Abstract: A method of fabricating a pump casing that includes an inlet, an outlet and a pump casing body. The pump casing body has a neck portion that defines a groove. The inlet is formed by stamping a sheet of metal to form a basin-shaped body, wherein the stamping the center portion of the basin-shaped body forms the inlet. Centering the basin-shaped body about a first axis and using one set of roller dies to roll form the basin-shaped body into a pump casing body. The pump casing body includes, starting from the inlet, an inlet end plate, a passage side plate, a motor end plate and a neck portion. Stamping the passage side plate forms the outlet. A set of roller dies include an internal roller die and a mating external roller die, wherein both are rotatably mounted along a second and third axes, respectively, wherein the first, second and third axes are parallel to but spaced from each other.

Abstract: A casing structure of metal construction for the rotor blade area of axial flow compressor and turbine stages includes a closed, stable outside wall, a segmented inside wall that is interrupted by multiple expansion joints, and a load-transmitting connecting structure between inside and outside wall. A multiple sub-divided hollow chamber structure with a plurality of thin wall elements standing upright on the inside wall and outside wall, at least the majority of which are directly connected together, is arranged as connecting structure. The hollow chamber structure is connected to the inside wall and/or the outside wall by brazing.

Abstract: A system and method are disclosed which include at least one blade implemented within an air moving device to enable enhanced performance of such air moving device. In one embodiment, an air moving device is disclosed that is operable to generate a flow of air from a low pressure region to a high pressure region. The air moving device comprises at least one blade that is operable to generate a flow of air as a result of movement thereof. The blade(s) include a rough surface on a side facing the low pressure region, and such rough surface is arranged to induce a turbulent boundary layer that enables operation of the air moving device in a manner that would otherwise result in separation of air from the blade(s). The rough surface may be formed by dimples or bumps, as examples, arranged on the surface of the blade(s).

Abstract: A duct fan unit, which is a simple structure that can be disassembled by an easy operation and the manufacture cost thereof can be decreased. The duct fan unit comprises a duct and a fan. The duct, allows air to pass through is constructed by engaging two duct constructing members together. The fan is installed inside the duct. A guide portion having a rib shape is set on only one of the duct constructing members such that the fan can be installed easily. A resilient protrusion is set on the other duct constructing member such that the fan can be resiliently pressed for securing the fan in position. Therefore, by simply latching the connecting plate of one duct constructing member with the connecting hole of the other duct constructing member the two duct constructing members are fixed to each other.

Abstract: An impeller for a circumferential current pump does not generate a weld phenomenon and can make a structure of an injection molding metal mold simple. An impeller (2) for a circumferential current pump (1) is provided with a plurality of vane grooves (12) on an outer periphery of a synthetic resin disc-like member (8) rotated by a motor (3a), and is rotatably received with a substantially disc-like space (6) formed between a pump casing (4) and a pump cover (5). An axial hole (15) engaging with a drive shaft (21) of the motor (3a) is formed in a center portion of the disc-like member (8), and a pressure adjusting groove (17) open to both side surfaces (10, 11) of the disc-like member (8) is formed in the axial hole (15). An annular recess portion (18) for arranging a ring gate (20) for injection molding is formed at a position a predetermined size apart from an outer peripheral side of the axial hole (15).

Abstract: An impeller shaft assembly, coupler and molten metal pump are described, in which a coupling member is configured to be secured to a pump drive shaft and includes a socket part that is defined by a socket wall formed about and extending along an axis. The socket wall includes a plurality of coupling shaft engaging surfaces and a plurality of socket corner surfaces joining the shaft engaging surfaces. The socket corner surfaces are disposed radially outward from adjacent shaft engaging surfaces with respect to the axis.

Abstract: A fluid powered drilling motor adapted for drilling oil wells and other subterranean bore holes. The motor having a rotor and a stator wherein the iron content of the whole motor is less than 0.1% wt. In one embodiment the motor is made of an alloy having a base metal comprising one of copper, nickel, and aluminum plus about 0.05-10 wt % Beryllium. In another embodiment, the motor is made of either 15Ni-8SN—Cu or 9Ni-6Sn—Cu.

Abstract: A hydraulic turbine drive with a multi-material turbine wheel. The turbine wheel is mounted on a shaft defining a shaft material. The blades and a portion of the turbine wheel are comprised of a high strength thermoplastic material having a thermal expansion coefficient substantially higher than the thermal expansion coefficient of the shaft material. The thermoplastic portion of the wheel is radially at least partially contained in a first containing wheel having a thermal expansion coefficient higher than that of the plastic material and lower than that of the shaft. The first containing wheel may also be radially contained in one or more additional containing wheels each having a thermal expansion coefficient higher than that of the first containing wheel. Preferred embodiments of the present invention are the drive wheels for supercharger systems for internal combustion systems. In a particular preferred embodiment the drive wheel is a part of a single shaft hybrid supercharger system.

Abstract: A wear resistant fuel pump for a vehicle includes a pump section having a rotatable impeller and a plurality of plates disposed axially adjacent to and cooperating with the impeller to pump fuel therethrough. The wear resistant fuel pump also includes a motor section disposed adjacent the pump section and having a motor to rotate the impeller. The wear resistant fuel pump further includes an outlet section disposed adjacent the motor section to allow pumped fuel to exit therethrough. The impeller is made of a first compound and the plates are made of a second compound having an abrasion wear resistance on a surface thereof that improves abrasion wear characteristics therebetween.

Abstract: One aspect of the invention is directed to an impeller made of a non-metallic, heat resistant material, comprising a generally cylindrical shaped body having a central rotational axis, first and second generally planar end faces extending transverse to the central axis and a side wall extending between the first and second faces. A plurality of passages have inlets circumferentially spaced apart from each other on the first face, outlets at the impeller sidewall, and connecting portions extending between the inlets and the outlets transverse to the central axis. Each of the passages extends at an angle to the central axis along substantially an entire length and perimeter of the passages.

Abstract: A stage of turbine blades (40) in a gas turbine engine (10) is surrounded by an array of shroud segments (42). The upstream ends of the segments (42) have plenum chambers (54) into which cooling air is fed from a compressor (12) via one hole (66) of a pair of holes, the other being numbered (68). Air from the plenum chambers (54) passes out to film cool the interior surface of each respective segment (42). Air from holes (68) passes out to convection cool the exterior surface of each segment (42), which effect is enhanced by the provision of ribs (80) and fences (82).

Abstract: A turbo-type machine, comprising a casing 2 storing an impeller within an inside thereof, and a plural number of grooves formed on an inner surface of the casing in a direction of pressure gradient of fluid, wherein the grooves 124 are provided from 80 to 150 pieces around a periphery on the inner surface of the casing, and a total width of the grooves all around the inner surface of the casing is from 30% to 50% of a peripheral length on the inner surface of the casing. Also, the area on cross-section of the groove 124 within an area where the blades exist is made larger than that of the groove outside where the blades exist, or openings 127 are drilled on a bottom surface of the grooves, each penetrating through thickness of the casing, or the groove is made in a two-layer structure in the direction of pressure gradient of fluid.

Abstract: Tip treatment bars 16 of a rotor casing 2 for a gas turbine engine are subjected to a process which induces compressive stress within the bars 16. The process may be a laser shock peening process applied to opposite sides 20 of each bar 16. The processing of the tip treatment bars 16 renders them less susceptible to fatigue failure.

Abstract: The invention concerns an apparatus for supporting blades of axial-flow machines, in particular turbojet propulsion units, which is distinguished by at least one pair of mutually oppositely disposed support rings (12, 14) which are supported adjustably relative to each other for assembly between guide or rotor blades of adjacent compressor or turbine stages.

Abstract: The object is, by simple measures, to ensure a particularly smooth inner surface and maintain particularly high dimensional accuracy of a pump housing of a cooling-water pump for a power plant. For this purpose, the cast-concrete pump housing of the cooling-water pump has, according to the invention, a number of formwork elements made of glass-fiber reinforced plastic.

Abstract: A turbine nozzle includes ceramic outer and inner bands and an integral ceramic vane aft segment. A metal vane forward segment adjoins the aft segment in a hybrid assembly.

Abstract: An airfoil having a melting temperature of at least about 1500° C. and comprising a first piece and a second piece joined by a braze to the first piece. The first piece comprises one of a first niobium-based refractory metal intermetallic composite and a first molybdenum-based refractory metal intermetallic composite, and the second piece comprises one of a second niobium-based refractory metal intermetallic composite and a second molybdenum-based refractory metal intermetallic composite. The braze joining the first piece to the second piece comprises one of germanium and silicon, and one of chromium, titanium, gold, aluminum, palladium, platinum, and nickel. This abstract is submitted in compliance with 37 C.F.R. 1.72(b) with the understanding that it will not be used to interpret or limit the scope of or meaning of the claims.

Abstract: A component such as a turbine blade (1) of a gas turbine is provided with an intermetallic felt (2). By providing the tip (11) of the turbine blade (1) with the intermetallic felt (2) and optionally a coating of a ceramic material (3), improved protection against thermal and mechanical effects and improved oxidation resistance can be achieved. Also conceivable would be an arrangement of the intermetallic felt (2) at the rotor (4, 4a) or stator (4, 4b) opposite from the turbine blade (1) or on the platform (12) of the turbine blade (1).

Abstract: A steam turbine rotor having a combination of at least one of a high pressure rotor, an intermediate pressure rotor and a low pressure rotor, which are each formed from a metal material of different chemical composition and welded together by means of welding.

Abstract: An airfoil having a melting temperature of at least about 1500° C. and comprising a first piece and a second piece joined at a bonded region to the first piece by a diffusion bond. The first piece comprises one of a first niobium-based refractory metal intermetallic composite and a first molybdenum-based refractory metal intermetallic composite. The second piece comprises one of a second niobium-based refractory metal intermetallic composite and a second molybdenum-based refractory metal intermetallic composite. The diffusion bond is formed from a first metallic element disposed on a first surface of the first piece and a second metallic element disposed on at least one of the first surface and a second surface of the second piece, the second surface contacting the first surface, wherein the first and second metal form a composition having a melting temperature less than about 1400° C. This abstract is submitted in compliance with 37 C.F.R. 1.

Abstract: A variable gas turbine compressor vane structure includes a gas turbine compressor vane having a vane support at an end thereof, and a case structure having a bearing support disposed to engage the vane support of the gas turbine compressor vane. The bearing support is typically a bearing bushing or a bearing washer. The bearing support is made of a metal skeleton having open-cell porosity extending therethrough, and an infiltrant material such as an organic or a ceramic infiltrated into the porosity of the metal skeleton.

Abstract: A thin wall cooling system has multiple in-wall channels traversing a thin wall structure such as the wall of a gas turbine engine blade or vane. The blade has a hollow interior that may be divided into multiple cavities. Coolant is introduced into an entry opening of each in-wall channel and then discharged through exit openings into the vane cavities. The coolant then exits the cavities by through wall channels to discharge the coolant to form a cool air film on the external surface of the blade. This combination allows improved cooling control for structures that experience an elevated temperature environment, as for example, the flow of hot gas across the exterior surface of a gas turbine engine blade.

Abstract: A furnace blower housing that can be flush mounted to a furnace and includes an integrally formed round exhaust outlet. The blower housing is formed from two separate housing members joined to each other. The blower housing includes an impeller cavity that encompasses a rotating impeller that directs the exhaust gases out of a rectangular outlet. An integrally formed transition section extends from the rectangular outlet to a circular exhaust outlet. The transition section is formed by a bottom half integrally formed with the first housing member and a top half integrally formed with the top housing member. The exhaust outlet is offset from the back plate of the blower housing such that the blower housing can be flush mounted to a furnace.

Abstract: An impeller for a molten metal pump includes a base and a plurality of vanes having openings for flow of molten metal there through during pumping, Alternatively, or in combination with the vane openings, a single drain opening extending through the base of the impeller may be provided remote of the rotational axis of the impeller. In another embodiment, an impeller provides axial and radial pumping. The multiflow impeller includes at least one pumping chamber inclined into the direction of rotation to provide axial pumping.

Abstract: A low pressure turbine shroud includes an arcuate backsheet having opposite mounting rails for engaging a surrounding annular case. The backsheet includes a thicker blade containment shield extending between the rails in a unitary construction. And, a honeycomb rub strip is fixedly joined to the backsheet between the rails.

Abstract: An impeller for a molten metal pump having a cylindrical body comprised of a refractory material. The cylindrical body includes generally coplanar top and bottom surfaces. A central bore is provided in the top surface to provide a point for mating with a shaft. A plurality of circumferentially spaced passages extend from the top or bottom surface to a side wall of the impeller, each of the passages being separate and preferably having an inlet opening which is equal to or less than the corresponding outlet opening in size. A recess being optionally formed in the top or bottom surface, forming the initial inlet to the passages.

Abstract: An inlet protector or guard that prevents jamming and clogging of a molten metal pump. The guard includes a flat surface having a central opening that accepts a shaft of the molten metal pump. A wall extends from the periphery of the flat surface along a longitudinal axis of the shaft. The wall is sized to fit within an inlet opening of the pump. The wall includes a plurality of openings, forming an inlet through which molten metal can enter a base of the pump. The plurality of openings are small enough to prevent solid particles that are larger than a distance between an impeller of the pump and a pump chamber from entering the pump and large enough to prevent the pump from clogging.

Abstract: A gas turbine engine fan blade containment assembly (38) comprising a generally cylindrical, or frustoconical, metal casing (40) has an upstream portion (56), a transition portion (58) and a blade containment portion (54). The upstream portion (56) has a flange (42) connecting the metal casing (40) to a flange (48) on axially adjacent casing (46). The blade containment portion (54) has a greater thickness (T2) than the thickness (T1) of the upstream portion (54). The transition portion (58) connects the blade containment portion (54) and the upstream portion (56) to transmit loads from the blade containment portion (54) to the flange (42) on the upstream portion (56). The ratio of the thickness (T4) of the flange (42) on the upstream portion (56) to the thickness (T1) of the upstream portion (56) is between 3 to 1 and 6 to 1.

Abstract: Disclosed is a producing method of an exhaust gas vane blade for superchargers of motor vehicles. The vane blade consists of a pivot part and a blade part with a streamlined section, which are integrally formed with each other. The vane blade is made of a heat resisting steel. The diameter of the pivot part is larger than the thickness of the blade part. The method comprises a multi-step cold-forging of a blank material of the above steel.

Abstract: An impeller for a circumferential current pump is provided with a plurality of vanes, and each of the vanes has an upstream side surface and a downstream side surface in a rotating direction thereof and a center line between both these surfaces extends along a radial direction of a disc-shape member, the upstream side surface has a radially inside portion and a radially outside portion which are formed to be continuous so that the radially inside portion is in parallel to the center line and the radially outside portion is inclined forward in the rotating direction of the disc-shape member, and the downstream side surface is formed entirely to be parallel to the center line.

Abstract: The invention relates to a radial blower for a work apparatus and especially for a suction/blower apparatus. The radial blower has a blower wheel (2) and a blower housing (1) which at least partially surrounds the blower wheel (2). The blower housing (1) includes a peripheral wall (3) and a side wall (4). The housing includes an intake opening (6) in the region of the blower wheel axis (5) as well as a discharge stub (7) peripherally of the blower wheel (2) in the region of the peripheral wall (3). The peripheral wall (3) and the side wall (4) are lined on the side facing toward the blower wheel (2) with a wear insert (8) configured as one piece.

Abstract: At least one airfoil shaped vane made of a low ductility material, for example a ceramic base material such as a ceramic matrix composite or an intermetallic material such as NiAl material, is releasably carried in a turbine vane assembly including inner and outer vane supports by at least one high temperature resistant compliant seal. The seal isolates the vane from at least one of the vane supports and allows independent thermal expansion and contraction of the vane in respect to the support.

Abstract: An improved mud motor for drilling bore holes in subterranean formations is formed from a non-magnetic alloy containing no more than 0.1 wt. % iron.

Abstract: A tip treatment bar (16) for a gas turbine engine has a damping coating (24) applied to one or more sides. The coating (24) may be a hard ceramic, for example Magnesia Alumina Spinel, and this may be plasma sprayed directly on to the bar (16) or applied to a substrate (26) which may then be applied to the bar (16).

Abstract: An impeller for a circumferential current pump is injection molded and can be used as it is without being polished. The impeller (7) is provided with a plurality of vane grooves (12) on an outer periphery of a synthetic resin disc-like member (8) rotated by a motor, and is rotatably received with a substantially disc-like space (6) formed between a pump casing (4) and a pump cover (5). A disc-like recess portion (14) is formed in both side surfaces (10, 11) of the disc-like member (8). A formation is performed so that a ratio (L/2t) between the sum (t1+t2=2t) of a gap (t1) between one side surface (10) and the pump casing (4) and a gap (t2) between another side surface (11) and the pump cover (5), and a size (L=R0−H−R1) obtained by subtracting a radical groove length (H) of the vane groove (12) and a radial size (R1) of the recess portion (14) from a radial size (R0) of the disc-like member (8) satisfies a relation 66≦(L/2t).

Abstract: According to the invention, an article that is exposed to high temperatures, e.g., over 1000 ° C. during operation is disclosed. In one embodiment, a turbine blade for a gas turbine engine includes a directionally solidified metallic substrate, e.g., a superalloy, which defines an airfoil, a root and a platform located between the blade and root. The platform has an underside adjacent the root, and a corrosion resistant noble metal-containing aluminide coating is located on portions of the blade susceptible to corrosion and/or stress corrosion cracking, such as the underside of the platform and the neck. The applied coating prevents corrosion and stress corrosion cracking of blade in these regions.

Abstract: The invention is a chambered vane impeller molten metal pump comprising a drive means, a motor mount, a coupling with a taper facilitating shaft removal, a shaft with a tapered top and a bottom with dovetail mating grooves for accepting impeller vanes, a bearing supporting the shaft, tapered support sockets, supports comprising a tapered end, an aperture, and groove, a laminated base, and a fabricated chambered vane impeller. The drive can be a motor with a gear box where the motor is air, hydraulic, electric, or a prior art direct drive electric motor with a soft start.

Abstract: An improved pump shell for a multistage metal working pump includes a plurality of pump shell units housed in series within a hollow cylindrical casing and has the impellers driven by a shaft. Each pump shell unit has a inner shell which forms a holding end at one side and a sealing flange at another side. The holding end of one pump shell may align and engage precisely and easily with the sealing flange of an adjacent pump shell unit to form a smooth fluid passage from the inlet of the impeller through the inner shell so that pumping efficiency may be enhanced with less turbulence. The sealing flange, holding end and the casing also form a close annular compartment for holding a seal ring inside to provide effective sealing function. The pump shell may be produced by stamping at low cost.

Abstract: According to the invention, an article that is exposed to high temperatures, e.g., over 1000° C. during operation is disclosed. In one embodiment, a turbine blade for a gas turbine engine includes a directionally solidified metallic substrate, e.g., a superalloy, which defines an airfoil, a root and a platform located between the blade and root. The platform has an underside adjacent the root, and a corrosion resistant noble metal-containing aluminide coating is located on portions of the blade susceptible to corrosion and/or stress corrosion cracking, such as the underside of the platform and the neck. The applied coating prevents corrosion and stress corrosion cracking of blade in these regions.

Abstract: A blower housing having a casing with a resilient bottom piece and a rigid top piece assembling with the bottom piece to define an interior of the casing is provided. The bottom piece of the blower housing directly abuts a blower mounting surface. The top piece supports a blower motor. The bottom piece is constructed from a vibration dampening material. The top piece is constructed from a rigid material. The vibration absorbing material attenuates noise and other vibrations transmitted from the blower motor and impeller of the blower housing to the blower mounting surface and other associated structures.

Abstract: A gas turbine stationary shroud is a curved stationary shroud body having a concave inner gas-path surface and a generally convex back. The curved stationary shroud body is made of an open-cell solid ceramic foam having ceramic cell walls with intracellular volume therebetween. The ceramic foam may be tailored to provide requirement properties. The ceramic adjacent to the gas path surface may be modified to increase or decrease its abrasion resistance, depending upon the design requirements of the stationary shroud. The intracellular volume adjacent to the gas-path surface may be porosity. Some of the ceramic material adjacent to the back of the shroud may be removed, and the intracellular volume adjacent to the back of the shroud may be filled with a nickel-base alloy.

Abstract: A protective structure includes a substrate made of a nickel-base superalloy component of a gas turbine engine, and a ceramic thermal barrier coating overlying and bonded to the substrate. The ceramic coating is an open-cell solid foam of aluminum oxide ceramic cell walls having a porous interconnected intracellular volume therebetween. The ceramic coating is prepared by depositing a precursor material onto the surface of the substrate. The precursor material includes a sacrificial ceramic, typically silicon dioxide, and a reactive metal, typically aluminum, which is reactive with the sacrificial ceramic to form an open-celled ceramic foam. The sacrificial ceramic and the reactive metal are reacted together to form ceramic cell walls of an oxidized ceramic of the reactive metal, preferably aluminum oxide, and an interconnected intracellular volume therebetween filled with an intracellular metal. The intracellular metal is thereafter removed to leave a porous intracellular volume.

Abstract: One aspect of the invention is directed to an impeller made of a non-metallic, heat resistant material, comprising a generally cylindrical shaped body having a central rotational axis, first and second generally planar end faces extending transverse to the central axis and a side wall extending between the first and second faces. A plurality of passages have inlets circumferentially spaced apart from each other on the first face, outlets at the impeller sidewall, and connecting portions extending between the inlets and the outlets transverse to the central axis. Each of the passages extends at an angle to the central axis along substantially an entire length and perimeter of the passages.

Abstract: A low-pressure turbine is provided with guide vanes and rotating vanes, the vane blades of which have a coating that is hydrophobic or water-repellant and has a smooth surface. The coating preferably contains amorphous carbon. The hydrophobic property of the coating has the result that small droplets contained in the steam phase, upon impacting a coated vane blade, roll off across the vane blade in the form of small droplets and further follow the steam flow. This prevents moisture losses and increases the efficiency of the turbine. It also prevents the small droplets on the vane blades from coalescing into larger drops or into a fluid film. This prevents erosion due to the impact of large drops on vanes and other components of the turbine.

Abstract: The main object of the present invention is to provide a steam turbine rotor shaft whose high-temperature strength is excellent at a selected temperature of 650 degrees C. A steam turbine rotor shaft comprising 0.05% to 0.20% by weight of carbon, 0.20% or less by weight of silicon, 0.05% to 1.5% by weight of manganese, 0.01% to 1.0% by weight of nickel, 9.0% to 13.0% by weight of chrome, 0.05% to 2.0% by weight of molybdenum, 0.5% to 5.0% by weight of tungsten, 0.05% to 0.30% by weight of vanadium, 0.01% to 0.20% by weight of niobium, 0.5% to 10.0% by weight of cobalt, 0.01% to 0.1% by weight of nitrogen, 0.001% to 0.030% by weight of boron, 0.0005% to 0.006% by weight of aluminum, and the remaining parts substantially comprising iron and inevitable impurities.

Abstract: An impeller is disclosed including a number of vanes, first and second coaxial disks formed from composite material on opposite sides of the vanes to fix the vanes in position, so that the impeller can rotate on an axis of rotation, and at least one reinforcing collar disposed coaxially with and adjacent to the axis of rotation to provide an interior collar, the at least one reinforcing collar comprising reinforcing fibers, such as carbon fibers.

Abstract: A steam turbine blade made of a martensite steel having high strength and high toughness, and a low pressure steam turbine and a steam turbine power generating plant using the steam turbine blades. The steam turbine blade is made of a martensite steel containing C of 0.13-0.40%; Si less than 0.5%; Mn less than 1.5%; Ni of 2-3.5%; Cr of 8-13%; Mo of 1.5-4%; at least one kind of Nb and Ta of 0.02-0.3% in total; V of 0.05-0.35; and N of 0.04-0.15%.

Abstract: A floatable impeller for multistage metal working pump includes an impeller hub which has an impeller metal working member supporting a rear wall of the impeller and an impeller plastic member integrally formed with the impeller working member. The impeller plastic member is engaged with and driven by the pump shaft. The impeller has a front wall attached with an impeller thrust ring which has a thrust metal working member integrally formed with a thrust plastic member located in front of the impeller front wall. The thrust plastic member serves as a bearing when rotating against a metallic pump shell of an adjacent pump unit for reducing friction loss. The impeller hub has axial grooves formed in the inside wall. The thrust plastic member has radial slots formed in the sidewall. The grooves and slots may collect and discharge grits and sands carried by fluid and generated by friction for reducing friction, improving pumping efficiency and enhancing pump durability.

Abstract: A device for pumping molten metal that eliminates rotor bearing members comprises a pump having a pump chamber including a first bearing surface, and a monolithic rotor having a second bearing surface that aligns with the first bearing surface. The second bearing surface is formed of and integral with the material forming the rotor. Preferably a rigid rotor shaft to motor shaft connection is utilized to rigidly center the rotor within the pump chamber and, hence, within the first bearing surface.

Abstract: A part is used that constitutes a platform web and that has a shape close to the shape of the platform with an inside face and an outside face that are opposite each other. Fiber reinforcement plies are draped on a blade core and at least some of these plies extend beyond an end of the blade that is to be connected to the platform so to form ply extensions. The ply extensions are folded down against the inside and outside faces of the platform to form flaps securing the blade to the platform, and fiber reinforcement plies are draped around the platform web and over the flaps so as to form a platform box holding the flaps prisoner.