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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


 new patent  Universal power electronic cell for distributed generation

A method of configuring a power conversion cell for a distributed power system according to an example of the present disclosure includes: importing one or more software modules onto a controller of a conversion device configured to control power conversion with one or more of the modules selected based on one or more of a load or source device, and the results of a software simulation.. . ... United Technologies Corporation

 new patent  Detection of crystallographic properties in aerospace components

Aspects of the disclosure are directed to an analysis of a material of a component. A radiation source is activated to transmit radiation to the component. ... United Technologies Corporation

 new patent  Combustor liner panel shell interface for a gas turbine engine combustor

A combustor for a gas turbine engine including a combustor liner support shell with a furrow formed therein; a forward liner panel mounted to the support shell via a multiple of studs, the forward liner panel including a forward liner panel rail the extends into the furrow; and an aft liner panel mounted to the support shell via a multiple of studs downstream of the forward liner panel, the aft liner panel including an aft liner panel rail that extends into the furrow.. . ... United Technologies Corporation

 new patent  Combustor liner panel with non-linear circumferential edge for a gas turbine engine combustor

A combustor for a gas turbine engine including a forward liner panel mounted to a support shell via a multiple of studs, the forward liner panel including an aft non-linear circumferential edge and an aft liner panel mounted to the support shell via a multiple of studs, the aft liner panel including a forward non-linear circumferential edge that is complementary to the aft non-linear circumferential edge.. . ... United Technologies Corporation

 new patent  Non-planar combustor liner panel for a gas turbine engine combustor

A combustor for a gas turbine engine including a liner panel mounted to a support shell via a multiple of studs, the liner panel including a forward section and an aft section that defines an arcuate surface section therebetween in the axial profile between the forward section and the aft section.. . ... United Technologies Corporation

 new patent  Non-planar combustor liner panel for a gas turbine engine combustor

A combustor for a gas turbine engine including a liner panel mounted to a support shell via a multiple of studs, the liner panel including a forward section and an aft section that defines an angle therebetween in the axial profile between the forward section and the aft section.. . ... United Technologies Corporation

 new patent  Multilayer abradable coating

A multilayer abradable coating includes at least one first abradable layer; and at least one second abradable layer, wherein the first abradable layer and the second abradable layer have different properties related to erosion resistance.. . ... United Technologies Corporation

 new patent  High compressor build clearance reduction

An aspect includes a system including a high compressor of a gas turbine engine having a ratio of a cold-rotor build clearance to a span between 0.7% and 7%. The cold-rotor build clearance is defined for a plurality of rotor blades of the high compressor with respect to an engine casing assembly interior surface of the high compressor, and the span is defined as a gap between a rotor disk of the high compressor and the engine casing assembly interior surface of the high compressor for at least a last two stages of the high compressor closest to a combustor section of the gas turbine engine. ... United Technologies Corporation

 new patent  Gas turbine engine front architecture

A turbine engine is disclosed that includes a fan case surrounding a fan rotatable about an axis. A core is supported relative to the fan case by support structure arranged downstream from the fan. ... United Technologies Corporation

 new patent  Efficient, low pressure ratio propulsor for gas turbine engines

A gas turbine engine includes a bypass flow passage and a core flow passage. The bypass flow passage defines a bypass ratio in a range of approximately 8.5 to 13.5. ... United Technologies Corporation

 new patent  Gas turbine engine with geared architecture

In one exemplary embodiment, a gas turbine engine includes a bypass flow ratio greater than about ten. A fan supported on a fan shaft having a plurality of fan blades and a low fan pressure ratio of less than 1.45 measured across the fan blades alone. ... United Technologies Corporation

 new patent  Gas turbine engine compressor arrangement

A gas turbine engine includes, among other things, a fan, a core engine, a bypass passage, and a bypass ratio defined as the volume of air passing into the bypass passage compared to the volume of air passing into the core engine, the bypass ratio being greater than or equal to 10. A gear arrangement drives the fan. ... United Technologies Corporation

 new patent  Ceramic matrix composite turbine exhaust case for a gas turbine engine

A gas turbine engine according to an example of the present disclosure includes, among other things, a turbine case extending along a turbine axis and a cmc turbine exhaust case mounted to the turbine case. The cmc turbine exhaust case includes a cmc core nacelle aft portion, a cmc tail cone connected to the cmc core nacelle aft portion, and a multiple of cmc turbine exhaust case struts extending between the cmc core nacelle aft portion and the cmc tail cone. ... United Technologies Corporation

 new patent  Engine cases and associated flange

Aspects of the disclosure are directed to a system for an engine having an axial centerline, comprising: a diffuser case, a turbine case, and a turbine vane support, where the diffuser case and the turbine case are coupled to one another via a substantially radially oriented flange, where the turbine vane support includes a heat shield for the flange, and where the turbine vane support includes a radially outward projecting tab that couples to the turbine case via a radial interference fit.. . ... United Technologies Corporation

08/16/18 / #20180230854

 new patent  Turbine engine lubrication system with wash flow filter

An assembly is provided for a turbine engine. This turbine engine assembly includes a turbine engine component and a lubrication system. ... United Technologies Corporation

08/16/18 / #20180230852

 new patent  System and method for controlling dual starter air valve

A system may comprise a sensor configured to measure a characteristic of an engine component. A valve assembly may have an airflow outlet in fluid communication with the engine component. ... United Technologies Corporation

08/16/18 / #20180230842

 new patent  Outer airseal abradable rub strip

A blade outer airseal has a body comprising: an inner diameter (id) surface; an outer diameter (od) surface; a leading end; and a trailing end. The airseal body has a metallic substrate and a coating system atop the substrate along at least a portion of the inner diameter surface. ... United Technologies Corporation

08/16/18 / #20180230840

 new patent  Two piece stator inner shroud

An inner shroud segment may include an inner housing and an outer housing. The inner housing may have a radial curve centered relative to an axis with a radial wall and a bottom wall that define a first channel. ... United Technologies Corporation

08/16/18 / #20180230814

 new patent  Airfoil cooling structure

An airfoil may comprise an airfoil body having a leading edge, a trailing edge, an inner diameter end wall and an outer diameter end wall. A first cooling structure may be disposed within the airfoil body. ... United Technologies Corporation

08/16/18 / #20180230804

 new patent  Rotor disk boss

The present disclosure provides devices and methods related to rotor disk bosses. For example, a rotor disk assembly comprises a first rotor disk, wherein the first rotor disk comprises a web, disposed between a rim and a bore. ... United Technologies Corporation

08/16/18 / #20180230602

 new patent  Coated combustor panel shell for a gas turbine engine combustor

A combustor for a gas turbine engine including a support shell with a shell coating applied thereto and a multiple of liner panels circumferentially mounted within the support shell via a multiple of studs, each of the multiple of liner panels having a liner coating applied thereto.. . ... United Technologies Corporation

08/16/18 / #20180229303

 new patent  Control for powder fusion

A powder processing machine includes a work bed, a powder deposition device operable to deposit powder in the work bed, at least one energy beam device operable to emit an energy beam with a variable beam power and direct the energy beam onto the work bed with a variable beam scan rate to melt and fuse regions of the powder, and a controller operable to dynamically control at least one of the beam power or the beam scan rate to change how the powder melts and fuses. The controller is configured to determine whether an instant set of process parameters falls within a defect condition or a non-defect condition and adjust at least one of the beam power or the beam scan rate responsive to the defect condition such that the instant set of process parameters falls within the non-defect condition.. ... United Technologies Corporation

08/16/18 / #20180229302

 new patent  Adaptive control for powder fusion

A powder processing machine includes a work bed, a powder deposition device operable to deposit layers of powder in the work bed, an energy beam device operable to emit an energy beam with a variable beam power and scan the energy beam in a path across the powder in the work bed with a variable beam scan rate to melt and fuse regions of the powder, a sensor operable to detect process characteristics in the work bed by location in the work bed during scanning of the energy beam and produce signals representative of the process characteristics and locations, and a controller in communication with the sensor to receive the signals. The controller is configured to identify anomalies in the process characteristics and responsively adjust at least one of the beam power or the beam scan rate at the locations of the anomalies.. ... United Technologies Corporation

08/09/18 / #20180226222

Part temperature measurement device

. . A system for measuring a temperature of a rotating workpiece comprises a deposition chamber, a crucible within the deposition chamber, an energy source, a drive system, a temperature sensor, first and second sensor wires, a dynamic electrical connection, and a control system. The crucible is configured to hold a deposition feedstock material. ... United Technologies Corporation

08/09/18 / #20180224353

System and method for blade health monitoring

A system and method for blade health monitoring is provided. The system and method may improve health diagnostic capabilities for engine blades, thus reducing the risk of blade failure during engine operation, increasing the useful life of each engine blade, and allowing for more accurate maintenance and/or inspection schedules of engine blades. ... United Technologies Corporation

08/09/18 / #20180224043

Threaded fitting for tube

A tubing assembly for fluid delivery to a bearing system may comprise a fitting having an inner surface defining an inner flow path and having an outer surface defining a first mating surface. A first tube may be coupled to the fitting. ... United Technologies Corporation

08/09/18 / #20180224042

Tube fitting

A fitting for a double wall tube may comprise an inner portion defining an inner fluid passage. An outer portion may be disposed concentrically around the inner portion and may define an outer fluid passage between the outer portion and the inner portion. ... United Technologies Corporation

08/09/18 / #20180223741

Bleed valve with neutral or closing bias

A compressor assembly may include a compressor case disposed about an axis. A bleed valve may be disposed about the compressor case to translate axially and/or rotationally relative to the compressor case. ... United Technologies Corporation

08/09/18 / #20180223738

Starter air valve system with dual electromechanical controls

According to an aspect, a system includes a starter air valve in fluid communication with an air turbine starter to drive motoring of a gas turbine engine responsive to a compressed air flow from a compressed air source. The system also includes a variable-position electromechanical device operable to adjust positioning of the starter air valve and a discrete-position electromechanical device operable to adjust positioning of the starter air valve and limit a motoring speed of the gas turbine engine below a resonance speed of the gas turbine engine responsive to a pulse width modulation control based on a failure of the variable-position electromechanical device.. ... United Technologies Corporation

08/09/18 / #20180223736

External mixing chamber for a gas turbine engine with cooled turbine cooling air

A gas turbine engine comprises a compressor section and a turbine section, the compressor section having a last compressor stage. High pressure cooling air is tapped from a location downstream of the last compressor stage and passed through a heat exchanger. ... United Technologies Corporation

08/09/18 / #20180223734

Fitting for multiwall tube

A mid-turbine frame for a gas turbine engine may comprise a bearing system including a bearing housing. A first tube may define a first fluid passage configured to carry a first fluid to the bearing system. ... United Technologies Corporation

08/09/18 / #20180223693

Ceramic matrix composite turbine exhaust assembly for a gas turbine engine

A turbine exhaust assembly for a gas turbine engine according to an example of the present disclosure includes, among other things, a turbine exhaust case comprised of cmc material and attachable to a turbine case, a tail cone comprised of cmc material that has a leading edge and a trailing edge, and an exhaust mixer comprised of cmc material and coupled to the turbine exhaust case. The exhaust mixer has a plurality of lobes arranged about the tail cone to define an exhaust flow path. ... United Technologies Corporation

08/09/18 / #20180223691

Case flange with stress reducing features

A gas turbine engine and a flange are disclosed. The gas turbine engine includes a case, and a flange coupled to the case, the flange including a flange body, a fastener hole formed through the flange body, the fastener hole configured to receive a fastener, a radial slot formed through the flange body, wherein the radial slot is adjacent to the fastener hole, the radial slot defines a first portion of the flange body and a second portion of the flange body, and the radial slot prevents transfer of a hoop stress between the first portion and the second portion.. ... United Technologies Corporation

08/09/18 / #20180223690

Non-contacting seals for geared gas turbine engine bearing compartments

A gas turbine engine includes a fan, a compressor section, a combustor, and a turbine section. The engine also includes a rotating element and at least one bearing compartment including a bearing for supporting the rotating element, a seal for resisting leakage of lubricant outwardly of the bearing compartment and for allowing pressurized air to flow from a chamber adjacent the seal into the bearing compartment. ... United Technologies Corporation

08/09/18 / #20180223684

Thrust rating dependent active tip clearance control system

Disclosed is an active tip clearance control system (atccs) for a gas turbine engine, having an electronically controlled regulating valve directing cooling airflow to a turbine case, and an engine electronic control (eec), controlling the electronically controlled regulating valve, wherein the eec controls the electronically controlled regulating valve to regulate cooling airflow according to a selected target blade tip clearance schedule, and wherein the selected target blade tip clearance schedule is selected before or after an engine cycle, from of a plurality of target blade tip clearance schedules, each correlating to one of a plurality of thrust rating applications for the engine.. . ... United Technologies Corporation

08/09/18 / #20180223682

Multiwall tube and fitting for bearing oil supply

A multiwall tubing assembly for fluid delivery to a bearing system may comprise a first tube defining an inner fluid passage configured to carry a first fluid. A second tube may be disposed around the first tube and may define an outer fluid passage between the first tube and the second tube. ... United Technologies Corporation

08/09/18 / #20180223678

Abrasive tip blade manufacture methods

A method is disclosed for manufacturing a blade tip coating. The blade tip coating (152) comprising an abrasive (156) and a matrix (154). ... United Technologies Corporation

08/09/18 / #20180223677

Cutting blade tips

A blade includes a blade body extending from a blade root to an opposed blade tip surface along a longitudinal axis. The blade body defines a pressure side and a suction side. ... United Technologies Corporation

08/09/18 / #20180223676

Airfoil turn caps in gas turbine engines

Turn caps for airfoils of gas turbine engines including cavity sidewalls, a first turn cap divider extending between the cavity sidewalls and defining a turning cavity between the first turn cap divider and the cavity sidewalls, and a second turn cap divider disposed radially inward within the turning cavity. A first turning path is defined between the first turn cap divider and the second turn cap divider and a second turning path is defined radially inward of the second turn cap divider and a merging chamber is formed in the turn cap wherein fluid flows through the first turning path and the second turning path are merged, the merging chamber, the first turning path, and the second turning path forming the turning cavity.. ... United Technologies Corporation

08/09/18 / #20180223668

Spoked rotor for a gas turbine engine

A rotor for a gas turbine engine includes a plurality of blades which extend from a rotor disk at an interface, where the interface is defined along a spoke. A spool for a gas turbine engine includes the rotor disk, the plurality of blades with the interface defined along the spoke radially inboard of a blade platform, a rotor ring axially adjacent to the rotor disk, and a plurality of core gas path seals which extend from the rotor ring. ... United Technologies Corporation

08/09/18 / #20180222805

Toughened bond layer and method of production

According to one embodiment of this disclosure, a coating includes a plurality of elongated reinforcing materials. The coating includes a bond coat in which a first portion of a first elongated reinforcing material is embedded. ... United Technologies Corporation

08/09/18 / #20180222026

Methods and tools for pressing a ring seal into a component

Methods and tools are provided for pressing a ring seal into a component. In one method, a tool is anchored to the component. ... United Technologies Corporation

08/09/18 / #20180221943

Axisymmetic single crystal shot tube for high temperature die casting

A die casting system includes a die including a plurality of die components that define a die cavity, a single crystal shot tube in fluid communication with the die cavity, and a shot tube plunger tip moveable within the shot tube to communicate a charge of a molten or semi-molten material into the die cavity. The system further includes a vacuum chamber that applies a vacuum to render a die casting process wherein at least a portion of the die is positioned within the vacuum chamber.. ... United Technologies Corporation

08/02/18 / #20180217585

Sensor data fusion for prognostics and health monitoring

A method includes converting time-series data from a plurality of prognostic and health monitoring (phm) sensors into frequency domain data. One or more portions of the frequency domain data are labeled as indicative of one or more target modes to form labeled target data. ... United Technologies Corporation

08/02/18 / #20180217026

Methods and systems for estimating residual useful life of a rolling element bearing

Estimating residual useful life of a rolling element bearing in an operating gas turbine engine is provided. A processor receives a vibration signal from a vibration sensor. ... United Technologies Corporation

08/02/18 / #20180216626

Aluminum brazing of hollow titanium fan blades

A fan blade includes first and second titanium alloy portions that are secured to one another with an aluminum alloy braze that contains manganese. The first titanium alloy portion includes ribs, a root, and at least a portion of an exterior airfoil contour of the fan blade. ... United Technologies Corporation

08/02/18 / #20180216538

Aircraft bleed system

A method of controlling an aircraft bleed may include the steps of monitoring a temperature of a precooled airflow exiting a precooler, and determining a status of a wing anti-ice system of an aircraft. The wing anti-ice system may be configured to receive the precooled airflow from the precooler. ... United Technologies Corporation

08/02/18 / #20180216537

Gas turbine start system to enable rotor thermal stabilization with backup bleed bypass cooling mode

A system is provided comprising: a starter air valve in fluid communication with an air turbine starter to drive motoring of a gas turbine engine responsive to a compressed air flow from a compressed air source; a manual override operably connected to the starter air valve, the manual override is operable to open the starter air valve a select percentage by moving the manual override to a detent engaged position, wherein the select percentage is operable to allow enough airflow to achieve the maximum allowed motoring speed of the gas turbine engine; and a pressure regulating bleed valve in fluid communication with the starter air valve, the pressure regulating bleed valve operable to bleed a portion of the compressed air flow to regulate a motoring speed of the gas turbine engine in response to detection of the manual override in a detent engaged position.. . ... United Technologies Corporation

08/02/18 / #20180216535

Heat pipe cooling of geared architecture

A thermal management system for a geared architecture of a gas turbine engine includes an evaporator portion located at the geared architecture and configured to exchange thermal energy with the geared architecture via boiling of a volume of heat transfer fluid flowing therethrough and a condenser portion located at a fan bypass flowpath of the gas turbine engine to reject thermal energy from the volume of heat transfer fluid into the fan bypass flowpath. One or more fluid pathways extend from the evaporator portion to the condenser portion to convey the volume of heat transfer fluid therebetween.. ... United Technologies Corporation

08/02/18 / #20180216531

Lubrication of epicyclic gear system for gas turbine engine

An epicyclic gear system includes a sun gear, a ring gear, and two or more star gear assemblies enmeshed between the sun gear and the ring gear. Each star gear assembly includes a star gear and a journal bearing supportive of the star gear. ... United Technologies Corporation

08/02/18 / #20180216530

Bypass valve system state indication

A fluid system may comprise a fluid passage comprising a passage inlet and a passage outlet, through which fluid may flow by entering the passage inlet as an inlet flow and exiting the passage outlet as an outlet flow; a bypass valve comprising a bypass inlet and a bypass outlet, the bypass inlet being in fluid communication with the passage inlet, wherein the bypass valve further comprises a piston coupled to a spring; and a position sensor coupled to the bypass valve and configured to detect a position of the piston in the bypass valve. The spring may retain the piston in a rest position, and the spring and the piston may be configured to block the fluid from passing through the bypass outlet in response to the inlet flow exerting a pressure below a bypass pressure threshold.. ... United Technologies Corporation

08/02/18 / #20180216483

Gas turbine engine forward bearing compartment architecture

A gas turbine engine includes a front center body case structure. A geared architecture is at least partially supported by the front center body case structure. ... United Technologies Corporation

08/02/18 / #20180216482

Gas turbine engine forward bearing compartment architecture

A gas turbine engine includes a front center body case structure. A geared architecture is at least partially supported by the front center body case structure. ... United Technologies Corporation

08/02/18 / #20180216478

Wear resistant coating, method of manufacture thereof and articles comprising the same

An abrasive coating for a substrate comprises a strike layer is formed on a substrate top surface; a base layer is coupled to the strike layer; a tack layer is coupled to the base layer, wherein the tack layer is configured to adhere first grit particles to the base layer; a plurality of first grit particles are adapted to be coupled to the tack layer, a plurality of second grit particles are placed between each of the plurality of first grit particles, the second grit particles having a nominal size smaller than the first grit particles; and an overplate layer comprising a matrix material is bonded to the tack layer; the matrix material envelops the second grit particles and bonds and partially surrounds the first grit particles, wherein the first grit particles extend above the overplate layer.. . ... United Technologies Corporation

08/02/18 / #20180216473

Hybrid airfoil cooling

An airfoil may comprise an airfoil body having a leading edge and a trailing edge. A heat pipe may be disposed within the airfoil. ... United Technologies Corporation

08/02/18 / #20180216472

Turbine blade with slot film cooling

A component for a gas turbine engine, the component having: a cooling slot located on a surface of the component, the cooling slot being defined by a plurality of diffuser portions each extending from a respective one of a plurality of cooling openings providing cooling fluid to the cooling slot.. . ... United Technologies Corporation

08/02/18 / #20180216237

System and method for applying abrasive grit

A method for forming an abrasive surface includes utilizing an energy source to form a melt pool layer in a substrate and applying abrasive grit into the melt pool layer. A method for forming an abrasive surface including applying an abrasive grit to a substrate and utilizing an energy source to form a melt pool layer in the substrate without disturbing the abrasive grit such that the abrasive grit becomes embedded in the melt pool layer.. ... United Technologies Corporation

08/02/18 / #20180215670

Ceramic article and method therefor using particle infiltration and preceramic polymer infiltration

A method of fabricating a ceramic article includes providing a porous body that includes a plurality of fiber bundles that has an intra-bundle porosity and an inter-bundle porosity, infiltrating the intra-bundle porosity and the inter-bundle porosity with a mixture of particles in a liquid carrier, the particles having an average size selected with respect to at least the intra-bundle porosity, removing the liquid carrier from the porous body to deposit the particles in the intra-bundle porosity and in the inter-bundle porosity, infiltrating a preceramic polymer into a remaining intra-bundle porosity and a remaining inter-bundle porosity, and thermally converting the preceramic polymer to a ceramic material.. . ... United Technologies Corporation

08/02/18 / #20180214965

Spherical articulating fixture

A fixture includes a base with a bottom and a rim, a clamp with an exterior in a shape of a portion of a clamp sphere and a component space that is wholly within the clamp sphere, wherein the clamp is positioned such that the clamp exterior is in contact with the rim.. . ... United Technologies Corporation

08/02/18 / #20180214941

Detection of blockage in internal passages of gas turbine engine components

A method of forming a component includes the steps of placing a core into a mold and pouring a component material around the core. The component material is allowed to solidify. ... United Technologies Corporation

07/26/18 / #20180211336

Classification of gas turbine engine components and decision for use

A method of determining a use for substantially the same gas turbine engine components and comprises the steps of receiving manufacturing information about a plurality of gas turbine engine components; classifying each of the plurality of gas turbine engine components into at least two categories, with a first category being components closer to a specification than a second category; and recommending a suggested future use for the first category on aircraft that will operate in more challenging flight conditions and for the second category on aircraft that will operate in less challenging flight conditions. A system is also disclosed.. ... United Technologies Corporation

07/26/18 / #20180211061

Data filtering for data request workflow system

A data request workflow system comprises a vehicle operational data. A file processing system receives the vehicle operational data. ... United Technologies Corporation

07/26/18 / #20180210923

Data request workflow system

A data request workflow system comprises vehicle operational data. A file delivery request comprises a data request for a subset of the vehicle operational data. ... United Technologies Corporation

07/26/18 / #20180209652

Fuel 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

07/26/18 / #20180209471

Self-anti-rotating dual lock washer

A disclosed lock washer includes a first opening spaced apart from a second opening for receiving fasteners and preventing rotation. A first set of tabs is associated with the first opening and a second set of tabs is associated with the second opening. ... United Technologies Corporation

07/26/18 / #20180209379

Low pressure ratio fan engine having a dimensional relationship between inlet and fan size

According to an example embodiment, a gas turbine engine assembly includes, among other things, a fan section including a fan, the fan including a plurality of fan blades, a diameter of the fan having a dimension d that is based on a dimension of the fan blades, each fan blade having a leading edge, and a forward most portion on the leading edges of the fan blades in a first reference plane, a turbine section including a high pressure turbine and a low pressure turbine, the low pressure turbine driving the fan, a nacelle including an inlet portion forward of the fan, a forward edge on the inlet portion in a second reference plane, and a length of the inlet portion having a dimension l measured along an engine axis between the first reference plane and the second reference plane. A dimensional relationship of l/d is no more than 0.45.. ... United Technologies Corporation

07/26/18 / #20180209350

Advanced geared gas turbine engine

A gas turbine engine comprises a fan rotor driven by a fan drive turbine, the fan drive turbine also rotating with one of a ring gear, an intermediate gear carrier, and a sun gear. A first compressor is driven by another of the ring gear, the intermediate gear carrier, and the sun gear. ... United Technologies Corporation

07/26/18 / #20180209343

Intercooled cooling air system with bypass

An intercooled cooling system for a gas turbine engine includes a heat exchanger in fluid communication with a cooling airflow source directed through the heat exchanger and an auxiliary compressor fluidly coupled to the heat exchanger via a discharge duct to compress the cooling airflow exiting the heat exchanger. A compressor discharge pathway directs a first portion of the cooling airflow from the auxiliary compressor to a first cooling location of the gas turbine engine, and a bypass pathway is fluidly coupled to the discharge duct between the heat exchanger and the auxiliary compressor to direct a second portion of the cooling airflow to a second cooling location of the gas turbine without passing through the auxiliary compressor.. ... United Technologies Corporation

07/26/18 / #20180209342

Gas turbine engine with heat pipe system

A gas turbine engine includes a rotor section proximate to a combustor section, where the rotor section is subject to bowing effects due to thermal differences and heat transfer at engine shutdown. The gas turbine engine also includes a heat pipe system. ... United Technologies Corporation

07/26/18 / #20180209339

Simplified engine bleed supply with low pressure environmental control system for aircraft

An environmental control system includes a low pressure tap at a location on a first compressor section of a main compressor section. The low pressure tap communicates airflow to a first passage leading to a downstream outlet. ... United Technologies Corporation

07/26/18 / #20180209298

Gas turbine engine case mount with vibration damping

An assembly is provided for a gas turbine engine. This assembly includes a mount, a component and a fastener assembly attaching the component to the mount. ... United Technologies Corporation

07/26/18 / #20180209290

Gas turbine seal

A labyrinth seal includes a first annular member positioned on a center axis and a second annular member disposed circumferentially around the first annular member. A seal land is disposed on one of the first annular member and the second annular member. ... United Technologies Corporation

07/26/18 / #20180209287

Internally cooled engine components

A component of a gas turbine engine is provided. The component may include an external surface with a skin cavity adjacent the external surface. ... United Technologies Corporation

07/26/18 / #20180209286

Trailing edge pressure and flow regulator

A gas turbine engine component comprises a body having a leading edge, a trailing edge, and a radial span. One internal channel in the body provides an upstream supply pressure. ... United Technologies Corporation

07/26/18 / #20180209279

Apparatus and method for masking under platform areas of airfoil components

A fixture for masking a gas turbine engine blade, the blade having a root, a platform and an airfoil, the platform having inner and outer surfaces and peripheral faces extending between the surfaces, the fixture including a base with a receptacle for receiving the root of the blade; a removable sidewall mountable to the base to form a masking box with the receptacle that shields the root; a first removable z plane detail mountable to the base, the first removable z plane detail providing a first electrical contact point to the root; and a second removable z plane detail mountable to the removable sidewall, the second removable z plane detail providing a second electrical contact point to the root. . ... United Technologies Corporation

07/26/18 / #20180207461

Fire suppression system with multi-directional pass through nozzle

A fire suppression system for a gas turbine engine includes a fire suppressant delivery circuit, a first nozzle and a multi-directional nozzle. The fire suppressant delivery circuit includes and extends between an upstream inlet and a downstream distal end. ... United Technologies Corporation

07/19/18 / #20180205276

Internal mount permanent magnet attachment for electric machine

A rotor of an electric machine includes a rotor core including a rotor central core and at least one intermediate core element. A plurality of permanent magnets are located between the rotor central core and the at least one intermediate core element. ... United Technologies Corporation

07/19/18 / #20180205275

Surface mount permanent magnet attachment for electric machine

A rotor of an electric machine includes a rotor core having a plurality of axially-stacked rotor laminations, and a plurality of permanent magnets. The plurality of permanent magnets are first permanent magnets secured at the core outer circumferential surface of the rotor core and are made of a first permanent magnet material with a first magnetic orientation. ... United Technologies Corporation

07/19/18 / #20180202557

Multi-flowpath fluid control valve

An assembly includes a valve housing and a valve element such as a poppet valve. The valve housing includes a tubular duct and an annular valve seat disposed within the tubular duct. ... United Technologies Corporation

07/19/18 / #20180202461

Two-piece multi-surface wear liner

A liner assembly for placement between a mounting foot of a platform and a case of a gas turbine engine includes first and second annular liner segments configured to move independently of each other. The first annular liner segment is configured to be mounted on at least a portion of a radially outward surface of the mounting foot. ... United Technologies Corporation

07/19/18 / #20180202449

Jem stator outer platform sealing and retainer

A system for retaining stators and reducing air leakage in a gas turbine engine having an axis includes a stator having an inner platform, an outer platform, a low pressure side, a high pressure side, and at least one foot, and designed to turn air. The system also includes a case positioned radially outward from the stator and having at least one recess designed to interface with the at least one foot to resist movement of the stator relative to the case. ... United Technologies Corporation

07/19/18 / #20180202369

Gas turbine engine for long range aircraft

A gas turbine engine comprises a fan for delivering air into a bypass duct as bypass flow, into a core housing as core flow, with the core housing containing an upstream compressor rotor and a downstream compressor rotor. An overall pressure ratio is defined across the upstream and downstream compressor rotors. ... United Technologies Corporation

07/19/18 / #20180202368

Gas turbine engine with intercooled cooling air and dual towershaft accessory gearbox

An exemplary gas turbine engine assembly includes a first spool having a first turbine operatively mounted to a first turbine shaft, and a second spool having a second turbine operatively mounted to a second turbine shaft. The first and second turbines are mounted for rotation about a common rotational axis within an engine static structure. ... United Technologies Corporation

07/19/18 / #20180202367

Gas turbine engine dual towershaft accessory gearbox assembly with a transmission

A gas turbine engine assembly includes a turbine section having first and second turbines mounted for rotation about a common rotational axis within an engine static structure, first and second turbine shafts coaxial with one another and to which the first and second turbines are respectively operatively mounted, first and second towershafts respectively coupled to the first and second turbine shafts, an accessory drive gearbox mounted to the engine static structure, the accessory drive gearbox including a first gear train and a second gear train, the first towershaft extending into a housing and coupled to the first gear train, the second towershaft extending into the housing and coupled to the second gear train, a hydraulic pump, a transmission coupling the hydraulic pump to the first gear train, the transmission transitionable between a first mode where the hydraulic pump is driven at a first speed relative to the first towershaft, a second mode where the hydraulic pump is driven at a different, second speed relative to the first towershaft, and a third mode where the hydraulic pump is driven at a different, third speed relative to the first towershaft.. . ... United Technologies Corporation

07/19/18 / #20180202366

Gas turbine engine dual towershaft accessory gearbox assembly with a transmission

A gas turbine engine assembly includes a turbine section having first and second turbines mounted for rotation about a common rotational axis within an engine static structure, first and second turbine shafts coaxial with one another and to which the first and second turbines are respectively operatively mounted, first and second towershafts respectively coupled to the first and second turbine shafts, an accessory drive gearbox mounted to the engine static structure, the accessory drive gearbox including a first set of gears and a second set of gears, the first towershaft extending into a housing and coupled to the first set of gears, the second towershaft extending into the housing and coupled to the second set of gears, an electric machine, and a transmission coupling the electric machine to the first set of gears, the transmission transitionable between a first mode where the electric machine is driven at a first speed relative to the first towershaft, and a second mode where the electric machine is driven at a different, second speed relative to the first towershaft.. . ... United Technologies Corporation

07/19/18 / #20180202365

Hollow-wall heat shield for fuel injector component

A fuel injector component includes a monolithic body devoid of joints from manufacturing, an elongate void, and a plurality of bores. The monolithic body has a first surface and a second surface. ... United Technologies Corporation

07/19/18 / #20180202363

Cooled gas turbine engine cooling air with cold air dump

A high pressure compressor has a downstream most end. A housing surrounds the compressor section and a turbine section. ... United Technologies Corporation

07/19/18 / #20180202362

Injection cooled cooling air system for a gas turbine engine

A gas turbine engine includes an engine core having a compressor section, a combustor fluidly connected to the compressor section, and a turbine section fluidly connected to the combustor section. At least one compressor bleed connects a compressor flowpath with a first cooled cooling air path. ... United Technologies Corporation

07/19/18 / #20180202359

Jem lock for threaded in place nosecone or spinner

A lock for securing a nosecone having first threading to an inlet case having second threading and for use with a gas turbine engine having an axis includes an annular ring designed to be positioned about the first threading. The lock also includes a tab extending radially from the annular ring, and having a ramped circumferential end and an angled circumferential end such that the ramped circumferential end passes over a detent of the inlet case in response to the nosecone being fastened to the inlet case and the angled circumferential end engages with the detent to resist unfastening of the nosecone from the inlet case.. ... United Technologies Corporation

07/19/18 / #20180202321

Rotatable vanes

A gas turbine engine, having an engine central longitudinal axis, includes at least one of a vane support, a vane stage, a blade outer air seal support, and a blade outer air seal. At least one of the vane support, the vane stage, the blade outer air seal support, and the blade outer air seal is rotatable about the engine central longitudinal axis. ... United Technologies Corporation

07/19/18 / #20180202310

Gas turbine engine dual towershaft accessory gearbox and starter generator assembly

An exemplary gas turbine engine assembly includes a transmission coupling a starter generator assembly to a first set of gears. The transmission is transitionable between a first mode where the starter generator assembly is driven at a first speed relative to the second towershaft, and a second mode where the starter generator assembly is driven at a different, second speed relative to the second towershaft.. ... United Technologies Corporation

07/19/18 / #20180202307

Passive tip clearance control with variable temperature flow

A clearance control system for a gas turbine engine comprises a blade outer air seal mounted on a carrier. At least one blade is rotatable about an engine axis. ... United Technologies Corporation

07/19/18 / #20180202306

Compact advanced passive tip clearance control

A section of a gas turbine engine includes a rotor blade designed to rotate about an axis. The section also includes a case positioned radially outward from the rotor blade and extending circumferentially about the axis. ... United Technologies Corporation

07/19/18 / #20180202304

Constant speed 2 piece ring seal arrangement

A carbon ring for a seal assembly in a gas turbine engine includes an outer face extending circumferentially around a center axis of the carbon ring. The carbon ring also includes an inner face extending around the center axis and disposed radially inward from the outer face. ... United Technologies Corporation

07/19/18 / #20180202299

Fan blade with anode and method for galvanic corrosion mitigation

A blade for a gas turbine engine. The blade having: an airfoil formed from a first material; a protective sheath disposed on a leading edge of the airfoil, the protective sheath being formed from a second material, the first material being galvanically incompatible with the second material and the first material being less noble than the second material; a non-conductive material disposed between the protective sheath and the airfoil so that they are electrically isolated from each other; a sacrificial anode in contact with the blade, wherein the sacrificial anode is formed from a third material that is less noble than the first material such that it will corrode before the first material if the non-conductive material disposed between the protective sheath and the airfoil is compromised and the first material and the second material are no longer electrically isolated from each other.. ... United Technologies Corporation

07/19/18 / #20180202297

Tip leakage flow directionality control

An airfoil according to an example includes, among other things, a suction sidewall and a pressure sidewall. A tip wall extends from a leading edge to a trailing edge and joins respective outer ends of the suction and pressure sidewalls. ... United Technologies Corporation

07/19/18 / #20180202294

Trailing edge configuration with cast slots and drilled filmholes

A gas turbine engine component comprises a body having a leading edge and a trailing edge. At least one internal channel is formed within the body, wherein the channel includes an inlet to direct cooling flow into the body. ... United Technologies Corporation

07/19/18 / #20180200961

Method for producing void-free additively manufactured components

A method of additive manufacturing of a component includes cutting a plurality of sheets, each sheet corresponding to a respective cross-section of the component, tack welding the sheets to one another to form a stack, arranging the stack in a mold, and spark plasma sintering the tack-welded stack of sheets to reduce vacancies and dislocations between adjacent sheets of the stack.. . ... United Technologies Corporation

07/19/18 / #20180200798

Grain size control in laser based additive manufacturing of metallic articles

An additively manufactured alloy component has a first portion formed of the alloy and having a first grain size, and a second portion formed of the alloy and having a second grain size smaller than the first grain size. In an embodiment, the alloy component is an alloy turbine disk, the first portion is a rim region of the alloy turbine disk, and the second portion is a hub region of the alloy turbine disk. ... United Technologies Corporation

07/19/18 / #20180200755

Cold spray system with variable tailored feedstock cartridges

A feedstock cartridge for a cold spray system including at least one powder; and a binder that interconnects at least two particles of the at least one powder.. . ... United Technologies Corporation

07/12/18 / #20180195463

Flow path routing within a gas turbine engine

A method of communicating flow through a gas turbine engine having multiple flow paths according to an exemplary embodiment of the present disclosure includes moving core flow along a core flow path from a compressor section to an exhaust section, selectively communicating a first amount of bypass flow from a bypass flow path defined by a bypass duct to the exhaust section or a second amount of bypass flow from the bypass flow path to the exhaust section, the first amount different than the second amount.. . ... United Technologies Corporation

07/12/18 / #20180195440

Oil loss protection for a fan drive gear system

A fan drive gear system includes at least one intermediate gear that includes an axial gear passage for receiving and conveying a fluid suitable for cooling and/or lubricating. At least a first axial end of the intermediate gear includes a first fluid storage trap for capturing fluid entering and/or exiting the gear passage and storing the fluid therein during powered operation of the fan drive gear system. ... United Technologies Corporation

07/12/18 / #20180195415

Carbon seal spring retention

A seal assembly for a turbine engine extends along a center axis and includes a seal support and a seal carrier configured to translate relative the seal support. A seal is connected to the seal carrier and a spring is disposed between the seal support and the seal carrier. ... United Technologies Corporation

07/12/18 / #20180195413

Gas turbine engine oil tank with integrated packaging configuration

A gas turbine engine includes a fan case radially outwardly of a core compartment. A compressor section is located within an engine core compartment and includes a front mount flange and an aft mount flange. ... United Technologies Corporation

07/12/18 / #20180195412

Lubricating fluid damped anti-rotational systems

A lubricating fluid damped anti-rotational system is provided comprising a pawl carrier having an axis of rotation and a radial aperture, a pawl pivotably mounted to the pawl carrier on a pivot joint, the pawl having a contact portion and a counterweight portion, a lubricating fluid jet configured to propel a lubricating fluid through the radial aperture toward the contact portion.. . ... United Technologies Corporation

07/12/18 / #20180195410

Vented tangential on-board injector for a gas turbine engine

An on-board injector that delivers discharge air toward a turbine rotor of a gas turbine engine includes a second wall spaced form a first wall to define an annular inlet about an engine longitudinal axis and a multiple of airfoil shapes between the first wall and the second wall to segregate discharge air from the annular inlet, and a multiple of bypass apertures each along a radial axis transverse to the engine longitudinal axis through each of the multiple of airfoil shapes and the respective first wall, the second wall.. . ... United Technologies Corporation

07/12/18 / #20180195402

Disposable fan platform fairing

A fan assembly for a gas turbine engine is disclosed. The fan assembly may include a rotor, a plurality of airfoils extending radially from the rotor, and a platform surrounding the rotor and including a surface that defines a flow path between the plurality of airfoils. ... United Technologies Corporation

07/12/18 / #20180195397

Airfoil turn caps in gas turbine engines

Airfoils having hollow bodies defining first and second airfoil cavities and having inner and outer diameter ends, a first airfoil platform at one end of the hollow body having a gaspath surface and a non-gaspath surface, wherein the hollow body extends from the gaspath surface. A first cavity opening is formed in the non-gaspath surface of the platform to fluidly connect to the first airfoil cavity and a second cavity opening in the platform is fluidly connected to the second airfoil cavity. ... United Technologies Corporation

07/12/18 / #20180195393

High temperature compliant metallic elements for low contact stress ceramic support

A ceramic component retention system includes a metallic component, a ceramic component, and at least one spring element arranged between the metallic component and the ceramic component. The metallic component has a first coefficient of thermal expansion, and the ceramic component has a second coefficient of thermal expansion. ... United Technologies Corporation

07/12/18 / #20180195192

Pulse plated abrasive grit

A method for forming an abrasive surface includes applying an electric current through a plating solution so as to cause an abrasive grit to be deposited onto a workpiece and varying a waveform of the electric current while building up a matrix material at least partially around the abrasive grit.. . ... United Technologies Corporation

07/12/18 / #20180194981

Method to fabricate high temperature composite

A method of fabricating a ceramic component includes processing a hybrid matrix blend formed of a ceramic precursor and a glass powder to form a hybrid matrix composite component. A polymer-derived ceramic component including a hybrid matrix composite formed of a hybrid matrix blend including at least one of a ceramic precursor and a conversion char, and a glass powder.. ... United Technologies Corporation

07/12/18 / #20180194695

Method to fabricate high temperature composite with integrated barrier coating

A method of fabricating a ceramic component includes hot pressing a composite component with a glass powder/filler cover mixture to form a consolidated glass-based coating on the composite component.. . ... United Technologies Corporation

07/12/18 / #20180193863

Integrated multicoat automatic pause resume circuit

The present disclosure sets forth an automated apparatus and method for applying gas plasma coatings to aircraft engine parts. The process and apparatus employ a plurality of sensors which continually monitor various process parameters associated with the coating process. ... United Technologies Corporation

07/05/18 / #20180187982

Tube assembly

A tube assembly that may be for a fuel nozzle of a fuel system of a gas turbine engine may have a first tube defining a first flowpath along a centerline, a second tube generally spaced radially outward from the first tube with a first void located between and defined by the first and second tubes, and a support structure located in the first void and extending between the first and second tubes. The support structure is constructed and arranged to minimize or eliminate thermal conduction between the tubes. ... United Technologies Corporation

07/05/18 / #20180187831

Self-retaining oil nozzle

An oil nozzle assembly includes a nozzle body and a nozzle insert. The nozzle body includes a main portion, a tip portion, and a lip. ... United Technologies Corporation

07/05/18 / #20180187770

Oil quieting direction control baffle

A baffle includes a disk, a rim, a peripheral portion, and an outlet. The rim is connected to and circumferentially surrounds a portion of the disk. ... United Technologies Corporation

07/05/18 / #20180187769

Gear with fluid control dam and apertures

Aspects of the disclosure are directed to a gear comprising: gear teeth, a cone wall having an interior surface that forms a chamber, where the gear teeth extend circumferentially from a distal end of the cone wall, a dam that extends radially inward on the interior surface and is axially disposed between the cone wall and the gear teeth, and at least one aperture formed in the cone wall to allow fluid on the interior surface to exit the chamber, where the at least one aperture is located a first distance from the gear teeth along a length of the gear and the dam is located a second distance from the gear teeth along the length of the gear, and where the first distance is greater than the second distance.. . ... United Technologies Corporation

07/05/18 / #20180187724

Shaft interlock

A shaft interlock system may have an a interlocking piston that translates a movable locking apparatus configured to interface with a turbine shaft having a fixed locking apparatus. The movable locking apparatus may engage and disengage the fixed locking apparatus. ... United Technologies Corporation

07/05/18 / #20180187639

Chemical scavenging component for a fuel system

A chemical scavenging component includes a porous body that has a radical-scavenging material. The radical-scavenging material has a composition of, by weight, greater than 50% of cerium oxide that is chemically active with regard to oxygen-containing radicals.. ... United Technologies Corporation

07/05/18 / #20180187629

Exhaust stream mixer

An exhaust nozzle for a turbine engine includes multiple daisy style corrugations arranged circumferentially about the exhaust nozzle. Each of the daisy style corrugations has a radially inner base portion and multiple lobes protruding radially outward from the base portion.. ... United Technologies Corporation

07/05/18 / #20180187605

Systems and methods involving multiple torque paths for gas turbine engines

A turbofan engine includes a fan, a compressor section, a combustor in fluid communication with the compressor section, a turbine section in fluid communication with the combustor, a shaft configured to be driven by the turbine section and coupled to the compressor section through a first torque load path, and a speed reduction mechanism configured to be driven by the shaft through a second torque load path separate from the first load path for rotating the fan.. . ... United Technologies Corporation

07/05/18 / #20180187602

Intercooled cooling air

A gas turbine engine includes a plurality of rotating components housed within a compressor section and a turbine section. A first tap is connected to the compressor section and configured to deliver air at a first pressure. ... United Technologies Corporation

07/05/18 / #20180187562

Blade platform with damper restraint

A blade having: a root; a platform located between the root and the blade, wherein the platform defines a cavity; a damper restraint retaining a lateral edge of a damper seal received in the cavity, wherein the lateral edge of the damper seal extends between a first end portion and an opposing second end portion of the damper seal, the first end portion and the second end portion extend towards the root when the damper seal is located in the cavity and wherein the damper restraint extends along and adjacent to a portion of the lateral edge of the damper seal.. . ... United Technologies Corporation

07/05/18 / #20180187559

Blade platform with damper restraint

A blade for a gas turbine engine is disclosed herein. The blade having: a root; a platform located between the root and the blade, wherein the platform defines a cavity; a damper restraint located at a peripheral edge of the platform, wherein the damper restraint is a raised feature extending along at least a portion of the peripheral edge of the platform.. ... United Technologies Corporation

07/05/18 / #20180187558

Blade platform with chamfer

A blade for a gas turbine engine is provided. The blade having: a root; a platform located between the root and the blade, wherein the platform defines a cavity; and a chamfer located on opposing peripheral edges of the platform.. ... United Technologies Corporation

07/05/18 / #20180187554

Platform cooling core for a gas turbine engine rotor blade

A rotor blade according to an exemplary aspect of the present disclosure includes, among other things, a platform, an airfoil that extends from the platform, a first cooling core that extends at least partially inside the airfoil, a second cooling core inside of the platform and a first cooling hole that extends between a mate face of the platform and the second cooling core.. . ... United Technologies Corporation

06/28/18 / #20180180119

Damped anti-rotational systems

A damped anti-rotational system is provided comprising a pawl carrier having an axis of rotation, a pawl pivotably mounted to the pawl carrier on a pivot joint, the pawl having a contact portion and a counterweight portion, a stop pin axially disposed in the pawl carrier and configured to contact the contact portion of the pawl in response to radially inward movement of the pawl, wherein the stop pin is mounted to the pawl carrier at a forward portion of the stop pin and an aft portion of the stop pin, wherein a forward o ring is disposed on the forward portion of the stop pin and an aft o ring is disposed on the aft portion of the stop pin.. . ... United Technologies Corporation

06/28/18 / #20180179959

Duct blocker seal assembly for a gas turbine engine

A seal system for a gas turbine engine includes a cover plate with a radial flange; a seal carrier adjacent the cover plate; an outer compliant seal supported by the seal carrier; an inner compliant seal supported by the seal carrier, the inner compliant seal engaged with the radial flange; and a spring between the cover plate and the seal carrier.. . ... United Technologies Corporation

06/28/18 / #20180179641

Multi-wall deposited thin sheet structure

A method for forming a metallic structure having multiple layers includes providing a main tool having a main formation surface corresponding to a desired shape of a first layer of material. The method also includes depositing the first layer of material on the main formation surface using a cold-spray deposition technique. ... United Technologies Corporation

06/28/18 / #20180179640

Reinforcement of a deposited structure forming a metal matrix composite

A method for forming a reinforced metallic structure includes providing a tool having a formation surface corresponding to a desired structure shape of the reinforced metallic structure. The method also includes positioning a plurality of fibers on the formation surface of the tool. ... United Technologies Corporation

06/28/18 / #20180179639

Modular tooling for a deposited structure

A method for forming a sheet structure includes depositing at least one layer of material on a main formation surface of a main tool using a cold-spray technique, the main tool having a plurality of tool portions that each have a formation surface such that the formation surface of each of the plurality of tool portions forms the main formation surface corresponding to a desired structure shape of the sheet structure. The method also includes removing the at least one layer of material from the main formation surface to create the sheet structure.. ... United Technologies Corporation

06/28/18 / #20180179638

Deposited material structure with integrated component

A method for forming a metallic structure having a secondary component includes positioning the secondary component on a main formation surface of a main tool, the main formation surface corresponding to a desired shape of a first layer of material. The method also includes depositing a layer of material on the secondary component and the main formation surface using a cold-spray technique such that the layer of material bonds to the secondary component. ... United Technologies Corporation

06/28/18 / #20180179637

Material deposition to form a sheet structure

A method for forming a sheet structure includes providing a tool having a formation surface corresponding to a shape of the sheet structure. The method also includes depositing at least one layer of material on the formation surface using a cold-spray deposition technique. ... United Technologies Corporation

06/28/18 / #20180178432

Systems and methods for manufacturing fiber-reinforced polymeric components

Components may be manufactured by co-extruding a polymer filament and a fiber filament from a nozzle. The polymer filament and the fiber filament may be heated within the nozzle, which may couple the polymer filament to the fiber filament. ... United Technologies Corporation

06/28/18 / #20180178332

Deposited structure with integral cooling enhancement features

A method for forming a metallic structure having a non-linear aperture includes providing a main tool having a formation surface corresponding to a desired structure shape of the metallic structure. The method also includes attaching a removable tool having a shape corresponding to a desired aperture shape of the non-linear aperture to the main tool. ... United Technologies Corporation

06/28/18 / #20180178331

Reinforcement of a deposited metallic structure using reinforcing particles

A method for forming a reinforced metallic structure includes depositing a mixture of metallic particles and reinforcing particles on a formation surface of a tool by cold-spraying the metallic particles to form a layer of mixed material, the formation surface corresponding to a desired shape of the reinforced metallic structure. The method also includes removing the layer of mixed material from the formation surface to create the reinforced metallic structure. ... United Technologies Corporation

06/21/18 / #20180173171

Microgrid system and controller

. . A microgrid controller includes a database in communication with a processor. The processor is operable to receive at least one microgrid input, to determine a first plurality of optimal power characteristic levels at a corresponding one of a plurality of first time intervals for a first time period, and to determine a second plurality of optimal power characteristic levels of a device determined at a corresponding one of a plurality of second time intervals for a second time period. ... United Technologies Corporation

06/21/18 / #20180171826

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

06/21/18 / #20180171820

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

06/21/18 / #20180171815

Traction drive transmission for gas turbine engine accessory gearbox

A gas turbine engine assembly according to an example of the present disclosure includes, among other things, a turbine section having first and second turbines mounted for rotation about a common rotational axis within an engine static structure, first and second turbine shafts coaxial with one another and to which the first and second turbines are respectively operatively mounted, an accessory drive gearbox a first towershaft interconnecting the accessory drive gearbox and the first or second turbine shaft, and a multispeed transmission interconnecting the accessory drive gearbox and at least one accessory component.. . ... United Technologies Corporation

06/21/18 / #20180171462

Abradable seal and method of producing a seal

An air seal for use in a gas turbine engine. The seal includes a thermally sprayed abradable seal layer. ... United Technologies Corporation

06/21/18 / #20180171448

Deep rolling tool and method

An embodiment of a tool assembly includes a robotic assembly, a tool mount, and a non-axisymmetric deep rolling tool. The robotic assembly includes a plurality of linear arms connected in series between a base end and a working end. ... United Technologies Corporation

06/21/18 / #20180171447

Deep rolling tool and method

An embodiment of a tool assembly includes a hub connected to a distal end of a spring-loaded shaft assembly disposed along a first axis. An upper hub portion is adjacent to the distal end of the spring-loaded shaft assembly aligned with the first axis, and a lower hub portion extends along a second axis, forming a nonzero angle relative to the first axis. ... United Technologies Corporation

06/21/18 / #20180171431

Method for solution heat treated alloy components

A method of estimating an unknown solvus for a phase of a given alloy includes providing empirical data of a plurality of alloys from an alloy class, the empirical data at least including chemical compositions, heating rates, cooling rates and alloy solvus temperatures of the plurality of alloys, providing an alloy chemical composition, a selected heating rate and a selected cooling rate of another alloy from the alloy class that has an unknown solvus temperature, estimating the unknown solvus temperature based upon the empirical data to provide an estimated solvus temperature of the alloy, and establishing a solution heat treatment temperature corresponding to the estimated solvus temperature at which to treat a component that includes the alloy.. . ... United Technologies Corporation

06/21/18 / #20180169828

Deep rolling tool and method

An embodiment of a tool assembly includes a spring-loaded shaft assembly disposed along a first axis, a hub, and a roller disk. The hub is connected to a distal end of the spring-loaded shaft assembly. ... United Technologies Corporation

06/14/18 / #20180163751

Stator with support structure feature for tuned airfoil

A vane stage assembly includes an airfoil including a leading edge and a trailing edge. An inner shroud extends from the leading edge to the trailing edge for supporting the airfoil. ... United Technologies Corporation

06/14/18 / #20180163746

Fan blade with protective cladding and method of making

Disclosed herein is a coated aluminum component which includes an aluminum substrate and a protective material disposed on the substrate wherein the protective material includes a galvanic corrosion protection layer and an impact protection layer. Also disclosed is a method of applying the protective material.. ... United Technologies Corporation

06/14/18 / #20180163743

Fan blade having a tip assembly

A fan blade includes a tip assembly that is disposed on a blade body. The tip assembly has a leading edge wall disposed proximate a leading edge of the blade body, a trailing edge wall disposed proximate a trailing edge of the blade body, a suction side wall that extends between the leading edge wall and the trailing edge wall, a pressure side wall disposed opposite the suction side wall and extends between the leading edge wall and the trailing edge wall, and a tip wall that extends between the leading edge wall, the trailing edge wall, the suction side wall, and the pressure side wall and is disposed parallel to the tip.. ... United Technologies Corporation

06/14/18 / #20180163665

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 that drives a fan section and a compressor section. The step of designing the compressor section includes the step of designing a first compressor and a second compressor, with an overall pressure ratio being greater than or equal to about 35. ... United Technologies Corporation

06/14/18 / #20180163664

Concentric shafts driving adjacent fans for aircraft propulsion

A propulsion system for an aircraft has at least two fans, each fan having a fan drive shaft. A turboshaft gas turbine engine drives each of the at least two fans, and drive an output shaft which drives a gear to, in turn, engage for driving a gear on a first intermediate shaft extending from the turboshaft gas turbine engine in a rearward direction toward an intermediate fan drive shaft. ... United Technologies Corporation








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