Abstract: A metal annular casing (16) for a turbine engine compressor, the casing having at least one annular row of radial chimneys for receiving outer cylindrical pivots of variable-pitch vanes, together with an outer cylindrical centering track (28) that is continuous or interrupted and against which runners carried by an annular ring for controlling the pitch of the vanes are to come to bear, the casing being characterized in that the track is formed by blocks (30) of plastics material fitted onto the casing and that are fastened or held on the casing.

Abstract: An example turbomachine system includes a first variable outer air seal including at least one channel. The first variable outer air seal configured to selectively communicate a fluid in response to movement of a second variable outer air seal relative to the first variable outer air seal. An example fluid control method includes selectively covering a channel inlet using a variable outer air seal to control flow through the channel.

Abstract: Embodiments of the present invention may include a turbocharger having a turbine, a turbine housing, a variable valve, a first plate, a second plate and a heat shield member. The turbine housing accommodates the turbine and has a flow path. The variable valve rotates about each pivot member provided thereon, thereby adjusting the flow velocity of fluid guided from the flow path to the turbine. The first plate supports one end of each pivot member, and defines the flow path. The second plate supports the other end of each pivot member or the variable valves, and defines the flow path. The heat shield member covers a wall surface of the turbine housing, and defines the flow path.

Abstract: A turbine housing comprises an exhaust port flange, a turbine discharge flange, a crossover flange, and a bearing support ring. The exhaust port flange is configured for mechanically coupling the turbine housing to a mating structure providing a source of working fluid. The turbine discharge flange is configured for mechanically coupling the turbine housing to an exhaust system. The crossover flange is configured for mechanically coupling the turbine housing to a crossover duct. The bearing support ring is configured for mechanically supporting a bearing, on which a turbine output shaft is supported. The turbine housing defines an inlet plenum, a turbine shroud, and a discharge vent. The exhaust port flange defines an inlet port configured to provide fluid communication between the inlet plenum and the source of working fluid. The turbine shroud defines a fluid expansion flow path for expansion of the stream of working fluid.

Abstract: The invention relates to an aircraft propulsion engine (1) comprising a case, notably a fan case (18), a cowl (20) forming part of the nacelle of the engine (1), the cowl (20) being designed to at least partially surround said case leaving a space (22) between the cowl and the case (18), in which space (22) at least one piece of equipment (24) is mounted and extends along the axis (10) of said engine (1), the cowl comprising a wall and wall stiffeners fixed to the internal face (34) of this wall, wherein at least a part of the stiffeners of the cowl is arranged to form air guide ducts, said air guide ducts being assembled into an air distribution circuit to ventilate said equipment.

Abstract: A fan device for high torque output has two base plates, multiple fans, and a spindle. The base plates are mounted parallel to each other. The fans are mounted between the base plates, and each fan has an inner side, an outer side, and an inflection point. The spindle is connected with one of the base plates and is located at a middle position of the base plate. A connecting line that connects the inflection point and the spindle is out of an area defined between a connecting line that connects the spindle and the inner side and a connecting line that connects the spindle and the outer side when the inflection point, the inner side, and the outer side are located at the same horizontal plane. Therefore, each fan has a large frontal area to be pushed by fluid.

Abstract: A feed diffuser is disclosed. The diffuser may comprise a base disposed orthogonal to a flow, a body extending from the base toward the flow, and an apex provided at a termination of the body in a direction toward the flow. The body may decrease in cross-sectional area from the base to the apex.

Abstract: A method for profiling a replacement blade for an axial turbomachine is provided. The method includes: measuring hub contour geometry and housing contour geometry of the flow channel of the old blade and the axial position of the centre of gravity of the blade aerofoil of the old blade; laying out geometry of the blade aerofoil of the replacement blade, the blade aerofoil having a rearward sweep on its leading edge; defining a region of the blade aerofoil near the mounting and in which positive influence of the rearward sweep on the degree of stage efficiency is rated as low; and axially displacing the replacement blade aerofoil section arranged outside this region in the upstream direction, until the axial position of the centre of gravity of the blade aerofoil of the replacement blade coincides with the old blade.

Abstract: A tilting pad bearing for a high speed rotary machines, such as a turbocharger for an internal combustion engine, comprises a cage and a plurality of tilting pads. The cage is formed by two annular rings separated by spacers machined from a single billet of high-temperature metal. The bearing pads are inserted between the spacers of the cage. One or more O-rings retain the bearing pads within the cage during assembly of the bearing but are not required after installation of the bearing. When retained in the final assembly and installation of the bearing, the O-rings allow tilting movement of the pads within the cage. The outer surfaces of the spacers have a plurality of grooves, and outer surfaces of each of the pads have matching grooves. One of the grooves is an oil groove, wherein the oil groove of the spacers communicating with and oil inlet holes in the spacers. At least one of the other grooves receives an O-ring that hold the pads in place in the cage during installation.

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

Abstract: This invention describes a device effective in maximizing the power output of a rotor in a fluid. This turbine uses a rotor (2) similar to HAWT but placed in a vertical position enclosed in a static diffuser with the shape of an inverted wing. The motionless structure (1) is influenced by two combined flows, enhancing the energy produced by the rotor (2). The rotor (2) is connected to an element of transformation of mechanical energy integrated in the structure (1) with an aerodynamic shape of an inverted wing. The system does not have an orientation mechanism with the direction of the wind since it is completely omnidirectional and presents only one movable component, the rotor (2) with blades (3). The turbine may still comprise an aerodynamic deflector in a brim (6) in the upper part of the structure (1) and is divided in multi-elements (9) with at least two aerodynamic elements. This invention is applicable in the energy producing energy with the micro-generation, as well as large power systems.

Abstract: A device is of a self-adjusting foil suspension in which a foil is placed in a fluid flow, typically a tidal flow. The foil is rotatable around a rotational axis, and the foil is connected by means of an arm to a track. The arm is rotatable around the rotational axis and rotatably connected to the track around a suspension axis at a radial distance from the rotational axis, the suspension axis being parallel to the rotational axis.

Abstract: A fluidfoil is disclosed including a leading edge and a leading edge zone behind the leading edge. The leading edge zone extends spanwise for the full length of the fluidfoil. The leading edge zone includes one or more deflected regions which locally reduce the angle of attack of the fluidfoil.

Abstract: The invention generally relates elevator assemblies suitable for lifting heavy components associated with wind turbines. In certain embodiments, the invention provides an elevator assembly encompassing a wind turbine nacelle and an elevator frame. The elevator frame is configured to surround a tower supporting the nacelle of the wind turbine and is equipped with a means for balancing the frame along a horizontal axis. In some aspects, the means for balancing the frame include a ballast tank system.

Abstract: The invention regards a method for estimating the temperature of a semiconductor chip accommodated in a power semiconductor device in operation, such as an IGBT power module, the method comprising the steps of; while the power semiconductor device is in operation determining a voltage drop over the power semiconductor device for a value of applied load current and; estimating the temperature of the semiconductor chip by evaluating the relationship between the determined voltage drop and the value of applied load current on the basis of a semiconductor chip temperature model. The invention also regards the corresponding apparatus for estimating the temperature of a semiconductor chip, as well as a wind turbine comprising such an apparatus.

Abstract: A nacelle main frame structure and drive train assembly (10) for mounted on a tower (2) of a wind turbine (1). The nacelle main frame structure and drive train assembly (10) comprise a nacelle main frame structure (3) and at least part of a drive train (4). The at least part of the drive train (4) comprises a first connection interface (11) with the nacelle main frame structure (3) at a rotor side (R) of the nacelle main frame structure and drive train assembly (10) and a second connection interface (13) with the nacelle main frame structure (3). The second connection interface (13) is axially displaced with respect to the first connection interface (11) with respect to a direction away from the rotor side (R).

Abstract: A ring fan and shroud guide system which includes a rotating fan member with a conical outer ring and a cylindrical shroud member overlapping at least a portion of the outer ring. A plurality of guide vanes are provided in the shroud which minimize the tangential velocity component of the air flow entering the tip-gap region and provide improved air flow through the system. The guide vanes can have a curved configuration.

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

Abstract: An aircraft rotor blade having a root portion having a through seat and designed for connection to the rotor; and a main portion extending from the root portion. The blade is produced by polymerizing an assembly having a main structure of composite material, and a composite material covering defining the outer surface of the blade. At the root portion, the main structure has a contoured block; and a lamina member extending about at least part of the block, and having a first part adhering to a first peripheral portion of the block, and a second part spaced apart from and facing a second peripheral portion of the block to form the seat; the lamina member having a pre-preg of continuous unidirectional fibres.

Abstract: A ceiling fan blade includes a lower blade and an upper blade combined together. The lower blade is provided with a recess and secured thereon with a plurality of engage fasteners, and the upper blade is formed with a recess and embedded therein with a plurality of engage posts respectively corresponding with the engage fasteners. The engage post is engaged with the engage fastener to form a one-way engagement for reinforcing combination of the upper blade with the lower blade. The ceiling fan blade of this invention can not only conform to environmental protection but also avoid being broken apart when used to insure safety in use. In addition, the ceiling fan blade of this invention is hollow in structure, able to lighten the blade, and no locking member is provided on the surface of the blade, able to keep beautiful external features of the ceiling fan.

Abstract: A gas turbine engine spinner assembly including a spinner defining at least in part an aerodynamically smooth surface, a shell defining at least in part the aerodynamically smooth surface, and circumferentially spaced apart removable aerodynamic fairings located around the shell. Fairing shanks disposed in circumferentially spaced apart axially extending slots in the shell may be attached to the aerodynamic fairings. The fairings may shield radially extending portions of the fan blades including portions of blade shanks or portions of transition regions of the blade shanks. The fairing shanks may be disposed between and monolithically formed with the fairings and fairing roots attached to the fairing shanks. The fairings may be made of an injectable thermoplastic and the shell made of metal. The fairing shanks may be setback from fairing forward tips and the fairing shanks may be setback from root forward tips of the fairing roots.

Abstract: A method of at least one of coating of and applying lacquer on magnetic rings of a rotor magnetic bearing mounted on the rotor, includes arranging of the magnetic rings (4) of the magnetic bearing on the rotor (1) at a location (3) provided for the magnetic rings (4), and coating of and/or applying lacquer on exposed surfaces (10) of the magnetic rings (4), respectively. The rotor includes magnetic rings arranged thereon or therein and coated or having lacquer applied thereon in accordance with the above-described method, and a vacuum pump includes such a rotor.

Abstract: A gas turbine engine component includes a structure having a cooling passage providing upstream and downstream portions separated from one another by an inner wall and fluidly connected by a bend. First and second trip strips are respectively arranged in the upstream and downstream portions. The first trip strips are arranged at a first spacing from one another. The second trip strips are arranged at a second spacing from one another. A turbulence promoter is arranged in the bend and at a third spacing from the first trip strips that is different than the first spacing. The turbulence promoter is arranged at a fourth spacing from the second trip strips that is different than the second spacing.

Abstract: An airfoil for a gas turbine engine includes pressure and suction walls spaced apart from one another and joined at leading and trailing edges to provide an airfoil having an exterior surface that extends in a radial direction to a tip. A camber line at the tip extends from the leading edge to the trailing edge. Pressure and suction side shelves are arranged in the exterior surface on opposing sides of the camber line respectively in the pressure and suction side walls. A plateau is proud of and separates the pressure and suction side shelves. The plateau is arranged along the camber line and extends to the leading edge.

Abstract: A propulsion engine for an aircraft, the propulsion engine comprising: one or more fans (1, 2) rotatably linked to one or more respective shafts (11); a driving means arranged to drive the one or more fans; and a first hydraulic pump-motor (10) connected to one of the fan shafts, the first hydraulic pump-motor comprising a cam (12) disposed about the shaft and one or more radially extending pistons (13) arranged to engage a surface of the cam, the cam and pistons being arranged such that the pistons reciprocate due to the rotation of the cam, wherein the first hydraulic pump-motor is arranged to selectively transfer a variable amount of power to or from the one or more fans so as to control the rotational speed of the one or more fans.

Abstract: A variable displacement hydrostatic power unit (7) is in a drive connection with an internal combustion engine (2). When operated as a pump, the power unit (7) delivers hydraulic fluid to at least one consumer (V). When operated as a motor, the power unit (7) is a hydraulic starter for the internal combustion engine (2) and is supplied with hydraulic fluid from a hydraulic accumulator (25). The displacement volume of the power unit (7) is set by a displacement volume control device (50) actuated by a positioning device (52). The displacement volume control device (50) is displaced into a position with maximum displacement volume by a corresponding actuation of the positioning device (52) chronologically prior to the shutoff of the internal combustion engine (2). A securing device (60) holds the displacement volume control device (50) in the maximum displacement volume position when the internal combustion engine (2) is shut off.

Abstract: An electric motorcycle comprises a hydraulic pump, an oil passage, a first hydraulic pressure detecting section for detecting a hydraulic pressure in the oil passage, a hydraulic pressure determiner section for determining if the hydraulic pressure is less than a first allowable value, a pump state determiner section for determining if an activation command is output to the hydraulic pump, and a warning output section for outputting a warning signal according to a result of the determination performed by the hydraulic pressure determiner section and a result of the determination performed by the pump state determiner section, wherein the warning signal is not output when the activation command is not output and the hydraulic pressure is less than the first allowable value; and the warning signal is output when the activation command is output and the hydraulic pressure is less than the first allowable value.

Abstract: Methods and apparatus for lubricating suspension seals by pumping fluid to the seals using a compression or rebound action of a suspension component.

Abstract: In a blower fan according to a preferred embodiment of the present invention, a stationary portion of a motor portion includes a stator, a bearing portion, and a holding portion to which both the stator and the bearing portion are fixed, while a rotating portion includes a central rotating portion, and an annular cup portion fixed to the central rotating portion. The central rotating portion includes a shaft, a bearing opposing portion, and a cylindrical seal portion. The cup portion includes a cylindrical cup inner wall portion fixed to an outer circumferential surface of the cylindrical seal portion, a cup top plate portion, and a cup outer wall portion. A seal portion having a surface of a lubricating oil defined therein is defined in a seal gap between an inner circumferential surface of the cylindrical seal portion and an outer circumferential surface of the bearing portion.

Abstract: A dryer with a modular blower assembly that allows easy assembly and field servicing through replacement of the blower assembly as a unit. The blower assembly generally includes unique motor mounts that allow a motor assembly to be secured within a housing without being directly fastened to other members.

Abstract: A drive train (1) includes an internal combustion engine (2) and working hydraulics (4) having at least one hydraulic pump (7). When operated as a pump, the hydraulic pump (7) sucks hydraulic fluid from a tank (9) and delivers into a delivery line (10) that leads to the working hydraulics (4). When operated as a motor, the hydraulic pump (7) is supplied with hydraulic fluid from a hydraulic accumulator (25). The drive train (1) has a charge pump (20) to supply a charging circuit (23). The charge pump (20), when operated as a pump, sucks hydraulic fluid out of the tank (9) and delivers into a charge pressure line (22) that leads to a charging circuit (23), and the charge pump (20) when operated as a motor is supplied with hydraulic fluid from the hydraulic accumulator (25).

Abstract: The invention relates to a turbine (1), in particular of an exhaust gas turbocharger, having a turbine rotor (4), which is rotatably mounted in a housing (2), with which at least one radial inlet channel (9) for a guide apparatus (7) forming a medium which drives the turbine rotor (4) is associated, wherein said guide apparatus (7) has multiple guide vane bearing rings (10), which radially enclose said turbine rotor (4) and have guide vanes (8) which lie in said inlet channel (9), and a guide vane cover ring (12), and wherein said inlet channel (9) is axially delimited by said guide vane bearing ring (10) and said guide vane cover ring (12) and said guide apparatus (7) is mounted in the housing (2) so it is axially and/or radially movable for material relaxation. Furthermore, the invention relates to an exhaust gas turbocharger, in particular for a motor vehicle.

Abstract: The compressor fittings, both suction and discharge, of a compressor can have braze rings positioned inside of the fittings as part of the compressor assembly. The braze ring can then be used by an installer to connect the compressor to corresponding suction and discharge lines of a system. The installer can insert the system tube or connection into the fitting and apply a torch until braze material can be seen exiting the joint around the system tube, which indicates the tube has been connected.

Abstract: A sealed compressor of the present invention comprises an electric component (103); a compression component (105); a sealed container (101); and a suction pipe (115); wherein the compression component (105) includes a compression chamber (141), and a suction muffler (115) through which a refrigerant gas flows; wherein the suction muffler (157) includes a muffler body (165) in which a muffling space (163) is formed, a tail pipe (159) through which a refrigerant gas is introduced into the muffling space (163); and a muffler cover (169) provided to surround the muffler body (165) such that a first space (167) is formed between the muffler cover (169) and the muffler body (165); wherein the muffler cover (169) is provided with a refrigerant inlet (175) in a portion which faces an outlet (117) of the suction pipe (115) and is in the vicinity of a suction port (171) of a tail pipe (159), the refrigerant inlet communicating the interior of the sealed container (101) with the first space (167).

Abstract: A motor cap has a plurality of holes in the top of the cap for the entry of refrigerant into the suction plenum. The holes are sized and located to create a tortuous path for a stream of refrigerant to enter the compression chamber. The refrigerant stream is broken into multiple streams and any liquid refrigerant is encouraged to flash to vapor. Any oil that is brought from the sump at startup by boiling liquid refrigerant is likewise encouraged to remain on the motor cap and drain back to the sump while the liquid refrigerant flashes to vapor.

Abstract: A suction fitting for a compressor can include screens, filters, and direction control louvers to both filter out particulates and direct higher mass liquid refrigerant downward away from the inlet to the compression chamber. Alternatively, a mesh filter can be place over the opening(s) to the suction plenum to prevent debris and contaminants from entering the suction plenum.

Abstract: A compressor can have one or more of a suction fitting with integral louvers and a screen, a motor cap with a plurality of holes in the top surface of the motor cap to permit refrigerant to enter a suction plenum, a filter positioned over the plurality of holes in the motor cap, a filter for the cage bearing and a braze ring installed in one or more of the compressor fittings.

Abstract: A magnetic bearing device comprises a controller configured to obtain magnetic levitation information of the rotor shaft by AD sampling of current detection signals from the plurality of current sensors and a sum signal obtained by adding the pair of current detection signals relating to the pair of electromagnets, and perform PWM control of the excitation amplifiers based on the magnetic levitation information. The controller performs PWM control so that a length of one of an on-duty period and an off-duty period of the PWM carrier signal is always longer than a predetermined time period based on an attenuation characteristic of a spike noise produced in the electromagnetic current, and performs the AD sampling after the predetermined time period passes from starting timing of one of the on-duty period and the off-duty period.

Abstract: A pump includes an electric motor that is mounted in a motor compartment, a rotor that is mounted in a pump chamber and coaxial to a driven shaft of the motor and driven by the motor, a pump inlet nozzle, and a pump discharge nozzle, wherein the pump is enclosed by a housing and wherein the motor compartment is connected to a surrounding atmosphere by a ventilation channel. The ventilation channel is arranged parallel to the shaft of the motor in the housing and is guided from a lower end of the housing in the region of the pump inlet nozzle up to a passage opening that is formed directly underneath a motor bearing bracket.

Abstract: Linear peristaltic pump for pumping a fluid through a flexible tube (13) comprises a rotatable central member (34) with a plurality of radially disposed planetary gears (51-53). An offset roller (61-63) is disposed on each of the planetary gears (51-53). The flexible tube (13) is inserted between a generally flat compression surface (40) and at least one of the plurality of rollers (61-63). Rotation of the central member (34) enables the plurality of rollers (61-63) to serially collapse the flexible tube (13) and to move in a substantially linear motion along the generally flat compression surface (40) for pumping the fluid through the flexible tube (13).

Abstract: A method and system for reducing pulsation in a gas compressor system. A side branch absorber, which may be installed on the lateral piping of either the suction or discharge side of the cylinders, has a hyperbolic horn at the input end. The hyperbolic horn in series with an inlet reducer substantially increases the mass reactance of the resonator and substantially reduces the resonator frequency or the required cavity volume for target resonator frequency. The horn is hyperbolic in the sense that it has a large diameter at the first end tapers to a smaller diameter near the second end.

Abstract: The invention relates to a double-helical gear rotary positive displacement pump comprising a pump housing (14) rotatably supporting at least a driving shaft (2) and at least a driven shaft (3), at least a first toothing (4) and a second toothing (5) being associated to said driving shaft (2) and at least a third toothing (6) and a fourth toothing (7) being associated to said driven shaft (2). The toothings (4, 5, 6, 7) have individually a helical profile that allows their mutual herringbone meshing. Three of toothings (4, 5, 6) are rigidly connected to their respective shafts (2, 3): the fourth toothing (7), or other suitable one, is idle on the shaft and axially constrained.

Abstract: A method of manufacturing an annular wall (46) of a combustion chamber (15) comprises depositing layers of a metal sequentially one upon the other to form layers of a spiral wall (45) of the combustion chamber (15). Each layer of metal is deposited in a spiral pathway (122). The ends (E1, E2) of the spiral wall (45) of the combustion chamber (15) are joined together to form the annular wall (46) of the combustion chamber (15). The ends (E1, E2) of the spiral wall (45) of the combustion chamber (15) are at the opposite ends of the spiral pathway (122).

Abstract: A method is of producing a circular saw blade having cooling channels. In that case, placing of a plurality of thread-shaped bodies on a first circular disc of plastic material is carried out in such a manner that each of the thread-shaped bodies is oriented in radial direction. A second circular disc of plastic material is then placed on the first disc and the thread-shaped bodies. Subsequently, pressure is exerted on the second disc in the direction of the first disc. Removal of the plate-shaped bodies from the compressed disc pair is thereafter carried out, whereby cooling channels are created. Finally, sintering of the disc pair in order to obtain a circular saw blade having cooling channels running in radial direction is carried out.

Abstract: A high strength titanium alloy member with superior fatigue resistance, and a production method therefor, are provided. The production method includes preparing a raw material made of titanium alloy, nitriding the raw material to form a nitrogen-containing raw material by generating a nitrogen compound layer and/or a nitrogen solid solution layer in a surface layer of the raw material, mixing the raw material and the nitrogen-containing raw material to yield a nitrogen-containing mixed material, sintering the nitrogen-containing mixed material to obtain a sintered titanium alloy member by bonding the material together and uniformly diffusing nitrogen in solid solution from the nitrogen-containing raw material to the entire interior portion of the sintered titanium alloy member, hot plastic forming and/or heat treating the sintered titanium alloy member to obtain a processed member, and surface treating the processed member to provide compressive residual stress.

Abstract: The present invention provides a process of initiating a self-propagating reaction with a coherent radiation source, which comprises mixing the chemical reactants, and contacting the chemical reactants by the coherent radiation, more specifically, the coherent radiation source may be a laser.

Abstract: The object of the present invention is to provide a heat-resistant steel for exhaust valves, having relatively small Ni content, high mechanical characteristics (for example, tensile strength, fatigue strength, wear resistance and hardness) at high temperature, and excellent oxidation resistance. The present invention provides a heat-resistant steel for exhaust valves, which includes: 0.45?C<0.60 mass %, 0.30<N<0.50 mass %, 19.0?Cr<23.0 mass %, 5.0?Ni<9.0 mass %, 8.5?Mn<10.0 mass %, 2.5?Mo<4.0 mass %, 0.01?Si<0.50 mass %, and 0.01?Nb<0.30 mass %, with the balance being Fe and unavoidable impurities, in which the steel satisfies 0.02?Nb/C<0.70 and satisfies 4.5?Mo/C<8.9.

Abstract: Provided is duplex stainless steel having high strength, SCC resistance and SSC resistance excellent in a high-temperature chloride environment, and capable of suppressing precipitation of a ? phase. The duplex stainless steel of the present embodiment includes, in mass %, of: C: at most 0.03%; Si: 0.2 to 1%; Mn: more than 5.0% to at most 10%; P: at most 0.040%; S: at most 0.010%; Ni: 4.5 to 8%; sol. Al: at most 0.040%; N: more than 0.2% to at most 0.4%; Cr: 24 to 29%; Mo: 0.5 to less than 1.5%; Cu: 1.5 to 3.5%; W: 0.05 to 0.2%; the balance being Fe and impurities, wherein the duplex stainless steel satisfies Formula (1): Cr+8Ni+Cu+Mo+W/2?65 . . . (1), where a symbol of each element in Formula (1) represents a content of the element (in mass %).

Abstract: The present invention relates to a multilayer overlay welding section in which a first layer of an overlay welding section to be formed on the bearing contact surface of a high Cr steel turbine rotor includes C: 0.05 to 0.2%, Si: 0.1 to 1.0%, Mn: 0.3 to 1.5%, Cr: 4.0 to 7.7%, and Mo: 0.5 to 1.5% with a remainder including Fe and unavoidable impurities, a multilayer overlay welding section in which, in addition to the above layer, an upper layer welding section includes C: 0.05 to 0.2%, Si: 0.1 to 1.0%, Mn: 0.3 to 2.5%, Cr: 1.0 to 4.0%, and Mo: 0.5 to 1.5%, and a welding material therefor and a process for producing the multilayer overlay welding section.

Abstract: Provided by the present invention are a fine crystallite high-function metal alloy member, a method for manufacturing the same, and a business development method thereof, in which a crystallite of a metal alloy including a high-purity metal alloy whose crystal lattice is a face-centered cubic lattice, a body-centered cubic lattice, or a close-packed hexagonal lattice is made fine with the size in the level of nanometers (10?9 m to 10?6 m) and micrometers (10?6 m to 10?3 m), and the form thereof is adjusted, thereby remedying drawbacks thereof and enhancing various characteristics without losing superior characteristics owned by the alloy.