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Gas Turbine patents



      
           
This page is updated frequently with new Gas Turbine-related patent applications.



Date/App# patent app List of recent Gas Turbine-related patents
01/28/16
20160028236 
 Systems and methods for generating energy using a hydrogen cycle patent thumbnailSystems and methods for generating energy using a hydrogen cycle
Systems and methods for continuously generating electric power using a renewable energy power source to continuously generate electrical energy are disclosed. An illustrative embodiment includes transmitting electrical power from the renewable energy power source to an electrolyzer to produce hydrogen gas, storing the hydrogen gas in a storage facility until production of power from the renewable energy power source drops below a predetermined threshold, and activating a secondary power generation system that converts the stored hydrogen to electrical energy.
Bunker Energy Partners, Llc


01/28/16
20160026739 
 Systems and methods for gas turbine operational impact modeling using statistical and physics-based methodologies patent thumbnailSystems and methods for gas turbine operational impact modeling using statistical and physics-based methodologies
Systems and methods for gas turbine operational impact modeling using statistical and physics-based methodologies are disclosed. According to one embodiment of the disclosure, a method can include receiving, by one or more processors, operational conditions data associated with a hardware component of a gas turbine; based at least in part on the operational variation data, applying, by one or more processors, statistical methods to establish an operational profile of the hardware component; receiving, by one or more processors, operating parameters and operational conditions data associated with the hardware component; based at least in part on the operating parameters and the operational conditions data, applying, by one or more processors, physics-based methods to establish an operational impact factor of the hardware component; and based at least in part on the operational profile and the operational impact factor determining, by one or more processors, a probability of a failure of the hardware component within a time period..

01/28/16
20160025346 
 Gas turbine combustor patent thumbnailGas turbine combustor
A combustor is capable of ignition and flame propagation at low fuel concentrations for gas or liquid fuel. Combustors are disposed annularly along an outer peripheral portion of a casing of a turbine.
Mitsubishi Hitachi Power Systems, Ltd.


01/28/16
20160025345 
 Liner element for a combustor patent thumbnailLiner element for a combustor
There is disclosed a liner element in the form of an impingement/effusion tile for a gas turbine combustor having a structural wall. The liner element has a unitary construction defining a cooling side and combustion side, and a plurality of effusion holes extending between a cooling side surface of the element and a combustion side surface of the element.
Rolls-royce Plc


01/28/16
20160025342 
 Active cooling of grommet bosses for a combustor panel of a gas turbine engine patent thumbnailActive cooling of grommet bosses for a combustor panel of a gas turbine engine
A liner assembly for a combustor of a gas turbine engine according to one disclosed non-limiting embodiment of the present disclosure includes a grommet with a multiple of grommet cooling passages.. .
United Technologies Corporation


01/28/16
20160025331 
 Condensate preheater for waste heat steam generator patent thumbnailCondensate preheater for waste heat steam generator
A condensate preheater for a waste-heat steam generator, including condensate preheater heating surfaces, around which exhaust gas of a gas turbine flows in operation in order to heat up water flowing in the condensate preheater heating surfaces, wherein a respective heat transfer coefficient of the condensate preheater heating surfaces is selected such that a surface temperature of the condensate preheater heating surfaces is above an exhaust gas dew point in operation, wherein the condensate preheater has a condensate preheater inlet and a condensate preheater outlet and the heat transfer coefficient at the condensate preheater inlet is reduced relative to the heat transfer coefficient at the condensate preheater outlet, is provided.. .
Siemens Aktiengesellschaft


01/28/16
20160025221 
 Aircraft gas turbine with a seal for sealing an igniter plug on the combustion chamber wall of a gas turbine patent thumbnailAircraft gas turbine with a seal for sealing an igniter plug on the combustion chamber wall of a gas turbine
A sealing arrangement of an igniter plug of a combustion chamber of a gas turbine, with an igniter plug passing through a recess of a combustion chamber wall, with at least one sealing ring through which the igniter plug projects and which is in sealing contact with an edge area of the recess facing away from the combustion chamber interior, wherein the sealing ring is designed in the form of a flat, annular and flexible disk.. .
Rolls-royce Deutschland Ltd & Co Kg


01/28/16
20160025038 
 Pivot door thrust reverser patent thumbnailPivot door thrust reverser
A geared turbofan engine includes a fan, a low pressure turbine, a geared architecture, and a nacelle. The fan and low pressure turbine are capable of rotation about an axial centerline of the gas turbine engine.
United Technologies Corporation


01/28/16
20160025037 
 Thrust reverser unit patent thumbnailThrust reverser unit
A thrust reverser unit (tru) 100 for a gas turbine engine 10 is provided that has first and second cascade elements 110, 120. In a stowed configuration, both the first and second cascade elements, and the operating mechanism, are located inside the nacelle 40, meaning that the tru has no detrimental impact on the flow through the bypass duct 22.
Rolls-royce Deutschland Ltd & Co Kg


01/28/16
20160025009 
 Method of supplying fuel to an internal fuel manifold patent thumbnailMethod of supplying fuel to an internal fuel manifold
The described method of supplying fuel to an internal fuel manifold of a bypass gas turbine engine includes directing a fuel flow through a fuel fairing having an outer surface exposed to a cool bypass airflow, directing the fuel flow in the fuel fairing through a heat exchanging structure on the outer surface of the fuel fairing to cool the fuel flow being below a coking temperature of the fuel, and then feeding the cooled fuel flow from the fuel fairing to the internal fuel manifold.. .
Pratt & Whitney Canada Corp.


01/28/16
20160025006 

Self-cooled orifice structure


A self-cooled orifice structure, that may be for a combustor of a gas turbine engine includes a hot side panel, a cold side panel spaced from the hot side panel, and a continuous first wall extending axially between the hot and cold side panels and spaced radially outward from a centerline. The structure may further include a first plurality of helical vanes projecting laterally, radially, inward from the first wall for flowing cooling air in a spiraling fashion through the cold side panel, then through the hot side panel..
United Technologies Corporation


01/28/16
20160025005 

Bifurcated air inlet housing for a miniature gas turbine engine


A gas turbine engine has a nose cone with a nose cone upstream end and an inlet housing including a plurality of separate flow paths at a housing upstream end which is downstream of the nose cone upstream end. The inlet housing includes a mixing portion downstream of the housing upstream end which mixes airflow from the separate flow paths, such that the airflow is generally around 360 degrees of a rotational axis of the gas turbine engine.
United Technologies Corporation


01/28/16
20160025004 

Low noise turbine for geared turbofan engine


A gas turbine engine comprises a fan, a compressor section including a compressor having a low pressure portion and a high pressure portion, a combustor section, and a turbine having a downstream portion. A gear reduction effects a reduction in the speed of the fan relative to an input speed to the fan.
Mtu Aero Engines Ag


01/28/16
20160024972 

Nosecone support


A example nosecone support of a gas turbine engine includes, among other things, a spar to extend radially from a nosecone. The spar is configured to attach to a case to support the nosecone..
United Technologies Corporation


01/28/16
20160024970 

Compressor assembly for gas turbine


A compressor assembly, and more in general relates to a compressor for a gas turbine providing a solution that teaches to locate within a cavity formed by the outer casing of the compressor and the inner vane carrier a separator element, or membrane, such to divide the cavity into two sub-cavities. This advantageously results in a more flexible design with respect to the positioning of the flange blow-off extractor and to the cavity sizing, as the flange position is not necessarily the boundary for the flow anymore as it would be without the separator element..
Alstom Technology Ltd


01/28/16
20160024968 

Air oil cooler airflow augmentation system


An oil supply system for a gas turbine engine has a lubricant pump delivering lubricant to an outlet line. The outlet line is split into at least a hot line and into a cool line, with the hot line directed primarily to locations associated with an engine that are not intended to receive cooler lubricant, and the cool line directed through one or more heat exchangers at which lubricant is cooled.
United Technologies Corporation


01/28/16
20160024966 

Method of manufacturing gas turbine engine element having at least one elongated opening


A method of manufacturing a gas turbine engine element, for example a shroud segment. An insert has at least one elongated feature received in a mold cavity.
Pratt & Whitney Canada Corp.


01/28/16
20160024965 

Geared architecture turbofan engine thermal management system and method


A method of sizing a heat exchanger for a geared architecture gas turbine engine includes sizing a minimum frontal area of at least one heat exchanger located in communication with a fan bypass airflow such that a ratio of waste heat area to horsepower generation characteristic area is between 1.6 to 8.75.. .
United Technologies Corporation


01/28/16
20160024964 

Gas turbine engine with air-oil cooler oil tank


A thermal management system according to one disclosed non-limiting embodiment of the present disclosure includes an at least partially annular oil tank; and a fan airflow diverter upstream of the cooling fins.. .
United Technologies Corporation


01/28/16
20160024962 

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


01/28/16
20160024960 

Gas turbine and operating the gas turbine


A gas turbine includes an intake tract and a compressor having a compressor flow channel. The compressor further includes an inlet guide vane row positioned in the compressor flow channel having inlet guide vanes that can be adjusted.
Siemens Aktiengesellschaft


01/28/16
20160024958 

Gas turbine engine with low stage count low pressure turbine


A gas turbine engine according to an example of the present disclosure includes, among other things, a fan section, a low spool that includes a low pressure compressor section, the low pressure compressor section including three (3) or more stages, and a high spool including a high pressure compressor section. The high pressure compressor section includes between eight to thirteen (8-13) stages.
United Technologies Corporation


01/28/16
20160024957 

Gas turbine engine with low stage count low pressure turbine


A gas turbine engine according to an example of the present disclosure includes, among other things, a fan section, a first compressor section including three (3) or more stages, a second compressor section including between eight (8) and thirteen (13) stages, and a first turbine section operable for driving the first compressor section, the first turbine section including between three (3) and six (6) stages, a second turbine section operable for driving the second compressor section, and a gear train defined along an engine centerline axis. One of the first turbine section and the second turbine section is operable to drive the fan section through the gear train..
United Technologies Corporation


01/28/16
20160024956 

Floating blade outer air seal assembly for gas turbine engine


A blade outer air seal (boas) assembly for an engine case of a gas turbine engine includes a multiple of supported air seal segments and a multiple of floating air seal segments circumferentially alternate with the multiple of supported air seal segments.. .
United Technologies Corporation


01/28/16
20160024949 

Mid-turbine frame and gas turbine engine including same


A mid-turbine frame for a gas turbine engine ducts gases between a high pressure turbine and a low pressure turbine. The mid-turbine frame may include an outer flowpath ring, an inner flowpath ring, and a plurality of vanes extending therebetween.
United Technologies Corporation


01/28/16
20160024946 

Rotor blade dovetail with round bearing surfaces


A blade for use in a gas turbine engine, the blade having an airfoil portion and a dovetail root portion, wherein the dovetail root portion is dimensioned and configured to enable the blade to rotate within a shaped slot formed in a supporting hub of the engine about a center of rotation that extends parallel to a central axis of the hub in response to an impact force on the airfoil portion of the blade.. .
United Technologies Corporation


01/28/16
20160024943 

Structural guide vane leading edge


A structural guide vane for use in a gas turbine engine has a leading edge section, a trailing edge, a pressure surface and a suction surface. An erosion coating such as polyurethane resin is on the pressure surface and the suction surface.
United Technologies Corporation


01/28/16
20160024940 

Fan blade damping device


An airfoil for a gas turbine engine and method of manufacture of the airfoil are disclosed. The airfoil may comprise a first side extending axially from a leading edge to a trailing edge and extending radially from a base to a tip, a second side opposite to the first side, a pocket disposed in the first side, a filler disposed in the pocket, and a preloaded spring disposed within the filler..
United Technologies Corporation


01/28/16
20160024938 

Airfoil cooling apparatus


An airfoil for a gas turbine engine, the airfoil includes a wall that has a leading edge and a trailing edge and at least partially defining a boundary of a leading edge cavity radially along the leading edge. A cooling jet structure is operatively associated with a portion of the wall proximate the leading edge and is configured to direct a cooling fluid tangent to the portion of the wall..
United Technologies Corporation


01/28/16
20160024937 

Multi-lobed cooling hole


A gas turbine engine component subjected to a flow of high temperature gas includes a wall having first and second surfaces and a cooling hole extending through the wall. The cooling hole includes an inlet located at the first surface, an outlet located at the second surface, a metering section extending downstream from the inlet, and a diffusing section extending from the metering section to the outlet.
United Technologies Corporation


01/28/16
20160024935 

Gas turbine engine blade with variable density and wide chord tip


A blade for a gas turbine engine includes a body that includes an airfoil that extends in a radial direction from a 0% span position near an airfoil base to a 100% span position at an airfoil tip. The airfoil includes a first portion near the airfoil base with a first density and includes a second portion near the airfoil tip with a second density.
United Technologies Corporation


01/28/16
20160024934 

Aluminum fan blade construction with welded cover


An airfoil includes, among other possible things, a main body extending between a leading edge and a trailing edge. Channels are formed into the main body, with a plurality of ribs extending intermediate the channels.
United Technologies Corporation


01/28/16
20160024929 

Gas turbine engine airfoil


An airfoil for a turbine engine includes an airfoil that has pressure and suction sides that extend in a radial direction from a 0% span position at an inner flow path location to a 100% span position at an airfoil tip. The airfoil has a relationship between a leading edge dihedral and a span position.
United Technologies Corporation


01/28/16
20160024928 

Blade cascade for a turbomachine


The present invention relates to a blade cascade for a gas turbine, which has a first group with at least two, in particular at least three, first blade arrangements of the same type to one another (a1, . .
Mtu Aero Engines Ag


01/28/16
20160024679 

Turbine engine component with a diffused chromium layer


Turbine blades, including airfoils, of aviation or industrial gas turbine engines are treated with chromium to improve resistance to hot corrosion. Various alloys, including, but not limited to nickel, cobalt, molybdenum, and stainless steel alloys may be treated with chromium.
Csa Group Llc


01/28/16
20160024444 

Gel solvent and removing diffusion and overlay coatings in gas turbine engines


A method of stripping an engine component may comprise applying an acidic gel solvent to a coating of a surface of the engine component, leaving the acidic gel solvent on the surface of the engine component for a predetermined duration, and removing the acidic gel solvent from the surface of the engine component. The method may further include mixing an acid with a gelling agent to form the acidic gel solvent.
United Technologies Corporation


01/28/16
20160023773 

Hybrid electric pulsed-power propulsion system for aircraft


A propulsion system has a gas turbine engine optimized to operate at a single operating condition corresponding to a maximum continuous power output of the gas turbine engine, an electric motor system, an electric machine rotatably attached to the gas turbine engine and electrically connected to the electric motor system, and an energy storage system having bi-directional electrical connections with the electric motor system and the electric machine. A method of operating the propulsion system including operating the gas turbine engine for a first period of time to provide electric power to the electric motor system and to recharge the energy storage system, turning off the gas turbine for a second period of time, and discharging the energy storage system to operate the electric motor system during the second period of time..
Hamilton Sundstrand Corporation


01/28/16
20160023275 

Additive manufacturing baffles, covers, and dies


A method includes (a) depositing a layer of a powder material on a work stage, the layer having a thickness, (b) solidifying a portion of the layer based upon data that defines an insert with a body that is shaped to fit into a cavity in a gas turbine engine component, and (c) lowering the work stage by the thickness. Steps (a)-(c) can then be repeated until the insert is complete.
United Technologies Corporation


01/28/16
20160023272 

Turbulating cooling structures


In a first embodiment, a hollow gas turbine engine workpiece comprises first and second walls formed via additive manufacturing, and a cooling passage defined between the first and second walls by a surface of the first and second walls having arithmetic average surface roughness of at least 100 μin (0.0025 mm). In a second embodiment, a method of manufacture of a gas turbine engine component comprises depositing successive layers of pulverant material via additive manufacturing to form first and second walls defining a cooling passage therebetween, and loading a grain size of the pulverant material to produce lattice convective cooling design networks of various size and proportions with each having a range of relative roughness values, 0.10<ε/dh<0.50 to achieve optimal thermal cooling performance along the cooling passage..
United Technologies Corporation


01/21/16
20160018292 

Gas turbine inspection apparatus and inspecting a gas turbine


A method and a system for inspection of gas turbine are presented. An inspection tool is attached on a track which is permanently positioned on site with respect to the gas turbine.
Siemens Energy, Inc.


01/21/16
20160018111 

Method of operating a gas turbine with staged and/or sequential combustion


The invention concerns a method of operating a gas turbine with staged and/or sequential combustion. The burners of a second stage or a second combustor are singularly and sequentially switched on during loading and switched off during de-loading.
Alstom Technology Ltd


01/21/16
20160018110 

Axially staged gas turbine combustor with interstage premixer


The present invention discloses a novel and improved apparatus and method for reducing the emissions of a gas turbine combustion system. More specifically, a combustion system is provided having a first combustion chamber and a premixer positioned proximate an outlet end of a combustion liner for mixing a second fuel/air mixture with hot combustion gases and burning the subsequent mixture to achieve reduced emissions levels.
Timothy Hui


01/21/16
20160017815 

Expanding shell flow control device


A gas turbine engine includes a bypass flowpath between an outer engine case structure and a core engine. The bypass flow exits the engine through a nozzle.
United Technologies Corporation


01/21/16
20160017812 

Geared gas turbine engine with oil deaerator


A gas turbine engine comprises a fan drive turbine for driving a gear reduction. The gear reduction drives a fan rotor.

01/21/16
20160017810 

Acoustic liner heat exchanger


The present disclosure provides an acoustic liner for a gas turbine engine including an acoustic structure for the absorption of acoustic excitation and a heat exchanger. The heat exchanger is able to exchange heat across the acoustic structure..
United Technologies Corporation


01/21/16
20160017809 

Self-purging fuel nozzle system for a gas turbine engine


A self-purge system includes an additively manufactured purge valve assembly in communication with a fuel passage to selectively purge the fuel passage.. .
United Technologies Corporation


01/21/16
20160017806 

Gas turbine engine component having shaped pedestals


A component according to an exemplary aspect of the present disclosure includes, among other things, a first wall, a second wall and at least one row of shaped pedestals extending between the first wall and the second wall. The at least one row of shaped pedestals includes a first set of c-shaped pedestals and a second set of c-shaped pedestals adjacent to the first set of c-shaped pedestals..
United Technologies Corporation


01/21/16
20160017803 

Gas turbine engine de-icing system


A de-icing system for a gas turbine engine according to an exemplary aspect of the present disclosure includes, among other things, a forward assembly and a rear assembly adjacent to the forward assembly. One of the forward assembly and the rear assembly is rotatable relative to the other to generate an amount of air friction between said forward and rear assemblies..
United Technologies Corporation


01/21/16
20160017802 

Hydrogen production system and process


Hydrogen production process and apparatus using a combined stream of gas turbine exhaust from a gas turbine and combustion air from forced draft fan as combustion oxidant in a steam reforming furnace. A valve assembly for providing draft air is included to quickly provide additional combustion air to the reformer furnace when the gas turbine unexpectedly shuts down..
Air Products And Chemicals, Inc.


01/21/16
20160017798 

Integrated calcium looping combined cycle for sour gas applications


A chemical looping combustion (clc) process for sour gas combustion is integrated with a gas turbine combined cycle and a steam generation unit, and is configured to provide in-situ removal of h2s from the sour gas fuel by reacting the h2s with a oxygen carrier at a location within the fuel reactor of the clc unit. The process is also configured such that oxygen-rich exhaust gases from the gas turbine combined cycle is used to feed the air reactor of the clc unit and re-oxidize oxygen carriers for recirculation in the clc unit..
Saudi Arabian Oil Company


01/21/16
20160017796 

Gas turbine engine having a misturned stage


A stage of a gas turbine engine according to an exemplary aspect of the present disclosure includes, among other things, a row of flow directing components circumferentially disposed about a centerline axis and at least one flow directing component of the row having at least one design characteristic that is dissimilar from a corresponding design characteristic of at least one other flow directing component of the row.. .
United Technologies Corporation


01/21/16
20160017793 

Turbocharger with electrically coupled fully variable turbo-compound capability and controlling the same


A turbocharger apparatus of an internal combustion engine and method of controlling the same is provided with electrically coupled fully variable turbo-compound capability. The turbocharger includes an exhaust gas turbine and an intake air compressor.
Avl Powertrain Engineering, Inc.


01/21/16
20160017762 

Gas turbine unit operating mode and design


gas turbine unit (gtv) provides compressed air and steam methane-hydrogen mixture to a combustion chamber to enrich combustion products and cooling by evaporation or superheating of water steam. The temperature of heat exchange processes of the gas turbine unit is increased by additional fuel combustion in the steam-methane-hydrogen mixture postcombustion flow extracted at the output from the additional free work gas turbine, and before supply of steam-methane-hydrogen mixture to the combustion chamber it is previously cooled to the temperature of 200+240° c.
Otkrytoe Aktsionernoe Obshchestvo Gazprom


01/21/16
20160017755 

Common joint for a combustor, diffuser, and tobi of a gas turbine engine


An assembly for a gas turbine engine is disclosed. The gas turbine engine may have a combustor, a diffuser, and a tangential onboard injector.
United Technologies Corporation


01/21/16
20160017754 

Mid-turbine frame rod and turbine case flange


A turbine section of a gas turbine engine includes a first turbine supported for rotation about an axis, a second turbine spaced axially aft of the for first turbine section for rotation about the axis, and a mid-turbine frame disposed between the first turbine and the second turbine defining a passage between the first turbine and the second turbine. A first case surrounds the first turbine and a second case surrounding the second turbine and attached to the first case.
United Technologies Corporation


01/21/16
20160017750 

Annular ring assembly for shroud cooling


A gas turbine engine includes an annular casing and a plurality of shroud segments forming an annular shroud. The annular shroud forms with the annular casing an annular cavity therebetween.
Pratt & Whitney Canada Corp.


01/21/16
20160017748 

Gas turbine engine exhaust drain


An exhaust system of a gas turbine engine includes an exhaust duct, and a venturi drainage device that drains fluid collected in the exhaust duct. The venturi drainage device includes an inlet in fluid communication with the exhaust duct.
United Technologies Corporation


01/21/16
20160017747 

Oil system debris monitor for a gas turbine engine


A debris monitor sensor system according to one disclosed non-limiting embodiment of the present disclosure includes a first passage disposed substantially linearly along a flow path, the first passage includes a sensor passage section. A second passage splits from the first passage and is offset from the flow path.
United Technologies Corporation


01/21/16
20160017745 

Case with vane retention feature


One exemplary aspect of this disclosure relates to an assembly for a gas turbine engine having an engine axis. The assembly includes a case including an integrally formed projection configured to extend transverse to the engine axis.
United Technologies Corporation


01/21/16
20160017743 

Actuator for gas turbine engine blade outer air seal


A blade outer air seal (boas) actuator assembly, according to an exemplary aspect of the present disclosure includes, among other things, an actuator member; and a retractor configured to move with the actuator member to move a boas segment from a first position to a second position that is radially outside the first position, the boas segment seated against a support structure when in the first position and spaced from the support structure when in the second position.. .
United Technologies Corporation


01/21/16
20160017741 

Box rim cavity for a gas turbine engine


A gas turbine engine having a rotor with blades and a stationary vane, a platform seal is formed between the blade and vane for inhibiting ingestion of hot gas from a hot gas flow through the turbine into turbine wheel spaces, the platform seal including axial extending platforms on the blade and vane, and radial extending fingers extending from the platforms and forming restrictions between the fingers and the platforms, and a buffer cavity formed between the restrictions, where the fingers are so arranged in a generally radial direction that the vane can be removed from the turbine engine in a radial direction without having to remove the blades first. In additional embodiments, the platform seal assembly can have two or three buffer cavities formed between additional restrictions..

01/21/16
20160017740 

Riffled seal for a turbomachine, turbomachine and manufacturing a riffled seal for a turbomachine


A seal of a turbomachine reduces a leakage flow between a first and second component of the turbomachine. The first component has a first surface and the second component has a second surface, wherein the first component is stiff with regard to a first force exerted perpendicularly thereto and the second component is stiff with regard to a second force exerted perpendicularly thereto.
Siemens Aktiengesellschaft


01/21/16
20160017737 

Gas turbine engine rotor disk-seal arrangement


A disk-seal arrangement for a gas turbine engine rotor includes a blade retention disk having a longitudinally opening slot therein and a seal disk juxtaposed to said blade retention disk and a single anti-rotation tab received within the blade retention disk slot. The seal disk also includes a pair of balance slots disposed immediately adjacent the antirotation tab to offset the weight thereof for preserving rotor balance.
United Technologies Corporation


01/21/16
20160017736 

Cooled composite sheets for a gas turbine


A laminated sheet for a gas turbine component, the laminated sheet has a first cover layer, a second cover layer and a first intermediate layer, wherein the first cover layer, the second cover layer and the first intermediate layer are stacked together on top of each other. The first intermediate layer is located between the first cover layer and the second cover layer.
Siemens Aktiengesellschaft


01/21/16
20160017732 

Off-cambered vanes for gas turbine engines


An off-cambered vane for a guide vane assembly in a gas turbine engine is described. The guide vane assembly may comprise a nominal vane having a tip portion, a mid-span portion, and a hub portion.
United Technologies Corporation


01/21/16
20160017731 

Vane assembly


A compressor for a gas turbine engine includes a plurality of rotating wheel assemblies, a plurality of static vane assemblies, and a case extending around the rotating wheel assemblies and static vane assemblies. The static vane assemblies include an inner band, an outer band, and a plurality of vanes extending between the inner and outer bands..
Rolls-royce Corporation


01/21/16
20160017730 

Method and attaching a transition duct to a turbine section in a gas turbine engine


An apparatus for attaching a transition duct to a turbine section of a gas turbine engine includes an annular shaped vane carrier that engages with a transition aft frame. The transition aft frame includes an outwardly extending clamp that is at least partially inserted into a radial recess of the vane carrier structure.
Siemens Energy, Inc.


01/21/16
20160017721 

Composite turbine components adapted for use with strip seals


A turbine shroud for a turbine of a gas turbine engine is disclosed. The turbine shroud is configured to direct products of a combustion reaction in a combustor of the gas turbine engine toward a plurality of rotatable turbine blades of the turbine to cause the plurality of turbine blades to rotate..
Rolls-royce Corporation


01/21/16
20160017720 

Airfoil platform impingement cooling holes


An airfoil structure for a gas turbine engine includes an airfoil which includes a leading edge and a trailing edge. A platform is located adjacent a first end of the airfoil and includes a core passage that extends through the platform, a mate-face for engaging an adjacent airfoil structure and a set of impingement cooling holes in communication with the core passage that extend through the mate-face adjacent the trialing edge of the airfoil..
United Technologies Corporation


01/21/16
20160017719 

Gas turbine engine blade squealer pockets


A blade for a gas turbine engine includes an airfoil having a tip with a terminal end surface and multiple squealer pockets recessed into the terminal end surface.. .
United Technologies Corporation


01/21/16
20160017717 

Gas turbine engine airfoil cooling circuit


An airfoil for a gas turbine engine according to an exemplary aspect of the present disclosure includes, among other things, an airfoil body and a cooling circuit disposed inside the airfoil body and including a leading edge cavity with a first portion extending from a radially inner wall to a radially outer wall of the airfoil body and a second portion that extends from a leading edge inner wall to a trailing edge inner wall of the airfoil body. The cooling circuit is configured to communicate cooling airflow through the first portion and the second portion prior to exiting the leading edge cavity into a second cavity of the cooling circuit..
United Technologies Corporation


01/21/16
20160017712 

Turbine engine repair methods


A method for patching a damaged polymeric erosion coating (250) on a gas turbine engine component. The method comprises removing a portion of the coating around a damage site (200; 202; 204) and applying a pre-formed coating patch (220)..
United Technologies Corporation


01/21/16
20160017154 

Lightweight and corrosion resistant abradable coating


An abradable coating for application to a gas turbine engine part is formed from a titanium aluminide alloy, a filler material, and porosity. The coating may be applied to a part such as a casing made from a titanium alloy..
United Technologies Corporation




Gas Turbine topics: Gas Turbine, Gas Turbine Engine, Internal Combustion Engine, Distributed, Combustion, Uv Radiation, Exhaust Gas, Circulation, Downstream

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