Class / Patent application number | Description | Number of patent applications / Date published |
416221000 | Resilient or deformable | 22 |
20090022594 | Wear prevention spring for turbine blade - A turbine airfoil support system for supporting a turbine blade to prevent wear during turning gear operation when a rotor assembly supporting the turbine blade rotates at about two revolutions per minute (RPM) to keep the turbine ready for quick startup requirements. The turbine airfoil support system may be formed from a radial biasing spring positioned between a radially outermost point of a disk steeple extending from a rotor assembly and a radially inner surface of the platform. The radial biasing spring may be formed from a first flat member with a disk steeple engaging surface, a second flat member with a blade platform engaging surface, a bent biasing section extending from the first flat member to the second flat member and biasing the first and second flat members away from each other, and a stress reducing member extending from the second flat member toward the first flat member. | 01-22-2009 |
20090060746 | BLADE RETAINING CLIP - A blade retaining clip and a blade assembly for axially securing a root portion of a blade component within an axially extending slot of a rotating disk. The blade retaining clip includes a shank portion, a first end portion and a second end portion. The shank portion includes an axial downwardly curved profile. The first end portion and the second end portion are integrally formed at opposed ends of the shank portion. The first end portion and the second end portion are configured to secure the root portion of the blade component within the axially extending slot of the rotating disk. The axial downward curvature of the shank portion minimized operating stresses at the first end portion and the second end portion and subsequent failure of the blade retaining clip. | 03-05-2009 |
20090269203 | AEROENGINE FAN ASSEMBLY - A fan assembly of a gas turbine engine, the fan assembly includes an array of radially extending blades defining gaps therebetween and an annulus filler located within at least one gap. The annulus filler includes at least two individual bodies arranged circumferentially adjacent one another with at least one adjacent a blade, one of the bodies includes a flexible wall arranged to centrifuge outwardly against the other body thereby urging both bodies against the blades and securing them during engine operation. | 10-29-2009 |
20100189564 | BLADE PRELOADING SYSTEM AND METHOD - A removable fan blade of a turbofan engine includes a blade root at one end thereof. A rotor disk has a retention slot having dimensions corresponding for receiving the root of the fan blade in the slot. An elongated resilient member extends within the retention slot in a lengthwise direction between the root of the fan blade and the bottom of the retention slot and an elongated member extends lengthwise between the root of the fan blade and the elastomeric member to compress the resilient member and provide a radial preload to the fan blade. | 07-29-2010 |
20100226777 | Shim for a turbojet blade - A shim for a turbomachine blade is disclosed. The shim includes two branches which wrap around flanks of a blade root, and two tabs. Each of the tabs extend from one end of a respective one of the two branches. The tabs are folded towards each other and are interconnected in such a manner as to prevent them from unfolding. Advantageously, the shim includes a connection part which interconnects the tabs in such a manner as to prevent them from unfolding. The connection part is assembled to the tabs in such a manner as to allow the branches of the shim to spread apart. For example, the connection part can be suitable for stretching in the direction for spreading the branches apart. | 09-09-2010 |
20100290914 | Blade Closing Key System for a Turbine Engine - A blade closing key system includes a first key piece and a second key piece. The first key piece includes a first finger and an elongated alignment plate. The second key piece includes a second finger and a key slot. The key pieces are installed in a cavity collectively formed by a notch in a blade root and a slot in a rotor disc. The first and second fingers are bent toward each other and engage each other at their ends. Simultaneously, at least a portion of the alignment plate is received in the key slot. During engine operation, the engagement between the alignment plate and the key slot keeps the first and second key pieces aligned. Thus, regardless of the width of either of the two key pieces or the width of the cavity, the fingers remain constantly engaged during engine operation, minimizing the potential for blade liberation. | 11-18-2010 |
20110176925 | TORSIONAL FLEXING ENERGY ABSORBING BLADE LOCK - A lock for constraining blades in a hub includes a flexible ring for constraining the blades from moving axially in the hub, a finger attached to the hub for preventing the ring from rotating relative to the hub and whereby the ring flexes about at least a partial circumference thereof if urged axially by the blades. | 07-21-2011 |
20120237352 | DAMPER AND SEAL PIN ARRANGEMENT FOR A TURBINE BLADE - A bucket for a turbomachine rotor wheel includes an airfoil portion, a shank portion and a dovetail mounting portion, the shank portion including opposite sides, one of the sides formed with a substantially axially-oriented groove extending between forward and aft ends of the shank portion. The other one of the opposite sides is formed with at least one substantially radially-oriented groove. The substantially axially-oriented groove is adapted to receive an elongated damper pin, and the at least one substantially radially-oriented groove is adapted to receive an elongated radial seal pin. | 09-20-2012 |
20130071248 | COMPRESSIVE STRESS SYSTEM FOR A GAS TURBINE ENGINE - The present application provides a compressive stress system for a gas turbine engine. The compressive stress system may include a first bucket attached to a rotor, a second bucket attached to the rotor, the first and the second buckets defining a shank pocket therebetween, and a compressive stress spring positioned within the shank pocket. | 03-21-2013 |
20130156591 | ENERGY ABSORBENT FAN BLADE SPACER - A gas turbine engine fan assembly includes a rotor disk, a fan blade and a spacer. The rotor disk includes a longitudinally extending slot with a first spacer contact surface. The fan blade includes a root with a second spacer contact surface arranged within the slot. The spacer includes a leaf spring backbone and a compliant member. The leaf spring backbone includes one or more root contact segments connected longitudinally to one or more slot contact segments. A first of the root contact segments contacts the second spacer contact surface, and a first of the slot contact segments contacts the first spacer contact surface. The compliant member is radially between the first spacer contact surface and the first root contact segment, and radially between the second spacer contact surface and the first slot contact segment. | 06-20-2013 |
20130259695 | SPACER INTERPOSED BETWEEN A BLADE ROOT AND THE BOTTOM OF A SLOT IN THE DISK IN WHICH THE BLADE IS MOUNTED - Wedging blades attached to the disk of a rotor having slots. According to the invention, each wedging spacer is made of an elastically deformable material and at least one longitudinal segment of the spacer presents a transverse profile of arcuate shape to define two lateral contact zones. | 10-03-2013 |
20140023508 | ROTOR ASSEMBLY - A rotor assembly includes a rotor disc and a plurality of circumferentially-spaced, radially outwardly extending rotor blades. The rotor disc has a rim and a plurality of circumferentially spaced slots provided in the rim of the rotor disc, each rotor blade having a root, the root of each rotor blade being arranged in a corresponding one of the slots in the rim of the rotor disc, and at least one of the slots having a chocking device accommodated within a space between a radially outer surface of the slot and a radially inner surface of the root of the rotor blade. The chocking device includes at least a first spring and a second spring, the first and second springs each abutting a radially inner surface of the root of the corresponding rotor blade and arranged transversely relative to a longitudinal axis of the slot. | 01-23-2014 |
20140161617 | BLADED ROTOR WHEEL FOR A TURBINE ENGINE - A bladed rotor wheel for a turbine engine, the rotor wheel including a disk including, formed in its outer periphery, at least one slot for mounting the roots of blades, and a spacer mounted between each blade root and a bottom of the slot. The spacer includes at least one member of type that is bistable in position and that can occupy a first stable position for assembly or disassembly in which the member does not exert force on the blade root, and a second stable position in which the bistable member exerts a radial force on the blade root. The spacer also includes at least one resilient damper member mounted between the bottom of the slot and the blade root. | 06-12-2014 |
20140178202 | TURBINE ENGINE IMPELLER - A turbine engine rotor wheel including a disk including at least one slot formed in its outer periphery for mounting roots of blades, a presser being mounted between each blade root and a bottom of the slot. The presser is bistable in position and is capable of occupying a first stable position for assembly and disassembly in which it does not exert a force on the blade root, and a second stable position in which it exerts a radial force on the blade root to hold the blade stationary and to stabilize the blade in a final position. | 06-26-2014 |
20150110635 | Adjustable Blade Root Spring for Turbine Blade Fixation in Turbomachinery - An adjustable blade root spring device for turbine blade fixation in turbomachinery. The device is designed to be placed in a space in a rotor disk cavity adjacent to a tip of a blade root fir tree, where the device applies a radial outward force on the turbine blade to fix the blade position in the rotor disk. The device includes an accordion-shaped spring which is compressed by a bolt and a coil spring. When the accordion spring is compressed in length, it increases in height and makes contact with the rotor disk and the turbine blade. The force of the accordion spring on the turbine blade can be adjusted via the bolt, and the coil spring provides an increased compliance range. The device can be inserted into the space without scraping against the blade root or the rotor disk, and expanded once it is in position. | 04-23-2015 |
20150300364 | DETACHABLE BLADES FOR A CEILING FAN - A detachable blade and support assembly for a ceiling fan includes a support having an insert groove, a blade having an insert end portion inserted into the insert groove and having two retaining grooves formed respectively formed in two opposite side surfaces, and a mounting unit connecting the blade to the support. The mounting unit includes two side resilient members disposed on the support and having engaging portions engaging respectively and fittingly the retaining grooves in the support to retain releaseably the insert end portion of the blade in the insert groove in the support, a centrifugal resilient member for preventing the engaging portions of the side resilient members from movement in the retaining grooves in the blade. | 10-22-2015 |
20150322805 | BLADE UNDERROOT SPACER WITH HOOK REMOVAL - A rotor for use in a gas turbine engine has rotor slots receiving a blade. The blades have an airfoil extending from a dovetail, and the dovetail is received by a rotor slot. A spacer is positioned between an inner wall of the dovetail and an outer wall of the slot, and the spacer is formed with a removal slot. A spacer, a gas turbine engine, and a method are also disclosed. | 11-12-2015 |
20150330235 | VARIABLE DUAL SPRING BLADE ROOT SUPPORT FOR GAS TURBINES - An adjustable blade root spring device for turbine blade fixation in turbomachinery. The device is designed to be placed in a space in a rotor disk cavity adjacent to a tip of a blade root, where the device applies a radial outward force on the turbine blade to fix the blade position in the rotor disk. The device includes a wave spring with integral end blocks which is compressed by a bolt and a coil spring. When the wave spring is compressed in length, it increases in height and makes contact with the rotor disk and the turbine blade. The force of the wave spring on the turbine blade can be adjusted via the bolt, and the coil spring provides an increased compliance range. The body of the device has an oblong cross-sectional shape, thereby preventing rotation of the device in the space between the blade and the disk. | 11-19-2015 |
20150361950 | FIXATION FOR A WIND TURBINE BLADE TO THE HUB - The blade root ( | 12-17-2015 |
20160090850 | BLADED ROTOR ARRANGEMENT AND A LOCK PLATE FOR A BLADED ROTOR ARRANGEMENT - A bladed rotor arrangement comprises a rotor, a plurality of rotor blades and a plurality of lock plates. The rotor blades are mounted in circumferentially spaced axially extending slots in the periphery of the rotor. A plurality of lock plates are arranged at a first axial end of the rotor and a plurality of lock plates are arranged at a second axial end of the rotor. The radially outer ends of the lock plates engage corresponding grooves defined by radially inwardly extending flanges on the platforms of the rotor blades. The radially inner ends of the lock plates also engage circumferentially extending grooves. The radially inner end of each lock plate has three crushable, deformable, circumferentially spaced feet to reduce the risk of the lock plates chocking against the rotor, or seal plates and additional radial loads being reacted by the rotor blades into the rotor. | 03-31-2016 |
20160097288 | LOCKING MEMBER - A lock apparatus securing a blade to a hub, the lock apparatus comprising a planar element having a spring actuable between an expanded position and a compressed position without deviation from the plane of the element, wherein in the expanded position of the spring the planar element is partly located in a slot provided in the blade, the spring being compressible to its compressed position to disengage the planar element from the slot. | 04-07-2016 |
20160251973 | RETENTION DEVICE | 09-01-2016 |