Class / Patent application number | Description | Number of patent applications / Date published |
416215000 | Blade received by continuous circumferential channel | 28 |
20090110557 | Interface for a stamped stator and a one-way clutch - A stator, including: a one-way clutch with at least one slot opening radially outward from an outer circumferential portion of an outer race; and a blade assembly including first and second separately formed, stamped blade segments rotationally connected to the one-way clutch via the at least one slot. The blade segments are fixedly connected at respective outer circumferential portions. In one embodiment, the stamped blade segments include respective portions disposed in the at least one slot and disposed radially inward from respective blades for the respective blade segments. In one embodiment, the stator includes at least one rivet disposed in the at least one slot and fixedly secured to first and second portions of the first and second stamped blade segments, respectively, the first and second portions located radially inward from blades for the first and second stamped blade segments, respectively. | 04-30-2009 |
20090208338 | Single channel inner diameter shroud with lightweight inner core - An inner diameter shroud for receiving an inner diameter base portion of a rotatable vane in a gas turbine engine has a single piece channel and a core. The channel has a leading edge wall, an inner diameter wall, a trailing edge wall, a radial outer surface, and at least two axial projections. The axial projections prevent radial movement of the core. The core has an outer radial surface that generally aligns with the radial outer surface of the channel. The core is movable in the channel in a circumferential direction and is configured to rotatably retain the inner diameter base portion of the rotatable vane. | 08-20-2009 |
20090246029 | TURBINE ROTOR BLADE, TURBINE ROTOR AND STEAM TURBINE EQUIPPED WITH THE SAME - A turbine rotor blade according to the present invention includes a cover provided at the top of an effective blade portion and a blade-fitting portion provided at the bottom of the effective blade portion. A turbine wheel is provided with a turbine-wheel engagement portion to which the blade-fitting portion is fittable. The turbine rotor blade is a portion of a blade array structure formed by arranging the cover and a neighboring cover in contact with each other. The blade-fitting portion is provided with an anti-twist segment, and the turbine-wheel engagement portion is provided with an untwist restraining segment engageable to the anti-twist segment. | 10-01-2009 |
20110027090 | LOCKING SPACER ASSEMBLY FOR A CIRCUMFERENTIAL DOVETAIL ROTOR BLADE ATTACHMENT SYSTEM - A dual-component locking spacer assembly for insertion in a circumferential dovetail slot includes a stationary member having a platform configured to fit into a space between the adjacent rotor blade platforms. A first leg extends transversely from an underside of the platform. A longitudinally extending groove is defined in the platform. A slide member is movably engaged with the stationary member along the groove, and includes an upper plate and a second leg connected to the upper plate. The slide member is movable along the groove between a first unlocked position wherein the first and second legs are spaced apart a first distance so as to be insertable into the dovetail slot, and a second locked position wherein the first and second legs are spaced apart an extended second distance so as to engage against opposite walls of the dovetail slot and lock the stationary member in position in the dovetail slot. | 02-03-2011 |
20110110782 | LOCKING SPACER ASSEMBLY FOR A CIRCUMFERENTIAL ENTRY AIRFOIL ATTACHMENT SYSTEM - A locking spacer assembly for insertion in a circumferential attachment slot includes a first end piece and a second end piece. The first and second end pieces each comprise an outer surface and an inner surface, the inner surfaces generally facing towards each other when the end pieces are inserted into the attachment slot. An actuator is movable between the inner surfaces and a spacer block is configured to be inserted between the inner surfaces. A fastener is configured to secure the spacer block to the actuator. The actuator is configured to engage the inner surfaces such that the end pieces move toward each other and lock the assembly within the attachment slot. | 05-12-2011 |
20110116933 | ROTOR WITH ONE-SIDED LOAD AND LOCK SLOTS - A rotor for a turbine engine has a pair of spaced rails that extend around a cylindrical surface space. The rails define a space for receiving blades and locks. A plurality of slots are formed in one of the rails, with an opposed surface on an opposed rail not being formed with a slot. The slots are utilized to move at least one of the locks and the blades into the space. | 05-19-2011 |
20110200441 | TURBINE ASSEMBLY - A turbine assembly includes a rotor ( | 08-18-2011 |
20110206524 | Gas turbine having sealing plates on the turbine disc - A turbine rotor having a plurality of rotor blades assembled into rotor blade rows and arranged on a turbine disk is provided. The respective turbine disc on the side surfaces thereof includes a plurality of sealing plates having edges that are arranged radially towards the inside, enables a simplified design and assembly, while maintaining maximum operational reliability and maximum efficiency of a turbine equipped therewith. Therefore, between the edge of the respective sealing plate and a side wall of the turbine disc groove, a closure member is provided, wherein the edge extends over the entire azimuthal length of the sealing plate and the closure members abut each other in the azimuthal direction for sealing purposes. The closure members may be inserted into the turbine disc groove via a recess interrupting the respective edge and extending substantially azimuthally on the side facing the turbine axis. | 08-25-2011 |
20140219804 | HUB FOR A WIND TURBINE - The invention provides a hub for a wind turbine, the hub comprising a continuous shell being assembled from at least two shell parts. To improve stiffness of the hub, a plate element is attached within blade flanges of the assembled hub. Due to the combination between shell parts and a plate element, manufacturing and transportation is facilitated while strength and rigidity is ensured. | 08-07-2014 |
20140334933 | CONING RESISTANT ROTOR FOR A SEAL ASSEMBLY - A coning-resistant rotor and a seal assembly including a coning-resistant rotor are disclosed. An embodiment of the rotor includes a rotor base, a rotor head, and an axially-extending web interposed between the rotor base and rotor head, wherein the web includes axial and radial web regions defined by at least one circumferential groove provided in the web. In another embodiment, a rotor base includes a sealing surface and an inner diameter surface, and the inner diameter surface includes a channel with a taper. | 11-13-2014 |
20140341742 | METHOD AND DEVICE FOR MOUNTING A ROTOR HUB ON A WIND TURBINE - The invention concerns a rotor hub of a wind power installation comprising a handling apparatus for lifting the rotor hub by means of a crane for mounting the rotor hub to a pod arranged on a wind power installation pylon, wherein the handling apparatus is so adapted that upon being lifted at a fixing portion of the handling apparatus the rotor hub rotates from a perpendicular orientation with a substantially perpendicular hub axis into a horizontal orientation with a substantially horizontal hub axis. | 11-20-2014 |
20150037161 | METHOD FOR MOUNTING A GAS TURBINE BLADE IN AN ASSOCIATED RECEIVING RECESS OF A ROTOR BASE BODY - A gas turbine blade in an associated receiving recess of a rotor base body includes a slot in the blade root and has the shape of a straight cylinder. A blade retaining plate has a first securing region and a second securing region interconnected by a shaft region; the shaft region having the shape of a straight cylinder configured to conform to the slot of the blade root. The shaft region comes to rest on a bottom of the receiving recess of the rotor base body; the first securing region being reshaped to form a first limit stop for a first end wall of the blade root; and the second securing region being reshaped to allow the blade root to be inserted along the insertion direction into the receiving recess. The second securing region of the blade retaining plate is subsequently reshaped to allow the second securing region to form a second limit stop for a second end wall of the blade root facing opposite the first end wall, and the blade root to be secured in position in the receiving recess. | 02-05-2015 |
20150147180 | AERODYNAMIC ROOT ADAPTERS FOR WIND TURBINE ROTOR BLADES - Aerodynamic root adapters for rotor blades include an interior support section having a first end that connects to a root end of the rotor blade and a second end that connects to a rotor hub of the wind turbine, and, an aerodynamic exterior section supported by the interior support section. The aerodynamic exterior section thereby extends an aerodynamic profile of the rotor blade beyond the root end of the rotor blade to at least partially between the root end of the rotor blade and the rotor hub when the aerodynamic root adapter is connected thereto. | 05-28-2015 |
20150147181 | DIFFERENTIAL BLADE DESIGN FOR PROPELLER NOISE REDUCTION - A propeller is provided including a hub and a first blade group and a second blade group. The first blade group includes at least one first propeller blade and the second blade group includes at least one second propeller blade. The at least one first propeller blade and the at least one second propeller blade are mounted to and equidistantly spaced about the hub. The at least one first propeller blade of the first blade group has at least one geometric characteristic different from the at least one propeller blade of the second blade group. The different blade groups will generate different noise signatures over a wider range of frequencies allowing for the design of low noise propeller systems. | 05-28-2015 |
20150292340 | FIBER-REINFORCED TURBINE COMPONENT - A turbine component includes an airfoil section elongated in a longitudinal direction; a dovetail section continuous with an end of the airfoil section and bulging in a width direction across the longitudinal direction; a plurality of first reinforcement fibers running continuously from the airfoil section to the dovetail section; a plurality of second reinforcement fibers running at least partly in the width direction in the airfoil section; and a matrix joining an entirety of the first reinforcement fibers and the second reinforcement fibers. In the airfoil section, the second reinforcement fibers are woven into the first reinforcement fibers to form a three-dimensional fabric. In the dovetail section, the first reinforcement fibers are not gathered in the width direction by other fibers but deploy in the width direction. | 10-15-2015 |
416216000 | Radially spaced ribs or grooves | 1 |
20090148296 | METHOD OF MACHINING A TURBINE DISK - A method of manufacturing a turbine disk involves machining to an initial form a slot in a turbine disk using a firm cutting tool. An intermediate form is then machined using a second cutting tool different from the first cutting tool. A final form using a third cutting tool different from the first cutting tool and the second cutting tool is then machined. | 06-11-2009 |
416217000 | Divided blade root | 7 |
20100296936 | LOW STRESS CIRCUMFERENTIAL DOVETAIL ATTACHMENT FOR ROTOR BLADES - A retaining system is provided for circumferential entry rotor dovetails inserted into dovetail slot in a rotor. A plurality of rotor blade dovetails are circumferentially slidable into and along the dovetail slot, with each rotor blade dovetail having a neck and a pair of oppositely oriented lobes. A plurality of rail segments are circumferentially slid into channels in the dovetail slot between the dovetail lobes and the respective disk hoops. The rail segments define a first pressure face that engages against an outward pressure face of the dovetail lobes, and a second pressure face that engages against an inward pressure face of the respective disk hoop component. | 11-25-2010 |
20130195668 | TURBOMACHINE ROTOR WITH BLADE ROOTS WITH ADJUSTING PROTRUSIONS - A turbomachine rotor includes a rotor blade mounted to a rotation element. The rotor blade includes a root for mounting the rotor blade to the rotation element. The root has a protrusion structure forming a stop face supporting the mounted root against the rotation element under action of a radially inwardly directed force. The protrusion structure defines a maximum clearance between the stop face and the rotation element. The root is radially moveable to a certain extent where in a radially outermost position the protrusion structure has the maximum radial clearance from the rotation element. The rotation element includes a groove therein. The groove has a groove face bearing the stop face of the rotor blade under action of a radially inwardly directed force. The groove is a circumferential groove extending in a circumferential direction with regard to an axis of rotation of the rotation element. | 08-01-2013 |
20140030094 | WIND TURBINE BLADE HAVING A ROOT REGION WITH ELONGATED FASTENING MEMBERS PROVIDED WITH METAL FIBRES - A wind turbine blade for a wind turbine is a shell structure of a fibre-reinforced composite and comprises a root region and an airfoil region. The root region has ring-shaped cross section and comprises a plurality of elongated bushings | 01-30-2014 |
20140030095 | WIND TURBINE BLADE WITH ELONGATED FASTENING MEMBERS IN THE ROOT REGION THEREOF - A wind turbine blade for a wind turbine is a shell structure of a fiber-reinforced composite and comprises a root region and an airfoil region. The root region has ring-shaped cross section and comprises a plurality of elongated bushings | 01-30-2014 |
20140030096 | WIND TURBINE BLADE WITH TAPERING ROOT BUSHINGS - A wind turbine blade for a wind turbine is a shell structure of a fibre-reinforced composite and comprises a root region and an airfoil region. The root region has a ring-shaped cross section and comprises a plurality of elongated bushings | 01-30-2014 |
20140030097 | WIND TURBINE BLADE COMPRISING CYLINDRICAL METAL INSERTS IN A ROOT REGION THEREOF - A wind turbine blade for a wind turbine is a shell structure of a fibre-reinforced composite and comprises a root region and an airfoil region. The root region has a ring-shaped cross section and comprises a cylindrical insert | 01-30-2014 |
20140334934 | ROTOR BLADE AND CONNECTING DEVICE - A rotor blade of a wind power installation for fixing to a rotor hub and having a rotor blade longitudinal axis, including a rotor blade inner part towards the rotor hub, and a rotor blade outer part away from the rotor hub, wherein the rotor blade inner part and the rotor blade outer part are connected together by means of at least one connecting device and the connecting device includes at least one anchoring element anchored in the rotor blade outer part, at least one counterpart element anchored in the rotor blade inner part, and at least one connecting bolt which extends through the counterpart element and is fixed in the anchoring element. | 11-13-2014 |
416218000 | Having circumferentially extending binder | 5 |
20090214349 | Airfoil Structure Shim - An airfoil structure, shim and retention member combination is provided. The combination comprises an airfoil structure, a retention member and a shim. The airfoil structure may comprise a first recess. The retention member may comprising a second recess. The first and second recesses may define a cavity. The shim may comprise a main body and a plurality of first fins extending outwardly from a first side of the main body. The first fins may further extend transverse to a longitudinal axis of the main body. The shim may be positioned in the cavity such that the first fins extend in a direction substantially transverse to a longitudinal axis of the cavity. | 08-27-2009 |
20110008171 | ROTATING BODY - A rotating body includes a rotor disk | 01-13-2011 |
20140255196 | DOUBLE SPLIT BLADE LOCK RING - A rotor assembly for a gas turbine engine includes a plurality of blades including a root portion and an airfoil portion. The rotor includes a plurality of slots that receive the root portion of a corresponding blade. The rotor includes an annular groove for a first and second retaining ring. The retaining rings are received within a common annular groove for holding each of the plurality of blades within the slots of the rotor. | 09-11-2014 |
20150110633 | RETENTION ASSEMBLY WITH A CONICAL INTERFACE FOR A PROPELLER BLADE - A retention assembly for a propeller blade includes an inner ring that is conformally shaped to a bore of an annular loop, the annular loop being associated with a root portion of the propeller blade; a base that is configured to be immediately adjacent the annular loop; an annular outer ring including a bearing race interface that is conical in shape and includes a radially inner surface that conforms to a radially outer surface of the annular loop; and an adhesive that adhesively connects complementary surfaces of the outer ring and the annular loop. Also, a propeller blade assembly includes a propeller blade having a blade portion and a root portion; and the retention assembly that is configured to attach to the propeller blade. | 04-23-2015 |
20150139811 | Blade-disk assembly, method and turbomachine - Disclosed is a blade-disk assembly of a turbomachine, the blade-disk assembly having a plurality of adjacent rotor blades and a closure blade which are tilted into an anchoring groove, and at least one circumferential retention element which interlockingly cooperates with at least one blade, as well as a plurality of tilt-out prevention elements which are disposed between the groove base and the root portions and which, in the rest state, space the blades from the groove base when in the upper position. The blade-disk assembly further has a locking element, a portion of which is located between the groove base and the root portions and which, in the rest state, spaces the closure blade from the groove base when in the upper position. Also disclosed are a method for assembling such a blade-disk assembly, as well as a turbomachine. | 05-21-2015 |