Abstract: A wind power generator is provided in which a reduction in weight is achieved by reducing the wall thickness of a nacelle, and an increase in the amount of heat input to the interior of the nacelle from sunlight is suppressed. In a wind power generator in which driving/power-generating mechanisms linked to a rotor head to which wind-turbine blades are attached are accommodated and installed inside a nacelle, a coating of high-reflectivity paint is formed on at least part of the outer wall that receives sunlight.

Abstract: The invention is a class of nickel-base alloys for gas turbine applications, comprising, by weight, about 13.7 to about 14.3 percent chromium, about 5.0 to about 10.0 percent cobalt, about 3.5 to about 5.2 percent tungsten, about 2.8 to about 5.2 percent titanium, about 2.8 to about 4.6 percent aluminum, about 0.0 to about 3.5 percent tantalum, about 1.0 to about 1.7 percent molybdenum, about 0.08 to about 0.13 percent carbon, about 0.005 to about 0.02 percent boron, about 0.0 to about 1.5 percent niobium, about 0.0 to about 2.5 percent hafnium, about 0.0 to about 0.04 percent zirconium, and the balance substantially nickel. The nickel-base alloys may be provided in the form of useful articles of manufacture, and which possess a unique combination of mechanical properties, microstructural stability, resistance to localized pitting and hot corrosion in high temperature corrosive environments, and high yields during the initial forming process as well as post-forming manufacturing and repair processes.

Abstract: An example composite fan case assembly includes a composite fan case body disposed on an axis. The fan case body has a radially inner surface and a radially outer surface. There is at least one mounting attachment to receive a threaded member. The at least one mounting attachment includes a base component and a spool component. The base component extends through an opening in the fan case body from the radially outer surface and toward the radially inner surface of the fan case body. The base component including a base portion, a boss having a non-cylindrical profile, and a cylindrical portion. The mounting attachment also includes a spool component disposed on the radially outer surface and attached to the base component. The spool component receives at least a portion of the base component. An outer surface of the cylindrical portion and an inner surface of the spool component are threaded and correspondingly mate to lock the spool component relative to the base component.

Abstract: The invention relates to a guide-vane arrangement (1) for deviating the flow present in the by-pass flow channel (2) of an engine (3), said arrangement comprising an outer ring (4) and an inner ring (5) and guide vanes (6) arranged therebetween in a substantially radial manner, wherein the outer ring (4) has elements (7) for connecting to an outer engine structure (8), and the inner ring (5) has elements (9) for connecting to an inner engine structure (10), with a plurality of segments (11) being provided.

Abstract: A compressor housing (16) of a radial compressor at least two housing portions (10, 12, 14) at least partially of plastic material and defines compressor impeller installation space (48) and a spiral duct (46) that surrounds it radially on the outside with regard to a rotational axis (18) of an impeller. A securement structure (50) encloses the compressor impeller installation space (48) at least partially in an annular manner and is arranged in radial direction between the impeller installation space (48) and the spiral duct (46). The securement structure includes a separate burst-protection ring (50) with a tubular wall section (34) enclosing the impeller installation space (48) circumferentially.

Abstract: Composite material turbine nozzle blade including an airfoil (10) adapted to have a cooling fluid flow through it and extending between a shroud (11) and a root (12), said shroud being shaped to be attached to one or more turbine casings (6, 7) of a turbomachine and said root being shaped to provide a junction with a turbine internal casing (5), wherein its root (12) is produced with a loosened texture and includes an external upstream side loosened texture lug (122) and an external downstream side loosened texture lug (124), the ends of the two external side lugs extending axially relative to the rotation axis of the turbomachine to form means for supporting and centering said internal casing.

Abstract: In a method for producing an inlet coating (21) on a surface of a turbomachine (10), an electric arc (37) is produced between a first electrode (31) having a first material and a second electrode (32) having a second material. A gas stream (42) is produced through the electric arc (37) onto the surface, which entrains the first material and the second material from the electric arc (37) and deposits them on the surface to form the inlet coating (21) or a precursor layer (22) of the inlet coating (21).

Abstract: The invention relates to a fan comprising a housing and a fan wheel arranged on a motor shaft and being drivable by a motor. According to the invention, the fan is designed as a mixing fan for transporting and mixing a combustible medium with air, wherein at least the fan wheel is designed in an insulating manner.

Abstract: Provided is a compressor that is capable of, with a simple configuration, facilitating the insertion operation of a compressor bundle by reliably preventing tilting thereof during insertion into a chamber; and that also makes it possible to reduce a roller size without increasing the contact pressure of rollers for sliding the compressor bundle. A small tilt sensor that detects a relative angle difference ? of the compressor bundle with respect to the bundle casing is provided at at least one location in the compressor bundle to be inserted into the chamber inside the bundle casing. In addition, the weight of the compressor bundle during the insertion into the chamber is supported by rollers provided at a bottom portion near the front end of the compressor bundle by making the rollers come in contact with an inner circumferential wall surface of the chamber.

Abstract: Various turbine component preforms are disclosed having near-net shape features. In one embodiment, a turbine casing preform is disclosed. The turbine casing preform includes an as-cast body comprising a partially cylindrical wall section of a turbine casing, the wall section having an inner surface and an outer surface. The turbine casing preform also includes a circumferentially-extending vane slot formed in the wall section on the inner surface. In another embodiment, a turbine nozzle diaphragm preform is disclosed. The turbine nozzle diaphragm preform includes an as-cast body comprising a partially-cylindrical wall section of a turbine nozzle diaphragm having an inner surface and an outer surface. The turbine nozzle diaphragm preform also includes an as-cast, circumferentially-extending seal member projecting from one of the outer surface or inner surface.

Abstract: In one embodiment, the invention provides an air movement device having a matrix polymer and nanoparticles. In another embodiment, the invention provides a method of manufacturing an air movement device having dry-mixing about 30% to about 80% by weight matrix polymer and about 2% to about 15% by weight layered clay to form a dry mixture, extruding the mixture to form a polymer nanocomposite, and molding the polymer nanocomposite into an air movement device. In yet another embodiment, the invention provides an air movement device having about 30% to about 80% by weight polypropylene, about 3% to about 10% by weight layered clay, and about 1% to about 10% by weight maleic anhydride grafted polystyrene, wherein the air movement device has a UL 94 5VA flame retardant rating.

Abstract: The present application provides a component for use in streams of hot gas, which comprises a first region of fiber-ceramic material, a second region of fiber-ceramic material and a middle layer of fiber-ceramic material which is arranged between the first region and the second region, wherein the fiber-ceramic material of the middle layer has a lower ceramic content than the fiber-ceramic material of the first region and the second region, and wherein at least one acute-angled in-flow edge and/or away-flow edge of the component is formed on the middle layer.

Abstract: A ventilation fan arranged to reduce vibrations includes an impeller rotating around a center axis, a motor portion arranged to rotate the impeller, a motor supporting portion arranged to support the motor portion, and a housing arranged to accommodate the impeller and the motor portion. The motor supporting portion includes a substantially disk-shaped base portion, and a substantially cylindrical bearing holding portion axially extending with the center axis as the center. At least the base portion is made from resin. On the surface of the base portion, a plurality of recessed portions which are axially recessed are arranged in the form of a net, a staggered pitch, a grid, or a honeycomb. A flat portion of the base portion excluding the recessed portions does not have a continuous region extending in a straight line radially from the center of the base portion.

Abstract: In one embodiment a transition section for a turbine engine is provided that includes one or more components constructed of a ceramic matrix composite. The transition section may fluidly connect a high-pressure turbine and a low-pressure turbine within the gas turbine engine. The transition section may include a transition duct and a variable area turbine nozzle. One or both of the transition duct and the variable area turbine nozzle may be constructed of the ceramic matrix composite.

Abstract: The invention relates to a housing for covering the ends of a row of rotor blades of an axial turbomachine compressor, the housing being provided with a sealing device between the blade tips and the housing. It comprises a shell segmented along its circumference, each segment being fixed to the housing by a series of elastomeric elements in a recess in the shape of a channel cut into the inner surface of the housing. In this way, in the event of misalignment of the rotor relative to the stator, the rotor blades coming into contact with sections of the shell will be able to move to compensate for this misalignment while reducing the frictional forces generated by contact between the blades and the shell. In the event of alignment being re-established the segments of the shell will be able to resume their initial position because of the elastic behaviour of the elements.

Abstract: A pump used in a gasification system, the pump comprises a housing having an inlet and an outlet, a rotor supported within the housing for rotation relative to the housing, the rotor comprising a hub, a plurality of disks spaced apart by sections of the hub, and defining a plurality of transport channels for transporting solid carbonaceous feedstocks for the gasification system, and an interior feedstock facing surface adjacent to the solid carbonaceous feedstocks, wherein at least a portion of the interior feedstock facing surface is coated with a coating.

Abstract: The present invention provides a compressor housing capable of reducing the weight of a compressor without leading to an increase in the size and a reduction in the efficiency of the compressor. The compressor housing includes: an inner cylinder made of a plastic material and extending in an axial direction and in a circumferential direction to surround blade tips of the blades; and an outer cylinder made of a plastic material and extending in the axial direction and in the circumferential direction to surround the inner cylinder. The inner cylinder and the outer cylinder are bonded or jointed at the first end, opposite the second end where the volute is formed.

Abstract: A segmented component for use with a gas turbine engine comprises a radially extending gas path portion. The gas path portion is for interacting with gas flow from the gas turbine engine. The component is divided into axially aligned segments comprising a forward segment, an aft segment, and a plurality of middle segments disposed between the forward segment and the aft segment. The middle segments comprise radially elongate ceramic matrix composite material plates. In one embodiment, the gas path portion comprises an airfoil for a turbine blade. In another embodiment, the gas path portion comprises a removable platform for a turbine blade. In another embodiment, the gas path portion comprises an airfoil for a turbine vane.

Abstract: A working member for a power plant is disclosed herein. The working member includes a body defining at least one working surface of the working member. The at least one working surface is operable to contact a working fluid. The body also includes at least one inner surface opposite the at least one working surface. The working member also includes an interior chamber defined within at least part of the body proximate to the at least one working surface. The working member also includes at least one inlet to the interior chamber. The working member also includes at least one outlet from the interior chamber. The working member also includes a quantity of open-cell foam positioned in the interior chamber between the inlet and the outlet. The quantity of open-cell foam fills less than all of the interior chamber such that at least one empty space is defined in the interior chamber between the at least one inner surface and the quantity of open-cell foam.

Abstract: Methodology and tooling arrangements for increasing interlaminar shear strength in a ceramic matrix composite (CMC) structure are provided. The CMC structure may be formed by a plurality of layers of ceramic fibers disposed between a top surface and a bottom surface of the composite structure. A plurality of surface recesses are formed on the surfaces of the structure. For example, each of the surfaces of the composite structure may be urged against corresponding top and bottom surfaces of a tool having a plurality of asperities. The plurality of surface recesses causes an out-of-plane sub-surface fiber displacement along an entire thickness of the structure, and the sub-surface fiber displacement is arranged to increase an interlaminar shear strength of the structure.

Abstract: A turbomolecular pump includes: a rotor (4) on which rotary vanes (19) in multiple stages are formed; fixed vanes (21) in multiple stages; and a pump casing (7) in which a pump inlet opening (7a) is defined, and that houses the rotor (4) and the fixed vanes (21) in multiple stages; wherein: a surface of the rotor (4) facing the inlet opening has a first emissivity; a surface of one vane stage that is visible from the inlet opening, among a plurality of vane stages including the rotary vanes (19) and the fixed vanes (21), has the first emissivity; and a surface of one vane stage, among the plurality of vane stages, that is not visible from the inlet opening has a second emissivity that is greater than the first emissivity.

Abstract: A single-piece compressor nozzle stage for a turbine engine, the stage comprising two coaxial rings, connected together by radial vanes, the inner ring including an annular cavity for housing damper means for damping vibration by friction, which damper means are secured to an annular abradable-material support.

Abstract: A fan unit has a fan (10). Associated with the fan is an air-guiding tube (22) through which the fan (10) transports air, during operation. The air-guiding tube (22) is connected to at least one carrier tube (23) for suspension of the fan (10). The fan includes a carrier part (25). A damping member (30) is arranged between the carrier part (25) and the carrier tube (23) to reduce any structure-borne sound which occurs during operation of the fan (10).

Abstract: The invention relates to the use of a thermal insulating layer for a housing of a steam turbine in order to even out the deformation behavior of different components based on different heatings of the components.

Abstract: An example turbomachine shroud assembly includes an annular shroud configured to receive a rotating component. A radially outer surface of the annular shroud establishes positioning slots and relief slots. The positioning slots are configured to receive a support finger that limits radial movement of the annular shroud. The relief slots are different than the positioning slots.

Abstract: This hydraulic machine member has at least one flow of water passing through it, and comprises at least one wetted surface extending between two edges of the member, at least one of the edges of the member and part of the adjacent wetted surface being reinforced and formed by at least one removable solid element made from material having a high resistance to abrasion.

Abstract: A process for joining silicon-containing ceramic articles, and particularly ceramic articles and CMC articles that contain both silicon carbide and free silicon. The process entails providing a reactive metal-containing braze material between the articles, and then heating the braze material and the articles to react the reactive metal with the silicon within the articles to form a brazement containing a silicide phase of the reactive metal. The brazement and articles are then cooled to produce a component comprising the two articles and the silicide phase-containing brazement. The process is preferably carried out at temperatures below that which would thermally degrade constituents of the articles, and more preferably below the melting point of silicon.

Abstract: The invention relates to the use of a thermal insulating layer for a housing of a steam turbine in order to even out the deformation behavior of different components based on different heatings of the components.

Abstract: A vane has an airfoil shell and a spar within the shell. The vane has an outboard shroud at an outboard end of the shell and an inboard platform at an inboard end of the shell. The shell includes a region having a coefficient of thermal expansion (CTE) varying with depth.

Abstract: A composite nozzle segment includes one or more airfoils extending radially between arcuate radially outer and inner band segments having band plies curved about a centerline axis, an outer chordal seal line on an outer aft flange of the outer band segment, and thickened areas in corners of the outer aft flange along pressure and suction side edges of the outer band segment. The thickened areas may be thickest at the pressure and suction side edges and thinnest near a middle of the outer band segment. The thickened areas taper off from an aft end of the thickened area towards a forward flange of the outer band segment. Insert plies may be disposed between some of the band plies within the thickened areas may be grouped together in a discrete group or be interspersed with some of the band plies. The insert plies may have triangular shapes.

Abstract: In a turbocharger equipped with a nozzle vane for changing the speed of exhaust gas running through a turbine in accordance with the speed of engine revolution, the member to constitute the nozzle vane and to constitute an exhaust guide for guiding exhaust gas to the turbine is characterized in that the exhaust guide member of a nozzle vane-type turbocharge is formed of an austenite stainless steel containing, in terms of % by mass, at most 0.08% of C, from 2.0 to 4.0% of Si, at most 2.0% of Mn, from 8.0 to 16.0% of Ni, from 18.0 to 20.0% of Cr and at most 0.04% of N and containing these ingredients in such a manner that they satisfy a DE value of the specified formula to be from 5.0 to 12.0, with a balance of Fe and inevitable impurities.

Abstract: An inlet case for a small gas turbine engine, where the inlet case is formed as a hybrid piece with a metallic inner shroud cylinder and plastic guide vanes and plastic outer shroud molded around the metallic inner shroud cylinder. The metallic inner shroud cylinder carries an electric generator and provides for a good convective heat transfer surface to carry heat away from the electric generator and into the inlet air flow entering the engine. The plastic guide vanes and outer shroud allow for a light weight inlet case assembly that is also much easier to form the airfoil shapes than a machined metallic inlet case. The plastic guide vanes and outer shroud are injection molded around the metallic inner shroud cylinder to produce a rigid single inlet case. The metallic cylinder includes axial extending slots that receive the lower ends of the guide vanes during the injection molding process.

Abstract: A vane has an airfoil shell and a spar within the shell. The vane has an outboard shroud at an outboard end of the shell and an inboard platform at an inboard end of the shell. The shell includes a region having a depth-wise coefficient of thermal expansion and a second coefficient of thermal expansion transverse thereto, the depth-wise coefficient of thermal expansion being greater than the second coefficient of thermal expansion.

Abstract: A method of weld repairing an air-cooled aft frame of a transition piece of a gas turbine engine. The transition piece has an interior surface coated with a ceramic coating. The aft frame has a surface with cooling holes therein and from which cracks have propagated. The method includes removing the transition piece from the engine and, without removing the ceramic coating or the aft frame from the transition piece, weld repairing the cracks by performing a laser beam welding technique that deposits a filler material on the surface but does not close the cooling holes in the surface. The surface of the aft frame can be machined to remove excess filler material prior to re-installing the transition piece in a gas turbine engine.

Abstract: A centrifugal compressor is equipped with a resin housing, that is made in a manner such that compression efficiency is not lost and merits such as weight and cost reduction are not cancelled out. The turbo charger housing comprises a volute section, a channel formation section, and an impeller that is fixed in the center of the channel formation section to a rotating shaft. An annular shroud is disposed in a recess formed on the inner wall of the channel formation section. The annular shroud forms the outer walls of a channel and a diffuser for compressed gas. The edge of the annular shroud spaced from a partition wall, which forms a portion of a bearing housing. If the resin housing undergoes thermal deformation, the dimensions of a gap between the annular shroud and the curved profile of a blade is maintained.

Abstract: A fan case for a gas turbine engine includes a composite fan containment case having an outer surface, a front and a rear. An attachment flange and a mounting ring are respectively provided on the front and the rear. A bolt attachment is supported on the outer surface. The composite fan containment case has a containment area that is configured to be axially aligned with a fan blade. A ballistic liner is arranged in the containment area.

Abstract: A turbocharger includes a center housing having a bearing surface configured to contact an inner surface of a unison ring. A conversion coating is impregnated onto at least the bearing surface of the center housing.

Abstract: A fan frame structure includes a plastic casing and a metal fixing frame. The plastic casing and the metal fixing frame are provided for an axial flow fan or a blower fan. The plastic casing includes a bottom having a plurality of first fixing portions. The metal fixing frame includes a base with a shaft tube seat in a center thereof. The base includes a plurality of second portions each engaged with one of the first fixing portions. Since the plastic casing is made of inexpensive plastic material, the manufacturing costs are cut. The metal fixing frame provides sufficient structural strength and desired heat dissipating effect.

Abstract: A method of repairing a case for a gas turbine engine includes identifying areas of damage on its internal holding structures in a gas turbine case, and utilizing cold metal transfer to deposit weld material to the internal holding structures.

Abstract: A rotordynamic pump for delivering continuous flow of fluids, such as blood, is provided. In one embodiment, the pump includes a stator housing having an inlet and an outlet. A rotor hub is disposed within the stator housing having a first, mixed-stage impeller and a second, axial-flow stage impellers. One or more stator vanes and extend radially inwardly from the stator housing. In one particular embodiment, the second stage impeller is disposed nearer to the outlet than to the inlet. The stator vanes may include a first set of stator vanes disposed between the first and second stage impellers, and a second set of stator vanes positioned between the second stage impellers and the outlet.

Abstract: A vane assembly for a gas turbine engine where each vane is connected to at least one adjacent portion of at least one of the inner and the outer shrouds through a melt-weld connection. The melt-weld connection includes non-metallic heat-meltable material with a metal wire mesh layer trapped therein, the metal wire mesh being heatable to melt the heat-meltable material for formation and breakdown of the melt-weld connection.

Abstract: An assembly is disclosed for forming a fluid-tight seal between a pump housing and a seal plate. The housing includes a first flange with a first plurality of apertures formed therein, and the seal plate includes a second flange with a second plurality of apertures formed therein. A gasket is provided between the pump housing and the seal plate. A plurality of inserts extend through the first plurality of apertures, and a plurality of spacers extend through the second plurality of apertures. A plurality of threaded connectors are used to couple the seal plate to the pump housing to form a fluid-tight seal. The dimensions of the inserts and spacers are selected so as to inhibit crushing of the gasket and the flanges when the connectors are fully tightened.

Abstract: An assembly between a metal piece and a ceramic material piece made of SiC and/or C based ceramic material. The assembly includes a stack structure including the following elements assembled together in pairs in this order, by brazing: the metal piece; a first intermediate piece; a second intermediate piece; and the ceramic material piece. The second intermediate piece is made of another ceramic material, that is chemically less reactive relative to metals than are SiC or C, and that presents a coefficient of expansion smaller than that of the material constituting the metal piece. The first intermediate piece is made of metal and can deform to compensate for expansion difference between the metal piece and the second intermediate piece. The assembly can be used in a turbomachine.

Abstract: In one aspect, a method for assembling an outlet guide vane is provided. The method includes providing an outlet guide vane frame having a first side and a second side. The outlet guide vane includes a radially inward flange coupled to a radially outward flange by a leading edge. A trailing edge is coupled to the radially inward flange and the radially outward flange aft of the leading edge. A cavity is defined between the radially inward flange, the radially outward flange, the leading edge, and the trailing edge. A first and a second mating surface circumscribe the cavity on the first and second sides respectively. The method further includes coupling a filler portion within the cavity wherein the filler portion includes a third side and a fourth side, coupling a first skin to the third side and the first mating surface, and coupling a second skin to the fourth side and the second mating surface, wherein at least one of the first skin and the second skin are fabricated from a composite material.

Abstract: An inlet duct, an induction system, and a system are disclosed for directing an inlet flow into an inlet compressor for use in an internal combustion engine. An example inlet duct may include one or more relief features disposed on an inner surface of the inlet duct. The one or more relief features may be made integral with the inlet duct. The one or more relief features may be disposed to protrude into the inlet flow to cause the inlet flow to swirl before reaching the inlet compressor.

Abstract: A turbine vane of a gas turbine, especially a gas turbine aircraft engine, is disclosed. The turbine vane includes a vane base body with an outer surface forming a suction side and a pressure side, the outer surface of the vane base body being at least partially coated with a thermal barrier coating. The thermal barrier coating extends continuously or uninterruptedly at least largely over the suction side and largely over the pressure side of the surface of the vane base body, with the layer thickness of the thermal barrier coating being variable or adjustable.

Abstract: A thermal protection coating, in particular for a turbine-engine part (12), the coating being deposited by thermal spraying onto the surface of the part (12) and including at least 80% by volume of hollow ceramic microbeads distributed in a metal alloy based on nickel or cobalt, it being possible for the coating to be deposited on a bonding layer (22) of metal alloy and for it to be covered in a layer (26) providing protection against erosion or against friction wear, or in a reflective layer that reflects thermal radiation.

Abstract: The invention relates to a housing (1) of a radial flow compressor, comprising an intake pipe (4), a compressor duct (7) and an outlet pipe (5), wherein the housing comprises a housing body (basic construction) comprising at least an upper housing member (3) and a lower housing member (2) made of a fibre-reinforced thermoplastic polymer composition, and wherein the members (2, 3) are made, assembled together and fixed to each other in an integrated 2-step injection molding process.

Abstract: An aeroengine fan casing is made of composite material comprising fiber reinforcement densified by a matrix. The casing (10) is secured to at least one ring (24) or ring sector that is situated on the inside face of the casing and that is mechanically connected to an equipment fastener part (26) that is situated on the outside face of the casing, in particular for fastening an accessory gearbox.

Abstract: A turbine nozzle element including an inner annular platform sector, an outer annular platform sector, and at least one vane extending between the platform sectors and connected to both of them. The nozzle element includes a single piece of composite material including fiber reinforcement densified by a matrix that is at least partially ceramic, and the fiber reinforcement includes a fiber structure that is woven by three-dimensional or multi-layer weaving, and that presents continuity throughout the volume of the nozzle element and throughout the periphery of the vane.