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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
05/26/16
20160149469 
 Tail cone generator with integral speed increasing gearbox patent thumbnailnew patent Tail cone generator with integral speed increasing gearbox
A gas turbine engine is provided, comprising a tail cone and a low-pressure spool outside the tail cone. An input shaft may be coupled to the low-pressure spool and inside the tail cone.
Hamilton Sundstrand Corporation


05/26/16
20160146601 
 Throat area calculation for a section of a gas turbine engine patent thumbnailnew patent Throat area calculation for a section of a gas turbine engine
A method of calculating a throat area of a section of a machinery, according to an exemplary aspect of the present disclosure includes, among other things, outlining a boundary of the throat area of the section, selecting a plurality of inspection points along the boundary of the throat area, dividing the throat area into a plurality of sections, calculating an individual area of each of the plurality of sections and summing the individual areas of each of the plurality of sections to calculate the throat area.. .
United Technologies Corporation


05/26/16
20160146465 
 Nozzle guide for a combustor of a gas turbine engine patent thumbnailnew patent Nozzle guide for a combustor of a gas turbine engine
A nozzle guide is provided for a combustor of a gas turbine engine. The nozzle guide includes an annular structure including a plurality of cooling holes, a guide plate including a plurality of openings on an outer periphery of the guide plate, and a plurality of cooling passages within the annular structure to provide air flow from the plurality of cooling holes to the plurality of openings..
United Technologies Corporation


05/26/16
20160146155 
 Gas turbine engine and  assembling the same patent thumbnailnew patent Gas turbine engine and assembling the same
A gas turbine engine having a centerline axis is provided. The gas turbine engine includes a fan and a fan cowl assembly surrounding the fan to define a bypass duct configured to channel airflow for the fan.
General Electric Company


05/26/16
20160146119 
 Gas turbine engine optimization control device patent thumbnailnew patent Gas turbine engine optimization control device
A gas turbine engine optimization control device estimates a specific fuel consumption using a given control parameter of a variable mechanism, determines a change between a specific fuel consumption estimation value by the control parameter of the variable mechanism in a previous operation period and a specific fuel consumption estimation value by the control parameter of the variable mechanism in this operation period, determines a new control parameter of the variable mechanism with which the specific fuel consumption estimation value approaches a minimum, adds the new control parameter of the variable mechanism to a preset control parameter initial value, and sets the addition value to be a control parameter command value of the variable mechanism in a next operation period.. .
Ihi Corporation


05/26/16
20160146115 
 Gas turbine engine and  assembling the same patent thumbnailnew patent Gas turbine engine and assembling the same
A method and system for a turbofan gas turbine engine system is provided. The gas turbine engine system includes a variable pitch fan (vpf) assembly coupled to a first rotatable shaft and a low pressure compressor lpc coupled to a second rotatable shaft.
General Electric Company


05/26/16
20160146113 
 Gas turbine engine and  assembling the same patent thumbnailnew patent Gas turbine engine and assembling the same
A gas turbine engine having a forward thrust mode and a reverse thrust mode is provided. The gas turbine engine includes a variable pitch fan configured for generating forward thrust in the forward thrust mode of the engine and reverse thrust in the reverse thrust mode of the engine.
General Electric Company


05/26/16
20160146103 
 Gas turbine engine shaft members and maintenance method patent thumbnailnew patent Gas turbine engine shaft members and maintenance method
A gas turbine engine includes first and second shaft members in an interference fit relationship with one another at an interface. The first and second shaft members respectively include first and second flanges that are arranged adjacent to the interface.
United Technologies Corporation


05/26/16
20160146102 
 Geared architecture gas turbine engine with oil scavenge patent thumbnailnew patent Geared architecture gas turbine engine with oil scavenge
A gas turbine engine includes a geared architecture with a multiple of intermediate gears, and a baffle with an oil scavenge scoop adjacent to each of the multiple of intermediate gears. A geared architecture and method are also disclosed..
United Technologies Corporation


05/26/16
20160146089 
 Compressor cooling patent thumbnailnew patent Compressor cooling
A cooling arrangement for a compressor drive cone (48) in a gas turbine engine (10). An annular cavity (62) defined by the drive cone (48), a portion of a compressor rotor disc (44) and a downstream cavity wall (52).
Rolls-royce Plc


05/26/16
20160146055 
new patent

Liner hanger with spherical washers


A liner assembly for a gas turbine engine includes a liner defining an inner surface exposed to exhaust gases and a duct spaced radially outward of the liner. A hanger assembly supports the liner relative to the duct.
United Technologies Corporation


05/26/16
20160146053 
new patent

Blade outer air seal support structure


A support structure for a gas turbine engine includes an axially extending portion that forms a loop. A radially extending portion extends radially inward from the axially extending portion.
United Technologies Corporation


05/26/16
20160146052 
new patent

Forged cast forged outer case for a gas turbine engine


A case for a gas turbine engine includes a cast case section cast case section configured to be welded between a forward case section and an aft case section.. .
United Technologies Corporation


05/26/16
20160146049 
new patent

Sealing interface for a case of a gas turbine engine


A case assembly for a gas turbine engine, includes a case with an oversized case boss, said oversized case boss including a peripheral wall that defines a first inner diameter in a first condition to receive a piston seal, and a second inner diameter in a second condition, the second condition including enlargement of the first inner diameter to form a second inner diameter and a bushing mounted within the second inner diameter, an inner diameter of the bushing defines a bushing inner diameter about equivalent to the first inner diameter to receive the piston seal.. .
United Technologies Corporation


05/26/16
20160146046 
new patent

Radially stacked intershaft bearing


An exemplary gas turbine engine includes a radially stacked intershaft bearing assembly. The assembly includes an outer stubshaft having outer and inner diameter surface portions disposed concentrically with respect to one another.
Rolls-royce Corporation


05/26/16
20160146044 
new patent

Internally cooled turbine platform


A turbine flowpath component for a gas turbine engine includes a platform defining at least one internal cooling cavity and a turbine flowpath component cover disposed radially outward of the platform. The turbine flowpath component cover defines a radially outward edge of the at least one internal cooling cavity.
United Technologies Corporation


05/26/16
20160146040 
new patent

Alternating vane asymmetry


A vane assembly for a gas turbine engine may include a plurality of vanes being arranged in vane groupings symmetrically spaced circumferentially from each other. Each vane grouping may include at least a first and a second vane.
United Technologies Corporation


05/26/16
20160146033 
new patent

Gas turbine engine clearance control


A gas turbine engine includes first and second structures secured to one another at a bolted flange joint. A seal is supported by a third structure.
United Technologies Corporation


05/26/16
20160146032 
new patent

Pressure seal with non-metallic wear surfaces


A gas turbine engine has a first component and a second component. The first and second components have a high-pressure chamber on one side and a low pressure chamber on an opposed side.
United Technologies Corporation


05/26/16
20160146030 
new patent

Non-metallic engine case inlet compression seal for a gas turbine engine


A non-metallic engine case inlet compression seal for a gas turbine engine includes a non-metallic longitudinal leg section that extends from the non-metallic arcuate interface section and a non-metallic mount flange section that extends from the longitudinal leg section.. .
United Technologies Corporation


05/26/16
20160146028 
new patent

High strength joints in ceramic matrix composite preforms


A joint between a first preform component and a second preform component that are constructed for ultimate use in a gas turbine engine is disclosed. A plurality of extended fibers may be integral with the first preform component and be at least partially enveloped by the second preform component.
Rolls-royce Corporation


05/26/16
20160146026 
new patent

Transition duct arrangement in a gas turbine engine


An arrangement for a gas turbine engine includes a combustor for producing a working medium by combustion of a mixture of fuel and an oxidant, a turbine section comprising a stationary vane carrier on which a first row of stationary vanes is arranged, and a transition duct for leading the working medium from the combustor to the turbine section. The transition duct has a forward end that adjoins the combustor and an aft end that adjoins the stationary vane carrier.
Siemens Energy, Inc.


05/26/16
20160146025 
new patent

Variable pitch fan for gas turbine engine and assembling the same


A gas turbine engine is provided. The gas turbine engine includes a core and a variable pitch fan arranged in flow communication with the core.
General Electric Company


05/26/16
20160146021 
new patent

Composite blades for gas turbine engines


A turbine wheel for use in a gas turbine engine having a plurality of blades attached to a rotor disk. Each blade is formed as a composite structure including a number of plies of ceramic-containing material.
Rolls-royce North American Technologies, Inc.


05/26/16
20160146012 
new patent

Airfoil with stepped spanwise thickness distribution


An airfoil in a gas turbine engine includes opposed pressure and suction sides joined together at chordally opposite leading and trailing edges. The pressure and suction sides extend spanwise from a root to a tip of the airfoil.
Pratt & Whitney Canada Corp.


05/19/16
20160138807 

Gas turbine engine flow regulating


A gas turbine combustor assembly includes a fuel injector, a dome stator around the fuel injector, and a dome sleeve coupled to the dome stator. The dome sleeve defines an air inlet opening with the dome stator, and is carried to move with respect to the dome stator to change a flow area of the air inlet opening.
United States Government


05/19/16
20160138603 

Split axial-centrifugal compressor


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


05/19/16
20160138523 

Optimal thrust control of an aircraft engine


A control system for a gas turbine engine, a method for controlling a gas turbine engine, and a gas turbine engine are disclosed. The control system may include a nozzle scheduler for determining an exhaust nozzle position goal based on a nozzle schedule of exhaust nozzle positions related to flight conditions.
United Technologies Corporation


05/19/16
20160138478 

Gas turbine engine


A gas turbine engine is disclosed comprising a shaft driven by a turbine, the turbine directly driving a lower speed compressor via a shaft and driving a higher speed compressor via the shaft and a multiplier power gearbox. The gearbox comprises a ring gear, a plurality of planet gears and planet carrier and a sun gear.
Rolls-royce Deutschland Ltd & Co Kg


05/19/16
20160138475 

Method of starting a gas turbine engine


(iii) modifying at least one operating parameter of the gas turbine engine as the rotational speed increases such that for a rotational speed, an operational working line is closer to the reference stability boundary than the reference working line is to the reference stability boundary.. .

05/19/16
20160138474 

Low noise compressor rotor for geared turbofan engine


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


05/19/16
20160138425 

Turbofan engine front section


A front section for a gas turbine engine according to an example of the present disclosure includes, among other things, a fan section including a fan hub. The fan hub includes a hub diameter supporting a plurality of fan blades including a tip diameter.
United Technologies Corporation


05/19/16
20160138423 

Titanium-aluminide components


The present disclosure relates to a hot section gas turbine engine component assembly and a method for forming such.. .
Rolls-royce North American Technologies, Inc.


05/19/16
20160138416 

Variable fan nozzle using shape memory material


A gas turbine engine includes a fan, a nacelle arranged about the fan, and an engine core at least partially within the nacelle. A fan bypass passage downstream of the fan between the nacelle and the gas turbine engine conveys a bypass airflow from the fan.
United Technologies Corporation


05/19/16
20160138406 

Composite components for gas turbine engines


A turbine wheel for use in a gas turbine engine having a plurality of blades attached to a rotor disk. Each blade is formed as a composite structure including a number of plies of ceramic-containing material.
Rolls-royce North American Technologies, Inc.


05/19/16
20160138399 

Reinforced gas turbine engine rotor disk


A structurally-reinforced rotor disk for a gas turbine engine is disclosed. The rotor disk may comprise a body including a rim configured to support airfoils (which may be separate or integral with the airfoils), an axially-extending bore disposed radially inward of the rim, and a radially-extending web connecting the rim and the bore.
United Technologies Corporation


05/12/16
20160131151 

Gas turbine engine airfoil


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


05/12/16
20160131084 

Geared turbofan arrangement with core split power ratio


A gas turbine engine according to an example of the present disclosure includes, among other things, a fan section, and a compressor section including at least a first compressor section and a second compressor section. A power ratio is provided by the combination of the first compressor section and the second compressor section.
United Technologies Corporation


05/12/16
20160131045 

Emissions control system for a gas turbine engine


An emissions control system (10) for a gas turbine engine (12) for reducing co emissions at partial load of the gas turbine engine (12) is disclosed. In at least one embodiment, the emissions control system (10) may be formed from one or more compressed air exhausts (14) for exhausting compressed air into a hot gas pathway contained within a channel (18) formed by a transition (20) extending from a combustor (22) to a turbine assembly (24).
Siemens Energy, Inc.


05/12/16
20160131044 

Gas turbine engine driving multiple fans


A gas turbine engine includes a core engine with a compressor section, a combustor and a turbine. The turbine drives an output shaft, and the output shaft drives at least four gears.
United Technologies Corporation


05/12/16
20160131043 

Turbine engine gearbox


A gas turbine engine comprises a fan, a compressor, a combustor, and a fan drive turbine rotor. The fan drive turbine drives the fan through a gear reduction.
United Technologies Corporation


05/12/16
20160131039 

Gas turbine engine heat exchanger manifold


A heat exchanger manifold for a gas turbine engine according to an exemplary aspect of the present disclosure includes, among other things, a manifold body extending between a first face and a second face, a first seal land defining a first fluid port extending through the manifold body between the first face and the second face, and a first seal received within the first fluid port.. .
United Technologies Corporation


05/12/16
20160131037 

Supply duct for cooling air


In a featured embodiment, a gas turbine engine has a compressor section having a downstream rotor and a diffuser downstream of the compressor section. A combustor receives air downstream of the diffuser.
United Technologies Corporation


05/12/16
20160131036 

Thermal management system for a gas turbine engine


In one exemplary embodiment, a gas turbine engine system for cooling engine components includes an engine core, a core housing containing the engine core, an engine core driven fan forward of the core housing, a nacelle surrounding the fan and the core housing, and a bypass duct defined between an outer diameter of the core housing and an inner diameter of the nacelle. Also included is a thermal management system having a coolant circuit including at least one of a first heat exchanger disposed on the inner diameter of the nacelle and a second heat exchanger disposed on a leading edge of a bifi spanning the bypass duct.
United Technologies Corporation


05/12/16
20160131031 

Gas turbine fast regulation and power augmentation using stored air


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


05/12/16
20160131030 

Gas turbine efficiency and power augmentation improvements utilizing heated compressed air and steam injection


The present invention discloses a novel apparatus and methods for augmenting the power of a gas turbine engine, improving gas turbine engine operation, and reducing the response time necessary to meet changing demands of a power plant. Improvements in power augmentation and engine operation include systems and methods for preheating piping of a power augmentation system and directing flows of hot compressed air, steam or a combination thereof into the gas turbine engine..
Powerphase Llc


05/12/16
20160130982 

Gas turbine efficiency and power augmentation improvements utilizing heated compressed air


The present invention discloses a novel apparatus and methods for augmenting the power of a gas turbine engine, improving gas turbine engine operation, and reducing the response time necessary to meet changing demands of a power plant. Improvements in power augmentation and engine operation include systems and methods for preheating a steam injection system..
Powerphase Llc


05/12/16
20160130980 

Gas turbine engine and frame


One embodiment of the present invention is a unique gas turbine engine. Another embodiment is a unique frame for a gas turbine engine.
Rolls-royce North American Technologies, Inc.


05/12/16
20160130977 

Turbine rotor segmented sideplates with anti-rotation


A segmented sideplate for use in a gas turbine engine is described. The segmented sideplate includes a first plate having a first circumferential edge configured to interface with a complementary circumferential edge.
United Technologies Corporation


05/12/16
20160130975 

Collapsible support structure for a gas turbine engine


Described is a shaft support system for a gas turbine engine comprising: a rotatable fan shaft; first and second support structures extending in parallel from the shaft to a load bearing structure to provide radial location of the shaft within an engine casing, wherein the first support and second support structures include first and second respective mechanical fusible joints; wherein the first fusible joint is a two-stage fuse which partially fails within a first predetermined load range, the second fusible joint fails within a second predetermined load range which is different to the first load range, and the first fusible joint fully fails only when the second fusible joint has failed.. .
Rolls-royce Plc


05/12/16
20160130973 

Guide vane


A gas turbine engine variable guide vane has a fixed portion on an upstream side, a movable flap on a downstream side and a transfer slot between a fixed portion trailing surface and a movable flap leading surface. The movable flap has opposite pressure and suction sides along a chord line between leading and trailing edges, and is rotatable about an axis along a movable flap span over a range of angular positions between open and closed.
Rolls-royce Plc


05/12/16
20160130972 

Bleed valve


A bleed valve for a gas turbine engine, the bleed valve comprising: an inlet coupled to an air source; and an outlet coupled to an air sink. The bleed valve also comprises a first stage of flow area modulation between the inlet and the outlet.
Rolls-royce Plc


05/12/16
20160130971 

Gas turbine electrical machine arrangement


A gas turbine engine comprising an electrical machine 30, 130, 200, 210, the electrical machine 30, 130, 200, 210 having an axis of rotation that is canted with respect to the main rotational axis of the gas turbine engine.. .
Rolls-royce Plc


05/12/16
20160130969 

Additive process for an abradable blade track used in a gas turbine engine


A gas turbine engine assembly comprising a rotor, a gas path component, and a carrier. The rotor includes a shaft adapted to rotate about an axis and a gas-path component that extends from the shaft for rotation therewith about the axis.
Rolls-royce Corporation


05/12/16
20160130966 

Sealing arrangement for a gas turbine engine


There is described a seal assembly for a gas turbine engine comprising: a first seal having a sealing passage which defines a flow path trajectory for leakage air, the first seal for partitioning a first pressure area to a lower pressure area; a second seal located along the line of the flow path trajectory of the first seal, the second seal for partitioning a second pressure area and the lower pressure area; a deflection member located between the first seal and second seal, and in the trajectory of the flow path from the first seal.. .
Rolls-royce Plc


05/12/16
20160130964 

Gas turbine engine flow control device


A flow control device for a gas turbine engine according to an exemplary aspect of the present disclosure includes, among other things, a seal body having a radially inner surface and a radially outer surface and at least one stand-up protruding from the radially outer surface and configured to seal an interrupted surface.. .
United Technologies Corporation


05/12/16
20160130963 

Gas turbine engine and seal assembly therefore


The present disclosure relates generally to a hydrostatic advanced low leakage seal having a shoe supported by at least two beams. An anti-vibration beam spacer is disposed in contact with two adjacent beams and operative to mitigate an externally induced vibratory response of the beams..
United Technologies Corporation


05/12/16
20160130961 

Gas turbine engine


A gas turbine engine includes in axial flow series a fan rotor, a series of outlet guide vanes for guiding flow from the fan rotor; and a bifurcation. The gas turbine engine further includes a substantially annular fluid passageway extending from fan to the bifurcation, the outlet guide vanes being positioned within the passageway.
Rolls-royce Plc


05/12/16
20160130959 

Gas turbine engine


A gas turbine engine comprising in axial flow series: a fan having a fan rotor; a series passages defined between adjacent outlet guide vanes for guiding flow from the fan; and a bifurcation. The gas turbine engine further comprises a substantially annular fluid passageway extending from the fan to the bifurcation, the outlet guide vanes being positioned within the passageway.
Rolls-royce Plc


05/12/16
20160130958 

Gas turbine engine structural guide vanes


A structural guide vane is disclosed. The structural guide vane may include a first root, a second root positioned radially outward from the first root and a truss extending between the first root and second root.
United Technologies Corporation


05/12/16
20160130950 

Gas turbine engine component with rib support


A component according to an exemplary aspect of the present disclosure includes, among other things, an airfoil that includes a first sidewall and a second sidewall joined together at a leading edge and a trailing edge and extending from a base to a tip. A plenum is defined inside the airfoil.
United Technologies Corporation


05/05/16
20160123596 

Combustor with axial staging for a gas turbine engine


A combustor a gas turbine engine includes an axial fuel injection system in communication with a combustion chamber, the axial fuel injection system operable to supply between about 10%-35% of a combustion airflow. A radial fuel injection system communicates with the combustion chamber downstream of the axial fuel injection system, where the radial fuel injection system is operable to supply between about 30%-60% of the combustion airflow.
United Technologies Corporation


05/05/16
20160123592 

Gas turbine engine combustor liner panel


A liner panel is provided for a combustor of a gas turbine engine. The liner panel includes a multiple of heat transfer augmentors.
United Technologies Corporation


05/05/16
20160123234 

High pressure compressor rotor thermal conditioning using discharge pressure air


A compressor for use in a gas turbine engine comprises a compressor rotor including blades and a disc, with a bore defined radially inwardly of the disc. A high pressure air tap includes a lower temperature tapped path and a higher temperature tapped path and a valve for selectively delivering one of the lower temperature tapped path and the higher temperature tapped path into the bore of the disc.
United Technologies Corporation


05/05/16
20160123233 

Spline ring for a fan drive gear flexible support


A gear assembly support for a gas turbine engine includes a spline ring configured to fit into a case of the gas turbine engine and a flex support. The flex support includes splines for engaging the spline ring and an inner portion attachable to a portion the gear assembly..
United Technologies Corporation


05/05/16
20160123229 

System and providing air-cooling, and related power generation systems


A cooling system for providing chilled air is disclosed, including a cooling coil; an evaporator and absorber contained within a vacuum chamber; and a desiccant that absorbs water vapor from the cooling process. The system also includes an external heat source for treating the desiccant; along with a regenerator to make the desiccant re-useable.
General Electric Company


05/05/16
20160123227 

Separator assembly for a gas turbine engine


A separator assembly for removing entrained particles from a fluid stream passing through a gas turbine engine includes a first particle separator for separating the fluid stream into a reduced-particle stream and a particle-laden stream, and emitting the particle-laden stream through a scavenge outlet. Another particle remover is fluidly coupled to the scavenge outlet to remove more particles from the air stream..
General Electric Company


05/05/16
20160123226 

Gas turbine using a cryogenic fuel and extracting work therefrom


There is disclosed a method of operating a gas turbine engine of a type having a compressor section, a combustor section, and a turbine section arranged in flow series. The method involves the steps of: providing a supply of cryogenic liquid fuel; vaporising the cryogenic liquid fuel to produce a gaseous fuel; expanding said gaseous fuel in at least one fuel turbine external to the engine's turbine section; and thereafter directing said expanded gaseous fuel into the engine's combustion section for combustion therein.
Rolls-royce Plc


05/05/16
20160123187 

Heatshield assembly with double lap joint for a gas turbine engine


A heat shield assembly for a gas turbine engine includes a first heat shield segment defined about an axis and a second heat shield segment defined about the axis. A double circumferential lap joint is defined between the first heat shield segment and the second heat shield segment..
United Technologies Corporation


05/05/16
20160123178 

Dual-mode plug nozzle


A variable geometry convergent-divergent nozzle for a gas turbine engine includes a centerbody extending rearward along a longitudinal axis of the engine which has a maximum diameter section. An inner shroud surrounds the centerbody and cooperates with the centerbody to define the throat of the nozzle.
General Electric Company


05/05/16
20160123176 

High pressure compressor rotor thermal conditioning using outer diameter gas extraction


A compressor for use in a gas turbine engine comprises a compressor rotor including blades and a disc, with a bore defined radially inwardly of the disc. A radially outer housing surrounds an outer diameter of the blades.
United Technologies Corporation


05/05/16
20160123171 

Turbine shroud with locating inserts


A turbine shroud for a gas turbine engine includes an annular metallic carrier, a blade track, and a cross-key connection formed between the annular metallic carrier and the ceramic blade track. The cross-key connection is formed between the annular metallic carrier and inserts included in the blade track..
Rolls-royce North American Technologies, Inc.


05/05/16
20160123169 

Methods and system for fluidic sealing in gas turbine engines


A sealing system for a rotatable element defining an axis of rotation includes a rotor blade including a shank and an angel wing extending axially from the shank. The sealing system also includes a stator vane positioned axially adjacent the rotor blade.
General Electric Company


05/05/16
20160123168 

Methods and system for fluidic sealing in gas turbine engines


A sealing system for a rotatable element defining an axis of rotation includes a rotor blade including a shank and an angel wing extending axially from the shank. The sealing system also includes a stator vane positioned axially adjacent the rotor blade.
General Electric Company


05/05/16
20160123166 

Turbine vanes with variable fillets


An airfoil extends between radially inner and radially outer platforms. The airfoil extends between a leading edge and a trailing edge, and merges into facing surfaces of the radially inner and outer platforms.
United Technologies Corporation


05/05/16
20160123165 

Variable area gas turbine engine component having movable spar and shell


A component according to an exemplary aspect of the present disclosure includes, among other things, a shell defining an interior, a spar extending into the interior and a first flange attached to the spar. The spar is configured to pivot to change a positioning of the shell..
United Technologies Corporation


05/05/16
20160123164 

Vane assembly for a gas turbine engine


A vane assembly for a gas turbine engine is disclosed in this paper. The vane assembly includes an inner platform, an outer platform, and a ceramic-containing airfoil.
Rolls-royce Corporation


05/05/16
20160123163 

Vane assembly for a gas turbine engine


A vane assembly for a gas turbine engine is disclosed in this paper. The vane assembly includes an inner platform, an outer platform, and a ceramic-containing airfoil.
Rolls-royce Corporation


05/05/16
20160123161 

Turbine rotor nut and bolt arrangement with improved fatigue resistance under centrifugal load


A gas turbine engine rotor (14), including: a rotor disk (16) comprising a bolt hole (82) there through and a counterbore (86); a bolt (18) configured to fit in the bolt hole and when so disposed to define an end (72) protruding beyond the counterbore; and a nut (84) configured to be disposed in the counterbore and to engage the protruding end. The counterbore is configured to permit limited eccentricity between the nut and the protruding end..
Siemens Energy, Inc.


05/05/16
20160123156 

Cooled component


A cooled gas turbine engine component comprises a wall having first and second surfaces. The second surface has a plurality of recesses and each recess has a planar upstream end surface arranged so that it hangs over the upstream end of the recess.
Rolls-royce Plc


05/05/16
20160123150 

Method of balancing a gas turbine engine rotor


A method of balancing a gas turbine engine rotor, including axisymmetrically removing an annular portion of the balancing flange exceeding that required to provide the unbalance correction, and creating the unbalance correction by non-axisymmetrically removing material from the balancing flange. In one embodiment, the configuration of a theoretical notch in the balancing flange that would create the unbalance correction is determined.
Pratt & Whitney Canada Corp.




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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