FreshPatents.com Logo
Enter keywords:  

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

[SEARCH]

Gas Turbine topics
Gas Turbine
Gas Turbine Engine
Internal Combustion Engine
Distributed
Combustion
Uv Radiation
Exhaust Gas
Circulation
Downstream

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 patents



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


Low pressure compressor bleed exit for an aircraft pressurization system

Geared turbofan gas turbine engine architecture

Gas turbine engine buffer system

Date/App# patent app List of recent Gas Turbine-related patents
07/17/14
20140200721
 Stabilizing a gas turbine engine via incremental tuning during transients patent thumbnailnew patent 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 patent thumbnailnew patent 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 patent thumbnailnew patent 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
20140199163
 Abradable layer including a low thermal conductivity composition patent thumbnailnew patent Abradable layer including a low thermal conductivity composition
A system may include a blade track or blade shroud and a gas turbine blade that includes a blade tip. The blade track or blade shroud may include a substrate and an abradable layer formed over the substrate.
07/17/14
20140196473
 Geared turbofan gas turbine engine architecture patent thumbnailnew patent 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 patent thumbnailnew patent 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 patent thumbnailnew patent 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 patent thumbnailnew patent 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 patent thumbnailnew patent 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
20140196467
 Oxidizing fuel patent thumbnailnew patent Oxidizing fuel
A mixture of air and fuel is received into a reaction chamber of a gas turbine system. The fuel is oxidized in the reaction chamber, and a maximum temperature of the mixture in the reaction chamber is controlled to be substantially at or below an inlet temperature of a turbine of the gas turbine system.
07/17/14
20140196466
new patent 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
new patent 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
new patent 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
new patent 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
new patent 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
20140196458
new patent Damping device and gas turbine combustor
In a damping device according to the present invention, a damping device 63 is mounted on a bypass pipe 61 that supplies an amount of high-pressure air to a combustor transition piece 33. The damping device 63 includes a fluid introducing unit 71 that forms a fluid introduction space b by covering an outer peripheral portion of the bypass pipe 61, a plurality of acoustic boxes 73a and 73b that forms resonance spaces da and db with the base portions connected to the fluid introducing unit 71 and the end portions extending along the outer peripheral portion of the bypass pipe 61 in the circumferential direction, and partition plates 74a and 74b that form resonance ducts ea and eb of a predetermined length by partitioning the resonance spaces da and db..
07/17/14
20140196437
new patent Method for operating a static gas turbine, and intake duct for intake air of a gas turbine
An ambient air intake duct of a static gas turbine is provided, having at least one filter, which is arranged in the intake duct, for cleaning the ambient air (a) that can flow through the intake duct. A method for operating a static gas turbine which is equipped with a filter for cleaning the ambient air (a) is also provided.
07/17/14
20140196433
new patent 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
20140193252
Gas turbine half-casing lifting and shipping fixture
A lifting fixture assembly adapted for shipping and/or lifting includes a lower turbine casing having two horizontal joint flanges adapted to engage mating flanges on an upper-turbine casing. The horizontal joint flanges are provided with plural bolt holes used for securing the upper turbine casing to the lower turbine casing.
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
20140193241
Internally coolable component for a gas turbine with at least one cooling duct
An internally coolable component for a gas turbine with at least one cooling duct, on the inner surface of which swirl elements are arranged in the form of turbulators which extend transversely with respect to the main flow direction of a coolant is provided. In order to reduce pressure losses for the coolant in the cooling duct, pins with different heights are set up between the turbulators..
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
20140191476
Labyrinth seal
A labyrinth seal is provided for sealing the annular interspace between the rotor and the stator of a steam turbine or gas turbine. The labyrinth seal includes a multiplicity of sealing strips which are arranged in series in the axial direction and fastened on the stator and project into the interspace.
07/10/14
20140190181
Rotor cover plate
A cover plate for a rotor disk in a gas turbine machine includes a cylindrical body having multiple outward facing snaps and multiple inward facing snaps.. .
07/10/14
20140190180
Fairing of a gas turbine structure
A gas turbine structure includes a first housing and a second housing, one of the first and second housings being located around the other of the first and second housings such that a core flow passage is obtained between the first and second housings. The gas turbine structure further includes an elongate structural member extending in a structural member direction from the first housing to the second housing and the gas turbine structure further includes a fairing circumferentially enclosing at least a portion of the structural member..
07/10/14
20140190177
Method for running up a stationary gas turbine
A method for running up a stationary gas turbine is provided. The turbine has a combustion chamber, the burners of which have a pilot burner and a main burner and by which various types of fuel are introduced into the combustion chamber for burning.
07/10/14
20140190176
Fuel control method and fuel control apparatus for gas turbine and gas turbine
A fuel control method for a gas turbine with a combustor being formed of at least two groups of a pluralities of main nozzles for supplying fuel, and that supplies fuel from the main nozzles of all groups upon ignition of the combustor (s1), and supplies fuel from three main nozzles of a group a during subsequent acceleration of the gas turbine (s3). Because fuel is injected from a small number of the main nozzles during acceleration, the fuel flow rate per one main nozzle is increased, thereby increasing the fuel-air ratio (fuel flow rate/air flow rate) in a combustion region and improving the combustion characteristics.
07/10/14
20140190173
Power generation system and method of stopping power generation system
A gas turbine including a compressor and a combustor, an sofc including an air electrode (cathode) and a fuel electrode (anode), a first compressed air supply line adapted to supply a compressed air compressed by the compressor to the combustor, a second compressed air gas supply line adapted to supply a part of a compressed air compressed by the compressor to the air electrode (cathode), a first fuel gas supply line adapted to supply a fuel gas to the combustor, a second fuel gas supply line adapted to supply a fuel gas to the fuel electrode (anode), a fuel gas recirculation line adapted to return an exhausted fuel gas discharged from the fuel electrode (anode) to the fuel electrode (anode), a cooler provided in the fuel gas recirculation line are provided.. .
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.. .
07/10/14
20140190146
Carbon dioxide membrane separation system in coal gasification process, and integrated coal gasification combined cycle power generation facility using same
The carbon dioxide membrane separation system in a coal gasification process contains introduction of a mixed gas of hydrogen (h2) and carbon dioxide (co2) in a high temperature and high pressure condition generated through water gas shift reaction from a water gas shift reaction furnace, while maintaining the temperature and pressure condition, to a zeolite membrane module containing a zeolite membrane for removing carbon dioxide, thereby removing carbon dioxide and generating a fuel gas rich in hydrogen. The fuel gas rich in hydrogen in a high temperature and high pressure condition discharged from the zeolite membrane module is fed to a gas turbine of the power generation facility while maintaining the temperature and pressure condition..
07/10/14
20140190144
Power generating system and method for operating the same
A power generating system includes a fuel cell, an exhausted oxidized gas line to which exhausted oxidized gas is discharged from the fuel cell, a gas turbine having a combustor configured to burn an exhausted oxidized gas passing through the exhausted oxidized gas line together with a fuel gas, a temperature detection unit configured to detect a temperature of the exhausted oxidized gas discharged from the fuel cell or a temperature of the exhausted oxidized gas passing through the exhausted oxidized gas line, a fluid supply unit configured to supply a fluid to the exhausted oxidized gas line, and a control unit configured to control an amount of the fluid to be supplied from the fluid supply unit to the exhausted oxidized gas line based on a detection result in the temperature detection unit.. .
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.


Popular terms: [SEARCH]

Gas Turbine topics: Gas Turbine, Gas Turbine Engine, Internal Combustion Engine, Distributed, Combustion, Uv Radiation, Exhaust Gas, Circulation, Downstream

Follow us on Twitter
twitter icon@FreshPatents

###

This listing is a sample listing of patent applications related to Gas Turbine for is only meant as a recent sample of applications filed, not a comprehensive history. There may be associated servicemarks and trademarks related to these patents. Please check with patent attorney if you need further assistance or plan to use for business purposes. This patent data is also published to the public by the USPTO and available for free on their website. Note that there may be alternative spellings for Gas Turbine with additional patents listed. Browse our RSS directory or Search for other possible listings.
     SHARE
  
         


FreshNews promo



0.1754

3988

449492 - 0 - 80