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Gas Turbine Engine patents



      
           
This page is updated frequently with new Gas Turbine Engine-related patent applications. Subscribe to the Gas Turbine Engine RSS feed to automatically get the update: related Gas RSS feeds. RSS updates for this page: Gas Turbine Engine RSS RSS


Turbine split ring retention and anti-rotation method

Turbine split ring retention and anti-rotation method

Turbine cylinder cavity heated recirculation system

Turbine cylinder cavity heated recirculation system

Turbine cylinder cavity heated recirculation system

Turbine engine shutdown temperature control system with nozzle injection for a gas turbine engine

Date/App# patent app List of recent Gas Turbine Engine-related patents
10/09/14
20140301861
 Airfoil having an erosion-resistant coating thereon patent thumbnailAirfoil having an erosion-resistant coating thereon
A compressor blade having an airfoil that comprises oppositely-disposed convex and concave surfaces, oppositely-disposed leading and trailing edges defining therebetween a chord length of the airfoil, a forward-most nose of the airfoil located at the leading edge and having a profile, a blade tip, and an erosion-resistant coating. The coating is present on the concave surface near the trailing edge, optionally present on the nose, optionally present on the convex surface, wherein the convex surface is free of the erosion resistant coating within at least 20% of the chord length from the nose.
10/09/14
20140301849
 Turbine split ring retention and anti-rotation method patent thumbnailTurbine split ring retention and anti-rotation method
A gas turbine engine disk split retainer ring system is provided and includes an apparatus and method for retaining a split ring in relation to a turbine cover plate or disk. Pegs are used to capture and retain a split retainer ring of the gas turbine rotor in relation to the cover plate.
10/09/14
20140301834
 Turbine cylinder cavity heated recirculation system patent thumbnailTurbine cylinder cavity heated recirculation system
A turbine engine heating system configured to heat compressor and turbine blade assemblies to eliminate turbine and compressor blade tip rub during warm restarts of gas turbine engines is disclosed. The turbine engine heating system may include a heating air extraction system configured to withdraw air from the turbine engine and to pass that air thru a heating element configured to increase a temperature of the air supplied by the heating air extraction system.
10/09/14
20140301820
 Turbine engine shutdown temperature control system with nozzle injection for a gas turbine engine patent thumbnailTurbine engine shutdown temperature control system with nozzle injection for a gas turbine engine
A turbine engine shutdown temperature control system configured to limit thermal gradients from being created within an outer casing surrounding a turbine blade assembly during shutdown of a gas turbine engine is disclosed. By reducing thermal gradients caused by hot air buoyancy within the mid-region cavities in the outer casing, arched and sway-back bending of the outer casing is prevented, thereby reducing the likelihood of blade tip rub, and potential blade damage, during a warm restart of the gas turbine engine.
10/09/14
20140298821
 Gas turbine engine provided with heat exchanger, and method for starting same patent thumbnailGas turbine engine provided with heat exchanger, and method for starting same
A method of starting a gas turbine engine includes a primary warming step of warming a heat exchanger (6) by means of a compressed gas (g1) while with the use of an inverter motor (im) the rotation speed of the engine is maintained at a partial rotation speed, a secondary warming step of warming the heat exchanger (6) by activating a main combustor (2) to gradually increase the temperature of an exhaust gas (g3) while with the use of the inverter motor (im) the rotation speed is maintained at the partial rotation speed, and a speed increasing step of increasing the rotation speed to the rated rotation speed with the use of the inverter motor (im) while the fuel burning amount of the main combustor (2) is increased.. .
10/09/14
20140298820
 Gas turbine engine and method for starting same patent thumbnailGas turbine engine and method for starting same
A starting method for a gas turbine engine includes a primary warming step of warming up the gas turbine engine while a constant primary warm-up rotation speed is maintained by an inverter motor and a secondary warming step of warming up the gas turbine engine while a constant secondary warm-up rotation speed is maintained by further increasing the speed of the inverter motor. The primary warming step terminates when an electric power required by the inverter motor attains a predetermined preset electric power value.
10/09/14
20140298818
 Control method and control device for lean fuel intake gas turbine patent thumbnailControl method and control device for lean fuel intake gas turbine
A method and a device for controlling a lean fuel intake gas turbine engine, which can stably maintain operation of the gas turbine engine by preventing misfire and burnout of a catalytic combustor even when a catalyst in the combustor is deteriorated. A difference between measured temperatures of an inlet and an outlet of the combustor with respect to a methane concentration in an intake gas that is to be taken into the lean fuel intake gas turbine engine is compared with reference temperature difference data that is data indicating difference between temperatures of the inlet and the outlet of the combustor including a catalyst in its initial state to be a reference, and at least one of the inlet temperature and the outlet temperature of the combustor is controlled based on a difference between the measured temperature difference and the reference temperature difference data..
10/09/14
20140298788
 Gas turbine engine including pneumatic actuator system patent thumbnailGas turbine engine including pneumatic actuator system
A gas turbine engine that includes a compressor section and a pneumatic actuator system is delivered. The pneumatic actuator system includes a bleed air duct that receives bleed air from the compressor section and delivers the bleed air through an accumulator and to an actuator.
10/02/14
20140297155
 Aircraft power outtake management patent thumbnailAircraft power outtake management
A system and method for controlling the operation of a gas turbine engine supplying power to an aircraft. The engine is controlled according to a reading of an amount of power drawn from the supplied power.
10/02/14
20140294598
 Turbine blade patent thumbnailTurbine blade
The cooling effectiveness of a turbine blade that a gas turbine engine or the like is provided with is further increased by providing a convex portion that is arranged in the inner portion of a cooling air hole and that is provided projecting out from the inner wall surface of the cooling air hole.. .
10/02/14
20140294589
Asymmetrically slotted rotor for a gas turbine engine
A spool for a gas turbine engine includes at least one rotor disk defined along an axis of rotation and at least one rotor ring defined along the axis of rotation, with the rotor ring being in contact with the rotor disk. The rotor disk and rotor ring are contoured to define a smooth rotor stack load path..
10/02/14
20140294581
Gas turbine engine access panel
An integrated access panel is disclosed that can be used to assist in adjusting a component like a fan blade of a turbofan engine. In one form the integrated access panel is hinged at one end such that the panel remains attached during adjustment of the fan blade.
10/02/14
20140294572
Wall section for the working gas annulus of a gas turbine engine
A seal segment is provided for a shroud ring of a rotor of a gas turbine engine. The seal segment is positioned, in use, radially adjacent the rotor.
10/02/14
20140294571
Seal segment
A seal segment is provided for a shroud ring of a rotor of a gas turbine engine. The seal segment is positioned, in use, radially adjacent the rotor.
10/02/14
20140294564
Auxiliary power units and other turbomachines having ported impeller shroud recirculation systems
Embodiments of a turbomachine, such as a gas turbine engine, are provided. In one embodiment, the turbomachine includes an impeller, a main intake plenum in fluid communication with the inlet of the impeller, and an impeller shroud recirculation system.
10/02/14
20140294562
Strut for a gas turbine engine
The strut is for use in a gas turbine engine has body, typically having an airfoil shape, having a leading edge and a trailing edge. The leading edge has at least one gas inlet in direct fluid communication with at least one outlet located in the trailing edge through which gas may be redirected from the leading edge to the trailing edge through the strut for injection back into a wake region downstream of the strut..
10/02/14
20140294559
Multiple mode gas turbine engine gas fuel system with integrated control
A method for operating a gas turbine engine is disclosed. The method includes determining whether the gas turbine engine fuel system is in a steady state mode or a transient mode.
10/02/14
20140291993
Method for operating lean fuel intake gas turbine engine, and gas turbine power generation device
A method for stably operating a lean fuel intake gas turbine engine by controlling the rotation speed of the lean fuel intake gas turbine engine for which it is difficult to control the rotation speed by controlling a fuel flow rate, is provided. In a method for operating a lean fuel intake gas turbine engine (gt) configured to use, as a fuel, a combustible component contained in a low-concentration methane gas to drive a power generator, a power converter (17) is provided between an external electric power system (19) and the power generator (11), and a rotation speed of the power generator (11) is controlled by the power converter (17), to control a rotation speed of the gas turbine engine (gt)..
10/02/14
20140290272
Gas turbine engine cooling arrangement
A gas turbine engine comprises a compressor, a combustion chamber, an outer casing, an inner casing and a cooling arrangement. The outer casing surrounds the compressor and the combustion chamber and the combustion chamber has turbine nozzle guide vanes.
10/02/14
20140290271
Mounting arrangement
A rigid electrical raft is provided to a gas turbine engine via a fusible mount arrangement. The rigid electrical raft may be a part of an electrical system of the gas turbine engine, for example a part of the electrical harness.
10/02/14
20140290269
Duct blocker seal assembly for a gas turbine engine
A seal system for a gas turbine engine includes a cover plate with a radial flange; a seal carrier adjacent the cover plate; an outer compliant seal supported by the seal carrier; an inner compliant seal supported by the seal carrier, the inner compliant seal engaged with the radial flange; and a spring between the cover plate and the seal carrier.. .
10/02/14
20140290268
Gas turbine engine geared architecture axial retention arrangement
A gas turbine engine includes a fan, an engine static structure, a geared architecture to drive the fan and supported relative to the static structure, a fan drive turbine to drive the geared architecture, a first member secured to the geared architecture, and a second member secured to the engine static structure and configured to cooperate with the first member to limit movement of the geared architecture relative to the static structure. A fan drive gear system and method are also disclosed..
10/02/14
20140290266
Fuel and actuation system for gas turbine engine
A fuel system for an aircraft comprises a boost pump, a main fuel pump and a motive pump. The boost pump receives fuel from a storage unit.
10/02/14
20140290265
Gas turbine engine with transmission
A multi spool gas turbine engine with a differential having a selectively rotatable member which rotational speed determines a variable ratio between rotational speeds of driven and driving members of the differential. The driven member is engaged to the first spool and a rotatable shaft independent of the other spools (e.g.
10/02/14
20140290262
Low flow correction for gas turbine engine fuel valve characteristics
A method for controlling a gas turbine engine fuel control valve during low flow conditions includes positioning the fuel control valve in an operating position. The method also includes determining a fuel control valve flow sensor flow rate while in the operating position and determining a corrected effective flow area (“cda”) of the fuel control valve.
10/02/14
20140290261
Compensation for gas turbine engine fuel valve characteristics
A method for operating a gas turbine engine fuel system with a fuel control valve is disclosed. The method includes metering fuel through the fuel control valve with an effective flow area versus command data set.
10/02/14
20140290254
Cyclonic dirt separating turbine accelerator
A dirt separator assembly for a gas turbine engine comprises a cyclonic accelerator in flow communication with compressor discharge air, the accelerator having a plurality of passages, each passage having an inlet, an outlet and at least one vent located in the passage, a plurality of turning vanes disposed along each of the passages, the passage turning tangentially between the inlet and the outlet, the accelerator passages decreasing from a first cross-sectional area to a second cross-sectional area and said turning vanes inducing helical swirl of compressed cooling air, and, at least one vent located in the accelerator passages for expelling dust separated from the swirling compressed cooling air.. .
10/02/14
20140290252
Gas turbine engine provided with scroll
A gas turbine engine having high reliability is provided by suppressing occurrence of thermal stress between a scroll and a support member thereof. A gas turbine engine equipped with a combustor of a single-can type includes a scroll to guide a combustion gas fed from a combustor to a turbine while swirling the combustion gas about a rotation axis, a flange member to support the scroll with respect to the gas turbine engine from an inner peripheral side of the scroll, and a coupling member of an annular shape to couple the scroll and the flange member with each other.
10/02/14
20140290213
Duct blocker seal assembly for a gas turbine engine
A seal system for a gas turbine engine includes an annular seal carrier and an annular compliant seal mounted around the annular seal carrier, the compliant seal includes a multiple of legs in cross-section.. .
09/25/14
20140286782
Turbine blade staking pin
A staking pin for a gas turbine engine is disclosed. The staking pin may include a solid portion extending part of a length of the staking pin, and a hollow portion extending an additional part of the length of the staking pin.
09/25/14
20140286781
Integral fan blade wear pad and platform seal
A fan section for a gas turbine engine includes a fan hub having a slot. A platform is supported by the fan hub.
09/25/14
20140286773
Gas turbine engine
The gas turbine engine (s1) includes: turbine blades (7b); and a cooling air supply unit (11) to supply cooling air to the turbine blades (7b). A flow path surface (31) is formed so as to be positioned in an upstream side of the turbine blades (7b) and so as to be connected to a base surface (32) in which the turbine blades (7b) are provided.
09/25/14
20140286771
Cooling passages for turbine buckets of a gas turbine engine
The present application and the resultant patent provide a turbine bucket for a gas turbine engine. The turbine bucket may include a platform, an airfoil extending radially from the platform, and a number of cooling passages defined within the airfoil and near an outer surface of the airfoil.
09/25/14
20140286765
Composite aerofoil vane
A composite aerofoil vane for a gas turbine engine extends in use in a generally radial direction across an axially- and circumferentially-extending annular duct. The vane comprises a plurality of first reinforcing fibres extending in a generally radial direction and a plurality of second reinforcing fibres extending in generally axial and circumferential directions.
09/25/14
20140286763
Gas turbine outer case active ambient cooling including air exhaust into sub-ambient cavity
A gas turbine engine including an outer case and an exhaust gas passage defined within the outer case for conducting an exhaust gas flow from a turbine section of the gas turbine engine. A cooling channel is associated with an outer surface of the outer case, the cooling channel having a channel inlet and a channel outlet.
09/25/14
20140286760
Seal assembly including grooves in an inner shroud in a gas turbine engine
A seal assembly between a disc cavity and a hot gas path in a gas turbine engine includes a rotating blade assembly having a plurality of blades that rotate with a turbine rotor during operation of the engine, and a stationary vane assembly having a plurality of vanes and an inner shroud. The inner shroud includes a radially outwardly facing first surface, a radially inwardly facing second surface, and a plurality of grooves extending into the second surface.
09/25/14
20140286751
Cooled turbine ring segments with intermediate pressure plenums
A ring segment for a gas turbine engine includes a panel and a cooling system. The cooling system is provided within the panel and includes an elongated intermediate plenum extending parallel to leading and trailing edges of the ring segment, and is located radially between an inner side of the panel and a hook structure extending from an outer side of the panel.
09/25/14
20140286748
Fan containment case with thermally conforming liner
A fan section of a gas turbine engine includes a fan containment case assembly includes an outer case of an aluminum alloy. The outer case extends circumferentially around an axial centerline.
09/25/14
20140286746
Compressor shroud reverse bleed holes
A gas turbine engine compressor includes a rotor defining a central axis of rotation and a plurality of blades which project into an annular compressor gas flow passage, and a shroud circumferentially surrounding the rotor and having a radially inner surface adjacent to the blade tips. Bleed holes extend through the shroud adjacent the blade tips, each of the bleed holes having an inlet end disposed in the shroud radially inner surface and an outlet end disposed in a shroud radially outer surface.
09/25/14
20140284395
Gas turbine exhaust noise reduction
A gas turbine jet noise reduction apparatus including a variable geometry gas turbine engine nozzle comprising a circumferentially distributed array of nozzle flap panels supported for alternate collective splaying and gathering motion, with the collective splaying motion of the flap panels being from a narrow position defining a minimum cross-sectional area at a nozzle exit plane, to a wide position defining a maximum cross-sectional area at the nozzle exit plane. A plurality of nozzle seal panels is supported in a circumferentially distributed array within the array of nozzle flap panels.
09/25/14
20140283922
Spring assemblies for use in gas turbine engines and methods for their manufacture
In accordance with an exemplary embodiment, a method for manufacturing a bypass valve of a turbine engine control system is described. The bypass valve includes a proportional valve and an integrator valve and the integrator valve includes an integrator spring assembly.
09/25/14
20140283525
Two-branch mixing passage and method to control combustor pulsations
A gas turbine engine combustion system including a mixing duct that separates into at least two branch passages for the delivery of a fuel and working fluid to distinct locations within a combustion chamber. The residence time for the fuel and working fluid within each of the two branch passages is distinct..
09/25/14
20140283523
System and method for controlled fuel blending in gas turbines
A system includes a gas turbine engine having a combustor, and a fuel blending system. The fuel blending system further includes a first fuel supply configured to supply a first fuel, a second fuel supply configured to supply a second fuel, a first fuel circuit, a second fuel circuit, and a controller.
09/18/14
20140278200
Temperature measurement in a gas turbine engine combustor
A method and system for determining a temperature of a working gas passing through a passage to a turbine section of a gas turbine engine. The method includes identifying an acoustic frequency at a first location in the engine upstream from the turbine section, and using the acoustic frequency for determining a first temperature value at the first location that is directly proportional to the acoustic frequency and a calculated constant value.
09/18/14
20140277991
Prognostic health management approaches for propulsion control systems
A real-time gas turbine management system includes a controller system coupled to a gas turbine engine. The controller system is configured to control demand on a first and second component of a gas turbine engine.
09/18/14
20140277790
Ensuring non-excessive variation of gradients in auto-tuning a gas turbine engine
Methods are provided for ensuring non-excessive variation of a gradient of an applied split bias versus firing temperature of a gas turbine engine. It is determined that an incremental split bias step is to be taken, and a current firing temperature of the gas turbine engine is identified on a graph.
09/18/14
20140277789
Dynamic tuning of a gas turbine engine to detect and prevent lean blowout
A method for tuning a combustor of a gas turbine engine based on one or more monitored operating conditions is provided. One or more operating conditions of the gas turbine engine are monitored.
09/18/14
20140274420
Spline lubrication system
A gearbox assembly for use in a gas turbine engine includes a gearbox housing and first and second shafts. The first shaft is rotatably mounted in the gearbox housing.
09/18/14
20140273757
Drag finishing system, method and fixture for gas turbine engine airfoils
A system, fixture and method for media finishing a cluster of airfoils are provided. The fixture may include a base having a first end and a second end, a receptacle disposed on the base and configured to receive the stator cluster, and at least one mock airfoil disposed at each of the first and second ends of the base in alignment with the airfoils of the cluster..
09/18/14
20140272431
Layered deposition for reactive joining of composites
A method including applying layers of multiple constituents where the constituents are capable of producing a non-equilibrium condition on the contacting surfaces of a ceramic matrix composite component and a gas turbine engine component where one outer coating includes a first constituent and the other outer coating includes a second constituent; forming a component assembly with the ceramic matrix composite component coupled to the gas turbine engine component with contact between the outer coatings; adding an energy to facilitate an equilibrium reaction between the first constituent of the first outer coating and the second constituent of the second outer coating; and as a result of adding the energy, forming a bond structure in the component assembly with a product of the equilibrium reaction where the bond structure affixes the ceramic matrix composite component to the gas turbine engine component between the first constituent and the second constituent.. .
09/18/14
20140272274
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.
09/18/14
20140272248
Ceramic matrix composite repair by reactive processing and mechanical interlocking
A method for modifying a ceramic matrix component is disclosed including identifying a non-conforming region of a composite component capable of operating in a gas turbine engine; removing at least a portion of the non-conforming region to create an exposed surface of the composite component; preparing a preform in response to the removing at least a portion of the non-conforming region; applying a reactive constituent surface region to at least one of the exposed surface of the composite component and the preform, the reactive constituent surface region being capable of producing a non-equilibrium condition; positioning the preform to provide a contact region between the exposed surface of the composite component and the preform proximate the reactive constituent surface region; and reacting the reactive constituent surface region in an equilibrium reaction at the contact region to form a bond structure between the exposed surface of the composite component and the preform.. .
09/18/14
20140272197
Directed vapor deposition of environmental barrier coatings
In some examples, a method may include directing an electron beam at a coating source to create a vapor plume, wherein the coating source comprises alumina and at least one rare earth oxide. The method also may include transporting the vapor plume using a gas stream provided adjacent to the coating source to within an internal cavity defined by a surface of a substrate of a gas turbine engine blade, vane, blade track, or combustor liner, and wherein the substrate comprises at least one of a silicon-containing ceramic or a ceramic matrix composite.
09/18/14
20140272166
Coating system for improved leading edge erosion protection
A gas turbine engine includes airfoils. At least a portion of the airfoils are coated with a coating that provides for erosion and corrosion protection for the portion of the airfoils..
09/18/14
20140271227
Manufacture of hollow aerofoil
A method of manufacturing a hollow aerofoil component for a gas turbine engine includes using a capping panel to cover a pocket in a pocketed aerofoil body. During manufacture, the outer surface of the capping panel is located relative to the pocketed aerofoil body.
09/18/14
20140271207
Fan blade
A rotor blade assembly for a gas turbine engine includes two aerofoil members joined together at their roots by a blade assembly attachment web. The rotor blade assembly is made from a composite material, for example an organic fibre composite material.
09/18/14
20140271206
Turbine blade with a pin seal slot
A gas turbine engine turbine disk assembly includes a turbine disk, turbine blades, and pin seals. Each turbine blade includes a platform with a pressure side seal slot extending into a pressure side of the platform and a suction side seal slot extending into a suction side of the platform.
09/18/14
20140271205
Turbine blade pin seal
A gas turbine engine turbine disk assembly includes a turbine disk, turbine blades, and pin seals. Each turbine blade includes a platform with a pressure side seal slot extending into a pressure side of the platform and a suction side seal slot extending into a suction side of the platform.
09/18/14
20140271178
Fan blades for gas turbine engines with reduced stress concentration at leading edge
A light weight fan blade for a gas turbine engine is disclosed. The disclosed fan blade has an increased chord length at a transition section between the inner edge or single tooth attachment portion of the fan blade that connects to the rotor disk and the airfoil.
09/18/14
20140271173
Centrifugal compressor with axial impeller exit
A gas turbine engine includes a centrifugal compressor having an improved impeller structure. The impeller structure includes a near axial discharge configuration thus reducing the overall size of the envelop surrounding the compressor assembly.
09/18/14
20140271168
Radial diffuser exhaust system
The present application provides a radial diffuser exhaust system for use with a gas turbine engine. The radial diffuser exhaust system may include a radial diffuser positioned within an asymmetric exhaust collector.
09/18/14
20140271161
Ceramic matrix composite
A novel ceramic matrix composite is disclosed for forming components that are operable in high temperature environments such those in gas turbine engines and the like. The ceramic matrix composite can include at least one layer of non-crimped fibers positioned substantially parallel to one another.
09/18/14
20140271158
Compressor stator
Compressor stators (22) for gas turbine engines (10) are disclosed. An exemplary compressor stator (22) comprises a circumferential array of stator vanes (28) and a shroud (24, 26) for supporting the stator vanes (28).
09/18/14
20140271157
Fan containment system
A fan containment system arranged to be fitted around an array of radially extending fan blades mounted on a hub in an axial gas turbine engine. Each fan blade has a respective tip.
09/18/14
20140271152
Turbine engine temperature control system with heating element for a gas turbine engine
A turbine engine temperature control system configured to limit thermal gradients from being created within an outer casing surrounding a turbine airfoil assembly during shutdown of a gas turbine engine and for preheating an engine during a cold startup is disclosed. By reducing thermal gradients caused by hot air buoyancy within the mid-region cavities in the outer casing, arched and sway-back bending of the outer casing is prevented, thereby reducing the likelihood of blade tip rub, and potential blade damage, during a warm restart.
09/18/14
20140271149
Gas turbine engine, machine and self-aligning foil bearing system
One embodiment of the present invention is a unique gas turbine engine. Another embodiment is a unique machine.
09/18/14
20140271148
Engine casing assembly
A gas turbine engine casing assembly has a first casing element which is located radially outward of one or more rotating aerofoil elements of the gas turbine engine. The first casing element is radially enclosed by a track element, a septum layer, a second casing element and a fan case.
09/18/14
20140271145
Turbine blade track assembly
A gas turbine engine is disclosed with a turbine section having at least one turbine rotor with a plurality of turbine blades, a plurality of blade tracks positioned circumferentially around the turbine blades, at least one dovetail shaped connecting member extending radially outward from each blade track, and a hanger connected to a structural member of the gas turbine engine and configured to releasably couple with the at least one dovetail shaped connecting member of a corresponding blade track.. .
09/18/14
20140271144
Turbine shroud
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.
09/18/14
20140271131
Trenched cooling hole arrangement for a ceramic matrix composite vane
One aspect of the present application provides an apparatus comprising a shape operable as a gas turbine engine component, an internal cavity within the shape including a radius, a trench on an external surface of the shape including a rear face tangential to an arc centered on the radius of the internal cavity, and a cooling hole extending from the internal cavity and exiting to the trench through the rear face of the trench wherein a cooling fluid introduced to the internal cavity flows through the cooling hole and into the trench during operation of the gas turbine engine component.. .
09/18/14
20140271121
Gas turbine engine architecture with intercooled twin centrifugal compressor
A gas turbine engine includes an intercooled twin centrifugal compressor. A pipe diffuser extends from the intercooled twin centrifugal compressor into an airflow path..
09/18/14
20140271118
Gas turbine engine lubrication system
A lubrication system for a gas turbine engine is disclosed. The lubrication system is configured to provide pressurized air and lubricant to a bearing sump of the gas turbine engine to cool and lubricate a bearing included in the bearing sump..
09/18/14
20140271116
Heat exchanger integrated with a gas turbine engine and adaptive flow control
One embodiment of an engine may include an enclosure surrounding an engine having an engine centerline, and the enclosure defining a passage for a cold-side airflow. The engine may also include one or more contiguous heat exchangers having a cold side inlet surface receiving a cold-side airflow.
09/18/14
20140271112
Low noise turbine for geared gas turbine engine
A gas turbine engine according to an exemplary aspect of the present disclosure includes, among other things, a turbine section including a fan drive turbine, a compressor section driven by the turbine section, a geared architecture driven by the fan drive turbine, and a fan driven by the fan drive turbine via the geared architecture. At least one stage of the turbine section includes an array of rotatable blades and an array of vanes.
09/18/14
20140271111
Method and apparatus to improve heat transfer in turbine sections of gas turbines
A gas turbine engine system having a combustion section and a turbine section is provided. The turbine section includes at least one turbine stage having a plurality of turbine blades coupled to a rotor and an inner casing circumferentially disposed about the plurality of turbine blades.
09/18/14
20140271109
Axial compressor and method for controlling stage-to-stage leakage therein
The present application and the resultant patent provide an axial compressor for a gas turbine engine. The compressor may include a rotor disk positioned along an axis of the compressor.
09/18/14
20140271108
Compressor bleed self-recirculating system
A compressor for a gas turbine engine having a bleed air recirculation system includes a plurality of bleed holes extending through the shroud at a first axial location thereon substantially adjacent the blade tips. The bleed holes have a closed outer perimeter along their complete length.
09/18/14
20140271105
Turbine shroud segment sealing
A segmented shroud ring surrounds a circumferential array of blades of a gas turbine engine rotor. The shroud ring has a plurality of shroud segments disposed circumferentially one adjacent to another.
09/18/14
20140271104
Turbine shroud cooling system
The present application provides a turbine shroud cooling system for a gas turbine engine. The turbine shroud cooling system may include a number of variable area cooling shrouds with tuning pins and a number of fixed area cooling shrouds with anti-rotation pins.
09/18/14
20140271103
Vane carrier thermal management arrangement and method for clearance control
A thermal management arrangement (110) in a gas turbine engine (60), including: a conduit-arrangement (62) providing fluid communication between a compressor section (156) and: a relatively thermally responsive portion (52) of a turbine vane carrier (10); and a relatively thermally unresponsive portion (48) of a first turbine vane carrier. The conduit-arrangement includes: a general cooling flow outlet (122) disposed proximate the relatively thermally responsive portion of the turbine vane carrier and configured to discharge a general cooling flow (124); and an impingement flow outlet (118) disposed proximate the relatively thermally unresponsive portion and configured to discharge an impingement flow (120).


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