Abstract: The present invention relates to an annular case (20) of a multi-flow turbojet engine comprising a first element (22) forming a hub, a second element (24) forming a cylindrical casing, radially on the outside of and concentric with the first element, radial arms (23) connecting the first element (22) to the second element (24), at least part of said arms being structural and having an aerodynamic flow straightener vane profile, characterized in that it comprises a first ring sector (20C) of the case and a second ring sector (20T), the first ring sector being made of composite material and the second ring sector of metal, said radial arms (23T) of the second ring sector (20T) being structural.

Abstract: A turbofan engine comprising an annular inner wall surrounding tips of the fan blades, a layer of insulating material surrounding the inner wall, and an outer casing including an annular outer wall surrounding the insulating material and concentric to the inner wall and at least two annular rub elements extending radially inwardly from the outer wall through only part of a radial thickness of the layer of insulating material, at least two of the rub elements being in axial alignment with the blade tips at every point around a circumference of the fan, each rub element having a radially inner end spaced apart from the inner wall and made of a material harder than that of the blades, and a containment fabric layer wrapped around a support structure of the outer wall.

Abstract: A stator vane assembly includes a vane having an inner end. In one example, the vane is aluminum. An inner shroud has an aperture receiving the inner end. A flexible material secures the inner end to the inner shroud. The material has an inner surface opposite the vane providing a seal land in one example. The inner shroud provides an arcuate inner shroud segment, which is constructed either cast aluminum or stamped sheet steel. An inner shroud segment has an arcuate wall providing multiple apertures, for example. First and second flanges are integral with and extending radially inwardly from a concave side of the wall.

Abstract: A rotor, a steam turbine having a rotor, and a method of producing a rotor are disclosed. The rotor disclosed includes a shaft high pressure section. The high pressure section includes a first high pressure section, a second high pressure section, the second high pressure section being joined to the first pressure section, and a third high pressure section, the third high pressure section being joined to the second high pressure section. At least a portion of the second high pressure section is formed of a high-chromium alloy steel comprising 0.1-1.2 wt % of Mn, up to 1.5 wt % of Ni, 8.0-15.0 wt % of Cr, up to 4.0 wt % of Co, 0.5-3.0 wt % of Mo, 0.05-1.0 wt % of V, 0.02-0.5 wt % of Cb, 0.005-0.15 wt % of N, up to 0.04 wt % of B, up to 3.0 wt % of W, and balance Fe and incidental impurities.

Abstract: A process for applying a bond coat layer to a substrate includes cold spraying a first powdered material onto a surface of the substrate at a first velocity, wherein the first powdered material has a first particle size distribution; and cold spraying a second powdered material onto the surface at a second velocity to form the bond coat layer, wherein the second powdered material has a second particle size distribution and the bond coat layer comprises a microstructure comprising at least the first and second particle sizes.

Abstract: A fan housing structure including a base seat and a sideboard. The base seat has a bed section and a mating section extending along a periphery of the bed section. The bed section has a bush made of a material other than the material of the bed section. The bush is disposed on the bed section to axially protrude therefrom. The sideboard is made of a material other than the material of the base seat. The sideboard is disposed on the mating section and integrally connected with the base seat. The sideboard and the base seat together define a space therebetween. The sideboard and the bush are made of a material other than the material of the base seat and are integrally connected with the base seat by means of insert injection molding. Accordingly, the fan housing structure has enhanced structural strength and thinner thickness to save room.

Abstract: A boron-containing nucleating agent is provided for use with a polyarylene sulfide. The boron-containing nucleating agent can have low crystallinity, a small particle size, and a large specific surface area. By selectively controlling certain aspects of the nucleating agent, the crystallization properties of a thermoplastic composition including the nucleating agent and a polyarylene sulfide can be significantly improved. For instance, the recrystallization temperature can be increased, which can allow the “cooling time” during a molding cycle to be substantially reduced. Through use of the boron-containing nucleating agent the recrystallization temperature can be greater than about 231° C.

Abstract: A pump housing of a rotary pump has a pump chamber in which an impeller can rotate, an intake port, an output port similar to the intake port, the intake and output ports having respective axially oppositely directed flanges centered on a flange axis, and respective unitary projections on the flanges each formed with a respective flat extending parallel to the flange axis. The flats form only two axially spaced mounting points for securing the pump to a support surface extending parallel to the axis.

Abstract: A structural platform comprises a first end, a second end, a first side wall and a second side wall, a platform body extending between the first end and the second end and further between the first side wall and the second side wall, a first fillet joining the first side wall and the platform body, a second fillet joining the second side wall and the platform body, the sidewalls being curved.

Abstract: An aluminum alloy turbine housing includes an inlet for exhaust, a turbine wheel space configured to receive exhaust via the inlet, a wastegate opening configured to receive exhaust via the inlet and to provide received exhaust to a wastegate chamber, and a locally hardened valve seat surrounding the wastegate opening. Various other examples of devices, assemblies, systems, methods, etc., are also disclosed.

Abstract: A gas turbine engine component is provided including at least one ring element, and a plurality of circumferentially spaced load carrying vanes extending in a radial direction of the ring element. The load carrying vanes have an internal structure with an anisotropic load carrying property, and the internal structure is configured so that a main load carrying direction is in parallel with the extension direction of the load carrying vane. The component includes a stiffening structure bridging the distance between at least two adjacent load carrying vanes in the circumferential direction of the ring element, and the at least two adjacent load carrying vanes are attached to the stiffening structure.

Abstract: A low rhenium nickel-base superalloy for single crystal casting that exhibits excellent high temperature creep resistance, while also exhibiting other desirable properties for such alloys, comprises 5.60% to 5.80% aluminum by weight, 9.4% to 9.9% cobalt by weight, 4.9% to 5.5% chromium by weight, 0.08% to 0.35% hafnium by weight, 0.50% to 0.70% molybdenum by weight, 1.4% to 1.6% rhenium by weight, 8.1% to 8.5% tantalum by weight, 0.60% to 0.80 titanium by weight, 7.6 to 8.0% tungsten by weight the balance comprising nickel and minor amounts of incidental impurity elements.

Abstract: A fibrous structure for fabricating a composite part including a matrix reinforced by the fibrous structure, the fibrous structure being made by three-dimensional weaving and presenting a main portion and a margin adjacent to the main portion. The margin presents a thickness greater than the thickness of the main portion and the margin includes a first portion arranged in continuity with the main portion and a second portion superposed on the first portion to constitute extra thickness, the margin thus being configured to be folded towards the second portion so that the first and second portions respectively form a flange and a counter-flange for fastening the part.

Abstract: A vacuum pump (1) includes: a rotor (30) provided with a rotor-side discharge function unit (32); a motor (36) that drives the rotor (30) to rotate with respect to a stator-side discharge function unit (22); and a cylindrical pump casing (2) made of a magnetic material, in which the rotor (30) and the stator-side discharge function unit (22) are disposed.

Abstract: A blood pump includes a rotor mounted in a pump housing via a bearing. The housing includes a metal rod extending from the outer wall of the housing towards the inner side of the housing. The rod allows dissipating heat and has a stabilising action.

Abstract: A gas turbine engine fan casing duct wall comprises an intake section and a containment casing, provided respectively with flanges. An acoustic flutter damper is secured between the flanges. The acoustic flutter damper has a skin accommodating an internal structure that dampens fan blade flutter. The skin is secured to the flanges at separate locations. In normal operation of the engine, the internal structure is sufficiently robust to support loads transmitted through the acoustic flutter damper between the intake section and the containment casing. If a blade or blade fragment detaches, the resulting deflection wave in the containment case ruptures the internal structure, and the load path between the intake section and the containment casing passes along the skin, which consequently maintains the connection between the intake duct and the containment casing, while permitting substantial radial deflection of the containment casing relative to the intake section.

Abstract: Various embodiments of the invention provide a low nickel austenitic stainless steel alloy composition including about 0.6% to about 0.8% by weight carbon; about 16% to about 18% by weight chromium; about 4.5% to about 5.5% by weight nickel; about 2.0% to about 5.0% by weight manganese; about 0.8% to about 1.2% by weight tungsten; about 0.8% to about 1.2% by weight molybdenum; about 0.65% to about 0.85% by weight niobium; about 0.3% to about 1.0% by weight silicon; balance iron and unavoidable impurities, wherein percentages are based on the overall weight of the composition. The invention further provides articles, such as turbine housings, prepared using the inventive alloys.

Abstract: A segmented composite shell for an axial turbomachine compressor, each segment formed of a first polymeric material and comprises at least one working surface formed of a second polymeric material co-injected with the first polymeric material. The working surface can be a contact surface with a blade, wherein the working surface has a lipped profile and is made of an elastomeric material. The working surface can be the inner surface for bonding an abradable material, wherein the material can be silicone to facilitate the bonding of the abradable material to the silicone base. The working surface can be a lateral face of the shell that contacts a mating fixed surface, wherein the material can comprise Teflon so as to form a working surface with dry friction properties. Such features enable the shell to have additional technical features implemented directly during the injection moulding of the shell segments.

Abstract: Composite pre-forms are molded at high pressure to form composite parts that can be used in place of metal-based high performance parts, such as the outlet guide vanes found in turbofan jet engines. The composite pre-forms include two different fiber orientations that are co-molded in a resin matrix at high pressures to provide composite outlet guide vanes and other high performance parts. Chambers within the composite part are optionally formed during molding of the pre-form at high pressures.

Abstract: A fan casing (2) for a jet engine has a burst protection arrangement (7) made up of layers at least in an area of fan blades (5). To contain detached fan blades (5) within a fan casing (2) of a jet engine by use of a low-weight and easily manufacturable burst protection arrangement (7), the fan casing (2) is made of a fiber-composite material which itself forms at least one layer provided with at least one inorganic, non-metallic protective layer (8).

Abstract: A static structure of a gas turbine engine according to an exemplary aspect of the present disclosure includes a multiple of airfoil sections between an outer ring and an inner ring. A spring biased tie-rod assembly is mounted through at least one of the multiple of airfoil sections.

Abstract: A bypass turbojet engine including an outer fan duct and an inner fan duct (IFD), between which the secondary flow passes, and a high pressure compressor having an outer casing is disclosed. The IFD is fastened on the outer casing.

Abstract: A plastic compressor housing, in particular a radial compressor housing, preferably for a turbocharger, includes at least one first housing part and at least one second housing part, which respectively comprise at least in some areas at least one thermoset material. The first housing part and/or the second housing part comprises or comprise at least two individual elements, wherein the first housing part and the second housing part are coated at least in some areas with at least one thermoset body or at least one thermoplastic body such that the first housing part, the second housing part and the individual elements of the first housing part and/or the second housing part respectively are in contact at least in some areas with the thermoset body or the thermoplastic body. Also disclosed is a method for producing a plastic compressor housing and a turbocharger.

Abstract: Provided is a wind power generator that reduces the amount of heat input into a nacelle from the outside of the nacelle due to the solar radiation, and that improves the heat dissipation performance from the inside of the nacelle to the outside air. In a wind power generator in which a driving mechanism and power generation mechanism that are connected with a rotor head, to which wind-turbine blades are attached, are accommodated and installed in a nacelle, an outer wall surface of the nacelle is provided with, on at least a part of the wall surface where no direct sunlight is radiated, a heat-dissipation-resistance reducing portion that uses a member having a higher thermal conductivity than that of a peripheral wall member.

Abstract: A lining for a compressor case in use with a gas turbine engine compressor is provided. The compressor includes a compressor casing, which is generally comprised of a first and second half. Inside the casing is a plurality of vanes attached to a plurality of vane bands. The vane bands are affixed to the interior of the compressor casing. A lining, comprising a carbon fiber reinforced-type material is applied to the interior of the compressor casing over the vane bands. The lining allows a minimal clearance to be between the lining and wheel blade tips spinning within the compressor casing. The carbon fiber in the lining allows the lining to withstand a high number of temperature cycles due to the use of the compressor and the gas turbine engine.

Abstract: In one embodiment, a steam device includes a high-temperature member and a low-temperature member. One surface of the high-temperature member is exposed to high-temperature steam, and the other surface is cooled by cooling steam having a temperature lower than the high-temperature steam. The low-temperature member is disposed to face the high-temperature member with a passage for the cooling steam therebetween and is formed of a material having a heat resistance lower than that of the high-temperature member.

Abstract: The invention provides a wind direction cover of an electric fan, comprising a central cap, an external circular frame, a plurality of wind guiding blades between the central cap and the external circular frame which are concentric with the central cap, and a plurality of anchor plates of the wind guiding blades. The exterior side of the most internal wind guiding blade is parallel to the flank of the central cap, and the exterior sides of external wind guiding blades slant toward the external circular frame, angulating the exterior sides of the wind guiding blades with the parallel plane of the flank of the central cap, and the more external the wind guiding blade is, the larger its angle slanting toward the external circular frame is.

Abstract: A manufacturing method and assembly for providing ventilation to a selected structure is disclosed. The assembly may include various features such as flexible portions, rigid portions, and assembly portions. Further, various steps may be used to form the assembly to achieve selected results, such as single piece formation, inclusion of various positioning members, and packaging or shipping considerations.

Abstract: A high-vacuum pump comprises a plurality of pumping stages, each comprising a plurality of mutually cooperating elements, including at least one rotating rotor element and one stationary stator element. At least one of the elements of at least one of the pumping stages is made of a plastic material reinforced with short fibres, dispersed in chaotic and substantially random manner inside the matrix of plastic material. Use of a plastic material reinforced with short fibres allows making the at least one element by injection molding and allows manufacturing the vacuum pump with considerably reduced production costs if compared to the conventional vacuum pumps.

Abstract: A method of processing turbine airfoils includes depositing a protective coating on first and second turbine airfoils, and bonding the first and second turbine airfoils together after the deposition such that there is an open throat between the first and second turbine airfoil and at least portions of surfaces in the open throat are coated with the protective coating.

Abstract: A centrifugal pump is provided capable of pumping liquid volume flow rates of at least 20 m3/sec. The pump includes a centrifugal impeller rotatable about an axis and operable to direct a liquid towards a concrete volute arranged around the impeller. The pump further includes fixed fin-like elements arranged between the impeller and the volute. The elements form a discontinuous barrier around the impeller and are effective to reduce uneven radial thrusts exerted by the water on the centrifugal impeller, whilst limiting the water flow rate in a simple and economic manner.

Abstract: A blade of a turbomachine, in particular of a gas turbine, is disclosed. The blade includes at least one fastening section for fastening the same in a locating section of a rotor-side or stator-side component of the turbomachine. The, or each, fastening section has a core region which is made of a relatively brittle and relatively light material and is embedded in an encasing region made of a material having relatively high ductility.

Abstract: A method for joining a cast metal material blade ring and a metal material hub structure into a turbine rotor. One of the blade ring and the hub structure is mounted in a holder and the other is mounted in a rotation holder for being rotated. At least one of these mountings is heated, and then they are pressed together with a selected force while rotating to weld the ring interior wall and the disk side to form the assembled structure.

Abstract: A method for the application and/or renewal of a protection for a thermal barrier coating system of a heat engine involves a thermal barrier coating system that includes a bond coat layer (2) and a thermal barrier coating layer (3) of porous structure (4), wherein the bond coat layer (2) is located between and in contact with a base metal (1) of a heat engine component and with the thermal barrier coating layer (3) and bonds the thermal barrier coating layer (3) to the base metal (1).

Abstract: A multi-layer filter, a gas turbine including a multi-layer filter, and a process of filtering are disclosed. The multi-layer filter includes a nano-fiber layer positioned to receive an airflow, a coalescing base medium layer, and a membrane layer. The coalescing base medium and the membrane layer are positioned for the airflow to travel through the nano-fiber layer and the coalescing base medium layer, then through the membrane layer. The gas turbine includes an inlet and the multi-layer filter in a filter portion.

Abstract: A shroud for use in a gas turbine engine has a ring with a plurality of protrusions and a plurality of slots and each of the protrusions having an arc length and parallel sides.

Abstract: An airfoil or vane for a combustive power plant includes an inner core formed from a first composite material having discontinuous fibers. An outer sleeve is formed from a second composite material having continuous fibers. The first composite material is different from the second composite material. The outer sleeve generally surrounds and is bonded or otherwise connected to the inner core. A method of fabrication includes injecting or otherwise introducing thermoplastic fiber composite material including chopped or otherwise discontinuous fibers into a mold to form the core and platforms of an airfoil assembly. The injected thermoplastic fiber composite material is then cured in the mold. The cured thermoplastic fiber composite material is then removed from the mold. A layup including one or more surface plies of a thermoset continuous fiber composite material is then applied to the core material. The surface plies are then compressed and cured in a mold.

Abstract: A shroud apparatus for a gas turbine engine includes: a shroud segment comprising low-ductility material and having a cross-sectional shape defined by opposed forward and aft walls, and opposed inner and outer walls, the walls extending between opposed first and second end faces, wherein the inner wall defines an arcuate inner flowpath surface, wherein the shroud segment includes: a radially-inward facing chordal forward mounting surface; and a radially-inward facing chordal aft mounting surface; and an annular case surrounding the shroud segment, the case including: a radially-outward facing chordal forward bearing surface which engages the forward mounting surfaces; and a radially-outward facing chordal aft bearing surface which engages the aft mounting surface of the shroud segment.

Abstract: A plastic compressor housing, in particular a radial flow compressor housing, preferably for a turbocharger, has at least one thermosetting plastic body for providing an intake pipe, a compressor duct, and an outlet pipe, and a thermoplastic at least partially covering the thermosetting plastic body in a hood-like fashion. The thermosetting plastic body is formed as a basic body and the thermoplastic is injection molded on the basic body. At least a first anchoring element is embodied on at least a first surface of the thermosetting plastic body and at least a second surface of the first anchoring element is substantially completely covered with the thermoplastic. The disclosure further relates to a method for producing a plastic compressor housing.

Abstract: A fireshield fastener hood and method of bonding a cover to a substrate therefor.

Abstract: In a cementless pump for pumping molten metal, support structure is suspended above the molten metal. A motor is supported by the support structure. A shaft is fastened to the motor. An impeller is mounted to a lower end of the shaft. A refractory base is supported in the molten metal and includes at least one impeller chamber in which the impeller is rotated and at least one discharge passageway. The base includes through holes. Support posts are each fastened to the support structure and to the base. Refractory sleeves are each disposed in one of the through holes. Post fastening members fasten the lower ends of the posts to the base without cement. A portion of each of the post fastening members is located inside the refractory sleeve. Also featured is a method of replacing posts in a cementless pump for pumping molten metal.

Abstract: A containment case comprises a composite core, with an inner surface, and at least one ceramic layer integrated with the composite core. The at least one ceramic layer is bonded to the inner surface of the composite core with a resin. In another embodiment, a containment case comprises a composite core, with an inner surface, and a hybrid material comprising at least one ceramic material and at least one non-ceramic material. The hybrid material is disposed on the inner surface of the composite core. The hybrid material is bonded to the inner surface of the composite core with a resin. A method of fabricating a containment case includes the steps of disposing one or more layers of ceramic fabric on an inner surface of a composite core, infusing the composite core and the one or more layers of ceramic fabric with resin, and curing the resin.

Abstract: An Ni-based alloy for casting used for a steam turbine of an embodiment contains in percent (%) by mass C (carbon): 0.01 to 0.1, Cr (chromium): 15 to 25, Co (cobalt): 10 to 15, Mo (molybdenum): 5 to 12, Al (aluminum): 0.5 to 2, Ti (titanium): 0.3 to 2, B (boron): 0.001 to 0.006, Ta (tantalum): 0.05 to 1, Si (silicon): 0.1 to 0.5, Mn (manganese): 0.1 to 0.5, and the balance of Ni (nickel) and unavoidable impurities.

Abstract: A method for manufacturing a torque converter includes providing an outer race of a one way clutch, contacting the outer race with a side plate, and casting a stator housing together with the outer race and the side plate. A torque converter is also provided.

Abstract: A method of repairing a flange of a casing, or a casing made of aluminum, for a turbine engine or an airplane turboprop or turbojet, the flange including at least one through hole for passing a bolt for fastening equipment. The method includes: forming a spot face in the flange around the hole for passing the bolt; anodizing the bottom surface of the spot face; placing a washer on the spot face; and fastening the washer to the flange using adhesive.

Abstract: A gas turbine engine includes a CMC static structure and a rotor module with a multiple of CMC airfoils, a radial growth of said rotor module matched with said CMC static structure.

Abstract: Described is reinforcement of a fan case in a gas turbine jet engine. In one embodiment, a containment ring and a hear resistance ring are shrink interference fit on the inside diameter of the fan case, the containment ring where the large fan blades turn, and the heat resistance ring where heated air from backfiring heats up the fan case. In one example, the containment ring is made of a sue alloy to provide added strength to the fan case should a fan blade break, containing the fan blade within the fan case. Also, the containment ring may extent forward of at least the leading edge of each fan blade and aft of at least the trailing edge of each fan blade. The heat resistance ring is made of titanium or other suitable material. Additionally, one or more stiffener rings may be shrink interference fit on the outside diameter of the fan case.

Abstract: A turbine housing of an exhaust-gas turbocharger includes an outer housing, an inner housing, and a tubular fitting which is formfittingly connected to the inner housing and has a flange collar for attachment of a bearing case of a turbine wheel. The inner housing traverses the fitting and has an end portion which is bent radially outwards about the flange collar. A press ring is arranged upon the end portion for additional securement of the inner housing in place.

Abstract: A method of heat treating an Ni-base superalloy article is disclosed. The method includes hot-working an article comprising an NiCrMoNbTi superalloy comprising, in weight percent, at least about 55 Ni to produce a hot-worked microstructure; solution treating the article at a temperature of about 1600° F. to about 1750° F. for about 1 to about 12 hours to form a partially recrystallized warm-worked microstructure; and cooling the article. The method also includes precipitation aging the article at a first precipitation aging temperature of about 1300° F. to about 1400° F. for a first duration of about 4 hours to about 12 hours; cooling the article to a second precipitation aging temperature; precipitation aging the article at a second precipitation aging temperature of about 1150° F. to about 1200° F. for a second duration of about 4 hours to about 12 hours; and cooling the article from the second precipitation aging temperature to an ambient temperature.

Abstract: A thermal barrier includes a thermal barrier member having at least one material selected from a metal foam or a ceramic foam. The thermal barrier member includes an attachment section for securing the thermal barrier member with a corresponding attachment section of a support.