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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


Gas turbine engine inlet assembly and method of making same

Pratt & Whitney Canada Corp.

Gas turbine engine inlet assembly and method of making same

Gas turbine engines with turbine airfoil cooling

Honeywell International

Gas turbine engines with turbine airfoil cooling

Gas turbine engines with turbine airfoil cooling

Ecoservices

System for washing an aero gas turbine engine

Date/App# patent app List of recent Gas Turbine Engine-related patents
03/26/15
20150086381
 Internally cooled airfoil patent thumbnailnew patent 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 patent thumbnailnew patent 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 patent thumbnailnew patent 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 patent thumbnailnew patent 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 patent thumbnailnew patent 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 patent thumbnailnew patent 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 patent thumbnailnew patent 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 patent thumbnailnew patent 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 patent thumbnailnew patent 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 patent thumbnailPiloted 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
02/26/15
20150056073

Method and system for cooling rotor blade angelwings


A system for cooling an angelwing coupled to a rotor blade in a gas turbine engine is provided. An angelwing coupled to a shank of a rotor blade includes at least one cooling passage extending from at least one inlet opening coupled in flow communication with a gas turbine engine inner wheelspace to at least one outlet opening coupled in flow communication with a gas turbine engine outer rotor/stator cavity.
General Electric Company
02/26/15
20150053750

High temperature brazing fixture and manufacture


A high temperature brazing fixture and method of manufacture for a gas turbine component made of a superalloy is disclosed herein. The high temperature brazing fixture includes a first and second frame member, a support member, and positioning member, all of which are made from the superalloy and fastened together using tab and tab lock couplings.
Solar Turbines Incorporated
02/26/15
20150052910

Apparatus and servicing gas turbine engines


The present disclosure relates to an apparatus having an elongated body configured to be inserted into a tubular structure extending between a first combustor and a second combustor of a gas turbine engine. A movable arm may be positioned proximate to a first end of the elongated body, and the movable arm may be configured to engage a surface of the first combustor when the elongated body is placed within the tubular structure.
General Electric Company
02/26/15
20150052908

Bleed duct assembly for a gas turbine engine


A bypass duct has a support unit comprising a pair of aerofoils arranged as an “a” frame. A bleed duct assembly is provided on the radially inner wall of the bypass duct annulus and the aerofoils project from the surface and extend across the annulus between the inner wall and an outer wall of the annulus.
Rolls-royce Deutschland Ltd & Co Kg
02/26/15
20150052907

Thermal management system for gas turbine engine


A method of thermal management for a gas turbine engine comprising selectively positioning a valve to communicate a bypass flow into either an environmental control system (ecs) pre-cooler or an air oil cooler (aoc) “peaker” through a common inlet.. .
United Technologies Corporation
02/26/15
20150052899

Airblast fuel injector


An airblast fuel injector for a gas turbine engine fuel spray nozzle has, in order from radially inner to outer, a coaxial arrangement of an inner air swirler passage, an annular fuel passage, an annular outer air swirler passage, and an annular shroud air swirler passage. The injector further has an annular shroud having an inner surface profile.
Rolls-royce Plc
02/26/15
20150052872

Thermal isolating service tubes and assemblies thereof for gas turbine engines


Thermal isolating service tubes and assemblies thereof for gas turbine engines are provided. The thermal isolating service tube comprises an inner tubular member defining a fluid passage and at least one outer tubular member disposed about the inner tubular member.
Honeywell International Inc.
02/26/15
20150052749

Method of fabricating integrally bladed rotor using surface positioning in relation to surface priority


A method of fabricating an integrally bladed rotor for gas turbine engines according to one aspect includes a step of positioning a blade on a hub in a joining procedure by using a priority surface of the blade as a reference surface. The priority surface is determined in relation to importance of surface functionality of the blades during engine operation.
Pratt & Whitney Canada Corp.
02/19/15
20150050158

Gas turbine engine component including a compliant layer


A blade for a gas turbine engine comprises a blade portion having a first end and a second end and an engagement portion including a first surface coupled to the second end of the blade portion and a second surface coupled to the second end of the blade portion, the first and second surfaces arranged to extend divergently away from one another. The engagement portion is adapted for coupling to a wheel included in a gas turbine engine wheel..
Rolls-royce North American Technologies, Inc.
02/19/15
20150050151

Annulus filler


An annulus filler is provided for mounting to a rotor disc of a gas turbine engine and bridging the gap between two adjacent blades attached to the rotor disc, the annulus filler has an outer lid which defines an airflow surface for air being drawn through the engine, the lid having a leading edge and a trailing edge in an axial airflow direction. The annulus filler further has a support arrangement which is connectable to the rotor disc.
Rolls-royce Plc
02/19/15
20150050150

Annulus filler


An annulus filler, mounted to a rotor disc of a gas turbine engine and bridging the gap between two adjacent blades attached to the rotor disc, is disclosed. The annulus filler, formed from a polymer matrix composite material, includes an outer lid, defining an airflow surface for air drawn through the engine in an axial airflow direction, and a support structure, connectable to the rotor disc, to support the rear of the lid on the rotor disc.
Rolls-royce Plc
02/19/15
20150050127

Air with integral spring for a gas turbine engine exhaust drive


A seal assembly for an exhaust duct section of a gas turbine engine includes a multiple of springs that axially extend from a split hoop opposite a seal surface.. .
United Technologies Corporation
02/19/15
20150050123

Switched reluctance, fully superconducting, integrated ring turbine motor, generator gas turbine, engine stage (ssrgts)


A superconducting integrated ring turbine motor generator gas turbine engine stage of the present invention includes a combination of turbine vanes, rotors and blisk assemblies that prevent temperatures during operation from interfering with the extraction or control of power generation processes. The engine stage includes a ring having an evenly spaced array of aerodynamic vanes affixed on the inside or outside of the ring.
02/19/15
20150047361

Nozzle with multi-tube fuel passageway for gas turbine engines


A pilot fuel nozzle for a combustor includes an igniter forming a central body extending along a longitudinal center of the nozzle. A nozzle tip includes a plurality of circumferentially spaced fuel passages and a plurality of circumferentially spaced air passages extending to an outer side of the nozzle tip.
Siemens Aktiengesellschaft
02/19/15
20150047359

Axial flow machine cooling system


This invention concerns a system for cooling components in a gas turbine engine, the gas turbine engine including a compressor for driving a primary gas flow to a combustor and a turbine arranged to be driven by combustion gases from the combustor, wherein the system includes: an annular cooling flow passage arranged for fluid communication between the compressor and the turbine, the flow passage having a first inlet arranged to receive gas from the primary gas flow downstream of compressor, and a second inlet located upstream of the first inlet, wherein the annular cooling flow passage has at least one internal wall for guiding airflow from the first inlet towards the airflow from the second inlet, the airflow from the first and second inlets coalesce within the annular flow passage prior to passing along the passage in a direction from the compressor to the turbine.. .
Rolls-royce Plc
02/19/15
20150047315

Gas turbine engine flow duct having integrated heat exchanger


A gas turbine engine flow duct comprising a flow duct disposed along an engine centerline of the gas turbine engine and defining a stream flow passage, and first and second rows of heat exchangers disposed along the engine centerline of the gas turbine engine and integrated in the flow duct in fluid communication with the stream flow passage of the flow duct.. .
Rolls-royce North American Technologies, Inc.
02/12/15
20150046126

Gas turbine engine rotor assembly optimization


A method for optimizing a rotor assembly for a gas turbine engine is disclosed. The rotor assembly includes rotating parts including a first journal and one or more rotor disks.
Solar Turbines Incorporated
02/12/15
20150044056

Airfoil with leading edge reinforcement


A leading edge member for a composite vane of a gas turbine engine. The leading edge member includes a first leg and a second leg.
Rolls-royce Corporation
02/12/15
20150044054

Composite retention feature


A retention feature for use in a gas turbine engine is disclosed herein. The retention feature includes a ceramic post, an insert, and a braze layer coupling the insert to the ceramic post.
Rolls-royce Corporation
02/12/15
20150044050

Composite blade with an integral blade tip shroud and forming the same


A gas turbine engine airflow member including a blade core portion, a shroud tip portion extending from the blade core portion, and an airfoil portion formed exteriorly to the blade core portion, where the blade core portion and the shroud tip portion are constructed as a first unitary structure and the airfoil portion is constructed as a second structure. A method of forming a gas turbine engine component is also disclosed..
Rolls-royce Corporation
02/12/15
20150044049

Dovetail retention system for blade tracks


A turbine shroud for a gas turbine engine includes a metallic support ring and a ceramic blade track. The blade track is formed from a plurality of blade track segments including dovetail posts.
Rolls-royce Corporation
02/12/15
20150044044

Turbine shroud


A turbine shroud for a gas turbine engine includes an annular metallic carrier, a ceramic blade track, and a cross-key connection formed between the annular metallic carrier and the ceramic blade track. The cross-key connection is formed between the annular metallic carrier and the ceramic blade track to locate the ceramic blade track relative to the annular metallic carrier.
Rolls-royce Corporation
02/12/15
20150044035

High porosity abradable coating


An abradable coating for a gas turbine engine includes a bond coat, an intermediate layer, and a porous layer. The bond coat includes a metal coating and a thickness from 0.152 millimeters to 0.229 millimeters.
Solar Turbines Incorporated
02/12/15
20150044029

Aerofoil


An aerofoil component of a gas turbine engine has an aerofoil portion which spans, in use, a working gas annulus of the engine. The aerofoil portion has a pressure side outer wall and a suction side outer wall, each extending from the leading edge to the trailing edge of the aerofoil portion.
Rolls-royce Plc
02/12/15
20150044028

Low pressure ratio fan engine having a dimensional relationship between inlet and fan size


According to an example embodiment, a gas turbine engine assembly includes, among other things, a fan that has a plurality of fan blades. A diameter of the fan has a dimension d that is based on a dimension of the fan blades.
United Technologies Corporation
02/12/15
20150042023

Hybrid part made from monolithic ceramic skin and cmc core


A hybrid part for use in a gas turbine engine has a platform and an attachment feature. The platform and an exterior portion of the attachment feature are formed from a monolithic ceramic material.
United Technologies Corporation
02/12/15
20150041274

Clutch coupled to gas turbine engine and cooling


A gas turbine engine clutch includes a dry clutch assembly, forward and aft working areas, and a shaft. The dry clutch assembly is operative to receive power from a gas turbine engine.
Rolls-royce Corporation
02/12/15
20150040577

System and preventing ice crystal accretion in gas turbine engines


A system and method of operating an engine anti-ice system includes supplying heat from one or more heat sources to one or more components on or within a gas turbine engine, sensing data representative of one or more parameters related to ice crystal accretion, and based on the data, at least selectively inhibiting at least selected ones of the one or more heat sources from supplying heat to at least selected ones of the one or more components on or within the gas turbine engine.. .
Honeywell International Inc.
02/12/15
20150040575

Fuel igniter assembly having heat-dissipating element and methods of using same


A combustor for a gas turbine engine includes a combustion chamber and a fuel igniter assembly. The combustion chamber is defined by an annular inner combustor liner and an annular outer combustor liner.
Unison Industries, Llc
02/12/15
20150040572

Gas turbine engine combustor with fluidic control of swirlers


A system and method for controlling air flow through a combustor swirler assembly that includes an inner swirler and an outer swirler. A bistable fluidic amplifier that includes an air inlet, a first air outlet, a second air outlet, and a control port is disposed upstream of the combustor swirler assembly.
Honeywell International Inc.
02/12/15
20150040570

Gas turbine engine component having foam core and composite skin with cooling slot


In one embodiment, a gas turbine engine component includes a foam based core and a composite skin member. Both the foam based core and the composite skin member can be used to structurally support the gas turbine engine component.
Rolls-royce North American Technologies, Inc.
02/12/15
20150040538

Rotor noise suppression


An apparatus is disclosed that includes a gas turbine engine including a first rotor blade axially adjacent a second rotor blade and an aperture formed in one of the first rotor blade and the second rotor blade and structured to emit a fluid therefrom. A fluid source is in flow communication with the aperture and configured to flow the fluid through the aperture..
Rolls-royce Corporation
02/12/15
20150040393

Manufacturing exhaust diffuser shell with strut shield collar and joint flange


Manufacture of a gas turbine exhaust diffuser shell (40a/40b) to achieve a final cross-sectional shell geometry by forming an opening (76) in the shell to receive a strut shield collar (46); forming a compensating outward bowing (78) of the shell around the opening that departs from a desired final shell geometry in an amount and shape that compensates for a welding shrinkage when welding the collar in the opening; and welding the collar in the opening. This produces the desired shell geometry after the welding.


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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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