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Patent # Description
2016/0186619 CAMSHAFT ADJUSTER
A camshaft adjusting device for an internal combustion engine, comprising a housing comprising a bearing sleeve arranged to be concentrically disposed on a...
2016/0186618 POSITIONAL CONTROL OF ACTUATOR SHAFT FOR E-PHASER AND METHOD OF CALIBRATION
An apparatus (10) and method for controlling an angular position of a camshaft (12) in an internal combustion engine having a camshaft phaser (14) for...
2016/0186617 SLIDING MEMBER AND METHOD OF MANUFACTURING THE SAME
A sliding member includes: a metal substrate; an undercoat primer layer that is formed on a sliding surface of the metal substrate; and a resin layer that is...
2016/0186616 THERMAL ELECTRIC POWER GENERATOR
A thermal electric power generator includes an evaporator, an expander, an electric generator, a condenser, and a pump. A working fluid used in the thermal...
2016/0186615 HEAT ENGINE SYSTEM
An improved heat engine is disclosed. The heat engine comprises at least one heat pipe containing a working fluid flowing in a thermal cycle between vapor...
2016/0186614 TURBINE EXHAUST CASE ASSEMBLY
A turbine exhaust case assembly includes a frame which includes an outer ring, an inner ring, a plurality of struts that connect the inner ring and the outer...
2016/0186613 DUCTED COWL SUPPORT FOR A GAS TURBINE ENGINE
A ducted cowl support includes an annular structure configured to be mounted to an annular turbine engine frame and including one or more bypass ducts...
2016/0186612 CASING RING ASSEMBLY WITH FLOWPATH CONDUCTION CUT
A casing assembly for a gas turbine engine having a centerline axis, the casing apparatus includes: a metallic inner ring defining an annular flowpath surface;...
2016/0186611 BLADE TRACK ASSEMBLY WITH TURBINE TIP CLEARANCE CONTROL
A turbine shroud assembly or blade track assembly adapted to extend around a turbine wheel assembly is disclosed. The turbine shroud assembly includes a...
2016/0186610 AUSTENITIC SEGMENT FOR STEAM TURBINE NOZZLE ASSEMBLY, AND RELATED ASSEMBLY
An austenitic segment for a steam turbine nozzle assembly, along with related assemblies. Various embodiments include a steam turbine austenitic ring segment...
2016/0186609 REPLACING AN APERTURE WITH AN ANNULAR BUSHING IN A COMPOSITE LAMINATED COMPOSITE COMPONENT
An annular bushing includes an annular cylindrical portion with a flange that defines a fastener aperture along an axis. A multiple of spacers extend from an...
2016/0186608 INTEGRAL GUTTER AND FRONT CENTER BODY
A fan drive gear system for a turbofan engine is disclosed and includes a gear assembly and a front center body. The front center body is an annular case that...
2016/0186607 BEARING SYSTEM FOR GAS TURBINE ENGINE
A bearing system is provided for a gas turbine engine. This bearing system includes a spring defined about an axis of rotation. The spring has a multiple of...
2016/0186606 GAS TURBINE ENGINE DUCT ASSEMBLY
A duct assembly according to an exemplary aspect of the present disclosure includes, among other things, a casing body that extends between a flange and a...
2016/0186605 SHROUD ASSEMBLY FOR A TURBINE ENGINE
A shroud assembly for a turbine section of a turbine engine includes a shroud plate in thermal communication with a hot combustion gas flow and a baffle...
2016/0186604 FLEXIBLY DAMPED MOUNTING ASSEMBLIES FOR POWER GEAR BOX TRANSMISSIONS IN GEARED AIRCRAFT ENGINE ARCHITECTURES
An assembly for flexibly damping a power gear box for a gas turbine engine, the assembly includes a flexible mount connected to the power gear box at a first...
2016/0186603 ROTOR CONSTRUCTION FOR HIGH SPEED MOTORS
A rotor shaft for a high speed motor that has a coating that is secured to a shaft body. The coating and the shaft body are formed from dissimilar materials....
2016/0186602 NOZZLE FOR FOAM WASHING OF JET ENGINE
Turbines and associated equipment are normally cleaned via water or chemical pressure washing via a mist, spray systems. However, these systems fail to reach...
2016/0186601 DIRT EXTRACTION APPARATUS FOR A GAS TURBINE ENGINE
A centrifugal compressor apparatus includes: an impeller mounted for rotation about a central longitudinal axis, the impeller including an impeller disk...
2016/0186600 VARIABLE AREA TURBINE ARRANGEMENT FOR A GAS TURBINE ENGINE
A variable area turbine arrangement according to an exemplary aspect of the present disclosure includes, among other things, a first turbine section having at...
2016/0186599 TURBINE ENGINE WITH GUIDE VANES FORWARD OF ITS FAN BLADES
A turbine engine such as a pusher fan engine is provided. This turbine engine includes a nacelle with a bypass flowpath. A fan rotor is configured to propel...
2016/0186598 Gas Turbine Engine With Accessory Gear Box
A nacelle for incorporation into a gas turbine engine has an inner wall defining a bypass duct, and an outer wall, at least one drive shaft extending through...
2016/0186597 TURBINE COOLING APPARATUS
A turbine cooling apparatus of an embodiment includes a cooling air supply unit and a control unit The control unit controls an operation of the cooling air...
2016/0186596 CLEARANCE CONTROL ASSEMBLY
A clearance control assembly for a gas turbine engine according to an exemplary aspect of the present disclosure includes, among other things, a clearance...
2016/0186595 COMPRESSOR ABRADABLE MATERIAL SEAL WITH TAILORED WEAR RATIO AND DESIRABLE EROSION RESISTANCE
What is described is a wear resistant seal system that is adapted for resisting wear of a rotating part in a gas turbine engine as it rotates against a...
2016/0186594 FLOWPATH BOUNDARY AND ROTOR ASSEMBLIES IN GAS TURBINES
A gas turbine that having a flowpath having a rotor assembly that includes: a first rotor wheel supporting a first rotor blade having a platform that defines a...
2016/0186593 FLOWPATH BOUNDARY AND ROTOR ASSEMBLIES IN GAS TURBINES
A gas turbine that having a flowpath having a rotor assembly that includes: a first rotor wheel supporting a first rotor blade having a platform that defines a...
2016/0186592 FLOWPATH BOUNDARY AND ROTOR ASSEMBLIES IN GAS TURBINES
A gas turbine that having a flowpath having a rotor assembly that includes: a first rotor wheel supporting a first rotor blade having a platform that defines a...
2016/0186591 FLOWPATH BOUNDARY AND ROTOR ASSEMBLIES IN GAS TURBINES
A gas turbine that having a flowpath having a rotor assembly that includes: a first rotor wheel supporting a first rotor blade having a platform that defines a...
2016/0186590 COVER PLATE ASSEMBLY FOR A GAS TURBINE ENGINE
A cover plate assembly according to an exemplary aspect of the present disclosure includes, among other things, a first cover plate and a second cover plate in...
2016/0186589 GAS TURBINE ENGINE AFT SEAL PLATE GEOMETRY
A gas turbine engine includes an engine static structure. A fairing is supported relative to the engine static structure and configured to provide a flow path...
2016/0186588 SLIDING SEAL
The present disclosure relates generally to a sliding seal between two components. The sliding seal includes a first seal section including one or more first...
2016/0186587 BAFFLE FOR GAS TURBINE ENGINE VANE
A vane structure includes an airfoil section with a first inner airfoil wall surface and a second inner airfoil wall surface. A baffle is mounted within the...
2016/0186586 FIRST STAGE TURBINE NOZZLE WITH EROSION COATING SURFACE FINISH
A first stage turbine nozzle includes a first stage hub portion extending axially along a central axis, a first stage disk portion attached to the first stage...
2016/0186585 SECOND STAGE TURBINE NOZZLE WITH EROSION COATING SURFACE FINISH
A second stage turbine nozzle includes a second stage disk portion having a central axis, and a plurality of second stage vanes positioned radially around and...
2016/0186584 TURBOMACHINE IMPELLOR ROTOR WITH DEVICE FOR FEATHERING THE BLADES OF THE IMPELLOR
The present invention relates to a rotor for a turbomotor impeller, with variable-pitch blades, comprising blade roots capable of rotating in a blade...
2016/0186583 GAS TURBINE ENGINE CMC AIRFOIL ASSEMBLY
A gas turbine engine airfoil assembly includes an airfoil and an attachment structure respectively bonded to opposing sides of a platform. At least one of the...
2016/0186582 TURBOMACHINE ROTOR WITH OPTIMISED BEARING SURFACES
The invention relates to a turbomachine rotor including a disk and at least one blade wherein the root comprises a bulb accommodated into a groove associated...
2016/0186581 TURBINE WHEELS WITH PRELOADED BLADE ATTACHMENT
A wheel assembly for a gas turbine engine is disclosed. The wheel assembly includes a disk arranged for rotation about a central axis and formed to include a...
2016/0186580 Calcium Magnesium Aluminosilicate (CMAS) Resistant Thermal Barrier Coating and Coating Process Therefor
A process for coating a component and a coating system including a bond coat on a superalloy substrate. A thermal barrier material may be applied to the bond...
2016/0186579 HYBRID GAMMA TiAl ALLOY COMPONENT
A hybrid component for a turbine engine having a casing includes a first part of a gamma TiAl intermetallic alloy and a second part of a material of at least...
2016/0186578 ADVANCED GAMMA TiAl COMPONENTS
Components include a low pressure turbine having a plurality of rotor assemblies including a first gamma TiAl intermetallic blade having a maximum operating...
2016/0186577 COOLING CONFIGURATIONS FOR TURBINE BLADES
A blade in a turbine of a gas turbine engine that includes: an outer surface bending along an edge at an angle greater than about 120.degree. so to define a...
2016/0186576 LARGE-FOOTPRINT TURBINE COOLING HOLE
A cooling hole for a component includes a meter section and a diffuser section. The diffuser section has a footprint region defined by five sides, a first side...
2016/0186575 HOT GAS PATH COMPONENT AND METHODS OF MANUFACTURE
Various embodiments of the disclosure include a turbomachine component. and methods of forming such a component. Some embodiments include a turbomachine...
2016/0186574 INTERIOR COOLING CHANNELS IN TURBINE BLADES
A blade for a turbine of a gas turbine engine that includes an airfoil, the airfoil having a leading edge, a trailing edge, an outboard tip, and an inboard...
2016/0186573 Radial Lock for Fan Blade Sheath
A turbojet fan blade adapted for securement to an engine rotor includes a titanium sheath that extends continuously over its leading edge from blade tip to...
2016/0186572 TURBINE BLADE PLATFORM UNDERCUT WITH DECREASING RADII CURVE
A turbine blade has an undercut beneath its platform proximate a trailing edge region. The undercut incorporates a curved portion to reduce to reduce...
2016/0186571 MIXING PLENUM FOR SPOKED ROTORS
A gas turbine engine may comprise a first rotor with a primary flowpath along an outer diameter of the first rotor. A secondary flowpath may be radially inward...
2016/0186570 SUPERCONDUCTING POWER SHAFT CORE
A gas turbine turbine rotor(s) having a combination there of proximal embedded permanent magnets in the blended turbine(s) trunion structure to which blades...
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