Class / Patent application number | Description | Number of patent applications / Date published |
416194000 | LASHING BETWEEN WORKING MEMBERS OR EXTERNAL BRACING | 26 |
20110243743 | ATTACHMENT ASSEMBLIES BETWEEN TURBINE ROTOR DISCS AND METHODS OF ATTACHING TURBINE ROTOR DISCS - A method of attaching two rotor discs in a turbine engine, the method comprising the steps of: forming a first rotor disc that includes a first axial extension and a disc flange; forming a second rotor disc that includes a second axial extension and a weld surface; forming a bridge, the bridge that includes a bridge flange at one end and a weld surface at the other end, and, along an outer radial surface, the bridge comprises means for sealing; attaching the bridge to the second rotor disc via welding the weld surfaces of the bridge and the second axial extension; and attaching the first rotor disc to the bridge via removably securing the disc flange to the bridge flange. | 10-06-2011 |
20140271208 | SYSTEMS AND METHOD FOR A COMPOSITE BLADE WITH FILLET TRANSITION - A system includes a turbomachine blade segment including an airfoil with an exterior surface, and a platform coupled to the airfoil having a first side and a second side. The system also includes a concave fillet transition extending between the airfoil and the platform. The concave fillet transition includes one or more interface ply segments extending across the exterior surface of the airfoil and the first or the second side of the platform to form a continuous surface between the airfoil and the platform. | 09-18-2014 |
20180023546 | TANDEM TIP-JOINED ROTOR BLADE AND HUB COUPLING FOR PASSIVE PITCH ANGLE CONTROL | 01-25-2018 |
416195000 | Peripheral | 7 |
20090068015 | ORGANIC MATRIX COMPOSITE INTEGRALLY BLADED ROTOR - An integrally bladed rotor is constructed from a plurality of layers of organic matrix composite material wound together in a spiral fashion to form the disc portion of the rotor, and at each rotor blade position at least the outermost one of the layers is turned substantially radially outwards from the periphery of the rotor disc to form a blade. Each blade is finished with further pieces of organic matrix composite material bonded into position on the. An encircling blade tip shroud may be formed by further layers of material wound around the tips of the blades in conjunction with closed loop inserts in the spaces between blades. | 03-12-2009 |
20110189021 | Turbine blade - A fluid turbine for generating electrical power, the turbine having a rotor assembly comprising a hub, a rim and a plurality of blade members joining them together, the blade members being rigid, flat panel, multi-ply, composite blade members having a plurality of parallel, longitudinally-oriented, reinforcing cords composed of non-braided aramid synthetic strands, the cords being disposed between at least two cloth layers impregnated with a cured polymer resin. | 08-04-2011 |
20130259692 | FAN WITH METALLIC HUB AND PLASTIC IMPELLER AND METHOD FOR MANUFACTURING SUCH FAN - An exemplary fan includes a hub and an impeller. The hub is made of metal, and includes a flange. The impeller is made of plastic. The impeller is formed around the hub and has the flange embedded therein. A method for manufacturing the fan is also provided. | 10-03-2013 |
20130323062 | Propeller For Ventilator, With A Variable Blade Angle - A blower wheel comprises a hub, a guide and blades extending radially between the hub and the guide, each blade comprising a root at its junction with the hub and a head at the junction with the guide, each blade having a leading edge and a trailing edge between which, at each flattened cross section, a chord is defined. For each blade, in the radial direction from the root to the head, the pitch angle between the chord and the rotation axis of the wheel varies and the variation in the pitch angle between the root and the head has a point of inflexion between a first level and a second level. | 12-05-2013 |
20140205459 | HIGH OUTPUT FAN WHEEL - A high output bent fin type of fan wheel for use in appliances such as but not limited to microwave ovens. The fan wheel is made by single 90-degree bends for each fan blade relative to the flat mounting plate. Unique to fan wheel is the large fan blade surface area in relation to the total area of the metal used in wheel. | 07-24-2014 |
20140255192 | TURBINE ROTOR FOR A THERMOELECTRIC POWER STATION - Low-pressure turbine rotors for a thermoelectric power station include an interconnection of slender blades. The rotor includes blades bearing caps being roughly in the shape of a chevron. | 09-11-2014 |
20150354374 | TURBINE BLISK AND METHOD OF MANUFACTURING THEREOF - A turbine blisk is provided. The turbine blisk includes an inner rim, a plurality of adjacent rotor blades extending radially outward from said inner rim, a shroud segment integrally coupled to each of the plurality of adjacent rotor blades, thereby forming a plurality of adjacent shroud segments, and a gap defined between each of the adjacent shroud segments. The gap has a geometry that facilitates interlocking the plurality of adjacent shroud segments when a torsional force is applied to the plurality of adjacent rotor blades. | 12-10-2015 |
416196000 | Connecting adjacent work surfaces | 16 |
20110142654 | Turbine Blade Damping Device With Controlled Loading - A damping structure for a turbomachine rotor. The damping structure including an elongated snubber element including a first snubber end rigidly attached to a first blade and extending toward an adjacent second blade, and an opposite second snubber end positioned adjacent to a cooperating surface associated with the second blade. The snubber element has a centerline extending radially inwardly in a direction from the first blade toward the second blade along at least a portion of the snubber element between the first and second snubber ends. Rotational movement of the rotor effects relative movement between the second snubber end and the cooperating surface to position the second snubber end in frictional engagement with the cooperating surface with a predetermined damping force determined by a centrifugal force on the snubber element. | 06-16-2011 |
20110158810 | TURBINE ROTOR ASSEMBLY AND STEAM TURBINE - A turbine rotor assembly | 06-30-2011 |
20110194939 | Snubber Assembly for Turbine Blades - A snubber associated with a rotatable turbine blade in a turbine engine, the turbine blade including a pressure sidewall and a suction sidewall opposed from the pressure wall. The snubber assembly includes a first snubber structure associated with the pressure sidewall of the turbine blade, a second snubber structure associated with the suction sidewall of the turbine blade, and a support structure. The support structure extends through the blade and is rigidly coupled at a first end portion thereof to the first snubber structure and at a second end portion thereof to the second snubber structure. Centrifugal loads exerted by the first and second snubber structures caused by rotation thereof during operation of the engine are at least partially transferred to the support structure, such that centrifugal loads exerted on the pressure and suctions sidewalls of the turbine blade by the first and second snubber structures are reduced. | 08-11-2011 |
20120045338 | CENTRIFUGAL FAN AND AIR CONDITIONER - Provided is a centrifugal fan that can accelerate an airflow also in a trailing edge part on a main plate side. A centrifugal fan | 02-23-2012 |
20120230826 | ROTOR OF A TURBOMACHINE - Rotor having of rotor blades. Every rotor blade has a blade body and coupling segment. A width of the coupling element segment is defined in circumferential direction by edges extending in axial direction. The coupling segment is contoured at a first side such that, on the flow inlet side to a flow inlet edge, the radially outer edge projects beyond the radially inner edge in axial direction. At this side on the flow outlet side of the blade body, the radially inner edge projects beyond the radially outer edge. The coupling segment is contoured at a second side such that, adjacent on the flow outlet side to the flow outlet edge, the radially outer edge extending in axial direction projects beyond the radially inner edge in axial direction. At, this second side facing away from the flow inlet edge the radially inner edge projects beyond the radially outer edge. | 09-13-2012 |
20120237348 | DAMPER PIN - A damper pin for coupling platforms of adjacent turbine blades includes a first flat longitudinal end region, a second flat longitudinal end region and a reduced cross sectional area. The reduced cross sectional area is separated from the first flat longitudinal end region by a first main body region and the reduced cross sectional area is separated from the second flat longitudinal end region by a second main body region. The cross sectional area of the reduced cross sectional area is less than the cross sectional area of each of the first and second main body regions. | 09-20-2012 |
20130017092 | ROTOR ASSEMBLY FOR GAS TURBINESAANM Miller; Christopher EdwardAACI FletcherAAST NCAACO USAAGP Miller; Christopher Edward Fletcher NC US - A rotor assembly is disclosed. The rotor assembly may include a first rotor disk defining a first axially extending slot and a second rotor disk defining a second axially extending slot. Additionally, the rotor assembly may include a pin extending lengthwise between the first and second rotor disks. The pin may include a first end terminating within the first axially extending slot and a second end terminating within the second axially extending slot. | 01-17-2013 |
20140112792 | DAMPER PIN - A damper pin for coupling platforms of adjacent turbine blades includes a first flat longitudinal end region, a second flat longitudinal end region and a reduced cross sectional area. The reduced cross sectional area is separated from the first flat longitudinal end region by a first main body region and the reduced cross sectional area is separated from the second flat longitudinal end region by a second main body region. The cross sectional area of the reduced cross sectional area is less than the cross sectional area of each of the first and second main body regions. | 04-24-2014 |
20150078901 | THREADED SHANK, CONNECTION ASSEMBLY AND GAS TURBINE ENGINE FOR IMPROVED FATIGUE LIFE OF THREADS - A threaded shank for engaging with a threaded further component is provided herein, the further component having a cylindrical first thread with a uniform first thread pitch and a uniform first thread angle, the threaded shank including a second thread with a uniform second thread pitch and a uniform second thread angle and including a third thread with a uniform third thread pitch and a uniform third thread angle along an axial expanse of the third thread. The first thread angle and the second thread angle and the third thread angle being substantially identical, the first thread pitch and the second thread pitch and the third thread pitch being substantially identical, wherein the second thread and the third thread are spaced apart axially by a thread-free region, a second thread helix and a third thread helix have an axial offset to one another. | 03-19-2015 |
20150132134 | Injection Molded Composite Fan Platform - A fan platform for a gas turbine engine may include an outer flow path surface extending between a first side and a second side. An inner surface extends between the first side and the second side, and faces radially oppositely the outer flow path surface. A plurality of platform hooks may extend radially inwardly from the inner surface. | 05-14-2015 |
20150300179 | FORMING A SECONDARY STRUCTURE DIRECTLY ONTO A TURBINE BLADE - A process and apparatus for solid freeform fabrication and repair of components on existing bodies (such as turbine blades), the innovative process and apparatus as well as the resultant product having the following advantages: a) Can build on existing 3-D surfaces. Not limited to horizontal flat surfaces, b) Usable for metals that are difficult to weld. c) Robust process that is adaptable to new damage modes. d) No shielding of the melt pool by inert gas is needed. e) Wide range of powder sizes. | 10-22-2015 |
20160040535 | TURBINE BLADE MID-SPAN SHROUD ASSEMBLY - A mid-span shroud assembly for a turbine blade airfoil includes a pressure side shroud body which is associated with a pressure side wall of the airfoil and a suction side shroud body which is associated with a suction side wall of the airfoil. At least one of the pressure side shroud body and the suction side shroud body defines a coupling spar which is formed to extend at least partially through a bore hole defined within the airfoil of the turbine blade. | 02-11-2016 |
20160040536 | TURBINE BLADE MID-SPAN SHROUD - A mid-span shroud assembly comprises a suction side shroud body which defines a first spar. The first spar is formed to extend at least partially through a spar opening defined within the airfoil and includes a root portion, a tip portion, an upper face and a lower face. The upper and lower faces converge from the tip portion towards the root portion. The mid-span assembly further includes a pressure side shroud body. The pressure side shroud body defines a second spar which is formed to extend at least partially through the spar opening of the airfoil and includes a root portion, a tip portion, an upper face and a lower face. At least a portion of the upper face of the second spar is formed to be substantially parallel with the lower face of the first spar when both the first and second spars are inserted into the spar opening. | 02-11-2016 |
20160040537 | TURBINE BLADE MID-SPAN SHROUD ASSEMBLY - A mid-span shroud assembly for a turbine blade includes a pressure side shroud body defining a spar pocket and a fastener hole and a suction side shroud body defining a spar pocket and a fastener hole. The mid-span shroud assembly further includes a spar having a first end portion which extends within the spar pocket of the pressure side shroud body and a second end portion which extends within the spar pocket of the suction side shroud body. The spar is formed to extend through a bore hole of the turbine blade. A fastener is formed to extend through the fastener hole of the pressure side shroud body, a fastener orifice of the turbine blade and the fastener hole of the suction side shroud body to provide a clamping force to hold the pressure side and suction side shroud bodies against the airfoil. | 02-11-2016 |
20120207605 | BLADE ASSEMBLY FOR A WIND TURBINE - A blade assembly is for a wind turbine, such as a vertical axis wind turbine. The blade assembly includes 3 or more blades and has an axis of rotation about which in use the blades rotate. In one variation the blades are elongated and have first and second ends and are twisted between their ends. The blades are positioned along the axis of rotation in a manner such that the first (bottom) end of each blade has a portion that has substantially the same angular orientation as a portion of the second (top) end of an adjacent blade. Alternatively or additionally the blades are arranged for orientation along the axis of rotation and are twisted about an axis of twist. The axis of twist substantially coincides with the axis of rotation of the wind turbine. | 08-16-2012 |
20120224968 | Lift-Type Vertical Axis Turbine - A vertical axis turbine includes a modified darrieus type rotor having at least three circumferentially spaced apart blades, each having an airfoil shape in cross section such that the blades generate a torque in a direction of rotation of the turbine about the vertical axis responsive to a generally horizontal wind across the blades. Support members, for example flexible cables, are connected under tension between adjacent ones of the blades to extend in a generally circumferential direction about the turbine at an inclination from horizontal in a criss-crossing pattern with other support members. A tensioning mechanism also urges opposing top and bottom ends of the rotor towards one another such that the blades are supported under compression in a pre-stressed condition by the support members and the tensioning mechanism to maintain the blades in a substantially rigid and fixed orientation throughout the operation of the turbine rotor. | 09-06-2012 |
416196000 | Non-turbo machine (windmills) | 2 |
20110142654 | Turbine Blade Damping Device With Controlled Loading - A damping structure for a turbomachine rotor. The damping structure including an elongated snubber element including a first snubber end rigidly attached to a first blade and extending toward an adjacent second blade, and an opposite second snubber end positioned adjacent to a cooperating surface associated with the second blade. The snubber element has a centerline extending radially inwardly in a direction from the first blade toward the second blade along at least a portion of the snubber element between the first and second snubber ends. Rotational movement of the rotor effects relative movement between the second snubber end and the cooperating surface to position the second snubber end in frictional engagement with the cooperating surface with a predetermined damping force determined by a centrifugal force on the snubber element. | 06-16-2011 |
20110158810 | TURBINE ROTOR ASSEMBLY AND STEAM TURBINE - A turbine rotor assembly | 06-30-2011 |
20110194939 | Snubber Assembly for Turbine Blades - A snubber associated with a rotatable turbine blade in a turbine engine, the turbine blade including a pressure sidewall and a suction sidewall opposed from the pressure wall. The snubber assembly includes a first snubber structure associated with the pressure sidewall of the turbine blade, a second snubber structure associated with the suction sidewall of the turbine blade, and a support structure. The support structure extends through the blade and is rigidly coupled at a first end portion thereof to the first snubber structure and at a second end portion thereof to the second snubber structure. Centrifugal loads exerted by the first and second snubber structures caused by rotation thereof during operation of the engine are at least partially transferred to the support structure, such that centrifugal loads exerted on the pressure and suctions sidewalls of the turbine blade by the first and second snubber structures are reduced. | 08-11-2011 |
20120045338 | CENTRIFUGAL FAN AND AIR CONDITIONER - Provided is a centrifugal fan that can accelerate an airflow also in a trailing edge part on a main plate side. A centrifugal fan | 02-23-2012 |
20120230826 | ROTOR OF A TURBOMACHINE - Rotor having of rotor blades. Every rotor blade has a blade body and coupling segment. A width of the coupling element segment is defined in circumferential direction by edges extending in axial direction. The coupling segment is contoured at a first side such that, on the flow inlet side to a flow inlet edge, the radially outer edge projects beyond the radially inner edge in axial direction. At this side on the flow outlet side of the blade body, the radially inner edge projects beyond the radially outer edge. The coupling segment is contoured at a second side such that, adjacent on the flow outlet side to the flow outlet edge, the radially outer edge extending in axial direction projects beyond the radially inner edge in axial direction. At, this second side facing away from the flow inlet edge the radially inner edge projects beyond the radially outer edge. | 09-13-2012 |
20120237348 | DAMPER PIN - A damper pin for coupling platforms of adjacent turbine blades includes a first flat longitudinal end region, a second flat longitudinal end region and a reduced cross sectional area. The reduced cross sectional area is separated from the first flat longitudinal end region by a first main body region and the reduced cross sectional area is separated from the second flat longitudinal end region by a second main body region. The cross sectional area of the reduced cross sectional area is less than the cross sectional area of each of the first and second main body regions. | 09-20-2012 |
20130017092 | ROTOR ASSEMBLY FOR GAS TURBINESAANM Miller; Christopher EdwardAACI FletcherAAST NCAACO USAAGP Miller; Christopher Edward Fletcher NC US - A rotor assembly is disclosed. The rotor assembly may include a first rotor disk defining a first axially extending slot and a second rotor disk defining a second axially extending slot. Additionally, the rotor assembly may include a pin extending lengthwise between the first and second rotor disks. The pin may include a first end terminating within the first axially extending slot and a second end terminating within the second axially extending slot. | 01-17-2013 |
20140112792 | DAMPER PIN - A damper pin for coupling platforms of adjacent turbine blades includes a first flat longitudinal end region, a second flat longitudinal end region and a reduced cross sectional area. The reduced cross sectional area is separated from the first flat longitudinal end region by a first main body region and the reduced cross sectional area is separated from the second flat longitudinal end region by a second main body region. The cross sectional area of the reduced cross sectional area is less than the cross sectional area of each of the first and second main body regions. | 04-24-2014 |
20150078901 | THREADED SHANK, CONNECTION ASSEMBLY AND GAS TURBINE ENGINE FOR IMPROVED FATIGUE LIFE OF THREADS - A threaded shank for engaging with a threaded further component is provided herein, the further component having a cylindrical first thread with a uniform first thread pitch and a uniform first thread angle, the threaded shank including a second thread with a uniform second thread pitch and a uniform second thread angle and including a third thread with a uniform third thread pitch and a uniform third thread angle along an axial expanse of the third thread. The first thread angle and the second thread angle and the third thread angle being substantially identical, the first thread pitch and the second thread pitch and the third thread pitch being substantially identical, wherein the second thread and the third thread are spaced apart axially by a thread-free region, a second thread helix and a third thread helix have an axial offset to one another. | 03-19-2015 |
20150132134 | Injection Molded Composite Fan Platform - A fan platform for a gas turbine engine may include an outer flow path surface extending between a first side and a second side. An inner surface extends between the first side and the second side, and faces radially oppositely the outer flow path surface. A plurality of platform hooks may extend radially inwardly from the inner surface. | 05-14-2015 |
20150300179 | FORMING A SECONDARY STRUCTURE DIRECTLY ONTO A TURBINE BLADE - A process and apparatus for solid freeform fabrication and repair of components on existing bodies (such as turbine blades), the innovative process and apparatus as well as the resultant product having the following advantages: a) Can build on existing 3-D surfaces. Not limited to horizontal flat surfaces, b) Usable for metals that are difficult to weld. c) Robust process that is adaptable to new damage modes. d) No shielding of the melt pool by inert gas is needed. e) Wide range of powder sizes. | 10-22-2015 |
20160040535 | TURBINE BLADE MID-SPAN SHROUD ASSEMBLY - A mid-span shroud assembly for a turbine blade airfoil includes a pressure side shroud body which is associated with a pressure side wall of the airfoil and a suction side shroud body which is associated with a suction side wall of the airfoil. At least one of the pressure side shroud body and the suction side shroud body defines a coupling spar which is formed to extend at least partially through a bore hole defined within the airfoil of the turbine blade. | 02-11-2016 |
20160040536 | TURBINE BLADE MID-SPAN SHROUD - A mid-span shroud assembly comprises a suction side shroud body which defines a first spar. The first spar is formed to extend at least partially through a spar opening defined within the airfoil and includes a root portion, a tip portion, an upper face and a lower face. The upper and lower faces converge from the tip portion towards the root portion. The mid-span assembly further includes a pressure side shroud body. The pressure side shroud body defines a second spar which is formed to extend at least partially through the spar opening of the airfoil and includes a root portion, a tip portion, an upper face and a lower face. At least a portion of the upper face of the second spar is formed to be substantially parallel with the lower face of the first spar when both the first and second spars are inserted into the spar opening. | 02-11-2016 |
20160040537 | TURBINE BLADE MID-SPAN SHROUD ASSEMBLY - A mid-span shroud assembly for a turbine blade includes a pressure side shroud body defining a spar pocket and a fastener hole and a suction side shroud body defining a spar pocket and a fastener hole. The mid-span shroud assembly further includes a spar having a first end portion which extends within the spar pocket of the pressure side shroud body and a second end portion which extends within the spar pocket of the suction side shroud body. The spar is formed to extend through a bore hole of the turbine blade. A fastener is formed to extend through the fastener hole of the pressure side shroud body, a fastener orifice of the turbine blade and the fastener hole of the suction side shroud body to provide a clamping force to hold the pressure side and suction side shroud bodies against the airfoil. | 02-11-2016 |
20120207605 | BLADE ASSEMBLY FOR A WIND TURBINE - A blade assembly is for a wind turbine, such as a vertical axis wind turbine. The blade assembly includes 3 or more blades and has an axis of rotation about which in use the blades rotate. In one variation the blades are elongated and have first and second ends and are twisted between their ends. The blades are positioned along the axis of rotation in a manner such that the first (bottom) end of each blade has a portion that has substantially the same angular orientation as a portion of the second (top) end of an adjacent blade. Alternatively or additionally the blades are arranged for orientation along the axis of rotation and are twisted about an axis of twist. The axis of twist substantially coincides with the axis of rotation of the wind turbine. | 08-16-2012 |
20120224968 | Lift-Type Vertical Axis Turbine - A vertical axis turbine includes a modified darrieus type rotor having at least three circumferentially spaced apart blades, each having an airfoil shape in cross section such that the blades generate a torque in a direction of rotation of the turbine about the vertical axis responsive to a generally horizontal wind across the blades. Support members, for example flexible cables, are connected under tension between adjacent ones of the blades to extend in a generally circumferential direction about the turbine at an inclination from horizontal in a criss-crossing pattern with other support members. A tensioning mechanism also urges opposing top and bottom ends of the rotor towards one another such that the blades are supported under compression in a pre-stressed condition by the support members and the tensioning mechanism to maintain the blades in a substantially rigid and fixed orientation throughout the operation of the turbine rotor. | 09-06-2012 |