| Class / Patent application number | Description | Number of patent applications / Date published |
|---|
| 416224000 | Having wear liner, sheathing or insert | 76 |
| 20090053067 | AIRFOIL AND METHOD FOR PROTECTING AIRFOIL LEADING EDGE - An airfoil is disclosed having a concave pressure side and a convex suction side defining a chord length, and a leading edge and a trailing edge. A leading edge protective strip is adhered by a bond layer to and protectively covers the leading edge and respective predetermined portions of the pressure side and suction side of the airfoil body from the leading edge downstream towards the trailing edge. The leading edge protective strip includes a multiplicity of inwardly-facing grooves in which the bond layer is embedded. The grooves define adjacent segments of a predetermined size sufficiently small that, if detached from the vane during engine operation, impact with downstream engine components will not cause damage to the downstream engine components. | 02-26-2009 |
| 20090087317 | Blade Set for Masserating Effluent Water in a Sewage Pump - A blade set for masserating effluent solids in a sewage pump is composed of a cutter ring and a wheel blade adapted to attach to an effluent water inlet at the lower base. Particularly, the cutter ring has an inner wall and multiple recesses defined on the inner wall to accept enhancing blocks made of tungsten carbide. Correspondingly, the wheel blade has multiple blade strips and each blade strip has a cutout defined at edge to combine with an enhancing corner also made of tungsten carbide. By having the structure made of tungsten carbide, the cutter ring and the wheel blade has excellent wearing resistance and less abrasion loss to keep the operational efficiency to masserate the effluent solids and to extend the lifespan of the sewage pump. | 04-02-2009 |
| 20090148302 | MAIN ROTOR BLADE WITH INTEGRAL TIP SECTION - A main rotor blade assembly having a blade skin bonded to a main spar and a tip spar. | 06-11-2009 |
| 20090162207 | Method For The Manufacture Of An Erosion Protection Layer And A Component With Said Erosion Protection Layer - In accordance with the invention a method for the manufacture of an erosion protection layer on a metallic substrate is proposed in which a material is welded onto the metallic substrate ( | 06-25-2009 |
| 20090263253 | ENGINE COMPONENTS AND ROTOR GROUPS - Engine components and rotor groups are provided. In an embodiment, by way of example only, an engine component includes an impeller and a protective sleeve. The impeller has a bore defined by an inner surface. The protective sleeve lines the inner surface of the impeller and comprises a polymer material. In another embodiment, by way of example only, a rotor group includes an impeller, a protective sleeve, a rotor component, and a tie shaft. The impeller has a first bore defined by an inner surface. The protective sleeve lines the inner surface of the impeller and comprises a polymer material. The rotor component has a second bore, and the tie shaft extends through the first bore and the second bore. | 10-22-2009 |
| 20090304519 | Gas-Compressor Impeller and Gas Compressor Having The Same - An object is to provide a gas-compressor impeller which has excellent durability even when gas containing solid particles is compressed and which does not increase the cost. A gas-compressor impeller installed in a gas compressor that compresses gas containing solid particles has a hub portion and a plurality of blades extending substantially radially from the outer circumferential surface of the hub portion. The hub portion and the blades are rotated about the central axial line to compress gas. The blades have abrasion-resistant films only at gas inlet portions. | 12-10-2009 |
| 20090324417 | BLADE INSERT - Blade insert arranged inside the blade walls so that the joint between the insert and composite ( | 12-31-2009 |
| 20100008788 | PROTECTOR FOR A LEADING EDGE OF AN AIRFOIL - A protector for the leading edge of a rotor blade to provide enhanced erosion protection thereof. In an embodiment, the protector includes an energy absorption member attached to the rotor blade by a first adhesive bond layer and an erosion resistant member attached to the energy absorption member by a second adhesive bond layer. The erosion resistant member is operative to protect the leading edge of the rotor blade from erosion due to impacts from particulate matter, such as sand and rain. The energy absorption member is operative to absorb and disburse energy from impacts to the erosion protection member so that forces from the impacts are diminished or not transferred to the rotor blade. In another embodiment, the erosion resistant member is coated with a diamond film. As the diamond film is harder than sand, excellent resistance to wear from particulate matter and impacts rain is obtained. Other advantages provided by use of the diamond film include: 1) an ultra-smooth surface that reduces drag on the rotor blade whereby flight performance may be improved, and 2) by being ultra-smooth and chemically inert de-icing equipment may not be needed. | 01-14-2010 |
| 20100028160 | Compressor blade leading edge shim and related method - A method of improving an erosion resistance at the leading edge of a compressor blade includes: a) cleaning a leading edge portion of the compressor blade airfoil; and b) attaching one or more erosion or corrosion-resistant shims to the leading edge portion. | 02-04-2010 |
| 20100296939 | COMPOSITE AEROFOIL BLADE WITH WEAR-RESISTANT TIP - The present invention relates to a reinforcing tip cap for an aerofoil blade. The tip cap comprises a body for attaching to the tip of an aerofoil blade and a plurality of abrading elements fixed in the body for abrading a surface against which the tip cap rubs in use. | 11-25-2010 |
| 20100322775 | Anti-Erosion shield for rotor blades - A rotor blade for a turbomachine, particularly a steam turbine is provided. The rotor blade includes a turbine blade and a blade base, wherein the turbine blade has a suction side and a pressure side, as well as an inflow edge and an outflow edge, wherein an erosion protection shield is disposed at a distance in front of the outflow edge in order to avoid liquid impingement erosion. | 12-23-2010 |
| 20110142661 | TRAILING EDGE BONDING CAP FOR WIND TURBINE ROTOR BLADES - A trailing edge bonding cap for use with a rotor blade of a wind turbine is disclosed. The trailing edge bonding cap may include a body projecting outwardly from a blade shell of the rotor blade. The body may have a first outer surface and a second outer surface. The first outer surface may intersect the second outer surface to define a trailing edge of the rotor blade. Additionally, the first and second outer surfaces may have a profile configured to correspond to an aerodynamic profile of the blade shell. | 06-16-2011 |
| 20110182740 | FAN AIRFOIL SHEATH - A sheath for a fan airfoil having a leading edge, a trailing edge, a tip, a root, a suction side and a pressure side includes a solid portion to wrap around the airfoil lead edge and over the airfoil tip and means for securing the solid portion to the airfoil. | 07-28-2011 |
| 20110194941 | CO-CURED SHEATH FOR COMPOSITE BLADE - A method of forming a composite blade having a sheath on a portion of the blade by placing the dry composite blade and sheath in a mold, adding a resin, and curing the resin to integrally bond the blade to the metal sheath. The portion of the blade having the sheath bonded thereto may be at least one of the leading edge, the tip and the trailing edge of the blade. | 08-11-2011 |
| 20110211967 | HYBRID METAL FAN BLADE - A fan blade is disclosed comprising a lightweight metallic airfoil portion and a high-strength sheath portion. The airfoil portion has a forward airfoil edge, a first airfoil surface, and a second airfoil surface. The sheath portion has a sheath head section, a first sheath flank, and a second sheath flank, both flanks extending chordwise from the forward sheath section. The sheath portion is bonded to the airfoil portion such that the sheath head section covers the forward airfoil edge, defining a blade leading edge. The first sheath flank covers a portion of the first airfoil surface proximate the airfoil forward edge, jointly defining a blade suction surface. The second sheath flank covers a portion of the second airfoil surface proximate the airfoil forward edge, jointly defining a blade pressure surface. | 09-01-2011 |
| 20110229334 | COMPOSITE LEADING EDGE SHEATH AND DOVETAIL ROOT UNDERCUT - An airfoil having a composite blade formed from a plurality of plies and having a leading edge and a root for attachment to an engine. The blade has a decreased number of plies at the junction of the blade leading edge and the root. A metallic sheath is attached to the leading edge, wherein the sheath has a portion proximate the junction of sufficient thickness to restore at least a portion of the decreased number of plies | 09-22-2011 |
| 20110229335 | MACHINE FOR CENTRIFUGALLY SHOOTING ABRASIVES - A machine for centrifugally shooting abrasives that shoots the abrasives by rotation of an impeller is provided. In the machine, the impeller comprises a pair of disc-shaped side plates that face each other at a predetermined distance and a plurality of blades disposed between the side plates in the radial direction of the side plates. The impeller is mounted on a hub that is fitted into an output shaft of an electric motor. The impeller is covered by a cover. The side liner and blades of the machine can be easily replaced. A side liner | 09-22-2011 |
| 20110250075 | ROTOR BLADE ASSEMBLY - A rotor blade assembly is disclosed herein. The rotor blade assembly includes a composite blade portion extending a length from a root to a tip. A leading edge of the composite blade portion extends from the tip to an end point along the length between the tip and the root. The rotor blade assembly also includes a base portion fixed to the composite blade portion proximate to the root. The rotor blade assembly also includes a sheath extending around the composite blade portion. The sheath is positioned along the length adjacent to the base portion and between the root and the end point of the leading edge. | 10-13-2011 |
| 20110274551 | PRODUCTION METHOD OF LEADING EDGE REINFORCEMENT OF FAN BLADE - A production method enables use of ultrasonic forming but does not leave a bonding face in a final product. | 11-10-2011 |
| 20120020802 | COMPRESSOR BLADE OF A GAS-TURBINE ENGINE WITH A SELF-SHARPENING LEADING-EDGE STRUCTURE - A compressor blade | 01-26-2012 |
| 20120057983 | METHOD FOR FORMING SURFACE LAYER, METHOD FOR FORMING EROSION RESISTANT COMPONENT AND STEAM TURBINE BLADE - A method for forming a surface layer, the method including: arranging a member in a machining fluid; and forming a surface layer including silicon by supplying silicon component from the silicon electrode to the member side by applying a predetermined voltage and generating electric discharge, wherein a value of an electric discharge detection level is set to be equal to or larger than a value obtained by adding a voltage depression at the silicon electrode to an arc potential during electric discharge, and wherein the surface layer is formed on a surface of the member by repetitively performing, after the voltage is applied, detecting the electric discharge generated between the silicon electrode and the member by detecting a drop of the voltage to be lower than the electric discharge detection level, stopping applying the voltage for a predetermined time, and applying the voltage again after a predetermined break time. | 03-08-2012 |
| 20120082553 | METAL ENCAPSULATED STATOR VANE - A hybrid vane airfoil for a gas turbine engine, such as a vane of a compressor stator, is disclosed which includes a non-metallic core, and an outer metallic shell at least partially covering the non-metallic core and which defines an outer surface of the airfoil. The non-metallic core is composed for example of a polymer, and the metallic outer shell is composed of a nanocrystalline metallic coating. | 04-05-2012 |
| 20120141282 | WIND-TURBINE ROTOR BLADE - An object is to improve the buckling strength with respect to a load in the edge direction, to bring the safety factor for the buckling strength closer to the safety factor for the material strength, and to achieve a further reduction in weight. A wind-turbine rotor blade ( | 06-07-2012 |
| 20120156048 | WIND TURBINE BLADE WITH MODULAR LEADING EDGE - A wind turbine blade has a leading edge and a trailing edge and includes an upper shell member and a lower shell member. The shell members include transversely spaced attachment edge that are spaced rearward of the leading edge. A preformed bond cap having opposite legs with rearward edges is mounted to the attachment edges of the upper and lower shell members. The bond cap is preformed into an aerodynamic parabolic shape and size so as to define the leading edge of said blade and lie essentially flush with the upper and lower shell members. The bond cap defines a primary external bonding bridge between the upper and lower shell members and defines at least a portion of the leading edge of the blade. | 06-21-2012 |
| 20120156049 | METHOD AND COATING FOR PROTECTING AND REPAIRING AN AIRFOIL SURFACE - Disclosed is a field repairable coated airfoil such as a wing or a rotor blade having a leading edge protected by a spray applied or prefabricated variable thickness, multilayer coating system composed a primer or adhesive layer, a basecoat layer and a topcoat where the coating is continuously tapering having a thicker cross section at the leading edge and a thinner cross section at the trailing edge of the airfoil. | 06-21-2012 |
| 20120163981 | METHOD AND COATING FOR PROTECTING AND REPAIRING AN AIRFOIL SURFACE - Disclosed is a field repairable coated airfoil such as a wing or a rotor blade having a leading edge protected by a spray applied or prefabricated variable thickness, multilayer coating system composed a primer or adhesive layer, a basecoat layer and a topcoat where the coating is continuously tapering having a thicker cross section at the leading edge and a thinner cross section at the trailing edge of the airfoil. | 06-28-2012 |
| 20120177500 | ANGLED AIRFOIL EXTENSION FOR FAN BLADE - An angled fan blade extension includes an attachment portion and an angled portion. The attachment portion is configured to facilitate securing the angled fan blade extension to the distal end of a fan blade. The angled portion is configured to extend from the distal end of the attachment portion, creating an angled extension relative to the fan blade. Adding angular fan blade extensions to fan blades may improve the airflow control, and thereby increase the utility and efficiencies of a fan. | 07-12-2012 |
| 20120257981 | RETENTION DEVICE FOR A COMPOSITE BLADE OF A GAS TURBINE ENGINE | 10-11-2012 |
| 20120275924 | INTERLOCKING BLADE SHEATH - A blade assembly includes a blade body and at least one sheath assembly located at a leading edge of the blade assembly. The at least one sheath assembly is retained to the blade body in a chordwise direction via an interlocking arrangement between the at least one sheath assembly and the blade body. A tip cap is located at a tip portion of the blade and secured to the blade body thus securing the at least one sheath assembly to the blade body in a spanwise direction. A method of assembling an airfoil includes securing at least one sheath assembly to a leading edge of a blade body via an interlocking arrangement between the at least one sheath assembly and the blade body, and assembling a tip cap to the blade body, thereby retaining the at least one sheath assembly to the blade body in a spanwise direction. | 11-01-2012 |
| 20120328445 | GRIT BLAST FREE THERMAL BARRIER COATING REWORK - A grit blast free method of removing a ceramic thermal barrier layer from a turbine component is described. The method comprises removing the layer in an autoclave with a caustic medium followed by a low pressure water jet wash. The component is dried in a stream of hot dry nitrogen and a new thermal barrier coating is applied before the component reenters product flow. | 12-27-2012 |
| 20120328446 | TURBINE AIRFOIL OF COMPOSITE MATERIAL AND METHOD OF MANUFACTURING THEREOF - A turbine blade having a root and a tip and an airfoil with a core section made of composite material and a protective sheath or layer joined to the composite core at a location or locations exposed to erosion is described with the composite core of the airfoil being continuous from a location in vicinity of the root to a location in vicinity of the tip of the blade and including a section which widens with distance from the rotational axis along the length of the airfoil and which ends at the location in vicinity of the tip of the blade. The protective sheath or layer is secured by interference fit with widening section of the core. | 12-27-2012 |
| 20130004322 | FAN BLADE WITH SHEATH - A fan blade includes an airfoil with a leading edge and a trailing edge in a chordwise direction, a root and a tip in a spanwise direction; and a sheath with a solid portion to cover the leading edge and first and second flanks extending in the chordwise direction to bond to the pressure and suction sides of the airfoil, respectively. The dimensions of the sheath are varied with respect to the spanwise direction of the blade. | 01-03-2013 |
| 20130004323 | FAN BLADE PROTECTION SYSTEM - A method for protecting a fan blade with an airfoil, a tip, a root and a sheath, the root to be inserted into a hub includes peening the airfoil of the blade; inserting a scrim cloth between the fan blade and the sheath to galvanically isolate the fan blade from the sheath; bonding the sheath to the blade with an epoxy adhesive; peening the blade root; bonding wear pads to the root with epoxy adhesive to galvanically isolate the root from the hub; applying a protective cover to the tip of the blade; and applying a coating to all exposed areas of the blade to inhibit corrosion. | 01-03-2013 |
| 20130004324 | NANO-STRUCTURED FAN AIRFOIL SHEATH - A method of forming a sheath for a fan airfoil having a leading edge, a trailing edge, a tip, a root, a suction side and a pressure side includes electroplating a nano-structured material to form a sheath with a solid portion to wrap around the leading edge and first and second flanks to secure the solid portion to the pressure side and the suction side of the airfoil. | 01-03-2013 |
| 20130045105 | WIND TURBINE BLADE AND METHOD OF PROTECTING THE SAME - A turbine blade for a wind turbine includes a leading edge, a trailing edge and a recess located within the leading edge. The blade further includes a protective layer having an inner side and outer side, the inner side is sized and orientated to locate within the recess to facilitate withstanding impact forces applied by an object. | 02-21-2013 |
| 20130071252 | Rotor Blade Erosion Protection System - The present application includes a rotor blade having an erosion protective coating, the coating being a cermet material configured to protect against erosion during the operation of the rotor blade. Further, the present application includes a method of selectively applying the erosion protective coating, a method of selectively repairing/reapplying the erosion protective coating, and a process of developing an erosion surface model map of an optimized erosion protective coating pattern and thickness. | 03-21-2013 |
| 20130101425 | Turbine Blade, and Turbine Rotor and Steam Turbine Using the Turbine Blade - Disclosed is a turbine blade including a turbine blade substrate including an iron-base alloy; an erosion shield plate including a Co-base alloy; and a shim including a Ni—Fe alloy, in which the erosion shield plate is fixed to a leading edge of the turbine blade substrate with the shim therebetween by an electron beam welding. Thus, a turbine blade having a highly reliable, bonded portion of an erosion shield, and a turbine rotor and a steam turbine using the turbine blade are provided. | 04-25-2013 |
| 20130101426 | BLADE AND LAMINATED PROTECTIVE SHEET FOR THE BLADE - A scratch-resistant blade such as an FRP wind turbine blade and a blade protective sheet which can be easily repaired when scratched. A blade is provided with a laminated protective sheet bonded to at least part of a leading edge of an FRP blade body of said blade, wherein the laminated protective sheet comprises an adhesive layer, a intermediate fabric layer and a durable surface layer, in that order from the blade body. | 04-25-2013 |
| 20130149163 | Method for Reducing Stress on Blade Tips - A turbine engine component has an airfoil portion with a tip portion and the tip portion has at least one chamfered edge on one side. If desired, the tip portion may have a first chamfered edge on a first side and a second chamfered edge on a second side opposed to the first side. A flattened tip portion may extend between the first and second chamfered edges. A tip treatment may be applied to the flattened tip portion. | 06-13-2013 |
| 20130236322 | EROSION RESISTANT AND HYDROPHOBIC ARTICLE - An erosion resistant and hydrophobic article includes a core that has a first hardness and a surface on the core. The surface includes a plurality of geometric features that have a second, greater hardness. The geometric features define a surface porosity by area percent and a corresponding surface solidity by area percent. The surface includes a ratio of the surface solidity divided by the surface porosity that is 1.8 or greater. The geometric features and the ratio establish the surface to be hydrophobic, and the second, greater hardness and the ratio establish an erosion rate of the surface that is equal to or less than an erosion rate of the core under identical erosion conditions. | 09-12-2013 |
| 20130259698 | Method of Joining at Least Two Components, a Method for Rendering a Component Resistant to Eroision, and a Turbine Blade - A method of joining at least two components, a method of preventing erosion of a base component and a turbine blade is provided. The method of joining at least two components includes providing a laser cladding apparatus, aligning a first component and second component, and jointing the first and second components by laser cladding. The first component includes a first joining surface adjacent to a seconding joining surface of the second component. The first joining surface and the second joining surface are joined by laser cladding along a joining plane. A joining material from the laser cladding provides at least one joining layer between the first joining surface and the second joining surface. The first and second joining surfaces include a bevel angle. A method for rendering a component resistant to erosion and a turbine blade are also provided. | 10-03-2013 |
| 20130259699 | MOVABLE BLADE FOR A TURBOMACHINE - A movable blade for a turbomachine, the blade including at its distal end a top portion including opposite first and second side edges and upstream and downstream sealing wipers. Each of the first and second side edges has a substantially Z-shaped profile between the upstream and downstream wipers. On a side of the first side edge, the platform includes a first outwardly projecting rim not connected to either of the upstream and downstream wipers. The platform includes a second outwardly projecting rim, the second rim including a downstream portion connected to the downstream wiper and extending along the second edge, and an upstream portion extending the downstream portion as far as the upstream wiper, and set back relative to the second side edge. | 10-03-2013 |
| 20140023511 | WIND TURBINE BLADE HAVING A CORROSION PROTECTION STRUCTURE, AND WIND TURBINE HAVING THE SAME - The present invention relates to a wind turbine component, having a connecting portion for connecting the wind turbine component to another turbine component and at least part of the connecting portion is formed of a first type of metal, characterized in that: the connecting portion is further provided with an additional part formed of a second type of metal which is connected to the metallic part of the connecting portion; and the second type of metal is more active than the first type of metal, whereby the additional part forms a sacrificial anode. The present invention further relates to a wind turbine having the above component. | 01-23-2014 |
| 20140093378 | EROSION AND FATIGUE RESISTANT BLADE AND BLADE COATING - A coating is described for an airfoil blade component. The coating comprises a cermet material and has, when applied to the rotor blade, a compressive residual stress greater than about 60 ksi. In another embodiment, the compressive residual stress of the coating is in the range of approximately 90-110 ksi. | 04-03-2014 |
| 20140093379 | GAS TURBINE ENGINE COMPONENT - A gas turbine engine component is described which ( | 04-03-2014 |
| 20140154089 | PROFILED PROTECTIVE TAPE FOR ROTOR BLADES OF WIND TURBINE GENERATORS - A multilayer protective tape for rotor blades of wind energy turbines said tape having a protective top layer comprising a polymer film and an adhesive bottom layer, wherein the top layer has a continuous surface (S) that is outwardly curved or outwardly trapezoidal surface such that the tape has a cross-sectional profile having an inner section between two lateral sections and wherein the inner section has a thickness (Ti) made up by the thickness of the top layer and adhesive bottom layer that is greater than the thickness of at least one of the lateral sections (T1,T2) made up by the thickness of the top layer and adhesive bottom layer and wherein the thickness (T1 or T2) of at least one lateral section is at most 600 μm and the thickness of the inner section (Ti) is at least 330 μm. Also provided are processes for making profiled tapes and methods for applying the tapes to rotor blades and blades containing protective tapes. | 06-05-2014 |
| 20140186188 | WIND TURBINE BLADE AND WIND TURBINE GENERATOR HAVIGN THE SAME - A wind turbine blade attached to a hub of a wind turbine generator is provided with a blade body; a first covering layer covering at least a leading edge in a first region including a tip part of the blade body; and a second covering layer covering at least the leading edge in a second region of the blade body, the second region being disposed on a hub side of the first covering layer, and the first covering layer has a higher erosion resistance than the second covering layer. | 07-03-2014 |
| 20140219808 | SHEATH WITH EXTENDED WINGS - A sheath for a fan airfoil having a leading edge and a trailing edge in a chordwise direction, a tip and a root in a spanwise direction, a suction side and a pressure side includes a solid portion to wrap around the airfoil leading edge; a first wing attached to the suction side of the airfoil; and a second wing attached to the pressure side of the airfoil. At least one of the first wing and the second wing extends at least about 35% of the chord of the airfoil. | 08-07-2014 |
| 20140271214 | AMORPHOUS METAL ROTOR BLADE ABRASION STRIP - A rotor blade abrasion strip and method to manufacturing the same. The abrasion strip being composed of a molded amorphous metal contoured to match a leading edge outer surface of the rotor blade. The abrasion strip being configured to removably attach to a leading edge of the rotor blade and configured to prevent damage to the leading edge during flight. The method includes molding the abrasion strip with the amorphous metal. | 09-18-2014 |
| 20140271215 | Systems and Methods of Constructing Composite Assemblies - A method of constructing a cured composite assembly includes positioning a composite assembly within a bonding tool, wherein the composite assembly comprises an uncured composite spar and a skin and performing a curing cycle on the composite assembly to simultaneously cure the uncured composite spar and bond the skin to the cured composite spar. | 09-18-2014 |
| 20140271216 | HORIZONTAL AXIS WIND OR WATER TURBINE WITH FORKED OR MULTI-BLADE UPPER SEGMENTS - Efficiency of a horizontal axis wind/water turbine (HAWT) is increased by the addition of a secondary blade associated with each main blade. The secondary blade is preferably a blade segment paralleling the main blade only in the outer reach of the main blade. The secondary blade travels rotationally ahead of the main blade and axially behind it, in an area in which air has not been disturbed by the main blades and in which disturbance of air by the secondary blade is not seen by the main blades. In one embodiment the secondary blade is carried by its associated main blade. In another embodiment, the secondary blades are carried by a ring or wheel which rotates with the main blades and the axle to which they are attached. | 09-18-2014 |
| 20140369845 | WIND TURBINE BLADE WITH EXTENDED SHELL SECTION - The present invention relates to a manufacturing method for wind turbine blade and a wind turbine manufactured according to that method. The wind turbine blade comprises two shell parts wherein each shell part has a leading edge connected to a trailing edge via an inner surface. One of the two shell parts comprises an extended shell section which is configured as a flexible shell section. The shell section is configured to flex in a radial direction from a first position to a second position relative to the leading edge when an incoming wind is acting on the pressure side of the wind turbine blade. The wind turbine blade may be manufactured using a non-bonding layer removable arranged adjacent to the glue line between the two shell parts which reduces the amount of manual grinding or polishing of the glue region. This provides a wind turbine blade with an improved blade characteristic where the extended flexible shell section is specifically designed to have significant flexibility. The configuration provides a method for passively controlling the lift of the wind turbine blade. | 12-18-2014 |
| 20140369846 | EROSION RESISTANT IMPELLER VANE MADE OF METALLIC LAMINATE - An impeller vane includes at least a first metallic core material and at least a first wear resistant material, wherein the hardness of the at least first wear resistant material exceeds the hardness of the at least first metallic core material. The impeller vane consists of a plurality of layers of the at least first metallic core material and the at least first wear resistant material, wherein the layers extend from a leading edge of the impeller vane to the trailing edge of the impeller vane and are arranged alternatingly throughout the cross section of the impeller vane. An impeller includes at least one of the above impeller vanes. The invention also relates to methods for manufacturing an impeller vane and an impeller having such. | 12-18-2014 |
| 20150017010 | TURBOMACHINE BLADE COMPRISING AN INSERT PROTECTING THE BLADE TIP - A turbomachine rotor blade, which includes a body radially extending and an insert covering the body tip, the insert being made of a first portion radially covering the blade tip and of a second portion partly covering the intrados face of the blade. The cross-section of the insert along a radial plane with respect to an axis of a rotor is corner-shaped and the first portion of the insert extends tangentially with respect to the main axis of the rotor and the second portion extends globally radially with respect to the main axis of the rotor. | 01-15-2015 |
| 20150044056 | AIRFOIL WITH LEADING EDGE REINFORCEMENT - A leading edge member for a composite vane of a gas turbine engine. The leading edge member includes a first leg and a second leg. The first leg includes a proximal end joined to a proximal end of the second leg. | 02-12-2015 |
| 20150086376 | EROSION SHIELD, METHOD OF FABRICATING A SHIELD, AND METHOD OF FABRICATING AN ARTICLE HAVING A SHIELD - A method of fabricating a near-net shape erosion shield, a method of forming a shielded article, and a near-net shape erosion shield are provided. The method of fabricating a near-net shape erosion shield includes providing a base, positioning an energy source relative to the base, and depositing at least one wear resistant material over the base with an energy beam from the energy source. The at least one wear resistant material deposited on the base forms the near-net shape erosion shield configured to be positioned on a turbine component. The method of forming a shielded article includes removing the base from the near-net shape erosion shield, and securing the near-net shape erosion shield to a turbine component. The near-net shape erosion shield includes a near-net shape erosion-resistant portion configured to be positioned on a turbine component. | 03-26-2015 |
| 20150086377 | METHOD OF MAKING A METAL REINFORCING MEMBER FOR A BLADE OF A TURBINE ENGINE - A method of making a metal reinforcing member that is to be mounted on a leading edge or a trailing edge of a composite blade of a turbine engine, the method including: shaping two metal sheets, positioning them on either side of a core including at least one recess that is to form a mold for a spacer for positioning the reinforcing member, assembling them together under a vacuum, conforming them against the core by hot isostatic compression, and cutting them to separate the reinforcing member and release the core. | 03-26-2015 |
| 20150104324 | FAN ROTOR BLADE OF AIRCRAFT JET ENGINE - A fan rotor blade includes a blade body made from a composite material of a resin and fibers, and having a pressure surface and a suction surface. A dovetail capable of being fitted into a fitting groove in a fan disk is provided in a base end of the blade body. The blade body is provided with a sheath. The sheath is more rigid than the blade body and is fixed to the blade body in a state where the sheath covers a leading edge portion of the blade body and the vicinity thereof. The sheath extends in the longitudinal direction of the blade body from a blade root side to a tip end side of the blade body, and a base end portion of the sheath located on the blade root side of the blade body extends to the dovetail. | 04-16-2015 |
| 20150104325 | FAN ROTOR BLADE OF AIRCRAFT JET ENGINE - A fan rotor blade includes a blade body made from a composite material of a resin and fibers, and having a pressure surface facing one side in a rotation direction and a suction surface facing the other side in the rotation direction. The blade body is provided with a sheath which is more rigid than the blade body and is fixed to the blade body in a state where the sheath covers a leading edge portion of the blade body, which is located on an upstream side in the direction of intake of external air, and the vicinity thereof. A tip end portion of the sheath extends from the leading edge portion side of the blade body to a trailing edge portion side of the blade body. An end portion of the tip end portion of the sheath is flush with the trailing edge portion of the blade body. | 04-16-2015 |
| 20150110636 | WEAR PAD TO PREVENT CRACKING OF FAN BLADE - A fan blade of a gas turbine engine includes an airfoil, a root received in a slot of a hub, and a wear pad covering at least a portion of the root and made of an integrally bonded woven composite laminate. | 04-23-2015 |
| 20150125308 | MANUFACTURE OF FILLED AEROFOIL - A method of manufacturing a filled aerofoil component ( | 05-07-2015 |
| 20150132140 | EROSION SHIELD FOR A WIND TURBINE BLADE - An erosion shield for a wind turbine blade is described, the erosion shield having a plurality of layers of erosion resistant material. The layers of erosion resistant material have an adhesive bond strength between adjacent layers less than the cohesive tensile strength of the layers, such that the outer layers of erosion resistant material are arranged to peel away or delaminate from the erosion shield under the action of the wind once the particular layer is ruptured or eroded. This dynamic removal of the outer layers of the erosion shield provides for increased shield lifetime, and a reduction in the maintenance operations required for a wind turbine blade having such an erosion shield. | 05-14-2015 |
| 20150147183 | Propeller With Lightening Strike Protection - A propeller blade assembly including a propeller blade having a leading edge, and a trailing edge extending between a tip and a hub, and an electrically conductive band extending longitudinally on either or both of the leading edge and trailing edge. The electrically conductive band secured to the leading edge of the propeller serves as an entry point on the aircraft and conductive channel into the airframe thereby avoiding the potentially damaging effect of the lightening on the carbon fiber composite propeller. | 05-28-2015 |
| 20150377030 | Locally Extended Leading Edge Sheath for Fan Airfoil - A sheath, for protecting the leading edge of airfoils used in gas turbine engines, may have a solid member, a pressure side flank and a suction side flank. The solid member may form an outer edge, which may include a main portion and a projecting portion. The projecting portion may have a variable dimension. The pressure side flank and suction side flank may project from the solid member opposite the outer edge. The pressure side flank and suction side flank may form a receiving cavity for receiving an airfoil. | 12-31-2015 |
| 20160001407 | Leading Edge Sheath Manufacturing Method - A method for manufacturing a protective sheath for a fan blade leading edge is described. The method may comprise generating a preform plate from a stock plate wherein the preform plate has a flattened surface and an inclined surface having a spike flanked by a first side and a second side. The method may further comprise bending the first side and the second side away from the spike to generate a sheath intermediate followed by generating the protective sheath from the sheath intermediate by shaping an outer surface and an inner surface of the sheath intermediate to match the contour of the fan blade leading edge. | 01-07-2016 |
| 20160003057 | ROTARY BLADE - A rotary blade tip insert for incorporation into a rotary blade, for example, a rotary fan blade in a gas turbine engine. The tip insert comprises a sleeve for insertion into a recess provided in said rotary blade. The sleeve has a radially outer end defining an opening, a radially inner end and opposing wall portions extending between said ends. The tip insert further comprises a tip element having a crown portion and a root portion for insertion into the opening of said sleeve. | 01-07-2016 |
| 20160003060 | HYBRID FAN BLADES FOR JET ENGINES - A fan blade for a jet engine, such as a turbo fan jet engine is disclosed. The fan blade includes a root for coupling the fan blade to a rotating hub. The root is connected to a blade portion or an airfoil. The blade includes a leading edge and a trailing edge. The leading edge includes at least one of a protrusion or a recess along the leading edge to enhance the structural characteristics of the blade portion. To ensure that the recess or recesses and/or protrusion or protrusions do not adversely affect the aerodynamic qualities of the fan blade, the leading edge of the blade portion is covered by a protective sheath. The sheath may be fabricated from a titanium alloy and is typically adhered to the blade portion using an adhesive, such as an epoxy. | 01-07-2016 |
| 20160003062 | Fan Blades with Protective Sheaths and Galvanic Shields - Light weight fan blades for turbofan jet engines are disclosed. The fan blades may be fabricated from an aluminum alloy. To enhance the hardness of the leading edge of the fan blade, a titanium sheath may be attached to the leading edges of the fan blades. To prevent galvanic coupling between the titanium and the aluminum, a polymeric liner may be disposed between the protective titanium sheath and the aluminum fan blade. The liner may be fabricated from a polymer material, such as a polyimide or another high performance polymer. | 01-07-2016 |
| 20160009369 | PROTECTIVE MAT FOR LEADING EDGES OF AIRFOIL ELEMENTS | 01-14-2016 |
| 20160084093 | Turbine Airfoil of Composite Material and Method of Manufacturing Thereof - A turbine blade having a root and a tip and an airfoil with a core section made of composite material and a protective sheath or layer joined to the composite core at a location or locations exposed to erosion is described with the composite core of the airfoil being continuous from a location in vicinity of the root to a location in vicinity of the tip of the blade and including a section which widens with distance from the rotational axis along the length of the airfoil and which ends at the location in vicinity of the tip of the blade. The protective sheath or layer is secured by interference fit with widening section of the core. | 03-24-2016 |
| 20160108743 | Turbine Blade, and Turbine Rotor and Steam Turbine Using the Turbine Blade - Disclosed is a turbine blade including a turbine blade substrate including an iron-base alloy; an erosion shield plate including a Co-base alloy; and a shim including a Ni—Fe alloy, in which the erosion shield plate is fixed to a leading edge of the turbine blade substrate with the shim therebetween by an electron beam welding. Thus, a turbine blade having a highly reliable, bonded portion of an erosion shield, and a turbine rotor and a steam turbine using the turbine blade are provided. | 04-21-2016 |
| 20160123158 | ROTOR BLADE WITH EDGE PROTECTION - The invention relates to sheath for a blade that has a uniform assembly direction over the radial height of the sheath whether the blade has a straight or curved trajectory. This is achieved by the a sheath formed around the edge, having a first inner surface wherein a first tangential vector projected tangentially to the first inner surface in a direction away from the head portion in an longitudinal plain forms a first angle with the rotational axis that does not vary over the radial height of the sheath while a second tangential vector projected tangentially from any point of the second inner surface of the sheath in a direction towards the head portion intersects the first tangential vector. | 05-05-2016 |
| 20160169008 | SYSTEM AND METHOD FOR BLADE WITH PROTECTIVE LAYER | 06-16-2016 |
| 20160169009 | EROSION RESISTANT MATERIAL AND TURBINE BLADE | 06-16-2016 |
| 20160201471 | FAN BLADE ASSEMBLY | 07-14-2016 |
| 20160201482 | ALUMINUM AIRFOIL WITH TITANIUM COATING | 07-14-2016 |
