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Patent # Description
2017/0159487 HT Enhancement Bumps/Features on Cold Side
The present disclosure is directed to a composite component for a gas turbine engine. The composite component includes a composite wall having a flow side...
2017/0159486 Method for Validation of an Investigated Sensor and Corresponding Machine
A method and machine for validating an investigated sensor within a sensor group includes receiving sensor data from sensors of the sensor group measuring the...
2017/0159485 METHOD AND SYSTEM FOR DIAGNOSING A CONDITION OF AN ENGINE USING LUBRICATING FLUID ANALYSIS
Methods and systems for diagnosing a condition of an engine based on lubrication fluid analysis are disclosed. One embodiment of the methods comprises:...
2017/0159484 INSTRUMENTED FLOW PASSAGE OF A TURBINE ENGINE
An annular air flow passage, particularly for a turbine engine, comprising two radially internal and external annular walls, wherein an element is elongated in...
2017/0159483 HIGH RESPONSE TURBINE TIP CLEARANCE CONTROL SYSTEM
An actuation system according to various embodiments can include an actuation ring having a first end and a second end separated by a gap, the actuation ring...
2017/0159482 RUN-IN COATING FOR AN OUTER AIR SEAL OF A TURBOMACHINE
The invention relates to a run-in coating (10) for an outer air seal of a turbomachine, especially of an aero engine, comprising a substrate (12) of segmented...
2017/0159481 BLADE OUTER AIR SEAL WITH SEAL ARC SEGMENT HAVING SECONDARY RADIAL SUPPORTS
A blade outer air seal includes a seal arc segment that has radially inner and outer sides, first and second circumferential ends, and first and second axial...
2017/0159480 SEAL ASSEMBLY FOR A TURBOMACHINE
The present disclosure relates to a turbomachine that includes a first component and a second component coupled to another and a seal assembly between the two...
2017/0159479 SEAL ASSEMBLY FOR A TURBOMACHINE
The present disclosure relates to a turbomachine that includes a first component and a second component coupled to another and a seal assembly between the two...
2017/0159478 SEAL ASSEMBLY FOR A TURBOMACHINE
The present disclosure relates to a turbomachine that includes a first component and a second component coupled to another and a seal assembly disposed between...
2017/0159477 STEAM TURBINE ROTOR SEAL RADIAL KEY MEMBER, RELATED ASSEMBLY AND STEAM TURBINE
Various embodiments include a rotor key member, along with a related assembly and steam turbine. Particular embodiments include a rotor key member for radially...
2017/0159476 STEAM TURBINE ROTOR SEAL SLIDING KEY MEMBER, RELATED ASSEMBLY AND STEAM TURBINE
Various embodiments include a rotor key member, along with a related assembly and steam turbine. Particular embodiments include a rotor key member for...
2017/0159475 TURBOMACHINE WITH AN OUTER SEALING AND USE OF THE TURBOMACHINE
A turbomachine having a stator with at least one stator component and a rotor with at least one rotatable rotor component. The stator component defines at...
2017/0159474 STEAM TURBINE ROTOR SEAL KEY MEMBER, RELATED ASSEMBLY AND STEAM TURBINE
Various embodiments include a rotor key member, along with a related assembly and steam turbine. Particular embodiments include a rotor key member for...
2017/0159473 STEAM TURBINE ROTOR SEAL KEY MEMBER, RELATED ASSEMBLY AND STEAM TURBINE
Various embodiments include a rotor key member having: a body with a primary axis extending in a direction substantially perpendicular to an axial direction in...
2017/0159472 STABILIZED SEALING RING FOR A TURBOMACHINE
Disclosed is a sealing ring (13, 13', 13'') for a turbomachine, which is constructed so as to be fastened at a radially inner region of a plurality of guide...
2017/0159471 INNER RING AND GUIDE VANE CASCADE FOR A TURBOMACHINE
An inner ring 10 according to the invention for a guide vane cascade of a turbomachine has a radially outer inner ring surface 11 as well as a plurality of...
2017/0159470 INNER RING SYSTEM FOR AN INLET GUIDE VANE CASCADE OF A TURBOMACHINE
The invention relates to an inner ring system for an inlet guide vane cascade (14) of a turbomachine (10). The inner ring system comprises an intermediate...
2017/0159469 CURVIC SEAL FOR USE IN A GAS TURBINE ENGINE AND METHOD OF ASSEMBLING A GAS TURBINE ENGINE
A curvic seal for use in a gas turbine engine is provided. The curvic seal includes a split ring including a first slit extending therethrough, and a biasing...
2017/0159468 TURBOMACHINE WITH AN INGESTION SHIELD AND USE OF THE TURBOMACHINE
A turbomachine, for instance a gas turbine or a steam turbine, has a stator with at least one stator component, a rotor with at least one rotor component, at...
2017/0159467 GUIDE VANE RING CASING FOR A TURBOMACHINE AND TURBOMACHINE HAVING A GUIDE VANE RING CASING
An inventive guide vane ring casing 10' for a turbomachine has a casing surface 11 extending about and facing a central axis A, the casing surface having...
2017/0159466 GUIDE VANE SEGMENT WITH RADIAL SECURING ELEMENTS
The invention relates to a guide vane segment (10) for a gas turbine comprising at least one radially outer shroud (14) and one radially inner shroud (12),...
2017/0159465 GUIDE VANE SEGMENT FOR A TURBOMACHINE
The invention relates to a guide vane cluster (10) for a turbomachine, in particular for a turbojet engine, having at least two vanes (14) that are joined...
2017/0159464 RUN-UP SURFACE FOR THE GUIDE-VANE SHROUD PLATE AND THE ROTOR-BLADE BASE PLATE
A guide vane segment 10 for a turbomachine includes a radially inner shroud plate 13 having a shroud plate surface 14 that is adapted to be configured in the...
2017/0159463 Compliant Shroud for Gas Turbine Engine Clearance Control
The present disclosure is directed to a shroud assembly for a gas turbine. The shroud assembly includes a casing and a shroud. The shroud includes a radially...
2017/0159462 FAN BLADE APPARATUS
A gas turbine engine fan blade apparatus is disclosed comprising a reverse pitch rotatable mounting and an aerofoil part. The aerofoil part comprises radially...
2017/0159461 STACKING OF ROTOR BLADES ON CENTROIDS
A rotor blade for a gas turbine, in particular an aircraft gas turbine, having a blade root element and a stream deflection portion adjoining the blade root...
2017/0159460 ENHANCED ADHESION THERMAL BARRIER COATING
A gas turbine engine including a compressor section, a combustor section fluidly connected to the compressor section, a turbine section fluidly connected to...
2017/0159459 PART COATED WITH A SURFACE COATING AND ASSOCIATED METHODS
A part made of composite material includes fiber reinforcement densified by a ceramic matrix. The part presents an outside surface and is coated over at least...
2017/0159458 METHOD FOR INSPECTING A ROTOR BLADE UNIT
A method for inspecting a rotor blade unit of a gas turbine, the rotor blade unit including a radially outwardly disposed outer shroud connected by a...
2017/0159457 DAMPER SEAL INSTALLATION FEATURES
Aspects of the disclosure are directed to a damper configured to be located in a cavity formed between first and second bases configured to seat respective...
2017/0159456 BAFFLE INSERT FOR A GAS TURBINE ENGINE COMPONENT AND COMPONENT WITH BAFFLE INSERT
A component of a gas turbine engine having: an internal cooling cavity; a baffle insert configured to be inserted into the internal cooling cavity; a plurality...
2017/0159455 BAFFLE INSERT FOR A GAS TURBINE ENGINE COMPONENT
A baffle insert for a component of a gas turbine engine is provided. The baffle insert having: a plurality of trip strips extending upwardly from an exterior...
2017/0159454 GAS TURBINE ENGINE COMPONENT WITH A BAFFLE INSERT
A component of a gas turbine engine, the component having: an internal cooling cavity extending through an interior of the component; a baffle insert...
2017/0159453 TURBINE DISCS AND METHODS OF FABRICATING THE SAME
A turbine disc having a radius and a circumference is provided. The turbine disc includes a central aperture and a plurality of cooling channels...
2017/0159452 TRAILING EDGE COOLING FOR A TURBINE BLADE
A component for a gas turbine engine comprises an airfoil having an outer surface. One or more cooling passages can be disposed within the airfoil, having a...
2017/0159451 TURBINE ENGINE WITH AN AIRFOIL HAVING A TIP SHELF OUTLET
An airfoil for a gas turbine engine includes a pressure side and a suction side, with a root and a tip wall. The pressure side and suction side extend beyond...
2017/0159450 FILLET OPTIMIZATION FOR TURBINE AIRFOIL
A blade for a gas turbine engine comprises an airfoil having a pressure side and a suction side, with a root and a tip wall. The pressure side and suction side...
2017/0159449 GAS TURBINE ENGINE WITH FILLET FILM HOLES
An airfoil for a gas turbine engine can have an exterior wall and an interior wall, with each wall having a thickness. The walls can intersect to define a...
2017/0159448 METHOD OF MANUFACTURE OF A TURBINE COMPONENT
A method for manufacturing a component having a defined geometry includes: a) defining a pre-component geometry including interim shape elements and...
2017/0159447 GAS TURBINE ENGINE COMPONENT HAVING ENGINEERED VASCULAR STRUCTURE
A component according to an exemplary aspect of the present disclosure includes, among other things, a wall and a vascular engineered lattice structure formed...
2017/0159446 METHODS AND SYSTEMS FOR DETERMINING WEAR IN A TURBINE ENGINE
A turbine engine system includes a component positioned such that the component is subject to wear. The component includes an outer surface configured to be...
2017/0159445 MISTUNED CONCENTRIC AIRFOIL ASSEMBLY AND METHOD OF MISTUNING SAME
An example method of reducing a vibratory response of airfoils that support a shroud includes circumferentially misaligning some of the airfoils in a radially...
2017/0159444 Blade channel, blade cascade and turbomachine
A blade channel of a turbomachine that is delimited in the circumferential direction of the turbomachine by a pressure side of an airfoil and by an opposite...
2017/0159443 CONTOURED SURFACE ANNULAR SECTION OF A GAS TURBINE
The invention relates to a blade or vane ring for a gas turbine having a plurality of blades or vanes that are arranged next to one another in the peripheral...
2017/0159442 COATED AND UNCOATED SURFACE-MODIFIED AIRFOILS FOR A GAS TURBINE ENGINE COMPONENT AND METHODS FOR CONTROLLING...
A surface-modified airfoil for a gas turbine engine component is provided. The surface-modified airfoil includes an airfoil having an exterior surface at a...
2017/0159441 TURBINE DISC ASSEMBLIES AND METHODS OF FABRICATING THE SAME
A turbine disc assembly is provided. The turbine disc assembly includes a first rotor disc, a second rotor disc, and a spacer disc coupled between the first...
2017/0159440 TURBOMACHINE BLADE COVER PLATE HAVING RADIAL COOLING GROOVE
A turbomachine blade may include an airfoil and a shank coupled to the airfoil. The shank may include a cover plate having a first circumferential face and a...
2017/0159439 ECCENTRICALLY PILOTED HYDRAULIC COMMUTATOR
A hydraulic motor includes a rotor and a stator, wherein the rotor and the stator define a plurality of motor pockets for receiving a flow of hydraulic fluid,...
2017/0159438 ROTARY SYNCHRONIZED COMBUSTION ENGINE
An engine system is provided, including a housing, multiple shafts in alignment and in parallel with each other, vertically penetrating through the housing,...
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