Follow us on Twitter
twitter icon@FreshPatents

Gas Turbine Engine patents

Bulk PDF Downloads
      

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




 Heat shield for a combustor patent thumbnailHeat shield for a combustor
A gas turbine engine includes a fan, a compressor section, a combustor, a fan drive gear system, and a turbine section coupled to drive the fan through the gear system. The combustor includes an annular outer shell and an annular inner shell that define an annular combustion chamber.
United Technologies Corporation


 Layered ice liner patent thumbnailLayered ice liner
A liner assembly for lining of a gas turbine engine includes a honeycomb core having at least two axially adjacent segments, including a forward segment and an aft segment. An impact resistant layer is disposed against and radially inward of the honeycomb forward segment.
United Technologies Corporation


 Turbofan arrangement with blade channel variations patent thumbnailTurbofan arrangement with blade channel variations
A fan section for a gas turbine engine according to an example of the present disclosure includes, among other things, a rotor hub defining an axis, and an array of airfoils circumferentially spaced about the rotor hub. Each of the airfoils include pressure and suction sides between a leading edge and a trailing edge and extending in a radial direction from a 0% span position at an inner flow path location to a 100% span position at an airfoil tip, facing pressure and suction sides of adjacent airfoils defining a channel in a chordwise direction having a width between the facing pressure and suction sides at a given span position of the adjacent airfoils.
United Technologies Corporation


 Cooled fuel injector system for a gas turbine engine patent thumbnailCooled fuel injector system for a gas turbine engine
A cooling system for a fuel injector system of a gas turbine engine has a heat exchanger for cooling a portion of diffuser case air and then routing the cooled diffuser case air through a sleeve that surrounds a fuel injector conduit located in at least the diffuser case plenum for minimizing fuel heat-up rates in the conduit. By minimizing fuel temperatures within the injector conduit, coking accumulation is thereby eliminated or reduced..
United Technologies Corporation


 Nosecap patent thumbnailNosecap
The present disclosure relates generally to a nosecap for a gas turbine engine. The nosecap may be injection molded in an embodiment.
United Technologies Corporation


 Systems and methods for control of combustion dynamics in combustion system patent thumbnailSystems and methods for control of combustion dynamics in combustion system
A system includes a gas turbine engine having a first combustor and a second combustor. Each combustor has at least one fuel nozzle that receives a mixture of liquid fuel and water, via main and pilot fuel supplies, and that injects the mixture and an oxidant into a combustion chamber.
General Electric Company


 Coated cooling passage patent thumbnailCoated cooling passage
A component for a gas turbine engine includes a substrate with a substrate aperture and a coating on the substrate that extends a length of the substrate aperture. A liner assembly for a gas turbine engine includes a hot sheet with a multiple of apertures and a coating on the hot sheet that extends a length of each of the multiple of apertures.
United Technologies Corporation


 Fan drive gear system manifold radial tube filters patent thumbnailFan drive gear system manifold radial tube filters
A lubrication system for gas turbine engine includes a main lubricant passage for providing lubricant from a lubricant supply to a lubricant manifold. The lubricant manifold includes first and second lubricant passages the lubricant manifold is configured to supply lubricant to first and second separate parts of a geared architecture at different first and second lubricant flow conditions.
United Technologies Corporation


 Cooling passages for a mid-turbine frame patent thumbnailCooling passages for a mid-turbine frame
A spoke for a mid-turbine frame on a gas turbine engine includes a cylindrical portion. A flange is attached to the cylindrical portion.
United Technologies Corporation


 Cooling passages for a mid-turbine frame patent thumbnailCooling passages for a mid-turbine frame
A mid-turbine frame for a gas turbine engine includes an inner frame case. A bearing support member is located adjacent the inner frame case.
United Technologies Corporation


Integrated washing system for gas turbine engine


A washing system is described for a gas turbine engine with an axial compressor, comprising: an inlet screen at the air flow inlet of the compressor to protect the compressor from foreign object damage, an arrangement of nozzles and manifolds for spraying the washing liquid, and a washing liquid supply system connected to the arrangement; the inlet screen comprises a supporting structure and a filtering net fixed to the supporting structure; the arrangement of nozzles and manifolds is integrated in the supporting structure of the inlet screen.. .
Nuovo Pignone Srl


Gas turbine engine health determination


A method is provided for determining an updated engine health factor of an aircraft engine. The method includes determining an engine health condition indicative of an engine health during operation of the aircraft engine.
General Electric Company


Variable vane control system


A variable vane control system for controlling the angle of rotation of a circumferential row of variable vanes of a gas turbine engine. The control system includes a mechanical linkage operable to rotate the variable vanes, one or more actuators for operating the linkage and one or more position sensors for detecting the respective actuation positions of the one or more actuators.
Rolls-royce Controls And Data Services Limited


Part load performance improvement using deformable boreplugs


A cooling arrangement for a gas turbine engine includes a discharge channel for airflow from a compressor, a first cooling channel, and at least one aperture providing communication between the flow of air through the discharge channel and the first cooling channel. A restrictor device in the aperture regulates the flow of air between the discharge channel and the first cooling channel.
General Electric Company


Tailored thermal control system for gas turbine engine blade outer air seal array


A clearance control ring for a clearance control system of a gas turbine engine includes a contoured radial outer portion that defines a multiple of fins and a multiple of slots. A clearance control system of a gas turbine engine includes a clearance control ring with a radial inner portion from which a contoured radial outer portion extends.
United Technologies Corporation


Seal assembly in a gas turbine engine


A gas turbine engine seal assembly (160) including: a rigid seal (58) cooperatively configured with a structure (14, 42) of a gas turbine engine to define a leakage path (102, 130) including a flow-controlling section (106, 134); and a compliant seal (162, 164) positioned in the leakage path.. .
Siemens Energy, Inc.


Vane


A vane for an exhaust system duct in a gas turbine engine including a vane plate, a guide plate, and a baffle. The vane plate includes a leading edge, a first leg and a second leg, with the first and second legs respectively extending on opposing sides of the leading edge to form a substantially u-shaped profile.
Rolls-royce Plc


Bladed rotor arrangement and a lock plate for a bladed rotor arrangement


A lock plate of a bladed rotor arrangement is hollow. The bladed rotor arrangement comprises is a bladed turbine rotor of a gas turbine engine.
Rolls-royce Plc


Internally cooled gas turbine engine airfoil


A gas turbine engine airfoil has a hollow airfoil section extending chordwise between a leading edge and a trailing edge. The airfoil has a leading edge cooling passage and a separate serpentine passage for cooling a remaining portion of the airfoil.
Pratt & Whitney Canada Corp.


Gas turbine engine airfoil with leading edge trench and impingement cooling


A gas turbine engine airfoil includes an airfoil structure including an exterior surface that is provided by an exterior wall that has a leading edge. A radially extending interior wall within the airfoil structure separates first and second radial cooling passages.
United Technologies Corporation


Engine component


An engine component for a gas turbine engine includes a film-cooled substrate having a hot surface facing hot combustion gas and a cooling surface facing a cooling fluid flow. The substrate includes one or more film holes that have a metering section defining a metering diameter and a diffusing section that defines a hooded length..
General Electric Company


Blade or vane arrangement for a gas turbine engine


A blade or vane arrangement for a gas turbine engine has an array of aerofoils mounted to respective platforms about an axis and defining a passage through which a working gas flow passes. The arrangement has a datum and the aerofoil has a radial span.
Siemens Aktiengesellschaft


Turbofan arrangement with blade channel variations


A fan section for a gas turbine engine according to an example of the present disclosure includes, among other things, a rotor hub defining an axis, and an array of airfoils circumferentially spaced about the rotor hub. Each of the airfoils include pressure and suction sides between a leading edge and a trailing edge and extending in a radial direction from a 0% span position at an inner flow path location to a 100% span position at an airfoil tip.
United Technologies Corporation


Calcium-magnesium-alumino-silicate resistant thermal barrier coatings


A method for forming a coating system on a component includes depositing a reactive layer with predetermined cmas reaction kinetics on at least a portion of a thermal baffler coating. The method also includes activating the reactive layer with a scanning laser.
United Technologies Corporation


Gas turbine engine wall assembly with offset rail


A liner panel within a gas turbine engine includes a perimeter rail that defines a first height from a cold side. The liner panel also includes an intermediate rail that defines a second height from the cold side, where the second height is less than the first height..
United Technologies Corporation


Variable port assemblies for wave rotors


A wave rotor combustor for use in a gas turbine engine includes an inlet assembly, a rotor drum, and an outlet assembly. The inlet assembly is arranged to direct a flow of gasses into rotor passages formed in the rotor drum.
Rolls-royce North American Technologies, Inc.


Fuel nozzle for a gas turbine engine


A fuel nozzle apparatus for a gas turbine engine includes: an annular outer body extending parallel to a centerline axis, with an exterior surface having a plurality of openings; a main injection ring disposed inside the outer body and including: a circumferential main fuel gallery; and a plurality of main fuel orifices, each main fuel orifice communicating with the main fuel gallery and aligned with one of the openings; a venturi disposed inside the main injection ring; an annular splitter disposed inside the venturi, and including inner and outer walls spaced-apart from each other defining a splitter cavity, and a plurality of discharge holes communicating with the splitter cavity; an array of outer swirl vanes extending between the venturi and the splitter; a pilot fuel injector within the splitter; and an array of inner swirl vanes extending between the splitter and the pilot fuel injector.. .
General Electric Company


Hybrid air blast fuel nozzle


A fuel nozzle apparatus for a gas turbine engine includes: a first pilot fuel injector disposed on a centerline axis of the fuel nozzle which defines a direction of air flow through the fuel nozzle, the first pilot fuel injector being of a pressure atomizing type; an annular second pilot fuel injector at least partially surrounding the first pilot fuel injector, the second pilot fuel injector being of an air blast type and having a fuel outlet disposed axially downstream and radially outboard of the first pilot fuel injector; an annular venturi surrounding the first and second pilot fuel injectors, the venturi including a throat of minimum diameter; an array of inner swirl vanes extending between the first pilot fuel injector and the second pilot fuel injector; and an array of outer swirl vanes extending between the second pilot fuel injector and the venturi.. .
General Electric Company


Swept combustor liner panels for gas turbine engine combustor


A liner panel is provided for use in a combustor of a gas turbine engine. The liner panel includes a first liner panel side edge between a liner panel aft edge and a liner panel forward edge.
United Technologies Corporation


Non symmetrical bi-directional thrust bearing with two active faces


A bearing device supports a shaft of a gas turbine engine. A first support disk is mounted to the bearing housing element.
Siemens Aktiengesellschaft


Compound fillet varying chordwise and method to manufacture


An improved structure and method of manufacturing a structure such as a guide vane for a gas turbine engine includes an improved guide vane having a stress transition section called a fillet that is positioned between an airfoil and a hub. The fillet includes a constant radius section and a compound radius portion that is collectively configured to handle the stress loads of the guide vane as well as to provide aerodynamic efficiencies.
Rolls-royce Corporation


Multi-stage co-rotating variable pitch fan


A fan for a gas turbine engine is disclosed. The fan includes a fan disk and a plurality of fan blades coupled to the fan disk.
Rolls-royce Corporation


Gas bleed arrangement


A gas bleed arrangement for a gas turbine engine. The gas bleed arrangement includes an annular casing defining a main gas flow path.
Rolls-royce Plc


High temperature, low oxidation, amorphous silicon-coated titanium


An exhaust system for a gas turbine engine may comprise a titanium alloy substrate. The titanium alloy may comprise imi 834, titanium 1100, titanium 6242, or beta-21s.
Rohr, Inc.


Cooling passages for a mid-turbine frame


A mid-turbine frame for a gas turbine engine includes an inner frame case. A bearing support member is located adjacent the inner frame case.
United Technologies Corporation


Secondary air system with venturi


A gas turbine engine including a secondary air system with interconnected fluid passages defining at least one flow path between a common source of pressurized air and a common outlet. Some of the fluid passages deliver the pressurized air to components of the gas turbine engine.
Pratt & Whitney Canada Corp.


Integral ceramic matrix composite fastener with polymer rigidization


A method of forming an integral fastener for a ceramic matrix composite component comprises the steps of forming a fiber preform, applying a polymer material to the fiber preform to form a rigid preform structure, machining an opening in the rigid preform structure, forming a fiber fastener, inserting the fiber fastener into the opening, removing the polymer material, and infiltrating a matrix material into the rigid preform structure and fiber fastener to form a ceramic matrix composite component with an integral fastener. A gas turbine engine is also disclosed..
United Technologies Corporation


Turbine vane with heat shield


A gas turbine engine may include a body and a turbine-vane ring coupled to the body. The turbine-vane ring may include a plurality of turbine-vane assemblies..
Rolls-royce Corporation


Integrated gas turbine engine support and sensor


An example integrated support and sensor includes a longitudinal member to support an inner duct relative to an outer duct, and a sensor received within a bore of the longitudinal member and configured to collect a measurement from a flow path bounded by the inner duct.. .
United Technologies Corporation


Gas turbine engine ramped rapid response clearance control system


An active clearance control system of a gas turbine engine includes a multiple of blade outer air seal assemblies and a multiple of rotary ramps. Each of the multiple of rotary ramps is associated with one of the multiple of blade outer air seal assemblies.
United Technologies Corporation


Tolerance resistance coverplates


A gas turbine engine component assembly comprises a first component and a second component circumferentially spaced from the first component relative to an engine center axis. A first baffle is associated with the first component.
United Technologies Corporation


Inner diffuser case for a gas turbine engine


A combustor section of a gas turbine engine has a diffuser case with a structural cone having variable wall thicknesses strategically located for reducing localized stress in the cone.. .
United Technologies Corporation


Chocking and retaining device


A device for chocking and retaining a dovetail root of a blade of a gas turbine engine in a corresponding axially-extending slot in the rim of a disc includes a retention body having a key portion receivable in a keyway formed in the base of the slot, and a mating portion for mating with a complementary mating portion of the root to prevent relative axial movement between the retention body and the root. The retention body has a lowered position in which the key portion is received sufficiently deeply in the keyway to allow the root to be positioned in the slot without interference from the retention body and also has a raised position in which, after the root is positioned in the slot, a part of the key portion is still received in the keyway while the mating portion mates with the complementary mating portion of the root..
Rolls-royce Plc


Chocking and retaining device


A device for chocking and retaining a dovetail root of a blade of a gas turbine engine in a corresponding axially-extending slot in the rim of a disc, the root being mounted in the slot by insertion of a leading end of the root into a proximal end of the slot and then sliding the root towards a distal end of the slot. The device includes a first wedging body having a key portion receivable in a keyway formed at the distal end of the slot.
Rolls-royce Plc


Gas turbine engine turbine blade tip cooling


A gas turbine engine component includes a structure having a surface configured to be exposed to a hot working fluid. The surface includes a recessed pocket that is circumscribed by an overhang.
United Technologies Corporation


Manufacture of a hollow aerofoil


A method of manufacturing a hollow aerofoil component for a gas turbine engine comprises using a capping panel to cover a pocket in a pocketed aerofoil body. The pocketed aerofoil body has a ledge of substantially constant thickness that extends around its perimeter, and to which the capping panel is joined (e.g.
Rolls-royce Plc


Bonded multi-piece gas turbine engine component


An airfoil component includes a first segment that has a first piece of a mount and a first piece of an airfoil. The first segment is formed of a first ceramic-based material.
United Technologies Corporation


Multiple piece engine component


One exemplary embodiment of this disclosure relates to a gas turbine engine, including a component having a first portion formed using one of a casting and a forging process, and a second portion formed using an additive manufacturing process.. .
Unitedtechnologies Corporation


Diagnosis of aircraft gas turbine engines


The present invention relates to a method for the at least partially automated diagnosis of aircraft gas turbine engines having the steps of: 1) detecting (s10) actual parameter values (nh, egt) of an aircraft gas turbine engine for several operational segments (z1, z2, . .
Mtu Aero Engines Ag


Fuel staging in a gas turbine engine


A gas turbine system includes a turbine combustor. The turbine combustor includes one or more first fuel injectors coupled to a head end of the turbine combustor and configured to deliver a first portion of a fuel to a first axial position of a combustion section of the turbine combustor.
Exxonmobil Upstream Research Company


Low net-swirl configurations for gas turbine engine combustors


The present disclosure relates to gas turbine engines, and in particular to combustor swirlers and swirler configurations. In one embodiment, a swirler includes an inner passage for receiving a fuel injector and a plurality of outer passages concentrically arranged around the inner passage.
United Technologies Corporation


Combustor and heat shield configurations for a gas turbine engine


The present disclosure relates to combustor and heat shield configurations for gas turbine engines. A heat shield for a gas turbine engine can include one or more effusion holes downstream of a dilution hole to restore a cooling film applied to the heat shield in the combustor.
United Technologies Corporation


Fan case ice liner for turbofan engine


An ice liner assembly for a fan containment case for a turbofan gas turbine engine is disclosed. The disclosed ice liner assembly includes a plurality of arcuate panels arranged end to end to form a cylindrical liner that is disposed within the fan containment case and aft of the fan and abradable strip liner that circumscribes the fan.
United Technologies Corporation


Airfoil blade


A fan blade of a gas turbine engine is disclosed which is composed of an airfoil having a leading edge and a trailing edge, and a root with a platform and a blade fixing for engaging a fan hub. The fan blade is composed of a core substrate selected from the group consisting of composites and polymers, and an entirety of the airfoil and the root of the fan blade has a nanocrystalline metal outer layer thereon which forms an outer surface fully enveloping the fan blade.
Pratt & Whitney Canada Corp.


Gas turbine engine with airfoil dampening system


A gas turbine engine includes a central wheel and a plurality of blades that extend outwardly from the central wheel. The gas turbine system includes a flutter control system that is adapted to use blade tip timing to determine blade flutter and to direct high pressure air from the compressor to the fan blade row to alter the surface unsteady pressure so that it is out of phase with the blade motion to reduce or eliminate fan blade flutter..
Rolls-royce Corporation


Spherical ball bearing housing


A fuel supply manifold of a gas turbine engine, a method for assembling a fuel supply manifold for a gas turbine engine, and a gas turbine engine are disclosed. The fuel supply manifold for the gas turbine engine man include a plurality of fuel supply tubes, a fitting connecting at least two members of the plurality of fuel supply tubes, a bracket attached to the fitting, a bearing housing having a ball bearing, a bushing attached to a diffuser case of the gas turbine engine, wherein the bushing is surrounded by the ball bearing, and a removable fastener to connect the bearing housing to the bracket..
United Technologies Corporation


Diversion of fan air to provide cooling air for gas turbine engine


A gas turbine engine section includes a plurality of spaced rotor stages, with a static guide vane intermediate the spaced rotor stages. The static guide vane provides swirl into air passing toward a downstream one of the spaced rotor stages, and an outer housing surrounding the spaced rotor stages.
United Technologies Corporation


Gas turbine engine with magnetic gearbox


A magnetic gearbox for use in a gas turbine engine includes an inner rotor assembly, a stator assembly, and an outer rotor assembly. The inner rotor assembly includes a first plurality of permanent magnets and an inner rotor.
Rolls-royce North American Technologies, Inc.


Auxiliary oil pump for gas turbine engine gear reduction


A gas turbine engine has a turbine driving a gear reduction. The gear reduction drives a fan drive shaft assembly to, in turn, drive a fan rotor at a reduced speed relative to the turbine.
United Technologies Corporation


Integrated inner case heat shield


A mid-turbine frame for a gas turbine engine according to an example of the present disclosure includes, among other things, a first frame case, a flange coupled to the first frame case, and a heat shield adjacent to the flange and between adjacent spokes. A method of cooling a portion of a gas turbine engine is also disclosed..
United Technologies Corporation


Vane assembly for a gas turbine engine


A vane assembly for a gas turbine engine is disclosed herein. The vane assembly includes an inner platform, an outer platform, and a ceramic-containing airfoil that extends from the inner platform to the outer platform.
Rolls-royce North American Technologies, Inc.


Compressed chopped fiber composite inlet guide vane


The present disclosure relates generally to the field of guide vanes for gas turbine engines. More specifically, the present disclosure relates to a compressed chopped fiber composite inlet guide vane for a gas turbine engine..
United Technologies Corporation


High-cycle, short range-of-motion linkage gas turbine engine applications


A high-cycle, short range-of-motion linkage apparatus for actuation of a turbofan engine component includes a pivot member having a head portion and a stem, and an actuator moveable between a first and second position. An actuator first end defines a receiving portion into which the stem is removably secured.
Roller Bearing Company Of America, Inc.


Turbine shroud with axially separated pressure compartments


A turbine shroud for a gas turbine engine includes an annular metallic carrier and a blade track. One or more cavities are formed between the carrier and blade track to provide cooling air to the blade track..
Rolls-royce North American Technologies, Inc.


Turbine assembly with load pads


A turbine shroud for a gas turbine engine includes a carrier and a blade track segment. The carrier is formed to include an inwardly opening blade track channel and the blade track segment is positioned in the blade track channel to couple the blade track segment with the carrier..
Rolls-royce North American Technologies, Inc.


Airfoil for a gas turbine engine


A component for a gas turbine engine includes an airfoil that has a first end. A first platform is located at the first end of the airfoil.
United Technologies Corporation


Method and assembly for inspecting engine component


One exemplary embodiment of this disclosure relates to a method of inspecting a component of a gas turbine engine. The method includes performing a through-hole inspection, and determining a location of the plurality of holes from results of the through-hole inspection..
United Technologies Corporation


Enhanced mixing tube elements


The present application provides a fuel nozzle for use with a flow of air and a flow of fuel in a gas turbine engine. The fuel nozzle may include a plenum, a mixing tube element positioned within the plenum, and an enhanced mixing feature positioned within the mixing tube element so as to promote mixing of the flow of air and the flow of fuel.
General Electric Company


Attachment assembly for protective panel


One exemplary embodiment of this disclosure relates to a gas turbine engine. The engine includes a first attachment member including an opening, a second attachment member including a loop at least partially extending through the opening, and a pin between the first attachment member and the loop..
United Technologies Corporation


Method and system to increase gas turbine engine durability


A method of operating a gas turbine engine includes measuring an exhaust gas temperature of the gas turbine engine. A first stage turbine nozzle assembly of the gas turbine engine is adjusted to a first position.
General Electric Company


Enhanced mixing tube elements


The present application provides a fuel nozzle for use with a flow of air and a flow of fuel in a gas turbine engine. The fuel nozzle may include a plenum, a mixing tube element positioned within the plenum, and an enhanced mixing feature positioned within the mixing tube element so as to promote mixing of the flow of air and the flow of fuel.
General Electric Company


Gas turbine filtration system with inlet filter orientation assembly


The present application provides a filtration system for a gas turbine engine. The filtration system may include a holding frame with a positioning element extending therefrom and a filtration unit for mounting within the holding frame.
Bha Altair, Llc


Method and system for a ceramic matrix composite shroud hanger assembly


A shroud and hanger assembly for a gas turbine engine and a method of transferring load from a ceramic matrix composite (cmc) shroud to a cmc shroud hanger assembly are provided. The shroud and hanger assembly includes a shroud hanger assembly formed of a first material having a first coefficient of thermal expansion, the shroud hanger assembly having a forward hanger portion and a separate aftward hanger portion and a shroud formed of a second material having a second coefficient of thermal expansion, the forward and aftward hanger portions configured to couple together to clamp across a forward radially extending wall of the shroud..
General Electric Company


Incident tolerant turbine vane gap flow discouragement


A turbine vane assembly for a gas turbine engine is disclosed and includes an airfoil rotatable about a first axis transverse to an engine longitudinal axis. The airfoil includes an endwall and at least one protrusion disposed on the endwall configured for obstructing flow through a gap between the endwall and a static structure of the gas turbine engine..
United Technologies Corporation


Turboengine water wash system


A system for cleaning gas turbine engines is described. More specifically, methods and apparatuses for cleaning stationary gas turbines and on-wing turbofan engines found on aircraft are disclosed that includes a trailer-mounted, automated low-pressure water delivery system, additive and detergent injection system, nozzle and manifold technology, and active waste water effluent collector system.
Ecoservices, Llc


System for braking a low pressure spool in a gas turbine engine


A braking system for the low pressure spool of a gas turbine engine includes a braking assembly connected to the low pressure spool and reversibly configurable between an actuated state and an unactuated state. The braking assembly in the unactuated state allows rotation of the low pressure spool without interference.
Prati & Whitney Canada Corp,


Turbine abradable air seal system


An air seal system for a rotor blade assembly of a gas turbine engine includes a substrate. An optional ceramic interlayer may be disposed on an optional bond coat deposited on the substrate.
United Technologies Corporation


Incident tolerant turbine vane cooling


A disclosed turbine vane assembly for a gas turbine engine includes an airfoil including a pressure side and a suction side that extends from a leading edge toward a trailing edge. The airfoil is rotatable about an axis transverse to an engine longitudinal axis and includes a forward chamber within the airfoil and in communication with a cooling air source, a forward impingement baffle defining a pre-impingement cavity within the forward chamber.
United Technologies Corporation


Gas turbine engine airfoil


An airfoil includes an airfoil wall including an exterior airfoil surface and at least partially defines an airfoil cavity. A fillet is on the exterior airfoil surface.
United Technologies Corporation


Gas turbine engine airfoil cooling configuration with pressure gradient separators


An airfoil for a gas turbine engine includes an airfoil including spaced apart pressure and suction side walls joined at leading and trailing edges to provide an exterior airfoil surface that extends in a radial direction from a platform to a tip. A cavity is provided between the pressure and suction side walls near the trailing edge.
United Technologies Corporation


Engine component


An engine component for a gas turbine engine includes a film-cooled substrate having a hot surface facing hot combustion gas flow and a cooling surface facing a cooling fluid flow. A film hole extends through the substrate to an outlet on the hot surface.
General Electric Company


Engine component


An engine component for a gas turbine engine includes a film-cooled substrate having a hot surface facing hot combustion gas flow and a cooling surface facing a cooling fluid flow. A film hole extends through the substrate to an outlet on the hot surface.
General Electric Company


Rotor blade vibration damper


A rotor blade vibration damper for a gas turbine engine includes an elongated damper body including a top portion extending longitudinally between a front end and a rear end. The top portion has a width defined between spaced apart lateral sides and is substantially flat between the front and rear ends and between the lateral sides such as to define a longitudinal plane within which the top portion lies.
Pratt & Whitney Canada Corp.


Gas turbine engine cover


A protective cover for an aircraft engine comprises a lower portion mountable to a corresponding lower portion of an opening of the engine, and an upper portion articulated to the lower portion. The upper portion is deployable from a collapsed position to a deployed position in which the upper portion extends upwardly from the lower portion.
Pratt & Whitney Canada Corp.


Forced cooled electrical coil cap and coil bobbin


This invention concerns cooling, specifically for electrical interface devices containing electrical coils (8,108,208,408,508) used in thermally challenging environments such as within gas turbine engines. A force cooled coil cap (2,102,302,402) or bobbin (202,502) has a first surface to be located immediately adjacent or in contact with the coil (8,108,208,408,508) and a chamber (6,106,206,306,406′,506′) through which a coolant (14,114,214,314,414,514) can flow..
Rolls-royce Plc


Combustor aft mount assembly


The present application provides a gas turbine engine. The gas turbine engine may include a compressor discharge casing, a number of combustors configured in an annular array, and a number of aft mounting assemblies.
General Electric Company


Circumferentially and axially staged annular combustor for gas turbine engine


A combustor section for a gas turbine engine includes an outer wall assembly and an inner wall assembly inboard of the outer wall assembly to define an annular combustion chamber therebetween. A forward fuel injection system is in communication with the combustion chamber.
United Technologies Corporation


Combustion staging system


A combustion staging system for fuel injectors of a multi-stage combustor of a gas turbine engine has pilot and mains fuel manifolds distributing fuel to the injectors. A splitting unit splits a fuel flow and sends portions of the flow to pilot and mains fuel manifolds to perform staging control of the combustor.
Rolls-royce Controls And Data Services Limited


Cooling technology for the fuel nozzle


A mixer assembly for a gas turbine engine is provided, including a main mixer, and a pilot mixer having an annular housing. The pilot mixer can further include features to cool portions of the annular housing, such as a radial edge of the annular housing..
United Technologies Corporation


Gas turbine engine quench pattern for gas turbine engine combustor


A combustor for a turbine engine includes an inner liner panel with a multiple of inner dilution passages. The multiple of dilution passages includes a repeating pattern of a first major inner air passage, a minor inner air passage, and a second major inner air passage.
United Technologies Corporation


Panel with cooling holes and methods for fabricating same


A gas turbine engine component and a method for forming a component with a plurality of apertures are provided. An additive metal manufacturing process for fabricating a component with apertures includes receiving data including a three-dimensional representation of the component, generating an electronic file based on the received data, wherein the electronic file includes fabrication instructions for entire portions of the component, and forming initial and additional portions of the component based on the electronic file..
United Technologies Corporation


Combustor panel with multiple attachments


A liner panel for a combustor of a gas turbine engine is provided that includes a first attachment and a second attachment that extends from a cold side of the liner panel. The first attachment is different than the second attachment.
United Technologies Corporation


Igniter position for a combustor of a gas turbine engine


The present disclosure relates combustor configurations for a gas turbine engine. In one embodiment, a combustor includes a combustor shell enclosing a first area of free space, and an igniter for the combustor shell, the igniter including a distal end.
United Technologies Corporation


Squeeze film damper


A bearing for a gas turbine engine may comprise a squeeze film damper. A bearing housing may comprise a roughened surface.
United Technologies Corporation


Fuel flow estimation and control system and method in a gas turbine engine


A system and methods of estimating and controlling fuel flow in a gas turbine engine are disclosed. The system and methods include providing a metering valve and a pressure regulating valve.
United Technologies Corporation


Automatic control of turbine blade temperature during gas turbine engine operation


A method of controlling an airfoil component temperature distribution includes the steps of detecting an airfoil component temperature, comparing the detected airfoil component temperature to a desired airfoil component temperature profile, and controlling a fuel flow in response to the comparing step to maintain the airfoil component temperature within the desired airfoil component temperature profile.. .
United Technologies Corporaton


Self-actuating and dual pivot flapper valve


A bleed valve includes a valve body, a first flapper body movable relative to the valve body between an open position and a closed position, and a second flapper body movable relative to the valve body between an open position and a closed position. A resilient member biases the first and second flapper bodies to the open position to vent bleed air.
Hamilton Sundstrand Corporation


Oil control module


An oil control module for a gas turbine engine is provided comprising a housing on which numerous components of a lubricating system are mounted. The components may include a variable oil reduction valve/shuttle valve, a main oil pressure sensor, a main oil temperature sensor, a main oil filter delta pressure sensor, an oil debris monitor, a lube filter, an active oil damper valve, a cool oil orifice, a knock down orifice and a lube trim orifice.
United Technologies Corporation


Imaging assisted gas turbine anti-icing system


A method includes receiving image data from a camera coupled to an air intake system of a gas turbine engine. The image data corresponds to an air passage of the air intake system.
General Electric Company


Compression molded fiber reinforced fan case ice panel


An ice panel for a fan case of a gas turbine engine is disclosed. The ice panel may comprise a facesheet located on an inner surface of the fan case and it may comprise a chopped prepreg tape that is cured.
United Technologies Corporation


Self-cooled gas bottle


A gas bottle assembly may be provided for a gas turbine engine system. The gas bottle system may include a gas bottle, a regulator cavity, a conductor coil, and an insulating jacket.
Rolls-royce North American Technologies, Inc.


In-line deaerator device for windmill-auxiliary oil system for fan drive gear system


A lubrication system for a fan drive gear system of a turbofan engine includes an auxiliary pump for communicating lubricant to bearings of a gear system. A deaerator is disposed between a lubricant source and the auxiliary pump for separating gases is contained within the lubricant.
United Technologies Corporation


Erosion resistant coating for air seal


A seal is formed of a matrix and includes hard particles. The matrix has a shear strength of greater than or equal to 200 psi and less than or equal to 2000 psi.
United Technologies Corporation


Apparatus and methods for sealing components in gas turbine engines


An apparatus adapted for use in a gas turbine engine includes a first circumferential member and a second circumferential member. The first circumferential member includes an end portion that defines a recess and includes a first seal surface.
Rolls-royce North American Technologies, Inc.


Gas turbine engine mid-turbine frame configuration


A gas turbine engine includes a core flow path that extends axially about an engine axis. A turbine section is arranged in the core flow path.
United Technologies Corporation


Gas turbine engine and turbine configurations


The present disclosure relates to gas turbine engines, and in particular high pressure turbine vane assemblies and combustor/turbine interface configurations. In one embodiment, a vane assembly includes a plurality of turbine vanes, an inner diameter platform, wherein the leading edge of the inner diameter platform is associated with a first axis, and an outer diameter platform, wherein the leading edge of the outer diameter platform is associated with a second axis.
United Technologies Corporation


Segmented turbine shroud with sealing features


A turbine shroud for a gas turbine engine is disclosed in this paper. The turbine shroud includes a ceramic-matrix composite blade track.
Rolls-royce Corporation


Blade wedge attachment lay-up


A blade for a gas turbine engine includes composite layers including neck plies and tooth plies that are flared relative to the neck plies. The neck plies and tooth plies respectively provide a neck and a root.
United Technologies Corporation


Multi-material turbine airfoil


A turbine component comprises a platform and an airfoil extending radially away from the platform and extending from a leading edge to a trailing edge. A leading edge portion defines the leading edge of the airfoil and a trailing edge portion including the trailing edge.
United Technologies Corporation


Gas turbine engine component having platform cooling channel


A component for a gas turbine engine according to an exemplary embodiment of the present disclosure can include a platform having an outer surface and an inner surface. A cover plate can be positioned adjacent to the outer surface of the platform.
United Technologies Corporation


Engine component


An engine component for a gas turbine engine includes a film-cooled substrate having a hot surface facing hot combustion gas and a cooling surface facing a cooling fluid flow. The substrate includes one or more film holes that have a passage with an inlet and an outlet, where the passage includes portions that are angled relative to each other..
General Electric Company


Gas turbine engine airfoil with auxiliary flow channel


A component for a gas turbine engine, according to an exemplary aspect of the present disclosure includes, among other things, an airfoil that includes a pressure side surface and a suction side surface that join together at a leading edge and a trailing edge and a flow channel that extends between the pressure side surface and the suction side surface.. .
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


  • Follow us on Twitter
    twitter icon@FreshPatents

    ###

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


    1.5063

    6058

    2 - 1 - 112