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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
04/07/16
20160097538 
 Fuel nozzle patent thumbnailFuel nozzle
A fuel nozzle for a combustor of a gas turbine engine includes a body defining an axial direction and a radial direction, an air passageway defined axially in the body, and a fuel passageway defined axially in the body radially outwardly from the air passageway. The air passageway has a swirl-inducing relief defined at an exit lip of an outer wall of the air passageway.
Pratt & Whitney Canada Corp.


04/07/16
20160097537 
 Fuel nozzle patent thumbnailFuel nozzle
A fuel nozzle for a combustor of a gas turbine engine includes a body defining an axial direction and a radial direction, an air passageway defined axially in the body, and a fuel passageway defined axially in the body radially outwardly from the air passageway. The fuel passageway has an outer wall including an exit lip at a downstream portion of the outer wall.
Pratt & Whitney Canada Corp.


04/07/16
20160097536 
 Fuel nozzle patent thumbnailFuel nozzle
A fuel nozzle for a combustor of a gas turbine engine includes a body defining an axial direction and a radial direction, an air passageway defined axially in the body, and a fuel passageway defined axially in the body radially outwardly from the air passageway. The fuel passageway has an outer wall including an exit lip at a downstream portion of the outer wall.
Pratt & Whitney Canada Corp.


04/07/16
20160097535 
 Combustor for gas turbine engine patent thumbnailCombustor for gas turbine engine
A combustor comprises an annular combustor chamber formed between the inner and outer liners, the annular combustor chamber having a central axis. Fuel nozzles are in fluid communication with the annular combustor chamber to inject fuel in the annular combustor chamber.
Pratt & Whitney Canada Corp.


04/07/16
20160097346 
 Electric boost actuation system for translating rings patent thumbnailElectric boost actuation system for translating rings
An actuation system for a gas turbine engine oriented about a centerline includes a translating ring, at least one hydraulic actuator, and at least one electric actuator. The translating ring is oriented about the centerline and configured to move axially along the centerline.
Hamilton Sundstrand Corporation


04/07/16
20160097329 
 Corrosion and abrasion resistant coating patent thumbnailCorrosion and abrasion resistant coating
A gearbox adapted for use with a gas turbine engine and a method for making the same are disclosed herein. The gearbox comprising a housing made from a magnesium alloy, and an aluminum oxide coating on the magnesium alloy housing.
Rolls-royce Corporation


04/07/16
20160097328 
 Accessory drive system for a gas turbine engine patent thumbnailAccessory drive system for a gas turbine engine
The described accessory drive system for a gas turbine engine includes a gearbox driving a plurality of accessories including a cabin air compressor to provide cabin air and an engine starter to start the gas turbine engine. An electrical power supply separate from a main electrical power supply of the gas turbine engine is electrically coupled to the accessories.
Pratt & Whitney Canada Corp.


04/07/16
20160097327 
 Synchronized air modulating system patent thumbnailSynchronized air modulating system
A system for modulating air flow in a gas turbine engine is provided. The system may include a seal wall comprising an opening, a seal door configured to slideably engage the seal wall, and an actuator configured to move the seal door over the opening.
United Technologies Corporation


04/07/16
20160097325 
 Cooled component patent thumbnailCooled component
A cooled gas turbine engine component comprises a wall which has a plurality of effusion cooling apertures extending there-through from a first surface to a second surface. The apertures are arranged at an angle to the second surface and each aperture has an inlet in the first surface and an outlet in the second surface.
Rolls-royce Plc


04/07/16
20160097324 
 Filtration system for use in a gas turbine engine assembly and  assembling thereof patent thumbnailFiltration system for use in a gas turbine engine assembly and assembling thereof
A filtration system and methods of assembly and operation are provided. The filtration system includes an array of perforated tubes in flow communication with a flow of intake air.
Bha Altair, Llc


04/07/16
20160097323 

Anti-ice splitter nose


Splitter apparatus for gas turbine engines are disclosed. An example splitter apparatus may include a splitter including an annular outer wall substantially defining a convex leading edge; an annular splitter support positioned radially within the outer and including a forward end disposed substantially against a splitter inner; and an annular first bulkhead spanning between the outer wall and the splitter support.
General Electric Company


04/07/16
20160097304 

Gas turbine engine with low stage count low pressure turbine


A gas turbine engine according to an example of the present disclosure includes, among other things, a fan section, and a low spool including a low pressure compressor section and a low pressure turbine. A high spool includes a high pressure compressor section.
United Technologies Corporation


04/07/16
20160097301 

Aircraft gas turbine engine with shock-absorbing element for fan blade loss


An aircraft gas-turbine engine having a fan mounted on a fan shaft and including several fan blades, where the fan shaft is mounted on an engine structure by means of an upstream fan bearing, when seen in the flow direction, and a downstream bearing, where at least one predetermined breaking point is provided in the area of the fan bearing, characterized in that at least one shock-absorbing element designed as metal fabric damper is arranged at a radial gap to have a parallel effect relative to the predetermined breaking point.. .
Rolls-royce Deutschland Ltd. & Co Kg


04/07/16
20160097295 

Sealing element


A sealing element for positioning radially outwardly of aerofoil blades of a gas turbine engine is provided. A radially inner surface region of the sealing element includes a seal structure having one or more inwardly projecting walls formed by additive layer, powder fed, laser weld deposition.
Rolls-royce Plc


04/07/16
20160097291 

Stator assembly for a gas turbine engine


A stator assembly includes a platform located on a radially inner end of a plurality of vanes that connects a first vane to a second vane. There is a platform groove on a radially inner side of the platform between the first vane and the second vane..
United Technologies Corporation


04/07/16
20160097289 

Slider


A slider for chocking a dovetail root of a blade of a gas turbine engine in a corresponding axially-extending slot in the rim of a disc. The slider, in use, is slidingly inserted in an axially-extending cavity formed in the base of the root and in the disc at the base of the slot to urge the blade radially outwardly and thereby mate flanks of the root to flanks of the slot.
Rolls-royce Plc


04/07/16
20160097287 

Fan


Fan for gas turbine engine includes hub and annular array of fan blades mounted to hub and extending radially outwardly from hub, each fan blade includes blade root. The hub includes plurality of hub grooves having shape complimentary to shape of blade root and each hub groove receives and radially retains one blade root.
Rolls-royce Plc


04/07/16
20160097286 

Internal cooling of engine components


A gas turbine engine component, especially an aerofoil-sectioned nozzle guide vane (ngv), having at least one internal cooling chamber for passage of cooling air, the chamber including leading edge portion and one inlet portion via which cooling air may enter the chamber from feed source, wherein the component includes a partitioning element, e.g. Curved or scoop-shaped partitioning plate or wall, provided in the chamber inlet portion and defining within the inlet portion a sub-chamber adjacent the leading edge portion, and wherein partitioning element is configured so the cooling air velocity in the sub-chamber is less than the cooling air velocity in the remainder of inlet portion.
Rolls-royce Plc


04/07/16
20160097285 

Cooled component


A cooled gas turbine engine component comprises a wall which has a plurality of effusion cooling apertures extending there-through from a first surface to a second surface. Each aperture has an inlet in the first surface and an outlet in the second surface.
Rolls-royce Plc


04/07/16
20160097281 

Gas turbine engine airfoil mistuning


A circumferential airfoil array that provides a total airfoil count for the stage and that includes first and second sets of airfoils with different vibrational frequencies. First and second arcuate regions are arranged opposite one another and third and fourth arcuate regions are arranged opposite one another.
United Technologies Corporation


04/07/16
20160096288 

Tooling production method


A method is provided of producing a tooling to be used for manufacturing a rigid panel formed of polymer matrix composite material. The panel is for attachment to a gas turbine engine and has a curved shape which allows the panel to be wrapped around at least a part of a circumference of the engine.
Rolls-royce Plc


03/31/16
20160090916 

Inner bypass duct


An inner bypass duct of a gas turbine engine includes a plurality of non-structural front panels arranged circumferentially. Each front panel has an outer surface and an inner surface.
Pratt & Whitney Canada Corp.


03/31/16
20160090915 

Inlet door control for startup of gas turbine engine


A gas turbine engine inlet door control system includes an actuator, an engine controller and a door controller. The actuator opens and closes an inlet door of a gas turbine engine.
United Technologies Corporation


03/31/16
20160090909 

Geared gas turbine engine with reduced fan noise


A fan section for a gas turbine engine according to an example of the present disclosure includes, among other things, a fan rotor having fan blades, and a plurality of fan exit guide vanes positioned downstream of the fan rotor. The fan rotor is configured to be driven through a gear reduction.
United Technologies Corporation


03/31/16
20160090870 

Gas turbine engine module adapter to a carrier


An engine mounting arrangement is provided for supporting a gas turbine engine. The mounting arrangement comprises a module adaptor mounted to an overhead or a ground based carrier for rotation about a substantially horizontal axis.
Pratt & Whitney Canada Corp.


03/31/16
20160090868 

Gas turbine engine mounting arrangement


A failsafe pin for providing a backup load path for attaching a gas turbine engine to an aircraft structure is provided with a driving element that allows a torque to be provided to the pin in order to check whether the pin has been engaged, and thus whether a primary load path has failed. The pin is provided with anti-tamper arrangements in order to ensure that the pin itself is not compromised when being tested for engagement..
Rolls-royce Plc


03/31/16
20160090867 

Apparatus for mounting a component in a gas turbine engine


Apparatus for mounting a component in a gas turbine engine, the apparatus comprising: a casing for a gas turbine engine, the casing including a flange; a first connector to connect a component of the gas turbine engine to the casing at a first location adjacent to the flange; and a second connector to connect the component of the gas turbine engine to the casing at a second location adjacent to the flange.. .
Rolls-royce Plc


03/31/16
20160090866 

Shroud segment retainer


A gas turbine, including: axially adjacent first and second components each having a gas path facing surface within an engine casing, inter-component cavity located between first and second components on the gas path outboard side, an axial-restrictor within the inter component cavity for restricting movement of the first or second component relative to at least one other first and second component or engine casing, wherein the axial-restrictor is radially located in the engine casing or other first and second component and includes a radially facing surface; a retaining element, including a body having circumferential length extending around the gas turbine engine and axial length extending between axially adjacent first and second components when in use; an obstructing portion between the radially facing surface of the axial-restrictor and opposing second radial surface of the other first or second component or engine casing to restrict radial movement of in use axial-restrictor.. .
Rolls-royce Plc


03/31/16
20160090862 

Tripod buckle for split fairing of a gas turbine engine


A fairing for a turbine engine strut includes: inner and outer bands; a vane extending between the bands; the fairing is split along a generally transverse plane passing through the bands and the vane, defining nose and tail pieces; wherein the vane is defined by spaced-apart sidewalls extending between a leading edge and a trailing edge, each sidewall split into forward and aft portions by the transverse plane; wherein each sidewall portion carries a radially-inwardly extending post, the posts positioned such that pairs of the posts lie adjacent to each other when the nose piece and tail piece are assembled, wherein each pair of adjacent posts includes at least two non-parallel faces; and a pair of slotted buckles, wherein each slotted buckle surrounds and clamps together a pair of the posts, wherein each pair of adjacent posts contacts a slot of the corresponding buckle in a tripod contact configuration.. .
General Electric Company


03/31/16
20160090859 

Gas turbine engine and a washing a gas turbine engine


There is disclosed a method of washing a gas turbine engine (10) of a type having an anti-icing arrangement comprising a fluid delivery system (33) configured to deliver a flow of hot gas to a region (36) of the engine during operation of the engine. The method comprises the steps of: connecting a supply of cleaning liquid to said fluid delivery system (33); creating a flow of said cleaning liquid through at least part of said fluid delivery system (33) for delivery to said region (36) of the engine; and directing said cleaning liquid towards internal components (25, 27, 30) of the engine.
Rolls-royce Plc


03/31/16
20160090852 

Gas turbine engine


In a gas turbine engine, an annular intermediate-temperature space is formed by a first partition member extending from an inner platform radially inward and a second partition member having a radially inner end portion fixed to the first partition member and a radially outer end portion facing the inner platform, the inner platform being connected to radially inner ends of nozzle guide vanes of a turbine, and the intermediate-temperature space overlapping with the inner platform over substantially its axial entire length. The low-temperature space, supplied with a low-temperature air from a compressor, is formed on a radially inside of the second partition member.
Honda Motor Co., Ltd.


03/31/16
20160090849 

Fan blade with static dissipative coating


The present disclosure relates generally to a fan blade for use in a gas turbine engine, wherein the fan blade includes a metallic fan blade body, including a fan blade body leading edge and body outer surface, extending radially outward from a root, and a static dissipative coating material disposed on the body outer surface.. .
United Technologies Corporation


03/31/16
20160090846 

Gas turbine engine airfoil trailing edge suction side cooling


An airfoil for a gas turbine engine includes an outer airfoil wall that provides an exterior surface and multiple radially extending cooling passages. The exterior surface provides pressure and suctions sides joined by leading and trailing edges.
United Technologies Corporation


03/31/16
20160090845 

Dual wall components for gas turbine engines


A dual wall component for use in a gas turbine engine and a method for making the same are disclosed herein. The dual wall component includes an inner support wall and an outer shield wall that extends around the inner support wall to act as a heat shield for the inner support wall..
Rolls-royce Corporation


03/31/16
20160090844 

Gas turbine engine airfoil cooling passage configuration


A component for a gas turbine engine includes an exterior surface that provides pressure and suction sides. A cooling passage in the component includes a serpentine passageway that has first and second passes respectively configured to provide fluid flow in opposite directions from one another.
United Technologies Corporation


03/31/16
20160090841 

Gas turbine engine blade slot heat shield


A gas turbine engine rotor assembly includes a rotor disk with a slot. A rotor blade has a root supported within the slot.
United Technologies Corporation


03/31/16
20160090840 

Carriers for turbine components


A carrier segment for forming a carrier section for one or more gas turbine engine components, the carrier segment including a carrier wall extending between front and rear carrier ends and having a circumferential profile, the carrier segment being configured for defining radially inwardly thereof a chamber for receiving cooling air from an outboard feed source via the front end, wherein the circumferential profile of the carrier wall is undulating, e.g. With a simple waveform configuration or a more complex arrangement of interleaved series of oppositely oriented part-conical surface formations..
Rolls-royce Plc


03/31/16
20160089722 

Method of manufacturing gas turbine engine component from a molybdenum-rich alloy


A method for manufacturing a gas turbine engine component from a molybdenum-rich alloy. The method includes the steps of providing a molybdenum powder of at least 50% molybdenum by weight, extruding the molybdenum powder to provide a first shape, forming the first shape to a second shape and forging the second shape to provide a third shape..
United Technologies Corporation


03/24/16
20160084736 

Systems and methods for attaching a probe to a casing of a gas turbine engine


A system for attaching a probe to a casing of a gas turbine engine is disclosed. The system may include a probe receptacle attachable to the casing.
General Electric Company


03/24/16
20160084503 

Fuel nozzle


A fuel nozzle for a combustor of a gas turbine engine includes a body defining an axial direction and a radial direction, a primary air passageway centrally defined axially in the body, and a plurality of concentrically-arranged nozzle tip projections disposed at a downstream portion of the body. Each of the plurality of nozzle tip projections has a radially inwardly facing fuel filming surface communicating with respective fuel passages.
Pratt & Whitney Canada Corp.


03/24/16
20160084265 

Gas turbine engine with partial inlet vane


A turbofan engine including an axially extending inlet wall surrounding an inlet flow path. A radial distance between the inlet wall and the inner wall adjacent the fan defines a downstream height of the inlet flow path.
Pratt & Whitney Canada Corp.


03/24/16
20160084260 

Gas turbine engine


A compressor disc for a compressor of a gas turbine engine includes a circumferentially extending groove for receiving blade roots of a plurality of compressor blades. The circumferentially extending groove includes a planar surface offset into the groove..
Rolls-royce Plc


03/24/16
20160084169 

Method of operating a multi-stage flamesheet combustor


The present invention discloses a novel way of controlling a gas turbine engine using detected temperatures and detected turbine rotor speed. An operating system provides a series of operating modes for a gas turbine combustor through which fuel is staged to gradually increase engine power, yet harmful emissions, such as carbon monoxide, are kept within acceptable levels..

03/24/16
20160084168 

Chemistry based methods of manufacture for maxmet composite powders


A method of manufacturing a gas turbine engine air seal comprising forming at least one max phase particle. The method includes coating the at least one max phase particle with a metallic shell.
United Technologies Corporation


03/24/16
20160084167 

Self-modulated cooling on turbine components


Systems and methods are disclosed herein for passively managing cooling air in a gas turbine engine. A cooling air supply line may supply cooling air to a component in the gas turbine engine.
United Technologies Corporation


03/24/16
20160084164 

Plate for metering flow


A cooling device for a gas turbine engine component comprises a gas turbine engine component having an upstream channel and a downstream channel that define a cooling flow path. A meter feature includes at least one hole to meter flow from the upstream channel to the downstream channel, and has an upstream side and a downstream side.
United Technologies Corporation


03/24/16
20160084162 

Gas turbine engine inlet


An inlet for a turbofan engine, including an inlet wall surrounding an inlet flow path. The inlet wall extends axially from an upstream end to a downstream end adjacent the fan.
Pratt & Whitney Cananda Corp.


03/24/16
20160084161 

Inlet air filtration system with self-cleaning hydrophobic filter bag


The present application provides a pulse filtration system for use with a compressor of a gas turbine engine. The pulse filtration system may include a pulse filter, a compressed air system in communication with the pulse filter, and a hydrophobic filter bag surrounding the pulse filter in whole or in part..
General Electric Company


03/24/16
20160084113 

Nacelle mounted latching system


A nacelle for a gas turbine engine includes a bifurcation, an outer diameter cowl and a first latch system. The outer diameter cowl extends from the bifurcation and the first latch system is mounted on the outer diameter cowl.
United Technologies Corporation


03/24/16
20160084111 

Methods and systems for preventing lube oil leakage in gas turbines


A sump pressurization system comprising an off-board source of pressurized air is provided to supplement pressurized air to a bearing sump arrangement when the operating conditions of the gas turbine engine are such that the on-board pressurized air source, e.g. The compressor of the gas generator, are such that the air pressure generated thereby is insufficient to pressurize a sump pressurization cavity.
Nuovo Pignone Srl


03/24/16
20160084106 

Anti-icing core inlet stator assembly for a gas turbine engine


A gas turbine engine is defined wherein the inlet guide vanes leading into a core engine flow path are sized and positioned such that flow paths positioned circumferentially intermediate the vane are sufficiently large that a hydraulic diameter of greater than or equal to about 1.5 is achieved. This will likely reduce the detrimental effect of icing..
United Technologies Corporation


03/24/16
20160084105 

Fan drive gear system


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


03/24/16
20160084104 

Fan drive gear system


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


03/24/16
20160084101 

Gas turbine engine blade outer air seal assembly


A gas turbine engine includes a rotating stage of blades. A circumferential array of blade outer air seal segments are arranged radially outward of the blades.

03/24/16
20160084095 

Diaphragm assembly with a preswirler


A preswirler for a gas turbine engine diaphragm assembly is disclosed herein. In embodiments, the preswirler includes an outer ring and an inner ring.
Solar Turbines Incorporated


03/24/16
20160084091 

High pressure turbine blade cooling hole distribution


A turbine blade for a gas turbine engine with an airfoil portion defined by a perimeter wall surrounding at least one enclosure, the perimeter wall having a plurality of cooling holes defined therethrough and providing fluid communication between the at least one enclosure and a gaspath of the gas turbine engine. The plurality of cooling holes includes at least one set of holes selected from the group consisting of a first set, a second set, a third set, a fourth set, a fifth set and a sixth set, wherein the first, second, third, fourth, fifth and sixth sets of holes respectively include the holes numbered a1 to a8, b1 to b10, c1 to c9, d1 to d6, e1 to e7 and f1 to f6 each located such that a central axis thereof extends through the respective point 1 and point 2 having a nominal location in accordance with the x, y, z cartesian coordinate values set forth in table 3..
Pratt & Whitney Canada Corp.


03/24/16
20160084090 

Method and assembly for reducing secondary heat in a gas turbine engine


A turbine section includes a rotor assembly which includes an internal cooling passage. A segmented seal is adjacent the rotor assembly and includes a fluid passage that is in fluid communication with the internal cooling passage..
United Technologies Corporation


03/24/16
20160084088 

Stress relieving feature in gas turbine blade platform


A gas turbine engine blade (10) having: an airfoil (12) having a leading edge (14), a trailing edge (16), a pressure side (22), and a suction side (24); an inner platform (30) associated with a base (18) of the airfoil, wherein the inner platform includes a platform aft face (34) spanning between an platform pressure side face (36) and a platform suction side face (38); and a trailing edge undercut (70) across the aft face. The trailing edge undercut tapers to zero penetration before reaching the platform suction side face.
Siemens Energy, Inc.


03/24/16
20160084086 

Gas turbine engine


A fan containment system for fitment around an array of radially extending fan blades mounted on a hub in an axial gas turbine engine. The fan containment system comprises a fan case having an annular casing element for encircling an array of fan blades and a hook projecting in a generally radially inward direction from the annular casing element.
Rolls-royce Plc


03/24/16
20160083852 

Method of machining a gas turbine engine component


A method of machining a nickel containing alloy gas turbine engine component (34) comprises applying a material removal gas comprising gaseous carbon monoxide at a nickel carbonyl gas forming temperature such as 50 to 60° c. To a surface of the component to form a nickel carbonyl gas, and thereby remove a surface layer from at least part of the component..
Rolls-royce Plc


03/24/16
20160082510 

Methods for producing gas turbine engine rotors and other powdered metal articles having shaped internal cavities


Embodiments of a methods for producing gas turbine engine rotors and other powdered metal articles having shaped internal cavities are provided. In one embodiment, the method includes consolidating a powdered metal body utilizing a hot isostatic pressing process to produce a rotor preform in which elongated sacrificial tubes are embedded.
Honeywell International Inc.


03/17/16
20160076483 

Gas turbine nozzle


The present application provides a nozzle for a gas turbine engine. The nozzle may include a band, a seal slot positioned within the band, an airfoil extending from the band, a cavity within the airfoil, and an embossment positioned about the band and the cavity..
Generl Electric Company


03/17/16
20160076461 

Dual fuel gas turbine thrust and power control


An aircraft, controller, and method for simultaneously using a liquid fuel and a gaseous fuel. The use of natural gas and other similar fuels in gas turbines engines can enable an aircraft to operate less expensively.
The Boeing Company


03/17/16
20160076460 

Nacelle and compressor inlet arrangements


A gas turbine engine includes a nacelle defining a centerline axis and an annular splitter radially inward from the nacelle. A spinner is radially inward of the nacelle forward of a compressor section.
United Technologies Corporation


03/17/16
20160076459 

Geared fan with inner counter rotating compressor


A gas turbine engine has a fan section including a fan hub supporting a plurality of fan blades for rotation relative to a fan case. A shaft is rotatable relative to the fan case about an engine center axis.
United Technologies Corporation


03/17/16
20160076452 

Gas turbine engine mechanical-electrical hybrid fuel delivery system


A gas turbine engine fuel delivery system includes a mechanically-driven fuel pump, an electrically-driven fuel pump, and an engine control. The mechanically-driven fuel pump is adapted to receive a drive torque from a gas turbine engine draw fuel into its fuel inlet and discharge the fuel from its fuel outlet.
Honeywell International Inc.


03/17/16
20160076451 

Film hole with in-wall accumulator


A gas turbine engine component is described. The component includes a component wall having an internal surface that is adjacent a flow of coolant and an external surface that is adjacent a flow of gas.
United Technologies Corporation


03/17/16
20160076447 

Composite material inlet plenum and gas turbine engine system comprising said plenum


An air inlet plenum for a gas turbine engine is described. The air inlet plenum comprises a hollow body having an air inlet aperture and an air outlet aperture arranged and configured for connection to the gas turbine engine.
Nuovo Pignone Srl


03/17/16
20160076446 

Aircraft hybrid engine


A propulsion engine comprising at least a first propulsion unit including a first fan encased by a geared ring and a gas turbine engine driving a first shaft connected to the first fan, at least a second propulsion unit including a second fan encased by a geared ring connected to a second shaft operatively coupled to an electric machine and at least an electric storage device connected to the electric machine. The geared rings are configured to transmit torque between the fans so that they can rotate in conjunction (directly or through an intermediate gear) when they are driven by at least one of said first and second shafts.
Airbus Operations S.l.


03/17/16
20160076445 

Geared turbofan engine with high compressor exit temperature


A gas turbine engine comprises a fan includes a plurality of fan blades rotatable about an axis. A compressor section includes at least a first compressor section and a second compressor section, wherein components of the second compressor section are configured to operate at an average exit temperature that is between about 1000° f.
United Technologies Corporation


03/17/16
20160076444 

Multi-fan engine with an enhanced power transmission


A multi-fan engine including a gas turbine engine, a casing and fans encased by geared rings, which connect with the geared rings of an adjacent fan(s) such that the rotation of one fan rotates the other fans. Intermediate gears may prove the connection between adjacent geared rings, wherein the intermediate gears are retracted by linear actuators to disengage the intermediate gears from the geared rings and thereby disengage the fans from each other.
Airbus Operations S.l.


03/17/16
20160076402 

Gas turbine engine


A gas turbine engine comprising a casing, a bonding patch (10, 22) bonded to a surface of the casing, and a liner attached to the bonding patch. The bonding patch (10, 22) comprising a bonding region (12) configured to receive an adhesive for bonding the patch (10, 22) to a surface.
Rolls-royce Plc


03/17/16
20160076392 

Endwall contouring for airfoil rows with varying airfoil geometries


An airfoil array for a gas turbine engine comprises a plurality of airfoils spaced circumferentially apart from each other about an engine center axis. Each airfoil is associated with a platform.
United Technologies Corporation


03/17/16
20160076384 

Gas turbine engine component having engineered vascular structure


A component according to an exemplary aspect of the present disclosure includes, among other things, a wall and a hollow vascular engineered lattice structure formed inside of the wall. The hollow vascular engineered lattice structure has an inlet hole and an outlet hole that communicate fluid into and out of the hollow vascular structure.
United Technologies Corporation


03/17/16
20160076382 

Component core with shaped edges


A gas turbine engine component according to an exemplary aspect of the present disclosure includes, among other things, at least one cooling passage. The at least one cooling passage includes a first wall and a second wall bounding the at least one cooling passage, the first wall having a plurality of first surface features and the second wall having a plurality of second surface features.
United Technologies Corporation


03/17/16
20160076381 

Secondary flowpath system for a gas turbine engine


A rotor assembly of a gas turbine engine may be spoked and includes a rotor and a shell. The rotor has a rotor disk and a plurality of blades each having a platform attached to the rotor disk and with a first channel defined radially between the platforms and the rotor disk.
United Technologies Corporation


03/17/16
20160076380 

Incidence-tolerant, high-turning fan exit stator


A gas turbine engine component is described. The gas turbine engine component includes an inner diameter edge, an outer diameter edge, a trailing edge and a leading edge.
United Technologies Corporation


03/10/16
20160072210 

Electrical harness connector


An electrical assembly is disclosed in which two flexible printed circuits are electrically joined. This allows greater lengths of flexible printed circuits to be provided, for example for gas turbine engine harnesses.
Rolls-royce Plc


03/10/16
20160069777 

Process for testing a compressor or a combustor of a gas turbine engine using a large compressed air storage reservoir


A process for testing a combustor or a compressor of a gas turbine engine, where a large volume of compressed air is stored in a large reservoir of at least 10,000 m3 such as an underground storage cavern, compressed air from the storage reservoir is passed through an air turbine to drive a compressor to produce high pressure and temperature compressed air, and where the compressed air can be discharged into a combustor and burned with a fuel for testing of the combustor under simulated conditions of a real gas turbine engine.. .

03/10/16
20160069567 

Single-walled combustor for a gas turbine engine and manufacture


A single-walled combustor includes a multi-layered wall having a first face defining a cooling plenum and an opposite second face. A thermal barrier coating of the wall may be secured to the second face and defines at least in-part a combustion chamber.
United Technologies Corporation


03/10/16
20160069274 

Engine-induced aircraft cabin resonance reduction system and method


A system method of reducing engine induced aircraft cabin resonance in an aircraft includes sensing a parameter representative of current aircraft flight conditions, and sensing a parameter representative of current engine operating conditions of at least one of a first turbofan gas turbine engines or a second turbofan gas turbine engine. In a control system, the parameter representative of current aircraft flight conditions and the parameter representative of current engine operating conditions are processed to supply a variable inlet guide vane (vigv) offset value.
Honeywell International Inc.


03/10/16
20160069269 

Vibration damping hydrostatic seal of gas turbine engine


A hydrostatic seal and vibration damping apparatus for a gas turbine engine adapted to reduce vibrations during cold engine start-ups is disclosed. In one disclosed configuration, the vibration damping apparatus is comprised of a temperature sensitive control ring having a relatively high coefficient of thermal expansion adapted to expand quickly at relatively low temperatures to protect the hydrostatic seal during such gas turbine engine startups.
United Technologies Corporation


03/10/16
20160069268 

Engine-induced aircraft cabin resonance reduction system and method


A system and method of reducing engine induced aircraft cabin resonance includes sensing the core engine speed of a first turbofan gas turbine engine, and sensing the core engine speed of a second turbofan gas turbine engine. In a control system, the core engine speed of the first turbofan gas turbine engine and the core engine speed of the second turbofan gas turbine engine are processed to determine a core engine speed difference between the first and second turbofan gas turbine engines.
Honeywell International Inc.


03/10/16
20160069267 

Reduced windage fastener assembly for a gas turbine engine


A fastener assembly for a gas turbine engine, and method of assembly, includes a first body having a first surface and a recess communicating through the first surface. The recess may be defined by a bottom surface and a side face spanning between the first and bottom surfaces.
United Technologies Corporation


03/10/16
20160069264 

Gas turbine engine with turbine cooling and combustor air preheating


A gas turbine engine, especially an industrial gas turbine engine for electrical power production, where a second compressor is used to supply a second compressed air at a higher pressure to a stage of stator vanes in the turbine section of the engine for cooling of the stage of stator vanes, and where the heated compressed air used to cool the stator vanes is then discharged into the combustor to be burned with a fuel and produce a hot gas stream that is passed through the turbine. An intercooler can be used with the second compressor to lower the temperature of the second compressed air used for cooling the stator vanes..

03/10/16
20160069260 

Compressor system


In a gas turbine engine, the booster compressor is driven by both the low pressure or fan shaft and high pressure shaft through a differential gear arrangement. The rotational speed of the booster compressor is intermediate between the speed of the fan and the speed of the high pressure compressor..
Derwent Aviation Consulting Ltd


03/10/16
20160069259 

Turbine minidisk bumper for gas turbine engine


An assembly for a gas turbine engine includes a minidisk that includes an axial extension extending from a disc. The axial extension includes an inner diameter surface and a recess arranged radially opposite the inner diameter surface.
United Technologies Corporation


03/10/16
20160069215 

Offtakes for gas turbine engine secondary gas flows


A turbo machinery case includes a shell body extending circumferentially about a longitudinal axis and defining therein a main gas path. The shell body defines a first offtake opening and a second offtake opening that extend in a circumferential direction about the longitudinal axis.
Pratt & Whitney


03/10/16
20160069214 

Fan case assemblies


A fan case for use in a gas turbine engine of an aircraft includes an outer shroud and a liner extending along the outer shroud. The fan case provides a protective band that blocks fan blades from being thrown out of the fan case in case of a blade-off event in which a fan blade is released during operation of the gas turbine engine..
Rolls-royce North American Technologies, Inc.


03/10/16
20160069210 

Windback heat shield


A heat shield includes a first end configured to connect to an inner engine case at an inner connecting point, and a second end configured to connect to an outer engine case at an outer connecting point. The heat shield also includes a bulge extending in an aft direction from a radially upstream portion.
United Technologies Corporation


03/10/16
20160069204 

Geared annular airflow actuation system for variable cycle gas turbine engines


An annular airflow control system for a gas turbine engine includes a sync ring rotatable to move the multiple of contra-rotatable variable vanes through a respective multiple of geared interfaces to throttle an airflow through the multiple of contra-rotatable variable vanes.. .
United Technologies Corporation


03/10/16
20160069203 

Integrally bladed rotor


An integrally bladed rotor for a gas turbine engine according to an exemplary aspect of the present disclosure includes, among other things, a radially inner hoop extending circumferentially about an axis, a plurality of circumferentially spaced, axially extending slots, separated by respective blade supports, and a seal system that includes seal fingers extending axially through the slots.. .
United Technologies Corporation


03/10/16
20160069201 

Attachment faces for clamped turbine stator of a gas turbine engine


An airfoil fairing shell for a gas turbine engine includes an airfoil section between an outer vane endwall and an inner vane endwall, at least one of the outer vane endwall and the inner vane endwall including a radial attachment face, a suction side tangential attachment face, a pressure side tangential attachment face, and an axial attachment face.. .
United Technologies Corporation


03/10/16
20160069200 

Turbine vane with platform pad


A vane has an airfoil extending between a radially outer platform and a radially inner platform. At least one of the platforms has nominally radially thinner portions, and a pad defining a radially thicker portion.
United Technologies Corporation


03/10/16
20160069199 

Stator vane platform with flanges


Disclosed is a gas turbine engine that includes a plurality of stator vanes. Each of the stator vanes includes an airfoil section and a platform provided at an end of the airfoil section.
United Technologies Corporation


03/10/16
20160069198 

Casting optimized to improve suction side cooling shaped hole performance


A gas turbine engine component includes a pressure side, a suction side, a leading edge, a trailing edge, an outer surface and an inner surface. The inner surface is positioned within the outer surface and defines a core.
United Technologies Corporation


03/10/16
20160069197 

Turbine vane with variable trailing edge inner radius


A turbine vane has an airfoil extending between an inner platform and an outer platform. The airfoil is hollow.
United Technologies Corporation


03/10/16
20160069196 

Repaired or remanufactured blade platform for a gas turbine engine


A article of manufacture, the article having a nominal profile substantially in accordance with cartesian coordinate values of x, y and z set forth in table 1, and wherein x and y are distances in inches which, when connected, define profile sections at each distance z in inches to form a portion of a rotor blade.. .
Pw Power Systems, Inc.


03/10/16
20160069194 

Turbine blades and methods of forming turbine blades having lifted rib turbulator structures


The present disclosure provides various embodiments of cooling circuits, turbine blades with cooling circuits, and methods of forming such turbine blades, having raised rib turbulator structures, which may be used in gas turbine engines. In one exemplary embodiment, a cooling circuit for directing a flow of fluid is disclosed, the cooling circuit includes a cooling circuit wall and a plurality of raised turbulator ribs, each turbulator rib of the plurality of raised turbulator ribs being spaced apart from the cooling circuit wall to allow the fluid to flow between the cooling circuit wall and the plurality of turbulator ribs..
Honeywell International Inc.


03/10/16
20160069193 

Coolant flow redirection component


A gas turbine engine includes a compressor section, a combustor fluidly connected to the compressor section, and a turbine section fluidly connected to the combustor and mechanically connected to the compressor section via a shaft. Multiple rotors are disposed in one of the compressor section and the turbine section.
United Technologies Corporation


03/10/16
20160069191 

Gas turbine engine airfoil cooling passage turbulator pedestal


A gas turbine engine component includes a structure that provides a cooling passage. The structure has a turbulator with a pedestal joining opposing first and second surfaces.
United Technologies Corporation


03/10/16
20160069190 

Beveled coverplate


A gas turbine engine includes a platform that has a gas path side, a non-gas path side, a first mate face, and a second mate face. The second mate face has a beveled edge sloping towards the first mate face.
United Technologies Corporation


03/10/16
20160069189 

Splayed tip features for gas turbine engine airfoil


A component for a gas turbine engine includes a trailing edge tip corner that at least partially defines a trailing edge cavity and a multiple of corner features within the trailing edge cavity, the multiple of corner features splayed along the trailing edge tip corner.. .
United Technologies Corporation


03/10/16
20160069188 

Gas turbine engine airfoil structure


An airfoil structure includes an airfoil that has a leading edge and a platform that includes a first side that is attached to the airfoil and a second side opposite the airfoil. The platform includes a relief cut on the second side of the platform axially aligned with the leading edge..
United Technologies Corporation


03/10/16
20160069187 

Gas turbine engine airfoil


An airfoil of a turbine engine according to an example of the present disclosure includes, among other things, pressure and suction sides extending in a radial direction from a 0% span position to a 100% span position. The airfoil has a relationship between a gap/chord ratio and span position that defines a curve with a gap/chord ratio having a portion with a negative slope..
United Technologies Corporation


03/10/16
20160069184 

Method of blade tip repair


A method for repairing a blade for use in a gas turbine engine, the method comprising removing a distal tip of an airfoil included in the blade to remove damaged portions of the airfoil and to expose previously internal cooling passages. The method further comprising positioning a tip cap in the place of the removed distal tip to cover the internal cooling passages, and welding the tip cap to the airfoil by applying a directed energy beam onto the tip cap and the airfoil at a joint between the tip cap and the airfoil..
Rolls-royce 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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