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Gas Turbine Engine patents



      

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




Date/App# patent app List of recent Gas Turbine Engine-related patents
02/04/16
20160036230 
 Synchronous condenser patent thumbnailSynchronous condenser
The present application thus provides a method of operating a synchronous condenser. The method may include the steps of accelerating a gas turbine engine to full speed no load conditions, connecting a generator attached to the gas turbine engine to an electric power grid, turning off a flow of fuel to the gas turbine engine, operating the generator in a synchronous condenser mode, and providing or absorbing reactive power to or from the electric power grid..
General Electric Company


02/04/16
20160033137 
 Laser clad fuel injector premix barrel patent thumbnailLaser clad fuel injector premix barrel
A fuel injector for a gas turbine engine may include a center body disposed about a longitudinal axis, and a premix barrel positioned radially outwardly from the center body to define an annular passageway between the center body and the premix barrel. The annular passageway may extend from an upstream end that is configured to be fluidly coupled to a compressor to a downstream end that is configured to be fluidly coupled to a combustor.
Solar Turbines Incorporated


02/04/16
20160033134 
 Seal in combustor nozzle of gas turbine engine patent thumbnailSeal in combustor nozzle of gas turbine engine
A nozzle for use in a combustor of a combustion turbine engine, the nozzle including: radial sections defined by sidewalls; a gap formed between opposing sidewalls of adjacent ones of the radial sections; a groove formed on each of the sidewalls that define the gap, the grooves positioned correspondingly so to together form a pocket; and a seal having a zigzagging profile disposed within the pocket. The pocket may intercept the gap over a seal length, and the seal may extend longitudinally within the pocket such that the zigzagging profile intersects the gap over the seal length..
General Electric Company


02/04/16
20160033133 
 Combustor nozzles in gas turbine engines patent thumbnailCombustor nozzles in gas turbine engines
A micro-mixer nozzle for use in a combustor of a combustion turbine engine, the micro-mixer nozzle including: a fuel plenum defined by a shroud wall connecting a periphery of a forward tube sheet to a periphery of an aft tubesheet; a plurality of mixing tubes extending across the fuel plenum for mixing a supply of compressed air and fuel, each of the mixing tubes forming a passageway between an inlet formed through the forward tubesheet and an outlet formed through the aft tubesheet; and a wall mixing tube formed in the shroud wall.. .
General Electric Company


02/04/16
20160033130 
 Fuel nozzle for a gas turbine engine patent thumbnailFuel nozzle for a gas turbine engine
A fuel nozzle for a combustor a gas turbine engine includes a flange with a first locator.. .
United Technologies Corporation


02/04/16
20160033129 
 Additive manufactured gas turbine engine combustor liner panel patent thumbnailAdditive manufactured gas turbine engine combustor liner panel
A combustor of a gas turbine engine includes an additively manufactured liner panel with a heat transfer augmentation feature.. .
United Technologies Corporation


02/04/16
20160032937 
 Gas turbine engine axial drum-style compressor rotor assembly patent thumbnailGas turbine engine axial drum-style compressor rotor assembly
A gas turbine engine includes an axial compressor which includes a rotor assembly including a first rotor segment with a first inner rim, a first sealing surface, and a first aft engagement feature, and a second rotor segment positioned aft of the first rotor segment and having a second inner rim, a second sealing surface, and a second inner rim with a second fore engagement feature that is complementary to the first aft engagement feature. The first and second sealing surfaces are complementary to each other, and are bonded together via a transient liquid phase diffusion process.
United Technologies Corporation


02/04/16
20160032865 
 Gas turbine engine ejector patent thumbnailGas turbine engine ejector
An ejector comprises a primary nozzle having an annular wall forming part of an outer boundary of an exhaust portion of a primary flow path of a gas turbine engine. The annular wall has a downstream end defining a plurality of circumferentially distributed lobes.
Pratt & Whitney Canada Corp.


02/04/16
20160032864 
 Gas turbine engine exhaust ejector/mixer patent thumbnailGas turbine engine exhaust ejector/mixer
An ejector/mixer for a gas turbine engine includes an annular wall having upstream end adapted to be fastened to an engine case and a downstream end forming a plurality of lobes. A support member interconnects the lobes, and includes an annular blade located radially inwardly of the bight of the lobes.
Pratt & Whitney Canada Corp.


02/04/16
20160032837 
 Rear mount assembly for gas turbine engine patent thumbnailRear mount assembly for gas turbine engine
A gas turbine engine with a rear mount assembly including link rods interconnecting the bypass duct wall and the core portion and connecting assemblies connected to the bypass duct wall. Each connecting assembly has inner and outer surfaces bordering an opening through which an outer end of a respective link rod extends.
Pratt & Whitney Canada Corp.


02/04/16
20160032835 

Air-driven particle pulverizer for gas turbine engine cooling fluid system


A cooling fluid system for a gas turbine engine includes a structure that provides a fluid passageway. The structure has a wall with an aperture that is in fluid communication with the fluid passageway.
United Technologies Corporation


02/04/16
20160032833 

Thermally conforming acoustic liner cartridge for a gas turbine engine


A cartridge for a fan case of a gas turbine engine includes an inlet acoustic liner section integrated with a thermally conforming liner section.. .
United Technologies Corporation


02/04/16
20160032832 

Gas turbine engine noise reducing nose cone


A fan section for a gas turbine engine includes a fan hub and a nose cone section operatively mounted to the fan hub. The nose cone section includes a noise attenuation feature..
United Technologies Corporation


02/04/16
20160032831 

Spinner aft-extended forward return flange


A spinner for a fan assembly of a gas turbine engine, a method of fabricating a spinner for a fan assembly of a gas turbine engine, and a gas turbine engine are disclosed. The fan section may include a nosecap.
United Technologies Corporation


02/04/16
20160032830 

Gas turbine engine architecture with nested concentric combustor


A gas turbine engine includes an inner annular combustor radially inboard of an outer annular combustor. An outer variable turbine vane array is downstream of the outer annular combustor and an inner variable turbine vane array downstream of the inner annular combustor..
United Technologies Corporation


02/04/16
20160032828 

Gas turbine engine with low stage count low pressure turbine


A gas turbine engine including a core nacelle defined about an engine axis. A fan nacelle is mounted at least partially around the core nacelle to define a fan bypass airflow path for a fan bypass airflow.
United Technologies Corporation


02/04/16
20160032825 

Gas turbine engine with supersonic compressor


A gas turbine engine having a compressor section using blades on a rotor to deliver a gas at supersonic conditions to a stator. The stator includes one or more of aerodynamic ducts that have converging and diverging portions for deceleration of the gas to subsonic conditions and to deliver a high pressure gas to combustors.
Dresser-rand Company


02/04/16
20160032780 

Triple flange arrangement for a gas turbine engine


A flange arrangement for a gas turbine engine includes a case flange between a forward flange and an aft flange.. .
United Technologies Corporation


02/04/16
20160032779 

Castellated latch mechanism for a gas turbine engine


A gas turbine engine includes a fan duct including a fan duct inner structure that surrounds a core engine, a fan case that surrounds a fan, a core engine frame, and at least one mechanism configured to secure a portion of the fan duct inner structure to a portion of the core engine frame. The at least one mechanism includes a castellated arcuate portion mounted to one of the fan duct inner structure and the core engine frame and an inwardly projecting retaining feature mounted to the other of the fan duct inner structure and the core engine frame.
United Technologies Corporation


02/04/16
20160032772 

Self cleaning debris filter for fan drive gear system


A pump system for a gas turbine engine has at least one pump. At least one valve has an outlet and at least one inlet is fluidly connected to the at least one pump.
United Technologies Corporation


02/04/16
20160032771 

Fluid-cooled seal arrangement for a gas turbine engine


A component for a gas turbine engine includes a compartment housing that redirects oil from at least one passage in a rotational component onto a backside of a seal land.. .
United Technologies Corporation


02/04/16
20160032770 

Geared gas turbine engine with oil deaerator and air removal


A gas turbine engine has a fan drive turbine for driving a gear reduction. The gear reduction drives a fan rotor.
United Technologies Corporation


02/04/16
20160032769 

Oil transfer passage arrangement for a shaft of a gas turbine engine


A shaft for a gas turbine engine includes a shaft bore along an axis, a circumferential groove within the shaft bore, a multiple of first axial grooves from said circumferential groove and a multiple of second axial grooves from said circumferential groove.. .
United Technologies Corporation


02/04/16
20160032767 

Gas turbine engine with axial compressor with internal cooling pathways


A gas turbine engine may include an axial high pressure compressor having an air flow pathway positioned between the inner and outer rim of the rotor section. The air flow pathway includes an inlet port, a transition segment, an axial segment, and an outlet port.
United Technologies Corporation


02/04/16
20160032764 

Gas turbine engine end-wall component


An end-wall component of the mainstream gas annulus of a gas turbine engine having an annular arrangement of vanes, the component including a cooling arrangement having ballistic cooling holes (33) through which, in use, dilution cooling air is jetted into the mainstream gas upstream of the vanes to reduce the mainstream gas temperature adjacent the end-wall, wherein the cooling holes are arranged in one or more circumferentially extending rows and wherein the axial position of the cooling holes in the or each row varies.. .
Rolls-royce Plc


02/04/16
20160032763 

Heatshield discourager seal for a gas turbine engine


A gas turbine engine includes a service line interface that extends from an outer surface of a bearing support such that a heat shield is spaced from the outer surface. A method of mounting a heat shield to a gas turbine engine includes trapping a heat shield within a gapped overlap spaced from an outer surface of a bearing support..
United Technologies Corporation


02/04/16
20160032756 

Low noise turbine for geared turbofan engine


A gas turbine engine comprises a fan and a turbine having a fan drive rotor. There is also a second turbine rotor.
Mtu Aero Engines Ag


02/04/16
20160032753 

Gas turbine engine with axial compressor having improved air sealing


A gas turbine engine including an axial high pressure compressor having expansion slots in the outer rim of the rotor section. The expansion slots may be positioned between blades of a rotor segment.
United Technologies Corporation


02/04/16
20160032751 

Reversible blade rotor seal


A rotatable sealing structure for a gas turbine engine includes a first blade and a second blade. A seal is arranged between the blades and has a body that is configured for operative association with the first and second blades in a first orientation and in a second orientation to seal a gap defined between the blades..
United Technologies Corporation


02/04/16
20160032738 

Gas turbine engine blade tip treatment


A fan blade and method of manufacturing a fan blade includes a metallic fan blade body with a crystalline oxidation layer and immersing the crystalline oxidation layer in a solution of ceramic nanosheets in suspension. A fan blade for a gas turbine engine includes a metallic fan blade body having a tip with a crystalline oxidation layer, wherein the crystalline oxidation layer includes pores containing ceramic nanosheets..
United Technologies Corporation


02/04/16
20160032733 

Outer shroud with gusset


A turbine blade comprises an airfoil. An outer shroud at a tip of the airfoil, has a main surface facing the airfoil and forming a first plateau.
Pratt & Whitney Canada Corp.


02/04/16
20160032732 

Gas turbine engine airfoil geometries and cores for manufacturing process


An airfoil for a gas turbine engine includes a body having leading and trailing edges joined by spaced apart pressure and suction sides to provide an exterior airfoil surface defined by a perimeter wall. An interior wall is arranged interiorly and adjacent to the perimeter wall to provide a cooling passage there between.
United Technologies Corporation


02/04/16
20160032731 

Thermal barrier coating inside cooling channels


A rotor for a gas turbine engine according to an exemplary aspect of the present disclosure includes, among other things, a rotor disk rotatable about an axis and a gas path wall coupled to and radially outward of the rotor disk. The gas path wall bounds a radially inward portion of a gas path.
United Technologies Corporation


02/04/16
20160032729 

Composite fan blade


A composite fan blade for a gas turbine engine is disclosed. The fan blade may include a core being made of a first material and a shell enclosing the core.
United Technologies Corporation


02/04/16
20160032728 

Gas turbine engine airfoil


An airfoil of a turbine engine includes 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 tangential stacking offset and a span position that is at least a third order polynomial curve that includes at least one positive and negative slope.
United Technologies Corporation


02/04/16
20160032726 

Gas turbine engine axial compressor rear hub


A gas turbine engine includes an axial high pressure compressor includes a rear hub disposed aft of an aft rotor segment. The rear hub includes an inner surface, an outer surface, and a sealing face, wherein the sealing face is sealingly engaged with the aft rotor segment, and in fluid communication with the cooling channel.
United Technologies Corporation


02/04/16
20160032725 

Methods for optimized engine balancing based on flight data


Methods for balancing rotating machinery, such as gas turbine engines, to minimize vibrations. An optimal engine balance solution is obtained using a hybrid optimization technique based on vibration data from one or more vibration sensors and corresponding influence coefficients which quantify the change in vibration level at the vibration sensors due to a unit increase in unbalance level at unbalance source locations.
The Boeing Company


02/04/16
20160032416 

Gas turbine engine airfoil impingement cooling


A method of manufacturing an airfoil includes the steps of depositing multiple layers of powdered metal onto one another. The layers are joined to one another with reference to cad data relating to a particular cross-section of an airfoil.
United Technologies Corporation


01/28/16
20160025342 

Active 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
20160025038 

Pivot 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


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


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
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
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
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
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
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
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
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


01/21/16
20160016230 

Method of shaping green part and manufacturing method using same


A method of shaping a part in a green state obtained through powder injection molding, including placing a surface of the part in contact with a shaping surface of a setter with at least one section of the surface of the part not conforming to the shaping surface, and locally heating at least one area of each of the at least one section to deform the part until the at least one section conforms to the shaping surface. The part remains in the green state during the local heating.
Pratt & Whitney Canada Corp.


01/14/16
20160010866 

Aerating fuel injector system for a gas turbine engine


An aeration system for a fuel injector system of a gas turbine engine includes a air tank in communication with a fuel injector and method of operation thereof.. .
United Technologies Corporation


01/14/16
20160010795 

Fan blade lubrication


In accordance with one aspect of the disclosure, a lubricant application device for providing lubricant to an airfoil of a gas turbine engine is disclosed. The device may include a container for holding a lubricant, a fluid outlet in fluid communication with the container, a discharge mechanism controlling a flow of the lubricant from the container to the fluid outlet, and an extension tube in fluid communication with the fluid outlet.
United Technologies Corporation


01/14/16
20160010773 

Component mount integrated with tube fitting


A component mount is disclosed which may comprise a tube fitting having first and second ends, a bracket extending from the tube fitting, and a mount extending from the tube fitting. The component mount may be used to mount a line replaceable unit to a casing of a gas turbine engine..
United Technologies Corporation


01/14/16
20160010590 

Nozzle arrangement for a gas turbine engine


A gas turbine engine comprising: a bypass duct having a bypass nozzle; an engine core having a core nozzle; and, a mixer duct defined by a mixer fairing and having a mixer nozzle, wherein the mixer duct is arranged to receive an airflow from the bypass duct through a mixer duct inlet and an airflow from the engine core, when in use, and the geometry of the mixer duct is selectively adjustable by moving the mixer fairing relative to the bypass duct and engine core in use.. .
Rolls-royce Plc


01/14/16
20160010589 

Two-part gas turbine engine


A gas turbine engine propulsion system in which a first propulsive unit has a core engine and a first low pressure turbine arranged to be driven by combustion products from the core engine. The first propulsive unit also has a first fan rotor and a first fan shaft drivingly connecting the first turbine and the first fan rotor.
Rolls-royce Plc


01/14/16
20160010567 

Fuel-air ratio control of gas turbine engines


A turbine engine includes a fan connected to a fan shaft, a combustion chamber, and an electric motor/generator in communication with the fan shaft. A controller is configured to direct power into the electric motor/generator during engine accelerations from steady state such that air flow to the combustion chamber is increased.
Rolls-royce North American Technologies, Inc.


01/14/16
20160010562 

Geared turbofan with integral front support and carrier


A gas turbine engine includes a fan section including a fan hub. A speed reduction device includes a star gear system.
United Technologies Corporation


01/14/16
20160010561 

Gas turbine engine accessory gearbox


An example gas turbine engine includes, among other things, a nacelle having an inner wall providing a bypass duct of a gas turbine engine, and an outer wall; an accessory gearbox is received between the inner wall and the outer wall of the nacelle; and an accessory drive of the accessory gearbox is configured to rotate about an accessory drive axis that is transverse to a central axis of the gas turbine engine.. .
United Technologies Corporation


01/14/16
20160010560 

Sealing features for a gas turbine engine


A blade for a gas turbine engine includes a fixed length member and a floating blade seal that is movable relative to the floating blade seal to change the length of the blade and vary the gap between the blade and an engine housing component.. .
Rolls-royce North American Technologies, Inc.


01/14/16
20160010559 

Finned ignitor grommet for a gas turbine engine


A heat shield for a combustor of a gas turbine engine includes a cold side opposite a hot side, the cold side defines a grommet that surrounds an igniter aperture, the grommet includes a multiple of fins.. .
United Technologies Corporation


01/14/16
20160010555 

Method and collecting pre-diffuser airflow and routing it to combustor pre-swirlers


A gas turbine engine is provided that includes a compressor section, a combustor section with a multiple of pre-swirlers, a diffuser case module, and a manifold. The diffuser case module includes a multiple of struts within an annular flow path from said compressor section to said combustor section, wherein at least one of said multiple of struts defines a mid-span pre-diffuser inlet in communication with said annular flow path.
United Technologies Corporation


01/14/16
20160010554 

Method and handling pre-diffuser airflow for use in adjusting a temperature profile


A gas turbine engine is provided that includes a compressor section, a combustor section, a diffuser case module, and a manifold. The diffuser case module includes a multiple of struts within an annular flow path from said compressor section to said combustor section, wherein at least one of said multiple of struts defines a mid-span pre-diffuser inlet in communication with said annular flow path.
United Technologies Corporation


01/14/16
20160010553 

Method and handling pre-diffuser flow for cooling high pressure turbine components


A gas turbine engine that includes a compressor section, a combustor section, a diffuser case module, and a manifold. The diffuser case module includes a multiple of struts within an annular flow path from said compressor section to said combustor section, wherein at least one of said multiple of struts defines a mid-span pre-diffuser inlet in communication with said annular flow path.
United Technologies Corporation


01/14/16
20160010552 

Method and handling pre-diffuser airflow for cooling high pressure turbine components


A gas turbine engine is provided that includes a compressor section, a combustor section, a diffuser case module, a turbine section, and a manifold. The diffuser case module includes a multiple of struts within an annular flow path from said compressor section to said combustor section, wherein at least one of said multiple of struts defines a mid-span pre-diffuser inlet in communication with said annular flow path.
United Technologies Corporation


01/14/16
20160010550 

Manifold for gas turbine


In various embodiments, a manifold assembly (64) for conducting one or more fluids to a gear assembly (60) in a gas turbine engine (20) is provided. The manifold assembly (64) may comprise a first plate (66) and a second plate (68) that rotatably couple together.
United Technologies Corporation


01/14/16
20160010507 

Retractable exhaust liner segment for gas turbine engines


A retractable exhaust liner segment according to an example of the present disclosure includes, among other things, at least one liner segment extending between a forward end and an aft end. The forward end of the at least one liner segment is configured to overlap an aft end of an engine structure and the aft end of the at least one liner segment is configured to overlap a forward end of an exhaust liner when in an assembled position.
United Technologies Corporation


01/14/16
20160010503 

Instrumentation boss for fan containment case


A method for installing a mounting hole through a wall of a fan case of a gas turbine engine is disclosed. The method may comprise: 1) installing a pilot hole through the wall of the fan case at an angle perpendicular to an outer surface of the wall, 2) inserting a boss through the pilot hole, 3) bonding the boss to the wall of the fan case, and 4) installing the mounting hole through the boss at an off-axis angle with respect to the angle perpendicular to the outer surface of the wall..
United Technologies Corporation


01/14/16
20160010502 

Nacelle compression rods


A compression rod may include a plunger and a spring. A proximal end and a distal end of the compression rod may contact engagement features in a core cowl of a gas turbine engine.
Rohr, Inc.


01/14/16
20160010499 

Lubrication system for a gas turbine engine


A gas turbine engine includes a lubrication system for distributing lubricant throughout the engine. The lubrication system includes a breather assembly that receives air and lubricant from various other components of the lubrication system.
Rolls-royce Corporation


01/14/16
20160010498 

Intercooled compressor for a gas turbine engine


A multi-stage intercooled compressor for a gas turbine engine, including multiple stages of rotating blades and cooling stator vanes, a cooling stator vane including an outer wall that defines an internal coolant fluid passage and has a length along a centerline from a leading edge to a trailing edge of the outer wall, and an internal flow divider wall disposed within the internal passage and extending along the centerline to divide the internal coolant fluid passage into an inflow pathway and an outflow pathway.. .

01/14/16
20160010497 

Cleaning system for a turbofan gas turbine engine


A turbofan gas turbine engine for use in an aircraft includes a fan, an engine core, and a cleaning system. The fan and engine core cooperate to provide thrust for an aircraft when in use but may suffer performance degradation when dirty.
Rolls-royce Corporation


01/14/16
20160010493 

System and control for a gas turbine engine


A system includes plurality of combustors and a distributed flow measurement system coupled to the plurality of combustors. Each combustor of the plurality of combustors includes one or more oxidant passages and one or more fuel passages.
Exxonmobil Upstream Research Company


01/14/16
20160010490 

Fan drive thrust balance


A gas turbine engine according to an exemplary aspect of the present disclosure includes, among other things, a fan section, a shaft including a bearing system, a turbine section in communication with the shaft, a speed change mechanism coupling the fan section to the turbine section and a biasing device configured to apply a biasing force against the shaft.. .
United Technologies Corporation


01/14/16
20160010489 

Variable nozzle for aeronautic gas turbine engine


A variable nozzle is comprised of: an exhaust duct vectoring a flow of the exhaust gas to the aft end; a plurality of primary flaps arranged to define a primary flow path converging toward the aft end, each of the primary flaps being swingably pivoted on the exhaust duct to regulate a degree of opening the primary flow path and including a first section and a second section forming an angle axially outward relative to the first section; and a plurality of secondary flaps arranged to define a secondary flow path in communication with the primary flow path, the secondary flow path being capable of divergent toward the aft end, the secondary flaps being respectively swingably pivoted on the second sections of the primary flaps to regulate a degree of opening the secondary flow path.. .
Ihi Corporation


01/14/16
20160010486 

Aero-actuated vanes


A turbomachinery vane includes a vane body defining a longitudinal axis, a trunnion extending from the vane body and defining a pivot point for pivoting the vane body about the longitudinal axis, and a lock system operatively connected to the trunnion and configured to lock the vane body in a plurality of locked positions. A gas turbine engine includes a turbomachinery component including a row of actuated stators, wherein the actuated stator row includes a plurality of the turbomachinery vanes.
United Technologies Corporation


01/14/16
20160010484 

Ring-shaped compliant support


A ring-shaped compliant support for a gas turbine engine includes, among other things, an annular case, and an adjustment member that will turn relative to the annular case if exposed to thermal energy.. .
United Technologies Corporation


01/14/16
20160010482 

Low leakage multi-directional interface for a gas turbine engine


An interface within a gas turbine engine includes a multiple of segmented components, each with a segment flange with a multiple of apertures, at least one of the multiple of apertures a first slot aperture. A full ring component with a ring flange that defines a multiple ring of apertures, at least one of the multiple of ring apertures a second slot aperture, the second slot aperture transverse to the first slot aperture..
United Technologies Corporation


01/14/16
20160010481 

Gas turbine spindle bolt structure with reduced fretting fatigue


A spindle bolt structure is provided in a gas turbine engine, and includes a pilot region located within a bolt hole extending through a seal disk. The pilot region includes a circumferential pilot ridge located adjacent to a downstream axial face of the seal disk and a circumferential trough portion located between a bolt shoulder and the pilot ridge.
Siemens Energy, Inc.


01/14/16
20160010479 

Modular instrumentation egress seal for a gas turbine engine


A modular egress seal assembly includes an annular plate with an axially extending aperture. A base plate is mountable to the annular plate.
United Technologies Corporation


01/14/16
20160010473 

Cooling hole for a gas turbine engine component


A component for a gas turbine engine according to an exemplary aspect of the present disclosure includes, among other things, a wall having an internal surface and an outer skin, a cooling hole having an inlet extending from the internal surface and merging into a metering section, and a diffusion section downstream of the metering section that extends to an outlet located at the outer skin. The diffusion section of the cooling hole includes a first side diffusion angle, a second side diffusion angle and a downstream diffusion angle at a downstream surface of the diffusion section, the downstream diffusion angle being less than the first side diffusion angle and the second side diffusion angle..
United Technologies Corporation


01/14/16
20160010472 

Coating and coating gas turbine engine component


The present invention provides a protective coating for a gas turbine blade or other component wherein the duplex coating includes an aluminum-bearing coating, such as a diffusion aluminide, formed on a first, relatively higher temperature region of the blade/component and a later-applied chromium-bearing diffusion coating formed on an adjacent relatively lower temperature region of the blade/component subject to hot corrosion in service. The chromium-bearing coating is applied after the aluminum-bearing coating by masking that coating and depositing a metallic chromium coating on the adjacent region followed by diffusing the chromium into the blade/component alloy to form a chromium-enriched diffusion coating thereon..
Howment Corporation


01/14/16
20160010470 

Frangible sheath for a fan blade of a gas turbine engine


In accordance with one aspect of the disclosure, a rotor for a gas turbine engine is disclosed. The rotor may include a rotor disk and a blade extending radially outward from the rotor disk.
United Technologies Corporation


01/14/16
20160010467 

Gas turbine engine component cooling channels


A component according to an exemplary aspect of the present disclosure includes, among other things, a wall, a first channel extending at least partially through the wall to a first outlet, and a second channel adjacent to the first channel and extending to a second outlet. The first channel is configured to communicate a cooling fluid along a first swirl flow path and the second channel is configured to communicate the cooling fluid along a second swirl flow path that is opposite the first swirl flow path..
United Technologies Corporation


01/14/16
20160010466 

Gas turbine engine component with twisted internal channel


A gas turbine engine component includes a component body that defines an internal micro-channel that extends in a lengthwise direction along a reference line. The internal micro-channel extends between a first reference position along the reference line and a second reference position along the reference line.
United Technologies Corporation


01/14/16
20160010465 

Gas turbine engine airfoil leading edge cooling


An example gas turbine engine component includes an airfoil having a leading edge area, a first circuit to cool a first section of the leading edge area, and a second circuit to cool a second section of the leading edge area. The first circuit separate and distinct from the second circuit within the airfoil..
United Technologies Corporation


01/14/16
20160010463 

Gas turbine engine high lift airfoil cooling in stagnation zone


An airfoil for a gas turbine engine includes pressure and suction side walls joined to one another at leading and trailing edges. A stagnation line is located on the pressure side wall aft of the leading edge.
United Technologies Corporation


01/14/16
20160010460 

Pretrenched rotor for gas turbine engine


A gas turbine engine according to an exemplary aspect of the present disclosure includes, among other things, a rotor having a pretrench that receives at least a portion of a tip of a stator, the portion of the tip extending radially into the pretrench.. .
United Technologies Corporation


01/14/16
20160010459 

Spinner for a gas turbine engine


A spinner for use in a gas turbine engine includes a body and an aft ring coupled to the body. The body is symmetrically formed by filament winding around a central axis.
Rolls-royce Corporation




Gas Turbine Engine topics: Gas Turbine, Gas Turbine Engine, Downstream, High Speed, Circulation, Heat Exchanger, Attenuation, Variable Inlet Guide Vanes, Variable Inlet Guide Vane, Guide Vane, Guide Vanes, Inlet Guide Vanes

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