Matches 201 - 250 out of 313 < 1 2 3 4 5 6 7 >


Match Document Document Title
US20130064668 TURBINE ROTOR BLADE ASSEMBLY AND METHOD OF ASSEMBLING SAME  
A rotor blade assembly for a rotor of a gas turbine engine having an axis of rotation includes a shank portion formed from a ceramic matrix composite (CMC) material. The rotor blade assembly also...
US20130004319 ROTOR ASSEMBLY AND REVERSIBLE TURBINE BLADE RETAINER THEREFOR  
A blade retainer for a gas turbine engine includes a plate-like member with an arcuate outer face, an opposed inner face, and two spaced-apart end faces. The member has an outer portion disposed...
US20110182751 ROTOR DISC  
A rotor disc 2 is provided with blade receiving recesses 40 at its outer periphery. The disc 2 has an internal cavity 34 for conveying cooling air to blades 4 retained in the recesses 40. Each...
US20110150657 TURBOMACHINE FAN ROTOR  
A turbomachine fan rotor including a disk carrying blades with roots that are engaged in axial grooves of the disk, a spacer being interposed between the bottom of each groove and the...
US20100209253 FAN BLADE ANTI-FRETTING INSERT  
A fan blade anti-fretting insert is described whereby to reduce wear between the root portion of a fan blade and the root slot of the rotor fan hub of a turbo fan engine to which the fan blade are...
US20100189562 COMPOSITE MATERIAL TURBOMACHINE BLADE WITH A REINFORCED ROOT  
The invention relates to a turbomachine blade made of composite material including fiber reinforcement, the blade being obtained by three-dimensionally weaving yarns and densifying with a matrix....
US20100172760 Non-Integral Turbine Blade Platforms and Systems  
In one embodiment, a turbine blade platform may be disposed between two turbine blades. The platform may include a first exterior side configured to interface with a first turbine blade. The...
US20100166563 METHOD FOR IMPROVING THE SEALING ON ROTOR ARRANGEMENTS  
A method is described for improving the sealing between rotor and a plurality of blades. The rotor has a plurality of generally axially extending profiled recesses into which a ring of blades,...
US20100150723 Rotor for a Compressor  
According to the present invention there is provided a rotor (20) for mounting of a plurality of blades (30) thereon to form an impeller (10) rotatable about a main axis thereof. Each of the...
US20100111701 TURBINE ROTOR BLADE AND FIXATION STRUCTURE THEREOF  
Disclosed is a turbine rotor blade that is highly manufacturable and capable of reducing the stress caused by centrifugal force. The turbine rotor blade includes: a vane portion having a blade...
US20170167495 CEILING FAN  
An ceiling fan comprising a motor system. The motor system is mounted around a motor shaft. The motor shaft couples to a downrod for suspending the ceiling fan from a structure. The motor shaft...
US20170146020 ROTOR ASSEMBLY FOR USE IN A TURBOFAN ENGINE AND METHOD OF ASSEMBLING  
A rotor assembly for use in a turbofan engine is provided. The rotor assembly includes an annular spool including a blade opening defined therein, and a rotor blade radially insertable through the...
US20170122118 DUCTILE COMPENSATION LAYER FOR BRITTLE COMPONENTS  
Disclosed is a blade element of a turbomachine, in particular of a gas turbine, which comprises a fastening element (10) with which the blade element is arranged in a receptacle (11) of the...
US20170122117 ROTATIONALLY SYMMETRICAL PART FOR A TURBINE ENGINE ROTOR, AND RELATED TURBINE ENGINE ROTOR, TURBINE ENGINE MODULE, AND TURBINE ENGINE  
The invention relates to a rotationally symmetrical part, such as a disk (24′), for a turbine engine rotor. Said part has a rotational axis (A) and comprises, on the periphery thereof, an annular...
US20170107999 ROTATING STRUCTURE AND A METHOD OF PRODUCING THE ROTATING STRUCTURE  
According to one aspect, a rotating structure comprises a hub having a mounting slot defined by a cavity surface and a body having an anchor structure disposed in the mounting slot. A wear member...
US20170074107 BLADE/DISK DOVETAIL BACKCUT FOR BLADE DISK STRESS REDUCTION (9E.04, STAGE 2)  
The present application thus provides a method for reducing stress on at least one of a turbine disk and a turbine blade. The method may include the steps of (a) determining a starting line for a...
US20170037734 UNDERPLATFORM DAMPING MEMBERS AND METHODS FOR TURBOCHARGER ASSEMBLIES  
Damping members for turbocharger assemblies, methods for providing turbocharger assemblies, and turbocharger assemblies are described herein. The damping members include bodies having shapes to...
US20170022825 ROTOR BLADE ROOT ASSEMBLY FOR A WIND TURBINE  
The present disclosure is directed to a root assembly for a rotor blade of a wind turbine and methods of manufacturing same. The root assembly includes a blade root section having an inner...
US20160369638 ROTARY MACHINES INCLUDING A HYBRID ROTOR WITH AN INTEGRALLY BLADED ROTOR PORTION  
Rotary machines including a hybrid rotor with an integrally bladed rotor portion are provided. The integrally bladed rotor portion for the hybrid rotor comprises a rotor disk portion and a blade...
US20160362990 COMPOSITE DISK  
A gas turbine engine composite disk includes dovetail slots between disk posts extending radially inwardly from a periphery, a hub ring of composite plies circumscribed about a centerline axis,...
US20160333889 COMPOSITE BLADE ROOT STRESS REDUCING SHIM  
A gas turbine engine blade root shim for use between a composite blade root and a wall of a slot in a rotor includes a longitudinally extending base having distal first and second transversely...
US20160333707 TURBO ENGINE ROTOR COMPRISING A BLADE-SHAFT CONNECTION MEANS, AND BLADE FOR SAID ROTOR  
In a turbo engine, the rotor includes a shaft, blades, and a shaft-blade connection. The shaft blade connection can be provided as a fir tree connection, having a fir tree blade root and fir tree...
US20160327055 FAN BLADE WITH ROOT THROUGH HOLES  
A lightweight fan blade for use in turbofan gas turbine engines is disclosed. The fan blade includes a metallic airfoil connected to a root. The airfoil has a pressure side and a suction side. The...
US20160312629 APPARATUS FOR MOUNTING A BLADE ON A TURBINE DISK  
A turbine wheel or disk having a plurality of dovetail slots formed in its circumference for receiving a dovetail root of a blade such as a compressor or turbine blade. Each of the dovetail slots...
US20160298480 AIRFOIL DEVICE FOR A GAS TURBINE AND CORRESPONDING ARRANGEMENT  
An airfoil device for a gas turbine has a root section mountable to an airfoil disc and an airfoil element. The root section has a platform at which the airfoil element is arranged. The root...
US20160298468 BLADED ROTOR  
A bladed rotor comprising a rotor disk (12) presenting two front faces (14, 15) and an outer peripheral face (16), sockets (18) being provided in the outer peripheral face (16) and opening out...
US20160298461 ARTICLE OF MANUFACTURE FOR TURBOMACHINE  
An article of manufacture includes a rotor blade configured for use with a turbomachine. The blade is configured for attachment to a rotor wheel. The blade is configured to substantially reduce...
US20160290141 RETAINING RINGS FOR TURBOMACHINE DISK AND COVERPLATE ASSEMBLIES  
A retaining ring for a turbomachine disk and coverplate assembly includes a ring body defining a coverplate interface side and an opposed disk lip interface side. A flow feature is defined by the...
US20160273367 FACETED TURBINE BLADE DAMPER-SEAL  
A damper seal received in a cavity of a turbine blade includes a central body with two ends and a two sides. A portion extends from each end, one side has a faceted edge, and a projection extends...
US20160251972 CERAMIC ATTACHMENT CONFIGURATION AND METHOD FOR MANUFACTURING SAME  
A component assembly includes a support structure, a ceramic substrate mounted to the support, and a foam-like coating adhered to one of the support structure and the ceramic substrate. The...
US20160251963 ROTOR BLADE VIBRATION DAMPER  
A rotor blade vibration damper for a gas turbine engine includes an elongated damper body including a top portion extending longitudinally between a front end and a rear end. The top portion has a...
US20160245100 BLADE WEDGE ATTACHMENT LAY-UP  
A blade for a gas turbine engine includes composite layers including neck plies and tooth plies that are flared relative to the neck plies. The neck plies and tooth plies respectively provide a...
US20160245086 HYBRID METAL AND COMPOSITE SPOOL FOR ROTATING MACHINERY  
A hybrid metal and composite spool includes metal rings on an outer diameter of a composite spool shell. Metal rings may include features such as annular or axial dovetail slots. Adhesive layers...
US20160230579 ROTOR DISK SEALING AND BLADE ATTACHMENTS SYSTEM  
A rotor disk assembly comprises a circular body configured to rotate about an axis, a contoured slot formed partially through the circular body in an axial direction, and a protrusion extending...
US20160222802 CMC BLADE WITH MONOLITHIC CERAMIC PLATFORM AND DOVETAIL  
A blade for a gas turbine engine includes a fiber reinforced ceramic matrix composite structure that provides an airfoil with an exposed exterior airfoil surface and a refractory structure that...
US20160186713 TURBINE ROTOR ASSEMBLY  
A turbine rotor assembly for extracting energy from an oscillating working fluid. The turbine rotor assembly includes a hub rotatable about a central axis. A plurality of blades is mounted to the...
US20160186583 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 airfoil, the platform and the...
US20160186582 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 with the disk, wherein the bulb...
US20160186581 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 plurality of slots. The wheel assembly...
US20160177751 BLADE AND GAS TURBINE PROVIDED WITH THE SAME  
A blade is formed with blade air passages connecting the inside of a blade body of the blade and the inside of a platform of the blade. The platform is formed with a plurality of pressure side...
US20160177749 BLADING MEMBER FOR A FLUID FLOW MACHINE  
A blading member for a fluid flow machine, for example, for use in gas turbine engines. The blading member includes a platform member and an airfoil member. The platform member and airfoil member...
US20160169011 TURBINE AIRFOIL ATTACHMENT WITH MULTI-RADIAL SERRATION PROFILE  
An attachment root of an airfoil is provided comprising a serration profile with a symmetry plane bisecting the serration profile. A first lobe of the serration profile has a first contact face...
US20160169007 APPARATUS HAVING ENGINEERED SURFACE FEATURE AND METHOD TO REDUCE WEAR AND FRICTION BETWEEN CMC-TO-METAL ATTACHMENT AND INTERFACE  
An apparatus having reduced wear and friction between CMC-to-metal attachment and interface of the apparatus, including a CMC component having a surface. The CMC component surface is configured...
US20160167767 ROTOR HUB FOR ROTARY WING AIRCRAFT  
A rotor hub configured to support and rotate a plurality of rotor blades about an axis of rotation is includes a cylindrical body having a central shaft hole including the axis of rotation. The...
US20160160663 PLATFORM OF SMALL HUB-TIP RATIO  
A platform for a bladed wheel having a small hub-tip ratio, suitable for being fabricated out of composite material from a three-dimensionally woven fiber preform, the platform including a bottom...
US20160160662 TURBINE AIRFOIL ATTACHMENT WITH SERRATION PROFILE  
An attachment root of an airfoil is provided. The attachment root may comprise a serration profile, a symmetry plane bisecting the serration profile, and a line perpendicular to the symmetry...
US20160152319 PROPELLER BLADE MOUNTING SYSTEM  
A propeller blade mounting system includes a mounting system (4) on rolling bearings between a propeller hub (3) and a propeller blade (2), wherein: at least one bearing outer ring (9) is...
US20160146021 COMPOSITE BLADES FOR GAS TURBINE ENGINES  
A turbine wheel for use in a gas turbine engine having a plurality of blades attached to a rotor disk. Each blade is formed as a composite structure including a number of plies of...
US20160131144 CENTRIFUGAL COMPRESSOR APPARATUS  
A compressor has an axial portion and a centrifugal portion. A disk structure is provided to support the centrifugal portion and is connected to the centrifugal portion with a rabbet joint.
US20160130957 TURBINE BLISK INCLUDING CERAMIC MATRIX COMPOSITE BLADES AND METHODS OF MANUFACTURE  
In some embodiments, an apparatus includes a disk, a coupling member and a set of blades. The coupling member has a first surface and a second surface, and defines a set of openings between the...

Matches 201 - 250 out of 313 < 1 2 3 4 5 6 7 >