Abstract: A component such as a blade for use in a gas turbine engine comprises a body 2 formed from outer panels 8, 10 defining an internal cavity 12. A damping element 14 is provided in the cavity 12 and is secured at one end between the panels 8, 10 at one end of the body 2, for example adjacent the root of the blade. Damping material fills the cavity 12 and so extends between the damping element 14 and the panels 8, 10. Vibration induced in the blade causes relative movement between the body 2 of the blade and the damping element 14, causing energy loss in the damping material which damps the vibration. The components 8, 10, 14 may be secured by a diffusion bonding process.

Abstract: Attaching a labyrinth seal composed of wear-resistant material to the surfaces of rotating equipment subject to wear can increase the life of the rotating equipment and reduce down-time for equipment maintenance and repairs.

Abstract: The present invention provides a structure comprising a blade attachment, a blade structure, an integrated driving shaft/generator for a wind system such as a vertical axis windmill, and a self erecting structure for such a wind system, together with an erecting method thereof.

Abstract: Methods for repairing and manufacturing a gas turbine blade, and the gas turbine blade repaired and manufactured with such methods are presented with, for example, the repair method comprising providing a gas turbine blade, the blade comprising a blade tip and a blade body; removing at least one portion of the blade tip; providing at least one freestanding tip insert; and disposing the at least one tip insert onto the gas turbine blade body such that the at least one tip insert replaces the at least one removed portion of the blade tip.

Abstract: A blade of an axial compressor comprising: an airfoil is disclosed that has a leading edge and a root; a platform attached to the root of the airfoil; a dovetail attached to a side of the platform opposite to the airfoil; a neck of the dovetail adjacent the platform, and a slot in the neck and generally parallel to the platform, and the slot extends from a front of the neck to position in the neck beyond a line formed by the leading edge of the blade.

Abstract: A lightweight, composite structural element for turbo engines, includes a thin metallic shell and a metallic core structure, of which a large proportion of the volume is empty space, the shell and the core structure being rigidly connected to each other. The core structure has a spatial, felt-like and/or mesh-like construction and is made of one or more wires, strips, shavings, or comparable elements. The core structure is sintered together, and sintered to the shell.

Abstract: The present invention provides a process for the lay-up of a composite laminate article, the article produced by this process, and the apparatus used to produce the composite laminate article. The composite laminate article may be, for example, an airfoil, particularly useful as a fan blade in a large high bypass ratio turbofan engine, wherein the blade is generally regarded as large and having a high degree of twist. In a preferred embodiment, the present invention provides a process for laying up a composite laminate article comprising a) reading a data set to enable the projection of an image of a ply section onto a work surface, the image indicating a ply section target point; b) laying up a ply section of composite laminating material within the image, wherein the ply section first contacts the work surface at the target point; and c) repeating steps (a)-(b) until the composite laminate article is complete.

Abstract: An airfoil body having a first wall including a plurality of ribs. An outer wall formed of a high temperature foil is attached to the ribs so as to form a plurality of channels. The first wall is protected from hot flowpath gases by the outer wall and by cooling air flowing through the channels.

Abstract: The invention relates to a wind turbine blade comprising a number of pre-fabricated strips arranged in a sequence along the outer periphery. The strips consist of a fibrous composite material, preferably carbon fibres, and consist of a wooden material, preferably plywood or wooden fibres held in a cured resin. The advantage is that it is possible to manufacture blades for wind turbines which are very stiff and generally have a high strength, but which nevertheless are easy to manufacture and also is much cheaper to manufacture compared to conventional manufacturing techniques. The invention also relates to methods for manufacturing prefabricated strips and for manufacturing wind turbine blades.

Abstract: In a joining method for manufacturing a rotor blade by joining a plurality of members, the members are pressed so as to exert a predetermined pressure on the bonding interface. A pulse voltage is applied to the members to pass electric current therethrough, and the joint portion is heated by resistance heating generated at the bonding interface and in the bulk of the members to cause diffusion bonding and thereby to join the members to each other. With this method, good joining can be achieved without substantially changing the crystal structure and mechanical properties of the base metals.

Abstract: A turbomachine turbine vane including a multiply-perforated liner defining an annular cavity between an outside wall of the liner and an inside wall of the vane, an air admission opening for feeding the inside of the liner with cooling air and an air exhaust opening for exhausting a fraction of the cooling air from the vane, the liner being secured to the vane at one end and being free at its other to slide along an inside edge of the vane under the effects of relative thermal expansion between the liner and the inside wall of the vane, the annular gap between said free end of the liner and the inside edge of the vane defining a leakage zone for cooling air and the inside edge includes a recess for generating head loss in this leakage zone so as to reduce the flow rate of cooling air passing therethrough.

Abstract: The turbine blade has a head (6) at its peripherally outer end, and on the outside face thereof there is formed at least one wiper (12) having a first end portion (16) and a second end portion (20), with a wiper tip (26) extending between the two end portions. The first portion (16) situated on the suction side of the blade is taller than the second end portion (20) so as to form a sawtooth effect between the wipers (12) of two adjacent blades mounted on a turbine rotor. The tip (26) of each wiper presents a convex surface between the first portion (16) and the second portion (20).

Abstract: A method of modifying a rotor blade, and a rotor blade are provided. The rotor blade is for a steam turbine and it is modified to facilitate altering a natural vibratory frequency of the rotor blade, the rotor blade includes a leading edge, a trailing edge, a first sidewall, and a second sidewall, wherein the first and second sidewalls are connected axially at the leading and trailing edges, and the sidewalls extending radially between a rotor blade root to a rotor blade tip. The method includes determining a vibratory resonance condition of the rotor blade and forming a blade extension between the rotor blade root and the rotor blade tip that alters the determined resonance condition.

Abstract: A turbine blade has an airfoil section with a root end and a tip end, and an attachment at the root end of the airfoil section. A blade tip seal is joined to the tip end of the airfoil section. The blade tip seal is formed as an open-cell solid aluminum oxide foam made of aluminum oxide cell walls having intracellular volume therebetween. The blade tip seal has a blade interface region adjacent to the tip end of the airfoil section. The blade interface region is formed of the aluminum oxide foam and a nickel-base alloy within the intracellular volume. The blade tip seal also has a contact region remote from the blade interface region and comprising the aluminum foam wherein the intracellular volume is porosity.

Abstract: To protect an article with an aerodynamic surface, such as an aeroplane propeller or helicotper rotor, from erosive damage caused by flying particulate matter, a thin elastomeric protective covering is provided. This layer covers approximately 15% of a forward face (15), a leading edge (12), and approximately 90% of the rear face (13) of the article. Typically it is made of polyurethane with hardness between 85 Shore A and 80 Shore D. It is applied by centrifugal casting using a silane log gammaglycidoxypropyl-trimethoxysilane as a coupling agent when bonding to a metal surface such as aluminium.

Abstract: A fan blade provided with an active carbon filter bed, wherein, an opening is provided in the center of the fan blade, and said opening is covered with an active carbon filter bed. And said active carbon filter bed can be in the form of powder, grain or fiber attached by any means to non-woven fabric, fiber layer, staple on the base filter element of porous PE or PU foam. Furthermore, both of the active carbon filter bed and the fan blade can be adhered to each other by glue, adhesive band, equi-directional magnet or other adhesion or structure.

Abstract: A hybrid vane (50) for a gas turbine engine having a ceramic matrix composite (CMC) airfoil member (52) bonded to a substantially solid core member (54). The airfoil member and core member are cooled by a cooling fluid (58) passing through cooling passages (56) formed in the core member. The airfoil member is cooled by conductive heat transfer through the bond ((70) between the core member and the airfoil member and by convective heat transfer at the surface directly exposed to the cooling fluid. A layer of insulation (72) bonded to the external surface of the airfoil member provides both the desired outer aerodynamic contour and reduces the amount of cooling fluid required to maintain the structural integrity of the airfoil member. Each member of the hybrid vane is formulated to have a coefficient of thermal expansion and elastic modulus that will minimize thermal stress during fabrication and during turbine engine operation.

Abstract: A connector sleeve 17 secured to the backing plate 7a of a wear-resistant liner 7 facilitates attachment of the liner 7 to the body9 of a rotor blade by virtue of welding of a thrust collar 20 to a portion of the connector sleeve 17 projecting past a bore 18 in the blade body 9. Removal of the liner later for replacement is possible by burning off the welds connecting the thrust collar to the connector sleeve. A clamping tool 22 comprising a tubular body 23 and a bolt 24 can be used to hold the thrust collar firmly against the back of the blade body 9 during the welding operation.

Abstract: A highly porous alumina material and a method for applying such material that is useful in the hot section of a jet aircraft engine. In order to manufacture the porous alumina, an aluminum-based metal/alumina material known in the art is first placed onto a metal alloy substrate. The aluminum-based metal is then dissolved using a solution that will not affect the alumina or the underlying substrate. The alumina is then washed with deionized water and dried. The resulting alumina has a porosity in the range of about 20% to about 45%. The alumina has globular interconnected surface features in the range of about 0.5 &mgr;m to about 20 &mgr;m.

Abstract: Attaching a labyrinth seal composed of wear-resistant material to the surfaces of rotating equipment subject to wear can increase the life of the rotating equipment and reduce down-time for equipment maintenance and repairs.

Abstract: A turbine blade assembly for a turbine assembly includes a turbine blade having a turbine blade damper cavity formed therein and stranded wire cable positioned within the turbine blade damper cavity. The stranded wire cable is maintained in the damper cavity during operation of the turbine blade assembly. It reduces vibration of the turbine blade assembly during operation by dissipating energy by friction between the stranded wire cable and the internal surface of the blade that defines the damper cavity. It also dissipates energy by friction between adjacent wires within the stranded wire cable.

Abstract: A turbomachine stator flap including a structural beam which is formed integrally with a structural core for a vane, and fastening portions, and a composite envelope surrounding the structural core and forming at least the aerodynamic profile of the vane.

Abstract: An article made of a metallic material and comprising a body and a body end portion integral with the body, includes a band of the metallic material at the end portion substantially through the entire end portion, the band being under a compressive stress greater than the body. An example of the article is a turbine engine blading member in which the body is the airfoil of the member and the band is disposed at the radially outer tip portion of the airfoil. One method for providing the band includes performing roller deformation on the end portion until a desired amount of compressive stress is developed in the band substantially through the entire end portion.

Abstract: A gas turbine engine fan blade (26) comprises a root portion (40) and an aerofoil portion (42). The aerofoil portion (42) has a leading edge (44), a trailing edge (46), a concave metal wall portion (50) extending from the leading edge (44) to the trailing edge (46) and a convex metal wall portion (52) extending from the leading edge (44) to the trailing edge (46). The aerofoil portion (42) has a hollow interior (54) and the interior (54) of the aerofoil portion (42) is at least partially filled with a vibration damping material (56). The vibration damping material (56) comprises a material having viscoelasticity for example one formed by mixing an amine terminated polymer and bisphenol a-epichlorohydrin epoxy resin.

Abstract: In order to create a rotor blade of hybrid design comprising a vane and a blade root, the vane having a first vane portion made of a metallic material and a second vane portion made of a lightweight material, provision is made for a rear edge of the rotor blade to be formed on the second vane portion, and for the second vane portion to be joined to the first vane portion in a single-section-type manner.

Abstract: Attaching a labyrinth seal composed of wear-resistant material to the surfaces of rotating equipment subject to wear can increase the life of the rotating equipment and reduce downtime for equipment maintenance and repairs.

Abstract: A turbine blade or turbine vane includes a metallic nonfoam region, and a ceramic foam region joined to the metallic region. The ceramic foam region is an open-cell solid ceramic foam made of ceramic cell walls having an intracellular volume therebetween. The ceramic is preferably alumina. The intracellular volume may be empty porosity, or an intracellular metal such as an intracellular nickel-base superalloy.

Abstract: A wind power generating system with an obstruction lighting or night marking device, and with at least one rotor blade allocated to a rotor hub which exhibits at least one optical waveguide, which is routed from the rotor blade hub-side end area to the rotor blade surface, and that a light source is allocated to the optical waveguide in the rotor blade hub-side end area.

Abstract: A turbine airfoil is provided having an integral tip cap and a pair of tip walls which extend radially outward past the tip cap to form a squealer tip. A coaxial pair of first and second holes extend through the tip cap and one of the tip walls respectively at an acute inclination angle, with the first hole being disposed so as to direct impingement cooling air on the tip wall having the second hole. A protective layer comprising a high temperature foil is disposed on the tip wall having the second hole therein.

Abstract: The present invention provides for a squealer tip to include some proportion of a highly oxidation-resistant material, and a method for casting same, such that if any environmental coating were removed, the tip would retain some increased level of environmental resistance. The oxidation-resistant material optionally may also be a high abrasion resistance material, such that recession of the tip due to rubbing against a stator would be reduced. In a preferred embodiment, an abrasion-resistant and/or oxidation-resistant material is placed and suitably anchored into the tip region of a wax precursor used to cast a turbine airfoil. During the casting operation, the abrasion-resistant and/or oxidation-resistant material is not completely melted. As the alloy used to form the majority of the turbine blade solidifies, the abrasion and/or oxidation resistant material is incorporated into the turbine airfoil by the solidification of the alloy around it.

Abstract: A HVOF process is used for applying brazing materials to repair surfaces of a substrate such as a turbine blade. The brazing material is applied in powdered form and is free of binders and adhesives. The brazing materials may be any one or more of a nickel based, cobalt based or ferrous based high temperature brazing material. Alloys of these elements may be used together with a temperature depressing melting point element such as boron or silicon.

Abstract: A gas turbine airfoil and methods for manufacturing and repair of an airfoil, the airfoil comprising a wall, the wall defining the perimeter of the airfoil and comprising a leading edge section and a trailing edge section, wherein a majority of the surface area of the wall comprises a first material, the first material having an oxidation resistance and a melting temperature, and at least one portion of the wall comprises a second material, the second material having an oxidation resistance that is greater than the oxidation resistance of the first material and a melting temperature that is at least about 83 degrees Celsius (about 150 degrees Fahrenheit) greater than the melting temperature of the first material, the at least one portion of the wall located in at least one section of the wall selected from the group consisting of the leading edge section and the trailing edge 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: An airfoil for a gas turbine includes a pressure sidewall and a suction sidewall, a tip cap, and a tip squealer. Cooling fluid flows from a hollow space within the airfoil through exit passages extending to the pressure side of the airfoil and to the tip cavity defined by the tip cap and the tip squealer. The tip squealer includes a smooth contour with curved and straight portions, allowing an even flow of the cooling fluid about the tip squealer and within the tip cavity. Furthermore, the exit passages are partially diffused and oriented at angles with respect to the radial direction. The smooth contour and shape of the exit passages avoids the formation of vortices and enhances film cooling of the tip squealer.

Abstract: In a joining method for manufacturing a rotor blade by joining a plurality of members, the members are pressed so as to exert a predetermined pressure on the bonding interface, a pulse voltage is applied to the members to pass electric current therethrough, and the joint portion is heated by resistance heating generated at the bonding interface and in the bulk of the members to cause diffusion bonding and thereby to join the members to each other. By this method, good joining can be achieved without substantially changing the crystal structure and mechanical properties of the base metals.

Abstract: An airfoil for a gas turbine engine, the airfoil having a core body with an airfoil body, an integral partial height squealer tip defining a tip shelf, and an integral tip cap between the airfoil body and the integral partial height squealer tip; and a squealer tip extension bonded to the partial height squealer tip. A method for manufacture and repair of an airfoil.

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: Attaching a labyrinth seal composed of wear-resistant material to the surfaces of rotating equipment subject to wear can increase the life of the rotating equipment and reduce downtime for equipment maintenance and repairs.

Abstract: The present invention provides for a squealer tip to include some proportion of a highly oxidation-resistant material, and a method for casting same, such that if any environmental coating were removed, the tip would retain some increased level of environmental resistance. The oxidation-resistant material optionally may also be a high abrasion resistance material, such that recession of the tip due to rubbing against a stator would be reduced. In a preferred embodiment, an abrasion-resistant and/or oxidation-resistant material is placed and suitably anchored into the tip region of a wax precursor used to cast a turbine airfoil. During the casting operation, the abrasion-resistant and/or oxidation-resistant material is not completely melted. As the alloy used to form the majority of the turbine blade solidifies, the abrasion and/or oxidation resistant material is incorporated into the turbine airfoil by the solidification of the alloy around it.

Abstract: Methods for repairing and manufacturing a gas turbine blade, and the gas turbine blade repaired and manufactured with such methods are presented with, for example, the repair method comprising providing a gas turbine blade, the blade comprising a blade tip and a blade body; removing at least one portion of the blade tip; providing at least one freestanding tip insert; and disposing the at least one tip insert onto the gas turbine blade body such that the at least one tip insert replaces the at least one removed portion of the blade tip.

Abstract: Methods for repairing and manufacturing a gas turbine airfoil, and the airfoil repaired and manufactured with such methods are presented with, for example, the repair method comprising providing an airfoil having specified nominal dimensions, the airfoil comprising a first material, the first material having a creep life and a fatigue life, the airfoil further comprising a leading edge section and a trailing edge section; removing at least one portion of at least one section of the airfoil to create at least one deficit of material for the airfoil relative to the specified nominal dimensions, the at least one section selected from the group consisting of the leading edge section and the trailing edge section; providing at least one insert comprising a second material, the second material having a creep life that is at least substantially equal to the creep life of the first material, and a fatigue life that is at least substantially equal to the fatigue life of the first material; and disposing the at least o

Abstract: A gas turbine engine blade includes pressure and suction sides extending between leading and trailing edges and root to tip. The pressure side includes a tip rib recessed therein to define a tip shelf terminating in an inclined ramp. The ramp may be aligned with streamlines of combustion gas flow for preventing interruption thereof and the increase of heat transfer therefrom.

Abstract: There is provided a turbine airfoil having a plurality of pressure side bleed slots through which cooling air is discharged. A portion of the slot openings are covered with an outer wall which comprises a high temperature foil.

Abstract: A grit blasting and alkaline etch surface pretreatment that is applied to a metallic airfoil. The metallic airfoil includes pockets or cavities that have been fabricated into the airfoil to reduce the weight of the airfoil. The pretreatment includes grit blasting the surface of the pockets or cavities, followed by washing the airfoil and treating the airfoil in an alkaline etch bath. After any remaining solution from the bath is neutralized and within twenty-four hours of the end of the pretreatment, primer is applied to the surface of the pockets or cavities. After the primer is applied to the surface of the pockets, a lightweight resin is injected into the pockets and bonds to the primer forming a mechanical bond with good fracture toughness at elevated temperatures.

Abstract: A gas turbine engine blade includes pressure and suction sides extending between leading and trailing edges and root to tip. The pressure side includes a tip rib recessed therein to define a tip shelf terminating in an inclined ramp. The ramp may be aligned with streamlines of combustion gas flow for preventing interruption thereof and the increase of heat transfer therefrom.

Abstract: A gas turbine blade (1) with a tip squealer (7) comprises cooling passages (12, 13) that provide cooling fluid for the cooling of the tip squealer (7). A first portion of the cooling passages (12) extends from an internal hollow space (11) through an end cap to a tip pocket. A second portion (13) of the cooling passage extends from the end cap in part through the rails (8) of the tip squealer (7) to the tip crown (9). The second portion (13) is partially bounded by the rail (8) and partially open to the tip pocket (14). The cooling passages according to the invention provide an improved cooling of the tip squealer and have the advantage that cooling fluid can cool the tip squealer (7) even in the event of clogging of the second portions (13) of the passages.

Abstract: An airfoil (1) for a gas turbine comprises a pressure sidewall (2) and a suction sidewall (3), a tip cap (4), and a tip squealer (6). Cooling fluid flows from a hollow space (5) within the airfoil (1) through exit passages (14, 16) extending to the pressure side of the airfoil (1) and to the tip cavity (9) defined by the tip cap (4) and the tip squealer (6). According to the invention, the tip squealer (6) comprises a smooth contour with curved and straight portions (10, 11, 12, 13) allowing an even flow of the cooling fluid (21) about the tip squealer (6) and within the tip cavity (9). Furthermore, the exit passages (14, 16) are partially diffused and oriented at angles with respect to the radial direction. The smooth contour and shape of the exit passages avoids the formation of vortices and enhances film cooling of the tip squealer (6).

Abstract: A blade (1) for a gas turbine comprises a tip cap (4) and a tip squealer (6) and passages (15, 25) for cooling fluid extending from a hollow space (5) to the tip squealer (6). According to the invention the tip squealer (6) comprises a cavity (16) extending from the tip pocket (9) into the tip squealer (6) such that the cooling passage is divided into first and second portions (17, 18) with an exit hole (11′) in the cavity (16) and an exit hole (11) on the tip crown (8) respectively. In case of a blockage of the exit hole (11) on the tip crown (8) cooling fluid can flow through the additional exit hole (11′) into the tip pocket (9) and cool the squealer (6).

Abstract: An airfoil for a gas turbine engine, the airfoil having a core body with an airfoil body, an integral partial height squealer tip defining a tip shelf, and an integral tip cap between the airfoil body and the integral partial height squealer tip; and a squealer tip extension bonded to the partial height squealer tip. A method for manufacture and repair of an airfoil.

Abstract: A turbine blade having a pre-segmented squealer tip is provided. The segment or slots in the squealer tip are located in regions of maximum stress, and reduce cracking of the squealer tip and propagation of cracks into the airfoil. The slots are preferably filled with a corrosion resistant material which is more ductile than the base alloy.