Abstract: A multi segment wind turbine blade comprises at least two blade segments. A first blade segment comprises an outer skin, a bulkhead, and first alignment brackets removably coupled to the outer skin of the first blade segment. A first portion of a flange of the bulkhead is bonded to the first blade segment and a second portion of the flange of the bulkhead projects out from the first blade segment. A second blade segment comprises an outer skin and second alignment brackets removably coupled to the outer skin of the first blade segment. The first and second alignment brackets are alignable upon the outer side of the second blade segment being inserted over the second portion of the flange of the bulkhead.

Abstract: A multi-segment wind turbine blade comprises at least two blade segments. A first spar cap segment is attached to a first blade segment and a second spar cap segment is attached to a second blade segment. The first and second spar cap segments are configured to form a scarf joint. First and second spar cap brackets are attached in locations of the first and second spar cap segments, respectively, selected to facilitate alignment of the first and second spar cap segments at the scarf joint. At a field site, the first and second spar cap segments are bonded after fastening the first and second spar cap brackets.

Abstract: A composition includes a polymer precursor and a coupling agent composition capable of bonding to a filler having a corresponding binding site. The polymer precursor includes cycloolefin and the coupling agent has at least one functional group that is an epoxy, an amine, an imine, a thiol, a carboxylic acid, a cyanato, a carboxylic acid anhydride, a cyano group, or a silane group. A method to make the composition is also provided.

Abstract: The invention provides a method of bonding a sensor to a surface comprising the steps of applying a thermoplastic film to a first surface of the sensor. The first surface of the sensor is contacted with a surface of an object to be monitored, wherein the composition effectively bonds the sensor to the object surface at a temperature up to approximately 250° C. The invention also provides a method of bonding a sensor to a surface comprising the steps of applying a thermoplastic film to a surface area of an object to be monitored. The first surface of a sensor is contacted with the object surface area, wherein the film effectively bonds the sensor to the object surface at a temperature up to approximately 250° C.

Abstract: A composition includes a first cycloolefin substituted with at least one epoxy group and an aromatic amine. The composition is capable of bonding to a filler having a corresponding binding site. The composition is compatible with a metathesis catalyst capable of catalyzing a ring-opening metathesis polymerization reaction when contacted to the first cycloolefin. An associated method is also provided.

Abstract: A composition includes a coupling agent composition and a polymer precursor. The coupling agent composition includes an aromatic amine and a first cycloolefin substituted with at least one epoxy group. The polymer precursor includes a second cycloolefin. The coupling agent composition is capable of bonding to a filler having a corresponding binding site and the coupling agent composition is compatible with a metathesis catalyst capable of catalyzing a ring-opening metathesis polymerization reaction when contacted to the first cycloolefin or the second cycloolefin. An associated method is also provided.

Abstract: An article includes a reaction product of a filler having binding sites, a coupling agent composition including an aromatic amine and a first cycloolefin substituted with at least one epoxy group, a polymer precursor including a second cycloolefin, and a metathesis catalyst capable of catalyzing a ring-opening metathesis polymerization reaction when contacted to the first cycloolefin or the second cycloolefin. The coupling agent composition is capable of bonding to the filler and the coupling agent composition is compatible with a metathesis catalyst. An associated method is also provided.

Abstract: A composition includes a coupling agent composition and a polymer precursor. The coupling agent composition includes an aromatic amine and a first cycloolefin substituted with at least one epoxy group. The polymer precursor includes a second cycloolefin and an epoxy compound. The coupling agent composition is capable of bonding to a filler having a corresponding binding site and the coupling agent composition is compatible with a metathesis catalyst capable of catalyzing a ring-opening metathesis polymerization reaction when contacted to the first cycloolefin or the second cycloolefin. An associated method is also provided.

Abstract: A method for manufacturing a multi-resin composite article is provided. The method comprises providing at least one fiber preform in a mold; injecting a plurality of resins into the at least one fiber preform at a plurality of locations on the at least one fiber preform; and forming at least one transition region along a mutual contact surface between the resins. Each of the at least one transition regions is defined by a gradual transition in composition from one of the resins to another of the resins. A multi-resin composite article is also provided. The article comprises: at least one fiber preform; a plurality of resins, wherein the at least one fiber preform is infused with the resins; and at least one transition region extending along a mutual contact surface between respective ones of the resins. A system for manufacturing such a multi-resin composite article is also provided.

Abstract: To address certain deficiencies of carbon fiber material as a filler in a hybrid blade, a glass composite layer is provided as a barrier layer between a carbon fiber resin filler and the metallic main body of the blade. The glass composite layer also advantageously provides a gradient in thermal expansion between the carbon fiber composite and the body of the blade (steel) to reduce interfacial residual stress.

Abstract: To address certain deficiencies of carbon fiber material as a filler in a hybrid blade, a glass composite layer is provided as a barrier layer between a carbon fiber resin filler and the metallic main body of the blade. The glass composite layer also advantageously provides a gradient in thermal expansion between the carbon fiber composite and the body of the blade (steel) to reduce interfacial residual stress.

Abstract: A steam turbine system for use in conjunction with hybrid last stage(s) LP buckets. The system is adapted to cool the bucket tip region during low VAN windage conditions whereby the beneficial design and efficiency outcomes of the use of hybrid blades can be realized.

Abstract: An enclosure for a rotor in a generator including the rotor, rotor windings and a stator, the enclosure comprising a plurality of composite rings located adjacent one another along a length dimension of the rotor so as to contain the rotor windings on the rotor, the rings each comprising at least two layers selected from the group consisting essentially of metals, glass fiber laminates and graphite fiber laminates.

Abstract: An apparatus and method for fabricating a high performance reflective material for use on scintillator elements in a computed tomograph (CT) imaging device. Adjacent scintillator elements are separated by gaps filled with a reflective coating layer. In one embodiment, the reflective coating layer consists of a surface level coating layer, an adhesion layer, a metallic reflective layer, and a top layer consisting of either a barrier coating layer or a polymeric encapsulant, or both. In another embodiment, the metallic reflective coating layer is applied to the scintillator element via an electroless metal deposition process utilizing a reducing agent and a metal complex. The CT reflectors formed by either embodiment have improved light output, minimized cross talk, higher geometric efficiency, and decreased performance degradation as compared with current CT reflectors that utilize organic binders and titanium dioxide fillers is achieved.

Abstract: The present invention provides tough, high modulus, low density thermoset polyurethane compositions which are useful in general as, for example, cast structural materials and in a preferred embodiment can be cured directly onto an aircraft engine fan blade, thereby providing a lighter blade, without concomitant loss in structural integrity or blade performance due to, for example, resistance to foreign object impacts and fuel efficiency. In a preferred embodiment, the composition is comprised of bis-amine compounds reacted with isocyanate-functional polyether polymers in the presence of hollow polymeric microspheres. The thermoset polymer compositions are formed by casting into a mold which is formed by a cavity within the metallic or composite fan blade or guide vane in the form of a pocket and a removable caul sheet. After the elastomeric polyurethane foam is injected through at least one injector port into the mold, the foam is cured.

Abstract: The present invention provides tough, high modulus, low density thermoset polyurethane compositions which are useful in general as, for example, cast structural materials and in a preferred embodiment can be cured directly onto an aircraft engine fan blade, thereby providing a lighter blade, without concomitant loss in structural integrity or blade performance due to, for example, resistance to foreign object impacts and fuel efficiency. In a preferred embodiment, the composition is comprised of bis-amine compounds reacted with isocyanate-functional polyether polymers in the presence of hollow polymeric microspheres. The thermoset polymer compositions are formed by casting into a mold which is formed by a cavity within the metallic or composite fan blade or guide vane in the form of a pocket and a removable caul sheet. After the elastomeric polyurethane foam is injected through at least one injector port into the mold, the foam is cured.

Abstract: Epoxy polymer precursors and epoxy polymers resulting therefrom are tolerant to bombardment by high-energy radiation. The epoxy polymer precursors comprise at least an epoxy resin free of aromatic units and at least a curing agent selected from the group consisting of aliphatic polyamines, cycloaliphatic polyamines, polyamides, aliphatic anhydrides, cycloaliphatic anhydrides, and mixtures thereof. In one embodiment of the invention the epoxy resin comprises at least a cycloparaffinic group, and the curing agent comprises a polyamine derived from cyclohexane. Such epoxy polymer compositions are used to form reflectors elements between adjacent scintillator elements in high-energy radiation detector array.

Abstract: A multi-component hybrid turbine blade comprises a shank portion and an airfoil portion. The airfoil portion comprises a composite section having a first density. The composite section comprises a recess and an insert section. The insert section has a second mass density, which is less than the first mass density. The insert section is disposed in the recess, and the insert section is bonded to the composite section. The composite section and the insert section together define an airfoil shape. A fabrication method comprising laying up composite material layers to form a portion of the composite section. The portion of the composite section comprises a recess. Disposing the insert section in the recess. Laying up additional composite material layers to achieve a final desired thickness of the composite section while covering the insert section.

Abstract: A multi-component hybrid turbine blade comprises a shank portion and an airfoil portion. The airfoil portion comprises a composite section having a first density. The composite section comprises a recess and an insert section. The insert section has a second mass density, which is less than the first mass density. The insert section is disposed in the recess, and the insert section is bonded to the composite section. The composite section and the insert section together define an airfoil shape. A fabrication method comprising laying up composite material layers to form a portion of the composite section. The portion of the composite section comprises a recess. Disposing the insert section in the recess. Laying up additional composite material layers to achieve a final desired thickness of the composite section while covering the insert section.

Abstract: The present invention provides tough, high modulus, low density thermoset polyurethane compositions which are useful in general as, for example, cast structural materials and in a preferred embodiment can be cured directly onto an aircraft engine fan blade, thereby providing a lighter blade, without concomitant loss in structural integrity or blade performance due to, for example, resistance to foreign object impacts and fuel efficiency. In a preferred embodiment, the composition is comprised of bis-amine compounds reacted with isocyanate-functional polyether polymers in the presence of hollow polymeric microspheres. The thermoset polymer compositions are formed by casting into a mold which is formed by a cavity within the metallic or composite fan blade or guide vane in the form of a pocket and a removable caul sheet. After the elastomeric polyurethane foam is injected through at least one injector port into the mold, the foam is cured.