This page is updated frequently with new Gas Turbine-related patent applications.
|| List of recent Gas Turbine-related patents
|Acoustic abatement system for air cooled heat exchanger|
A system configured to thermally regulate heat dissipation of a power plant system (e.g. Steam turbine, gas turbine compressor, intercooler or other fluidic thermal source, etc.) and acoustically attenuate operation of an air cooled heat exchanger via sound reflection, sound absorption, sound diffraction, and/or active noise cancellation is disclosed.
|Torque sensor monitoring for gas turbine engine|
A gas turbine engine torque monitoring system includes a gas turbine engine and gas turbine engine electronics. The gas turbine engine includes a torque sensor coupled to a rotatable element of the gas turbine engine, such as a drive shaft.
|Axially staged mixer with dilution air injection|
A method is disclosed for operating an axially staged mixer arrangement with dilution air or dilution gas injection in connection with a combustion arrangement of a gas turbine engine or turbo machinery, having at least one combustion chamber, at least one mixer arrangement for admixing air or gas portions to the hot gas flow leaving the combustion chamber. The mixer arrangement includes a plurality of injectors for admixing air portions to cool at least the hot gas flow leaving combustion chamber.
|Gas turbine engine components and cooling cavities|
The present disclosure relates to gas turbine engine components including cooling cavities. One embodiment is directed to a component including a forward surface, an aft surface, at least one inlet on the forward surface and a cavity between the forward surface and the aft surface.
|Separate feedings of cooling and dilution air|
A combustor arrangement of a gas turbine engine or power plant is disclosed, having at least one combustion chamber, at least one mixer arrangement for admixing air or gas to the hot gas flow leaving the combustion chamber. The mixer arrangement is configured to guide combustion gases in a hot gas flow path extending downstream of the combustion chamber, wherein the mixer includes a plurality of injection pipes pointing inwards from the side walls of the mixer arrangement for admixing air portions to cool at least the hot gas flow leaving combustion chamber.
|Combustor dilution hole active heat transfer control apparatus and system|
Systems and methods are described herein whereby an air jet is configured to manipulate local aerodynamics and/or boundary layer flows associated with a dilution hole. A gas turbine component including a combustor panel, a dilution hole located within the combustor panel and an air jet located within the combustor panel positioned in close proximity to the dilution hole is described.
|Gas turbine combustion chamber with modified wall thickness|
A gas turbine combustion chamber, including at least one combustion chamber wall in which mixed air holes are formed in a predefined area that extends around the combustion chamber in a ring-shaped manner with respect to the central axis of the combustion chamber in a central area of the same, characterized in that the combustion chamber wall has a greater thickness in the ring-shaped area of the mixed air holes than in the areas that are not provided with mixed air holes.. .
|Tiered brush seal|
The present disclosure relates to sealing systems for gas turbine engines. In one embodiment, a seal support structure for a gas turbine engine includes a seal support configured to retain a circumferential seal and an engine support configured for mounting the seal support structure to a gas turbine engine mount.
|Gas turbine engine|
A fan casing for fitment around an array of radially extending fan blades of a gas turbine engine. The fan casing includes an annular casing element; and an annular fan track liner positioned radially inward of the annular casing element.
|Compressor blade of a gas turbine|
The present invention relates to a compressor blade of a gas turbine having an airfoil and a blade root, said blade root and airfoil being made in one piece from a fiber-composite material, as well as a leading edge protector made from a sheet metal material, characterized in that the airfoil is provided with a radial groove extending substantially over the entire length of the airfoil and that the leading edge protector is detachably clamped onto the airfoil and is fixed with a sheet metal flange in the radial groove of the airfoil.. .
Method and system for a gas turbine engine purge circuit water injection
A method and fuel supply system for supply of a combustion chamber with at least one combustible fluid are provided. The fuel supply system includes a combustion chamber including a fuel injector, at least one supply circuit configured to supply the combustion chamber with a combustible fluid, and at least one purge circuit configured to purge the supply circuit, the purge circuit connected to a purge air source and the at least one supply circuit, the purge circuit including at least two isolation valves defining a cavity between the at least two isolation valves, the purge circuit including a water injection circuit configured to inject water into the cavity, the purge circuit including a cavity draining circuit configured to drain the cavity..
Method and system for a gas turbine engine air ventilation purge circuit
A method and fuel supply system for supply of a combustion chamber with at least one combustible fluid are provided. The fuel supply system includes a combustion chamber, at least one supply circuit, and at least one purge circuit, the purge circuit coupled to the at least one supply circuit, the purge circuit including at least two isolation valves defining a cavity between, a source of relatively high temperature purge air coupled in flow communication to the cavity through one of the at least two isolation valves, a source of relatively low temperature ventilation air coupled in flow communication to the cavity, and a vent coupled in flow communication to the cavity, the at least one purge circuit configured to channel a flow of relatively low temperature ventilation air from the source relatively low temperature ventilation air through the cavity to the vent during operation of the combustion chamber..
An exhaust duct for a gas turbine engine has an annular inlet conduit having an inlet axis. At least two outlet conduits branch off from the inlet conduit along respective outlet centerlines that are distinct from one another.
Auxiliary component mounts
A mount for mounting a component to a gas turbine engine is disclosed. The mount may include a central portion that attaches to the component, and a flange circumscribing the central portion and extending to the gas turbine engine, the flange including a fusible region that breaks at a predetermined load.
Gas turbine fuel pipe comprising a damper
The invention concerns a gas turbine fuel pipe, having a fuel line, the fuel line having a fuel line volume, a fuel line outer wall and an opening in the fuel line outer wall, a damper having a damper volume and a damper outer wall and attached in fluid communication with the fuel line, wherein the damper covers the opening in the fuel line outer wall, and a perforated lining extending across at least part of the opening in the fuel line outer wall. Various embodiments are also described, along with a method of use of the apparatus..
Gas turbine engine with angularly offset turbine vanes
A gas turbine engine includes a combustor having a plurality of fuel nozzles arranged circumferentially equidistant from one another about a first center. The plurality of fuel nozzles produce a plurality of pressure pulses in a fluid contained in the combustor.
Fuel nozzle structure
A gas turbine engine fuel nozzle apparatus includes: an annular outer body, the outer body extending parallel to a centerline axis, and having a generally cylindrical exterior surface extending between forward and aft ends, and having a plurality of openings passing through the exterior surface; an annular main injection ring disposed inside the outer body, the main injection ring including an annular array of fuel posts extending radially outward therefrom; a main fuel gallery extending within the main injection ring in a circumferential direction; a plurality of main fuel orifices, each main fuel orifice communicating with the main fuel gallery and extending through one of the fuel posts; and a suspension structure connecting the main injection ring to the outer body, the suspension structure configured to substantially rigidly locate the position of the main ring in axial and lateral directions while permitting controlled deflection in a radial direction.. .
Mixer for admixing a dilution air to the hot gas flow
The invention refers to a combustor arrangement of a gas turbine engine or power plant, having at least one combustion chamber, at least one mixer for admixing a dilution medium or air to the hot gas flow leaving the combustion chamber. The mixer is configured to guide combustion gases in a hot gas flow path extending downstream of the combustion chamber, wherein the mixer includes a plurality of injection pipes pointing inwards from the side walls of the mixer for admixing the dilution medium or air to cool the hot gas flow leaving combustion chamber.
Cooling-air supply device for a gas turbine
A cooling-air supply device for a gas turbine, in particular an aircraft gas turbine, including a cooling air chamber, that is disposed about a turbine shaft of the gas turbine, at least one cooling-air inlet opening, and at least one cooling-air outlet orifice; the cooling-air supply device having a first and a second axial bounding wall, and a peripheral wall that joins the two axial bounding walls, which, together, form the cooling air chamber; in at least one of the axial bounding walls, a plurality of cooling-air outlet orifices being provided, which are circumferentially distributed about the turbine shaft and are adapted to allow the cooling air to essentially be discharged from the individual cooling-air outlet orifices in the direction of rotation of the gas turbine. In the axial direction, the respective axial bounding wall having the cooling-air outlet orifices has a layer-type structure; the cooling-air outlet orifices being formed by deformation of at least one first cooling air chamber-side layer and by deformation of at least one second, turbine-side layer..
Microchannel heat exchangers for gas turbine intercooling and condensing
A gas turbine engine heat exchange system includes a first microchannel heat exchanger (mchx) configured to transfer heat between a first air stream and a working fluid. The first mchx includes a plurality of air-passage layers.
Staged heat exchangers for multi-bypass stream gas turbine engines
A gas turbine bypass flow arrangement comprises an outer housing and an inner housing, an outer bypass duct defined between the outer housing and the inner housing and an inner bypass duct defined inwardly of the inner housing. A first heat exchanger is positioned at an upstream location within the outer bypass duct and a second heat exchanger is positioned within the inner bypass duct at an upstream location.
Gas turbine power plant made flexible
A gas turbine power plant includes a gas turbine having a compressor, combustion chamber, and expander and is rotationally mechanically coupled to an energisation unit designed for motor operation of the compressor and for electricity-generating generator operation of the gas turbine. The power plant includes a recuperator, thermally connected to an exhaust-gas discharge line of the turbine such that heat is transferred from the exhaust-gas flow in the exhaust-gas discharge line to a fluid flow in a fluid line during operation, which fluid flow is fed to the combustion chamber.
Gas turbine engine intake duct
To be accompanied when published by fig. 2..
Generating power using an ion transport membrane
In some implementations, a system may include a compressor, a heat exchanger and an itm. The compressor is configured to receive an air stream and compress the air stream to generate a pressurized stream.
Low pressure environmental control system with safe pylon transit
A gas turbine engine includes a fan section delivering air into a compressor section. The compressor section compresses air and delivers air into a combustion section.
Simplified engine bleed supply with low pressure environmental control system for aircraft
A gas turbine engine assembly for an aircraft includes a fan section delivering air into a main compressor section. The main compressor section includes a first compressor section and a second compressor section operating at a higher pressure than the first compressor section.
Turboshaft engine exhaust nozzle having its outlet perpendicular to the axis of rotation of the engine
A gas exhaust nozzle for a gas turbine, the exhaust nozzle having an annular inlet section centered on the axis of the gas turbine, a diffuser, a plenum chamber, and an expansion nozzle. The diffuser extends around the axis with a shape that diverges from the inlet section to the plenum chamber, and comprises an inner first surface and an outer first surface that are concave on the same side.
Intergrated seal supports
An inner case for a gas turbine engine includes a case body defining a centerline axis. The case body includes a turbine seal support, and an i-rod support downstream of the turbine seal support.
A turbine shroud for a gas turbine engine includes an annular metallic carrier and a ceramic-containing blade track. A connection is formed between the annular metallic carrier and the ceramic-containing blade track by insert pins extending through metallic carrier into the ceramic-containing blade track..
Engine component having platform with passageway
One exemplary embodiment of this disclosure relates to a gas turbine engine including a component. The component includes a platform having a mateface on a circumferential side thereof.
System and controlling an environmental condition of an engine electronic component
The present disclosure relates generally to a gas turbine engine that includes a fan configured to generate a fanstream and a fanstream duct configured to receive the fanstream flowing therethrough. An engine electronic component is positioned in flow communication with the fanstream.
Optical measurement system for detecting turbine blade lockup
An optical measurement system for detecting at least one locked blade assembly in a gas turbine. The system includes at least one light source for emitting light that impinges on a blade surface of each blade in a row of blade assemblies.
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 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.
Thermal inspection system
A thermal inspection system is provided for a gas turbine engine hot section component with a cooling passage. This thermal inspection system includes a fluid subsystem operable to supply a fluid into the cooling passage.
Laser measurement system for detecting turbine blade lockup
A laser measurement system for detecting at least one locked blade assembly in a gas turbine. The system includes at least one laser device for emitting a laser beam that impinges on a blade surface of each blade in a row of blade assemblies.
Gas turbine engine with rotor blade tip clearance flow control
A gas turbine engine system includes a drive shaft and a compressor located in a compressor case. The compressor has a number of rotors.
Trough seal for gas turbine engine
This disclosure relates to a gas turbine engine including a first engine component and a second engine component. The first engine component has a mate face adjacent a mate face of the second engine component.
Compliant seal assembly and operating
A compliant seal assembly that may be for an mtf of a gas turbine engine includes a housing orientated about an axis with a circumferentially extending groove in the housing opened radially outward. An annular carrier of the assembly is constructed and arranged to move radially within the groove, and includes a circumferentially extending channel that is opened radially outward for receipt of a piston ring that may seal to a surrounding cylindrical wall.
Gas turbine engine sealing arrangement
A sealing arrangement for a gas turbine engine according to an exemplary aspect of the present disclosure includes, among other things, a groove that extends between an upstream rail and a downstream rail, a complementary static structure spaced from the groove, and a seal positioned within the groove and configured to seal a clearance between at least one of the upstream rail and the downstream rail and the complementary static structure.. .
Gas turbine vane
The present invention generally relates to a vane for a gas turbine, and more in particular it provides an innovative vane with improved flexibility leading to a reduction of stresses at the transition from the vane trailing edge to the vane platform, without interfering into the cooling scheme of such component. The present invention can increase flexibility of the vane platform by introducing on the vane platform a material cutback confined in the proximity of the trailing edge portion of the vane airfoil..
Angled rail holes
A gas turbine engine combustor configured to cool a first vane platform by directing airflow through an aft combustor rail is disclosed. In various embodiments, a gas turbine engine combustor may comprise an aft combustor rail connected between an outer wall of an outer liner and an aft heat shield panel, and a plurality of holes in the aft combustor rail.
The present disclosure includes airfoils for use in gas turbine engines. The airfoils comprise a fillet having a height of greater than 20% of the airfoil body span length.
Full hoop blade track with axially keyed features
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 locates the ceramic blade track relative to the metallic carrier..
Blading member for a fluid flow machine
A blading member for fluid flow machines, for example, gas turbine engines. The blading member includes a platform member, at least one airfoil member, and at least one interlock member..
Blade and gas turbine provided with the same
A blade is formed with blade air passages connecting the inside of a blade body of the blade and the inside of a platform of the blade. The platform is formed with a plurality of pressure side passages that extend from the blade air passages toward a circumferential pressure side, are open at a pressure side end face, and are arranged in an axial direction.
Blading member for a fluid flow machine
A blading member for a fluid flow machine, for example, for use in gas turbine engines. The blading member includes a platform member and an airfoil member.
Turbine wheel with composite bladed ring
A turbine wheel for use in a gas turbine engine having a bladed ring attached to a rotor disk. The bladed ring includes features to fit within slots of the rotor disk to couple the bladed ring to the rotor disk..
Abrasive tips for ceramic matrix composite blades and methods for making the same
A blade and method for producing the blade for a gas turbine engine are described herein. The blade may include a composite airfoil.
Composite airfoil for a gas turbine engine
Stationary vanes and rotating blades of a gas turbine engine are disclosed that include airfoils formed from ceramic matrix composite materials. The airfoils include at least one layer of ceramic-containing matrix material and ceramic-containing reinforcing fibers suspended in the matrix material.
Aerofoil blade or vane
An aerofoil blade or vane for the turbine of a gas turbine engine includes: an aerofoil leading edge; an aerofoil trailing edge; an aerofoil suction side; and at least one reverse-pass coolant passage, extending within the aerofoil blade or vane; wherein the at least one reverse-pass coolant passage includes a substantial reverse-pass portion in which, in use, coolant flows in a direction away from the trailing edge and towards the leading edge.. .
Gas turbine engine component with conformal fillet cooling path
A cooling circuit for a gas turbine engine comprises a gas turbine engine component having a first portion connected to a second portion via a curved surface. An inlet is formed in or near one of the first and second portions to receive a cooling air flow.
Gas turbine engine component with film cooling hole
A gas turbine engine component includes a wall that provides an exterior surface and an interior flow path surface. The wall has a wall thickness.
Gas turbine engine component with film cooling hole with accumulator
A gas turbine engine component includes a wall that provides an exterior surface and an interior flow path surface. A film cooling hole extends through the wall and is configured to fluidly connect the interior flow path surface to the exterior surface.
Cooled airfoil structure
An airfoil structure for a gas turbine engine includes an airfoil that includes a suction side cooling circuit with at least two segments that are connected by at least one impingement passage.. .
Method of forming cooling holes
A method of forming a component for use in a gas turbine engine comprises the steps of determining a desired shape for a cooling hole on a gas turbine engine component, and determining the likely deposition of a coating to be provided on the component into the cooling hole. An intermediate cooling hole is formed that has an enlarged area from the desired shape to account for deposition of the coating.
Hollow fan blade for a gas turbine engine
A blade includes a hollow metal airfoil having an opening to an internal cavity in a first major surface. A metal cover is adhesively bonded to the airfoil around the opening.
Hybrid airfoil for a gas turbine engine
A hybrid airfoil according to an exemplary aspect of the present disclosure includes, among other things, a leading edge portion made of a first material, a trailing edge portion made of a second material, and an intermediate portion between the leading edge portion and the trailing edge portion made of a non-metallic material. A rib is disposed between the leading edge portion and the intermediate portion.
Vane structure for axial flow turbomachine and gas turbine engine
A vane structure for an axial flow turbomachine that has: a single-vane section of a one-vane structure formed in a part in a vane radial direction; and a tandem-vane section which is formed in a remaining part in the vane radial direction continuously with the single-vane section, and which includes a front vane and a rear vane arranged forward and backward with respect to an airflow that flows through a flow path, respectively.. .
A gas turbine engine including a rotor and a cooling fluid delivery system is presented. The rotor includes a disc and a plurality of blades extending radially therefrom.
Turbine airfoil with optimized airfoil element angles
A turbine airfoil assembly for installation in a gas turbine engine. The airfoil assembly includes an endwall and an airfoil extending radially outwardly from the endwall.
Ni-based alloy, ni-based alloy for gas turbine combustor, member for gas turbine combustor, liner member, transition piece member, liner, and transition piece
A ni-based alloy comprises nitrides, of which an estimated largest size is an area-equivalent diameter of 12 μm to 25 μm, the estimated largest size of the nitrides being determined by calculating an area-equivalent diameter d which is defined as d=a1/2 in relation to an area a of a nitride with a largest size among nitrides present in a measurement field of view area s0 of an observation of the ni-based alloy, repeatedly performing this operation for n times corresponding to a measurement field of view number n to acquire n pieces of data of the area-equivalent diameter d, arranging the pieces of data of area-equivalent diameter d in ascending order into d1, d2, . .