FreshPatents.com Logo
Enter keywords:  

Track companies' patents here: Public Companies RSS Feeds | RSS Feed Home Page
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

Follow us on Twitter
twitter icon@FreshPatents

Web & Computing
Cloud Computing
Ecommerce
Search patents
Smartphone patents
Social Media patents
Video patents
Website patents
Web Server
Android patents
Copyright patents
Database patents
Programming patents
Wearable Computing
Webcam patents

Web Companies
Apple patents
Google patents
Adobe patents
Ebay patents
Oracle patents
Yahoo patents

[SEARCH]

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


Adjusted rotating airfoil

Adjusted rotating airfoil

Date/App# patent app List of recent Gas Turbine Engine-related patents
05/28/15
20150147479
 Methods for the formation of cooling channels, and related articles of manufacture patent thumbnailnew patent Methods for the formation of cooling channels, and related articles of manufacture
A method for the formation of channels on a metallic substrate is described. The method includes the steps of applying at least one layer of a metallic coating material onto a surface of the substrate by a cold spray technique, so as to define boundary walls for the channels, and to build the boundary walls to a desired height.
General Electric Company
05/28/15
20150147182
 Adjusted rotating airfoil patent thumbnailnew patent Adjusted rotating airfoil
A compressor component having an airfoil with a profile in accordance with table 1 is disclosed. The compressor component, such as a compressor blade, has an increased surface area over a portion of the airfoil chord length.
05/28/15
20150147165
 Methods for the formation and shaping of cooling channels, and related articles of manufacture patent thumbnailnew patent Methods for the formation and shaping of cooling channels, and related articles of manufacture
A method to modify the shape of a channel in a metallic substrate is described. The method includes the step of applying at least one metallic coating on selected portions of an interior surface of the channel, so as to alter the heat transfer characteristics of the channel during passage of a coolant fluid therethrough.
General Electric Company
05/28/15
20150147156
 Gas turbine engine patent thumbnailnew patent 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. The fan containment system comprises a fan case having an annular casing element for encircling an array of fan blades and a hook projecting in a generally radially inward direction from the annular casing element.
Rolls-royce Plc
05/21/15
20150142216
 Gas turbine engine turbine blade tip active clearance control system and method patent thumbnailGas turbine engine turbine blade tip active clearance control system and method
A system and method of controlling turbine blade tip-to-static structure clearance in a gas turbine engine includes processing aircraft data to determine when the aircraft is flying at altitude cruise conditions. When the aircraft is not flying at altitude cruise conditions, then compressor discharge air is directed to impinge upon at least a portion of the turbine shroud.
Honeywell International Inc.
05/21/15
20150139791
 Aircraft engine driveshaft vessel assembly and  assembling the same patent thumbnailAircraft engine driveshaft vessel assembly and assembling the same
A driveshaft vessel assembly for a gas turbine engine is disclosed. The driveshaft vessel assembly comprises a driveshaft vessel and an outlet guide vane.
General Electric Company
05/21/15
20150139782
 Air separator for gas turbine engine patent thumbnailAir separator for gas turbine engine
An air separator in a gas turbine engine includes a cylindrical member and a seal flange having a flange body extending radially outward at a rearward end of the cylindrical member. A head portion is located at a radially outer free end of the flange body and includes an axial flange located axially rearward of the flange body and defining a rearward seal face for engagement with a blade disc forward face, and a forward cantilevered head mass extending axially forward from the flange body.
05/21/15
20150139779
 Gas turbine engine patent thumbnailGas turbine engine
A fan containment system comprising an annular casing element and a hook projecting in a generally radially inward direction from the annular casing element. A fan track liner is connected to the hook via a fastener.
Rolls-royce Plc
05/21/15
20150136935
 Gas turbine engine stand patent thumbnailGas turbine engine stand
A gas turbine engine stand (38) comprising an engine frame (48) and a base frame (46). The base frame (46) has a slide rail (51) to enable axial translation of the engine frame (48) relative to the base frame (46).
Rolls-royce Plc
05/21/15
20150135727
 Automated water wash system for a gas turbine engine patent thumbnailAutomated water wash system for a gas turbine engine
The present application and the resultant patent provide a gas turbine engine system. The gas turbine engine system may include a gas turbine engine, a water wash system, and a system controller.
General Electric Company
05/21/15
20150135726

Surface cooler support mechanism


A surface heat exchanger is provided which utilizes forward and aft brackets to retain the heat exchanger in position. The surface heat exchanger includes a plurality of core cooling channels as well as fins which are disposed for air flow through the gas turbine engine.
Unison Industries, Llc
05/21/15
20150135678

Gas turbine engine with noise attenuating variable area fan nozzle


A nacelle assembly for a high-bypass gas turbine engine includes a core nacelle defined about an engine centerline axis. A fan nacelle is mounted at least partially around the core nacelle to define a fan bypass flow path.
United Technologies Corporation
05/21/15
20150135659

Gas turbine filtration system with inlet filter orientation assembly


The present application provides a filtration system for a gas turbine engine. The filtration system may include a holding frame with a positioning element extending therefrom and a filtration unit for mounting within the holding frame.
Bha Altair, Llc
05/21/15
20150135535

Gas turbine splitting


A gas turbine engine fan stand (40) comprising a base frame (42) and a fan case frame (44) coupled together at one edge by a hinge (46). The fan case frame (44) is arranged to: rotate about the hinge (46) between abutting the base frame (42) and substantially perpendicular thereto; and tilt about a yaw axis (52) perpendicular to the hinge (46) and in the plane of the fan case frame (44).
Rolls-royce Plc
05/14/15
20150132134

Injection molded composite fan platform


A fan platform for a gas turbine engine may include an outer flow path surface extending between a first side and a second side. An inner surface extends between the first side and the second side, and faces radially oppositely the outer flow path surface.
05/14/15
20150132122

Vane array with one or more non-integral platforms


A vane array adapted to be coupled to a vane carrier within a gas turbine engine is provided comprising: a plurality of elongated airfoils comprising at least a first airfoil and a second airfoil located adjacent to one another; a u-ring; first connector structure for coupling a radially inner end section of each of the first and second airfoils to the u-ring; second connector structure for coupling a radially outer end section of each of the first and second airfoils to the vane carrier; a platform extending between the first and second airfoils; and platform connector structure for coupling the platform to one of the u-ring and the vane carrier.. .
05/14/15
20150132117

Gas turbine engine ducting arrangement having discrete insert


A ducting arrangement (10), including: a plurality of discrete ducts (18), each defining a flow path and configured to receive a flow of combustion gases from a respective combustor can, where the plurality of discrete ducts merge to form a common duct structure; and a throat insert (50) configured to define at least part of a junction of one of the discrete ducts and the common duct structure.. .
05/14/15
20150132110

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.
05/14/15
20150132106

Gas turbine engine with low fan pressure ratio


A turbofan engine includes a fan variable area nozzle axially movable relative to the fan nacelle to vary a fan nozzle exit area and adjust a pressure ratio of the fan bypass airflow during engine operation.. .
05/14/15
20150132101

Cooling system with compressor bleed and ambient air for gas turbine engine


A cooling system for a turbine engine for directing cooling fluids from a compressor to a turbine blade cooling fluid supply and from an ambient air source to the turbine blade cooling fluid supply to supply cooling fluids to one or more airfoils of a rotor assembly is disclosed. The cooling system may include a compressor bleed conduit extending from a compressor to the turbine blade cooling fluid supply that provides cooling fluid to at least one turbine blade.
05/14/15
20150129676

Compact actuation system for flow nozzle


Embodiments may include an actuation system for an exhaust nozzle of a gas turbine engine. The actuation system may comprise a plurality of flap assemblies including a plurality of convergent flaps movable between first and second convergent positions and a plurality of divergent flaps movable between first and second divergent positions.
05/14/15
20150128606

Combustion casing manifold for high pressure air delivery to a fuel nozzle pilot system


The present application provides a pilot manifold system for a combustor of a gas turbine engine. The pilot manifold system may include a casing with a casing manifold, an end cover connected to the casing and having an end cover passage in communication with the casing manifold, and a fuel nozzle mounted about the end cover.
05/14/15
20150128605

Turbofan with variable bypass flow


A gas turbine engine is disclosed with a bypass flow path having a bypass nozzle positioned downstream of a fan; a core flow path having a compressor, a combustor, a turbine and an exhaust nozzle; an auxiliary duct fluidly connecting the core flow path and the bypass flow path downstream of the turbine; and a control valve operably connected to the auxiliary duct to control fluid flow from the core flow path into the bypass flow path.. .
05/14/15
20150128604

Gas turbine engine flow path geometry


A flow path surface of a gas turbine engine at the location of a bladed component is disclosed in which the flow path surface includes a cylindrical upstream side and a conical downstream side. The bladed component is located at the intersection of the cylindrical upstream side and the conical downstream side.
05/14/15
20150128599

Continuous detonation combustion engine and system


One embodiment of the present disclosure is a gas turbine engine. Another embodiment is a unique combustion system.
05/14/15
20150128598

Cooling air temperature reduction using nozzles


A converging-diverging nozzle that has particular application for providing a cooling air flow to ring segments in a gas turbine engine. The engine includes a turbine section that receives a hot working gas.
05/14/15
20150128561

Three stream, variable area, vectorable nozzle


An exhaust nozzle for a gas turbine engine may include a plurality of flap trains in the exhaust stream of the gas turbine engine. The flap trains are operable to selectively control three separate flow paths of gas that traverse the engine.
05/07/15
20150125308

Manufacture of filled aerofoil


A method of manufacturing a filled aerofoil component (100) for a gas turbine engine (10) comprises using a capping panel (200) to cover a pocket (310) in a pocketed aerofoil body (300). During manufacture, a pre-formed filler insert (400) is provided to support the capping panel (200) in the correct position.
Rolls-royce Plc
05/07/15
20150125305

Low profile fan platform attachment


A platform for a fan of a gas turbine engine includes a body portion, a forward flange at a front of the body portion that includes an engagement feature that interacts with a forward flange of a lug of a hub of a fan of a gas turbine engine, and a pin integral with a rear portion of the body portion. The pin is receivable in an aperture in a rear flange of the lug..
United Technologies Corporation
05/07/15
20150125304

Mass offset for damping performance


A gas turbine engine rotor assembly includes a plurality of blades spaced apart from each other for rotation about an axis. Each of the blades includes a platform having an inner surface and an outer surface.
United Technologies Corporation
05/07/15
20150125286

Atr axial v-groove


A gas turbine engine nacelle includes a first annular portion that is stationary and adapted for partially surrounding an engine core. The first annular portion includes a fore pylon connecting portion.
United Technologies Corporation
05/07/15
20150125285

Integrated nozzle and plug


A gas turbine engine includes a first annular portion that is stationary and adapted for partially surrounding an engine core. The first annular portion includes a fore pylon connecting portion.
United Technologies Corporation
05/07/15
20150125284

Atr full ring sliding nacelle


A gas turbine engine includes a core, a first annular portion, a rail, and a second annular portion. The first annular portion is stationary and adapted for partially surrounding an engine core.
United Technologies Corporation
05/07/15
20150125270

Atr guide pins for sliding nacelle


A gas turbine engine nacelle includes a first annular portion that is stationary and adapted for partially surrounding an engine core. The first annular portion includes a fore pylon connecting portion.
United Technologies Corporation
05/07/15
20150125267

Standardized gas turbine inspection port system


A standardized inspection port system with common inspection port bodies and port plugs are incorporated in plural inspection locations within a gas turbine engine casing to facilitate internal engine inspection. The inspection ports preferably have identical internal diameter, stub flange dimensions and axial length from the gas turbine casing inspection seat to the stub flange for standardized mounting of inspection instruments at different locations about the turbine.
05/07/15
20150125264

Gas turbine engine lubrication system


A lubrication system for a gas turbine engine is disclosed. The lubrication system is configured to provide pressurized air and lubricant to a bearing sump of the gas turbine engine to cool and lubricate a bearing included in the bearing sump..
Rolls-royce Corporation
05/07/15
20150125259

Gas turbine engine variable pitch fan blade


A gas turbine engine according to an exemplary aspect of the present disclosure includes, among other things, a fan section including a fan rotatable about an engine axis with a plurality of fan blades rotatable about a fan blade axis. A geared architecture is in communication with the fan and driven by a turbine section.
United Technologies Corporation
05/07/15
20150122952

Gas turbine engine inlet wall design


A gas turbine engine has an inlet duct formed to have a shape with a first ellipse in one half and a second ellipse in a second half. The second half has an upstream most end which is smaller than the first ellipse.
United Technologies Corporation
05/07/15
20150122905

Passive tangential ejector for an exhaust nozzle of a gas turbine engine


A flap for a convergent/divergent nozzle system includes an ejector door movably mounted to an inner skin at a hinge.. .
United Technologies Corporation
05/07/15
20150122446

Investment casting gas turbine engine vane segment


An investment casting method for a cast ceramic core (110), including an airfoil portion (116) shaped to define an inner surface (56) of an airfoil (52) of a vane segment (50) and an integral shell portion (122) having a backside-shaping surface (120) shaped to define a backside surface (68) of a shroud (62) of the vane segment. The backside-shaping surface has a higher elevation (132) and a lower elevation (134).
05/07/15
20150122339

Variable area bypass nozzle


A gas turbine engine includes a first duct, a second duct, and a bladder. The bladder is disposed in the first duct and communicates with the second duct.
United Technologies Corporation
05/07/15
20150121897

Gas turbine engine with soft mounted pre-swirl nozzle


An exemplary gas turbine engine may include a compressor, a turbine, and a combustor disposed between the compressor and the turbine. The combustor generally may have an inner casing.
Rolls-royce North American Technologies, Inc.
05/07/15
20150121895

Full ring sliding nacelle with thrust reverser


A gas turbine engine includes a first annular portion that is stationary and adapted for partially surrounding an engine core. The first annular portion includes a fore pylon connecting portion.
United Technologies Corporation
05/07/15
20150121894

Bifurcation fire purge system


A bifurcation assembly for a gas turbine engine is disclosed and includes a housing defining an inner cavity. A first partition and a second partition extend across the inner cavity and define a buffer area therebetween.
United Technologies Corporation
05/07/15
20150121886

Gas turbine engine afterburner


An afterburner is disclosed for use with a gas turbine engine and, in one form, is structured to receive a bypass air. The afterburner can be situated in a bypass duct and can be a toroidal combustor or a can combustor.
Rolls-royce North American Technologies, Inc.
05/07/15
20150121883

Fluid conduit


A gas turbine engine is provided. The gas turbine engine includes a compressor assembly and a combustion assembly in flow communication with the compressor assembly.
General Electric Company
05/07/15
20150121882

Mixer assembly for a gas turbine engine


A mixer assembly for a gas turbine engine is provided, including a main mixer with fuel injection holes located between at least one radial swirler and at least one axial swirler, wherein the fuel injected into the main mixer is atomized and dispersed by the air flowing through the radial swirler and the axial swirler.. .
United Technologies Corporation
05/07/15
20150121844

Geared turbofan arrangement with core split power ratio


A gas turbine engine includes a fan section and a compressor section. The compressor section includes both a first compressor section and a second compressor section.
United Technologies Corporation
05/07/15
20150121842

Pnuematic system for an aircraft


A pneumatic system 131 for use with gas turbine engines 10 and aircraft 100. The pneumatic system 131 comprises a first engine core compressor bleed offtake in the form of an engine handling bleed offtake 140, and a second engine core compressor bleed offtake in the form of first and second cabin bleed offtake 132, 134, the handling bleed being configured to supply higher pressure air than the cabin offtakes 132, 134.
Rolls-royce Plc
05/07/15
20150121841

Flow control device for a three stream turbofan engine


A gas turbine engine includes a core engine, a first bypass passage disposed about the core engine and a second bypass passage disposed about the first bypass passage. A flow control is disposed within the second bypass for controlling bypass airflow through the second bypass.
United Technologies Corporation
05/07/15
20150121840

Aircraft nozzle system


A nozzle is provided that is capable providing flowpaths for a combined cycle aircraft propulsion system that in one form includes a gas turbine engine and a ramjet. The gas turbine engine produces an exhaust flow that is offset from an exhaust flow from the ramjet.
Rolls-royce North American Technologies, Inc.
05/07/15
20150121839

Tandem thrust reverser with multi-bar linkage


One embodiment includes a pivot thrust reverser. The pivot thrust reverser includes a first tandem pivot door subassembly comprising an inner panel and an outer panel.
United Technologies Corporation
05/07/15
20150121838

Conjoined reverse core flow engine arrangement


A system of conjoined gas turbine engines has a first engine with a first propulsor having a first axis and a first engine core having a second axis, and a second engine with a second propulsor having a third axis and a second engine core having a fourth axis. The first axis and third axis are parallel to one another; and the second axis and fourth axis are angled from one another..
United Technologies Corporation
04/30/15
20150118485

Components protected with corrosion-resistant coatings and methods for making the same


A gas turbine engine component includes a substrate formed of a high temperature resistant material and a corrosion resistant layer. The corrosion resistant layer is inert to the molten salt impurities and includes a refractory metal vanadate of formula mxvyoz, wherein m is selected from the group consisting of alkaline earth metals, group iv and v transition metals, rare-earth metals and their combinations, and wherein z=x+2.5y, or z=1.5x+2.5y, or z=2x+2.5y..
General Electric Company
04/30/15
20150118064

Gas turbine engine airfoil trailing edge passage and core for making same


An airfoil has a body that includes leading and trailing edges that adjoin pressure and suction sides to provide an exterior airfoil surface. A cooling passage extends in a radial direction from a root to a tip.
United Technologies Corporation
04/30/15
20150118055

Gas turbine engine rotor assembly and assembling the same


A rotor assembly includes a rotor disc including a plurality of circumferentially-spaced diskposts and a plurality of dovetail slots. Each dovetail slot is defined between a pair of circumferentially-adjacent diskposts.
General Electric Company
04/30/15
20150118048

Gas turbine engine rotors including intra-hub stress relief features and methods for the manufacture thereof


Embodiments of a gas turbine engine rotor including stress relief features are provided, as are embodiments of method for producing a gas turbine engine rotor. In one embodiment, the method includes producing a hub preform in which a plurality of elongated sacrificial cores are embedded.
Honeywell International Inc.
04/30/15
20150118040

Outer vane support ring including a strong back plate in a compressor section of a gas turbine engine


A support ring for a row of vanes in an engine section of a gas turbine engine includes an annular main body portion for providing structural support for a row of vanes in the engine section, an aft hook, a forward wall, and a strong back plate. The aft hook extends from an aft side of the main body portion and is coupled to an outer engine casing for structurally supporting the support ring in the engine section.
04/30/15
20150118034

Trailing edge cooling using angled impingement on surface enhanced with cast chevron arrangements


A gas turbine engine component, including: a pressure side (12) having an interior surface (34); a suction side (14) having an interior surface (36); a trailing edge portion (30); and a plurality of suction side and pressure side impingement orifices (24) disposed in the trailing edge portion (30). Each suction side impingement orifice is configured to direct an impingement jet (48) at an acute angle (52) onto a target area (60) that encompasses a tip (140) of a chevron (122) within a chevron arrangement (120) formed in the suction side interior surface.
04/30/15
20150118023

Acoustic structure for a gas turbine engine


An acoustic structure for a gas turbine engine comprising an noise reduction layer and a fire protector layer connected to the noise reduction layer. The noise reduction includes a perforated inner wall adapted to be in contact with a first fluidic environment, and an noise reduction adjacent to the inner wall.
Pratt & Whitney Canada Corp.
04/30/15
20150118013

Hot gas path component with impingement and pedestal cooling


The present application provides a hot gas path component for use in a hot gas path of a gas turbine engine. The hot gas path component may include an internal wall, an external wall facing the hot gas path, an impingement wall, a number of internal wall pedestals positioned between the internal wall and the impingement wall, and a number of external wall pedestals positioned between the external wall and the impingement wall..
General Electric Company
04/30/15
20150117804

Gas turbine engine bushing


A gas turbine engine bushing includes a flange area, and an insert area to be received within an aperture. The insert area includes channels and a bond rib.
United Technologies Corporation
04/30/15
20150115534

Process and tool for aligning a seal housing assembly with a casing of a gas turbine engine


A process is provided for aligning a seal housing assembly with a casing of a gas turbine engine. The casing may comprise a plurality of connecting portions and the seal housing assembly may comprise a plurality of connecting sections.
04/30/15
20150114005

Gas turbine engine


A gas turbine engine having a fan and a bypass duct for discharging airflow from the fan to generate engine thrust. The bypass duct includes a first component and a second component each having a gas washed surface, the first component being positioned adjacent the second component with a gap therebetween.
Rolls-royce Plc
04/30/15
20150114002

Geared turbofan engine with a high ratio of thrust to turbine volume


A gas turbine engine turbine has a high pressure turbine configured to rotate with a high pressure compressor as a high pressure spool in a first direction about a central axis and a low pressure turbine configured to rotate with a low pressure compressor as a low pressure spool in the first direction about the central axis. A power density is greater than or equal to about 1.5 and less than or equal to about 5.5 lbf/cubic inches.
United Technologies Corporation
04/30/15
20150113997

Method and system for gas turbine power augmentation using steam injection


A method of augmenting power output by a gas turbine engine includes channeling fuel into the gas turbine engine at a predetermined fuel flow rate to generate a first power output. Steam is then injected into the gas turbine engine at a first steam flow rate, and a firing temperature bias is determined based at least on the first steam flow rate.
General Electric Company
04/30/15
20150113996

Cascaded multi-variable control system for a turboshaft engine


A control system for a gas turbine engine is disclosed. The control system may include a computer processor.
United Technologies Corporation
04/30/15
20150113994

Combustor for gas turbine engine


In a gas turbine combustor having an inner and outer liner defining an annular combustion chamber, at least an annular scoop ring provided on each inner and outer combustor liner. The annular scoop ring includes a solid radial inner base provided with bores defined therein and communicating with the combustion chamber to form air dilution inlets.
Pratt & Whitney Canada Corp.
04/30/15
20150113993

Gas turbine engines having fuel injector shrouds with interior ribs


A fuel injector assembly includes a fuel injector and a fuel injector shroud housing the fuel injector. The fuel injector includes a body and a nozzle coupled to the body.
Honeywell International Inc.
04/30/15
20150113945

Pivoting blocker door


A gas turbine engine that has a fan case radially surrounding a fan hub, and plural fan exit guide vanes rotatably connected between the fan hub and the fan case. The fan section also has a thrust reverser opening within the case, axially upstream of the guide vanes.
United Technologies Corporation
04/30/15
20150113943

Geared turbofan engine with power density range


A gas turbine engine turbine has a high pressure turbine configured to rotate with a high pressure compressor as a high pressure spool in a first direction about a central axis and a low pressure turbine configured to rotate with a low pressure compressor as a low pressure spool in the first direction about the central axis. A power density is greater than or equal to about 1.5 and less than or equal to about 5.5 lbf/cubic inches.
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

Follow us on Twitter
twitter icon@FreshPatents

###

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.
     SHARE
  
         











0.4157

3831

0 - 1 - 71