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Gas Turbine Engine patents

      

This page is updated frequently with new Gas Turbine Engine-related patent applications.




Date/App# patent app List of recent Gas Turbine Engine-related patents
08/18/16
20160238254 
 Device for improved air and fuel distribution to a combustor patent thumbnailDevice for improved air and fuel distribution to a combustor
A flow conditioning device for a can annular gas turbine engine, including a plurality of flow elements disposed in a compressed air flow path leading to a combustor, configured such that relative adjustment of at least one flow directing element with respect to an adjacent flow directing element during operation of the gas turbine engine is effective to adjust a level of choking of the compressed air flow path.. .
Siemens Energy, Inc.


08/18/16
20160238253 
 Passage geometry for gas turbine engine combustor patent thumbnailPassage geometry for gas turbine engine combustor
An annular grommet is provided for a wall assembly of a combustor section of a gas turbine engine. The annular grommet includes a wall that at least partially defines a chamber.
United Technologies Corporation


08/18/16
20160238252 
 Thermally expandable transition piece patent thumbnailThermally expandable transition piece
A gas turbine engine (gte) including a thermally expandable transition piece is disclosed. The gte includes at least a combustor section having a combustor sleeve, also known as top hat, and a transition piece.
Siemens Energy, Inc.


08/18/16
20160238034 
 Fan assembly patent thumbnailFan assembly
A fan assembly for use in a gas turbine engine includes a fan wheel and a plurality of blades extending radially from the fan wheel away from a central axis of the fan assembly. Each of the blades includes a root coupled with the fan wheel and an airfoil extending radially outwardly from the root.
Rolls-royce Corporation


08/18/16
20160238032 
 Mounting systems for gas turbine engines patent thumbnailMounting systems for gas turbine engines
A mounting system for a gas turbine engine includes a compressor case portion, an inlet frame, an outlet frame, and a mounting structure. The compressor case portion houses rotatable compressor blades.
United Technologies Corporation


08/18/16
20160238023 
 Gas turbine engine airfoil patent thumbnailGas turbine engine airfoil
An airfoil for a turbine engine includes pressure and suction sides that extend in a radial direction from a 0% span position at an inner flow path location to a 100% span position at an airfoil tip. The airfoil has a relationship between a total chord length and a span position and corresponds to a curve that has an increasing total chord length from the 0% span position to a first peak.
United Technologies Corporation


08/18/16
20160238022 
 Low hub-to-tip ratio fan for a turbofan gas turbine engine patent thumbnailLow hub-to-tip ratio fan for a turbofan gas turbine engine
A fan for a turbofan gas turbine engine having a low hub-to-tip ratio is disclosed. The fan includes a rotor hub and a plurality of radially extending fan blades.
Pratt & Whitney Canada Corp.


08/18/16
20160238018 
 Forward-swept impellers and gas turbine engines employing the same patent thumbnailForward-swept impellers and gas turbine engines employing the same
Embodiments of a forward-swept impeller are provide, as are embodiments of a gas turbine engine containing a forward-swept impeller. In one embodiment, the gas turbine engine includes a shaft and a forward-swept impeller mounted to the shaft.
Honeywell International Inc.


08/18/16
20160237950 
 Backside coating cooling passage patent thumbnailBackside coating cooling passage
A component is provided for a gas turbine engine includes a substrate with an aperture. The component also includes a backside coating on a backside of the substrate and at least partially onto an inner boundary of the aperture, where the backside coating forms a passage with the aperture.
United Technologies Corporation


08/18/16
20160237914 
 Geared turbofan with high gear ratio and high temperature capability patent thumbnailGeared turbofan with high gear ratio and high temperature capability
A gas turbine engine comprises a fan rotor having blades with an outer diameter. The outer diameter is greater than or equal to 77 inches (196 centimeters) and less than or equal to 135 inches (343 centimeter).
United Technologies Corporation


08/18/16
20160237909 

Intercooled cooling air using cooling compressor as starter


A gas turbine engine comprises a main compressor section having a high pressure compressor with a downstream discharge, and more upstream locations. A turbine section has a high pressure turbine.
United Technologies Corporation


08/18/16
20160237908 

Intercooled cooling air using existing heat exchanger


A gas turbine engine comprises a main compressor section having a high pressure compressor with a downstream discharge, and more upstream locations. A turbine section has a high pressure turbine.
United Technologies Corporation


08/18/16
20160237907 

Intercooled cooling air with auxiliary compressor control


A gas turbine engine comprises a main compressor section having a high pressure compressor with a downstream discharge, and more upstream locations. A turbine section has a high pressure turbine.
United Technologies Corporation


08/18/16
20160237906 

Intercooled cooling air with heat exchanger packaging


A gas turbine engine comprises a main compressor section having a high pressure compressor with a downstream discharge, and more upstream locations. A turbine section has a high pressure turbine.
United Technologies Corporation


08/18/16
20160237905 

Intercooled cooling air


Aa gas turbine engine comprises a main compressor section having a high pressure compressor with a downstream discharge, and more upstream locations. A turbine section has a high pressure turbine.
United Technologies Corporation


08/18/16
20160237904 

Systems and methods for controlling an inlet air temperature of an intercooled gas turbine engine


The present application and the resultant patent provide an intercooled gas turbine engine. The intercooled gas turbine engine may include a low pressure compressor configured to produce a compressed flow of air, an intercooler, a low pressure compressor configured to produce a compressed flow of air, a high pressure compressor, a second air line positioned between the intercooler and the high pressure compressor and configured to direct the first portion of the compressed flow of air toward the high pressure compressor, and a bypass air line positioned between the low pressure compressor and the high pressure compressor and configured to direct a second portion of the compressed flow of air to the second air line.
General Electric Company


08/18/16
20160237903 

High pressure compressor rotor thermal conditioning using conditioned compressor air


A gas turbine engine comprises a compressor including a disk and a blade. A turbine rotor has a disk and a blade.
United Technologies Corporation


08/18/16
20160237901 

Intercooled cooling air with improved air flow


A gas turbine engine comprises a main compressor section having a high pressure compressor with a downstream discharge, and more upstream locations. A turbine section has a high pressure turbine.
United Technologies Corporation


08/18/16
20160237899 

Gas turbine lubrication systems


A lubrication circuit for a gas turbine engine includes a bearing compartment, an air inlet connected to the bearing compartment, a lubricant inlet, and a lubricant outlet. The air inlet fluidly connects the bearing compartment to an environment external to the compartment.
United Technologies Corporation


08/18/16
20160237857 

Modular components for gas turbine engines


A system for maintaining a position of a bearing compartment in a gas turbine during disassembly of a low-pressure turbine of the gas turbine engine includes a forward annular shaft defining an engine centerline axis. The system includes a ring radially inward from and engaged with an inner diameter surface of the forward annular shaft.
United Technologies Corporation


08/18/16
20160237854 

Spacer for power turbine inlet heat shield


A gas turbine engine comprises an exhaust section member, a turbine section member, a heat shield and a spacer. The turbine section member is coupled to the exhaust section member.
United Technologies Corporation


08/18/16
20160237852 

Tortuous cooling passageway for engine component


One exemplary embodiment of this disclosure relates to a gas turbine engine including a component having a body. The body includes a tortuous cooling passageway, which provides a flow path extending between an inlet in a first surface of the body and an exit in a second surface of the body..
United Technologies Corporation


08/18/16
20160237851 

Probe tip cooling


A probe cooling system for a gas turbine engine includes a probe housing and a bushing disposed between an end of the probe housing and a gas path, the bushing extending from the end of the probe housing to form a cavity. The system also includes a first plenum defined within the probe housing and configured to direct air from an internal cooling air supply towards the cavity.
United Technologies Corporation


08/18/16
20160237849 

S-shaped trip strips in internally cooled components


A component for a gas turbine engine is provided. The component includes an internal cooling passage disposed within the component, and an s-shaped trip strip formed on a surface of the internal cooling passage..
United Technologies Corporation


08/18/16
20160237847 

Icing prevention of a gas turbine engine pressure sensing assembly


A combination of a gas turbine pressure sensing assembly and an engine electronics unit. The pressure sensing assembly includes a pressure manifold having an air inlet and one or more air outlets.
Rolls-royce Controls And Data Services Limited


08/18/16
20160237846 

Access port for a casing of a gas turbine engine and plug for plugging the access port


There is disclosed an access port for a casing of a gas turbine engine and a plug for plugging the access port. The access port and plug each include first and second baulking formations which are configured to engage with one another.
Rolls-royce Plc


08/18/16
20160237845 

Variable area vane endwall treatments


A gas turbine engine component includes an outer diameter endwall, an inner diameter endwall spaced radially inward of the outer diameter endwall, and at least one body supported between the outer and inner endwalls for rotation about an axis. The body includes an outer diameter surface spaced from the outer diameter endwall by a first gap and an inner diameter surface spaced from the inner diameter endwall by a second gap.
United Technologies Corporation


08/18/16
20160237842 

Gas turbine engine blade outer air seal thermal control system


A clearance control system for a gas turbine engine is provided. The system includes an inner axial wall that extends between a forward wall and an aft wall.
United Technologies Corporation


08/18/16
20160237837 

Endwall countouring trench


A gas turbine engine component comprises a casing, and a component fixed to the casing to extend from a first edge to a second edge. The component has a first side and a second side.
United Technologies Corporation


08/18/16
20160237836 

Structural honeycomb panel


A structural panel for use with a gas turbine engine includes a first exterior wall, a second exterior wall, and interior walls. The first exterior wall includes a first exterior surface and a first interior surface parallel to the first exterior surface.
United Technologies Corporation


08/18/16
20160237835 

Compressible fan blade with root spacer


A spacer for use in a hub and blade assembly of a gas turbine engine including a first layer of a first material forming the spacer body having an elongate shape. The first material has a first stiffness.
United Technologies Corporation


08/18/16
20160237827 

Gas turbine blade with corrugated tip wall


A gas turbine engine blade (10), including a base portion (12) having a cast wall, and a tip portion (14) attached to the base portion and having a wall (60) formed by an additive manufacturing process. The tip portion wall may be formed to be solid and less than 2 mm in thickness, or it may be corrugated and be greater than 2 mm in thickness.
Siemens Energy, Inc.


08/18/16
20160237824 

Rotating component balance ring


A balance ring for a gas turbine engine has a ring shaped body with a first radial thickness, an anti-rotation tab extending outward from the body and at least one millable balancing feature connected to the body.. .
United Technologies Corporation


08/18/16
20160236334 

Tool for removing collars


A method comprises the steps of providing a tool over a collar secured to a stud on a gas turbine engine system. The collet is driven to rotate and remove the collar from the stud.
United Technologies Corporation


08/18/16
20160236298 

Laser powder deposition weld rework for gas turbine engine non-fusion weldable nickel castings


A method is provided for reworking a component. The method includes at least partially filling a cavity in a non-fusion weldable base alloy with a multiple of layers of a multiple of laser powder deposition spots formed of a filler alloy.
United Technologies Corporation


08/18/16
20160236271 

Additive manufactured fuel nozzle core for a gas turbine engine


A method of manufacturing a fuel component for a gas turbine engine combustor includes additive manufacturing a sacrificial core and manufacturing a fuel component body at least partially around the sacrificial core. The sacrificial core is at least partially removed to at least partially define an internal geometry of the fuel component.
United Technologies Corporation


08/11/16
20160231068 

Additive manufactured ducted heat exchanger system with additively manufactured header


A heat exchanger system includes an additively manufactured inlet header upstream of, and in fluid communication with, the heat exchanger core and an additively manufactured exit header downstream of, and in fluid communication with, the heat exchanger core. A method of manufacturing a header for a ducted heat exchanger system for a gas turbine engine includes additively manufacturing a header with respect to a desired airflow therethrough..
United Technologies Corporation


08/11/16
20160231064 

Heat exchanger system with additively manufactured heat transfer tube that follows a non-linear path


A heat exchanger system for a gas turbine engine includes a plurality of fins; and an additively manufactured heat transfer tube that extends through the plurality of fins, the additively manufactured heat transfer tube follows a non-linear path though said plurality of fins.. .
United Technologies Corporation


08/11/16
20160230993 

Combustor liner effusion cooling holes


A gas turbine engine component may be manufactured by an additive manufacturing process. The component may be a combustor liner.
United Technologies Corporation


08/11/16
20160230875 

Gearbox having gear baffle apparatus


A gearbox in a gas turbine engine includes an enclosed gearbox housing, at least a pair of intermeshing gears lubricated and rotatably supported within the gearbox housing, and a baffle apparatus axially spaced apart from and positioned at least at one side of the pair of gears, the baffle apparatus including a collector defining a main opening adjacent a meshing point of the intermeshing gears for collecting and redirecting lubricant squeezed out axially from the intermeshing gears.. .
Pratt & Whitney Canada Corp.


08/11/16
20160230843 

Gearbox for gas turbine engine


A gearbox for a gas turbine engine includes a housing that includes a cavity provided between opposing first and second mounting surfaces. An input gear shaft is coupled to a drive gear.
United Technologies Corporation


08/11/16
20160230805 

Shaft of a gas turbine engine in hybrid design


A shaft of a turbine engine made from fiber-composite material, having a sinusoidal inner profile which extends over the entire length of the shaft on its inner wall, where a first inner layer forms the sinusoidal inner profile and has fibers arranged at ±45° relative to the axial direction, where the concave outer areas of the first layer are filled with fibers parallel to the center axis by a second layer to form a cylindrical outer contour. The second layer extends in the circumferential direction only in the concave area.
Rolls-royce Deutschland Ltd & Co Kg


08/11/16
20160230711 

Systems and methods for carbon black production with a gas turbine engine having exhaust gas recirculation


A gas turbine system includes a turbine combustor, a turbine, an exhaust gas compressor, an exhaust gas recirculation (egr) system, a carbon black recovery system, and a carbon black production controller. The carbon black production controller monitors data corresponding to a parameter of the carbon black.
Exxonmobil Upstream Research Company


08/11/16
20160230677 

Variable geometry gas turbine engine for use in inclement weather


A variable-geometry system for a gas turbine engine can be used to improve operations in various inclement weather conditions. This may be achieved by varying the orientation of an element in a gas turbine engine flowpath in response to a comparison between sensor-gathered parameter data and stored parameter values and ranges using a pre-programmed algorithm.
United Technologies Corporation


08/11/16
20160230674 

Gear reduction for lower thrust geared turbofan


A gas turbine engine comprises a fan rotor having a hub and a plurality of fan blades extending radially outwardly of the hub. A compressor is positioned downstream of the fan rotor, and has a first compressor blade row defined along a rotational axis of the fan rotor and the compressor rotor.
United Technologies Corporation


08/11/16
20160230667 

Accumulator assisted gas turbine engine start system and methods therefor


A gas turbine engine assembly is provided having a gas turbine engine and a fuel supply in flow communication with the gas turbine engine. An accumulator is positioned in flow communication between the fuel supply and the gas turbine engine to store fuel pressure in fuel flowing from the fuel supply to the gas turbine engine..
United Technologies Corporation


08/11/16
20160230666 

Orientation feature for swirler tube


A cooling structure for a gas turbine engine comprises a gas turbine engine structure defining a cooling cavity. A cooling component is configured to direct cooling flow in a desired direction into the cooling cavity.
United Technologies Corporation


08/11/16
20160230665 

Turbocooled vane of a gas turbine engine


The present invention discloses a novel apparatus and methods for augmenting the power of a gas turbine engine, improving gas turbine engine operational flexibility and efficiency, and reducing the response time necessary to meet changing demands of an electrical grid. Improvements in power augmentation and engine operation include systems and methods for providing rapid response given a change in electrical grid..
Powerphase Llc


08/11/16
20160230664 

Pedestals with heat transfer augmenter


A gas turbine engine component comprises a first side wall, and a second side wall spaced apart from the first side wall. At least one internal cooling channel is formed between the first and second side walls.
United Technologies Corporation


08/11/16
20160230662 

Gas turbine engine component with vascular cooling scheme


A component according to an exemplary aspect of the present disclosure includes, among other things, a body portion and a cooling scheme disposed inside the body portion, the cooling scheme including a vascular engineered lattice structure and a heat transfer device adjacent to the vascular engineered lattice structure.. .
United Technologies Corporation


08/11/16
20160230661 

Gas turbine engine having section with thermally isolated area


A gas turbine engine according to an exemplary aspect of the present disclosure includes, among other things, a first compressor having a first overall pressure ratio, and a second compressor having a second overall pressure ratio. A ratio of the first overall pressure ratio to the second overall pressure ratio is greater than or equal to about 2.0.
United Technologies Corporation


08/11/16
20160230658 

Gas turbine engine and an airflow control system


A gas turbine engine includes a core flowpath for flowing a core stream, a second flowpath located radially outward from the core flowpath for flowing a second stream, and an auxiliary flowpath located radially outward from the second flowpath for flowing an auxiliary stream. A heat exchanging device is constructed and arranged to divert a portion of the second stream into the auxiliary flowpath.
United Technologies Corporation


08/11/16
20160230602 

Mid-turbine frame assembly for a gas turbine engine


A tie rod assembly for a mid-turbine frame includes at least one tie rod for connecting an outer frame case to an inner frame case. At least one tie rod includes an inlet passage that branches into a first branch and a second branch.
United Technologies Corporation


08/11/16
20160230597 

Gas turbine engine having section with thermally isolated area


A section of a gas turbine engine according to an exemplary aspect of the present disclosure includes, among other things, a thermally isolated area, and a first rotor disk and a second rotor disk. Each of the first and second rotor disks are provided within the thermally isolated area..
United Technologies Corporation


08/11/16
20160230596 

Airfoil with skin core cooling


A gas turbine engine component has an airfoil extending radially inwardly of an outer platform to an inner platform. A central passage is formed within the airfoil and has an inlet end for receiving cooling air.
United Technologies Corporation


08/11/16
20160230590 

Method of measuring turbine blade tip erosion


A method of designing a turbine blade includes the steps of forming at least two notches on a tip of a turbine blade, each of the at least two notches having a known dimension. The turbine blade has a pressure side and a suction side.
United Technologies Corporation


08/11/16
20160230587 

Turbine assembly having a rotor system lock


A rotor system lock for a gas turbine engine is described which blocks movement of rotating wheel assemblies relative to static vane assemblies in a gas turbine engine in order to block unintended rotation (or windmilling) of the gas turbine engine when it is exposed to high winds while at rest or to ram air during pre-launch flight and thereby avoid damage to components of the engine.. .
Rolls-royce Corporation


08/11/16
20160230583 

Blade tip clearance control system including boas support


This disclosure relates to a gas turbine engine including a blade outer air seal (boas) mounted radially outwardly of a blade. The engine further includes a boas support.
United Technologies Corporation


08/11/16
20160230581 

Gas turbine engine airfoil component platform seal cooling


A gas turbine engine component array includes first and second components each having a platform. The platforms are arranged adjacent to one another and provide a gap.
United Technologies Corporation


08/11/16
20160230580 

Recirculation seal for use in a gas turbine engine


A recirculation seal for use within a gas turbine engine. The recirculation seal includes a first seal base, including a first seal base axis.
United Technologies Corporation


08/11/16
20160230578 

Gas turbine engine containment structures


A containment structure for a gas turbine engine includes a stator shroud with a wall. The stator shroud wall extends axially between a shroud inlet aperture and the shroud outlet aperture.
United Technologies Corporation


08/11/16
20160230576 

Vane assemblies for gas turbine engines


A vane ring for a gas turbine engine includes an outer end wall and a plurality of spars coupled to the outer end wall. The vane ring further includes an inner end wall positioned radially inward of the outer end wall and coupled to the spars.
Rolls-royce Corporation


08/11/16
20160230572 

Fan blade root


A dovetail root of a fan blade configured for operation within the fan assembly of a gas turbine engine. The dovetail root is imparted with a compressive residual stress layer along the outer faces of the dovetail root preventing crack formation within the dovetail root when the gas turbine engine is in operation.
United Technologies Corporation


08/11/16
20160230570 

Modified atmosphere melt infiltration


A ceramic matrix composite component for use in a gas turbine engine and method for making the same are described herein. The component comprising a body and an outer region.
Rolls-royce Corporation


08/11/16
20160230568 

Ceramic matrix composite gas turbine engine blade


The disclosure describes a gas turbine engine blade that includes a dovetail portion comprising a first ceramic matrix composite, an airfoil portion comprising the first ceramic matrix composite, a transition portion between the airfoil portion and the dovetail portion, and a platform portion that substantially surrounds the transition portion. The airfoil portion may define a capture feature that is configured to engage with and mechanically restrain the platform portion from moving beyond the capture feature toward a tip of the airfoil portion..
Rolls-royce North American Technologies, Inc.


08/11/16
20160230567 

Gas turbine engine airfoil having serpentine fed platform cooling passage


A gas turbine engine airfoil includes a platform, and spaced apart walls that provide an exterior airfoil surface that extends radially from the platform to an end opposite the platform. A serpentine cooling passage is arranged between the walls and has a first passageway that extends from the platform toward the end and a second passageway fluidly connecting to the first passageway and extending from the end toward the platform to an end.
United Technologies Corporation


08/11/16
20160230563 

Trip strip restagger


A. Structure for creating a core for a gas turbine engine component comprises a body with a curved surface defining a turn passage.
United Technologies Corporation


08/11/16
20160230560 

Gas turbine engines with internally stretched tie shafts


A tie shaft for a rotating group of an engine core includes a cylindrical body having an internal surface and an external surface and extending between a forward end and an aft end. The tie shaft further includes a first group of internal grooves on the internal surface of the cylindrical body proximate to the forward end and a second group of internal grooves on the internal surface of the cylindrical body proximate to the aft end.
Honeywell International Inc.


08/11/16
20160229549 

Apparatus and methods for powering an electrical device associated with an aircraft rotor technical field


Apparatus and methods for generating electrical power for powering a device associated with a bladed rotor driven by a gas turbine engine of an aircraft are disclosed. The apparatus includes a rotor shaft coupled the bladed rotor of the aircraft and driven by a turbine shaft of the engine via a speed-reducing gear train.
Pratt & Whitney Canada. Corp.


08/11/16
20160229543 

Icephobic flowpath for a nose cone and method therefor


A gas turbine engine is provided having a nose cone, wherein the nose cone is symmetrically disposed about an axis. The nose cone includes a leading edge and a base.
United Technologies Corporation


08/11/16
20160229005 

Mobile repair and manufacturing gas turbine engine maintenance


Refurbishment of hot gas path components of gas turbine engines can now be performed locally in lieu of the traditional use of a specialized fixed regional repair facility. A mobile manufacturing platform (10) is provided with the capability to inspect and to repair ceramic coated superalloy alloy components, including the ability to perform flux assisted laser processing (68) of powdered materials.
Siemens Energy, Inc.


08/11/16
20160228941 

Lost core molding cores for forming cooling passages


In a featured embodiment, a lost core assembly includes a ceramic component having a tapered shape in a radial direction. A refractory metal component extends radially from the ceramic core component.
United Technologies Corporation


08/11/16
20160228929 

Methods of manufacturing and cleaning


Methods of cleaning internal portions of additively manufactured components are provided, together with an apparatus for carrying out the cleaning. The methods use an impacting element which is contained within the internal portion and the component is vibrated to clean material from the component and leave one or more hollow portions.
Rolls-royce Plc


08/11/16
20160228913 

Open-cell reticulated foam


A foam for use in a lost-foam casting process utilized in the manufacture of a component for a gas turbine engine, the foam having a void fraction less than or equal to ninety five percent, is disclosed. The foam may include a first layer comprising polymer foam having an open-cell structure and a void fraction greater than ninety five percent.
United Technologies Corporation


08/04/16
20160223202 

Systems and methods for high volumetric oxidant flow in gas turbine engine with exhaust gas recirculation


A system having a gas turbine engine is provided. The gas turbine engine includes a turbine and a combustor coupled to the turbine.
Exxonmobil Upstream Research Company


08/04/16
20160223201 

Fuel injectors for gas turbine engines


A fuel injector for a gas turbine engine includes a monolithic nozzle body that defines within its interior one or more fuel circuits. Each fuel circuit includes an inlet, an outlet orifice, a main passage fluidly coupling the inlet with the outlet orifice, and a branch passage connected to the main passage.
Delavan Inc.


08/04/16
20160223193 

System and combustion swirler anti-rotation


A swirler comprising an anti-rotation feature is provided. The swirler may be installed on a combustor within a gas turbine engine.
United Technologies Corporation


08/04/16
20160222982 

Fluid injector for cooling a gas turbine engine component


An example method of cooling a compressor of a gas turbine includes, among other things, diverting a flow from a compressor, and directing the flow at the compressor in a direction, the direction having a circumferential component and an axial component.. .
United Technologies Corporation


08/04/16
20160222975 

Dual direction windmill pump for geared turbofan engine


A lubrication system includes a shaft rotatable about an axis, a lubrication pump configured to supply a lubricant flow to a gear system, and a gear train coupled to the shaft and configured to drive the lubrication pump in a first direction responsive to rotation of the shaft in both the first direction and a second direction. A gas turbine engine and method are also disclosed..
United Technologies Corporation


08/04/16
20160222973 

Gas turbine engine compressors having optimized stall enhancement feature configurations and methods for the production thereof


Multistage gas turbine engine (gte) compressors having optimized stall enhancement feature (sef) configurations are provided, as are methods for the production thereof. The multistage gte compressor includes a series of axial compressor stages each containing a rotor mounted to a shaft of a gas turbine engine.
Honeywell International Inc.


08/04/16
20160222888 

Fan drive gear system


A gas turbine engine includes a fan section and a star gear system for driving the fan section. A first fan section support bearing is mounted forward of the star gear system and a second fan section bearing is mounted aft of the star gear system..
United Technologies Corporation


08/04/16
20160222885 

Thermal management system manifold


A single, unitary thermal management system (tms) manifold for a gas turbine engine is provided which comprises one or more interfaces for mounting various thermal management system components directly to the tms manifold. The tms manifold also defines fluid passages for transferring fuel, engine lubricant or generator oil from one component to another component.
United Technologies Corporation


08/04/16
20160222823 

Insert and standoff design for a gas turbine engine vane


A component for a gas turbine engine according to an exemplary aspect of the present disclosure includes, among other things, a platform, an airfoil that extends from the platform, and an insert positioned such that a first portion of the insert extends relative to a surface of the platform and a second portion extends inside the airfoil. A standoff supports the insert above the surface..
United Technologies Corporation


08/04/16
20160222822 

Turbine vane with load shield


A turbine vane for use in a gas turbine engine is disclosed. The turbine vane includes an inner platform, an outer platform spaced from the inner platform, and an airfoil that extends from the inner platform to the outer platform.
Rolls-royce Corporation


08/04/16
20160222821 

Vibration damping assembly and damping vibration in a gas turbine engine


A vibration damping assembly and a method of damping vibration in a gas turbine engine are disclosed. The vibration damping assembly includes a strut configured to couple a fan case and turbine engine case of a turbine engine, a strut cavity disposed within the strut, and vibration damping media disposed in the strut cavity..
United Technologies Corporation


08/04/16
20160222815 

High efficiency geared turbofan


A gas turbine engine comprises a fan drive turbine. The fan drive turbine drives the fan through a gear reduction; a change in enthalpy is defined across the gas turbine engine.
United Technologies Corporation


08/04/16
20160222814 

Turbo-compressor with geared turbofan


A gas turbine engine includes a fan section. A turbo-compressor section is connected to the fan section through a speed change mechanism..
United Technologies Corporation


08/04/16
20160222812 

Seals for gas turbine engines


A turbine shroud for use in a gas turbine engine that includes a metallic carrier, a blade track, and a seal is disclosed. The seal is engaged with surfaces of the metallic carrier and the blade track to block ingress of hot gasses at the interface of the blade track and the metallic carrier..
Rolls-royce Corporation


08/04/16
20160222811 

Process of boas grinding in situ


A process for machining a turbine engine blade outer air seal in situ, the process comprising replacing a blade with a cutting tool assembly proximate a blade outer air seal, wherein the blade outer air seal is assembled in a gas turbine engine case. The process includes coupling a blower to the blade outer air seal.
United Technologies Corporation


08/04/16
20160222809 

Gas turbine engine with seal having protrusions


A gas turbine engine includes a turbine section. The turbine section includes a disk that is rotatable about an axis.
United Technologies Corporation


08/04/16
20160222808 

Gas turbine engine with disk having periphery with protrusions


A gas turbine engine includes a turbine section that has a disk rotatable about an axis. The disk has circumferentially-spaced blade mounting features and radially outer rim surfaces extending circumferentially between the blade mounting features.
United Technologies Corporation


08/04/16
20160222806 

Turbine vane with load shield


A turbine vane for use in a gas turbine engine is disclosed. The turbine vane includes an inner platform, an outer platform spaced from the inner platform, and an airfoil that extends from the inner platform to the outer platform.
Rolls-royce Corporation


08/04/16
20160222802 

Cmc blade with monolithic ceramic platform and dovetail


A blade for a gas turbine engine includes a fiber reinforced ceramic matrix composite structure that provides an airfoil with an exposed exterior airfoil surface and a refractory structure that provides at least an outer portion of a root secured relative to the airfoil.. .
United Technologies Corporation


08/04/16
20160222798 

Additive manufactured inseparable platform damper and seal assembly for a gas turbine engine


A damper-seal assembly for a gas turbine engine includes an additively manufactured seal and an additively manufactured damper inseparably assembled with the additively manufactured seal.. .
United Technologies Corporation


08/04/16
20160222795 

Turbine airfoil cooling core exit


A gas turbine engine component has an airfoil extending from a platform to a tip at an end of the airfoil spaced from the platform. The airfoil has a suction wall and a pressure wall, with at least one channel extending toward the tip from the platform.
United Technologies Corporation


08/04/16
20160222794 

Incidence tolerant engine component


This disclosure relates to a gas turbine engine including a component having a leading edge, a pressure side and a suction side opposite the pressure side. The component includes a first group of showerhead holes in the leading edge and a second group of showerhead holes in one of the pressure side and the suction side.
United Technologies Corporation


08/04/16
20160222793 

Cooling configuration for engine component


This disclosure relates to a gas turbine engine. The engine includes a component having a first wall and a second wall spaced-apart from the first wall.
United Technologies Corporation


08/04/16
20160222792 

Staggered core printout


A core for gas turbine engine component comprises a body extending between first and second ends to define a length, and extending between first and second edges to define a width. A plurality of core extensions are formed as part of the body.
United Technologies Corporation


08/04/16
20160222788 

Disk outer rim seal


A turbine section comprises a rotor, blade and rim seal. The rotor comprises a rim defining an outer diameter surface, and a slot in the outer diameter surface.
United Technologies Corporation


08/04/16
20160222785 

Balancing apparatus, arrangement and method


The present invention provides an apparatus for providing a balancing weight in a groove on a rotor disk in a gas turbine engine. The apparatus comprises an elongate reservoir for housing a hardenable material and an inflatable element in fluid communication with the distal end of the elongate reservoir.
Rolls-royce Plc


08/04/16
20160222784 

Gas turbine engine rotor disk balancing


A gas turbine engine rotor disk includes a web that extends inward in a radial direction from a rim to a bore that circumscribes an axis. An annular ridge extends axially from the side of the web.
United Technologies Corporation




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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