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


Method of operating a gas turbine for reduced ammonia slip

Seal assembly including grooves in a radially outwardly facing side of a platform in a gas turbine engine

Gas turbine system with manifold

Date/App# patent app List of recent Gas Turbine Engine-related patents
07/24/14
20140205449
 Superalloys and components formed thereof patent thumbnailnew patent Superalloys and components formed thereof
A gamma prime nickel-base superalloy and components formed therefrom that exhibit improved high-temperature dwell capabilities, including creep and hold time fatigue crack growth behavior. A particular example of a component is a powder metallurgy turbine disk of a gas turbine engine.
07/24/14
20140205443
 Seal assembly including grooves in an aft facing side of a platform in a gas turbine engine patent thumbnailnew patent Seal assembly including grooves in an aft facing side of a platform in a gas turbine engine
A seal assembly between a disc cavity and a hot gas path in a gas turbine engine includes a stationary vane assembly and a rotating blade assembly axially upstream from the vane assembly. A platform of the blade assembly has a radially outwardly facing first surface, an axially downstream facing second surface defining an aft plane, and a plurality of grooves extending into the second surface such that the grooves are recessed from the aft plane the grooves are arranged such that a circumferential space is defined between adjacent grooves during operation of the engine, the grooves impart a circumferential velocity component to purge air flowing out of a disc cavity through the grooves to guide the purge air toward a hot gas path such that the purge air flows in a desired direction with reference to a direction of hot gas flow through the hot gas path..
07/24/14
20140205441
 Seal assembly including grooves in a radially outwardly facing side of a platform in a gas turbine engine patent thumbnailnew patent Seal assembly including grooves in a radially outwardly facing side of a platform in a gas turbine engine
A seal assembly between a disc cavity and a turbine section hot gas path includes a stationary vane assembly and a rotating blade assembly downstream from the vane assembly and including a plurality of blades that are supported on a platform and rotate with a turbine rotor and the platform during operation of the engine. The platform includes a radially outwardly facing first surface, a radially inwardly facing second surface, a third surface, and a plurality of grooves extending into the third surface.
07/24/14
20140205439
 Gas turbine engine shaft bearing configuration patent thumbnailnew patent Gas turbine engine shaft bearing configuration
A gas turbine engine includes a housing including an inlet case and an intermediate case that respectively provide an inlet case flow path and an intermediate case flow path. A geared architecture is arranged within the inlet case.
07/24/14
20140205438
 Relationship between fan and primary exhaust stream velocities in a geared gas turbine engine patent thumbnailnew patent Relationship between fan and primary exhaust stream velocities in a geared gas turbine engine
An example gas turbine engine includes, among other things, a geared architecture rotatably coupling a fan drive shaft to an engine fan, the geared architecture having a speed reduction ratio that is greater than or equal to 2.4. The gas turbine engine is configured so that an exhaust velocity ratio, defined by a ratio of a fan stream exhaust velocity to primary stream exhaust velocity, is approximately in a range of 0.75 to 0.90..
07/24/14
20140205424
 Systems and methods to control variable stator vanes in gas turbine engines patent thumbnailnew patent Systems and methods to control variable stator vanes in gas turbine engines
Embodiments of the present application include a variable stator vanes control mechanism for a gas turbine engine. The control mechanism includes a moveable actuation rod in operative communication with a first unison ring such that movement of the actuation rod drives the first unison ring.
07/24/14
20140202166
 Method of operating a gas turbine for reduced ammonia slip patent thumbnailnew patent Method of operating a gas turbine for reduced ammonia slip
Described herein are methods of operating a gas turbine engine (12) for reduced ammonia slip. An exemplary method (100) includes operating (102) the engine over a range of power output levels; controlling (104) a mass flow of nox produced in exhaust (19) of the engine to be within 10% over the range of power output levels; and treating (106) the exhaust of the engine in a selective catalytic reduction process (22).
07/24/14
20140202164
 Gas turbine engine nozzle including housing having scalloped root regions patent thumbnailnew patent Gas turbine engine nozzle including housing having scalloped root regions
A gas turbine engine exhaust nozzle comprises a housing having an aft end that terminates in a row of chevrons. At least one surface of the housing has scalloped root regions proximate bases of adjacent chevrons.
07/24/14
20140202160
 Gas turbine system with manifold patent thumbnailnew patent Gas turbine system with manifold
A system including a gas turbine engine, including a combustor configured to generate products of combustion, a turbine driven by the products of combustion from the combustor, a compressor having a compressor discharge leading into a chamber between the combustor and a compressor discharge casing, an extraction manifold coupled to the combustor, wherein the extraction manifold is fluidly coupled to the chamber.. .
07/24/14
20140202158
 Gas turbine engine heat exchangers and methods of assembling the same patent thumbnailnew patent Gas turbine engine heat exchangers and methods of assembling the same
A heat exchanger assembly comprises a heat exchanger body including a first fluid circuit and a second fluid circuit. The first circuit includes a first bypass valve in flow communication with a first fluid circuit inlet channel.
07/24/14
20140202133
new patent Gas turbine engine mid turbine frame with flow turning features
A gas turbine engine includes first and second stages having a rotational axis. A circumferential array of airfoils is arranged axially between the first stage and the second stage.
07/17/14
20140200721
Stabilizing a gas turbine engine via incremental tuning during transients
Methods and systems are provided for automatically tuning a combustor of a gas turbine engine during a transient period, such as when a state of the gas turbine engine is changing. Once it has been determined whether the state of the gas turbine engine is changing, it is then determined whether a lean blowout is imminent, which is based conditions being monitored.
07/17/14
20140199176
Gas turbine engine nose cone attachment configuration
A gas turbine engine fan section includes a fan hub configured to rotate about an axis. A nose cone includes a spinner operatively mounted to the fan hub.
07/17/14
20140199175
Gas turbine engine components and methods for their manufacture using additive manufacturing techniques
In accordance with an exemplary embodiment, a method for manufacturing a component using additive manufacturing techniques includes providing a 3d design model for the component, adding one or more crack resistant features to the 3d design model of the component to produce an enhanced design model, and manufacturing the component using an additive manufacturing technique in accordance with the enhanced design model. The one or more crack resistant features are provided to reduce or eliminate the incidence of cracking in the manufactured component..
07/17/14
20140196473
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.
07/17/14
20140196472
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.
07/17/14
20140196471
Fan drive gear system flexible support features
A disclosed gear assembly support for a gas turbine engine includes a first portion configured for attachment to a case of the gas turbine engine and a second portion configured for supporting a gear assembly. The support further includes a snap portion defining a fit within the case.
07/17/14
20140196470
Gas turbine engine buffer system
A gas turbine engine includes a compressor section, a combustor in fluid communication with the compressor section, a turbine section in fluid communication with the combustor, a fan section configured to be driven by the turbine section via a geared architecture, and a buffer system that communicates buffer air to a portion of the gas turbine engine. The buffer system includes a first circuit configured to selectively mix a first bleed air supply having a first pressure and a second bleed air supply having a second pressure that is greater than the first pressure to provide a first buffer supply air having an intermediate pressure compared to the first pressure and the second pressure..
07/17/14
20140196469
Low pressure compressor bleed exit for an aircraft pressurization system
An aircraft pressurization system, includes an auxiliary compressor for further compressing compressed air received from a low pressure compressor section of a gas turbine engine while the compressed air is below a predetermined pressure level; a bleed passage for fluidically connecting the auxiliary compressor to the low pressure compressor section; and an environmental control system coupled to an output of the auxiliary compressor for conditioning the compressed air to a predetermined level.. .
07/17/14
20140196466
Methods and systems for operating gas turbine engines
Methods and systems for operating a gas turbine engine including a fuel delivery system and a plurality of combustor assemblies are provided. The fuel delivery system comprises a primary fuel circuit configured to continuously supply fuel to each of the plurality of combustor assemblies during a first mode of operation and a second mode of operation.
07/17/14
20140196465
Lean-rich axial stage combustion in a can-annular gas turbine engine
An apparatus and method for lean/rich combustion in a gas turbine engine (10), which includes a combustor (12), a transition (14) and a combustor extender (16) that is positioned between the combustor (12) and the transition (14) to connect the combustor (12) to the transition (14). Openings (18) are formed along an outer surface (20) of the combustor extender (16).
07/17/14
20140196464
System and method for protecting components in a gas turbine engine with exhaust gas recirculation
A system includes a gas turbine engine that includes a turbine section having one or more turbine stages between an upstream end and a downstream end, an exhaust section disposed downstream from the downstream end of the turbine section, and a fluid supply system coupled to the exhaust section. The fluid supply system is configured to route an inert gas to the exhaust section..
07/17/14
20140196463
High efficiency, high pressure gas turbine engine fuel supply system and method
A gas turbine engine fuel supply system includes a primary gear pump and a secondary gear pump. The primary gear pump always actively delivers fuel to the downstream fuel system, and is sized to supply 100% of the burn flow needed at a select low demand condition.
07/17/14
20140196459
High pressure, multiple metering zone gas turbine engine fuel supply system and method
A gas turbine engine fuel supply system includes a primary gear pump, a secondary gear pump, and a pump bypass valve. The primary gear pump always actively delivers fuel to the downstream fuel system, and is sized to supply 100% of the burn flow needed at a select low demand condition.
07/17/14
20140196433
Gas turbine engine component platform cooling
A component for a gas turbine engine according to an exemplary aspect of the present disclosure includes, among other things, a platform having an outer surface and an inner surface that axially extend between a leading edge portion and a trailing edge portion. At least one augmentation feature is disposed on at least one of the leading edge portion and the trailing edge portion of the outer surface of the platform..
07/10/14
20140193761
Rail cars for transporting heavy hydrocarbons
A method and system of temperature control of heavy hydrocarbons in a consist of rail cars is disclosed wherein waste heat from one or more of the locomotives propelling the train is utilized to heat the heavy hydrocarbons in a consist or ambient air is used to cool the heavy hydrocarbon cargo. The train is typically comprised of tanker cars that can be filled with raw heavy hydrocarbon, not dilbit thus allowing about 20% to about 30% additional heavy hydrocarbon to be transported in each tanker car.
07/10/14
20140193274
Fuel-cooled bladed rotor of a gas turbine engine
Liquid fuel from a rotary fluid trap is atomized by a sharp edge on an inside surface of an aft cavity of a bladed rotor of a gas turbine engine and directed into each of a plurality of associated hollow blades through corresponding blade inlet ducts that are in fluid communication with corresponding aft hollow interior portions of each blade. A radially-extending central rib within each blade partitions the hollow interior thereof into aft and forward hollow interior portions that are in fluid communication through an associated opening in the central rib and through a radially-extending gap between the central rib and the interior surface of the blade.
07/10/14
20140193272
Gas turbine engine cooling systems and methods incorporating one or more cover plate assemblies having one or more apertures therein
Turbine cooling systems and methods are disclosed herein. The turbine cooling system may include a rotor disk having a bucket attached thereto.
07/10/14
20140193251
Stator anti-rotation device
A stator vane assembly for a gas turbine engine is disclosed and includes a plurality of vanes received within channels defined within a case. An anti-rotation plate extends from a flange of the case between adjacent ones of the plurality of vanes for preventing rotation of the plurality of vanes relative to the case..
07/10/14
20140193249
Electrical conductor paths
A component, for example an aerofoil vane or other gas path structure in a gas turbine machine such as a gas turbine engine, in which an insulated electrical conductor path is embedded structurally integrally, and in which electromagnetic shielding, for the embedded electrical conductor path is provided structurally integrally.. .
07/10/14
20140193246
Cooling hole with crenellation features
A wall of a component of a gas turbine engine includes first and second wall surfaces, an inlet located at the first wall surface, an outlet located at the second surface, a metering section commencing at the inlet and extending downstream from the inlet, and a diffusing section extending from the metering section and terminating at the outlet. The diffusing section includes a leading edge formed at an upstream end of the outlet, a trailing edge formed at a downstream end of the outlet, a body region upstream of the trailing edge, and a plurality of crenellation features located on the body region..
07/10/14
20140193238
Method 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 that is rotatable about an axis. A speed reduction device is connected to the fan.
07/10/14
20140190167
Ceramic combustor can for a gas turbine engine
A combustor assembly having a support assembly between a metal support assembly and a ceramic combustor can section that accommodates a thermal expansion difference therebetween. An air fuel mixer and an igniter are mounted to the support assembly secured to the ceramic combustion can which receives the ignition products of the ignited fuel and air mixture..
07/10/14
20140190162
Heat recovery system for a gas turbine engine
A heat recovery system for an engine having an exhaust nozzle whereby exhaust gas is expelled, the heat recovery system comprising a heat exchanger disposed within the exhaust nozzle, heat exchanger containing a fluid, heat exchanger is further positioned to utilize heat energy from exhaust gas to vaporize fluid a turboexpander fluidly connected to heat exchanger and located downstream from heat exchanger, turboexpander further operatively connected to a utility a condenser fluidly connected to turboexpander and located downstream of turboexpander, and a pump fluidly connected to condenser and located between condenser and heat exchanger, pump is configured to direct fluid from condenser to heat exchanger; whereby operation of engine will generate heat energy in exhaust nozzle, vaporize fluid, and create a pressurized vapor which will drive turboexpander.. .
07/03/14
20140186187
Non-integral fan blade platform
Described are a gas turbine engine fan blade platform, related rotor assembly and gas turbine engine, as well as a method of assembling the same. The platform has a forward portion proximal to an axis of rotation, an aft portion, and a transition portion between the forward and aft portions.
07/03/14
20140186168
Component retention with probe
A gas turbine engine includes a casing, a probe, and a fairing. The probe extends through the casing and the fairing is disposed within the casing.
07/03/14
20140186167
Multi-piece fairing for monolithic turbine exhaust case
A gas turbine engine component comprises a frame and a fairing. The frame comprises a monolithic ring-strut-ring structure.
07/03/14
20140186165
Adhesive pattern for fan case conformable liner
A section of a gas turbine engine includes a case structure and a liner. The liner is attached to the case structure by a compliant adhesive.
07/03/14
20140186164
Non-line of sight electro discharge machined part
A method of machining cooling holes in a component includes the steps of inserting an electro discharge machining guide that houses an electrode into an internal cavity of a component, and machining a cooling hole into a wall of the component with the electrode. A gas turbine engine component includes first and second spaced apart walls providing an internal cavity.
07/03/14
20140186163
Blade outer air seal having shiplap structure
A blade outer air seal (boas) for a gas turbine engine, according to an exemplary aspect of the present disclosure includes, among other things a seal body having a radially inner face and a radially outer face that axially extend between a leading edge portion and a trailing edge portion and a shiplap structure that at least partially overlaps at least a portion of at least one of the leading edge portion and the trailing edge portion.. .
07/03/14
20140186160
Slider seal
An assembly for a gas turbine engine includes a component, a seal element, and a seal cap. The component defines a pocket adapted to accept the seal element and the pocket allows for sliding movement of the component relative to the seal element.
07/03/14
20140186158
Gas turbine engine shaft bearing configuration
A gas turbine engine includes a core housing that includes an inlet case and an intermediate case that respectively provide an inlet case flow path and an intermediate case flow path. A geared architecture is arranged within the inlet case.
07/03/14
20140186152
Blade outer air seal system for controlled tip clearance
A blade outer air seal system for a gas turbine engine includes a plurality of ring carriers made of a first material having a first coefficient of thermal expansion. A plurality of seal segments are carried, respectively, on the plurality of ring carriers.
07/03/14
20140186095
Thermally tunable systems
One embodiment of the present disclosure is a unique system. Another embodiment is a unique fastener system.
07/03/14
20140183825
Finger seal
An assembly for a gas turbine engine includes a component and a finger seal. The component has a first surface and a second surface.
07/03/14
20140183296
Gas turbine engine having fan rotor driven by turbine exhaust and with a bypass
A gas turbine engine has a core engine incorporating a core engine turbine. A fan rotor is driven by a fan rotor turbine.
07/03/14
20140182309
Geared gas turbine engine exhaust nozzle with chevrons
A gas turbine engine includes a core engine having a compressor section fluidly connected to a combustor section that is also fluidly connected to a turbine section. A core nacelle surrounds the core engine and includes a core nozzle.
07/03/14
20140182308
Gas turbine engine with v-band clamp connection for collector box
A gas turbine engine includes a turbine section, a compressor section, a bleed air collector box, and a v-band clamp. The compressor section is positioned upstream of the turbine section and includes a compressor case circumferentially surrounding the compressor section.
07/03/14
20140182293
Compressor rotor for gas turbine engine with deep blade groove
A compressor rotor has a rotor centered on an axis, and a groove with opposed side edges. The groove receives a plurality of removable compressor blades, and has tangential sides.
07/03/14
20140182292
Integral instrumentation in additively manufactured components of gas turbine engines
An article includes a body portion made of a metal and configured for use in a gas turbine engine, a sensing feature monolithically formed with the body portion, and an interior passage connected to the sensing feature and passing through the body portion. An article with integrated sensing features may be made additive manufacturing, resulting in a structure having internal passageways connecting an aperture at one surface of the monolithic article to a second aperture at another surface of the monolithic article at the opposite end of the internal passageway..
06/26/14
20140180606
Methods of analysing apparatus
Engine health monitoring is used to assess the health of an engine, such as a gas turbine engine. Blades mounted on a shaft produce a modal response when excited.
06/26/14
20140178632
High purity zirconia-based thermally sprayed coatings and processes for the preparation thereof
This invention relates to thermally sprayed coatings of a high purity yttria or ytterbia stabilized zirconia powder, said high purity yttria or ytterbia stabilized zirconia powder comprising from about 0 to about 0.15 weight percent impurity oxides, from about 0 to about 2 weight percent hafnium oxide (hafnia), from about 6 to about 25 weight percent yttrium oxide (yttria) or from about 10 to about 36 weight percent ytterbium oxide (ytterbia), and the balance zirconium oxide (zirconia). Thermal barrier coatings for protecting a component such as blades, vanes and seal surfaces of gas turbine engines, made from the high purity yttria or ytterbia stabilized zirconia powders, have a density greater than 88% of the theoretical density with a plurality of vertical macrocracks homogeneously dispersed throughout the coating to improve its thermal fatigue resistance..
06/26/14
20140178203
Coating fixtures for gas turbine engine compressor disks
A method for coating a gas turbine engine compressor rotor having a compressor disk with axial slots includes inserting masking fixtures into the axial slots. Each masking fixture includes a masking root that matches the shape of a blade root of an axial blade configured to be inserted into the axial slot the masking fixture is inserted into.
06/26/14
20140178180
Fundamental gear system architecture
A fan drive gear system for a gas turbine engine includes a gear system that provides a speed reduction between a fan drive turbine and a fan and a mount flexibly supporting portions of the gear system. A lubrication system supporting the fan drive gear system provides lubricant to the gear system and removes thermal energy produced by the gear system.
06/26/14
20140178174
Gas turbine engine including a pre-diffuser heat exchanger
According to an example embodiment, a gas turbine engine assembly includes, among other things, a compressor. A strut near the compressor includes a flow passage through a portion of the strut.
06/26/14
20140174855
Pressurized reserve lubrication system for a gas turbine engine
A lubrication system includes a control subsystem operable to selectively communicate lubricant from a reserve lubrication subsystem under a pressure to supplement lubricant from a main lubrication subsystem in response to identification of a prolonged reduced-g condition. A gas turbine engine includes a main lubrication subsystem in communication with a geared architecture; a reserve lubrication subsystem in communication with the geared architecture; and a control subsystem operable to selectively communicate lubricant from the reserve lubrication subsystem under a pressure in response to identification of a prolonged reduced-g condition.
06/26/14
20140174162
Ignitor plug isolation chamber (ipic) for a gas turbine engine
An ignitor plug isolation chamber (ipic) includes a first end cap mountable to a cylinder, the first end cap includes an igniter aperture to receive an ignitor plug. A second end cap mountable to the cylinder, the second end cap includes a ground aperture.
06/26/14
20140174093
Gas turbine engine lube oil system
A gas turbine engine lube oil system (740) includes a first passage (750) and a second passage (760). The first passage (750) includes a first elongated compartment (751) with a closed end (752) and a first open end (753) distal to the closed end (752).
06/26/14
20140174092
Closure of cooling holes with a filling agent
A method for filling cooling holes in a component of a gas turbine engine is disclosed. The component may include a plurality of first cooling holes extending through the wall of the component.
06/26/14
20140174091
Repair procedure for a gas turbine engine via variable polarity welding
A liner panel for a gas turbine engine includes a cold side having a backside feature and a hot side with a variable polarity weld.. .
06/26/14
20140174088
Alignment system and methodology to account for variation in a gas turbine engine
A gas turbine engine includes a bushing that is non-round in cross-section, the bushing receivable within an aperture. A fastener passes through the bushing to retain a second component to a third component with respect to the first component..
06/26/14
20140174056
Gas turbine engine with low stage count low pressure turbine
A gas turbine engine comprises a gear train defined along an axis. A spool along the axis drives the gear train and includes a low stage count low pressure turbine.
06/26/14
20140173899
Gas turbine rotor assembly methods
Method of assembling a rotor assembly of a gas turbine engine having a plurality of components. The method comprises in one aspect calculating the bending forces due to the mass distribution along the rotor.
06/26/14
20140173881
Blind installation pin for a gas turbine engine mount
A blind installation pin assembly for a gas turbine engine includes a pin that defines a bore. A paddle mounted to an end of the pin to pivot about a paddle axis between an install position and a lock position.
06/19/14
20140169979
Gas turbine engine fan blade platform seal
A fan section for a gas turbine engine includes a fan blade having an airfoil with an exterior surface. A platform seal is adhered to the airfoil.
06/19/14
20140169972
Fan with integral shroud
An integrally bladed rotor for use in a gas turbine engine includes a central hub; a plurality of airfoils extending from the central hub, each airfoil with a tip, a leading edge and a trailing edge; and a shroud with a metallic portion connecting to the tip of each airfoil to rotate with the airfoils.. .
06/19/14
20140169953
Drum seal
A gas turbine engine comprising at least one drum pack having two or more annular discs 62a-c. Adjacent discs 62a-c are connected by drive arms 68 the drum pack is provided with a tubular sealing body 84 positioned radially inwards of the drive arms 68 and extending from a first disc 62a to a last disc 62c in the drum pack.
06/19/14
20140169941
Forward compartment baffle arrangement for a geared turbofan engine
A baffle within a gas turbine engine includes a cylindrical flange with a multiple of holes at least partially therearound.. .
06/19/14
20140169935
Lightweight shrouded 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 with a plurality of fan blades rotatable about an axis. Each of the plurality of fan blades includes a mid-span shroud and a speed change device in communication with the fan..
06/19/14
20140169934
Anti-ice supply system for inlet guide vanes
Disclosed is a gas turbine engine including a plurality of inlet guide vanes. The gas turbine engine further includes an inlet case supporting each of the plurality of inlet guide vanes, and the inlet case is provided with at least one passageway in communication with a source of fluid.
06/19/14
20140166255
Closure of cooling holes with a filing agent
A method for filling cooling holes in a component of a gas turbine engine is disclosed. The component may include a plurality of first cooling holes penetrating the wall of the component.


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
  
         


FreshNews promo



0.2682

3831

2 - 1 - 71