Abstract: A diffuser pipe for a gas turbine engine comprises a hollow pipe body including a first end, a second end fluidly connected to the first end, and at least one flattened area proximate to the second end. A ring is connected to the second end. The ring is an outlet of the diffuser pipe. At least one stiffener is disposed on the at least one flattened area. The ring and the at least one stiffener reduce vibratory stresses at the second end of the pipe body. A method of manufacturing a diffuser pipe of a gas turbine engine is also presented.

Abstract: A water paddle comprising a first shaft having and a second shaft, a first cog collar located on an exterior surface of first shaft and having a first set of teeth extending radially from a mating end of first cog collar, a second cog collar located on an exterior surface of second shaft and having a second set of teeth extending radially from a mating end of second cog collar, second set of teeth mateable with first set of teeth to prevent rotational movement between shafts, a ferrule extending from a free end of second shaft, a snap button-alignment tab assembly comprising a bushing, a wavy washer, and a snap button base located within ferrule and a snap button skirt connected to free end of ferrule and an alignment tab fixed within first paddle shaft downstream of a set of corresponding holes of first paddle.

Abstract: A turbine engine includes a housing supporting compressor, turbine sections, and an epicyclic gear train including a carrier. Sun gear and intermediate gears are arranged about and intermeshing with the sun gear. The intermediate gears are supported by the carrier. A baffle includes a lubrication passage near at least one of the sun gear and intermediate gears for directing a lubrication on the at least one of the sun gear and intermediate gears.

Abstract: A method for repairing a degraded bolt hole in a casing flange by reaming and removing at least some corrosion on an inside and around the hole to form a reamed hole, mounting the flange to float relative to upper and lower electrodes of a welding machine, radially and axially clamping an area of the flange surrounding the reamed hole, placing upper and lower filler slugs in the reamed hole, placing the electrodes against upper and lower filler slugs and applying a welding current through the electrodes while applying pressure to the filler slugs with the electrodes and resistively heating and melting the filler slugs to form a weldment, and pulsing the welding current on and off. Pulsing may be performed with progressively increasing amounts of current. In situ tempering under the pressure of the electrodes may be performed on a substantially liquid pool formed by the welding current.

Abstract: A method of repairing a seal wire groove is disclosed, the groove forming an annular structure having an outer surface and an inner surface and defining an original profile when new, comprising the steps of: removing a less-than-annular portion of the original profile of the groove to remove damaged portions of at least one of the inner and outer surfaces thereby forming a void; adding new material to the void; and shaping the new material to form a new profile of the groove.

Abstract: A combustor assembly includes a hot skin of a combustion chamber wall having an inner face exposed to the combustion chamber and an opposite outer face, a receiving skin having a securing portion affixed to the hot skin outer face in an air-tight manner and a receiving flange, extending from the securing portion, that is offset from the hot skin outer face to form a female recess, a cold skin having a cold wall portion spaced from the hot skin and forming a cooling cavity therebetween, a securing portion extending from a first end of the cold wall portion affixed to the hot skin outer face in an air-tight manner and a male flange extending from a second end of the cold wall portion opposite the first end, the male flange snugly received in the female recess and forming a sliding engagement therebetween.

Abstract: A method of using machining to repair a component workpiece, such as a turbomachine blade, from a known profile of the component, is disclosed. The method includes deforming the profile using a morphing method so that the deformed profile interpolates a cluster of points measured on the component. Deforming the profile involves comparing each zone of the component workpiece that has excess or insufficient thickness with elementary deformation configurations (EDCs) each in the form of a mesh portion and of points, the elementary deformation configurations (EDCs) being filed in a database, the database associating the parameters of the morphing function with each elementary deformation configuration (EDC).

Abstract: In a manufacturing method of an impeller for a fluid transmitting device, multiple guide grooves aligned in a peripheral direction to allow communication between adjacent ones of multiple positioning holes are provided in a concave inner surface of a core in advance; and in a step of melting a brazing material and causing the molten brazing material to penetrate into gaps between coupling pieces and positioning holes that are fitted to each other and further into gaps between the core and the blades, the molten brazing material is guided to the positioning holes through the multiple guide grooves. Accordingly, the step allows the molten brazing material to be efficiently guided to the gaps between the coupling pieces and positioning holes, thereby improving the yield of the brazing material and preventing an influence of a residual brazing material over the rotational balance of the impeller.

Abstract: A turbine blade monitoring arrangement includes a bucket tip located at a radial outer location of a bucket. Also included is at least one component disposed radially outwardly of the bucket tip. Further included is a hollow portion of the at least one component, wherein the hollow portion extends radially from a first end to a second end through the at least one component. Yet further included is a first sealing component operatively coupled to the at least one component proximate the first end of the hollow portion, wherein the first sealing component comprises a translucent material. Also included is a proximity sensor disposed radially outwardly of the at least one component and aligned with the hollow portion, the proximity sensor configured to generate a first signal through the hollow portion to the bucket tip.

Abstract: A ram air fan inlet shroud for a ram air fan assembly is provided. The ram air fan inlet shroud includes a shroud portion extending outwardly from a conical portion. The conical portion provides a transition between a central portion and an inner ram air fan hub interface portion. The conical portion includes a plurality of inner cooling slots having a slot arc length and spaced apart by a slot spacing angle. A ratio of the slot spacing angle to the slot arc length is between about 1.24 and 1.4. The ram air fan inlet shroud also includes a recessed portion located between the inner ram air fan hub interface portion and an outer ram air fan hub interface portion. The recessed portion includes a plurality of outer cooling holes.

Abstract: One embodiment of the present invention is a unique vane system. Another embodiment is a unique gas turbine engine. Another embodiment is a unique method for manufacturing a bypass vane stage. Other embodiments include apparatuses, systems, devices, hardware, methods, and combinations for turbine engines and vane systems for turbine engines. Further embodiments, forms, features, aspects, benefits, and advantages of the present application will become apparent from the description and figures provided herewith.

Abstract: A process is provided for forming shaped air holes, such as for use in turbine blades. Aspects of the disclosure relate to forming shaped portions of air holes using a short pulse laser, forming a metered hole corresponding to each shaped portion, and separately finishing the shaped portion using a short-pulse laser. In other embodiments, the order of these operations may be varied, such as to form the shaped portions and to finish the shaped portions using the short-pulse laser prior to forming the corresponding metered holes.

Abstract: A rotor for a gas-turbine engine, is provided having a first and a second rotor disc that are suitable to be joined directly. The first and second rotor discs are symmetric with respect to an axis of rotation common to the two rotor discs. The first rotor disc provides an interrupted screw on one side. The second rotor disc provides an interrupted screw on another side. The interrupted screw of the second rotor disc reciprocates the interrupted screw of the first rotor disc.

Abstract: A torque converter having a housing with an impeller wall section, and pump vanes brazed to the impeller wall section. The housing is connected to an output of an engine for rotation about a longitudinal axis. A turbine having turbine vanes that are connected to a hub is located about the longitudinal axis within the housing and is connected to an input shaft of a transmission. A stator is located between the pump vanes and the turbine vanes. In order to allow for a thinner housing wall, particularly an area of the impeller wall section, an annular retainer plate is brazed to the impeller wall section about the longitudinal axis and forms a reinforcement. A rolling bearing is located between the retainer plate and the stator, and is used in supporting the housing. An assembly method is also provided.

Abstract: A contribution is made to the assembly of a wind turbine intended to comprise, in a final assembly condition, a tower (2) surmounted by a nacelle (4) cooperating with a rotor (5) receiving a plurality of blades (3a-3c). To this end, a temporary association is made between at least some blades from said plurality of blades and the tower, so that said blades extend substantially in the longitudinal direction of the tower.

Abstract: An apparatus comprising a hub configured to couple to a mast, a grip configured to couple to the hub and a rotor blade, a pitch actuator coupled to the grip and configured to change a pitch of the rotor blade relative to the mast, and a delta-3 restraint coupled to the pitch actuator, wherein the delta-3 restraint is fixed relative to the mast. An apparatus comprising a hub configured to couple to a mast, a grip configured to couple to the hub and a rotor blade, a pitch actuator coupled to the grip and configured to change a pitch of the rotor blade relative to the mast, and a delta-3 restraint coupled to the pitch actuator, wherein the delta-3 restraint is configured to control the pitch of the blade relative to the mast when the pitch actuator fails, and wherein the delta-3 restraint provides an instantaneous blade pitch-flap coupling response.

Abstract: An apparatus comprising a spinner fairing assembly comprising a spinner configured to be fixed relative to a gimbaled yoke coupled to a mast system, and a spinner base configured to be fixed relative to the mast system. A spinner fairing assembly comprising a spinner aligned along a first axis, and a spinner base aligned along a second axis and configured to interface with the spinner, wherein the spinner is configured to transition between a neutral position and a canted position with respect to the spinner base, wherein the first axis and the second axis are coincident in the neutral position, and wherein the first axis and the second axis are not coincident and meet at an origin within the spinner in the canted position.

Abstract: An apparatus comprising a rotor yoke comprising two longitudinal side portions interconnected by two outboard portions, wherein a center portion of each longitudinal side portion comprises a build-up of material that is configured to accommodate a yoke hub clamp. Included is an apparatus comprising a rotor yoke comprising two longitudinal side portions interconnected by two outboard portions, wherein no apertures pass through the two longitudinal side portions and the two outboard portions. Also included is a method of coupling aircraft blades comprising providing a rotor yoke comprising two longitudinal side portions interconnected by two outboard portions, wherein no apertures pass through the two longitudinal side portions and the two outboard portions.

Abstract: A flexible joint assembly for providing flexure to a rotor blade comprising an upper hub plate and a lower hub plate configured to secure a rotor blade yoke via a bolted joint located radially outward of a mast; and an upper flexure assembly connected to the upper hub plate and a lower flexure assembly connected to the lower hub plate, wherein the upper flexure assembly and lower flexure assembly are configured to promote flapping of the rotor blade yoke about a flapping hinge located radially outward of the bolted joint.

Abstract: A novel ceramic matrix composite is disclosed for forming components that are operable in high temperature environments such those in gas turbine engines and the like. The ceramic matrix composite can include at least one layer of non-crimped fibers positioned substantially parallel to one another. A relatively small diameter elastic fiber can be constructed to stitch the non-crimped fibers together and a ceramic matrix may be deposited around the at least one layer of non-crimped fibers.

Abstract: A particle capture unit adopted to be exposed to a space in which particles fly includes at least a first layer formed of a plurality of first fiber-like materials and a second layer formed of a plurality of second fiber-like materials. The first fiber-like materials are thinner than the second fiber-like materials and arrangement density of the first fiber-like materials in the first layer is higher than that of the second fiber-like materials in the second layer, the second layer is interposed between the first layer and the space, and the first and second layers are hardened and bonded together by sintering.

Abstract: A cooling jacket capable of improving production efficiency. The cooling jacket includes a tubular main body having a first end face and a second end face, and a groove unit defining a flow channel of a cooling medium successively disposed axially on an outer periphery of the main body. The cooling jacket includes no portion located radially outward from a bottom of the groove unit between a first end portion of the groove unit located on the axial rear side of the main body and the first end face of the main body.

Abstract: Fan assemblies, and in particular fan wheels and stator assemblies for fan assemblies, are disclosed. In one embodiment, the fan wheel includes a wheel back having an outer surface forming one of a curved dome-shape and a truncated cone-shape. The fan wheel may also include a plurality of fan blades radially spaced about and mounted to the outer surface of the wheel back. In one embodiment, each of the fan blades is formed from a segment of an airfoil-shaped aluminum extrusion defining at least one internal cavity. The fan blade first ends can be provided with a compound cut profile with at least one curved cut such that the first end of the blade is mounted flush to the wheel back outer surface. The stator assembly can also be provided with a plurality of stator blades formed from airfoil-shaped aluminum extrusion segments and provided with compound cut profiles.

Abstract: A floating wind turbine (1) for electric power production and a method for use of said wind turbine (1), is described, where the wind turbine (1) comprises a hull (2) attached to a supporting column (2?) for a wind turbine (3) which is arranged to be put into rotation by wind force acting on rotor blades (3?), the wind turbine (1) is connected to a buoyancy device (4) by means of a coupling device (5), the buoyancy device (4) is arranged encircling at least a portion of the hull (2), and the buoyancy device (4) is arranged to be able to support at least a portion of the mass of the wind turbine (1), the coupling device (5) is a rotary coupling arranged in such a way that the wind turbine (1) is arranged to be able to rotate an angle from an essentially vertical position towards a horizontal position, or the opposite, and the hull (2) is provided with an adjustable ballast means (9, 12) arranged to be able to balance the wind turbine (1) about the rotary coupling (5) in any position between said positions.

Abstract: A fast and effective method for cleaning and repairing the shell-spar glue voids of a wind turbine blade, comprising the steps of detecting voids, raising the turbine blade at an incline, drilling holes into top and bottom ends of the void, injecting cleaning solution into the holes, and allowing the cleaning solution to drain out of the bottom holes and drain holes at the tip. The void is then inspected for oil by FTIR spectroscopy. If oil is detected, additional cleaning steps are performed comprising injection of a second cleaning solution into at least two holes of the void followed by a rest period, washing the holes with water via a pressure washer, and drying with compressed air. The blade is then inspected for oil and moisture, and when clean, adhesive is applied to the void through the holes.

Abstract: There is provided a lifting unit for lifting a rotor of a wind power installation. The lifting unit has at least one first sling for looping around a region of a rotor blade on a rotor of the wind power installation, which region is near the rotor blade root, at least one transverse strut, at least one first and second strut or sling portion, and at least one first and second hinge unit. The at least one first and second struts or sling portions extend between the at least one first and second hinge units and the transverse strut. The lifting unit further has at least one second sling having first and second sling portions and a strut. The first ends of the first and second sling portions are fixed to the first and second hinge units. The second sling is adapted to be arranged around a rotor blade stub.

Abstract: An exemplary variable vane actuation system for a gas turbine engine includes a vane arm attachable to a vane stem and configured to rotate the vane stem about a radially extending axis. The vane arm includes a claw feature to be press-fit onto the vane stem.

Abstract: The present invention provides a method for manufacturing a closed impeller that has a simple configuration and enables fusion in a very accurate position. The method includes: forming a frustum-shaped front plate and a disk-shaped base plate formed therebelow, upper surfaces of a plurality of unit impeller blade plates made from a synthetic resin extending in radial directions which are formed as impeller blade tip surfaces, with sharp-pointed ridge-like protrusions having an acute upper end and a width less than a width of the impeller blade tip surface being integrally formed on the impeller blade tip surfaces. In the method, an inner surface of the front plate and the plurality of impeller blade tip surfaces are formed as parts of conical surfaces and formed so that the cone apex angles of the two conical surfaces are equal to each other.

Abstract: A turbine nozzle apparatus for a gas turbine engine includes: an annular inner band; an annular outer band circumscribing the inner band; a plurality of airfoil-shaped structural vanes extending between and interconnecting the inner band and the outer band; and a plurality of airfoil-shaped non-structural vanes extending between the inner band and the outer band, each non-structural vane having a root end received by the inner band and a tip end received by the outer band, such that each non-structural vane is free to move to a limited degree relative to the inner and outer bands.

Abstract: An airfoil member and platform assembly for a gas turbine engine is provided. The platform to which the airfoil member is anchored is made of a composite material and includes an endwall defining a contoured region for improved aerodynamics. The contoured region influences the flow of gases through the flow passages between the airfoil members, thereby reducing endwall losses due to horseshoe vortexing. The composite material may be woven ceramic matrix composite fibers infiltrated with a ceramic matrix material or woven organic matrix composite fibers infiltrated with an organic matrix material.

Abstract: A method and system for attaching a service device to a wind turbine of a wind power unit, using the wind turbine to rotate the service device into one or more service positions, and using the service device to perform servicing on the wind power unit. In some embodiments, a blade of the wind turbine is removed and the service device is mounted in its place. In other embodiments, the service device is mounted to a device mount approximately in a saddle region between adjacent blades. In one example, the service device is a crane. In another example, the service device is a stator module installation/removal tool.

Abstract: In accordance with an exemplary embodiment, a method for manufacturing a component using additive manufacturing techniques includes providing a 3D design model for the component, adding one or more crack resistant features to the 3D design model of the component to produce an enhanced design model, and manufacturing the component using an additive manufacturing technique in accordance with the enhanced design model. The one or more crack resistant features are provided to reduce or eliminate the incidence of cracking in the manufactured component.

Abstract: There is provided a through-hole manufacturing method for a cylindrical body wall that enables the operation of forming a through-hole without leaving a machining burr on the wall of a cylindrical member to be easily and reliably carried out without depending on experts.

Abstract: An impeller for a washing machine appliance is provided. The impeller includes a stamped plate that is rotatable about an axis of rotation. The stamped plate also defines an opening at the axis of rotation. A mounting insert is received within the opening of the stamped plate in order to fix the mounting insert to the stamped plate.

Abstract: A plate closes the main part of a vane in two parts. An internal cavity is closed by the plate. Around a bearing surface of the plate, a groove receives an elastic seal, and the outer edge of the plate extends over the groove to compress the seal and to establish excellent leak proofing. The position of the plate may be guaranteed by centring pins penetrating into holes adjacent to the seal and which it fills when the pins have been removed, which completes the closing of the cavity. The plate has application in particular to stationary gas guide vanes in turbine engines.

Abstract: A repair device and method for repairing a forward frame v-blade on an aircraft engine are described in which the repair device replaces a section of the forward frame v-blade. In one embodiment, the repair device includes a supplemental part, which is secured to the forward frame v-blade. The supplemental part includes a central web and a pair of legs with a leg thickness that is greater than the thickness of corresponding flanges on the forward frame v-blade. Fasteners such as rivets are used to couple the supplemental part to the forward frame v-blade.

Abstract: A wind turbine blade mounting system for use with variable-pitch wind turbine blades (100) having reduced diameter blade roots. For each wind turbine blade (100) to be installed on a nose cone structure (20) of a wind turbine nacelle, the mounting system incorporates a high capacity bearing assembly (106) configured with an outwardly-opening tapered inner sleeve (105) to engage a tapered shank section (104) of an associated wind turbine blade in a self-locking coupling, thereby facilitating assembly and disassembly of the wind turbine blades from a nose cone structure (20).

Abstract: In a method for producing a cellular wheel made of metal, the following steps are conducted consecutively: (a) providing a sheet metal strip (26) having a length (1) that corresponds at least to the length of a circumferential line of an intermediate sleeve and a width (b) that corresponds at least to the length of the cellular wheel; (b) placing disks (16) in predetermined locations in predetermined quantities on both sides of the sheet metal strip (26) perpendicular to the sheet metal surface and perpendicular to the longitudinal direction of the sheet metal strip (26) and connecting the disks (16) to the sheet metal strip (26) by welding or brazing; (c) bending the metal strip (26) equipped on both sides with the disks (16) and connecting the two ends of the sheet metal strip (26) by welding or brazing to form the intermediate sleeve; (d) placing a first tubular sleeve that is concentric to the intermediate sleeve as an outer sleeve, and a second tubular sleeve that is concentric to the intermediate sleeve

Abstract: A covering device for an integrally bladed rotor base body of a turbomachine for preventing or reducing a cooling air stream that flows from a high-pressure side to a low-pressure side through channels that are formed between adjacent rotor blades, a plurality of cover elements being provided that are individually insertable into the channels and have at least one peripheral sealing surface. Also an integrally bladed rotor base body having a covering device of this kind, a method for producing such an integrally bladed rotor base body, as well as a turbomachine having such an integrally bladed rotor base body.

Abstract: A gas turbine engine, a rotor assembly for a gas turbine engine, and a method for thermally insulating an impeller in a gas turbine engine are provided. In one embodiment, the gas turbine engine includes an impeller having a front face configured to modify a direction of air flow through the gas turbine engine. The impeller further includes backface to which a heat shield is mounted. A closed cavity is defined between the heat shield and the backface of the impeller, and is configured to insulate the backface of the impeller from a high temperature environment.

Abstract: A method for producing a run-in coating for a turbomachine for braking a rotor in the event of a shaft breakage, the run-in coating being formed as an integral, generative blade portion during a generative manufacture of a blade. A run-in system having an abradable ring that is configured circumferentially on a blade row and has a chamber-type material structure. A turbomachine having a run-in system of this kind, as well as a guide vane having such a run-in coating.

Abstract: A vane assembly includes first and second annular metal rings configured to accept a compressed gas flow therebetween. The first and second annular rings each include a cutout portion. The assembly further includes a ceramic matrix composite vane configured as an airfoil having a blunt rounded nose and a flattened and tapered tail. A first radial end of the vane is rigidly disposed on the first annular ring and a second radial end of the vane is slidably disposed within the cutout portion of the second annular ring such that the vane is encompassed by the first and second annular rings. The vane includes a hollow through opening portion extending radially therethrough. Still further, the assembly includes a metallic elongated member disposed within and extending through the hollow portion of vane and through the cutout portion of the first annular ring.

Abstract: An exemplary nozzle ring has two fastening rings and a plurality of guide vanes, wherein holes are provided in one of the fastening rings for accommodating pins of the guide vanes, and openings are provided in the other fastening ring for accommodating positioning aids on the guide vanes.

Abstract: A method of producing a turbine engine rotor includes: joining a first rotor disc (25H) and an intermediate member (26) together by electronic beam welding, the first rotor disc (25H) being formed of a precipitation hardened Ni-based superalloy, the intermediate member (26) being formed of a solid solution strengthened Ni-based superalloy; performing age-hardening treatment on the joined body at a first temperature which is a suitable temperature for age-hardening the precipitation hardened Ni-based superalloy; joining the intermediate member (26) and a second rotor disc (25L) together by electronic beam welding, the second rotor disc (25L) being formed of a steel; and performing annealing treatment on the joined body at a second temperature which is a suitable temperature for annealing the steel.

Abstract: A method for forming an inclined-blade blower wheel is provided by arranging a plurality of blades about respective circumferences of first and second end caps. The plurality of blades extend longitudinally between the first and second end caps and parallel to an axis defined by respective centers of the first and second end caps. The first end cap is rotated with respect to the second end cap a predetermined amount, therein skewing the plurality of blades at a desired longitudinal pitch between the first end cap and second end cap. The first end cap and second end cap are then rotated in unison while crimping the circumferences of the first end cap and second end cap, therein securing the plurality of blades to the first and second end caps and fixing the desired longitudinal pitch of the plurality of blades from the first end cap to the second end cap.

Abstract: A fan impeller balance calibrating method includes steps of: placing a fan impeller onto a balance measurement unit and activating the fan impeller to rotate; using a detector of the balance measurement unit to detect the amount of unbalance and phase of the fan impeller in rotation and generate a detection signal according to the amount of unbalance and phase of the fan impeller; and providing a counterweighing unit, which receives the detection signal to find at least one hole of the fan impeller according to the detection signal, which is to be counterweighed and counterweighs the hole with a counterweight. By means of the fan impeller balance calibrating method, the measurement and counterweighing of the fan impeller are automated. Therefore, the working time is shortened and the manufacturing cost is lowered.

Abstract: A rotor assembly is provided that includes a hub rotatable about an axis of rotation. The assembly also includes a plurality of rotor blades spaced circumferentially about the hub. Each of said rotor blades extends from a blade root to a blade tip such that said plurality of blades are rotatable through a plane of rotation extending about said axis of rotation, said plane of rotation is defined as substantially perpendicular to said axis of rotation, wherein each of said blade roots is coupled to said hub, wherein each of said blade tips is offset a distance upstream from said plane of rotation.

Abstract: A gas turbine having a system of stages including at least one stage having first and second airfoils arranged alternately in the circumferential direction. The first airfoils each have a first array of cavities and the second airfoils each have a second array of cavities different from the first array of cavities.

Abstract: A method of working a gas turbine engine component, for example, a turbine airfoil platform having a heat crack, is disclosed. The presented method may allow turbine airfoils to be repaired, modified, manufactured or otherwise worked and subsequently assembled into a turbine section of a gas turbine engine. This method may help to reduce the costs of operating a gas turbine engine by allowing damaged turbine airfoils to be repaired rather than discarded.

Abstract: A method is provided for machining a slot having a slot base in a turbine engine rotor disk. The method includes forming a preform slot that extends along a longitudinal axis through the rotor disk. The preform slot includes a preform slot endwall connected laterally between a first slot sidewall and a second slot sidewall. A cutting tool is rotated about its axial centerline, which is substantially parallel to the longitudinal axis. The preform slot endwall is machined with the rotating cutting tool to form the slot base.