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Gas Turbine Engine patents



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


Airfoil cooling circuit and corresponding airfoil

General Electric

Airfoil cooling circuit and corresponding airfoil

Airfoil cooling circuit and corresponding airfoil

Phd

Pneumatic control valve

Date/App# patent app List of recent Gas Turbine Engine-related patents
04/23/15
20150110637
 Hollow component manufacture patent thumbnailnew patent Hollow component manufacture
A method of manufacturing a hollow component, such as a fan blade for a gas turbine engine, includes the steps of: (a) providing first and second panels and a membrane; (b) providing a stop-off material on at least one of the first and second panels and the membrane to define regions where no diffusion bonding is to take place; (c) assembling the panels and the membrane together so the membrane is between the panels; (d) diffusion bonding the panels and the membrane together. The method is such that when assembled in step (c) the membrane does not extend to at least one edge of the first and second panels, so that in that region the first and second panels are diffusion bonded directly to each other..
Rolls-royce Plc
04/23/15
20150110636
 Wear pad to prevent cracking of fan blade patent thumbnailnew patent Wear pad to prevent cracking of fan blade
A fan blade of a gas turbine engine includes an airfoil, a root received in a slot of a hub, and a wear pad covering at least a portion of the root and made of an integrally bonded woven composite laminate.. .
United Technologies Corporation
04/23/15
20150110634
 Retainer plate patent thumbnailnew patent Retainer plate
A retainer plate is provided for retaining a dovetail root of a fan blade of a gas turbine engine in a corresponding axially-extending slot in the rim of a fan disc. In use, the plate locates in a cavity formed at an end of the slot such that a first side of the plate is arranged for contact with an axial end face of the dovetail root and an opposite second side of the plate is arranged for contact with an abutment surface of the cavity to limit axial movement of the root along the slot.
Rolls-royce Plc
04/23/15
20150110621
 Finger-foil seals and gas turbine engines employing the same patent thumbnailnew patent Finger-foil seals and gas turbine engines employing the same
Embodiments of a gas turbine engine including a finger-foil seal are provided, as are embodiments of a finger-foil seal. In one embodiment, the finger-foil seal includes an aerodynamic foil having a generally annular body through which a first opening is formed.
Honeywell International Inc.
04/23/15
20150110616
 Gas turbine nozzle trailing edge fillet patent thumbnailnew patent Gas turbine nozzle trailing edge fillet
A nozzle segment for a gas turbine engine has a turbine airfoil bound on a first side by an arcuate inner endwall having an inner platform and on a second side by an arcuate outer endwall having an outer platform. The airfoil extends outwardly from the inner platform toward the outer platform.
General Electric Company
04/23/15
20150110611
 Airfoil cooling circuit and corresponding airfoil patent thumbnailnew patent Airfoil cooling circuit and corresponding airfoil
An airfoil cooling circuit for a gas turbine engine having at least one internal cavity with a lobed cross-sectional shape.. .
General Electric Company
04/23/15
20150108248
 Thrust reverser fan ramp with noise suppression patent thumbnailnew patent Thrust reverser fan ramp with noise suppression
A fan ramp for use in a thrust reverser portion of a nacelle is disclosed. The nacelle is included in a propulsion system.
Rohr, Inc.
04/23/15
20150107267
 Reverse bulk flow effusion cooling patent thumbnailnew patent Reverse bulk flow effusion cooling
Effusion cooling holes formed through a transition component provided in a combustion section of a gas turbine engine. The transition component directs a hot working gas from a combustion basket to a first row of vanes in a turbine section of the engine.
04/23/15
20150107264
 Structural mounting arrangement for gas turbine engine combustion gas duct patent thumbnailnew patent Structural mounting arrangement for gas turbine engine combustion gas duct
A gas turbine engine ducting arrangement (10), including: an annular chamber (14) configured to receive a plurality of discrete flows of combustion gases originating in respective can combustors and to deliver the discrete flows to a turbine inlet annulus, wherein the annular chamber includes an inner diameter (52) and an outer diameter (60); an outer diameter mounting arrangement (34) configured to permit relative radial movement and to prevent relative axial and circumferential movement between the outer diameter and a turbine vane carrier (20); and an inner diameter mounting arrangement (36) including a bracket (64) secured to the turbine vane carrier, wherein the bracket is configured to permit the inner diameter to move radially with the outer diameter and prevent axial deflection of the inner diameter with respect to the outer diameter.. .
04/23/15
20150107263
 Pneumatic control valve patent thumbnailnew patent Pneumatic control valve
A control valve for a gas turbine engine air starter. The control valve includes a spherical or ball valve element rotatable between a closed position and an open position to connect an internal flow passage to the air starter.
Phd, Inc.
04/23/15
20150107261
new patent

Pneumatic system for an aircraft


A bleed air system for an aircraft has a gas turbine engine and operating method. The system includes an environmental control system (ecs) for providing cabin airflow to the aircraft, including operating modes such as first and second air cycle machine operating modes and heat exchanger operating modes.
Rolls-royce Plc
04/23/15
20150107256
new patent

Combustor for gas turbine engine


An assembly of a combustor and fuel manifold comprises a fuel manifold having at least an annular portion with a plurality of fuel outlets facing at least partially radially inward. A combustor comprises an annular inner liner and an annular outer liner spaced apart from the inner liner, the inner liner and outer liner concurrently forming an annular combustor chamber therebetween.
Pratt & Whitney Canada Corp.
04/23/15
20150107225
new patent

Variable immersion lobe mixer for turbofan jet engine exhaust and fabricating the same


A method of fabricating a mixer for a gas turbine engine is provided. The method includes forming a forward end and an aft end of the mixer, and forming an annularly undulating contour that defines a plurality of core immersion lobes and a plurality of bypass immersion lobes between the forward end and the aft end.
General Electric Company
04/23/15
20150107223
new patent

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
04/23/15
20150107221
new patent

Thrust reverser fan ramp with blocker door pocket


A fan ramp for use in a thrust reverser portion of a nacelle is disclosed. The nacelle is included in a propulsion system.
Rohr, Inc.
04/23/15
20150107109
new patent

Gas turbine engine combustor with cmc heat shield and methods therefor


A combustor for a gas turbine engine is disclosed. The combustor is described as comprising a dome plate coupled to a liner thereof, with at least one heat shield comprised of a ceramic matrix composite coupled at the aft end of the dome plate.
General Electric Company
04/16/15
20150105966

Condition based lifing of gas turbine engine components


A system and methods for the condition based lifing of a gas turbine engine component is disclosed. The system and methods determine the stress and caused by fatigue and creep for each load cycle of the gas turbine engine, and use a ductility exhaustion method to combine the fatigue and creep strain rates determined from the fatigue and creep stresses to determine the remaining useful of the gas turbine engine component..
Solar Turbines Incorporated
04/16/15
20150104315

Fan blade root integrated sealing solution


A gas turbine engine, a fan section for a gas turbine engine, and a method for assembling a fan section of a gas turbine engine are disclosed. The fan section may include a fan hub having a slot, a spinner having a castellated spinner seal, a fan blade including an airfoil extending from a root to a tip, wherein the airfoil has a leading edge and the root is received in the slot, and a platform secured to the fan hub and arranged between adjacent fan blades.
United Technologies Corporation
04/16/15
20150104306

Fan casing arrangement for a gas turbine engine and related method


A fan casing arrangement for a gas turbine engine having a propulsive fan, the arrangement having a fan case and a fan track liner and being configured to circumscribe the fan, wherein the fan track liner is provided around the inside of fan case so as to adopt a radial position between the fan and the fan case. The fan track liner includes an elongate member which is helically-wound against the inside of the fan case in a plurality of turns.
Rolls-royce Plc
04/16/15
20150104298

Tip treatment bars in a gas turbine engine


There is presented a casing arrangement for a gas turbine engine. The casing arrangement includes a plurality of tip treatment bars extending between a pair of spaced-apart annular supports, with each tip treatment bar being elongate and supported at each end by a respective support such that each end of the bar is received within an opening formed in the respective support.
Rolls-royce Plc
04/16/15
20150101345

Seal assembly for a gap between outlet portions of adjacent transition ducts in a gas turbine engine


A seal assembly for sealing a circumferential leakage gap between outlet portions of first and second adjacent transition ducts in a gas turbine engine includes a first seal member affixed to the outlet portion of the first transition duct and a second seal member movable with respect to the first seal member. The second seal member is positionable in a non-sealing first position and a sealing second position.
04/16/15
20150101340

System and improving efficiency of a gas turbine engine


A gas turbine engine is presented. The gas turbine engine includes a control unit having a first bypass channel that is coupled between an outlet of a first turbine and an inlet of a second turbine.
General Electric Company
04/16/15
20150101339

Energy efficient pump system


A fuel system for a gas turbine engine, which includes a combustor section and an actuator, includes a fuel source, a combustor system, and an actuation system. The combustor system includes a combustor pump that is fluidly connected to the fuel source and to the combustor section, with the combustor pump being mechanically connected to and powered by an electric motor.
Hamilton Sundstrand Corporation
04/16/15
20150101335

Hole arrangement of liners of a combustion chamber of a gas turbine engine with low combustion dynamics and emissions


A gas turbine combustion chamber with an inner housing and an outer housing the inner housing having an inner wall element with a first hole arrangement and a second hole arrangement is provided. The inner wall element envelopes a burner volume.
Siemens Aktiengesellschaft
04/16/15
20150101331

Gas turbine engine


A gas turbine engine having a fire wall that is configured to provide a fire resistant barrier between a first zone and a second zone in the gas turbine engine, the second zone being hotter than the first zone when the gas turbine engine is in use. The gas turbine also has an actuator that is located in the first zone and is configured to generate a mechanical force when operated, an actuatable device that is located in the second zone and is configured to be actuated by a mechanical force and a mechanical force transmitting device that extends from the actuator to the actuatable device via a hole in the fire wall.
Rolls-royce Plc
04/09/15
20150098830

Assembly fixture for a stator vane assembly


A fixture for assembling a stator vane assembly for a gas turbine engine includes, an outer locating ring including a plurality of outer locating pins defining a position for each of a plurality of vanes relative to an outer fairing. An inner locating ring includes a plurality of inner locating rings defining a position of each of the plurality of vanes relative to an inner fairing.
United Technologies Corporation
04/09/15
20150098829

Shroud assembly and seal for a gas turbine engine


A shroud assembly having rope seals disposed between the shroud hangers and the surrounding case structure.. .
General Electric Company
04/09/15
20150098826

Apparatus and assembling a damper bearing assembly


A damper bearing assembly for a gas turbine engine is disclosed. The damper bearing assembly is designed to define forward and aft axial gaps which allow for normal deflection under standard operating thrust loads, but then close during a fan blade out event to allow the increased load to transfer to the damper housing.
General Electric Company
04/09/15
20150098816

System and controlling backbone bending in a gas turbine engine


A flexible coupling for a gas turbine engine includes a fan hub frame having a first flange and a core engine having a second flange. The first flange includes a first plurality of fingers extending from a face of the flange and the second flange includes a second plurality of fingers extending from a face of the second flange.
General Electric Company
04/09/15
20150098791

Method and system for passive clearance control in a gas turbine engine


A method to design a turbine including: estimating rates of thermal radial expansion for each of a stator and a rotor corresponding to a period of operation of the turbine; estimating a clearance between the rotor and the stator based on the rates of thermal radial expansion, and determining a mass or surface area of the stator or rotor based on the clearance.. .
General Electric Company
04/09/15
20150096304

Air accelerator on tie rod within turbine disk bore


A gas turbine engine high pressure rotor with first and second high pressure turbine stages include first and second stage disks having first and second stage disk bores and a single tie rod therethrough. First and second bore annular flowpaths are radially located between first and second stage disk bores and tie rod.
General Electric Company
04/09/15
20150096303

Gas turbine engine with high speed low pressure turbine section


A gas turbine engine includes a very high speed low pressure turbine such that a quantity defined by the exit area of the low pressure turbine multiplied by the square of the low pressure turbine rotational speed compared to the same parameters for the high pressure turbine is at a ratio between about 0.5 and about 1.5.. .
United Technologies Corporation
04/09/15
20150096302

Combustor heat-shield cooling via integrated channel


A combustor heat shield for a gas turbine engine has a heat shield panel adapted to be mounted to an inner surface of a combustor shell with a back face of the panel spaced-apart from the combustor shell to define an air gap therewith. Studs project from the back face of the panel for engagement in corresponding mounting holes defined in the combustor shell.
Pratt & Whitney Canada Corp.
04/02/15
20150093252

Internally cooled airfoil


An internally cooled airfoil for a gas turbine engine has a hollow airfoil body defining a core cavity. An insert is mounted in the core cavity.
Pratt & Whitney Canada Corp.
04/02/15
20150093248

Retainer plate


A retainer plate is provided for retaining a dovetail root of a fan blade of a gas turbine engine in a corresponding axially-extending slot in the rim of a fan disc. In use, the plate locates in a cavity formed at an end of the slot such that a first side of the plate is arranged for contact with an axial end face of the dovetail root and an opposite second side of the plate is arranged for contact with an abutment surface of the cavity to limit axial movement of the root along the slot.
Rolls-royce Plc
04/02/15
20150093211

Bolt for gas turbine engine rotor


The bolt has, in sequence along a bolt axis: a threaded portion, a thread run-out portion, a shank, and a head, the threaded portion having a thread with a given root radius and a given depth, the thread run-out portion connected to the shank via a thread run-out fillet having a thread run-out fillet radius, the thread run-out fillet radius being between two and six times the thread root radius.. .
Pratt & Whitney Canada Corp.
04/02/15
20150089959

Gas turbine engine shaft bearing configuration


A gas turbine engine includes a core housing that has an inlet case and an intermediate case that respectively provide an inlet case flow path and an intermediate case flow path. The shaft supports a compressor section that is arranged axially between the inlet case flow path and the intermediate case flow path.
United Technologies Corporation
04/02/15
20150089958

Gas turbine engine with high speed low pressure turbine section


A gas turbine engine includes a very high speed low pressure turbine such that a quantity defined by the exit area of the low pressure turbine multiplied by the square of the low pressure turbine rotational speed compared to the same parameters for the high pressure turbine is at a ratio between about 0.5 and about 1.5.. .
United Technologies Corporation
04/02/15
20150089953

Systems and methods for preventing fuel leakage in a gas turbine engine


Systems and methods for preventing fuel leakage in a gas turbine engine are provided. A fuel accumulation system includes a control valve section fluidly coupled to a fuel manifold passage and an accumulator valve section fluidly coupled at a first side to the control valve section.
General Electric Company
04/02/15
20150089920

Airblast fuel injector


An airblast fuel injector is provided for a fuel spray nozzle of a gas turbine engine. The injector has an annular air passage for the passage of a swirling air flow therethrough.
Rolls-royce Plc
03/26/15
20150086381

Internally cooled airfoil


An internally cooled airfoil for a gas turbine engine has a hollow airfoil body including pressure and suction sidewalls defining a cooling passage therebetween. A combination of pedestal and trip-strips are used in the cooling passage to enhance heat transfer while minimizing the coolant pressure drop across these features..
Pratt & Whitney Canada Corp.
03/26/15
20150086352

Gas turbine engine inlet assembly and making same


A method of fabricating an inlet assembly for a gas turbine engine, the method including defining an intake duct of the inlet assembly between first and second space apart inlet case portions, locating at least one strut across the intake duct, each strut having a proximal end made integral to the first inlet case portion and an opposed distal end engaged in a respective strut-receiving aperture defined through the second inlet case portion, while maintaining the distal end of each strut in the respective strut-receiving aperture, adjusting the relative position of the first inlet case portion and the second inlet case portion until a predetermined throat dimension of the intake duct is obtained, and locking the adjusted relative position by attaching the second inlet case portion to each strut. An inlet assembly and gas turbine engine with inlet assembly as also disclosed..
Pratt & Whitney Canada Corp.
03/26/15
20150086339

Diffuser with strut-induced vortex mixing


A gas turbine engine includes inner and outer shrouds forming an annular gas path, and a plurality of struts connecting the inner shroud to the outer shroud. Airfoil shaped shields surround the struts, and each of the shields include a main body having an upstream leading edge defining a chordal axis extending in a downstream axial direction from the leading edge toward a downstream end of the shield.
03/26/15
20150083169

System for washing an aero gas turbine engine


A wash system includes a wash unit associated with a mobile unit for providing wash fluid, one or more nozzles for streamline injecting wash fluid provided by the wash unit directly into an engine inlet, and an articulating arm for use in positioning the one or more nozzles. The wash unit is physically spaced from a surface of the engine inlet cowling during a washing process.
Ecoservices, Llc
03/26/15
20150082808

Gas turbine engines with turbine airfoil cooling


An airfoil for a gas turbine engine is provided. The airfoil includes a body with a leading edge, a trailing edge, a first side wall extending between the leading edge and the trailing edge, and a second side wall extending between the leading edge and the trailing edge.
Honeywell International Inc.
03/26/15
20150082798

Component for attaching to a wall


A tile for attaching to a wall of a gas turbine engine. The tile has a main body.
Rolls-royce Plc
03/26/15
20150082794

Apparatus for acoustic damping and operational control of damping, cooling, and emissions in a gas turbine engine


Acoustic damping resonators (60, 62, 76, 78) formed in pockets (32) between reinforcing ribs (30) in a grid of ribs on the outer surface of a wall (74) surrounding a combustion gas flow path (18). Each resonator has a perforated cover plate (64a-c) spanning between sides formed by the ribs (30).
03/26/15
20150082768

Systems and methods for facilitating substantially uniform ventilation airflow inside an engine enclosure of a gas turbine engine


A diffuser assembly for a ventilation system is disclosed herein. The diffuser assembly may include a boundary defining an interior of the diffuser assembly.
General Electric Company
03/26/15
20150082767

Passive cooling system for control valve actuators


The present application provides a passive control valve actuator cooling system to provide a flow of cooling air to a control valve actuator used with a gas turbine engine. The passive control valve actuator cooling system may include a turbine enclosure with a negative pressure therein, a radiation shield with a number of radiation shield outlets and the control valve actuator positioned therein, and a cooling air line extending from outside of the turbine enclosure to the radiation shield such that the negative pressure within the turbine enclosure pulls the flow of cooling air into and through the radiation shield so as to cool the control valve actuator..
General Electric Company
03/19/15
20150078915

Piloted nut


The present disclosure relates generally to a piloted nut. The piloted nut may be used on a tie-shaft to apply an axial load to a rotor.
United Technologies Corporation
03/19/15
20150078908

Gas turbine engine for aircraft engine


A gas turbine stator for aircraft engines has a blade array with a plurality of blades constituted by a series of first blades and a series of second blades with different geometries; the array is formed by a plurality of sectors, each having an inner portion, an outer portion, at least one first blade and a least one second blade, and each defined by a body made in one piece; a single first blade is alternated with a single second blade for the entire circumference of the stator.. .
03/19/15
20150078901

Threaded shank, connection assembly and gas turbine engine for improved fatigue life of threads


A threaded shank for engaging with a threaded further component is provided herein, the further component having a cylindrical first thread with a uniform first thread pitch and a uniform first thread angle, the threaded shank including a second thread with a uniform second thread pitch and a uniform second thread angle and including a third thread with a uniform third thread pitch and a uniform third thread angle along an axial expanse of the third thread. The first thread angle and the second thread angle and the third thread angle being substantially identical, the first thread pitch and the second thread pitch and the third thread pitch being substantially identical, wherein the second thread and the third thread are spaced apart axially by a thread-free region, a second thread helix and a third thread helix have an axial offset to one another..
Siemens Aktiengesellschaft
03/19/15
20150075178

Gas turbine engines with turbine rotor blades having improved platform edges


A turbine rotor blade is provided. The turbine rotor blade includes a root, a platform coupled to the root, and an airfoil extending from the platform.
Honeywell International Inc.
03/19/15
20150075176

Connecting gas turbine engine annular members


A gas turbine engine assembly includes first and second annular members having different first and second thermal expansion coefficients connected together with dual arm v brackets. Brackets include first and second arms angularly spaced apart from a bracket centerline and extending axially away from bracket bases attached to a first one of the first and second annular members.
General Electric Company
03/19/15
20150075133

Gas turbine engine system that uses organic medium


A gas turbine engine system is provided which achieves high efficiency while using sunlight as a heat source. In a gas turbine engine system including: a compressor configured to compress a first working medium; a heater configured to heat the compressed first working medium by an external heat source; a turbine configured to output power from the first working medium; and an intermediate cooler provided at the compressor and configured to cool the first working medium compressed by a low-pressure compression part of the compressor and supply the first working medium to a high-pressure compression part of the compressor, an organic rankine cycle engine using, as a second working medium, an organic substance which is a cooling medium of the intermediate cooler is provided..
Kawasaki Jukogyo Kabushiki Kaisha
03/19/15
20150075131

Exhaust collector with curved side panel


An exhaust collector for a gas turbine engine is disclosed. The exhaust collector includes a front panel, a rear panel, and a side panel.
Solar Turbines Incorporated
03/12/15
20150069763

Load cover


A load cover for a coupling between a rotor of a gas turbine engine and a generator is provided. The load cover includes a guard which is disposed about the rotor and a baffle disposed around the guard to form an annulus of circumferentially increasing area.
General Electric Company
03/12/15
20150069148

Integrated heat shield


A fuel injector for a gas turbine engine includes a nozzle tip assembly having a substantially monolithically formed nozzle body. The nozzle body has an annular outlet chamber for issuing a spray from the nozzle tip.
Delavan Inc
03/12/15
20150068294

Flame monitoring of a gas turbine combustor using multiple dynamic pressure sensors in multiple combustors


The state of a flame in a subject combustor of a gas turbine engine is acoustically monitored using a dynamic pressure sensor within the subject combustor and one or more additional sensors in nearby combustors. Dynamic pressure sensor output signals from the sensors are cross correlated to identify acoustic oscillations generated by a flame in the subject combustor and received by the sensors.
Siemens Energy, Inc.
03/12/15
20150068214

Low thermal mass joint


A gas turbine engine includes a tangential on-board injector (tobi) fluidly connected to a compressor section. A diffuser case structurally supports a combustor section and the tangential on-board injector via at least one low thermal mass joint..
United Technologies Corporation
03/12/15
20150068213

Method of cooling a gas turbine engine


A method of cooling a gas turbine engine is provided. The method includes removing a load from the gas turbine engine.
General Electric Company
03/12/15
20150068211

Radial midframe baffle for can-annular combustor arrangement having tangentially oriented combustor cans


A can-annular gas turbine engine combustion arrangement (10), including: a combustor can (12) comprising a combustor inlet (38) and a combustor outlet circumferentially and axially offset from the combustor inlet; an outer casing (24) defining a plenum (22) in which the combustor can is disposed; and baffles (70) configured to divide the plenum into radial sectors (72) and configured to inhibit circumferential motion of compressed air (16) within the plenum.. .
03/12/15
20150068210

Tube fed tangential on-board injector for gas turbine engine


A tangential on-board injector assembly for a gas turbine engine includes an annular housing including a plenum. A plurality of discrete tubes is fluidly connected to the plenum and is configured to provide a cooling fluid to the annular housing..
United Technologies Corporation
03/05/15
20150065285

Geared architecture gas turbine engine with oil scavenge


A gas turbine engine includes a geared architecture with a multiple of intermediate gears, and a baffle with an oil scavenge scoop adjacent to each of the multiple of intermediate gears. A geared architecture and method are also disclosed..
United Technologies Corporation
03/05/15
20150064019

Gas turbine components with porous cooling features


The present application provides a hot gas path component for use with a gas turbine engine. The hot gas path component may include an airfoil, an internal cooling cavity, and a porous section created by a direct metal laser melting technique.
General Electric Company
03/05/15
20150063996

Inducer and diffuser configuration for a gas turbine system


A system includes at least one inducer including a flow passage configured to guide a fluid flow into a cavity defined by a casing and rotor of a gas turbine engine, the flow passage includes an inlet configured to receive the fluid flow from a compressor diffuser of the gas turbine engine, and an outlet configured to discharge the fluid flow into the cavity. The at least one inducer is configured to be disposed within the gas turbine engine so that the second outlet is axially disposed forward of a diffuser outlet of the compressor diffuser..
General Electric Company
03/05/15
20150063411

Non-intrusive measurment of hot gas temperature in a gas turbine engine


A method and apparatus for operating a gas turbine engine including determining a temperature of a working gas at a predetermined axial location within the engine. An acoustic signal is encoded with a distinct signature defined by a set of predetermined frequencies transmitted as a non-broadband signal.
03/05/15
20150059352

Dual fuel combustor for a gas turbine engine


The present application and the resultant patent provide a dual fuel combustor for a gas turbine engine. The combustor may include a primary premixer positioned within a head end plenum of the combustor, and a dual fuel, injection system positioned within the head end plenum and upstream of the premixer.
General Electric Company
03/05/15
20150059350

System and recirculating exhaust gas for use in a plurality of flow paths in a gas turbine engine


A method includes generating an exhaust gas from combustion gases with a turbine; recirculating the exhaust gas along an exhaust recirculation flow path; reducing moisture within the exhaust gas along the exhaust recirculation path with an exhaust gas processing system; providing the exhaust gas to a first exhaust gas inlet of an exhaust gas compressor for compression; and providing the exhaust gas from the exhaust recirculation path to a second exhaust gas inlet separate from the first exhaust gas inlet for cooling, preheating, sealing, or any combination thereof.. .
Exxonmobil Upstream Research Company
03/05/15
20150059349

Combustor chamber cooling


A gas turbine engine combustor which is cooled by a hybrid cooling apparatus and method. Heat shields cooled by impingement cooling air are present at an upstream section of the combustor liners and exhausted impingement cooling air is substantially discharged outside of the primary zone of the combustor chamber.
Pratt & Whitney Canada Corp.
03/05/15
20150059348

System and controlling fuel distributions in a combustor in a gas turbine engine


The present disclosure relates to a gas turbine engine system having a plurality of combustors, wherein a first combustor includes one or more fuel nozzles and one or more fuel injectors positioned downstream from the fuel nozzles. The gas turbine engine may also include a first valve disposed along a fuel delivery line between a fuel circuit and the first combustor to adjust a first flow of the fuel to the first combustor.
General Electric Company
03/05/15
20150059341

Gas turbine engine system equipped with rankine cycle engine


A combined-type gas turbine engine system is provided which achieves high efficiency by very effectively using exhaust heat from a gas turbine engine. In a gas turbine engine system including: a compressor for compressing a first working medium; a heater for heating the compressed first working medium by an external heat source; a turbine for outputting power from the first working medium; an intermediate cooler provided at the compressor for cooling the first working medium compressed by a low-pressure compression part of the compressor and supplying the first working medium to a high-pressure compression part of the compressor; and an exhaust heat boiler using as a heating medium an exhaust gas from the turbine, a rankine cycle engine using the intermediate cooler and the exhaust heat boiler as heat sources and a cooling medium of the intermediate cooler as a second working medium..
Kawasaki Jukogyo Kabushiki Kaisha


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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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