Real Time Touch



new TOP 200 Companies filing patents this week

new Companies with the Most Patent Filings (2010+)




Real Time Touch

Similar
Filing Names

United Technologies Corporation
United Technologies Corporation One Financial Plaza
United Technologies Corporation_20100114
United Technologies Corporation_20100107
United Technologies Corporation_20100121
United Technologies Corporation_20131212
United Technologies Corporation_20100128

United Technologies Corporation patents


Recent patent applications related to United Technologies Corporation. United Technologies Corporation is listed as an Agent/Assignee. Note: United Technologies Corporation may have other listings under different names/spellings. We're not affiliated with United Technologies Corporation, we're just tracking patents.

ARCHIVE: New 2018 2017 2016 2015 2014 2013 2012 2011 2010 2009 | Company Directory "U" | United Technologies Corporation-related inventors


Carbon as an aide for ductile nanocellular foam

A method of fabricating an article includes providing an arrangement of loose nanowires and bonding the loose nanowires in the presence of carbon together into a unitary cellular structure.... United Technologies Corporation

Machining a cooled region of a body

A method is provided for manufacturing a component using a body comprising metal. This method includes: cooling the body to provide at least a cooled region of the body; and machining the cooled region using a tool that contacts the cooled region.... United Technologies Corporation

Aluminum fan blade tip prepared for thermal spray deposition of abrasive by laser ablation

A process of preparing a blade tip for abrasive coating comprising: forming a hydroxide layer on a surface of the blade tip; ablating the hydroxide layer from the surface with a laser; and roughening the surface with the laser after the hydroxide layer ablation.... United Technologies Corporation

Hinged seal using wire mesh

A seal segment includes a flapper seal, a wire mesh acting as a hinge for the flapper seal, and a spring. The flapper seal has a first surface and a second surface. The wire mesh includes a first section connected to the first surface of the flapper seal and a... United Technologies Corporation

Non-contact seal with removal features

An assembly includes a plurality of seal shoes arranged about an axial centerline in an annular array. The assembly also includes a seal base and a plurality of spring elements. The seal base circumscribes the annular array of the seal shoes. A threaded base aperture extends axially through the seal... United Technologies Corporation

Non-contact seal with monolithic/unitary carrier structure

An assembly includes a monolithic carrier structure and a seal assembly. The monolithic carrier structure includes a carrier base and a support ring. The carrier base extends axially along the centerline. The support ring projects radially inward from the carrier base. The seal assembly is nested radially within the carrier... United Technologies Corporation

Multi-circuit buffer system for a gas turbine engine

A gas turbine engine according to an exemplary aspect of the present disclosure includes, among other things, a shaft and first and second bearing structures that support the shaft. Each of the first bearing structure and the second bearing structure includes a bearing compartment that contains a lubricant and a... United Technologies Corporation

Geared turbofan with low spool power extraction

A geared turbofan engine includes a first spool including a first compressor and a first turbine. The first compressor is immediately before a combustor and the first turbine is immediately after the combustor. A second spool includes at least a second turbine disposed axially aft of the first turbine. A... United Technologies Corporation

Gas turbine engine with high speed low pressure turbine section

A gas turbine engine includes a very high speed low pressure turbine such that a quantity defined by the exit area of the low pressure turbine multiplied by the square of the low pressure turbine rotational speed compared to the same parameters for the high pressure turbine is at a... United Technologies Corporation

Nose cone assembly and circulating air in a gas turbine engine

A nose cone assembly for a gas turbine engine and method of circulating air in a gas turbine engine are disclosed. The nose cone assembly includes a nose cone having an aperture communicating air to an interior space of the nose cone and a discharge member communicating the air out... United Technologies Corporation

Gas turbine engine with axial movable fan variable area nozzle

A turbofan engine according to an example of the present disclosure includes, among other things, a fan section including a plurality of fan blades, the plurality of fan blades having a fixed stagger angle and a design angle of incidence, a low pressure turbine driving the plurality of fan blades... United Technologies Corporation

Fiber composite material and preform and fan blade made therefrom

A fiber composite material comprises a polymer matrix, carbon fibers, and non-carbon fibers, wherein the non-carbon fibers have a strain to failure value greater than the strain to failure value of the carbon fibers. Also discussed is a preform comprising the fiber composite material combined in a three dimensionally woven... United Technologies Corporation

Shim for gas turbine engine

A joint for a gas turbine engine includes a first component, a second component, an annular shim disk, and fasteners. The first component has a first ring portion and a first annular radial flange that extends from the first ring portion. The second component has a second ring portion and... United Technologies Corporation

Hydrodynamic seal seat cooling features

A seal seat includes a base having an annular shape, a neck having an annular shape and being radially outward from the base with the neck having an axial length that is less than an axial length of the base, and a head having an annular shape and being radially... United Technologies Corporation

Mixer assembly for a gas turbine engine

A mixer assembly for a gas turbine engine is provided, including a main mixer with fuel injection holes located between at least one radial swirler and at least one axial swirler, wherein the fuel injected into the main mixer is atomized and dispersed by the air flowing through the radial... United Technologies Corporation

Removing material buildup from an internal surface within a gas turbine engine system

A method is provided involving a gas turbine engine system. The method includes configuring a plug within a fluid passage in the gas turbine engine system, where the plug is between first and second portions of the fluid passage. Material is removed from an interior surface of the fluid passage... United Technologies Corporation

Dual investment technique for solid mold casting of reticulated metal foams

A method to manufacture reticulated metal foam via a dual investment solid mold, includes pre-investment of a precursor with a diluted pre-investment ceramic plaster then investing the encapsulated precursor with a ceramic plaster.... United Technologies Corporation

Media containment for iso-grid structure forming

A method of forming an iso-grid structure may include filling multiple pockets of the iso-grid structure with a filler material, attaching a support structure to the perimeter of the iso-grid structure, shaping the iso-grid and support structures, and removing the support structure from the iso-grid structure. The support structure may... United Technologies Corporation

Direct drive aft fan engine

An aircraft engine includes a gas generator, a turbine fluidly connected to the gas generator, and a fan connected to the turbine via a shaft. The fan is positioned aft of the turbine, and the shaft is at least partially disposed in a fan inlet flowpath.... United Technologies Corporation

Cooling hole with enhanced flow attachment

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

Gas turbine engine stator vane baffle arrangement

A method of flowing cooling fluid through a stator vane in a gas turbine engine includes the step of providing an airfoil that has an exterior wall that provides a cooling cavity. The exterior surface has an interior surface that has multiple pin fins that extend therefrom. A baffle is... United Technologies Corporation

Air metering baffle assembly

A baffle assembly includes a collar with a port and a baffle positioned in the port. The baffle includes two ends, a hollow body, and a weld connecting the baffle to the collar, and the collar continuously surrounds the body of the baffle.... United Technologies Corporation

Adjustable blade outer air seal system

Controlling BOAS-to-blade-tip clearances by measuring a blade clearance between a first primary BOAS and a blade with a distance measurement device attached to the first primary BOAS, determining if the measured blade clearance of the first primary BOAS is at a value corresponding to a first predetermined blade clearance, measuring... United Technologies Corporation

Borescope plug

A borescope plug for a gas turbine engine includes a base attachable to a case and defining a base cavity, a shank having a base engagement element at a first end of the shank, and a plug member located at a second end of the shank, the plug member configured... United Technologies Corporation

Localized engine protection from corrosion and contamination

Aspects of the disclosure are directed to a cover configured to substantially conform to a profile of a first assembly of an engine in terms of the dimensions of the first assembly and hermetically seal the first assembly such that a second assembly of the engine that is external to... United Technologies Corporation

Flutter sensing and control system for a gas turbine engine

A gas turbine engine includes a fan section that has a fan. A fan casing surrounds the fan section. A compressor section defines an engine axis. A gear train reduces a rotational speed of the fan relative to a shaft. A low pressure turbine is coupled to the shaft. A... United Technologies Corporation

Flutter sensing and control system for a gas turbine engine

A gas turbine engine includes a fan section that has a fan with a plurality of airfoils, a compressor section, a gear train that reduces a rotational speed of the fan relative to a shaft in operation, a turbine section that has a first turbine and a second turbine, and... United Technologies Corporation

Exhaust duct for turbine forward of fan

A gas turbine engine includes a core engine assembly including a compressor section communicating air to a combustor section where the air is mixed with fuel and ignited to generate a high-energy gas flow that is expanded through a turbine section. The turbine section is coupled to drive the compressor... United Technologies Corporation

Variable preloaded duplex thrust bearing system for a geared turbofan engine

A bearing system for a gas turbine engine includes an outer housing and a first ball bearing assembly disposed radially inward from the outer housing relative a center axis of the outer housing. The bearing system also includes a second ball bearing assembly disposed radially inward from the outer housing... United Technologies Corporation

Mistuned laminate airfoil

A gas turbine engine includes a fan mounting a first group of blades and a second group of blades. The first group of blades and the second group of blades share a profile shape. The first group of blades have a first laminate composition, and the second group of blades... United Technologies Corporation

Micro lattice hybrid composite fan blade

A fan blade includes a lattice structure, a fill, and a structural wrap. The lattice structure defines an airfoil body that has a cavity. The lattice structure defines at least one spar that extends radially from a root of the airfoil body towards a tip of the airfoil body. The... United Technologies Corporation

Fan blade with composite cover

A fan blade assembly for a gas turbine engine includes a blade body, a blade cover secured to the blade body and an adhesive layer to secure the blade cover to the blade body, the adhesive layer configured to set at ambient temperature. A method of forming a fan blade... United Technologies Corporation

Combustor panel for gas turbine engine

A heat shield panel for a gas turbine engine includes a substrate layer having a first substrate surface and a second substrate surface opposite the first substrate surface. The first substrate surface and the second substrate surface define a substrate layer thickness therebetween. One or more thermally protective coating layers... United Technologies Corporation

Abradable material feedstock and methods and manufacture

A method for manufacturing a powder comprises vaporizing a solvent; passing a metallic powder and a polymer powder through the solvent vapor to mix the metallic powder with the polymer powder; and removing the solvent.... United Technologies Corporation

Solid lubricant filled structural matrix

A coating including a structural matrix having a porosity and a solid lubricant that at least partially fills the porosity.... United Technologies Corporation

02/01/18 / #20180030586

Outer airseal abradable rub strip manufacture methods and apparatus

A method for applying an abradable coating, comprises: generating a plasma; introducing a matrix-forming first particulate to the plasma at a first location; introducing a second particulate of an organic particulate and/or salt particulate to the plasma at a second location downstream from the first location to mix with the... United Technologies Corporation

02/01/18 / #20180030597

Coating methods and apparatus

An apparatus for depositing a coating on a part comprises: a chamber; a source of the coating material, positioned to communicate the coating material to the part in the chamber; a plurality of thermal hoods; and means for moving a hood of the plurality of thermal hoods from an operative... United Technologies Corporation

02/01/18 / #20180030842

Additively manufactured component with integral fuel lines passage

An aerospace component includes an augmentor vane and a fuel line additively manufactured within the augmentor vane. A method of manufacture including additively manufacturing an augmentor vane wall that forms an internal volume therein; and additively manufacturing a fuel line within the augmentor vane and extends through the internal volume.... United Technologies Corporation

02/01/18 / #20180030844

Combustor finger seal

An annular finger seal includes a base portion defining a base edge of the annular finger seal and having a center pass-through aperture. The base edge may be substantially continuous. The annular finger seal may also include a finger portion defining a finger edge of the annular finger seal and... United Technologies Corporation

02/01/18 / #20180030846

Gas turbine engine active clearance control system

A gas turbine engine includes a blade having a tip, a blade outer air seal operatively connected to a case assembly, and an active clearance control system disposed on the case assembly. The active control system includes an actuator assembly. The actuator assembly includes a motor assembly and a shaft.... United Technologies Corporation

02/01/18 / #20180030850

Oil debris monitor with sequential coil system and associated algorithms for particle confirmation

A debris monitoring system has a first sensor configured to generate a first signal indicating a presence of a metallic particle in a lubrication system. A second sensor is configured to generate a second signal indicating the presence of a metallic particle in the lubrication system. A signal processor is... United Technologies Corporation

02/01/18 / #20180030851

Systems and methods for assessing the health of a first apparatus by monitoring a dependent second apparatus

Systems and methods for assessing the health of a first apparatus by monitoring a second apparatus are described herein. A method for monitoring a health of a first apparatus may comprise receiving a performance parameter from a second apparatus, wherein performance of the second apparatus is dependent upon the health... United Technologies Corporation

02/01/18 / #20180030892

Inlet cap of an engine

Aspects of the disclosure are directed to an inlet cap, comprising: a first lug slot located proximate a perimeter of the inlet cap, and a second lug slot located proximate the perimeter of the inlet cap and located peripherally adjacent to the first lug slot, where the first lug slot... United Technologies Corporation

02/01/18 / #20180030898

Gas turbine engine fuel system prognostic algorithm

A system and method of calculating a fuel pump life expectancy in a fuel burning engine is provided. The method includes tracking a fuel pump speed of the fuel burning engine, tracking a position value of at least one fuel actuated actuator in the fuel burning engine, and calculating a... United Technologies Corporation

02/01/18 / #20180030925

Gas turbine engine with axial movable fan variable area nozzle

A turbofan engine includes fan section including a plurality of fan blades, a gear train, a low spool including a low pressure turbine and a low pressure compressor, the low pressure turbine driving the plurality of fan blades through the gear train, and a high spool including a high pressure... United Technologies Corporation

02/01/18 / #20180030926

Propulsion system arrangement for turbofan gas turbine engine

A method of designing an engine according to an exemplary aspect of the present disclosure includes, among other things, designing an engine and a nacelle assembly together in an interactive process, the engine including a turbine section configured to drive a fan section and a compressor section. The step of... United Technologies Corporation

02/01/18 / #20180030993

Abradable material

A blade outer airseal comprising a body having: an inner diameter (ID) surface; an outer diameter (OD) surface; a leading end; a trailing end; a metallic substrate; and a coating system atop the substrate along at least a portion of the inner diameter surface. At least over a first area... United Technologies Corporation

02/01/18 / #20180030995

Fan blade with composite cover

A fan blade includes a metallic body, a first composite cover, and a second composite cover. The metallic body may have a first side, a second side, a plurality of first retention slots, and a plurality of second retention slots, in accordance with various embodiments. The first and second retention... United Technologies Corporation

02/01/18 / #20180031002

Annular heatshield

A fan section includes a fan inlet case, fan bearing assembly, and an annular heatshield. The fan bearing assembly may be coupled to the fan inlet case and the annular heatshield may be mounted to the fan inlet case. In various embodiments, the annular heatshield is configured to reduce convective... United Technologies Corporation

02/01/18 / #20180031241

Component with integral wall passage

An aerospace component includes a wall with an integral longitudinal wall passage formed therein, the integral longitudinal wall passage including at least one entrance apertures and at least one exit aperture, the exit aperture transverse to the integral longitudinal wall passage. The aerospace component may be additively manufactured.... United Technologies Corporation

02/01/18 / #20180033129

Systems and methods for indexing and detecting components

Systems and methods for defect detection and position control are described herein. A method of performing position control on members in a device may comprise applying, by a deposition device, a fiducial mark to a first member of the device, and receiving, by a processing unit, from an image capture... United Technologies Corporation

01/25/18 / #20180021848

System and process to provide self-supporting additive manufactured ceramic core

A core for use in casting an internal cooling circuit within a gas turbine engine component, the core including a core body with an outer skin in which a core body additively manufacturing binder is locally eliminated. A method of manufacturing a core for casting a component, including casting a... United Technologies Corporation

01/25/18 / #20180022459

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. Products of combustion pass from the combustion section over a turbine section to drive the fan section and main compressor sections. A gearbox is... United Technologies Corporation

01/25/18 / #20180022463

Pre-start motoring synchronization for multiple engines

An aspect includes a system for pre-start motoring synchronization for multiple engines of an aircraft. The system includes a first engine starting system of a first engine and a controller. The controller is operable to synchronize a motoring time of the first engine starting system with one or more other... United Technologies Corporation

01/25/18 / #20180022464

Cross engine coordination during gas turbine engine motoring

A system is provided for cross engine coordination during gas turbine engine motoring. The system includes a first gas turbine engine of a first engine system, a first air turbine starter of the first engine system, a first starter air valve of the first engine system, and a controller. The... United Technologies Corporation

01/25/18 / #20180022465

Alternating starter use during multi-engine motoring

A system is provided for alternating starter use during multi-engine motoring in an aircraft. The system includes a first engine starting system of a first engine and a controller. The controller is operable to coordinate control of the first engine starting system to alternate use of power from a power... United Technologies Corporation

01/25/18 / #20180022466

Method and variable supplemental airflow to cool aircraft components

A cooling system for an aircraft has at least one moveable member configured to cover an opening formed within an aircraft outer skin. An actuator moves the at least one moveable member between a fully open position where external atmosphere air can be directed through the opening to an internal... United Technologies Corporation

01/25/18 / #20180023024

Auxiliary emergency protective lubrication system for metal mechanical components

An auxiliary lubricant comprising a composition, the comprising intermediate molecular weight surfactant-functionalized nanoparticles dispersed in a base oil.... United Technologies Corporation

01/25/18 / #20180023396

Rotor blade for a gas turbine engine

A rotor blade for a gas turbine engine includes a blade extending from a root and a contoured tip portion at a first end of the blade. The first end is opposite the root. The contoured tip portion includes a first sloped region and a second sloped region. The second... United Technologies Corporation

01/25/18 / #20180023407

Gas turbine engine turbine vane baffle and serpentine cooling passage

An airfoil for a gas turbine engine includes pressure and suction side walls joined to one another at leading and trailing edges. The pressure and suction side walls surround an airfoil cavity and provide an exterior airfoil surface. A baffle is arranged in the airfoil cavity and includes a supply... United Technologies Corporation

01/25/18 / #20180023413

Multi-engine coordination during gas turbine engine motoring

A system is provided for multi-engine coordination of gas turbine engine motoring in an aircraft. The system includes a controller operable to determine a motoring mode as a selection between a single engine dry motoring mode and a multi-engine dry motoring mode based on at least one temperature of a... United Technologies Corporation

01/25/18 / #20180023414

Oil debris monitoring for failure detection isolation

A method of detecting debris within a lubricant stream, the method includes generating data indicative of debris and sensor system functionality within a lubricant stream with a sensor system. The data is communicated to a controller. Features calculated from the data are indicative of a debris within the lubricant stream.... United Technologies Corporation

01/25/18 / #20180023417

Multi-ply heat shield assembly with integral band clamp for a gas turbine engine

A heat shield assembly for a gas turbine engine includes a first heat shield ply assembly defined about an axis; a second heat shield ply assembly defined about the axis, the second heat shield ply assembly receivable at least partially over the first heat shield assembly and a band clamp... United Technologies Corporation

01/25/18 / #20180023418

Engine bearing damper with interrupted oil film

Aspects of the disclosure are directed to an engine oil damper comprising: a bearing support, and a housing radially outward from the bearing support and co-axial with the bearing support, where at least one oil flow restrictor is formed with respect to at least one of the bearing support and... United Technologies Corporation

01/25/18 / #20180023420

Assembly with mistake proof bayoneted lug

An assembly for rotational equipment with an axial centerline. The assembly includes a first component and a second component. Each of the components extends circumferentially around and axially along the centerline. The first component includes a flange and a lug aperture extending axially through the flange. The second component includes... United Technologies Corporation

Patent Packs
01/25/18 / #20180023474

Boundary layer cooling air for embedded engine

A gas turbine engine has an inner housing surrounding a compressor, a combustor, and a turbine, with an inlet leading into the compressor, and a cooling sleeve defined radially outwardly of the inlet to the compressor for receiving cooling air radially outward of the compressor inlet. The cooling sleeve extends... United Technologies Corporation

01/25/18 / #20180023475

Gas turbine engine with heat pipe for thermal energy dissipation

A gas turbine engine includes a core nacelle and a core engine disposed in the core nacelle. The core engine includes at least a compressor section, a combustor section, and a turbine section, which define a core flowpath. A bypass duct is radially outwards of the core nacelle. A component... United Technologies Corporation

01/25/18 / #20180023479

Air supply control during motoring of a gas turbine engine

A system for motoring a gas turbine engine of an aircraft is provided. The system includes an air turbine starter, a starter air valve operable to deliver compressed air to the air turbine starter, and a controller. The controller is operable to control motoring of the gas turbine engine, detect... United Technologies Corporation

01/25/18 / #20180023484

Speed control during motoring of a gas turbine engine

A system is provided for speed control during motoring of a gas turbine engine of an aircraft. The system includes an air turbine starter, a starter air valve operable to deliver compressed air to the air turbine starter, and a controller. The controller is operable to adjust the starter air... United Technologies Corporation

01/25/18 / #20180023509

Thrust reverser structure mounted to fan case

A gas turbine engine has a core engine and a fan. A pivoting D-door structure includes a pivoting inner D-door portion and an outer D-door portion, which is axially moveable relative to the inner D-door portion between a stowed and thrust reverse position. A fan case surrounds the fan. Cascades... United Technologies Corporation

01/25/18 / #20180023511

Efficient, low pressure ratio propulsor for gas turbine engines

A gas turbine engine includes a bypass flow passage that has an inlet and defines a bypass ratio in a range of approximately 8.5 to 13.5. A fan is arranged within the bypass flow passage. A first turbine is a 5-stage turbine and is coupled with a first shaft, which... United Technologies Corporation

01/25/18 / #20180023576

Twin centrifugal single spool engine

An auxiliary power unit may comprise a twin centrifugal compressor including a first blade. A turbine may be disposed aft of the twin centrifugal compressor. The turbine may include a second blade. The first blade comprises a first material and the second blade comprises a second material. The first material... United Technologies Corporation

01/25/18 / #20180023684

Oil direction control baffle

A baffle for a gear may comprise a baffle wall and a baffle outlet, the baffle wall having a peripheral portion at least partially defining a channel, the channel extending circumferentially around an axial centerline, the channel configured to receive lubricant through a slot, the slot extending circumferentially around the... United Technologies Corporation

01/25/18 / #20180026446

Seamless transition between grid connected and islanded modes

A power balancing assembly according to an exemplary aspect of the present disclosure includes, among other things, at least one sensor operable to detect a first electrical parameter and a second electrical parameter relating to a first portion of a power grid. An energy storage device is coupled to a... United Technologies Corporation

01/18/18 / #20180016024

Electric heating for fuel system components

A fuel system for use with a gas turbine engine with a fuel flow and an oil flow includes a fuel-oil cooler in fluid communication with the fuel flow and the oil flow, the fuel-oil cooler to transfer heat between the fuel flow and the oil flow, a fuel filter... United Technologies Corporation

01/18/18 / #20180016672

Method of chromizing an article including internal passages of the article

A method for chromizing an article includes applying a slurry to an article. The slurry has active chromium and a residue-removal agent. The method also includes heating the article and slurry to diffuse chromium from the slurry into the article. The heating leaves a residue on the article with the... United Technologies Corporation

01/18/18 / #20180016912

Gas turbine engine airfoil

A gas turbine engine include a combustor section arranged between a compressor section and a turbine section. A fan section has multiple fan blades. A geared architecture couples the fan section to the turbine section or compressor section. The fan blades include an airfoil that has pressure and suction sides.... United Technologies Corporation

01/18/18 / #20180017067

Clearance control between rotating and stationary structures

Aspects of the disclosure are directed to a system of an engine, comprising: a clearance control thermal ring, and a seal ring, where a radial gap with respect to an axial centerline of the engine is formed between a radial end of the clearance control thermal ring and a facing... United Technologies Corporation

01/18/18 / #20180017165

Coated seal housing

A seal housing is disposed to support an axially facing seal segment, and comprises a substrate and a coating. The substrate has an inner annular surface, an axially facing substrate surface, and a corner feature at an intersection of the inner annular surface and the axially facing substrate surface. The... United Technologies Corporation

01/18/18 / #20180017168

Multi-ply seal ring

A multi-ply seal ring includes an inner seal ring and an outer seal ring. The inner seal ring includes a plurality of discrete inner ring segments disposed circumferentially about an axis in an annular array. The inner ring segments are arranged end-to-end within the annular array. The inner seal ring... United Technologies Corporation

Patent Packs
01/18/18 / #20180017260

Combustor anti-surge retention system

A combustor assembly for a gas turbine engine comprises a vane support ring; an annular combustor extending around a central axis and being located radially inwards of the vane support ring, the annular combustor including an aft end, a forward end with at least one opening through which at least... United Technologies Corporation

01/18/18 / #20180017378

Visual depth measurement gage

Systems and methods for depth measurement are described herein. A depth measurement device may comprise a first light source configured to direct a first beam of light, a second light source configured to direct a second beam of light, and a mirror. The mirror may be for viewing at least... United Technologies Corporation

01/11/18 / #20180009058

Machining using cryogenic cooling on a cutting tool while heating a work piece

The invention improves machining methods by using cryogenic cooling techniques in combination with a heat source to simultaneously cool a cutting tool while heating a work piece to make the work piece more pliable while increasing efficiency and/or longevity of the cutting tool.... United Technologies Corporation

01/11/18 / #20180009071

Iso-grid composite component

An iso-grid composite component according to an exemplary aspect of the present disclosure includes a spacer transverse to a uni-tape ply bundle, the spacer interrupted by the uni-tape ply bundle.... United Technologies Corporation

01/11/18 / #20180010213

Enhance ductility of gamma titanium aluminum alloys by reducing interstitial contents

A process to increase ductility includes utilizing γ-TiAl alloy as a base alloy and reducing at least one interstitial of the base alloy to create an alloy compositions with extremely low interstitials (Eli).... United Technologies Corporation

01/11/18 / #20180010232

Coating system and process

A coating system for coating a part (10), such as a turbine blade or vane, has a mask (14) positioned adjacent to a first portion (16) of the part (10) to be coated and a mechanism (30) for moving the mask (14) relative to the part (10). The mechanism (30)... United Technologies Corporation

01/11/18 / #20180010239

Vapor deposition apparatus and method

A vapor deposition apparatus includes a chamber configured to operate at vacuum and at least one crucible in the chamber. The crucible is configured to receive an ingot, a feeder operable to move the ingot with respect to the at least one crucible, and a heater in the chamber and... United Technologies Corporation

01/11/18 / #20180010459

Low energy wake stage

The leading edge, the trailing edge, or both may be axially offset for a portion of the airfoils in a disk. By offsetting the airfoils, the downstream wake energy to the next stage of airfoils may be decreased. By staggering airfoils which are offset with airfoils that are not offset,... United Technologies Corporation

01/11/18 / #20180010465

Cooling hole with shaped meter

A gas turbine engine component having a cooling passage includes a first wall defining an inlet of the cooling passage, a second wall generally opposite the first wall and defining an outlet of the cooling passage, a metering section extending downstream from the inlet, and a diffusing section extending from... United Technologies Corporation

01/11/18 / #20180010468

Enhanced temperature capability gamma titanium aluminum alloys

An alloy composition including a γ-TiAl alloy with a sustained temperature capability of about 1500 F. An alloy composition including a γ-TiAl alloy with an oxygen level of about 100 wppm and between about 1500-3000 appm carbon. An alloy composition including a γ-TiAl alloy with an alpha stabilizer.... United Technologies Corporation

01/11/18 / #20180010470

Ring stator

A stator assembly for a gas turbine engine includes an annular outer shroud, an annular inner shroud radially spaced from the outer shroud and a plurality of stator vanes extending from the outer shroud to the inner shroud. A volume of potting is located at the inner shroud and at... United Technologies Corporation

01/11/18 / #20180010472

Segmented stator assembly

A stator assembly for a gas turbine engine includes an arcuate outer shroud, an arcuate inner shroud radially spaced from the outer shroud and a plurality of stator vanes extending from the outer shroud to the inner shroud. A volume of potting is located at the inner shroud and at... United Technologies Corporation

01/11/18 / #20180010473

Attachment faces for clamped turbine stator of a gas turbine engine

An airfoil fairing shell for a gas turbine engine includes an airfoil section between an outer vane endwall and an inner vane endwall, at least one of the outer vane endwall and the inner vane endwall including a radial attachment face, a suction side tangential attachment face, a pressure side... United Technologies Corporation

01/11/18 / #20180010480

Bowed rotor sensor system

According to an aspect, a bowed rotor sensor system for a gas turbine engine is provided. The bowed rotor sensor system includes a bowed rotor sensor operable to transmit a sensing field in an observation region and receive a signal indicative of a gap between an air seal and a... United Technologies Corporation

01/11/18 / #20180010482

Tuned mass damper for tubes

A tuned mass damper for reducing vibration on a component includes a shaft connector member configured to be coupled to the component and a cable termination member. The tuned mass damper also includes at least one cable coupled to the shaft connector member and to the cable termination member such... United Technologies Corporation

01/11/18 / #20180010483

Cooling system for a gaspath component of a gas powered turbine

A gaspath component includes a flowpath body. A cooling plenum is disposed within the flowpath body. The cooling plenum includes a first region configured to receive a cooling flow and a second region configured to expel the cooling flow from the flowpath body. A metering obstruction is positioned between the... United Technologies Corporation

01/11/18 / #20180010484

Manufacturing methods for multi-lobed cooling holes

A method for producing a diffusion cooling hole extending between a wall having a first wall surface and a second wall surface includes forming a cooling hole inlet at the first wall surface, forming a cooling hole outlet at the second wall surface, forming a metering section downstream from the... United Technologies Corporation

01/11/18 / #20180010519

Nacelle anti ice system

An anti-icing system of a nacelle inlet of an engine of an aircraft includes first and second direct acting valves and first and second control valve assemblies fluidly connected to the nacelle inlet. The first direct acting valve includes a first inlet, outlet, valve chamber, and piston. The first piston... United Technologies Corporation

01/11/18 / #20180010550

Gas turbine engine with axial movable fan variable area nozzle

A method of designing a turbofan engine according to an exemplary aspect of the present disclosure includes, among other things, providing a fan section including a plurality of fan blades, providing a low pressure turbine driving the plurality of fan blades through a gear train, providing a fan nacelle and... United Technologies Corporation

01/11/18 / #20180010551

Geared gas turbine engine

A gas turbine engine includes a fan section that includes a fan rotatable about an engine axis. A compressor section includes a low pressure compressor rotatable about the engine axis. A turbine section includes a fan drive turbine for driving the fan and the low pressure compressor. A speed reduction... United Technologies Corporation

01/11/18 / #20180010681

Ring gear mounting arrangement with oil scavenge scheme

An epicyclic gear train for a turbine engine includes a gutter with an annular channel. A rotating structure includes a ring gear that has an aperture that is axially aligned with the annular channel. Axially spaced apart walls extend radially outward relative to the rotating structure to define a passageway.... United Technologies Corporation

01/11/18 / #20180013959

Method for turbine component qualification

A method for evaluating a turbine component includes inducing a thermal response of the component at an initial time, capturing a two-dimensional infrared image of the thermal response of the component with a thermal imaging device, wherein the two-dimensional infrared image comprises a plurality of infrared image pixels, generating a... United Technologies Corporation








ARCHIVE: New 2018 2017 2016 2015 2014 2013 2012 2011 2010 2009



###

This listing is an abstract for educational and research purposes is only meant as a recent sample of applications filed, not a comprehensive history. Freshpatents.com is not affiliated or associated with United Technologies Corporation in any way and there may be associated servicemarks. This data is also published to the public by the USPTO and available for free on their website. Note that there may be alternative spellings for United Technologies Corporation with additional patents listed. Browse our Agent directory for other possible listings. Page by FreshPatents.com

###