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Gas Turbine patents

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 Maintenance of a used gas turbine patent thumbnailMaintenance of a used gas turbine
The present invention is directed to a method for the maintenance of a used gas turbine having the at least partially automated steps of: determining (s13) the geometry of a flow-guiding component, in particular a rotating blade or a guide vane, of the gas turbine; prognosticating (s14) the aerodynamics and/or thermodynamics of the component based on the determined geometry; and classifying (s15) the component into one of several predetermined classes, particularly predetermined quality classes, based on the prognosticated aerodynamics and/or thermodynamics.. .
Mtu Aero Engines Ag


 Combustor and gas turbine patent thumbnailCombustor and gas turbine
An object is to realize combustion flame which can further reduce the amount of nox generation. A combustor (14) includes a pilot nozzle (40); a plurality of main nozzles (44) arranged apart from the pilot nozzle (40) in the circumferential direction on the outer peripheral side of the pilot nozzle (40) and configured to perform premix combustion; a combustor basket (34) surrounding the pilot nozzle (40) and each main nozzle (44); an outlet outer ring (50) provided at a tip end of the combustor basket (34); and a combustion liner (36) fitted, at an inner surface thereof, onto the outer periphery of the combustor basket (34) and surrounding the outlet outer ring (50).
Mitsubishi Heavy Industries, Ltd


 Heat shield for a combustor patent thumbnailHeat shield for a combustor
A gas turbine engine includes a fan, a compressor section, a combustor, a fan drive gear system, and a turbine section coupled to drive the fan through the gear system. The combustor includes an annular outer shell and an annular inner shell that define an annular combustion chamber.
United Technologies Corporation


 Layered ice liner patent thumbnailLayered ice liner
A liner assembly for lining of a gas turbine engine includes a honeycomb core having at least two axially adjacent segments, including a forward segment and an aft segment. An impact resistant layer is disposed against and radially inward of the honeycomb forward segment.
United Technologies Corporation


 Turbofan arrangement with blade channel variations patent thumbnailTurbofan arrangement with blade channel variations
A fan section for a gas turbine engine according to an example of the present disclosure includes, among other things, a rotor hub defining an axis, and an array of airfoils circumferentially spaced about the rotor hub. Each of the airfoils include pressure and suction sides between a leading edge and a trailing edge and extending in a radial direction from a 0% span position at an inner flow path location to a 100% span position at an airfoil tip, facing pressure and suction sides of adjacent airfoils defining a channel in a chordwise direction having a width between the facing pressure and suction sides at a given span position of the adjacent airfoils.
United Technologies Corporation


 Fuel injection system and  controlling the same patent thumbnailFuel injection system and controlling the same
A fuel injection system of a gas turbine includes a first pilot nozzle injecting fuel in a first flow rate range, a second pilot nozzle injecting fuel in a second flow rate range that is greater than the first flow rate range, a main nozzle injecting fuel in a third flow rate range that is greater than the second flow rate range, a first valve opening or closing a first supply pipe fueling the second pilot nozzle, a second valve opening or closing a second supply pipe fueling the main nozzle, and a controller selectively opening any one of the first supply pipe and the second supply pipe or opening or closing both of the first supply pipe and the second supply pipe by reflecting a change in altitude and thus applying control signals to the first valve and the second valve.. .
Hanwha Techwin Co., Ltd.


 Partial-load operation of a gas turbine with an adjustable bypass flow channel patent thumbnailPartial-load operation of a gas turbine with an adjustable bypass flow channel
A gas turbine has a compressor providing compressed air, a combustion chamber provided with a burner, and an expansion turbine, wherein a bypass flow channel is also provided designed to supply compressed air past the burner and to supply a hot gas flow generated in the combustion chamber during operation of the gas turbine. The opening cross section of the bypass flow channel can be adjusted, and an adjustment unit is designed to adjust the opening cross section of the bypass flow channel such that the modification speed of the opening cross section is selected such that the relative combustion chamber pressure drop or a material temperature of the combustion chamber is substantially constant, in particular that the relative combustion chamber pressure drop or the material temperature of the combustion chamber does not vary by more than 10%..
Siemens Aktiengesellschaft


 Gas turbine system and method patent thumbnailGas turbine system and method
A fuel supply system includes a first fuel gas compressor coupled to a fuel gas compressor shaft and configured to pressurize a fuel for a gas turbine system. A clutch is coupled to the fuel gas compressor shaft and is configured to selectively engage the fuel gas compressor shaft with a turbine shaft of the gas turbine system.
General Electric Company


 Cooled fuel injector system for a gas turbine engine patent thumbnailCooled fuel injector system for a gas turbine engine
A cooling system for a fuel injector system of a gas turbine engine has a heat exchanger for cooling a portion of diffuser case air and then routing the cooled diffuser case air through a sleeve that surrounds a fuel injector conduit located in at least the diffuser case plenum for minimizing fuel heat-up rates in the conduit. By minimizing fuel temperatures within the injector conduit, coking accumulation is thereby eliminated or reduced..
United Technologies Corporation


 Nosecap patent thumbnailNosecap
The present disclosure relates generally to a nosecap for a gas turbine engine. The nosecap may be injection molded in an embodiment.
United Technologies Corporation


Systems and methods for control of combustion dynamics in combustion system


A system includes a gas turbine engine having a first combustor and a second combustor. Each combustor has at least one fuel nozzle that receives a mixture of liquid fuel and water, via main and pilot fuel supplies, and that injects the mixture and an oxidant into a combustion chamber.
General Electric Company


Power generation system having compressor creating excess air flow and turbo-expander for supplemental generator


A power generation system may include a gas turbine system including a turbine component, an integral compressor and a combustor to which air from the integral compressor and fuel are supplied. The combustor is arranged to supply hot combustion gases to the turbine component, and the integral compressor has a flow capacity greater than an intake capacity of the combustor and/or the turbine component, creating an excess air flow.
General Electric Company


Power generation system having compressor creating excess air flow and eductor for augmenting same


A power generation system may include a gas turbine system including a turbine component, an integral compressor and a combustor to which air from the integral compressor and fuel are supplied. The combustor is arranged to supply hot combustion gases to the turbine component, and the integral compressor has a flow capacity greater than an intake capacity of the combustor and/or the turbine component, creating an excess air flow.
General Electric Company


Power generation system having compressor creating excess air flow and burner module therefor


A power generation system may include a gas turbine system including a turbine component, an integral compressor and a combustor to which air from the integral compressor and fuel are supplied. The combustor is arranged to supply hot combustion gases to the turbine component, and the integral compressor has a flow capacity greater than an intake capacity of the combustor and/or the turbine component, creating an excess air flow.
General Electric Company


Power generation system having compressor creating excess air flow and turbo-expander using same


A power generation system may include a generator, and a gas turbine system for powering the generator, the gas turbine system including a turbine component, an integral compressor and a combustor to which air from the integral compressor and fuel are supplied, the combustor arranged to supply hot combustion gases to the turbine component, and the integral compressor having a flow capacity greater than an intake capacity of at least one of the combustor and the turbine component, creating an excess air flow. A turbo-expander may also power the generator.
General Electric Company


Power generation system having compressor creating excess air flow and turbo-expander using same


A power generation system may include a generator, and a gas turbine system for powering the generator, the gas turbine system including a turbine component, an integral compressor and a combustor to which air from the integral compressor and fuel are supplied, the combustor arranged to supply hot combustion gases to the turbine component, and the integral compressor having a flow capacity greater than an intake capacity of at least one of the combustor and the turbine component, creating an excess air flow. A turbo-expander may also power the generator.
General Electric Company


Power generation system having compressor creating excess gas flow for supplemental gas turbine system


A power generation system may include a generator; a gas turbine system for powering the generator, the gas turbine system including a turbine component, an integral compressor and a combustor to which air from the integral compressor and fuel are supplied, the combustor arranged to supply hot combustion gases to the turbine component, and the integral compressor having a flow capacity greater than an intake capacity of at least one of the combustor and the turbine component, creating an excess air flow. A first control valve system controls flow of the excess air flow along an excess air flow path to a supplemental gas turbine system.
General Electric Company


Power generation system having compressor creating excess air flow and eductor for process air demand


A power generation system may include a gas turbine system including a first turbine component, an integral compressor and a combustor to which air from the integral compressor and fuel are supplied. The combustor is arranged to supply hot combustion gases to the turbine component, and the integral compressor has a flow capacity greater than an intake capacity of the combustor and/or the turbine component, creating an excess air flow.
General Electric Company


Power generation system having compressor creating excess air flow and turbo-expander to increase turbine exhaust gas mass flow


A power generation system may include: a first gas turbine system including a first turbine component, a first integral compressor and a first combustor to which air from the first integral compressor and fuel are supplied. The first integral compressor has a flow capacity greater than an intake capacity of the first combustor and/or the first turbine component, creating an excess air flow.
General Electric Company


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Power generation system having compressor creating excess air flow and turbo-expander for cooling inlet air


A power generation system may include: a first gas turbine system including a first turbine component, a first integral compressor and a first combustor to which air from the first integral compressor and fuel are supplied. The first integral compressor has a flow capacity greater than an intake capacity of the first combustor and/or the first turbine component, creating an excess air flow.
General Electric Company


Power generation system having compressor creating excess air flow and storage vessel for augmenting excess air flow


A power generation system includes: a first gas turbine system including a first turbine component, a first integral compressor and a first combustor to which air from the first integral compressor and fuel are supplied, the first combustor arranged to supply hot combustion gases to the first turbine component, and the first integral compressor having a flow capacity greater than an intake capacity of the first combustor and/or the first turbine component, creating an excess air flow. A second gas turbine system may include similar components to the first except but without excess capacity in its compressor.
General Electric Company


Power generation system having compressor creating excess air flow and supplemental compressor therefor


A power generation system includes: a first gas turbine system including a first turbine component, a first integral compressor and a first combustor to which air from the first integral compressor and fuel are supplied, the first combustor arranged to supply hot combustion gases to the first turbine component, and the first integral compressor having a flow capacity greater than an intake capacity of the first combustor and/or the first turbine component, creating an excess air flow. A second gas turbine system may include similar components to the first except but without excess capacity in its compressor.
General Electric Company


Power generation system having compressor creating excess air flow and heat exchanger therefor


A power generation system includes: a first gas turbine system including a first turbine component, a first integral compressor and a first combustor to which air from the first integral compressor and fuel are supplied, the first combustor arranged to supply hot combustion gases to the first turbine component, and the first integral compressor having a flow capacity greater than an intake capacity of the first combustor and/or the first gas turbine component, creating an excess air flow. A second gas turbine system may include similar components to the first except but without excess capacity in its compressor.
General Electric Company


Power generation system having compressor creating excess air flow and cooling fluid injection therefor


A power generation system includes: a first gas turbine system including a first turbine component, a first integral compressor and a first combustor to which air from the first integral compressor and fuel are supplied, the first combustor arranged to supply hot combustion gases to the first turbine component, and the first integral compressor having a flow capacity greater than an intake capacity of the first combustor and/or the first turbine component, creating an excess air flow. A second gas turbine system may include similar components to the first except but without excess capacity in its compressor.
General Electric Company


Power generation system having compressor creating excess air flow and eductor augmentation


A power generation system includes: a first gas turbine system including a first turbine component, a first integral compressor and a first combustor to which air from the first integral compressor and fuel are supplied, the first combustor arranged to supply hot combustion gases to the first turbine component, and the first integral compressor having a flow capacity greater than an intake capacity of the first combustor and/or the first turbine component, creating an excess air flow. A second gas turbine system may include similar components to the first except but without excess capacity in its compressor.
General Electric Company


Power generation system having compressor creating excess air flow


A power generation system includes: a first gas turbine system including a first turbine component, a first integral compressor and a first combustor to which air from the first integral compressor and fuel are supplied, the first combustor arranged to supply hot combustion gases to the first turbine component, and the first integral compressor having a flow capacity greater than an intake capacity of the first combustor and/or the first turbine component, creating an excess air flow. A second gas turbine system may include a second turbine component, a second compressor and a second combustor to which air from the second compressor and fuel are supplied, the second combustor arranged to supply hot combustion gases to the second turbine component.
General Electric Company


Coated cooling passage


A component for a gas turbine engine includes a substrate with a substrate aperture and a coating on the substrate that extends a length of the substrate aperture. A liner assembly for a gas turbine engine includes a hot sheet with a multiple of apertures and a coating on the hot sheet that extends a length of each of the multiple of apertures.
United Technologies Corporation


Exhaust gas liner for a gas turbine and gas turbine with such an exhaust gas liner


An exhaust gas liner for a gas turbine includes an annular inner shell and an annular outer shell, which are arranged concentrically around a machine axis of the gas turbine to define an annular exhaust gas channel in between. The inner shell and/or said outer shell are composed of a plurality of liner segments, which are attached to a support structure.
Alstom Technology Ltd


Fan drive gear system manifold radial tube filters


A lubrication system for gas turbine engine includes a main lubricant passage for providing lubricant from a lubricant supply to a lubricant manifold. The lubricant manifold includes first and second lubricant passages the lubricant manifold is configured to supply lubricant to first and second separate parts of a geared architecture at different first and second lubricant flow conditions.
United Technologies Corporation


Cooling passages for a mid-turbine frame


A spoke for a mid-turbine frame on a gas turbine engine includes a cylindrical portion. A flange is attached to the cylindrical portion.
United Technologies Corporation


Cooling passages for a mid-turbine frame


A mid-turbine frame for a gas turbine engine includes an inner frame case. A bearing support member is located adjacent the inner frame case.
United Technologies Corporation


Integrated washing system for gas turbine engine


A washing system is described for a gas turbine engine with an axial compressor, comprising: an inlet screen at the air flow inlet of the compressor to protect the compressor from foreign object damage, an arrangement of nozzles and manifolds for spraying the washing liquid, and a washing liquid supply system connected to the arrangement; the inlet screen comprises a supporting structure and a filtering net fixed to the supporting structure; the arrangement of nozzles and manifolds is integrated in the supporting structure of the inlet screen.. .
Nuovo Pignone Srl


Protective device for a turbomachine


A protective device (10) for a turbomachine, in particular a gas turbine, having a containment ring (12) which is disposed on the radially inner side of a casing element (14) of the turbomachine and which at least substantially prevents the casing element (14) from being penetrated by a fragment of a component of the turbomachine in the event of a structural failure of this component is provided. The containment ring (12) is composed, at least in the circumferential direction, of a plurality of ring segments (16) which are form-fittingly interconnected.
Mtu Aero Engines Ag


Gas turbine engine health determination


A method is provided for determining an updated engine health factor of an aircraft engine. The method includes determining an engine health condition indicative of an engine health during operation of the aircraft engine.
General Electric Company


Variable vane control system


A variable vane control system for controlling the angle of rotation of a circumferential row of variable vanes of a gas turbine engine. The control system includes a mechanical linkage operable to rotate the variable vanes, one or more actuators for operating the linkage and one or more position sensors for detecting the respective actuation positions of the one or more actuators.
Rolls-royce Controls And Data Services Limited


Part load performance improvement using deformable boreplugs


A cooling arrangement for a gas turbine engine includes a discharge channel for airflow from a compressor, a first cooling channel, and at least one aperture providing communication between the flow of air through the discharge channel and the first cooling channel. A restrictor device in the aperture regulates the flow of air between the discharge channel and the first cooling channel.
General Electric Company


Tailored thermal control system for gas turbine engine blade outer air seal array


A clearance control ring for a clearance control system of a gas turbine engine includes a contoured radial outer portion that defines a multiple of fins and a multiple of slots. A clearance control system of a gas turbine engine includes a clearance control ring with a radial inner portion from which a contoured radial outer portion extends.
United Technologies Corporation


Seal assembly in a gas turbine engine


A gas turbine engine seal assembly (160) including: a rigid seal (58) cooperatively configured with a structure (14, 42) of a gas turbine engine to define a leakage path (102, 130) including a flow-controlling section (106, 134); and a compliant seal (162, 164) positioned in the leakage path.. .
Siemens Energy, Inc.


Vane


A vane for an exhaust system duct in a gas turbine engine including a vane plate, a guide plate, and a baffle. The vane plate includes a leading edge, a first leg and a second leg, with the first and second legs respectively extending on opposing sides of the leading edge to form a substantially u-shaped profile.
Rolls-royce Plc


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Bladed rotor arrangement and a lock plate for a bladed rotor arrangement


A lock plate of a bladed rotor arrangement is hollow. The bladed rotor arrangement comprises is a bladed turbine rotor of a gas turbine engine.
Rolls-royce Plc


Internally cooled gas turbine engine airfoil


A gas turbine engine airfoil has a hollow airfoil section extending chordwise between a leading edge and a trailing edge. The airfoil has a leading edge cooling passage and a separate serpentine passage for cooling a remaining portion of the airfoil.
Pratt & Whitney Canada Corp.


Gas turbine engine airfoil with leading edge trench and impingement cooling


A gas turbine engine airfoil includes an airfoil structure including an exterior surface that is provided by an exterior wall that has a leading edge. A radially extending interior wall within the airfoil structure separates first and second radial cooling passages.
United Technologies Corporation


Engine component


An engine component for a gas turbine engine includes a film-cooled substrate having a hot surface facing hot combustion gas and a cooling surface facing a cooling fluid flow. The substrate includes one or more film holes that have a metering section defining a metering diameter and a diffusing section that defines a hooded length..
General Electric Company


Blade or vane arrangement for a gas turbine engine


A blade or vane arrangement for a gas turbine engine has an array of aerofoils mounted to respective platforms about an axis and defining a passage through which a working gas flow passes. The arrangement has a datum and the aerofoil has a radial span.
Siemens Aktiengesellschaft


Turbofan arrangement with blade channel variations


A fan section for a gas turbine engine according to an example of the present disclosure includes, among other things, a rotor hub defining an axis, and an array of airfoils circumferentially spaced about the rotor hub. Each of the airfoils include pressure and suction sides between a leading edge and a trailing edge and extending in a radial direction from a 0% span position at an inner flow path location to a 100% span position at an airfoil tip.
United Technologies Corporation


Cooling system for a gas turbine


The cooling system according the invention comprises an annular array of turbine blades which comprises an undercut (17) formed in a blade platform (11). A substantially cylindrical damper pin (22) is arranged between two turbine blades (10a and 10b).

Calcium-magnesium-alumino-silicate resistant thermal barrier coatings


A method for forming a coating system on a component includes depositing a reactive layer with predetermined cmas reaction kinetics on at least a portion of a thermal baffler coating. The method also includes activating the reactive layer with a scanning laser.
United Technologies Corporation


Laser powder deposition weld rework for gas turbine non-fusion weldable nickel castings


A method of reworking or repairing a component includes removing a casting defect from a component manufactured of a non-fusion weldable base alloy to form a cavity that results in a through hole; sealing the through hole with a backing; and at least partially filling the cavity with a multiple of layers of a multiple of laser powder deposition spots, each of the multiple of laser powder deposition spots formed of a filler alloy, a first layer of the multiple of layers includes a perimeter of the multiple of laser powder deposition spots that overlap a wall of the cavity and the backing.. .
United Technologies Corporation


Power generation system having compressor creating excess air flow for scr unit


A power generation system includes a gas turbine system including a turbine component, an integral compressor and a combustor to which air from the integral compressor and fuel are supplied, the combustor arranged to supply hot combustion gases to the turbine component, and the integral compressor having a flow capacity greater than an intake capacity of at least one of the combustor and the turbine component, creating an excess air flow. A first control valve system controls flow of the excess air flow along an excess air flow path to an exhaust of the turbine component.
General Electric Company


Gas turbine engine wall assembly with offset rail


A liner panel within a gas turbine engine includes a perimeter rail that defines a first height from a cold side. The liner panel also includes an intermediate rail that defines a second height from the cold side, where the second height is less than the first height..
United Technologies Corporation


Variable port assemblies for wave rotors


A wave rotor combustor for use in a gas turbine engine includes an inlet assembly, a rotor drum, and an outlet assembly. The inlet assembly is arranged to direct a flow of gasses into rotor passages formed in the rotor drum.
Rolls-royce North American Technologies, Inc.


Fuel nozzle for a gas turbine engine


A fuel nozzle apparatus for a gas turbine engine includes: an annular outer body extending parallel to a centerline axis, with an exterior surface having a plurality of openings; a main injection ring disposed inside the outer body and including: a circumferential main fuel gallery; and a plurality of main fuel orifices, each main fuel orifice communicating with the main fuel gallery and aligned with one of the openings; a venturi disposed inside the main injection ring; an annular splitter disposed inside the venturi, and including inner and outer walls spaced-apart from each other defining a splitter cavity, and a plurality of discharge holes communicating with the splitter cavity; an array of outer swirl vanes extending between the venturi and the splitter; a pilot fuel injector within the splitter; and an array of inner swirl vanes extending between the splitter and the pilot fuel injector.. .
General Electric Company


Twin radial splitter-chevron mixer with converging throat


A fuel nozzle for a gas turbine includes a first radial swirler and a second radial swirler that introduce radial swirl to a flow of pressurized air; a chevron splitter between the two swirlers that directs the swirled flow of pressurized air to a main mixer passage to form a fuel-air mixture with fuel injected into the fuel nozzle; and a main mixer passage that receives the fuel-air mixture from the premixing chamber, and includes a converging throat that accelerates the fuel-air mixture. A method of mixing fuel and air for combustion in a gas turbine includes introducing a radial swirl to first and second flows of pressurized air; directing the swirled, pressurized air to a premixing chamber via a chevron splitter; mixing the swirled, pressurized air with a fuel jet injected into the premixing chamber to form a fuel-air mixture; and accelerating the fuel-air mixture in the main mixer passage having a converging throat..
General Electric Company


Hybrid air blast fuel nozzle


A fuel nozzle apparatus for a gas turbine engine includes: a first pilot fuel injector disposed on a centerline axis of the fuel nozzle which defines a direction of air flow through the fuel nozzle, the first pilot fuel injector being of a pressure atomizing type; an annular second pilot fuel injector at least partially surrounding the first pilot fuel injector, the second pilot fuel injector being of an air blast type and having a fuel outlet disposed axially downstream and radially outboard of the first pilot fuel injector; an annular venturi surrounding the first and second pilot fuel injectors, the venturi including a throat of minimum diameter; an array of inner swirl vanes extending between the first pilot fuel injector and the second pilot fuel injector; and an array of outer swirl vanes extending between the second pilot fuel injector and the venturi.. .
General Electric Company


Combustion chamber with double wall


A combustion chamber includes a duct wall for guiding a hot gas flow in a hot gas flow path during operation. The duct wall is a double-walled construction including an inner face, an outer face, and a wall cavity.
Ansaldo Energia Ip Uk Limited


Swept combustor liner panels for gas turbine engine combustor


A liner panel is provided for use in a combustor of a gas turbine engine. The liner panel includes a first liner panel side edge between a liner panel aft edge and a liner panel forward edge.
United Technologies Corporation


Non symmetrical bi-directional thrust bearing with two active faces


A bearing device supports a shaft of a gas turbine engine. A first support disk is mounted to the bearing housing element.
Siemens Aktiengesellschaft


Compound fillet varying chordwise and method to manufacture


An improved structure and method of manufacturing a structure such as a guide vane for a gas turbine engine includes an improved guide vane having a stress transition section called a fillet that is positioned between an airfoil and a hub. The fillet includes a constant radius section and a compound radius portion that is collectively configured to handle the stress loads of the guide vane as well as to provide aerodynamic efficiencies.
Rolls-royce Corporation


Multi-stage co-rotating variable pitch fan


A fan for a gas turbine engine is disclosed. The fan includes a fan disk and a plurality of fan blades coupled to the fan disk.
Rolls-royce Corporation


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Method for operating a gas turbine


A gas turbine having a compressor is controlled at least by controlling an opening of variable inlet guide vanes between a maximum opening and a minimum opening. A function indicative of the mechanical stress undergone by compressor blades downstream of the variable inlet guide vanes has an increasing line trend from the maximum opening to the minimum opening of the variable inlet guide vanes.
Ansaldo Energia Ip Uk Limited


Gas bleed arrangement


A gas bleed arrangement for a gas turbine engine. The gas bleed arrangement includes an annular casing defining a main gas flow path.
Rolls-royce Plc


High temperature, low oxidation, amorphous silicon-coated titanium


An exhaust system for a gas turbine engine may comprise a titanium alloy substrate. The titanium alloy may comprise imi 834, titanium 1100, titanium 6242, or beta-21s.
Rohr, Inc.


Mounting and dismounting device for a liner of a gas turbine and a related method


A mounting and dismounting device for a liner of a gas turbine includes two inner rails attached at the turbine housing and each one having a first straight portion, two straight outer rails releasably attached at the turbine housing, wherein the adjacent free ends of the inner and outer rails can be positioned in full alignment one to the other. The rails are adapted to support the liner to be moveable in its axial direction.
Ansaldo Energia Switzerland Ag


Cooling passages for a mid-turbine frame


A mid-turbine frame for a gas turbine engine includes an inner frame case. A bearing support member is located adjacent the inner frame case.
United Technologies Corporation


Secondary air system with venturi


A gas turbine engine including a secondary air system with interconnected fluid passages defining at least one flow path between a common source of pressurized air and a common outlet. Some of the fluid passages deliver the pressurized air to components of the gas turbine engine.
Pratt & Whitney Canada Corp.


Nozzle, combustion apparatus, and gas turbine


A combustion apparatus includes a nozzle in which a fuel injection port for injecting a fuel is formed on the center of a tip. A plurality of water injection ports are formed with intervals therebetween in a circumferential direction around the fuel injection port of the tip of the nozzle, and the water injection ports are non-uniformly formed in the circumferential direction..
Mitsubishi Hitachi Power Systems, Ltd.


Integral ceramic matrix composite fastener with polymer rigidization


A method of forming an integral fastener for a ceramic matrix composite component comprises the steps of forming a fiber preform, applying a polymer material to the fiber preform to form a rigid preform structure, machining an opening in the rigid preform structure, forming a fiber fastener, inserting the fiber fastener into the opening, removing the polymer material, and infiltrating a matrix material into the rigid preform structure and fiber fastener to form a ceramic matrix composite component with an integral fastener. A gas turbine engine is also disclosed..
United Technologies Corporation


Turbine vane with heat shield


A gas turbine engine may include a body and a turbine-vane ring coupled to the body. The turbine-vane ring may include a plurality of turbine-vane assemblies..
Rolls-royce Corporation


Integrated gas turbine engine support and sensor


An example integrated support and sensor includes a longitudinal member to support an inner duct relative to an outer duct, and a sensor received within a bore of the longitudinal member and configured to collect a measurement from a flow path bounded by the inner duct.. .
United Technologies Corporation


Gas turbine engine ramped rapid response clearance control system


An active clearance control system of a gas turbine engine includes a multiple of blade outer air seal assemblies and a multiple of rotary ramps. Each of the multiple of rotary ramps is associated with one of the multiple of blade outer air seal assemblies.
United Technologies Corporation


Sealing system and gas turbine


A sealing system includes a bolt and a cover plate for sealing a joint between a rotor disk and a blade root of a rotor blade, the blade root being disposed in a blade root slot in the rotor disk. The sealing arrangement is used in particular in a gas turbine..
Siemens Aktiengesellschaft


Tolerance resistance coverplates


A gas turbine engine component assembly comprises a first component and a second component circumferentially spaced from the first component relative to an engine center axis. A first baffle is associated with the first component.
United Technologies Corporation


Inner diffuser case for a gas turbine engine


A combustor section of a gas turbine engine has a diffuser case with a structural cone having variable wall thicknesses strategically located for reducing localized stress in the cone.. .
United Technologies Corporation


Chocking and retaining device


A device for chocking and retaining a dovetail root of a blade of a gas turbine engine in a corresponding axially-extending slot in the rim of a disc includes a retention body having a key portion receivable in a keyway formed in the base of the slot, and a mating portion for mating with a complementary mating portion of the root to prevent relative axial movement between the retention body and the root. The retention body has a lowered position in which the key portion is received sufficiently deeply in the keyway to allow the root to be positioned in the slot without interference from the retention body and also has a raised position in which, after the root is positioned in the slot, a part of the key portion is still received in the keyway while the mating portion mates with the complementary mating portion of the root..
Rolls-royce Plc


Chocking and retaining device


A device for chocking and retaining a dovetail root of a blade of a gas turbine engine in a corresponding axially-extending slot in the rim of a disc, the root being mounted in the slot by insertion of a leading end of the root into a proximal end of the slot and then sliding the root towards a distal end of the slot. The device includes a first wedging body having a key portion receivable in a keyway formed at the distal end of the slot.
Rolls-royce Plc


Gas turbine engine turbine blade tip cooling


A gas turbine engine component includes a structure having a surface configured to be exposed to a hot working fluid. The surface includes a recessed pocket that is circumscribed by an overhang.
United Technologies Corporation


Manufacture of a hollow aerofoil


A method of manufacturing a hollow aerofoil component for a gas turbine engine comprises using a capping panel to cover a pocket in a pocketed aerofoil body. The pocketed aerofoil body has a ledge of substantially constant thickness that extends around its perimeter, and to which the capping panel is joined (e.g.
Rolls-royce Plc


Turbine blade


A turbine blade for a gas turbine has a securing region and a platform region that adjoins the securing region and has a platform on which a blade airfoil with a profiled cross-section and with a pressure-side wall and a suction-side wall is arranged, wherein each outer face of the pressure-side wall and/or the suction-side wall transitions into the platform surface via an outer rounded section. The turbine blade also has at least one cavity which is arranged in the blade airfoil and extends into the platform region and in which at least one rib is provided that connects the pressure-side wall to the suction-side wall, the rib extending along a longitudinal direction of the blade airfoil so as to divide the cavity.
Siemens Aktiengesellschaft


Bonded multi-piece gas turbine engine component


An airfoil component includes a first segment that has a first piece of a mount and a first piece of an airfoil. The first segment is formed of a first ceramic-based material.
United Technologies Corporation


Multiple piece engine component


One exemplary embodiment of this disclosure relates to a gas turbine engine, including a component having a first portion formed using one of a casting and a forging process, and a second portion formed using an additive manufacturing process.. .
Unitedtechnologies Corporation


Method for the production of a highly stressable component from an a+y-titanium aluminide alloy for reciprocating-piston engines and gas turbines, especially aircraft engines


Wherein the deformation is carried out in a single stage starting from a preform with a volume distribution varying over the longitudinal axis, wherein the component is deformed isothermally in the β-phase region at a logarithmic deformation rate of 0.01-0.5 1/s.. .



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


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