Abstract: In a turbine housing 12 of a turbocharger 10A of a twin-scroll type, a scroll-shaped passage is separated into a front scroll passage 42 and a rear scroll passage 44 by a partition wall 40. A front wall 50 and a root part 40b of the partition wall 40 curve toward a front side to secure cross-sectional areas a1, a2, a3 . . . and b1, b2, b3 . . . . The scroll passages 42, 44 are formed to have equal cross-sectional areas, a tip part 40a of the partition wall 40 is arranged perpendicular to the turbine rotor blade 26 and the scroll passages 42, 44 are symmetrical near the tip part 40a about an axis X so as to eliminate the flow rate difference.

Abstract: Several embodiments of a wobble plate motor include a disc mounted on a bent shaft. Driving the wobble plate so it revolves on a flat base causes the bent shaft to rotate and drive a generator or other work consumer. The wobble plate may be driven by a fluid stream impinging on the plate or by a blade assembly in a path of fluid movement. In one embodiment of a bladed motor, a shroud may direct the fluid stream so it more efficiently cooperates with the blade assembly.

Abstract: A fan rotor including a disk carrying blades including roots engaged in slots in the disk, a frustoconical cap mounted on the disk upstream from the blades, and a retaining mechanism axially retaining the blades on the disk and including a ring mounted in an annular groove of the disk and forming an abutment for the roots of the blades, the ring being festooned or crenellated and co-operating with a festooned radial annular bead of the annular groove of the disk, and a mechanism preventing the ring from moving in rotation, which includes an annulus carrying at least one axial tooth inserted in hollow portions of the bead of the disk and of the ring, the annulus being fastened by bolts on an upstream radial face of the disk.

Abstract: Embodiments of a turboshaft engine are provided, as are embodiments of a method for manufacturing a turboshaft engine. In one embodiment, the turboshaft engine includes an Inlet Particle Separator (IPS) system having an IPS scavenge flow circuit fluidly coupled to the engine's inlet section. A heat exchanger and a heat exchanger bypass duct are fluidly coupled to the IPS scavenge flow circuit. The heat exchanger bypass duct is configured to direct airflow around the heat exchanger. A particle separation device, such as an IPS blower, is fluidly coupled in series with the heat exchanger in the IPS scavenge flow circuit. The particle separation device is positioned to direct particulate matter entrained within the airflow through the IPS scavenge flow circuit into an inlet of the heat exchanger bypass duct and thereby reduce the amount of particulate matter ingested by the heat exchanger during operation of the turboshaft engine.

Abstract: A rotary energy generating device includes an output shaft, a rotor coupled to the output shaft, and a plurality of paddles coupled to the rotor, with each paddle being moved between vertical and horizontal positions as the rotor is rotated. A chamber housing includes inlet and output pairs. A respective open chamber area is defined between each inlet and outlet pair based on a given rotation direction of the rotor, with each respective open chamber area configured to receive the paddles in the vertical position as the rotor rotates in the given rotation direction. A respective slotted chamber area is defined between each outlet and inlet pair based on the given rotation direction of the rotor, with each respective slotted chamber area configured to receive the paddles in the horizontal position as the rotor rotates in the given rotation direction.

Abstract: A method of increasing wear resistance of one or more part(s) of a rotating mechanism includes manufacturing the one or more part(s) with a portion thereof configured to be exposed to wear during fluid flow associated with the rotating mechanism having a dimension different from that of a desired dimension, applying a protective coating of an aluminum bronze alloy to the portion through welding deposition, and mechanically treating the protective coating. The method also includes applying one or more layer(s) of solid-alloy over the protective coating through electro-erosion deposition, and continuing the mechanical treatment of the protective coating and/or the one or more layer(s) of solid-alloy after the solid-alloy deposition to obtain the desired dimension of the portion.

Abstract: A turbine bucket having an airfoil is disclosed. The airfoil may include a pressure side and a suction side extending between a leading edge and a trailing edge. In addition, the airfoil may include a tip. The tip may include a tip floor and a tip wall extending outwardly from the tip floor. The tip wall may include an inner surface defining an inner perimeter of the tip wall. Moreover, a plurality of notches may be defined by the inner surface around at least a portion of the inner perimeter.

Abstract: A device for converting the kinetic energy of molecules into useful work includes an actuator configured to move within a fluid or gas due to collisions with the molecules of the fluid or gas. The actuator has dimensions that subject it to the Brownian motion of the surrounding molecules. The actuator utilizes objects having multiple surfaces where the different surfaces result in differing coefficients of restitution. The Brownian motion of surrounding molecules produce molecular impacts with the surfaces. Each surface then experiences relative differences in transferred energy from the kinetic collisions. The sum effect of the collisions produces net velocity in a desired direction. The controlled motion can be utilized in a variety of manners to perform work, such as generating electricity or transporting materials.

Abstract: In a compressor housing, a scroll piece includes a cylindrical intake port forming section, a scroll wall surface forming section that forms an air-intake side wall surface of a discharge scroll chamber, and a scroll outer circumferential section that covers an outer circumferential side of the discharge scroll chamber. A shroud piece of the housing includes a cylindrical shroud press fitted section press fitted into the intake port forming section, and a shroud wall surface forming section that forms an inner circumferential side wall surface of the discharge scroll chamber and also forms a shroud surface that opposes an impeller and a diffuser surface. An outer circumferential annular piece of the housing includes an outer circumferential annular press fitted section press fitted inside the scroll outer circumferential section, and an outer circumferential annular wall surface forming section that forms an outer circumferential side wall surface of the discharge scroll chamber.

Abstract: A blade for a blade row of a turbomachine having wired sections, in particular a blade of a compressor rotor blade, as well as a method for wiring sections of such a blade, is disclosed. Sections of a blade are wired in such a way that a first central component of a second section is selected according to at least one central component of a first section.

Abstract: A pump intake device comprises a main body which includes a side wall section having an inner side and an outer side, an intake section extending from the outer side of the side wall section and an intake passage extending through the intake section, the intake passage having an inner surface and an entry end and an exit end with a central axis extending between the entry and exit ends, where a first portion of the inner surface has one or more first guides thereon for directing fluid passing through the intake passage so that, in use, the fluid leaves the exit end at the first portion with an exit angle which is inclined relative to the central axis.

Abstract: A gas turbine engine and a method of tuning a rotor in the gas turbine engine wherein the rotor includes an array of blades extending from a rotor hub each having an airfoil mounted to a blade platform. The method includes adding or removing material from bladed rotor projections to alter the mass of the rotor and change the frequency of the respective airfoil.

Abstract: A seal assembly for a rotary machine which includes a rotor assembly having a rotatable rotor shaft is disclosed. The seal assembly may comprise a spacer, a seal plate, a ring seal, and a ring seal midplate. The spacer, the seal plate, and the ring seal midplate may be rotatable with the shaft and extend outwardly from the shaft. The ring seal is free and provides a seal for a bearing compartment of the rotary machine. The ring seal midplate is not attached to the spacer or the seal plate during a hardface process which is applied to any component of the seal assembly. The ring seal midplate may be longitudinally located between the spacer and the seal plate and be radially spaced between the ring seal and the shaft.

Abstract: An exemplary heat dissipating fan includes a frame and an impeller rotatably received in the frame. The frame includes a base and a top cover disposed on the base, the base includes a bottom plate a peripheral sidewall. The sidewall extends between the bottom plate and the top cover, and the base and the top cover cooperatively defines a receiving space. The impeller is rotatably received in the receiving space. The top cover, the bottom cover and the sidewall cooperatively define an air inlet therebetween. The top cover, the bottom plate and the sidewall cooperatively define an outlet therebetween. The air outlet is generally adjacent to and substantially perpendicular to the air inlet.

Abstract: A system for removing heat from a gas turbine generally includes a plurality of stationary nozzles arranged in an annular array within the gas turbine. Each of the plurality of stationary nozzles may include a radially outer platform and a radially extending cooling passage. The radially extending cooling passage may have an inlet that extends generally axially and circumferentially across a portion of the radially outer platform. A closed loop cooling coil may extend continuously circumferentially around the radially outer platform of two or more of the plurality of stationary nozzles. The closed loop cooling coil may be disposed circumferentially across and outside of the inlet of the radially extending cooling passage of each of the two or more stationary nozzles, and a cooling medium may flow through the cooling coil and out of the gas turbine so as to remove heat from the gas turbine.

Abstract: An aerofoil typically for a blade or vane for a gas turbine engine comprises a pressure wall and a suction wall, at least one of the pressure and suction walls comprise corrugations and a coolant hole on an inner surface, the corrugations define a downstream surface and the coolant hole having an inlet defined in the downstream surface.

Abstract: The present application provides a wet gas compression system for a wet gas flow having a number of liquid droplets therein. The wet gas compression system may include a pipe, a compressor in communication with the pipe, and a thermoacoustic resonator in communication with the pipe so as to break up the liquid droplets in the wet gas flow.

Abstract: An aerofoil typically for a blade or vane for a gas turbine engine comprises a pressure wall, a suction wall and a web that extends therebetween. One of the walls comprises an inner leaf and an outer leaf which defines a cavity, the other wall defines a first outlet, the aerofoil defines at least one first passage extending from the cavity through the web and to the outlet. Coolant in the cavity on one side wall of the aerofoil is thereby routed across the web to be used to cool the other wall by convention and formation of a coolant film.

Abstract: A turbine engine rotor assembly includes a turbine engine rotor disk that extends axially along a centerline between a first disk end and a second disk end, and radially to an outer disk surface. The rotor disk includes one or more blade retention slots arranged circumferentially around the centerline. A first of the blade retention slots extends axially into the rotor disk from a disk end surface at the first disk end to a slot end surface, and radially into the rotor disk from the outer disk surface to a slot base surface.

Abstract: Disclosed is a cross-flow fan where an inner diameter (d) and an outer diameter (D) of a fan blade meet the relationship expressed by 0.55?d/D?0.95. In cross-flow fan, (N) representing number of fan blades, a chord length (L) and outer diameter (D) of fan blades, and (M) representing number of blade wheels meet the relationships expressed by of 0.6?L/(?D/N)?2.8 and 0.15??D/(N×M)?3.77. A plurality of blade wheels are stacked on each other in a manner that a displacement angle (?) is generated within the range of (1.2×360°/(N×M))???(360°/N) between adjacent blade wheels. The displacement angle (?) is set so that the overlapping number of fan blades having an equal installation angle is at most 5% of N×M representing a total number of fan blades. The present invention can provide a cross-flow fan that can succeed in noise reduction, a molding die used to produce the cross-flow fan, and a fluid feeder equipped with the cross-flow fan.