Abstract: An outlet guide vane system is disclosed for axial flow fans. Construction details are described which reduce losses in the end wall regions of the vanes, particularly for axial flow fans operating at low flow coefficient with strong localized swirl associated with upstream rotor tip clearance flows. In the preferred embodiment, the vane spanwise airfoil stacking line is approximately straight, while leaning circumferentially toward the incoming swirl flow over the majority of the radial span. The stacking line then curves abruptly in the opposite direction over the radially outboard spanwise portion, so as to lean away from the incoming swirl at the vane tip station. The radially outboard portion of the vanes simultaneously include a gradual increase in vane stagger angle, vane camber angle and vane chord. The vane may also include an axial sweep component.

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 system for controlling at least two variable-geometry equipments of a gas turbine engine is disclosed. The engine includes at least a first core rotating at a first speed and a second core rotating at a second speed. The first equipment includes at least one variable-pitch stator blade of a compressor of the first core and the second equipment includes at least one air bleed valve of a compressor of the second engine core moving between an open position at idle speed and a closed position at high speed. The system includes an actuator which actuates both equipments.

Abstract: A system for controlling at least two variable-geometry equipments of a turbomachine, in which the first equipment is a variable pitch stator blade stage of a compressor of a first core moving between a closed position at idle speed and an open position at high speed, and the second equipment is at least one bleed valve of a compressor of a second core moving between an open position at idle speed and a closed position at high speed, is disclosed. The actuator operates over a portion of its travel a first branch of an angle transmission member which actuates the first equipment and leaves this branch at rest on an abutment over the rest of its travel. The actuator operates the second equipment via a sliding junction member arranging a free travel in the actuation of said second equipment.

Abstract: A row of stator blades in a compressor of a combustion turbine engine, the combustion turbine engine including a diffuser located downstream of the compressor, and the row of stator blades disposed in close proximity to the diffuser; the row of stator blades comprising: a plurality of stator blades that include at least one of an inboard forward notch and an outboard forward notch.

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: A shroud for a wind turbine and a method for modifying performance of a wind turbine are disclosed. The wind turbine includes a rotor mounted to a nacelle, the rotor including a plurality of rotor blades and defining an outer diameter. The shroud is positioned downstream of the rotor in an air flow direction, and has an inner diameter of less than the outer diameter of the rotor.

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 centrifugal fan device includes a diverting member the height of which is lower than the height of an interior wall surface of a casing. The diverting member diverts the air flowing to an air outlet into a centrifugal fan side and a side wall side of the diverting member and also diverts the air flowing to the air outlet into a first cover side and a second cover side of the diverting member. As a result, the amount of air blown from the air outlet is dispersed uniformly over the entire area of the air outlet, and a deviation in the amount of air blown out of the air outlet is reduced.

Abstract: A fan assembly for creating an air current includes a nozzle mounted on a base. The base comprises an outer casing, an impeller housing located within the outer casing, the impeller housing having an air inlet and an air outlet, an impeller located within the impeller housing and a motor for driving the impeller to create an air flow through the impeller housing. The nozzle includes an interior passage for receiving the air flow from the air outlet of the impeller housing and a mouth through which the air flow is emitted from the fan assembly.

Abstract: An in-pipe hydraulic turbine system includes a pipeline for fluid transport, the pipeline having an inlet and an outlet, and a turbine disposed within the pipeline, between the inlet and the outlet. The turbine is actuated by fluid moving through the pipeline and leaves usable fluid pressure downstream of the turbine.

Abstract: A compressor scroll is provided for redirecting an airflow from a compressor. The compressor scroll includes a spiral-shaped body; a radial inlet formed in the body for receiving the airflow from the compressor as inlet airflow; and an outlet formed in the body such that inlet airflow flows through the body and exits the outlet as outlet airflow, with at least a portion of the outlet airflow crossing at least a portion of the inlet airflow.

Abstract: A compression stage having a plurality of stator vanes and rotor blades coaxial with a longitudinal centerline axis, each stator vane having an exit swirl angle distribution such that the exit swirl angle has a maximum value at an intermediate radius location and each rotor blade having a blade leading edge adapted to receive the flow from the stator vanes with the exit swirl angle distribution profile.

Abstract: A multistage centrifugal compressor includes a rotary shaft, and multistage impellers attached to the rotary shaft. Each of the impellers includes a hub, a shroud and blades therebetween in a radial cascade arrangement. An annular suction passage for guiding the fluid flow from the inward radial direction to a blade inlet is disposed upstream of the centrifugal impeller. A diffuser is disposed downstream of the centrifugal impeller. A bend portion is disposed downstream of the diffuser, and a return channel with a guide blade portion is disposed downstream of the bend portion. The annular suction passage at a hub side includes an axial parallel portion.

Abstract: A cooling fan having a fan housing, a motor which is positioned within the fan housing and a plurality of electronics components which are associated with the motor includes at least one strut which extends radially between the motor and the fan housing and on which the electronics components are mounted.

Abstract: The invention relates to a device suitable for vertical and horizontal transport of loads, in particular heavy loads, in good weather conditions, using the load-bearing capacity obtained by means of blowing a stream of air, produced by a generator, on two longitudinal lifting wings, substantially rectilinear, arranged symmetrically on either side of a supporting structure, to which the wings are connected.

Abstract: A blower includes an electric motor having a shaft, a housing having a housing inlet and a housing outlet between which is defined a flow path for gas, a first impeller having a plurality of blades adapted to accelerate gas tangentially and to direct it radially outward, and a stationary portion. The stationary portion includes a gas flow path defined between an external wall of the motor and a wall of the stationary portion, a first stationary vane structure located downstream of the first impeller, and a shield constructed and arranged to provide a barrier between the first stationary vane structure and the blades of the first impeller to isolate leading edges of the first stationary vane structure from an impeller blade pressure pulse. The flow path is of sufficient width to allow a flow of gas therethrough without introducing excessive pressure drop.

Abstract: In a multistage centrifugal compressor, a plurality of impellers is attached to the same rotary shaft. Vaned Diffusers and vaneless diffusers are used, as diffusers, for respective compressor stages configuring the compressor. The vaned diffusers are continuously used from the first compressor stage to the middle compressor stage, and the vaneless diffusers are used for the last compressor stage and the previous stage. While high efficiency is maintained at the compressor stages having the vaned diffusers, an operating flow range is secured at the compressor stages having the vaneless diffusers.

Abstract: A variable geometry compressor housing module has a housing (1) into which a diffuser plate (3), a unison ring (5) and vanes (7) supported by a backplate (9) are inserted. The backplate is fixed to the housing by a crimping process. An actuation mechanism (13) for actuating the vanes (7) is provided on an inlet side of the housing (1). Furthermore, a shroud groove is partly defined by the diffuser plate (3).

Abstract: Air moving device includes a housing, an impeller in the housing for generating a downward air flow, and vanes in the housing in close proximity to and a selected distance below the impeller to straighten the air flow. The device produces an air flow that substantially remains in a column over a substantial distance. The method includes producing an air flow that substantially remains in a column over a substantial distance and directing the air flow from the ceiling towards the floor to provide temperature destratification of the air in an enclosed space. The method also includes directing warm air from the ceiling to the floor and storing heat in the floor, apparatus on the floor and ground under the floor. The stored heat is released when the ceiling is cooler than the floor.

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 fan apparatus includes a casing and a fan unit. The casing is a hollow member having an inlet and an outlet. The fan unit has an inlet and an outlet, and includes a plurality of axial fans. The fan unit is disposed on the inside of the casing, and the inlet of the fan unit is disposed in the vicinity of the inlet of the casing. The position of the fan unit within the casing can be varied in order to alter the air flow and static pressure of the air discharged by the fan apparatus.

Abstract: A support frame includes a rail engaging a hook of a composite article having plys. The rail included a rail contact surface generally conformal to and contacting a hook contact surface of the hook. The rail and hook contact surfaces being substantially normal to the plys beneath the hook contact surface. One embodiment of the article is a composite nozzle segment including one or more airfoils extending radially between arcuate radially outer and inner band segments having plys curved about a centerline axis and the rail engages a hook of the radially inner band segment. The hook and the rail may be straight or arcuate. The frame includes a central body extending axially aftwardly from the rail to an aft frame flange. A frame pin may be mounted on the frame, engage the inner band segment or one of the airfoils, and may extend into a cavity in the airfoil.

Abstract: Rotodynamic machine for compressing a multiphase fluid comprising at least one gas phase and one liquid phase. The machine comprises at least one mobile wheel 6 rotating around an axis A-A?, mounted in a housing 1, and at least one fixed wheel 7 secured to housing 1. Mobile wheel 6 comprises a hub fitted with at least two blades 20 so as to form at least two channels delimited by hub 8, housing 1 and two of said blades 20. The channels have a centrifugal part. The length of one of the channels defined as the ratio of the volume of a channel to the maximum orthoradial area of said channel, measured in a plane perpendicular to the axis of rotation, ranges between 10 cm and 20 cm, and the ratio of the area of the largest orthoradial channel cross-section to the area of the smallest orthoradial channel cross-section is less than or equal to 3.

Abstract: An air diffuser system for an impeller for a centrifugal pump has least one channel (36) with first opening (40) through the backside (14) and a second opening (42) through the front side (38) of the impeller (12). Tubes (44) are associated with each channel (36) and extend from the backside (14) of the impeller (12). Tube ends (48) are oriented in the direction of rotation (46) of the impeller (12).

Abstract: An ultra-high power density wind turbine system for producing energy from a wind including a structure having a shape adapted to produce a positive wind pressure on a high-pressure portion of a surface that faces into the wind and to produce a vacuum on two low pressure portions of its surface and one or more shrouded wind turbine systems mounted in the structure and comprising turbine stator vanes, turbine rotor blades and a turbine discharge duct adapted to channel turbine exhaust to exit the structure at the two low-pressure portions of the structure surface. In preferred embodiments the structure is a vertical tower that is generally cylindrical and the turbine is a horizontal axis axial flow shrouded wind turbine.

Abstract: Disclosed is a turbo-molecular pump, which comprises a rotor including a first cylindrical body formed with a part of a plurality of rotating blades arranged in multistage, a second cylindrical body integrally connected to an outer peripheral region of a downstream end of the first cylindrical body and formed with the remaining rotating blades, and a stress-releasing protrusion extending from the downstream end of the first cylindrical body along a direction of a rotation axis of the rotor. The turbo-molecular pump of the present invention can reduce a stress in the downstream end of the first cylindrical body.

Abstract: Disclosed is a cross flow apparatus including a surface and at least one outlet located at the surface. The cross flow apparatus further includes at least one guide at the surface configured to direct an intersecting flow flowing across the surface and increase a velocity of a cross flow being expelled from the at least one outlet downstream from the at least one outlet.

Abstract: An apparatus for extending the effective exhaust gas path in order to allow gradual diffusion of the exhaust gases in a turboshaft engine wherein the engine includes an annular engine case with at least an exhaust gas duct having an axial component communicating with an annular duct with a substantially radial component and traversing the engine case, the apparatus comprising a collector plenum having a convex annular shape and a diameter larger than that of the engine case with at least one exhaust outlet defined in the plenum and wherein the annular duct extends into the plenum beyond the diameter of the engine case to extend the exhaust gas path.

Abstract: Provided is an exhaust scroll capable of reducing mixing loss caused by fluid swirling inside the exhaust scroll and fluid flowing thereinto, while collecting and discharging the fluid which has flowed. The exhaust scroll is provided with a scroll body (11) in which a space having a substantially annular cross section is formed and a connecting portion (12) which connects an exhaust passage (8) with the scroll body (11) to forcibly decelerate fluid (A) discharged from the exhaust passage (8), thereby allowing the fluid (A) to flow into the scroll body (11).

Abstract: A vacuum pump (100) comprises a pumping mechanism having an annular pumping chamber (112, 114, 116) extending about a longitudinal axis (107) and through which fluid is pumped by the pumping mechanism. A plenum (126) located remote from the pumping mechanism has an inlet (128) for receiving fluid to be pumped by the pumping mechanism and a plurality of outlets (132) arranged about the longitudinal axis (107) for supplying fluid to the annular chamber.

Abstract: An engine stage includes a row of airfoils joined to corresponding platforms to define flow passages therebetween. Each airfoil includes opposite pressure and suction sides and extends in chord between opposite leading and trailing edges. Extending from a surface of the platforms is a trailing edge ridge structure which adjoins the pressure sides, suction sides, and trailing edges of the airfoils with their respective platforms.

Abstract: A fan includes at least one fan frame, at least one impeller and at least one active flow-control device. The fan frame includes at least one air inlet and at least one air outlet. The impeller is disposed in the fan frame. The active flow-control device, is disposed on the fan frame for adjusting the size of the air inlet or the size of the air outlet according to demands.

Abstract: A composite nozzle segment includes one or more airfoils extending radially between arcuate radially outer and inner band segments having band plies curved about a centerline axis, an outer chordal seal line on an outer aft flange of the outer band segment, and thickened areas in corners of the outer aft flange along pressure and suction side edges of the outer band segment. The thickened areas may be thickest at the pressure and suction side edges and thinnest near a middle of the outer band segment. The thickened areas taper off from an aft end of the thickened area towards a forward flange of the outer band segment. Insert plies may be disposed between some of the band plies within the thickened areas may be grouped together in a discrete group or be interspersed with some of the band plies. The insert plies may have triangular shapes.

Abstract: An air distribution blower housing has an adjustable restriction in the interior of the blower housing. The adjustable restriction has the configuration of a rectangular plate. One edge of the plate is connected by a pivoting connection to an interior wall of the blower housing in the air flow path from the blower housing. The plate can be pivoted about the pivot connection through a plurality of adjusted angular positions of the plate in the air flow path. In each adjusted position of the plate, the length of the plate extends from the pivot connection in the air flow direction. A sliding connection is provided between the plate and at least one side wall of the blower housing. The sliding connection selectively holds the plate in its adjusted angular position and also provides a visual indication on the exterior of the blower housing of the adjusted angular position of the plate inside the blower housing.

Abstract: A turbine of a turbocharger having a floating insert which defines a nozzle for passing a fluid and that is supported axially slidable with respect to a housing by a sliding support. The turbine includes a gas shielding for preventing a flow of fluid from impinging on the sliding support.

Abstract: A vane cluster has a coated metallic substrate. The cluster includes a platform and a shroud. At least first and second airfoils extend between an outer face of the platform and an inner face of the shroud. Each airfoil has a pressure side and a suction side. The pressure side of the first airfoil faces the suction side of the second airfoil. The cluster includes a cooling passageway system including one or more first feed passageways in the first airfoil and one or more second feed passageways in the second airfoil. At least a first side selected from the pressure side of the first airfoil and the suction side of the second airfoil includes a first region with a local thinning or gap in the coating. Along the first side, the cooling passageway system includes means for locally cooling said first region.

Abstract: A diffuser for carrying air flow to an evaporator in an air conditioning system of an automotive vehicle includes an inlet and an outlet, a wall extending between the inlet and the outlet, and a guide vane, extending at least partially between the inlet and the outlet, spaced from the wall by a containing a control region whose area ratio changes along a length of the guide vane.

Abstract: A shroud for a wind turbine and a method for modifying performance of a wind turbine are disclosed. The wind turbine includes a rotor mounted to a nacelle, the rotor including a plurality of rotor blades and defining an outer diameter. The shroud is positioned downstream of the rotor in an air flow direction, and has an inner diameter of less than the outer diameter of the rotor.

Abstract: A method for increasing the total-to-static pressure ratio across a Ram Air Turbine (RAT) has designed and experimentally tested. The invention develops a localized accelerated flow of free-stream air near the discharge of the turbine rotor exhaust. This localized accelerated flow decreases the static pressure at the exit of the turbine and allows for additional power generation for a given free-stream flight condition. Full-scale wind tunnel experimenting testing shows that creating this low static pressure region behind the turbine resulted in significant increases in turbine output power when compared to a turbine that is not subjected to this invention. The invention showed the ability to increase the total-to-static pressure ratio across the turbine.

Abstract: The present application provides a diffuser for an exhaust hood of a steam turbine. The diffuser may include a first end adjacent to a last bucket and a second end downstream of a steam guide and adjacent to a bearing cone. An exhaust flow path extends therethrough. The second end may include an axial extension enlarging the exhaust flow path.

Abstract: A gas turbine engine includes a spool along an engine centerline axis which drives a gear train, said spool includes a low pressure compressor with four (4) stages.

Abstract: A diffuser is provided for an exhaust steam housing adjacent a last stage row of buckets fixed to a rotor in a steam turbine, each bucket in the last stage row of buckets having a platform portion and an airfoil portion. The diffuser includes an annular inner diffuser ring and an outer annular diffuser ring defining a flow path for steam exiting the last stage row of buckets in a substantially axial direction at a diffuser inlet and turning substantially ninety degrees to a diffuser outlet. A first portion of the inner annular ring extends in a downstream direction beyond the last stage row of buckets substantially parallel to a center axis of the rotor, the first portion having a length dimension in the downstream direction from a radial center line of the last stage row of buckets in a range of between 0.40 and about 0.70 of a center line radial length from the platform portion to a radially outer tip of any bucket in the last stage row of buckets.

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 one aspect, a method for assembling an outlet guide vane is provided. The method includes providing an outlet guide vane frame having a first side and a second side. The outlet guide vane includes a radially inward flange coupled to a radially outward flange by a leading edge. A trailing edge is coupled to the radially inward flange and the radially outward flange aft of the leading edge. A cavity is defined between the radially inward flange, the radially outward flange, the leading edge, and the trailing edge. A first and a second mating surface circumscribe the cavity on the first and second sides respectively. The method further includes coupling a filler portion within the cavity wherein the filler portion includes a third side and a fourth side, coupling a first skin to the third side and the first mating surface, and coupling a second skin to the fourth side and the second mating surface, wherein at least one of the first skin and the second skin are fabricated from a composite material.

Abstract: A fan includes an impeller rotatable about a rotation axis and having a plurality of rotating vanes, and a plurality of stationary vanes connecting an outer casing to a supporting body which supports a motor rotating the impeller. At least in a portion of each stationary vane in a radial direction, an axial distance between that stationary vane and one of the rotating vanes closest thereto and a slant angle of that stationary vane with respect to an axial direction increase as that stationary vane moves outwardly in the radial direction.

Abstract: An article of manufacture having a nominal profile substantially in accordance with Cartesian coordinate values of X, Y and Z set forth in TABLE A. X and Y are distances in inches which, when connected by smooth continuing arcs, define airfoil profile sections at each distance Z in inches. The profile sections at the Z distances can be joined smoothly with one another to form a complete airfoil shape.

Abstract: An extension of an intermediate casing for an aircraft jet engine, intended to project towards the downstream end from an external shell of said intermediate casing is disclosed. This extension includes an annular connecting downstream end forming an annular groove open radially towards the outside, intended to receive nacelle covers. The annular connecting downstream end is produced by a plurality of angular sectors.

Abstract: A two-stage high pressure turbine includes a second stage blade having an airfoil with a profile substantially in accordance with at least an intermediate portion of the Cartesian coordinate values of X, Y and Z set forth in Table 2. The X and Y values are distances, which when smoothly connected by an appropriate continuing curve, define airfoil profile sections at each distance Z. The profile sections at each distance Z are joined smoothly to one another to form a complete airfoil shape.