Abstract: A turbo machine is provided. The turbo machine comprises a turbo stator having a shroud, a turbo rotor having an impeller within the shroud, a brush seal between the impeller and the shroud, and at least one vane extending from the shroud toward the impeller upstream of the brush seal.

Abstract: To make manifest the above noted desire, a revelation of the present invention is brought forth. A fan assembly (7) is provided including a hub (10) with a plurality of projecting fan blades (12). A recirculating flow element (18) is provided which is generally forward adjacent an outer diameter of the fan blades (12). A plurality of guide vanes (22) are positioned within the recirculating flow element (18). The guide vanes (22) have an inlet angle (24) that is nearly tangential with an outer diameter surface (15) of the recirculating flow element (18). The guide vanes (22) have an outlet angle (26) which is nearly radial along an inner diameter surface (17) of the recirculating flow element (18).

Abstract: A compressor diffuser for a gas turbine includes: a compressor diffuser having an upstream end and a downstream end, the downstream end defined by a peripheral annular edge, the annular edge formed with a plurality of substantially axially-oriented slots extending from an opening at the downstream edge in an upstream direction.

Abstract: An airfoil comprises pressure and suction surfaces extending axially from a leading edge to a trailing edge and radially from a root section to a tip section, defining a mean span therebetween. An inner endwall defines an inner endwall contour extending axially and circumferentially from the root section, and an outer endwall defines an outer endwall contour extending axially and circumferentially from the tip section. The inner and outer endwall contours are defined by varying radial deviations from circumferentially uniform nominal inner and outer radii, where one of the radial deviations varies axially and circumferentially by at least three percent of a mean span of the airfoil.

Abstract: The invention aims at achieving a mounting of a turbomachine stator blading while avoiding a delicate machining process of the engine casing. It also aims at simplifying the mounting as well as at reducing the costs, and at decreasing the number of item references for the engine. To achieve these objects, the invention uses an extension of the engine casing. A turbomachine comprises at least one stator blading for air or gas stream flowing on the internal engine casing. The stator blading comprises a rim which is assembled on a radial extension of engine casing with axial fastening means. In a preferred embodiment of the turbomachine, the engine casing presents an annular wall provided with fingers originating axially from this wall and extending according to a curvature so that they present a radial extension tip against the rim of the stator blading.

Abstract: A turbine engine airfoil structure including an airfoil adapted to extend across a gas passage, and a platform structure defining an endwall located at one end of the airfoil and positioned at a location forming a boundary of the gas passage. A saddle portion is associated with at least one airfoil surface of the airfoil, the saddle portion defining a contour having a first radially outer edge located on the at least one airfoil surface and a second radially inner edge located radially inwardly from the radially outer edge. The contour includes a curvature in a plane extending generally perpendicular to the at least one airfoil surface and passing through the saddle portion, the curvature being radially spaced from the endwall and defining an apex located between the radially outer and inner edges of the saddle portion.

Abstract: A power turbine employs a plurality of turbine blades which allows the turbine to regulate pressure and ventilate for a greater ability to generate power without back pressure of the power source. It also relieves much of the stress on the uni-body construction. The vent ports (30) work at various times to transfer pressure naturally from one compartment to another, greatly increasing the balance of pressure throughout the process within the turbine.

Abstract: A diffuser pipe (38) of a compressor diffuser assembly (28) for gas turbine engines defines a depressed local area (58) in the pipe wall of an upstream section of the diffuser pipe (38). The depressed local area (58) is bent into the diffuser pipe (38) to reduce the accumulation of fluid boundary layer and improve stall margin of the diffuser pipe (38).

Abstract: A bearing housing of a rotor shaft support assembly of a turbocharger core mounts to and closes a forward end of a cavity that both receives and discharges exhaust gases of an internal combustion engine. A turbine rotor operatively coupled to a rotor shaft and a compressor rotor of an associated turbocharger rotor assembly rotates within a turbine rotor shroud portion of an associated turbine nozzle cartridge assembly, wherein the rotor shaft is rotationally supported by at least one bearing within the bearing housing. The turbine nozzle cartridge assembly provides for directing exhaust gases from the cavity through a peripheral inlet leading to a plurality of vanes between forward and aft walls, through the turbine rotor shroud portion, and then through a nozzle exhaust portion incorporating an external sealing surface on an aft portion thereof that cooperates with a sealing element where the exhaust gases are discharged from the cavity.

Abstract: The present invention includes a pivotable vane having an airfoil with a vane spindle or stem extending toward a distal end thereof. The vane stem has a head with a pair of tapered flats having an outwardly extending angle as defined from the distal end of the head towards the airfoil. A vane arm having a substantially C-shaped connector with a pair of contact ends is constructed to maintain a gap with the tapered flats at an initial assembly step and positively engage the tapered flats at a final assembly step.

Abstract: A pedestal for a fan assembly includes a telescopic duct for conveying an air flow to an outlet of the fan assembly. The duct includes an outer tubular member having a first stop member, an inner tubular member located at least partially within and slidable relative to the outer tubular member, the inner tubular member having a second stop member for engaging the first stop member to inhibit withdrawal of the inner tubular member from the outer tubular member, and a mainspring rotatably mounted on the second stop member, the mainspring having a free end retained by the first stop member.

Abstract: A section of a gas turbine engine including a radial spoke is provided. The spoke includes an aerodynamic shape with a leading side and a trailing side and, extending from the leading side to the trailing side, a first side and a second side, opposite the first side. The spoke also includes at least one flow guiding element arranged on at least the first side.

Abstract: A pump, in particular a centrifugal pump, includes at least one flow-leading part with an at least regional surface layer (50) of an elastomer. The flow-leading part with the surface layer (50) is formed as a multi-component injection molded part, with a base structure (55) made of plastic as a first component, and with the elastomer as a second component.

Abstract: A stator for installation in a rear section of a jet engine includes a plurality of guide vanes which extend in the radial direction of the stator and between them define ducts for leading a gas. A first side of the stator in its axial direction defines an inlet for the gas and a second side, opposite the first side, defines an outlet for the gas. The guide vanes have such a shape that together they at least substantially cover the gas inlet viewed in the axial direction of the stator from the outlet side thereof.

Abstract: A gas turbine engine compressor has a compressor case comprising spaced apart inner and outer walls. An axial rotor is positioned within the outer wall. A bearing structure supports the axial rotor for rotation. A plurality of inlet guide vanes are coupled to the outer wall of the compressor case and radially extend inwardly, wherein each of at least a sub-set of said inlet guide vanes comprises a radial bore. Nested tie rods are received within a respective one of the inlet guide vane radial bores. Each tie rod comprises an outward end attached to the compressor case outer wall and an inward end attached to the compressor case inner wall.

Abstract: Systems and methods for maneuvering an underwater vehicle by generating vehicle maneuvering forces from a propulsor of the vehicle are provided. A ducted, pre-swirl propulsor is configured such that the pitch angles of the stator blades of the upstream stator row can be varied. By varying the pitch angles of the stator blades about the circumference, a mean stator side force is generated. Subsequently, the axial velocity and swirl that is ingested into the inflow is varied. The rotor of the propulsor then generates a side force in response to the inflow.

Abstract: A ducted fan for a helicopter includes a transverse duct and a counter-torque device supported within the duct. The counter-torque device includes a rotor rotatably mounted within the duct and a stator fixedly mounted within the duct downstream from the rotor. The rotor includes a rotor hub having a rotor axis, and rotor blades extending from the hub. The Rotor blades have a modulated angular distribution about the rotor axis. The stator includes a stator hub, and a plurality of stator vanes distributed around the stator hub. The stator vanes are angularly modulated around the stator hub.

Abstract: Axial flow action turbine utilizing the energy of water entering axially and tangentially into a turbine runner with cylindrical hub equipped with radial oriented buckets having cross-section consisting of segments of cylindrical tube where the segments are angularly offset along the bucket's radial axis and where the water exits the turbine runner axially.

Abstract: A turbine rotor, e.g., for a drive turbine of a rotary atomizer, is disclosed having a rotatably supported turbine shaft with the potential for mounting an atomizer wheel, and having at least one drive turbine wheel having a plurality of turbine blades. The turbine blades of the drive turbine wheel may be impinged on during operation by a drive fluid in order to drive the turbine rotor. The drive turbine wheel may be designed for the drive fluid to axially impinge on the turbine blades. A complete drive turbine having such a turbine rotor is also disclosed, as well as a complete rotary atomizer and individual exemplary components of the drive turbine.

Abstract: The present invention relates to a turbine which can absorb energy from bi-directional reversing flows, as is the case of ocean wave energy converters. In the periphery of the bladed rotor (2) of the turbine there are two openings (5, 6) through which the fluid alternately enters, or exits from, the rotor, the outward flow being radially centrifugal and the inward flow being radially centripetal. The turbine stator comprises two sets of guide vanes (7, 8) for alternately directing the bi-directional reversing flow to, and from, the rotor, and two ducts (9, 12) disposed between the rotor and the guide vanes and extending radially beyond the guide vanes. Two stator arrangements are considered. In both arrangements, the inlet guide vanes deflect the inward flow and impart a circumferential swirl component in the same direction as the normal rotational direction of the rotor.

Abstract: A rotor wheel is provided and includes a body having first and second opposing faces and portions recessed from a plane of the first face to define therein an annular groove and a plurality of tributary grooves, the annular groove being receptive of fluid from an external source and formed to direct the fluid to flow along an annular flow path, and the plurality of tributary grooves being receptive of the fluid from the annular groove and respectively formed to direct the fluid to flow sequentially along radial and axial tributary flow paths while preventing inter-tributary groove fluid communication.

Abstract: A stator for a turbine includes an arrangement of vanes including at least a first vane and a second vane circumferentially neighbouring the first vane. Each of the first vane and the second vane include: an airfoil; a channel system configured to cool the respective vane with cooling gas; and an inner diameter platform disposed at an inner end of the airfoil, the inner diameter platform including an inner diameter platform cavity and a circumferentially arranged side wall which delimits the inner diameter platform cavity, the inner diameter platform cavity being connected with the channel system so as to feed the cooling gas to the inner diameter platform. At least one sealing plate is disposed between the circumferentially arranged side walls of the first vane and the second vane so as to form an intermediate cavity that is fluidically separated from the inner diameter platform cavities.

Abstract: A cooling fan includes an impeller which comprises a plurality of radially extending blades, each of which includes a blade hub, a blade tip and a blade midspan approximately midway between the hub and the tip. In addition, each blade includes a camber of between about 60° and 90° at the blade hub, between about 15° and 40° at the blade midspan and between about 15° and 40° at the blade tip.

Abstract: A trans cowl for a jet engine includes a chevron coupled with a linear actuators. The chevron is movable by the linear actuator forward or aft to change a gas flow path formed by an core cowl and thrust reverser translating cowl. In a first position, the chevrons are disposed substantially parallel the gas flow path to attenuate drag and/or loss of engine thrust. In a second position, the chevrons are moved aft to project, or further project, into the gas flow path. In one embodiment, the linear actuator comprises a first component that is coupled with the outer cowl. A second component of the linear actuator is coupled with the chevron. When installed, the linear actuator can be coupled with a controller and an electrical power source. A position sensor coupled with the controller senses a position of the linear actuator and/or the chevron.

Abstract: The invention relates to a compressor, particularly a high pressure compressor, of a gas turbine, particularly of a gas turbine aircraft engine, having at least one rotating blade ring on the rotor side, and having at least one guide blade ring on the stator side, wherein the, or each, guide blade ring is formed of a plurality of guide blade segments, and wherein each guide blade segment is formed of a plurality of individual blades. According to the invention, adjacent individual blades (11, 12; 12, 13; 13, 14) are permanently connected to each other within each guide blade segment (10) of at least one guide blade ring on opposing surfaces positioned radially outward, whereas the same are not connected to each other on opposing surfaces positioned radially inward.

Abstract: An outlet guide vane assembly for turbomachines is provided. The outlet guide vane assembly comprises one or more outlet guide vanes, wherein each of the one or more outlet guide vanes comprises a first surface and a second surface, and wherein the one or more outlet guide vanes are disposed between an inner wall and an outer wall of an engine and a surface cooler layer disposed on at least a portion of the first surface, the second surface, or both of the one or more outlet guide vanes, wherein the surface cooler layer comprises a metal foam, a carbon foam, or a combination thereof, wherein the metal foam, the carbon foam or the combination thereof is configured to augment heat transfer and enhance acoustic absorption.

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 ram air turbine comprises a turbine housing which mounts a number of circumferentially spaced turbine blades that function predominantly as impulse turbine blades and a number of splitters, each located in between adjacent turbine blades, which function predominantly as a reaction turbine blade but are shorter in length than the turbine blades. The cross section of the turbine housing decreases between its forward and aft ends while the height of both the turbine blades and splitters increases in the same direction such that the tips of the turbine blades and splitters collectively form a substantially cylindrical shape.

Abstract: A motor-fan unit includes an end plate assembly, a motor assembly supported by the end plate assembly, and a shaft rotated by the motor assembly and extending through the end plate assembly. The fan assembly further includes a discharge shell, a tapered stationary fan which has a concave underside, and a rotating fan secured to the rotatable shaft and disposed between the discharge shell and the stationary fan. The tapered stationary fan includes a fan side which is substantially parallel and aligned with the frusto-conical shape of the fan disc of the rotating fan. A tapered fan shell is supported by the discharge shell and held in place by the stationary fan. A fan shroud secures the stationary fan and the fan shell to the discharge shell to prevent damage to a rotating fan secured to the shaft and positioned between the fan shroud and the stationary fan.

Abstract: A motor-fan unit includes an end plate assembly, a motor assembly supported by the end plate assembly, and a shaft rotated by the motor assembly and extending through the end plate assembly. The fan assembly further includes a fan secured to the rotatable shaft which is supported by the end plate assembly. The fan includes a fan disc having a substantially frusto-conical shape, a fan ring having a substantially frusto-conical shape, and a plurality of vanes connecting the fan disc to the fan ring such that the frusto-conical shapes are substantially parallel to one another. A diffuser with a tapered fan side is also provided between the fan and the end plate assembly, wherein the tapered fan side is substantially parallel with the fan disc.

Abstract: To reduce secondary flow loss and to improved turbine efficiency, a section located radially outward of a border section 28 of a stationary blade 21 is bent in the rotational direction of a rotor. Thus, even if combustion gas leaks from a tip clearance between an end wall of a casing and a tip portion of a rotor blade, and a stagnation line 35 near a tip portion 22 is situated in the side of a back surface 24, because a section located radially outward of the border section 28 is bent in the rotational direction of the rotor, the stagnation line 35 is also situated toward the rotational direction of the rotor. Therefore, the stagnation lines 35 formed at various heights in the heightwise direction of the stationary blade 21 are generally aligned in the rotational direction of the rotor. Thus, fluctuation of pressure distribution in the heightwise direction of the stationary blade 21, of the combustion gas flowing into the stationary blade 21 can be reduced.

Abstract: A flow-routing component of a pump is composed of at least two parts, a first part (2) of the component being manufactured by metal-powder injection molding, and a second part (4) of the component being manufactured from sheet metal. A pump assembly is also provided having such a flow-routing component.

Abstract: A diffuser apparatus in a turbomachine is provided comprising a diffuser structure and stabilizing structure. The diffuser structure includes inner and outer walls defining a flow passageway through which gases flow and diffuse such that kinetic energy is reduced and pressure is increased in the gases as they move through the passageway. The stabilizing structure stabilizes a separated gas recirculation zone.

Abstract: A compressor assembly for a gas turbine engine includes rotatable impeller with forward and aft ends, including: an annular hub defining a generally concave-curved cross-sectional inner flowpath surface at its radially outer periphery, the inner flowpath surface extending between an inlet and an exit; an annular array of airfoil-shaped inducer blades extending radially outward from the inner flowpath surface near the forward end; and an annular array of exducer blades extending outward from the inner flowpath surface, the array of exducer blades axially spaced apart from the array of inducer blades; a non-rotating shroud assembly surrounding the impeller and including a convex-curved outer flowpath surface, wherein the inner and outer flowpath surfaces cooperate to define a primary flowpath past the blades and the stator vanes; and an annular array of airfoil-shaped stator vanes extending radially inward from the outer flowpath surface into a space between the inducer and exducer blades.

Abstract: Disclosed herein is a turbine variable position guide vane actuation system. The system includes, a plurality of variable position guide vanes, a plurality of actuators with each actuator in operable communication with one of the plurality of variable position guide vanes, and each of the plurality of actuators having a pin. The system further having at least one structure, movable parallel to an axis of the turbine, having a plurality of slots and each of the plurality of slots is in operable communication with one of the pins.

Abstract: The invention provides a blower system of a high performance, which is constructed to have stabilized characteristics, a high efficiency, a reduced thickness and a reduced noise. A blower system according to the invention includes an impeller, a motor for rotating the impeller and having a rotor and a stator, and a bell-mouth for supplying air to an intake port in the impeller, wherein the rotor is fixed to the impeller, and the stator is fixed to the bell-mouth. A gap between the impeller and the bell-mouth is composed of a gap between the rotor and the stator of the motor. Alternatively, the rotor is fixed to the impeller, and the stator is fixed to a fitting for mounting a housing of the blower system or the blower system.

Abstract: The present invention relates to a stator of an axial compressor stage of a turbomachine featuring a radially outer blade ring forming an outer ring surface, a radially inner blade ring forming an inner ring surface, and several stator blades connected to the blade rings. It is provided that the outer ring surface and/or the inner ring surface has at least in a partial area a changing radius relative to a central axis of the stator both in the axial direction and in the circumferential direction.

Abstract: A stator for a turbomachine. The stator includes a plurality of nozzle vanes, with the distance between each of the plurality of nozzle vanes varying circumferentially around the stator in a repeating pattern configured to distribute a vibration energy over a plurality of side band vibration frequencies around a nominal passing frequency in a rotor.

Abstract: A stator vane for a compressor is described. The stator vane has an airfoil root, an airfoil tip, a leading edge, a trailing edge, an inner span region, a midspan region and an outer span region, wherein the stator vane has a normalized camber profile that increases in the outer span region in a spanwise direction towards the tip and is more than 1.4 in the outer span region.

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

Abstract: A flow-guiding device for an impeller radial pump is arranged radially outside the impeller and extends in a ring-shaped manner with a circumferential carrier ring on which several guide blades are arranged. These latter are formed so as to be resilient in such a manner that when there is a small fluid flow a blade angle points more in the radial direction at an angle of approximately 70° with respect to the longitudinal center axis of the pump. When there is strong fluid flow, the angle becomes smaller and the guide blades bend in a resilient manner at least in regions such that they stand at a smaller angle of between 30° and 40° with respect to the longitudinal center axis of the pump. The fluid is conveyed better in the pump chamber in this way.

Abstract: A high drag vortex generator for inhibiting the formation of boundary layer gas flow is mounted in a duct having a strong adverse pressure gradient with high speed gas flow over a primary aerodynamic. The vortex generator includes a mounting for supporting the high drag vortex generator at a spatial interval in the high speed gas flow above the primary aerodynamic surface. The high drag vortex generator is supported from the mounting and extends from the mounting in the high speed gas flow less than the full distance to the primary aerodynamic surface. Each high drag vortex generator includes first and second vanes. The first and second vanes have flow confining components at substantial right angles to one another. The vanes flow confining components deflect fluid flow towards and/or away from the primary aerodynamic surface inhibiting boundary layer formation downstream of the vortex generator.

Abstract: In a blade row of an axial flow type compressor in which a rotor blade row and a stator blade row are alternately arranged in an axial direction, the stator blade row 10 is formed by plural main stator blades 12 and plural sub-stator blades 14. Each main stator blade 12 is formed by a basic blade portion 12a which has the same shape as that of each sub-stator blade and a forward blade portion 12b which extends to the upstream side of the basic blade portion. The basic blade portion 12a are located at the same position in an axial direction. The forward blade portion 12b forms a forward stator blade row which has a circumferential interval larger than that of the basic stator blade row in the vicinity of at least a radial inner end.

Abstract: A portable fluid blower with a housing having a central axis and defining a fluid flow path extending axially between an upstream inlet and a downstream outlet. A fan assembly has a rotary component that is operable to draw fluid into a first stage of the flow path and accelerate fluid incoming at the inlet radially outwardly to against a first housing surface portion that diverts the fluid to a second stage of the flow path. The second flow path stage is defined by facing second and third housing surface portions that cause the fluid to flow substantially fully axially in an annular space extending around the central axis between the first stage and a third stage. The fluid flows from the third stage to and through the downstream outlet.

Abstract: A hybrid gas compressor has at least one rotor and shroud which define a compressor gas path extending from an inlet to an outlet. The compressor includes at least two compression stages and one diffusion stage between the inlet and outlet, the compression stages including respective circumferential arrays of blades extending from the rotor and the diffusion stage including a circumferential array of vanes between the compression stages. Blade aerodynamic loadings may be controlled, particularly in the last stage, to provide desired compression characteristics across the compressor. A bleed outlet is optionally located between the inlet and outlet for bleeding from the gas path.

Abstract: A turbomachine including a variable-pitch stator vane stage is disclosed. A control ring that is coaxial around the casing includes two segments that are assembled together by side connection straps fastened on either side of the segments with mutual insetting and in the vicinity of the ends of the segments.

Abstract: A variable vane arm has a hook portion comprising a radially inner leg connected to a radially outer leg by an arcuate connection, and an actuation lever extending from the hook portion. The hook portion and actuation lever are formed from a singular piece of material.

Abstract: A groove 50 formed in each stator ring segment piece 41 is formed to have side wall portions 50b on opposite sides inclined with respect to a bottom 50a so that a width of the groove 50 gradually decreases from an outer peripheral side toward the bottom 50a. A coupling member 42 has a sectional shape so as to have a maximum width at protrusions 42b at an intermediate portion in a thickness direction. The protrusions 42b on the opposite sides abut against or approach the side wall portions 50b of the groove 50 when the coupling member 42 is placed in the groove 50, a space 100 is formed on the side of the bottom 50a of the groove 50, and a welding groove 200 having a substantially V-shaped section is formed on the side remote from the bottom 50a of the groove 50.

Abstract: A gas turbine engine rotor drum includes spaced apart discs providing a cavity between the discs. The discs are configured to rotate in a rotational direction about an axis. An annular support is mounted on at least one of the discs and within the cavity. A cascade of relatively short anti-vortex members is mounted circumferentially on the annular support. The anti-vortex members include an outer end having a concave surface extending within the cavity radially outward from the annular support. The concave surface faces the rotational direction and promotes swirl as the rotor drum rotates.

Abstract: In a guide vane element for a gas turbine with a vane blade extending between a platform that is located radially inward in relation to the main housing of the gas turbine and a radially outward platform, a flange is provided on at least one edge of the platforms adjoining an adjacent second guide vane element in the circumferential direction and on the side of the platform facing away from the vane blade. The second guide vane element can be attached, via a second flange provided on a second platform on the second guide vane element. The connection of the platforms forms a cover band, or a connection between the guide vane elements that is tight, flush, and stress-free at different temperatures.