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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


Gas flow path for a gas turbine engine

Siemens Energy

Gas flow path for a gas turbine engine

Fuel manifold for a gas turbine engine

United Technologies

Fuel manifold for a gas turbine engine

Fuel manifold for a gas turbine engine

United Technologies

Gas turbine engine airfoil


Date/App# patent app List of recent Gas Turbine Engine-related patents
08/20/15
20150233789 
 Method and system for predicting the serviceable life of a component patent thumbnailMethod 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 patent thumbnailGas 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 patent thumbnailFuel 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
20150233323 
 Gas turbine engine airfoil patent thumbnailGas 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 patent thumbnailMethod 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 patent thumbnailOperability 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 patent thumbnailMethod 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 patent thumbnailGeared 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 patent thumbnailReduction 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 patent thumbnailFuel 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
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
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
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
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
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
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
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
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
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.


08/06/15
20150219246 

Polymeric or composite interlocking mount assembly for cable harnesses and fluid tubes


A kit for building a mount assembly for securing a tubular member to a support structure of a gas turbine engine is described. The kit may comprise a base unit including a bottom surface configured to bond to the support structure and an upper portion with a concave surface.
United Technologies Corporation


08/06/15
20150219017 

Actuator mounted to torque box


An actuator system mounted to a gas turbine engine that communicates mechanical power for positioning variable guide vanes within the gas turbine engine. The actuator system includes a torque box having components for communicating mechanical power to the variable guide vanes for positioning the vanes and an actuator mechanically coupled to provide mechanical power to the components of the torque box used to communicate the provided mechanical power to the inlet guide vanes.
United Technologies Corporation


08/06/15
20150219015 

Seal assembly for a static structure of a gas turbine engine


A static structure of a gas turbine engine according to an exemplary aspect of the present disclosure includes, among other things, an outer platform, an inner platform, an airfoil that extends between the outer platform and the inner platform, a service tube disposed at least partially through the airfoil, and a seal assembly that seals between the service tube and one of the outer platform and the inner platform.. .
United Technologies Corporation


08/06/15
20150219011 

Dual oil supply tube


The present disclosure relates generally to a dual oil supply tube for a gas turbine engine. The dual oil supply tube locates a scheduled damper supply tube inside a compartment oil supply tube which remains full while the engine is operating..
United Technologies Corporation


08/06/15
20150218966 

Gas turbine engine fan spacer platform attachments


A fan hub assembly for a gas turbine engine includes a fan hub that is configured to rotate about an axis. The fan hub has an axially extending aperture and a platform.
United Technologies Corporation


08/06/15
20150218964 

Fan casing for a gas turbine engine


The present invention relates to a fire resistant fan casing for a gas turbine engine. The casing has a projection such as a reinforcing rib or a mounting pad.
Rolls-royce Plc


08/06/15
20150218963 

Cooling supplying a cooling gas flow


A turbine case cooling system and a method for supplying a cooling gas flow are provided. The cooling system has a turbine case and a turbine case cooling manifold.
Pratt & Whitney Canada Corp.


08/06/15
20150218961 

Gas turbine engine


Fan containment system fitting around array of radially extending fan blades mounted on a hub in an axial gas turbine engine. The fan containment system includes a fan case having an annular casing element for encircling array of fan blades and a hook projecting in radially inward direction from the annular casing element and positioned axially forward of an array of fan blades when the fan containment system fitted around fan blades.
Rolls-royce Plc


08/06/15
20150218957 

Guide vane seal


A seal for use with a static guide vane of a gas turbine engine has a strap member extending to a generally cylindrical bulb. The bulb forms a diameter, and is spaced a distance defined between an end of the strap remote from the bulb, to a point on the bulb furthest from the end.
United Technologies Corporation


08/06/15
20150218953 

Leading edge protector


A component of a gas turbine engine is provided. The component has a leading edge with two air-washed surfaces extending rearwardly therefrom to define opposing sides of the component, the component has a leading edge protector formed as a plurality of protector segments which succeed in a line along the leading edge.
Rolls-royce Plc


07/30/15
20150211741 

Method for repairing fuel nozzle guides for gas turbine engine combustors using cold metal transfer weld technology


A fuel nozzle guide for a combustor of a turbine engine includes an annular base with a hub section, the hub section at least partially formed of a cold metal transfer (cmt) weld and a method and system therefor.. .
United Technologies Corporation


07/30/15
20150211444 

Aft counter-rotating shrouded geared turbofan


A gas turbine engine comprises an outer shroud. An inner core housing is positioned radially inwardly of the outer shroud, and has a core engine including at least one compressor rotor and at least one turbine rotor.
United Technologies Corporation


07/30/15
20150211443 

Divot for blocker doors of thrust reverser system


A gas turbine engine includes a thrust reverser including a plurality of blocker doors moveable between a deployed position and a stowed position. A gap is defined between adjacent blocker doors when in the stowed position.
United Technologies Corporation


07/30/15
20150211441 

Variable exhaust mixer and cooler for a three-stream gas turbine engine


A gas turbine engine includes an outer case structure around a central longitudinal engine axis. An intermediate case structure is included inboard of the outer case structure.
United Technologies Corporation


07/30/15
20150211420 

Combustor igniter assembly


A gas turbine engine comprising a combustor having a combustor liner assembly and a mounting bracket provided on the combustor liner assembly, a floating collar being slidingly received on the mounting bracket for relative sliding movement in a plane normal to an axis of an igniter opening in the liner assembly. The floating collar includes an annular surface defining a collar opening, and an igniter having an axis concentric with the axis of the collar opening is sealingly engages the annular surface.
Pratt & Whitney Canada Corp.


07/30/15
20150211416 

Gas turbine engine with twin offset gas generators


A gas turbine engine comprises a fan on an engine central axis. Plural gas generators are downstream of the fan, each along a respective central axis, mutually offset, and offset from the engine central axis.
United Technologies Corporation


07/23/15
20150204439 

Variable vane actuating system


A variable vane assembly for a gas turbine engine having an actuating system including a rotatable face gear and a respective pinion engaged to and extending transversely from the end of each of the moveable vanes. The teeth of each pinion define land surfaces angled with respect to adjacent ones of the land surfaces of the teeth of the face gear meshed therewith.
Pratt & Whitney Canada Corp.


07/23/15
20150204347 

Fan blades with abrasive tips


A fan blade for a gas turbine engine is disclosed. The disclosed fan blade includes an airfoil having a leading edge, a trailing edge, a convex side, a concave side and a distal tip.
United Technologies Corporation


07/23/15
20150204245 

Turbine blade platform seal assembly validation


A platform seal assembly for a gas turbine engine with a turbine disk and a plurality of turbine blades is disclosed. The platform seal assembly includes a platform seal and a validation tab.
Solar Turbines Incorporated


07/23/15
20150204244 

Selectively deoxygenated stored fuel system


A gas turbine engine includes a multi-stage fuel injection system including at least a first fuel injection stage and a second fuel injection stage, a first fuel reservoir fluidly connected to the first fuel injection stage and fluidly connected to a selective valve, and a second fuel reservoir fluidly connected to the selective valve. The selective valve connects one of the first fuel reservoir and the second fuel reservoir to the second fuel injection stage..
United Technologies Corporation


07/23/15
20150204243 

Structural support bracket for gas flow path


A structural support system is provided in a can annular gas turbine engine having an arrangement including a plurality of integrated exit pieces (ieps) forming an annular chamber for delivering gases from a plurality of combustors to a first row of turbine blades. A bracket structure is connected between an iep and an inner support structure on the engine.
Siemens Energy, Inc.


07/23/15
20150204238 

Low noise turbine for geared turbofan engine


A gas turbine engine includes a fan, a turbine having a fan drive rotor, and a speed reduction device effecting a reduction in the speed of the fan relative to an input speed from the fan drive rotor. The fan drive rotor has a number of turbine blades in at least one of a plurality of rows of the fan drive rotor, and the turbine blades operating at least some of the time at a rotational speed, and the number of turbine blades in the at least one row and the rotational speed being such that the following formula holds true for the at least one row of the fan drive turbine (the number of blades×the rotational speed)/(60 seconds/minute)>4000 hz.
Mtu Aero Engines Ag


07/23/15
20150204212 

High durability turbine exhaust case


A turbine exhaust case has an outer housing to be secured within a gas turbine engine and a central hub. Struts extend between the outer housing and the central hub.
Gkn Aerospace Sweden Ab


07/23/15
20150204210 

Method of inspecting the fan track liner of a gas turbine engine


A method of inspecting the fan track liner of a gas turbine engine of a type having a rotatable propulsive fan circumscribed by a fan track liner and having a plurality of fan blades extending radially outwardly from a central hub. The method comprises the steps of: affixing at least part of an inspecting device to the fan so as to be directed towards the fan track liner; and rotating the fan within the fan track liner to move said at least part of the inspecting device circumferentially relative to at least a region of the fan track liner to thereby scan said region of the fan track liner with said at least part of the inspecting device..
Rolls-royce Plc


07/23/15
20150204201 

Contoured flowpath surface


A spacer assembly for a rotor assembly of a gas turbine engine includes an endwall segment having a non-axisymmetric flowpath surface, a first depression and a second depression. A perimeter of the flowpath surface includes a forward edge, an aft edge, a suction side edge and a pressure side edge.
United Technologies Corporation


07/23/15
20150203209 

Gas turbine engine configuration interface


A gas turbine engine is disclosed which is capable of being reconfigured for one operating mode to another. A display is provided that permits a pilot or other operator to select between engine modes.
Rolls-royce North American Technologies, Inc.


07/23/15
20150202707 

Attachment of structures having different physical characteristics


Methods of bonding first structures to second structures are disclosed wherein the first and second structures are fabricated materials having different physical characteristics. For example, the first structure may be a composite fan blade and the second structure may be a composite or metallic rotor, both for use in gas turbine engines.
United Technologies Corporation


07/23/15
20150202702 

Gas turbine engine cast structure finishing


A method of finishing a cast structure includes providing a cast exterior surface with an undesired cast feature and electrochemically machining the undesired cast feature to provide a finished contour.. .
United Technologies Corporation


07/16/15
20150198333 

Fuel injector with a diffusing main gas passage


A fuel injector for a combustor of a gas turbine engine is disclosed. The fuel injector includes a gas gallery and a gas passage.
Solar Turbines Incorporated


07/16/15
20150198116 

Variable area exhaust mixer for a gas turbine engine


A variable area exhaust mixer is provided for a gas turbine engine. The variable area exhaust mixer includes an outer wall with a multiple of doors.
United Technologies Corporation


07/16/15
20150198097 

Systems and methods for managing a combustor


Certain embodiments herein relate to systems and methods for managing a combustor of a gas turbine engine. In one embodiment, a system can include at least one memory configured to store computer-executable instructions and at least one controller configured to access the at least one memory and execute the computer-executable instructions.
General Electric Company


07/16/15
20150198092 

Dual function air diverter and variable area fan nozzle


A modulating fan air diverter and annular air-oil cooler for a gas turbine engine located in the inner fixed structure adjacent to the core cowl is provided. The fan air diverter modulates between an open position, corresponding to maximum fan nozzle area and airflow through the air-oil cooler, and a closed position, corresponding to minimum fan nozzle area and airflow through the air-oil cooler.
United Technologies Corporation


07/16/15
20150198091 

Electric probe assembly, gas turbine engine having same and cooling same


A gas turbine engine comprises a hot section module which includes at least one electric probe assembly surrounded by an immediate environment having a local ambient temperature. The at least one electric probe assembly includes an electric probe having a probe body, and a conduit surrounding at least a portion of the probe body.
Pratt & Whitney Canada Corp.


07/16/15
20150198062 

Turbine components with bi-material adaptive cooling pathways


The present application thus provides a turbine component for use in a hot gas path of a gas turbine engine. The turbine component may include an outer surface, an internal cooling circuit, an adaptive cooling pathway in communication with the internal cooling circuit and extending through the outer surface, and a cooling plug having two or more materials positioned within the adaptive cooling pathway..
General Electric Company


07/16/15
20150198059 

Gas turbine manual cleaning and passivation


A gas turbine engine may be manually cleaned by removing a compressor casing and a turbine casing from the gas turbine engine, cleaning stator vanes of the gas turbine engine, and applying an organic acid solution to metallic surfaces of the gas turbine engine. The organic acid solution may be rinsed from the gas turbine engine and an anticorrosive solution may be applied to the metallic surfaces of the gas turbine engine..
General Electric Company


07/16/15
20150198056 

Abradable seal having nanolayer material


A gas turbine engine includes a plurality of circumferentially-spaced blades. The blades have a polymeric coating thereon.
United Technologies Corporation


07/16/15
20150198053 

Gas turbine engine with exit flow discourager


A turbine stage for a gas turbine engine is disclosed. The turbine stage includes a turbine disk and a turbine diaphragm, forming a cavity there between.
Solar Turbines Incorporated


07/16/15
20150198050 

Internal cooling system with corrugated insert forming nearwall cooling channels for airfoil usable in a gas turbine engine


An airfoil for a gas turbine engine in which the airfoil includes an internal cooling system formed from one or more midchord cooling channels with a corrugated insert positioned therein and creating nearwall leading edge, pressure side and suction side nearwall cooling channels. The corrugated insert may be formed from a wall that oscillates in a repeating pattern between peaks and valleys, such that the peaks are closer to an inner surface of the outer wall forming the generally elongated hollow airfoil the corrugated insert may work in concert with the rows of partition walls to create periodic impingement on the inner surface of the outer wall such cooling system provides adequate cooling for use in environments in which few, if any, cooling holes are desired, such as in crude oil engine applications.
Siemens Energy, Inc.


07/16/15
20150198047 

Mistuned airfoil assemblies


A mistuned airfoil assembly for a gas turbine engine is disclosed. The mistuned airfoil assembly may comprise a hub and airfoils extending radially from the hub.
United Technologies Corporation


07/16/15
20150197456 

Protective coating systems for gas turbine engine applications and methods for fabricating the same


Protective coating systems for gas turbine engine applications and methods for fabricating such protective coating systems are provided. An exemplary protective coating system includes a substrate formed of a ceramic matrix composite material, a first coating layer formed directly on to the substrate and comprising an oxygen barrier material, a compliance material, or a bonding material and a second coating layer formed directly on to the first coating layer and comprising a thermal barrier material.
Honeywell International Inc.


07/09/15
20150192912 

Method and system for combustion mode transfer for a gas turbine engine


A method and system for transferring between combustion modes in a gas turbine engine is provided. A processor generates data representative of an initial set of splits for providing at least one of fuel and air to at least one combustor in the gas turbine engine.
General Electric Company


07/09/15
20150192300 

Light weight swirler for gas turbine engine combustor and a manufacturing


A swirler body for a combustor of a gas turbine engine includes an annular mount face which defines at least one pocket and a method of manufacturing.. .
United Technologies Corporation


07/09/15
20150192299 

Compensating for thermal expansion via controlled tube buckling


One embodiment includes a fuel injector for a gas turbine engine. The fuel injector has an inlet fitting for receiving fuel.
Delavan Inc.


07/09/15
20150192298 

Gas turbine engine with improved fuel efficiency


A turbofan engine includes a fan driven by a low pressure turbine through a gear reduction. The gear reduction has a gear ratio of greater than or equal to about 2.4.
United Technologies Corporation


07/09/15
20150192165 

Systems and methods for centering bearing compartments


Systems and methods are disclosed herein for dressing centering a bearing compartment in a gas turbine engine. A nut may be inserted through an outer case of a gas turbine engine.
United Technologies Corporation


07/09/15
20150192072 

Fluid transport system having divided transport tube


A fluid transport system for a gas turbine engine includes a plenum configured to provide a fluid, an airfoil having an internal cavity, and a transfer tube arranged to transfer the fluid between the plenum and the internal cavity of the airfoil. The transfer tube includes an inlet, an outlet, a cavity extending from the inlet to the outlet, and at least one partition wall dividing the cavity into multiple flow passages..
United Technologies Corporation


07/09/15
20150192071 

Geared turbofan gas turbine engine architecture


A gas turbine engine includes a combustor. A turbine section is in fluid communication with the combustor.
United Technologies Corporation


07/09/15
20150192070 

Geared turbofan gas turbine engine architecture


A gas turbine engine typically includes a fan section, a compressor section, a combustor section and a turbine section. A speed reduction device such as an epicyclical gear assembly may be utilized to drive the fan section such that the fan section may rotate at a speed different than the turbine section so as to increase the overall propulsive efficiency of the engine.
United Technologies Corporation


07/09/15
20150192069 

Recuperator for gas turbine engine


A recuperator inserted in the exhaust duct of a gas turbine engine includes a casing surrounding a core having spiral cross channels. Inlet and outlet openings are defined in the casing for the passage of hot exhaust gases through the exhaust channels in the core.
Pratt & Whitney Canada Corp.


07/09/15
20150192039 

Auxillary steam generation arrangement for a combined cycle power plant


A combined cycle plant (10) including: a gas turbine engine (12) having a compressor (14), a combustor and a gas turbine (16); a heat recovery steam generator (20) (hrsg) configured to receive exhaust from the gas turbine engine; a steam turbine (22, 24) configured to receive steam from the hrsg; a supplemental air arrangement (40) configured to generate supplemental heated air (42) when operating and to operate independent of the gas turbine engine; and a kettle boiler (26, 28) configured to use heat from the supplemental heated air to generate steam used in the steam turbine. .

07/09/15
20150192038 

Combined cycle plant injection water preheating arrangement


A combined cycle plant (10), including a heat recovery steam generator (hrsg) (36), a working fluid which is heated by the hrsg and effective to operate a steam turbine (38), and a blowdown heat transfer arrangement (90, 92, 94,102, 104) configured to capture heat present in blowdown water drawn from the working fluid and to transfer the heat to injection water (28), a gas turbine engine (16) having a compressor (18), a combustor (20), and a turbine (22), and a water injection arrangement (30) configured to inject the injection water into the combustor. .

07/09/15
20150192037 

Combined cycle plant fuel preheating arrangement


A combined cycle plant (10), including: a gas turbine engine (16) having a compressor (18), a combustor (20), and a gas turbine (22); and a heat recovery steam generator (hrsg) (36), a steam turbine (38), working fluid heated by the hrsg and effective to turn the steam turbine, and a blowdown heat transfer arrangement (90, 92, 94, 102, and 104) configured to capture heat present in blowdown water drawn from the working fluid and to transfer the heat to fuel (24) used in the combustor.. .

07/09/15
20150192036 

Preheating arrangement for a combined cycle plant


A power generation station (10), including: a combined cycle plant (12) having a gas turbine engine (20); a hrsg (30) configured to receive engine exhaust from the gas turbine engine and to generate steam, and a steam turbine (38, 40) configured to use the steam to develop mechanical energy; an auxiliary boiler (14) configured to generate heat used to create auxiliary steam for use in the combined cycle plant and to generate auxiliary boiler exhaust (52); and an auxiliary boiler exhaust heat transfer arrangement (16) configured to transfer heat present in the auxiliary boiler exhaust to the combined cycle plant.. .

07/09/15
20150192034 

Systems and methods for centering bearing compartments


Systems and methods are disclosed herein for dressing centering a bearing compartment in a gas turbine engine. A nut may be inserted through an outer case of a gas turbine engine.
United Technologies Corporation




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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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