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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
07/21/16
20160209040 
 Gas turbine combustor and gas turbine engine equipped with same patent thumbnailGas turbine combustor and gas turbine engine equipped with same
The liquid fuel-using gas turbine combustor prevents the generation of combustion oscillation. The gas turbine combustor is provided with a pilot burner disposed on the central position of the combustion casing, main burners disposed so as to surround the pilot burner.
Mitsubishi Hitachi Power Systems, Ltd.


07/21/16
20160209038 
 Dual fuel nozzle with swirling axial gas injection for a gas turbine engine patent thumbnailDual fuel nozzle with swirling axial gas injection for a gas turbine engine
A fuel nozzle for a combustor of a gas turbine engine includes an outer air swirler along an axis, the outer air swirler defines an outer annular air passage. An inner air swirler along the axis defines an annular fuel gas passage around the axis between the outer air swirler and the inner air swirler, the annular fuel gas passage terminates with a multiple of skewed slots..
United Technologies Corporation


07/21/16
20160209037 
 Dual fuel nozzle with liquid filming atomization for a gas turbine engine patent thumbnailDual fuel nozzle with liquid filming atomization for a gas turbine engine
A fuel nozzle for a combustor of a gas turbine engine includes an outer air swirler along an axis, said outer air swirler defines an outer annular air passage between an outer wall and an inner wall, the outer wall defines a convergent-divergent nozzle. An inner air swirler along the axis to define an annular liquid passage therebetween, the annular liquid passage terminates upstream of the convergent-divergent nozzle and an annular fuel gas passage around the axis between the outer air swirler and the inner air swirler..
United Technologies Corporation


07/21/16
20160209036 
 Swirler, fuel and air assembly and combustor patent thumbnailSwirler, fuel and air assembly and combustor
An air swirler, a fuel and air admission assembly, and a staged combustor are disclosed. The staged combustor may be equipped with the fuel and air admission assemblies incorporating the air swirlers for use in gas turbine engines, such as for example gas turbine engines powering aircraft having supersonic cruise capability..
United Technologies Corporation


07/21/16
20160208926 
 Splined honeycomb seals patent thumbnailSplined honeycomb seals
A seal assembly includes an annular carrier defining a radially inward face, and an opposed radially outward face defining a plurality of spline slots. The spline slots are configured and adapted to receive corresponding spline tabs to center the carrier in a surrounding structure.
United Technologies Corporation


07/21/16
20160208818 
 Compressor flowpath patent thumbnailCompressor flowpath
A compressor section for a gas turbine engine according to an example of the present disclosure includes, among other things, a low pressure compressor including a plurality of rotor blades arranged about an axis, a high pressure compressor, and a core flowpath passing through the low pressure compressor. The core flowpath at the low pressure compressor defines an inner diameter and an outer diameter relative to the axis.
United Technologies Corporation


07/21/16
20160208737 
 System for actuating an exhaust cowl patent thumbnailSystem for actuating an exhaust cowl
In various embodiments, a cowl actuation system may comprise a cowl, an actuator, a bell crank, and a guide arm. The cowl may be configured to modulate at least a portion of the exhaust flow of a gas turbine engine.
United Technologies Corporation


07/21/16
20160208717 
 System and  load power management in a turboshaft gas turbine engine patent thumbnailSystem and load power management in a turboshaft gas turbine engine
A control system for a gas turbine engine including a power turbine is disclosed. The control system may also include an outer loop control module to determine a torque request.
United Technologies Corporation


07/21/16
20160208716 
 Method for detecting a fault, fault detection system and gas turbine engine patent thumbnailMethod for detecting a fault, fault detection system and gas turbine engine
A method for detecting a fault in a gas supply system for a gas turbine engine. The method comprises: measuring a pressure difference between two gas supplying ducts of the gas supply system; comparing the measured pressure difference to a threshold level; and determining a fault based on the measured pressure difference and the comparison..
Rolls-royce Plc.


07/21/16
20160208714 
 Gas turbine engine and blocker door assembly patent thumbnailGas turbine engine and blocker door assembly
A blocker door assembly which may be for a cooling system that may be applied to a gas turbine engine includes a plurality of blocker doors circumferentially spaced about an engine axis. Each blocker door is constructed and arranged to move in a circumferential direction to, at least in-part, control air flow through a passage in an adjacent fixture.
United Technologies Corporation


07/21/16
20160208713 

Gas turbine engine with high speed and temperature spool cooling system


A gas turbine engine includes a turbine section that includes a turbine rotor arranged in a plenum. A compressor section includes a compressor rotor assembly that has spaced apart inner and outer portions that provide an axially extending cooling channel.
United Technologies Corporation


07/21/16
20160208712 

Gas turbine engine control for rotor bore heating


A gas turbine engine comprises a compressor rotor including blades and a disk, with a bore defined radially inwardly of the disk, and a combustor. A tap directs the products of combustion first to a valve and then into the bore of the disk.
United Technologies Corporation


07/21/16
20160208705 

Bore-cooled film dispensing pedestals


A cooling circuit for a gas turbine engine comprises a first wall having a first surface facing a first cavity and a second surface facing away from the first cavity. A second wall is spaced outwardly of the second surface of the first wall to provide at least one second cavity.
United Technologies Corporation


07/21/16
20160208704 

Angled combustor liner cooling holes through transverse structure within a gas turbine engine combustor


A wall assembly for use in a combustor of a gas turbine engine includes a transverse structure with at least one effusion passage that extends at an angle a therethrough. The effusion passage includes an inlet in an outer periphery of a wall.
United Technologies Corporation


07/21/16
20160208703 

Overcooled air cooling system with annular mixing passage


A cooling system is provided. The cooling system may comprise a heat exchanger and a first conduit fluidly coupled to an outlet of the heat exchanger.
United Technologies Corporation


07/21/16
20160208701 

Cooling passages for a mid-turbine frame


A gas turbine engine includes a mid-turbine frame that includes an inner frame case. At least one spoke is connected to the inner frame case.
United Technologies Corporation


07/21/16
20160208698 

Gas turbine engine thermal management system


The present disclosure provides systems and methods related to thermal management systems for gas turbine engines. For example, a thermal management system comprises a thermally neutral heat transfer fluid circuit, a first heat exchanger disposed on the fluid circuit, and a second heat exchanger disposed on the fluid circuit..
United Technologies Corporation


07/21/16
20160208697 

Mid-turbine frame buffer system


A mid-turbine frame buffer system for a gas turbine engine includes a mid-turbine frame that supports a shaft by a bearing. An air compartment and a bearing compartment are arranged radially inward of the mid-turbine frame.
United Technologies Corporation


07/21/16
20160208695 

Gas turbine engine inlet


In or for an aircraft turbine engine, the invention comprises a fitting comprising at least one blade, said blade being elongate and being adapted to be located such that it lies across the mouth of the engine inlet in use, such that, in use, the blade shears the air flowing towards it, such that the force of at least a portion of the air flowing into the turbine is reduced, the invention also comprises a housing for a gas turbine engine, comprising a fitting of the invention and wherein the fitting is mounted at the, in use, front of the housing, the front of the housing having an inside periphery, and wherein the fitting is mounted within the inside periphery of the housing,. .

07/21/16
20160208692 

Gas turbine engine with a multi-spool driven fan


A gas turbine engine includes low and high spools constructed and arranged to rotate about an engine axis. The low spool drives at least one leading stage of a fan section and the high spool drives an aft stage of the fan section.
United Technologies Corporation


07/21/16
20160208690 

Gas turbine engine split torque fan drive gear system


A gas turbine engine includes a turbine section configured to rotate about an engine axis relative to an engine static structure. A fan section is configured to rotate about the engine axis relative to the engine static structure.
United Technologies Corporation


07/21/16
20160208689 

Modifying a gas turbine engine to use a high pressure compressor as a low pressure compressor


A method comprises the steps of modifying an existing engine which includes a high pressure compressor driven by a high pressure turbine and a low pressure turbine to drive a low pressure compressor. The modifying step includes utilizing the high pressure compressor as a low pressure compressor in a modified gas turbine engine, and designing and incorporating a new high pressure compressor downstream of the low pressure compressor section in the modified engine, such that a portion of the design of the existing engine is utilized in the modified engine.
United Technologies Corporation


07/21/16
20160208688 

Inflow radial turbine with reduced bore stress concentration


A gas turbine engine is provided comprising an impeller configured to rotate about an axis. A combustor is in fluid communication with the impeller.
United Technologies Corporation


07/21/16
20160208655 

Tie rod for a mid-turbine frame


A mid-turbine frame for a gas turbine engine includes an inner frame case that includes a bolt opening and at least one spoke for connecting an outer frame case to the inner frame case that includes an inlet passage that extends in a radial direction. A central bolt extends through the bolt opening for securing at least one spoke to the inner frame case..
United Technologies Corporation


07/21/16
20160208648 

Cooling passages for a mid-turbine frame


A mid-turbine frame for a gas turbine engine includes at least one spoke for connecting an outer frame case to an inner frame case. At least one spoke includes an inlet passage and at least two branches that extend transverse to the inlet passage..
United Technologies Corporation


07/21/16
20160208647 

Cooling passages for a mid-turbine frame


A mid-turbine frame for a gas turbine engine includes an inner frame case that includes a fluid passage. A swirler tube is in fluid communication with the fluid passage and is configured to direct cooling airflow in a radial inward and downstream direction..
United Technologies Corporation


07/21/16
20160208646 

Cooling passages for a mid-turbine frame


A mid-turbine frame for a gas turbine engine includes an outer frame case and an inner frame case. At least one spoke connects the outer frame case to the inner frame case.
United Technologies Corporation


07/21/16
20160208644 

Cooling passages for a mid-turbine frame


A mid-turbine frame for a gas turbine engine includes an outer frame case and an inner frame case. At least one spoke connects the outer frame case to the inner frame case.
United Technologies Corporation


07/21/16
20160208640 

Gas turbine engine


A fan containment system has a fan case having an annular casing element for encircling an array of fan blades and a hook projecting generally radially inwardly from the annular casing element. An annular fan track liner is positioned substantially coaxial to the annular casing element, and positioned such that a forward end of the fan track liner is axially spaced from the hook so that there is a gap between the hook and the fan track liner.
Rolls-royce Plc


07/21/16
20160208639 

System and controlling a gas turbine engine


A control system for a gas turbine engine including a power turbine is disclosed. The control system may include a control module to receive engine operating goals and an estimated current engine state, wherein the estimated current engine state is produced by a model-based estimation module using a bandwidth signal produced by an adaptation logic module.
United Technologies Corporation


07/21/16
20160208637 

Variable vane bushing


A variable vane assembly includes a variable vane, a trunnion arranged on one end of the variable vane, an inner bushing configured to receive the trunnion in a press fit relationship, and an outer bushing configured to rotatably receive the inner bushing. A retention feature is configured to retain the trunnion axially with respect to the outer bushing.
United Technologies Corporation


07/21/16
20160208635 

Turbine shroud with tubular runner-locating inserts


A turbine shroud for a gas turbine engine includes a carrier and a blade track. The blade track includes an annular runner and a plurality of inserts that extend radially outward away from the annular runner.
Rolls-royce North American Technologies, Inc.


07/21/16
20160208634 

Repair or remanufacture of blade outer air seals for a gas turbine engine


A method of remanufacturing a turbine component is provided. This method includes removing a donor portion from a damaged component; removing a to-be-replaced portion from a serviceable component generally equivalent to the donor portion leaving a remainder; and welding the donor portion to the remainder.
United Technologies Corporation


07/21/16
20160208629 

Anti-rotation vane


A vane for a gas turbine engine includes a radially inner platform and a radially outer platform. At least two airfoils extend between the radially inner platform and the radially outer platform.
United Technologies Corporation


07/21/16
20160208626 

Integrally bladed rotor with pressure side thickness on blade trailing edge


An integrally bladed rotor comprises a hub centered about an axis and having a plurality of blades extending radially outwardly of the axis across a span. Each of the blades includes an airfoil extending between a leading edge and a trailing edge, and having a pressure side and a suction side.
United Technologies Corporation


07/21/16
20160208621 

Gas turbine engine airfoil with wishbone baffle cooling scheme


A gas turbine engine component includes a structure including spaced apart first and second exterior walls that extend in a first direction to an endwall. The first and second exterior walls are joined at the endwall to provide a cooling cavity.
United Technologies Corporation


07/21/16
20160208620 

Gas turbine engine airfoil turbulator for airfoil creep resistance


A gas turbine engine component includes spaced apart walls that extend in a load direction and provide a cooling passage. The cooling passage provides a tortuous passage having a generally straight portion that extends in the load direction and a bend transverse to the load direction.
United Technologies Corporation


07/21/16
20160208614 

Gas turbine engine truncated airfoil fillet


An integrally bladed rotor includes a rim integral with a web that extends radially inward to a bore. The rim provides an end wall from which integral blades extend radially outward to a tip.
United Technologies Corporation


07/21/16
20160208613 

Gas turbine engine integrally bladed rotor


A rotor disk includes a web that extends from a rim radially inward to a bore. A spacer is integral with and extending generally axially from the rim.
United Technologies Corporation


07/21/16
20160207632 

Upper bifi frame for a gas turbine engine and methods therefor


An upper bifi frame for preventing air leakage in a gas turbine engine including an engine casing and a fan case is provided. The upper bifi frame includes a forward fairing having a forward fairing midsection extending between the engine casing and the fan case.
United Technologies Corporation


07/21/16
20160207630 

Aircraft


An aircraft (2) comprises at least first and second gas turbine engines (10a, 10b) arranged in a line extending generally normally to an aircraft longitudinal axis (a), each engine (10a, 10b) comprising at least one compressor or turbine rotor disc (32-42) defining a respective rotational plane (d32-d42). The rotational plane (d32-d42) of at least one of the rotors (32-42) of at least one of the engines (10a, 10b) is angled relative to the aircraft longitudinal line (a) such that a burst disc plane of the respective engine (10a, 10b) is nonintersecting with another engine (10a, 10b)..
Rolls-royce Plc


07/14/16
20160201917 

Cooled fuel injector system for a gas turbine engine


A fuel injector is provided for a gas turbine engine. The fuel injector includes a fuel conduit and a cooling fluid circuit through a strut.
United Technologies Corporation


07/14/16
20160201915 

Swirler mount interface for gas turbine engine combustor


A swirler for a combustor of a gas turbine engine includes a swirler outer body with a male snap component and/or female snap component of a snap-fit interface defined around a swirler central longitudinal axis. A bulkhead assembly for a combustor of a gas turbine engine includes a swirler mounted to a bulkhead support shell through a snap-fit interface..
United Technologies Corporation


07/14/16
20160201914 

Sealed combustor liner panel for a gas turbine engine


A liner panel for a combustor of a gas turbine engine includes a rail which at least partially defines an impingement cavity. The rail includes a notch which faces toward the impingement cavity.
United Technologies Corporation


07/14/16
20160201910 

Protective panel and frame therefor


One exemplary embodiment of this disclosure relates to a gas turbine engine including a plate, a frame attached to the plate, and a panel. The panel is supported by the frame..
United Technologies Corporation


07/14/16
20160201909 

Gas turbine engine wall assembly with support shell contour regions


A wall assembly for a combustor of a gas turbine engine is provided. The wall assembly includes a support shell with a contoured region to define at least one convergent passage between the support shell and a multiple of liner panels.
United Technologies Corporation


07/14/16
20160201908 

Vena contracta swirling dilution passages for gas turbine engine combustor


A liner panel for use in a combustor of a gas turbine engine includes a nozzle includes an inner periphery along an axis. The inner periphery includes a flow guide around the axis.
United Technologies Corporation


07/14/16
20160201805 

Wide differential pressure range air riding carbon seal


An exemplary carbon seal assembly generally may include a stator fixable to a static component, such as a mechanical housing of a gas turbine engine, and a rotor fixable to a rotating component, such as a shaft of the gas turbine engine, where the rotating component is rotatable relative to the static component. The carbon seal assembly may also include a carbon ring and a spring attached thereto positioned between the stator and the rotor, where the spring may be configured to move the carbon ring fore and aft between the stator and the rotor.
Rolls-royce Corporation


07/14/16
20160201688 

Gas turbine engine diffuser cooling and mixing arrangement


A diffuser for a gas turbine engine includes a diffuser housing that has a circumferential array of hollow struts that provide a cavity. The diffuser housing includes inlet and outlet apertures that are in fluid communication with the cavity.
United Technologies Corporation


07/14/16
20160201684 

Compressor area splits for geared turbofan


A gas turbine engine has an upstream compressor having an upstream entrance area leading into a first vane upstream of the upstream compressor. A downstream compressor has an exit area at a leading edge of an exit vane for the downstream compressor.
United Technologies Corporation


07/14/16
20160201682 

Split axial-centrifugal compressor


A gas turbine engine including a compressor, a turbine, and a transmission is disclosed. The turbine is coupled to the compressor to drive rotation of multiple stages of the compressor.
Rolls-royce Corporation


07/14/16
20160201608 

Systems and methods controlling fan pressure ratios


A system for varying the fan pressure ratio of a gas turbine engine is provided. The system may comprise a stator having a variable area component.
United Technologies Corporation


07/14/16
20160201607 

Efficient, low pressure ratio propulsor for gas turbine engines


A gas turbine engine includes a core flow passage, a bypass flow passage, and a propulsor arranged at an inlet of the bypass flow passage and the core flow passage. The propulsor includes a row of propulsor blades.
United Technologies Corporation


07/14/16
20160201606 

Low weight large fan gas turbine engine


A gas turbine engine according to an example of the present disclosure includes, among other things, a fan configured to deliver airflow to a bypass passage, and a core engine configured to rotate the fan. The core engine includes a high pressure turbine section configured to drive a high pressure compressor section, and a low pressure turbine section configured to drive the fan and a low pressure compressor section.
United Technologies Corporation


07/14/16
20160201600 

Thrust reverser sliding door assembly


A gas turbine engine assembly has a pylon with a first side and a second side. A first rail is mounted to the first side and a second rail is mounted to the second side.
United Tecnologies Corporation


07/14/16
20160201568 

Geared gas turbine engine with reduced oil tank size


A gas turbine engine comprises a fan drive turbine for driving a gear reduction, which drives a fan rotor. A lubrication system supplies oil to the gear reduction.

07/14/16
20160201567 

System and diversified gearbox


A gas turbine engine assembly comprising, a gearbox including a first housing that includes a first auxiliary gear drive on a first portion thereof, a second housing that includes a second auxiliary gear drive on a second portion thereof, and a third housing that includes a third auxiliary gear drive on a third portion thereof, the housings being interconnected so that the first portion of the first housing, the second portion of the second housing and the third portion of the third housing form a substantially triangular polyhedron shape, with the second portion of the second housing disposed between the first portion of the first housing and the third portion of the third housing. The first auxiliary gear drive, the second auxiliary gear drive and the third auxiliary gear drive project outwardly in mutually divergent directions..
United Technologies Corporation


07/14/16
20160201566 

Large displacement high temperature seal


A seal assembly is provided for a gas turbine engine. This seal assembly includes a tadpole seal with a bulb and a tail, where the tail is directed toward a backwall.
United Technologies Corporation


07/14/16
20160201562 

Fuel manifold for a gas turbine engine


A fuel supply manifold for a gas turbine engine includes a first manifold segment includes a first multiple of double-barrel fittings in communication with a primary fuel circuit and a secondary fuel circuit. A second manifold segment includes a second multiple of double-barrel fittings in communication with the primary fuel circuit and the secondary fuel circuit.
Untied Technologies Corportion


07/14/16
20160201557 

Gas turbine engine thermal management system


A thermal management system for a gas turbine engine according to an exemplary aspect of the present disclosure includes, among other things, a heat exchanger and a valve that controls an amount of a first fluid that is communicated through the heat exchanger. A first sensor senses a first characteristic of a second fluid that is communicated through the heat exchanger to exchange heat with the first fluid and a second sensor senses a second characteristic of the second fluid.
United Technologies Corporation


07/14/16
20160201516 

Gas turbine engine mid-turbine frame tie rod arrangement


A gas turbine engine mid-turbine frame includes an annular case which includes a first face. A tie rod includes a flange that is secured to the annular case.
United Technologies Corporation


07/14/16
20160201515 

Connection for a fairing in a mid-turbine frame of a gas turbine engine


A fairing assembly for a gas turbine engine includes an inner fairing platform; an outer fairing platform located radially outward of the inner fairing platform; a plurality of vanes radially outward from the inner fairing platform between the inner fairing platform and outer fairing platform; a mount located on a radially outer side of the outer fairing platform, the mount attached to the outer fairing platform on the radially outer side; and a link that includes an elongated member with a first end and an opposite second end, the first end configured to fit within the mount and define a pivot axis of the link with respect to the mount.. .
United Technologies Corporation


07/14/16
20160201512 

Gas turbine engine mid-turbine frame tie rod arrangement


A gas turbine engine mid-turbine frame includes inner and outer cases that are arranged about an engine axis. A radial plane is arranged normal to the engine axis.
United Technologies Corporation


07/14/16
20160201511 

Shielding pockets for case holes


A case is provided for a gas turbine engine. The case includes a wall defining a through-hole.
Mitsubishi Heavy Industries America, Inc.


07/14/16
20160201508 

Gas turbine engine and foil bearing system


A gas turbine engine including a compressor, a turbine and a static structure is disclosed herein. The gas turbine engine further includes a foil bearing system operative to transmit rotor loads from at least one of the compressor and the turbine to the static structure.
Rolls-royce Corporation


07/14/16
20160201507 

Engine component for a gas turbine engine


An engine component for a gas turbine engine includes a film-cooled wall having a hot surface facing hot combustion gas and a cooling surface facing a cooling fluid flow. A film hole in the wall has an inlet, an outlet, and a passage connecting the inlet and outlet that defines an inflection point..
General Electric Company


07/14/16
20160201492 

Tangential on-board injection vanes


A tangential on-board injection (tobi) system for gas turbine engines includes a first endwall and a second endwall radially spaced apart from the first endwall. A plurality of airfoils extend radially from the first endwall to the second endwall.
United Technologies Corporation


07/14/16
20160201484 

Turbine wheel with clamped blade attachment


A turbine wheel for use in a gas turbine engine having a plurality of blades attached to a rotor disk. Each blade is formed from a composite comprising ceramic matrix material.
Rolls-royce North American Technologies, Inc.


07/14/16
20160201483 

Turbine wheel with clamped blade attachment


A turbine wheel for use in a gas turbine engine having a plurality of blades attached to a rotor disk. Each blade is formed from a composite comprising ceramic matrix material.
Rolls-royce North American Technologies, Inc.


07/14/16
20160201478 

Braided blades and vanes having dovetail roots


A gas turbine engine composite article having a composite article airfoil extending outwardly to an article root to an article airfoil tip. Within the article airfoil is a core including a core airfoil attached to a core root including a core dovetail.
General Electric Company


07/14/16
20160201477 

Gas turbine engine airfoil crossover and pedestal rib cooling arrangement


A gas turbine engine component includes spaced apart walls that provide a cooling passage that extends in a first direction. A cross-over rib joins the walls and extends along the first direction.
United Technologies Corporation


07/14/16
20160201475 

Cooling for gas turbine engine components


A gas turbine engine component includes a body with a wall surrounding an interior cavity. The wall has opposed interior and exterior surfaces.
United Technologies Corporation


07/14/16
20160201474 

Gas turbine engine component with film cooling hole feature


A gas turbine engine component includes a wall that provides an exterior surface and an interior flow path surface. A film cooling hole extends through the wall and is configured to fluidly connect the interior flow path surface to the exterior surface.
United Technologies Corporation


07/14/16
20160201466 

Coating pocket stress reduction for rotor disk of a gas turbine engine


A rotor is provided for a gas turbine engine. The rotor includes a rim that extends transverse to the web.
United Technologies Corporation


07/07/16
20160195411 

Encapsulated soft-lead capacitance probe for a gas turbine engine


A capacitance probe monitors the distance between a blade tip and a fan, compressor or turbine case. The capacitance probe may be attached to a liner, and may travel with the liner as it radially expands due to thermal changes.
United Technologies Corporation


07/07/16
20160195275 

Hybrid diffuser case for a gas turbine engine combustor


A hybrid diffuser case for a gas turbine engine includes an outer diffuser case wall that extends downstream from an annular outer pre-diffuser case shroud. An inner diffuser case wall extends downstream from an annular inner pre-diffuser case shroud.
United Technologies Corporation


07/07/16
20160195274 

Airblast fuel injector


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


07/07/16
20160195272 

Methods for coating gas turbine engine components


The present disclosure relates to methods for coating gas turbine engine components, such as combustor panels. In one embodiment, a method includes forming a first layer to a substrate to form a bond coat, and forming a second layer over the first layer.
United Technologies Corporation


07/07/16
20160195038 

Convergent divergent exit nozzle for a gas turbine engine


A nacelle for a gas turbine engine includes a ring shaped body defining a center axis and having a radially outward surface and a radially inward surface. An aft portion of the radially inward surface includes an axially extending convergent-divergent exit nozzle.
United Technologies Corporation


07/07/16
20160195025 

Gas turbine flameout detection


A method includes receiving an indication of exhaust gas temperature (egt) for a gas turbine engine, and determining, by at least one processor, based on the received indication of the egt, a representation of a second derivative with respect to time of the egt. The method further includes comparing the representation of the second derivative of the egt to a threshold value, and determining, based on the comparing, an engine flameout condition of the gas turbine engine.
United Technologies Corporation


07/07/16
20160195022 

Geared turbofan architecture for regional jet aircraft


A gas turbine engine according to an example of the present disclosure includes, among other things, a fan situated at an inlet of a bypass passage, and a core engine configured to drive the fan. The core engine includes a low pressure compressor section driven by a low pressure turbine section, and a high pressure compressor section driven by a high pressure turbine section.
United Technologies Corporation


07/07/16
20160195021 

Low noise compressor and turbine for geared turbofan engine


A gas turbine engine according to an example of the present disclosure includes, among other things, a fan, a turbine section having a fan drive turbine rotor, and a compressor rotor. A gear reduction is configured to effect a reduction in a speed of the fan relative to an input speed from the fan drive turbine rotor.
United Technologies Corporation


07/07/16
20160195019 

Turbine section support for a gas turbine engine


A gas turbine engine includes a compressor portion, a combustor fluidly connected to the compressor portion via a primary flowpath, and a turbine portion fluidly connected to the combustor via the primary flowpath. The turbine section includes a first turbine portion and a second turbine portion.
United Technologies Corporation


07/07/16
20160195018 

Turbine last stage rotor blade with forced driven cooling air


A turbine of a gas turbine engine with a rotor and a stator forming a rim cavity, where the rotor includes a turbine rotor blade with a cooling air channel opening into the rim cavity, and a centrifugal impeller rotatably connected to the rotor in which the centrifugal impeller discharges pressurized cooling air into the rim cavity to improve the rim cavity seal and to supply pressurized cooling air to the rotor blade cooling air channel.. .

07/07/16
20160195017 

Recuperated gas turbine engine


A gas turbine engine that includes a compressor, a turbine, a heat exchanger, and a combustor. The compressor is mounted on a rotating shaft with at least one rotor with an inlet and an outlet, and at least one diffuser downstream from each rotor.
The Government Of The United States Of America, As Represented By The Secretary Of The Navy


07/07/16
20160195015 

Gas turbine engine nosecone attachment structure


A single piece nosecone with support ring and fastening method providing smooth aerodynamic flow into a gas turbine engine is disclosed. The support ring may include a rim having a curved upper surface, the curvature following a curve of the nosecone and having a hole extending radially therethrough to connect to the nosecone.
United Technologies Corporation


07/07/16
20160195011 

Split gear system for a gas turbine engine


A gas turbine engine includes a fan section, a compressor section aft of the fan section, a combustor fluidly connected to the compressor section, and a turbine section fluidly connected to the combustor. The turbine section includes at least a first turbine and a second turbine.
United Technologies Corporation


07/07/16
20160195010 

Vaneless counterrotating turbine


A gas turbine engine includes a compressor section, a combustor, and a turbine section. The turbine section includes a first turbine portion and a second turbine portion, with the first and second turbine portions being counter-rotating turbine portions.
United Technologies Corporation


07/07/16
20160194981 

Dual anti surge and anti rotation feature on first vane support


A gas turbine engine includes a vane and a combustor housing that are supported relative to an engine static structure. A retaining assembly clamps the combustor housing and the vane to one another in an axial direction.
United Technologies Corporation


07/07/16
20160194980 

Gas turbine engine component providing prioritized cooling


A component for a gas turbine engine according to an exemplary aspect of the present disclosure includes, among other things, a platform having a non-gas path surface and a gas path surface, a cover plate positioned relative to the non-gas path surface and a cooling passage that extends between the cover plate and the non-gas path surface. At least one cooling entrance is formed through the cover plate and configured to bias the flow of a cooling fluid toward a prioritized location of the non-gas path surface..
United Technologies Corporation


07/07/16
20160194976 

Borescope plug for gas turbine engine


A borescope plug includes a threaded section that extends from a head section along an axis, the threaded section including a central passage along said axis. A spindle is located within the central passage.
United Technologies Corporation


07/07/16
20160194974 

Boas with radial load feature


This disclosure relates to a gas turbine engine including a blade outer air seal (boas) having at least one attachment hook adjacent one of a leading edge and a trailing edge thereof. The boas further includes at least one radial standoff axially aligned with the at least one attachment hook..
United Technologies Corporation


07/07/16
20160194973 

Fan platform with leading edge tab


A platform for a gas turbine engine has an outer surface and an inner surface. The inner surface is provided with a mount location for mounting the platform to a rotor.
United Technologies Corporation


07/07/16
20160194969 

Turbine vane with platform rib


A vane for use in a gas turbine engine has an airfoil extending between a leading edge and a trailing edge, a radially outer platform and a radially inner platform. A rib is on one of the radially inner and radially outer platforms, and is adjacent the trailing edge of the airfoil.
United Technologies Corporation


07/07/16
20160194967 

Cooling having tailored flow resistance


The present disclosure includes gas turbine engine components which are cooled internally through the inclusion of lattice structures. Such structures may comprise a network of branches and nodes.
United Technologies Corporation


07/07/16
20160194964 

Three dimensional airfoil micro-core cooling chamber


A component for use in a gas turbine engine comprises a body and a micro-core cooling circuit embedded within the body. The micro-core circuit has a variation in either the thickness or contoured surface, away from a generally planar shape to a non-planar shape..
United Technologies Corporation


06/30/16
20160187227 

Methods of analysing apparatus


Engine health monitoring is used to assess the health of an engine, such as a gas turbine engine. Blades mounted on a shaft produce a modal response when excited.

06/30/16
20160186999 

Retention system for gas turbine engine assemblies


A combustor of a gas turbine engine and a turbine shroud for a turbine of a gas turbine engine are disclosed. The combustor is configured to ignite a mixture of compressed air and fuel in a combustion chamber included therein.

06/30/16
20160186998 

Contoured dilution passages for gas turbine engine combustor


A wall assembly for use in a combustor of a gas turbine engine includes a support shell with a first inner periphery along an axis and a liner panel with a second inner periphery along the axis. The second inner periphery is smaller than the first inner periphery.

06/30/16
20160186994 

Boss for combustor panel


A combustor for use in a gas turbine engine has a combustor outer shell. A panel has an inner face which will face hot products of combustion, and a boss surrounding a feature, with the boss extending to an outer end.

06/30/16
20160186690 

Non-axisymmetric fan flow path


A gas turbine engine propulsion system and method of assembling such is disclosed. The gas turbine engine propulsion system comprises a gas turbine engine that includes a fan flow path.

06/30/16
20160186667 

Gas turbine engine with two-spool fan and variable vane turbine


A method of operating a gas turbine engine includes modulating a variable high pressure turbine inlet guide vane of a high pressure spool to performance match a first stage fan section of a low pressure spool and an intermediate stage fan section of an intermediate spool to maintain a generally constant engine inlet flow while varying engine thrust.. .

06/30/16
20160186666 

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


A turbine section for a gas turbine engine includes a first rotor assembly with a first rotor assembly bleed air source and an aft cavity that is in fluid communication with the first rotor assembly bleed air source. A second rotor assembly includes a forward cavity.

06/30/16
20160186665 

Gas turbine sealing


A turbine in a gas turbine engine that includes a stator blade and a rotor blade having a seal formed in a trench cavity. The trench cavity may include an axial gap defined between opposing inboard faces of the stator blade and rotor blade.

06/30/16
20160186664 

Gas turbine sealing


A gas turbine engine having a turbine that includes a stator blade and a rotor blade having a seal formed in a trench cavity defined therebetween. The seal may include: a stator overhang extending from the stator blade toward the rotor blade so to include an overhang topside, and, opposite the overhang topside, an overhang underside; a rotor outboard face extending radially inboard from a platform edge, the rotor outboard face opposing at least a portion of the overhang face across the axial gap of the trench cavity; an axial projection extending from the rotor outboard face toward the stator blade so to axially overlap with the stator overhang; and an interior cooling channel extending through the stator overhang to a port formed through the overhang underside.

06/30/16
20160186663 

Pilot nozzle in gas turbine combustor


A fuel nozzle for a gas turbine engine that includes: an elongated centerbody; an elongated peripheral wall formed about the centerbody so to define a primary flow annulus therebetween; a primary fuel supply and a primary air supply in the primary flow annulus; and a pilot nozzle. The pilot nozzle may be formed in the centerbody and include: axially elongated mixing tubes defined within a centerbody wall; a fuel port positioned on the mixing tubes for connecting each to a secondary fuel supply; and a secondary air supply configured so to fluidly communicate with an inlet of each of the mixing tubes.

06/30/16
20160186662 

Pilot nozzle in gas turbine combustor


A fuel nozzle for a gas turbine engine that includes: an elongated centerbody; an elongated peripheral wall formed about the centerbody so to define a primary flow annulus therebetween; a primary fuel supply and a primary air supply in fluid communication with an upstream end of the primary flow annulus; and a pilot nozzle. The pilot nozzle may be formed in the centerbody and include: axially elongated mixing tubes defined within a centerbody wall; a fuel port positioned on the mixing tubes for connecting each to a secondary fuel supply; and a secondary air supply configured so to fluidly communicate with an inlet of each of the mixing tubes.

06/30/16
20160186661 

Cooled cooling air taken directly from combustor dome


A gas turbine engine includes a compressor, a turbine, and a combustor. The combustor includes a fuel injector and a vaporizer within the combustor positioned to receive liquid fuel from the fuel injector to vaporize the liquid fuel therein.

06/30/16
20160186626 

Engine component and methods for an 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 multi-faceted diffusing section configured to improve the adhesion of a coating on the substrate..

06/30/16
20160186613 

Ducted cowl support for a gas turbine engine


A ducted cowl support includes an annular structure configured to be mounted to an annular turbine engine frame and including one or more bypass ducts integrally formed therein.. .

06/30/16
20160186612 

Casing ring assembly with flowpath conduction cut


A casing assembly for a gas turbine engine having a centerline axis, the casing apparatus includes: a metallic inner ring defining an annular flowpath surface; a metallic outer ring positioned in axial alignment with and radially outward of the inner ring; and a conduction cut structure disposed between the inner and outer rings.. .

06/30/16
20160186607 

Bearing system for gas turbine engine


A bearing system is provided for a gas turbine engine. This bearing system includes a spring defined about an axis of rotation.

06/30/16
20160186606 

Gas turbine engine duct assembly


A duct assembly according to an exemplary aspect of the present disclosure includes, among other things, a casing body that extends between a flange and a wall, a first discrete cooling passage formed in the casing body and a second discrete cooling passage circumferentially spaced from the first discrete cooling passage. At least one of the first discrete cooling passage and the second discrete cooling passage includes an axial portion and a tangential portion configured to turn a cooling fluid communicated in each of the first and second discrete cooling passages..

06/30/16
20160186604 

Flexibly damped mounting assemblies for power gear box transmissions in geared aircraft engine architectures


An assembly for flexibly damping a power gear box for a gas turbine engine, the assembly includes a flexible mount connected to the power gear box at a first end of the flexible mount; a member connected to the flexible mount at the first end of the flexible mount and a second end of the flexible mount, wherein the first end of the flexible mount includes an outer rim connected to the member and an inner rim connected to the power gear box and a set of circumferentially segmented squeeze film damper lands configured to receive a damping fluid is provided between the inner rim and the outer rim.. .

06/30/16
20160186601 

Dirt extraction a gas turbine engine


A centrifugal compressor apparatus includes: an impeller mounted for rotation about a central longitudinal axis, the impeller including an impeller disk carrying an array of impeller blades around its periphery; a diffuser disposed downstream of the impeller, configured to diffuse and turn airflow discharged from the impeller; an extraction scoop disposed in fluid communication with the impeller and with a plenum disposed adjacent the impeller, and a dirt collector disposed in fluid communication with the plenum and configured to trap dirt therein.. .

06/30/16
20160186600 

Variable area turbine arrangement for a gas turbine engine


A variable area turbine arrangement according to an exemplary aspect of the present disclosure includes, among other things, a first turbine section having at least a first variable vane row and a second turbine section downstream from the first turbine section and having at least a second variable vane row. A transition duct is disposed between the first turbine section and the second turbine section..

06/30/16
20160186598 

Gas turbine engine with accessory gear box


A nacelle for incorporation into a gas turbine engine has an inner wall defining a bypass duct, and an outer wall, at least one drive shaft extending through said inner wall, said at least one drive shaft to be connected to a gas turbine engine receiving the nacelle, said at least one drive shaft being connected to drive at least two accessory gear boxes, with said at least two accessory gear boxes being received between said inner and outer walls of said nacelle. A gas turbine engine is also disclosed..

06/30/16
20160186596 

Clearance control assembly


A clearance control assembly for a gas turbine engine according to an exemplary aspect of the present disclosure includes, among other things, a clearance control ring to position a blade outer air seal assembly radially relative to a blade tip. The clearance control ring is compression fit to the blade outer air seal assembly..

06/30/16
20160186595 

Compressor abradable material seal with tailored wear ratio and desirable erosion resistance


What is described is a wear resistant seal system that is adapted for resisting wear of a rotating part in a gas turbine engine as it rotates against a stationary part in the engine. The system includes an axially rotable member including an abrasive tip having a first tensile strength.

06/30/16
20160186590 

Cover plate assembly for a gas turbine engine


A cover plate assembly according to an exemplary aspect of the present disclosure includes, among other things, a first cover plate and a second cover plate in contact with a portion of the first cover plate to at least axially retain the first cover plate.. .

06/30/16
20160186589 

Gas turbine engine aft seal plate geometry


A gas turbine engine includes an engine static structure. A fairing is supported relative to the engine static structure and configured to provide a flow path surface of a flow path extending in an axial direction.

06/30/16
20160186587 

Baffle for gas turbine engine vane


A vane structure includes an airfoil section with a first inner airfoil wall surface and a second inner airfoil wall surface. A baffle is mounted within the airfoil section between the first inner airfoil wall surface and the second inner airfoil wall surface..

06/30/16
20160186583 

Gas turbine engine cmc airfoil assembly


A gas turbine engine airfoil assembly includes an airfoil and an attachment structure respectively bonded to opposing sides of a platform. At least one of the airfoil, the platform and the attachment structure are constructed from a ceramic matrix composite..

06/30/16
20160186581 

Turbine wheels with preloaded blade attachment


A wheel assembly for a gas turbine engine is disclosed. The wheel assembly includes a disk arranged for rotation about a central axis and formed to include a plurality of slots.

06/30/16
20160186577 

Cooling configurations for turbine blades


A blade in a turbine of a gas turbine engine that includes: an outer surface bending along an edge at an angle greater than about 120° so to define a first outer surface to a first side of the edge and a second outer surface to a second side of the edge; an internal flow passage; and a forked cooling channel configured so to fluidly connect the internal flow passage to a first film cooling port and a second film cooling port formed to each side of the edge.. .

06/30/16
20160186574 

Interior cooling channels in turbine blades


A blade for a turbine of a gas turbine engine that includes an airfoil, the airfoil having a leading edge, a trailing edge, an outboard tip, and an inboard end. The airfoil may further include a cooling configuration that includes a plurality of cooling channels for receiving and directing a coolant.

06/30/16
20160186571 

Mixing plenum for spoked rotors


A gas turbine engine may comprise a first rotor with a primary flowpath along an outer diameter of the first rotor. A secondary flowpath may be radially inward from the primary flowpath.



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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