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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.

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Apparatus and method for non-destructive detection of fan blade electrical isolation

An apparatus and method for detecting a short in a blade of a gas turbine engine, the apparatus including: a first plate configured to form a first capacitor with the protective sheath when the apparatus is located proximate to the blade; a second plate configured to form another capacitor with a portion of the airfoil when the apparatus is located proximate to the blade; and a voltage source electrically connected to the first plate and the second plate.. . ... United Technologies Corporation

Rotating detonation engine wave induced mixer

A rotating detonation engine includes an annulus that defines a volume having a detonation region which is configured for a mixture of an oxidizer and a fuel to detonate in a rotating fashion, the volume defining a downstream outlet through which detonation exhaust flows. The rotating detonation engine further includes an oxidizer outlet configured to output the oxidizer into the volume. ... United Technologies Corporation

Squeeze film damper with low pressure reservoirs

A squeeze film damper includes a static member and a whirling member positioned adjacent to the static member. A gap is formed between the static member and the whirling member. ... United Technologies Corporation

Gas turbine engine bifurcation located fan variable area nozzle

A gas turbine engine includes a core engine defined about an axis, a gear system driven by the core engine, and a pylon variable area flow system. A fan is driven by the gear system. ... United Technologies Corporation

Two-shaft tower shaft support

A tower shaft support for a gearbox of a gas turbine engine includes a mounting ring, first and second gussets, and first and second tower shaft bearing mounts. Each gusset extends outward from and substantially normal to an outer circumference of the mounting ring. ... United Technologies Corporation

Rotating detonation engine upstream wave arrestor

A rotating detonation engine includes an annulus that defines a volume in which a mixture of an oxidizer and a fuel detonate in a rotating fashion, the volume defining a downstream outlet through which detonation exhaust flows. The rotating detonation engine further includes a wave arrestor positioned upstream from a location of detonation and configured to reduce a magnitude of a pressure wave traveling upstream from the location of detonation.. ... United Technologies Corporation

Rotating detonation engine multi-stage mixer

A fuel mixer for mixing a fuel and an oxidizer prior to detonation in a rotating detonation engine includes a combustion channel configured to transport a final mixture of the fuel and the oxidizer for combustion. The fuel mixer also includes a mixture channel positioned upstream from the combustion channel and configured to transport a first mixture having at least some of the fuel and at least some of the oxidizer. ... United Technologies Corporation

Bowed rotor prevention system

A bowed rotor prevention system for a gas turbine engine includes a bowed rotor prevention motor. A motor shaft of the bowed rotor prevention motor is operable to drive rotation of the gas turbine engine through an engine accessory gearbox. ... United Technologies Corporation

Airfoil tip pocket with augmentation features

A component for a gas turbine engine includes, among other things, an airfoil that includes a pressure sidewall and a suction sidewall that meet together at both a leading edge and a trailing edge, the airfoil extending radially from a platform to a tip, a tip pocket formed in the tip and terminating prior to the trailing edge, and one or more heat transfer augmentation devices formed in the tip pocket.. . ... United Technologies Corporation

Airfoil cooling

An airfoil may include an external airfoil surface and an airfoil body. The airfoil body may include an external wall structure and an internal wall structure. ... United Technologies Corporation

Turbine blade with tip vortex control and tip shelf

A blade for a gas turbine engine includes an airfoil which includes pressure and suction side surfaces joined at leading and trailing edges to provide an exterior airfoil surface. The airfoil extends from a 0% span position to a 100% span position at a tip. ... United Technologies Corporation

Method of sealing an anodized metal article

A method of coating a metal article is disclosed that includes immersing a metal article having an exterior anodized layer in a bath containing a chemically active corrosion inhibitor, and applying a voltage to the article during the immersing, the voltage driving the chemically active corrosion inhibitor from the bath into the exterior anodized layer. An article is also disclosed that has a substrate comprising a metal, and a porous anodized layer formed on an exterior surface of the substrate that is infiltrated with a chemically active corrosion inhibitor, the anodized layer having an inward-facing region and an outward-facing region, the anodized layer having a greater concentration of chemically active corrosion inhibitors in the inward-facing region than in the outward-facing region.. ... United Technologies Corporation

Abrasive tip blade manufacture methods

A method is provided for manufacturing a blade. The blade comprises an airfoil (100) having: a root end and a tip (106); a metallic substrate (102) along at least a portion of the airfoil; and an anodized layer (154). ... United Technologies Corporation

Solution composition and method for single-bath post treatment of substrate

Disclosed is a solution composition which may be used for a single-bath electrochemical passivation and a method using the same. The solution composition includes a metal cation, a metal-oxide anion; and an organic ligand, and optionally includes a non-metallic oxide anion or a polymer. ... United Technologies Corporation

09/27/18 / #20180272514

Spring loaded pilot punch assembly

A punch assembly includes a punch that defines an axis and a sleeve that is spring biased to the punch, the sleeve movable axially along the axis between a compressed positon and an extended position.. . ... United Technologies Corporation

09/20/18 / #20180266689

Combustor liner with gasket for gas turbine engine

A gasket for installation within a cavity between a support shell and a liner panel of a combustor wall assembly, the support shell having a multiple of impingement holes, and the liner panel having a multiple of film holes, the gasket including a multiple of cells arranged with respect to the multiple of impingement holes and the multiple of film holes, wherein at least one of the multiple of cells segregate a respective subset of the multiple of impingement holes and a subset of the multiple of film holes.. . ... United Technologies Corporation

09/20/18 / #20180266688

Impingement cooled components having integral thermal transfer features

Components for gas turbine engines having a hot side surface, a cold side surface, the cold side surface receiving cooling impingement at one or more cold locations, and at least one thermal transfer feature located between the hot side surface and the cold side surface within the component and arranged such that a condenser section of the thermal transfer feature is located proximate at least one of the cold locations and an evaporator section of the thermal transfer feature is located away from the cold location.. . ... United Technologies Corporation

09/20/18 / #20180266686

Regulated combustor liner panel for a gas turbine engine combustor

A liner panel for use in a combustor of a gas turbine engine, the liner panel including a liner panel with a perimeter rail and a multiple of intermediate rails. A combustor for a gas turbine engine including a support shell and a multiple of liner panels mounted to the support shell via a multiple of studs, each of the multiple of liner panels having a multiple of intermediate rails to form a multiple of circumferential cavities.. ... United Technologies Corporation

09/20/18 / #20180266266

Epicyclic gear train

A turbine engine according to an example of the present disclosure includes, among other things, a fan shaft, at least one tapered bearing mounted on the fan shaft, the fan shaft including at least one passage extending in a direction having at least a radial component, and adjacent the at least one tapered bearing, a fan mounted for rotation on the at least one tapered bearing. An epicyclic gear train is coupled to drive the fan, the epicyclic gear train including a carrier supporting intermediate gears that mesh with a sun gear, and a ring gear surrounding and meshing with the intermediate gears, wherein the epicyclic gear train defines a gear reduction ratio of greater than or equal to 2.3. ... United Technologies Corporation

09/20/18 / #20180266262

Thin seal for an engine

Aspects of the disclosure are directed to a seal configured to interface with at least a first component and a second component of a gas turbine engine. A method for forming the seal includes obtaining an ingot of a fine grained, or a coarse grained, or a columnar grained or a single crystal material from a precipitation hardened nickel base superalloy containing at least 40% by volume of the precipitate of the form ni3(al, x), where x is a metallic or refractory element, and processing the ingot to generate a sheet of the material, where the sheet has a thickness within a range of 0.010 inches and 0.050 inches inclusive.. ... United Technologies Corporation

09/20/18 / #20180265223

Modified start sequence of a gas turbine engine

A system for controlling a start sequence of a gas turbine engine includes an electronic engine control system, a thermal model, memory, a model for determining a time period (fmotoring), and a controller. The thermal model synthesizes a heat state of the gas turbine engine. ... United Technologies Corporation

09/20/18 / #20180264546

Casting molds, manufacture and use methods

A casting mold (260) comprises a shell (262) extending from a lower end (264) to an upper end (266) and having: an interior space (280) for casting metal; and an opening (268) for receiving metal to be cast. A plurality of thermocouples (900) are vertically-spaced from each other on the shell.. ... United Technologies Corporation

09/06/18 / #20180252165

Planetary gear system for turbomachine

A planetary gear system for a turbomachine includes a forward planetary gear assembly including a plurality of forward planet gears meshed to a forward sun gear disposed on a power shaft and a forward ring gear meshed to the forward planet gears and an aft planetary gear assembly aft of the forward planetary assembly including a plurality of aft planet gears meshed to an aft sun gear disposed on the power shaft and an aft ring gear meshed to the aft planet gears. The system also includes a gear housing disposed between the forward planetary gear assembly and the aft planetary gear assembly. ... United Technologies Corporation

09/06/18 / #20180252162

Gas turbine engine thermal management system

The present disclosure provides systems and methods related to thermal management systems for gas turbine engines. For example, a thermal management system comprises a thermally neutral heat transfer fluid circuit, a first heat exchanger disposed on the fluid circuit, and a second heat exchanger disposed on the fluid circuit.. ... United Technologies Corporation

09/06/18 / #20180252118

Borescope plug for gas turbine engine

A borescope plug includes a threaded section that extends from a head section along an axis, the threaded section including a central passage along said axis. A spindle is located within the central passage. ... United Technologies Corporation

09/06/18 / #20180252117

Wear indicator for gas turbine engine

In combination a wear indicator and a component of a gas turbine engine is provided. The wear indicator is secured to a surface of the component of the gas turbine engine. ... United Technologies Corporation

09/06/18 / #20180252111

Thermal barrier coating compositions, methods of manufacture thereof and articles comprising the same

Disclosed herein is a process for coating a component, comprising applying a bond coat on a substrate of a component; applying a thermal barrier material to the bond coat; and applying a coating containing polynuclear aluminum oxide/hydroxide clusters, to the thermal barrier material. Disclosed herein too is a gas turbine engine component, comprising a superalloy substrate; a bond coat on the substrate; a thermal barrier material on the bond coat; and a coating containing polynuclear aluminum oxide/hydroxide clusters on the thermal barrier material.. ... United Technologies Corporation

09/06/18 / #20180252108

Staggered core printout

A core for gas turbine engine component comprises a body extending between first and second ends to define a length, and extending between first and second edges to define a width. A plurality of core extensions are formed as part of the body. ... United Technologies Corporation

09/06/18 / #20180251881

Ceramic coating deposition

A ceramic coating process comprises introducing a suspension including a fine ceramic particulate suspended in a liquid carrier into a plasma torch. The fine ceramic particulate comprising a first material having high toughness and a second material having a beneficial reaction in combination with calcium-magnesium alumino-silicates. ... United Technologies Corporation

08/23/18 / #20180241211

Multifunctional power correction device

A power factor correction system according to the present disclosure includes an inverter connected in parallel with at least one load and a controller configured to command an output voltage of the inverter to provide reactive power to the at least one load when a voltage source is available to the load and real power and reactive power to the at least one load when the voltage source is unavailable to the load.. . ... United Technologies Corporation

08/23/18 / #20180239795

Conflict resolution for a multi-user cax environment

A system for conflict resolution in a multi-user design package includes a host computer having a memory and a processor, wherein the host computer is configured to operate a multi-user cax environment, and is configured to receive edit commands from a plurality of local computers. A conflict resolution module is configured to be executed by the host computer, and the conflict resolution module is configured to prevent implementation of conflicting edit commands received from the plurality of local computers in the multi-user cax environment.. ... United Technologies Corporation

08/23/18 / #20180238673

Encapsulated fan cap probe

Disclosed is a probe including a housing; a plurality of axially stacked caps disposed within the housing, the plurality of stacked caps including an inner cap and an outer cap, a probe sensor fixedly disposed between the inner cap and an axial bottom of the housing, and an electronic lead connected to the probe sensor and axially extending through the plurality of caps to an exterior of the probe.. . ... United Technologies Corporation

08/23/18 / #20180238594

Electrocaloric heat transfer system

A cooling system includes an electrocaloric element (12) having a liquid crystal elastomer or a liquid form liquid crystal retained in an elastomeric polymer matrix. A pair of electrodes (14.16) is disposed on opposite surfaces of the electrocaloric element. ... United Technologies Corporation

08/23/18 / #20180238547

Combustor liner panel end rail cooling interface passage for a gas turbine engine combustor

A combustor for a gas turbine engine includes a support shell; a first liner panel mounted to the support shell via a multiple of studs, the first liner panel including a first rail that extends from a cold side of the first liner panel; and a second liner panel mounted to the support shell via a multiple of studs, the second liner panel including a second rail that extends from a cold side of the second liner panel adjacent to said first rail, the second rail includes a discontinuous rail end surface.. . ... United Technologies Corporation

08/23/18 / #20180238546

Combustor liner panel end rail cooling enhancement features for a gas turbine engine combustor

A combustor for a gas turbine engine includes a support shell; a first liner panel mounted to the support shell via a multiple of studs, the first liner panel including a first rail that extends from a cold side of the first liner panel; a second liner panel mounted to the support shell via a multiple of studs, the second liner panel including a second rail that extends from a cold side of the second liner panel adjacent to the first rail to form an interface passage; and at least one heat transfer feature within the interface passage.. . ... United Technologies Corporation

08/23/18 / #20180238545

Combustor liner panel end rail angled cooling interface passage for a gas turbine engine combustor

A combustor for a gas turbine engine includes a support shell with an angled shell interface; a first liner panel mounted to the support shell via a multiple of studs, the first liner panel including a first rail that extends from a cold side of the first liner panel adjacent to the angled shell interface; and a second liner panel mounted to the support shell via a multiple of studs, the second liner panel including a second rail that extends from a cold side of the second liner panel adjacent to said first rail, the second rail adjacent to the angled shell interface.. . ... United Technologies Corporation

08/23/18 / #20180238437

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. ... United Technologies Corporation

08/23/18 / #20180238394

Bearing thermal relief fan drive gear system assembly method

A method of assembling mating components includes the steps of heating an inner surface of a first cavity of a first part to generate a first expansion, heating an outer surface of a component surrounding an outer periphery of the first part to generate a second expansion of the component that corresponds to the first expansion of the first part, inserting a second part into the first cavity while the first part is in an expanded condition, and cooling the first part to contract around the second part.. . ... United Technologies Corporation

08/23/18 / #20180238270

Integrated heat exchangers for low fan pressure ratio geared turbofan

An oil cooling system and method are provided for use with respect to a lubricated mechanical system within a bypass configured gas turbine engine. A surface cooler is fluidly linked to the lubricated mechanical system to receive oil from the lubricated mechanical system for cooling and reuse. ... United Technologies Corporation

08/23/18 / #20180238268

Composite wear pad for exhaust nozzle

A composite wear pad for being coupled to a slider block of a convergent nozzle of a gas turbine engine includes a high heat capacity composite having a resin and a plurality of carbon fibers bonded together by the resin. The composite wear pad also includes a first rod coupled to the high heat capacity composite at a first axial end of the composite wear pad such that a first end thickness. ... United Technologies Corporation

08/23/18 / #20180238243

Method of defining gas turbine engine control ratings

A disclosed control system and method of controlling a gas turbine engine utilizes a thrust rating schedule generated from airframe selected requirements. The system utilizes a generic logic structure for ratings combined with simple selection logic to customize rating schedules for multiple airframe customers. ... United Technologies Corporation

08/23/18 / #20180238242

Geared gas turbine engine with oil deaerator

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

08/23/18 / #20180238241

Gear system architecture for gas turbine engine

A gas turbine engine includes a gear system that transfers power input from a fan drive turbine to a fan through a gear system with a gear reduction ratio greater than 2.3. A flexible mount supports the gear system and accommodates movement of the gear system relative to an engine static structure. ... United Technologies Corporation

08/23/18 / #20180238240

Composite piston ring seal for axially and circumferentially translating ducts

A seal system is provided. The seal system may comprise a first duct having an annular geometry, a second duct overlapping the first duct in a radial direction, and a seal disposed between the first duct and the second duct. ... United Technologies Corporation

08/23/18 / #20180238233

De-icing by integral electric heat generation

Systems and methods for de-icing a fan of a gas turbine engine are disclosed. The systems and methods may include an electrical coil an electrical coil operatively associated with a non-rotating forward assembly of the gas turbine engine; a magnet operatively associated with a rotating surface of the fan, the magnet and the electrical coil producing electricity when the fan is in motion; and a heating element operatively associated with a surface on the fan, the heating element being powered by the electricity produced by the magnet and the electrical coil.. ... United Technologies Corporation

08/23/18 / #20180238204

Thermally compliant heatshield

A heat shield comprising a sidewall portion, a top portion, and a plurality of flexible tabs attached to the sidewall portion is described herein, in accordance with various embodiments. The top portion may comprise an aperture. ... United Technologies Corporation

08/23/18 / #20180238179

Combustor liner panel end rail with curved interface passage for a gas turbine engine combustor

A combustor for a gas turbine engine includes a support shell; a first liner panel mounted to the support shell via a multiple of studs, the first liner panel including a first rail that extends from a cold side of the first liner panel such that the rail is non-perpendicular to the cold side and includes a concave surface to at least partially form a curved interface passage; and a second liner panel mounted to the support shell via a multiple of studs, the first liner panel including a second rail that extends from a cold side of the second liner panel and includes a convex surface to at least partially form the curved interface passage.. . ... United Technologies Corporation

08/23/18 / #20180238177

Fan platform with stiffening feature

A fan blade platform is provided. The fan blade platform may include a wall, a first sidewall extending from the flowpath to a circular member, and a second sidewall extending from the flowpath to the circular member. ... United Technologies Corporation

08/23/18 / #20180237910

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 position and replacing the hood with another hood of the plurality of hoods.. . ... United Technologies Corporation

08/23/18 / #20180237147

Propulsor mounting for advanced body aircraft

A propulsor and mount arrangement comprises a propulsor rotor and a fan casing surrounding the propulsor rotor. The fan casing receives two side mounts and a thrust link pivotally attached to the fan casing at a location that will be within 10° of a vertically lowermost location when the propulsor is mounted on an aircraft, and the side mounts being at circumferentially opposed positions, and within a lower 270° when the propulsor is mounted on an aircraft. ... United Technologies Corporation

08/23/18 / #20180236718

Mold-less curing method of manufacturing a composite vessel assembly

A method of manufacturing a composite vessel assembly includes the step of placing the composite vessel assembly in a pliable containment prior to curing of a resin of the composite vessel assembly. With the composite vessel assembly in the pliable containment, a vacuum is applied through an orifice in the pliable containment to evacuate air and compact the composite vessel assembly.. ... United Technologies Corporation

08/23/18 / #20180236533

Castings and manufacture methods

A method includes casting a metallic material (56) in a mold (20) containing a core, the core having a substrate (40, 44) coated with a coating (42). A removing of the metallic material from the mold and decoring leaves a casting having a layer formed by the coating. ... United Technologies Corporation

08/16/18 / #20180234031

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

08/16/18 / #20180231478

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

08/16/18 / #20180231251

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

08/16/18 / #20180231250

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

08/16/18 / #20180231249

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

08/16/18 / #20180231248

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

08/16/18 / #20180231014

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

08/16/18 / #20180230946

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

08/16/18 / #20180230944

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

08/16/18 / #20180230943

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

08/16/18 / #20180230942

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

08/16/18 / #20180230912

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

08/16/18 / #20180230909

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

08/16/18 / #20180230856

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

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

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

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

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

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

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

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

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

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








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