitoring system for a gas turbine engine


A system for optically monitoring a gas turbine engine includes a viewport having an opening disposed within a casing of the gas turbine engine. The opening extends from an interior side of the casing to an exterior side of the casing, and the viewport is configured to receive an image from inside the casing.
General Electric Company
12/25/14
20140376589

Optical monitoring system for a gas turbine engine


A system for optically monitoring a gas turbine engine includes a viewport into the gas turbine engine, and an optical connection having a first axial end and a second axial end. The first axial end is optically coupled to the viewport and configured to receive an image from the viewport, the optical connection includes a substrate having multiple hollow passages each extending from the first axial end to the second axial end, and each hollow passage includes a reflective coating disposed on an inner surface of the hollow passage to facilitate transmission of a respective portion of the image from the first axial end to the second axial end.
General Electric Company
12/25/14
20140376588

System and on-line optical monitoring and control of a gas turbine engine


A system for on-line optical monitoring of a gas turbine engine includes a viewport into a combustor of the gas turbine engine and an optical filter optically coupled to the viewport. The optical filter is configured to receive broad wavelength band thermal radiation from an interior surface of the combustor while the gas turbine engine is in operation, to substantially block wavelengths of the broad wavelength band thermal radiation emitted and/or absorbed by a flame and/or by exhaust gas within the combustor, and to output narrow wavelength band thermal radiation from the interior surface of the combustor.
General Electric Company
12/25/14
20140373610

Engine inspection apparatus and system


Inspection systems for a gas turbine engine (20) are provided. The inspection systems may comprise an inspection port (106), a bore-scope plug (100), a seal seat (108) and a seal (110a/110b).
United Technologies Corporation
12/25/14
20140373609

Optical monitoring system for a gas turbine engine


A system for optically monitoring a gas turbine engine includes an optical multiplexer configured to receive multiple images from respective viewports into the gas turbine engine. The optical multiplexer includes a movable reflective device configured to selectively direct at least a portion of each image toward a detector array, and the detector array is directed toward a fixed location on the optical multiplexer..
General Electric Company
12/25/14
20140373556

Support structure for a gas turbine engine


The present invention relates to a support structure (16) for a gas turbine engine (1). The support structure (16) has an axial extension in an axial direction (a) and a circumferential extension in a circumferential direction (c).
Gkn Aerospace Sweden Ab
12/25/14
20140373555

Accessory mounting for a gas turbine engine


A gas turbine engine assembly is connected to a pylon for mounting the gas turbine engine to an aircraft. The assembly has a frame supporting at least one accessory independently of the gas turbine engine.
Rolls-royce Deutschland Ltd & Co Kg
12/25/14
20140373554

Air turbine starter pressure monitor system


A method of monitoring a gas turbine engine start system includes monitoring a pressure in a starter air duct in communication with a starter air valve which is in communication with an air turbine starter (ats); identifying an expected transient pressure response in the starter air duct; and identifying the starter air valve as degraded if the expected transient pressure response does not occur after an open command to the starter air valve.. .
United Technologies Corporation
12/25/14
20140373551

Gas turbine air injection system control and operation


The present invention discloses a novel apparatus and methods for controlling an air injection system 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 control of the air injection system include ways directed towards preheating the air injection system, including using an gas turbine components, such as an inlet bleed heat system to aid in the preheating process..
Powerphase Llc
12/25/14
20140373549

Cooling hole with curved metering section


A gas turbine engine component includes a cooling hole. The component includes a first wall having an inlet, a second wall having an outlet and a metering section extending downstream from the inlet and having a substantially convex first surface and a substantially concave second surface.
United Technologies Corporation
12/25/14
20140373503

Method of finishing a blade


An automated technique for finishing gas turbine engine blades or vanes by generating a bespoke tooling path for each blade or vane. The bespoke tooling path is generated by scanning the aerofoil surface to generate a 3-d electronic representation of the surface.
Rolls-royce Plc
12/18/14
20140369852

Cooled turbine blade with double compound angled holes and slots


A turbine blade for a gas turbine engine. The turbine blade includes a base having a blade root, a platform, a cooling air inlet, and a base air passageway.
Solar Turbines Incorporated
12/18/14
20140369832

Internally cooled seal runner


A contact seal assembly for a shaft of a gas turbine engine includes a seal runner adapted to be connected to the shaft and rotatable relative to a carbon ring. The seal runner includes concentric inner and outer annular portions radially spaced apart to define at least one internal fluid passage between the inner and outer annular portions of the seal runner..
Pratt & Whitney Canada Corp.
12/18/14
20140369818

Planetary gear system arrangement with auxiliary oil system


A gas turbine engine includes a fan, a speed reduction device driving the fan and a lubrication system for lubricating components across a rotation gap. The lubrication system includes a lubricant input.
United Technologies Corporation
12/18/14
20140369814

Diffuser pipe for a gas turbine engine and manufacturing same


A diffuser pipe for a gas turbine engine comprises a hollow pipe body including a first end, a second end fluidly connected to the first end, and at least one flattened area proximate to the second end. A ring is connected to the second end.
Pratt & Whitney Canada Corp.
12/18/14
20140369783

Self-retaining shear pin for blind mount location


A shear pin connection for use in a difficult to access location has a bolt head to be positioned at an inner end of a bearing. A bushing is received between the bolt and an inner periphery of the bearing.
United Technologies Corporation


Popular terms: [SEARCH]

Gas Turbine Engine topics: Gas Turbine, Gas Turbine Engine, Downstream, High Speed, Circulation, Heat Exchanger, Attenuation, Variable Inlet Guide Vanes, Variable Inlet Guide Vane, Guide Vane, Guide Vanes, Inlet Guide Vanes

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This listing is a sample listing of patent applications related to Gas Turbine Engine 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 Engine with additional patents listed. Browse our RSS directory or Search for other possible listings.
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