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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
06/16/16
20160172931 
 Alternator rotor to stator integrated hrdrodynamic bearing patent thumbnailAlternator rotor to stator integrated hrdrodynamic bearing
A gas pressurized system, incorporated as the fluid means yields improved bearing life, reduced machine axial rotor system length and reduced costs in high speed alternators and or motors applications such as in turbomachinery, alternators for generating electricity, microturbines, hybrid gas turbine engines removing the need for external bearings.. .

06/16/16
20160171796 
 Gas turbine engine anomaly detections and fault identifications patent thumbnailGas turbine engine anomaly detections and fault identifications
System and methods for detecting anomalies and identifying faults of a gas turbine engine may include a recorder in communication with a processor. The recorder may be configured to capture archival data of the gas turbine engine.
Inha University


06/16/16
20160169521 
 Swirler mount interface for gas turbine engine combustor patent thumbnailSwirler mount interface for gas turbine engine combustor
A swirler is provided for a gas turbine engine. The swirler includes a swirler body with a threaded section and a multiple of circumferentially arranged tabs operable to flex radially outward.
United Technologies Corporation


06/16/16
20160169516 
 Gas turbine engine combustor bulkhead assembly patent thumbnailGas turbine engine combustor bulkhead assembly
A bulkhead assembly for a combustor of a gas turbine engine includes a bulkhead support shell with a multiple of swirler openings. Each of the multiple of swirler openings is surrounded by a first multiple of cooling impingement passages that define an angle α with respect to a hot side of the bulkhead support shell and a second multiple of cooling impingement passages that define an angle β with respect to the hot side of the bulkhead support shell.
United Technologies Corporation


06/16/16
20160169514 
 Gas turbine engine diffuser-combustor assembly inner casing patent thumbnailGas turbine engine diffuser-combustor assembly inner casing
An inner casing for a diffuser-combustor assembly of a gas turbine engine is disclosed. The inner casing may include an outer-ring, an inner-ring circumscribed by the outer-ring, and a strut having a body extending between the inner-ring and the outer-ring.
United Technologies Corporation


06/16/16
20160169512 
 Cooled wall assembly for a combustor and  design patent thumbnailCooled wall assembly for a combustor and design
A wall assembly that may be for a combustor of a gas turbine engine includes a liner having a hot face that defines a combustion chamber, an opposite cold face, and a plurality of effusion holes. A shell of the assembly is spaced outward from the cold face and includes a plurality of impingement holes each having a centerline orientated substantially normal to the cold face.
United Technologies Corporation


06/16/16
20160169246 
 Plastic variable inlet guide vane patent thumbnailPlastic variable inlet guide vane
The present disclosure relates generally to the field of variable geometry guide vanes for gas turbine engines. More specifically, the present disclosure relates to a plastic variable inlet guide vane for a gas turbine engine..
United Technologies Corporation


06/16/16
20160169245 
 High compressor exit guide vane assembly to pre-diffuser junction patent thumbnailHigh compressor exit guide vane assembly to pre-diffuser junction
A pre-diffuser and exit guide vane (egv) system for a gas turbine engine includes an annular egv assembly containing a number of guide vanes and having an annular opening bounded by a radially inner annular sealing surface at a first radius and a radially outer annular sealing surface at a second radius. First and second seals substantially matching the first and second radii respectively join the egv assembly to an annular pre-diffuser having an annular opening bounded by radially inner and outer annular sealing surfaces at substantially the first and second radii.
United Technologies Corporation


06/16/16
20160169243 
 Gas turbine engine airfoil shaped component patent thumbnailGas turbine engine airfoil shaped component
Where βi is inlet metal angle, βe is exit metal angle, and β is a camber angle at a given chord location.. .

06/16/16
20160169157 
 Gas turbine engine and thrust reverser assembly therefore patent thumbnailGas turbine engine and thrust reverser assembly therefore
The present disclosure relates generally to a thrust reverser for a gas turbine engine. As a translating cowl is translated aft from the nacelle of the gas turbine engine, a cascade is also translated in the aft direction and a blocker door coupled to the cascade is pivoted into a fan duct by means of a camming surface, thereby diverting air in the fan duct through the cascade.
United Technologies Corporation


06/16/16
20160169120 

Fuel schedule for robust gas turbine engine transition between steady states


A fuel injection system for a gas turbine engine can be used to ensure successful transition in all conditions, while avoiding the possibility of steady state, or increasing power mode, operations with an insufficiently filled secondary fuel line. This may be accomplished by altering a pressure in a secondary fuel line.
United Technologies Corporation


06/16/16
20160169118 

Dual tower shaft gearbox for gas turbine engine


A gas turbine engine includes a turbine section that has first and second turbines mounted for rotation about a common rotational axis within an engine static structure. First and second turbine shafts coaxial with one another and to which the first and second turbines are respectively operatively mounted.
United Technologies Corporation


06/16/16
20160169117 

Systems and methods for compressor anticorrosion treatment using cooling water system


The present application provides a gas turbine engine. The gas turbine engine may include a compressor, a condensate or boiler feed water system in communication with the compressor, a dosing system in communication with the condensate or boiler feed water system, and a cooling water system in communication with the condensate or boiler feed water system..
General Electric Company


06/16/16
20160169116 

Systems and methods for compressor anticorrosion treatment


The present application provides a gas turbine engine. The gas turbine engine may include a compressor, a compressor wash system in communication with the compressor, a condensate or boiler feed water system in communication with the compressor, and a dosing system in communication with the condensate or boiler feed water system..
General Electric Company


06/16/16
20160169110 

Premixing nozzle with integral liquid evaporator


The present application provides a fuel nozzle for a gas turbine engine using a primary fuel and a secondary fuel. The fuel nozzle may include a number of primary fuel injection ports for the primary fuel, a water passage, a number of secondary fuel injection ports, and a secondary fuel evaporator system for atomizing the secondary fuel..
General Electric Company


06/16/16
20160169109 

Modulated cooled p3 air for impeller


A method and apparatus using a cooler to selectively cool p3 air directed into an impeller rear cavity of a gas turbine engine during engine high power levels, may include connection of the cooler to a low pressure compressor bleed-off valve apparatus that is modulated to be closed during engine high power levels to create a pressure differential over the bleed-off valve apparatus, to drive a stream of low pressure compressor air as a cooling work fluid under such pressure differential to selectively flow through the cooler.. .
Pratt & Whitney Canada Corp.


06/16/16
20160169107 

Systems and methods for injecting fluids at one or more stages of a multi-stage component


A system for injecting one or more fluids at one or more stages of a multi-stage component of a gas turbine engine is disclosed herein. The system includes a fluid source having a fluid.
General Electric Company


06/16/16
20160169102 

Reverse core flow gas turbine engine


A reverse flow gas turbine engine includes a propulsor section which includes a propulsor compressor section and a propulsor turbine section. The propulsor section includes a fan section and a geared architecture.
United Technologies Corporation


06/16/16
20160169050 

Gas turbine engine mid-turbine frame tie rod arrangement


A gas turbine engine mid-turbine frame includes an annular case that has a hole. A tie rod with a first end extends through the hole.
United Technologies Corporation


06/16/16
20160169049 

Pre-diffuser strut for gas turbine engine


A pre-diffuser of an inner diffuser case of a gas turbine engine may comprise an annular outer wall and an annular inner wall radially inside of the annular outer wall to define a passage for primary airflow therebetween. The pre-diffuser may further comprise at least one strut extending radially between the annular inner wall and the annular outer wall and at least one aperture formed in the strut that extends radially through the strut, the annular inner wall, and the annular outer wall.
United Technologies Corporation


06/16/16
20160169048 

Fan track liner


A containment arrangement for a gas turbine engine comprises: a radially outer annular casing (12); a fan track liner (28) radially within the casing comprising: an impact region (30) comprising a cellular material having a first compressive strength; at least one elongate ridge portion (26) extending through the impact region in a direction having an axial component, the ridge portion having a second compressive strength higher than the first compressive strength; and a gas-washed layer (38) radially within the fan track liner.. .
Composite Technology And Applications Limited


06/16/16
20160169043 

Fan casing arrangement for a gas turbine engine


There is proposed a fan casing arrangement for a gas turbine engine (10) of a type having a propulsive fan (12), the fan casing arrangement being configured to circumscribe the fan (12) and having a fan case (24) and a fan track liner. The fan track liner is provided around the inside of the fan case (24) so as to adopt a radial position between the fan (12) and the fan case (24), and the arrangement is configured such that the fan track liner includes a liner ring (25) which is radially outwardly biased against the inside of the fan case (24).
Rolls-royce Plc


06/16/16
20160169037 

Turbine shroud sealing architecture


A shroud sealing arrangement for a gas turbine engine, which comprises a static shroud assembly mounted to an engine case and having a platform surrounding a rotatable airfoil array. The platform has an inner side and an outer side and extends from a leading edge to a trailing edge.
Pratt & Whitney Canada Corp.


06/16/16
20160169036 

Gas turbine engines with heated cases


A case for a gas turbine engine includes a case body defining an axially extending core flow path, a radially extending bleed air duct coupling the core flow path in fluid communication with the external environment, and a structure-supporting member spanning the bleed air duct. A lubricant conduit is connected to the case body and is in thermal communication with the structure-supporting member..
United Technologies Corporation


06/16/16
20160169034 

Core case heating for gas turbine engines


A case for a gas turbine engine includes a core body. The core body defines a longitudinally extending core flow path, a laterally extending bleed air duct coupling the core flow path in fluid communication with the external environment, and a structure-supporting member spanning the bleed air duct.
United Technologies Corporation


06/16/16
20160169032 

Borescope plug assembly for gas turbine engine


A borescope plug assembly includes a borescope plug having a shaft section and a tip section, a bushing engageable with the shaft section and a seal engageable with the tip section.. .
United Technologies Corporation


06/16/16
20160169029 

Geared turbofan engine with low pressure environmental control system for aircraft


A gas turbine engine assembly includes a fan section delivering air into a main compressor section. The main compressor section compresses air and delivers air into a combustion section.
United Technologies Corporation


06/16/16
20160169027 

Tip clearance control for turbine blades


A carrier segment of a carrier section for circumscribing an array of circumferentially spaced turbine blades of a gas turbine engine, the blades being disposed radially inwardly of a turbine casing, the carrier segment including a carrier wall disposed radially inwardly of the casing and radially outwardly of the turbine blades, and the carrier wall including one or more portions facing the casing, wherein at least one of the one or more portions of the carrier wall is provided with one or more impingement apertures therein for passage therethrough of air of a predetermined temperature, heating air, from a feed source into impingement onto the turbine casing. The application of heating air onto the casing during transient stages of enhanced engine power, e.g.
Rolls-royce Plc


06/16/16
20160169026 

Tip clearance control for turbine blades


An engine includes circumferentially spaced turbine blades radially inward a casing and circumscribed by a carrier section having segments, each having a carrier wall radially inward the casing and radially outward the turbine blades. The wall has one or more portions facing the casing.
Rolls-royce Plc


06/16/16
20160169022 

Annular cartridge seal


A seal for a gas turbine engine may include a first cartridge, a second cartridge, and a wave spring. The wave spring may be located between the first cartridge and the second cartridge.
United Technologies Corporation


06/16/16
20160169020 

Gas turbine engine non-rotating structure wedge seal


A seal assembly arrangement for a gas turbine engine includes first and second non-rotating structures respectively that provide first and second faces. A sealing assembly includes first and second sealing rings respectively that engage the first and second faces.
United Technologies Corporation


06/16/16
20160169019 

Seal runner


A seal runner for a gas turbine engine, the seal runner including an annular body having a sealed cavity defined therein, the cavity being elongated along an axial direction of the body and being annular, the cavity at least partially filled with a coolant, the coolant being liquid across a range of operating temperatures of the gas turbine engine, the coolant having a temperature dependent density across the range of operating temperatures of the gas turbine engine. A gas turbine engine and a method of cooling a seal runner exposed to a temperature gradient are also discussed..
Pratt & Whitney Canada Corp.


06/16/16
20160169017 

Circumferentially varying axial compressor endwall treatment for controlling leakage flow therein


A compressor for a gas turbine engine including one or more endwall treatments for controlling leakage flow and circumferential flow non-uniformities in the compressor. The compressor includes a casing, a hub, a flow path formed between the casing and the hub, a plurality of blades positioned in the flow path, and one or more circumferentially varying end-wall treatments formed in an interior surface of at least one of the casing or the hub.
General Electric Company


06/16/16
20160169013 

Gas turbine engine component with abrasive surface formed by electrical discharge machining


A component for a gas turbine engine is described. The component may comprise a body portion formed from a metallic material.
United Technologies Corporation


06/16/16
20160169012 

Plated polymer components for a gas turbine engine


Plated polymeric gas turbine engine parts and methods for fabricating lightweight plated polymeric gas turbine engine parts are disclosed. The parts include a polymeric substrate plated with one or more metal layers.
United Technologies Corporation


06/16/16
20160169005 

Gas turbine engine component with increased cooling capacity


A cooling circuit for a gas turbine engine comprises a gas turbine engine component having a body with at least one internal cavity defined by a cavity wall. A plurality of cooling holes formed within the cavity wall, wherein each cooling hole is defined by a length extending from a cooling hole inlet to a cooling hole outlet, and wherein the cooling holes are positioned relative to each other such that a minimum allowable ligament distance is maintained between adjacent cooling holes along the entire length of each cooling hole.
United Technologies Corporation


06/16/16
20160169004 

Cooling passages for gas turbine engine component


A gas turbine engine component includes a wall having an inner surface and an outer surface. At least one non-rectangular slot extends through the outer wall surface and is in communication with a passage.
United Technologies Corporation


06/16/16
20160169003 

Cooling of engine components


A component, e.g. An aerofoil component like a turbine-blade or guide-vane, for a gas turbine engine, including first and second walls defining at least one passage for supply of cooling fluid to a portion of the component to be cooled, the portion including a slot via which cooling fluid passes from the passage to exit of slot for effecting cooling of the portion, wherein the slot includes at least one side wall, pair of opposite side walls, each having surface profile defining array of channels for passage of cooling fluid, and surface profile defining each of arrays of channels is undulating with the respective arrays of channels in two side walls being angled with respect to one another.
Rolls-royce Plc


06/16/16
20160169001 

Diffused platform cooling holes


A gas turbine engine component has first and second components each having a platform with an upper surface and a lower surface and with a plurality of side faces extending between the upper and lower surfaces. The platforms are arranged adjacent to one another such that one side face of the platform faces a mating side face of an adjacent platform.
United Technologies Corporation


06/16/16
20160168996 

Removable riveted balance ring


The present disclosure includes a system for balancing a turbine disk stack, including a high pressure turbine disk stack. A flange is grooved to accommodate and orient a slip ring.
United Technologies Corporation


06/16/16
20160167798 

Variable pitch mounting for aircraft gas turbine engine


Aircraft engine mounted to aircraft pylon with variable pitch mounting system includes variable length actuator disposed between engine and pylon for pitching engine relative to pylon. Spaced apart pylon front and rear mounts may pivotably mount front and rear stationary engine components of engine to front and rear mount positions on pylon.
General Electric Company


06/16/16
20160167797 

Engine mount


A mounting system is arranged in use for attaching a gas turbine engine to a pylon of an aircraft. The mounting system comprises a first frame of three elongate members arranged in a triangle.
Rolls-royce Plc


06/16/16
20160167190 

Systems and methods for finishing flow elements


Systems and methods for finish portions of parts for gas turbine engines are provided. More specifically, systems and methods for finishing flow elements (e.g., stator vanes and turbine blades) or gas turbine engines are provided.
United Technologies Corporation


06/09/16
20160164372 

Concentric ring generators


A concentric generator usable with a gas turbine engine having a shaft. Disclosed embodiments include a generator with a rotor integral with the gas turbine shaft and a stator mounted concentrically with respect to the rotor.
The Boeing Company


06/09/16
20160161124 

Single-fitting, dual-circuit fuel nozzle


A manifold fitting receiving radial and axial manifolds and providing two radial outlets is disclosed. The manifold fitting, when used in conjunction with a fuel injector and a combustor for a gas turbine engine, reduces the radial footprint of the fuel injector and thereby allows for a more compact engine.
United Technologies Corporation


06/09/16
20160161123 

Fuel supply system for a gas turbine engine


In one aspect, a fuel supply system may include a fuel injector having a primary and a secondary pilot fuel nozzle in fluid communication with a primary and a secondary fuel circuit, respectively, and a main fuel nozzle in fluid communication with a main fuel circuit. The fuel injector may also define a by-pass fuel circuit connected between the primary circuit and the secondary circuit and/or the main circuit.
General Electric Company


06/09/16
20160161121 

Gas turbine engine with ceramic panel


A gas turbine engine ceramic panel assembly includes a ceramic liner that has a slot and includes a hole. An insert is received in the slot and provides a female fastening element aligned with the hole.
United Technologies Corporation


06/09/16
20160160875 

Gas turbine engine with fan clearance control


A fan section for use in a gas turbine engine has a fan rotor with a plurality of blades and an outer fan housing surrounding the plurality of blades. A tip clearance is defined between a radially outer tip of the blades and a radially inner surface of the fan housing.
United Technologies Corporation


06/09/16
20160160869 

Plated polymer compressor


Plated polymeric gas turbine engine parts and methods for fabricating lightweight plated polymeric gas turbine engine parts are disclosed. The parts include a polymeric substrate plated with one or more metal layers.
United Technologies Corporation


06/09/16
20160160867 

Electrically coupled counter-rotation for gas turbine compressors


A system and method for implementing stage-by-stage counter rotation in a multi-stage axial compressor of a gas turbine engine. The system includes an electrical power generator and an electric motor.
Embry-riddle Aeronautical University, Inc.


06/09/16
20160160863 

Plated polymer fan


Plated polymeric gas turbine engine parts and methods for fabricating lightweight plated polymeric gas turbine engine parts are disclosed. The parts include a polymeric substrate plated with one or more metal layers.
United Technologies Corporation


06/09/16
20160160761 

Gas turbine engine with single turbine driving two compressors


A gas turbine engine comprises a lower pressure compressor and a higher pressure compressor. A single turbine drives both the lower pressure compressor and the higher pressure compressor through a gear reduction.
United Technologies Corporation


06/09/16
20160160760 

Self-opening cooling passages for a gas turbine engine


A turbine component for a gas turbine engine includes a multiple of self-opening cooling passages each of which defines a self-opening cooling passage axis that extends through a gas path surface.. .
United Technologies Corporation


06/09/16
20160160758 

Gas turbine engine nacelle anti-icing system


A gas turbine engine de-icing system includes a heat exchanger. A coolant loop is in fluid communication with the heat exchanger and is configured to circulate a coolant.
United Technologies Corporation


06/09/16
20160160714 

Gas turbine engine with split lubrication system


A lubrication system for use in a gas turbine engine is comprised of a first pump driven by a first shaft at a first speed and a second pump driven by a second shaft at a second speed that is faster than the first speed. The first and second pumps provide lubricant to an engine operating system.
United Technologies Corporation


06/09/16
20160160688 

Attachment of piloting feature


A fan assembly for use in a gas turbine engine of an aircraft includes a fan disk having a number of fan blades and a windage shield coupled to the fan disk to move therewith. The fan assembly supplies air for use in the engine.
Rolls-royce Corporation


06/09/16
20160160687 

Outer diffuser case for a gas turbine engine


An outer diffuser case of a diffuser case assembly for use in a gas turbine engine may have a housing orientated about an engine axis, a forward flange projecting radially outward from the housing, a mid-flange spaced axially aft of the forward flange and projecting radially inward from the housing, and an aft flange projecting radially outward from the housing. The mid flange is spaced axially between the forward and aft flanges and is configured to detachably engage an inner diffuser case of the case assembly.
United Technologies Corporation


06/09/16
20160160686 

Lubrication system for a gear system of a gas turbine


The present disclosure is directed to lubrication systems for gear systems of a gas turbine engine. In one embodiment, a lubrication system includes an auxiliary reservoir configured to store lubricant and a lubrication collection device.
United Technologies Corporation


06/09/16
20160160685 

Eliminatin of unfavorable outflow margin


A panel for use in a gas turbine engine exhaust case is disclosed. The panel has an airfoil section and a flow diverting structure adjacent a leading edge, wherein the flow diverting structure directs fluid flow into an area of the airfoil that lacks sufficient internal pressure for cooling fluid flow..
United Technologies Corporation


06/09/16
20160160682 

System and method to manage transients for rapid power demand changes


An exemplary system may include a gas turbine engine configured to operate at an engine power level to satisfy an engine power demand. The system may also include at least one generator operatively coupled to the engine and configured to generate electrical power based at least in part on the engine power demand.
Rolls-royce Corporation


06/09/16
20160160681 

Plated polymer nacelle


Plated polymeric gas turbine engine parts and methods for fabricating lightweight plated polymeric gas turbine engine parts are disclosed. The parts include a polymeric substrate plated with one or more metal layers.
United Technologies Corporation


06/09/16
20160160680 

Compressed chopped fiber composite structural guide vane


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


06/09/16
20160160678 

Ground handling system for a composite fan case and a using the same


The present disclosure relates generally to a system for handling a gas turbine engine fan case. The system includes a composite fan containment case including a case outer surface, a case inner surface, and at least one main case aperture extending from the case outer surface through the case inner surface, and at least one shear puck, the at least one shear puck including a shear puck protrusion; wherein the shear puck protrusion of each of the at least one shear pucks is disposed within a respective one of each of the at least one main case apertures..
United Technologies Corporation


06/09/16
20160160676 

Gas turbine engine variable stator vane


A gas turbine engine includes a stator stage arranged in a core flow path that includes a vane that is configured to be retractable from the core flow path during engine operation.. .
United Technologies Corporation


06/09/16
20160160674 

Gas turbine engine forward bearing compartment architecture


A gas turbine engine includes a front center body case structure. A geared architecture is at least partially supported by the front center body case structure.
United Technologies Corporation


06/09/16
20160160673 

Stiffness controlled abradable seal system and methods of making same


A stiffness controlled abradable seal system for a gas turbine engine includes a cantilevered arm that supports one of a rotating seal surface and a static seal surface, a stiffness of the cantilevered arm controlled to achieve a desired operational temperature at a seal interface, and an optimally matched abradeable seal material with required thermo-physical and friction properties to enable desired wear mechanisms and maximized sealing and durability.. .
United Technologies Corporation


06/09/16
20160160671 

Method to pilot using flexible profile


A fan assembly for use in a gas turbine engine of an aircraft includes a fan disk having a number of fan blades and a windage shield coupled to the fan disk to move therewith. The fan assembly supplies air for use in the engine.
Rolls-royce Corporation


06/09/16
20160160670 

Vane assembly of a gas turbine engine


A first stage vane array of a high pressure turbine that may be for a geared turbofan engine includes a plurality of airfoils circumferentially spaced from one-another and orientated about an engine axis. Each airfoil has a leading edge and a trailing edge with the trailing edge being circumferentially separated by the next adjacent trailing edge by a pitch distance.
United Technologies Corporation


06/09/16
20160160669 

Abrasive flow media fixture with end contour


A fixture assembly includes an inner diameter wall displaced from a main body by a first end wall with a convex surface and a second end wall with a concave surface. A method of machining a gas turbine engine component with an abrasive flow media (afm) process includes restricting a flow of media adjacent to an outer sidewall of an outer airfoil to be generally equal between each of a multiple of airfoils of the component..
United Technologies Corporation


06/09/16
20160160668 

Inner diffuser case cone and skirt


An inner diffuser case for a gas turbine engine may include a pre-diffuser including a plurality of struts. At least one of the struts may include an aperture therethrough.
United Technologies Corporation


06/09/16
20160160665 

Gas turbine engine stator vane asymmetry


A gas turbine engine includes an array of airfoils that include first and second segments. The first segment includes a first number of airfoils that are circumferentially spaced from one another a first angular spacing.
United Technologies Corporation


06/09/16
20160160664 

Recession resistant ceramic matrix composites and environmental barrier coatings


The disclosure relates generally to recession resistant gas turbine engine articles that comprise a silicon containing substrate, and related coatings and methods. The present disclosure is directed, inter alia, to an engine article comprising a silicon substrate which is coated with a chemically stable porous oxide layer.
General Electric Company


06/09/16
20160160660 

Turbine engine components with chemical vapor infiltrated isolation layers


An assembly for use in a gas turbine engine and method for making the same are described herein. The assembly comprising a cmc component, a metallic component spaced apart from the cmc component, and a spacer.
Rolls-royce Corporation


06/09/16
20160160652 

Cooled pocket in a turbine vane platform


An airfoil includes a platform including a pocket, a continuous solid cover plate bonded over the pocket, and a plurality of apertures in the platform in fluid communication with the pocket and adjacent the continuous solid cover plate. A gas turbine engine including the airfoil and a method of cooling an article of a gas turbine engine are also disclosed..
United Technologies Corporation


06/09/16
20160160648 

Rotor disk assembly for a gas turbine engine


A rotor assembly for a gas turbine engine includes a rotor disk. The rotor disk includes a heat barrier feature radially inward of a rotor blade and radially outward of a rotor disk..
United Technologies Corporation


06/09/16
20160159488 

Plated polymer nosecone


Plated polymeric gas turbine engine parts and methods for fabricating lightweight plated polymeric gas turbine engine parts are disclosed. The parts include a polymeric substrate plated with one or more metal layers.
United Technologies Corporation


06/02/16
20160153865 

Gas turbine engine airfoil growth inspection method


A method of measuring untwist in an gas turbine engine airfoil, the method includes measuring first and second cooling holes on an exterior airfoil surface of an airfoil, determining untwist in a chord-wise direction and/or creep in a radial direction based upon the measurement, evaluating the determination relative to reference information for the airfoil, and outputting a part status based upon the evaluation.. .
United Technologies Corporation


06/02/16
20160153660 

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 swirler threaded section defined around a swirler central longitudinal axis. A bulkhead support shell for a combustor of a gas turbine engine includes a swirler boss with a boss threaded section defined around a swirler central longitudinal axis.
United Technologies Corporation


06/02/16
20160153659 

Gas turbine engine ceramic component assembly and bonding material


A gas turbine engine component assembly includes a ceramic component having a first thermal characteristic. A metallic component has a second thermal characteristic.
United Technologies Corporation


06/02/16
20160153658 

Combustor wall for a gas turbine engine and acoustic dampening


A vascular wall of a combustor that may be for a gas turbine engine includes a first face defining at least in-part a combustion chamber, a second face defining at least in-part a cooling air plenum, and a vascular lattice structure located between the first and second faces for distributing cooling air from the plenum and to the chamber. The vascular lattice structure may be configured to enhance cooling air flow where needed whiling providing structural support.
United Technologies Corporation


06/02/16
20160153466 

Variable vane for gas turbine engine


A turbomachine includes a vane, a rotation support coupled to an end of the vane, and a spindle coupled to the rotation support. The spindle, the vane, and the rotation support are rotationally aligned.
Rolls-royce North American Technologies, Inc.


06/02/16
20160153465 

Axial compressor endwall treatment for controlling leakage flow therein


An axial compressor for a gas turbine engine including one or more endwall treatments for controlling leakage flow in the compressor. The one or more endwall treatments having a height formed in an interior surface of a compressor casing or a compressor hub and configured to return a flow adjacent a plurality of rotor blade tips or a plurality of stator blade tips to a cylindrical flow passage upstream of a point of removal of the flow.
General Electric Company


06/02/16
20160153463 

Fiber reinforced spacer for a gas turbine engine


A spacer of a gas turbine engine is reinforced with a fiber. The fiber can be cured with a substrate to form a fiber reinforced composite material.
United Technologies Corporation


06/02/16
20160153399 

Gas turbine engine and thrust reverser assembly therefore


The present disclosure relates generally to a thrust reverser for a gas turbine engine. As a translating cowl is translated aft from the nacelle of the gas turbine engine, a cascade is also translated in the aft direction and a blocker door coupled to the cascade is pivoted into a fan duct, thereby diverting air in the fan duct through the cascade.
United Technologies Corporation


06/02/16
20160153398 

Gas turbine engine exhaust mixer


An exhaust mixer for a gas turbine engine includes an annular wall having upstream end adapted to be fastened to an engine case and a downstream end forming a plurality of inner and outer mixer lobes. A support member interconnects at least a number of the inner lobes, and includes a circumferentially extending stiffener ring located radially inwardly from the inner lobes and a series of circumferentially spaced apart mixer struts radially extending from the inner lobes to the stiffener ring.
Pratt & Whitney Canada Corp.


06/02/16
20160153397 

Gas turbine engine system for modulating flow of fan by-pass air and core engine air


The system (10) provides a modulator ring (54) secured adjacent an exhaust end (56) of an inner wall of a by-pass fan air duct (40) and secured adjacent a convergent nozzle section (38) of the engine wherein flow of by-pass fan air (42) and core engine air (18) converge within an exhaust nozzle (34), the modulator ring (54) may be actuated to extend beyond the exhaust end (56) of the duct (40) to decrease air passage (62) forcing more air into the core engine (14) for greater thrust from the core engine (14) with minimal loss of thrust from the by-pass fan air (42). The modulator ring (54) stay alternatively rotate to uncover trailing-edge slots in the exhaust end (56) of the duct to also modulate flow rates of by-pass fan air (42) into the convergent nozzle section (38),.
United Technologies Corporation


06/02/16
20160153365 

Method of operation of a gas turbine engine


A method of operating a gas turbine engine (20) comprising a variable geometry compressor (24), a variable geometry combustor (28), and a variable geometry turbine (30). The method comprises operating the variable geometry combustor (28) such that a corrected flow ωc through a combustion zone (46, 48) of the combustor (28) matches a predetermined value..
Rolls-royce Plc


06/02/16
20160153364 

Gas turbine fuel control system


A method of controlling a flow of a fuel mixture of different types of fuel in a gas turbine engine is described which includes determining a combustive energy value of an input of the fuel mixture in the engine, extracting fuel schedule data from a fuel schedule established for a reference fuel, determining a desired fuel mixture flow rate by adapting the fuel schedule data to the fuel mixture based on the combustive energy value, and controlling a fuel metering device of the engine such that the fuel mixture flow rate corresponds to the desired fuel mixture flow rate.. .
Pratt & Whitney Canada Corp.


06/02/16
20160153361 

Bleed valve resonance augmentations


Bleed valve assemblies in a gas turbine engine are disclosed herein. A bleed valve assembly in a low pressure compressor may include a bleed valve and a resonator chamber.
United Technologies Corporation


06/02/16
20160153356 

Geared turbofan engine gearbox arrangement


A gas turbine engine according to an example of the present disclosure includes, among other things, a fan section having a plurality of fan blades. The plurality of fan blades has a peak tip radius rt and an inboard leading edge radius rh at a first inboard boundary of a first flowpath.
United Technologies Corporation


06/02/16
20160153313 

Flange partial section replacement repair


A method of repairing a casing for a gas turbine engine, wherein the casing has a wall extending generally axially, and between at least one radially extending flange, the radially extending flange being formed with a plurality of bolt holes, includes the steps of removing a portion of the flange including at least one bolt hole. The removed portion is associated with a defect and a remaining portion of the flange includes at least one non-removed bolt hole.
United Technologies Corporation


06/02/16
20160153306 

Radial position control of case support structure with splined connection


A radial position control assembly for a gas turbine engine includes a case structure. A support structure is operatively supported by the case structure respectively with first and second splines in engagement with one another.
United Technologies Corporation


06/02/16
20160153305 

Tuned rotor disk


A gas turbine engine includes a rotor that has a rotor disk and a plurality of circumferentially-spaced blades. The rotor disk and the blades are co-rotatable about an axis.
United Technologies Corporation


06/02/16
20160153303 

Snap in platform damper and seal assembly for a gas turbine engine


A turbine assembly includes a first turbine blade circumferentially adjacent to a second turbine blade. The first turbine blade includes a first platform with a first underplatform surface.
United Technologies Corporation


06/02/16
20160153300 

Sealing assembly


A seal arrangement for a gas turbine engine includes a seal runner having a sealing lip extending radially outwardly from a root portion to a tip portion. A static seal is mounted in axially opposed facing relationship to the sealing lip.
Pratt & Whitney Canada Corp.


06/02/16
20160153297 

Gas turbine engine turbine vane ring arrangement


A vane pack for a gas turbine engine includes an annular arrangement of vanes. A ring is secured around the vanes and extends proud of an axial end of the vanes..
United Tehnologies Corporation


06/02/16
20160153296 

Flow discourager for vane sealing area of a gas turbine engine


An interface within a gas turbine engine includes a sealing surface defined by a portion of a vane platform. A seal is in contact with said sealing surface.
United Technologies Corporation


06/02/16
20160153291 

Cooling system of a stator assembly for a gas turbine engine having a variable cooling flow mechanism and operation


A cooling system integrated into a stator assembly of a gas turbine engine has an on-board injector or cooling nozzle located for cooling of a rotor assembly. The nozzle may be generally annular and may contain a plurality of pivoting airfoils circumferentially spaced from one-another for directing cooling air flow from the nozzle and generally toward a plurality of holes in a cover of the rotor assembly.
United Technologies Corporation


06/02/16
20160153290 

Gas turbine blade and protecting same


A method of protecting a blade of a gas turbine engine by applying a nanocrystalline metal coating to a portion of the blade root is disclosed, which includes preparing at least a portion of a dovetail of the blade root for coating; and then applying a nanocrystalline metal coating to said portion.. .

06/02/16
20160153289 

Gas turbine engine ceramic component assembly attachment


A gas turbine engine component assembly includes first and second portions, wherein at least one of the first and second portions is a ceramic material. The first portion includes an aperture having a first angled surface.
United Technologies Corporation


06/02/16
20160153288 

Recession resistant ceramic matrix composites and environmental barrier coatings


The disclosure relates generally to recession resistant gas turbine engine articles that comprise a silicon containing substrate, and related coatings and methods. The present disclosure is directed, inter alia, to an engine article comprising a silicon substrate which is coated with a chemically stable porous oxide layer.
General Electric Company


06/02/16
20160153287 

Plated polymer turbine component


Plated polymeric gas turbine engine parts and methods for fabricating lightweight plated polymeric gas turbine engine parts are disclosed. The parts include a polymeric substrate plated with one or more metal layers.
United Technologies Corporation


06/02/16
20160153284 

Gas turbine engine flow path member


A gas turbine engine flow path member is disclosed which includes an extending end portion capable of contacting a surface of the turbine engine. The flow path member includes openings to pass a cooling fluid to cool the extending end portion.
Rolls-royce North American Technologies, Inc.


06/02/16
20160153283 

Gas turbine engine component with converging/diverging cooling passage


A component for a gas turbine engine includes a gas path wall having a first surface and a second surface and a cooling hole extending through the gas path wall from the first surface to the second surface. The cooling hole includes an inlet portion having an inlet at the first surface, an outlet portion having an outlet at the second surface, and a transition defined between the inlet and the outlet.
United Technologies Corporation


06/02/16
20160153282 

Stress reduction for film cooled gas turbine engine component


A component for a gas turbine engine includes a highly conductive film cooled component with a leading edge area and a trailing edge area, the leading edge area including a multiple of film holes spaced to reduce a thermal gradient between the leading edge area and the trailing edge area to below about 200 f (93 c).. .
United Technologies Corporation




Gas Turbine Engine topics: Gas Turbine, Gas Turbine Engine, Downstream, High Speed, Circulation, Heat Exchanger, Attenuation, Variable Inlet Guide Vanes, Variable Inlet Guide Vane, Guide Vane, Guide Vanes, Inlet Guide Vanes

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