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 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 vane assembly of a gas turbine engine includes a plurality of circumferentially spaced vanes extending radially between an outer case and an inner case. A spring-tensioned stator restraining strap is provided around the outer case and surrounding outer ends of the respective vanes. The outer ends of the vanes are received in corresponding openings defined in the outer case and project radially outwardly from the outer case. The spring-tensioned strap compresses the respective vanes radially and inwardly in position.

Abstract: A sealing apparatus in a gas turbine. The sealing apparatus includes a seal housing apparatus coupled to a disc/rotor assembly so as to be rotatable therewith during operation of the gas turbine. The seal housing apparatus comprises a base member, a first leg portion, a second leg portion, and spanning structure. The base member extends generally axially between forward and aft rows of rotatable blades and is positioned adjacent to a row of stationary vanes. The first leg portion extends radially inwardly from the base member and is coupled to the disc/rotor assembly. The second leg portion is axially spaced from the first leg portion, extends radially inwardly from the base member, and is coupled to the disc/rotor assembly. The spanning structure extends between and is rigidly coupled to each of the base member, the first leg portion, and the second leg portion.

Abstract: A fan module and server equipment are provided that can achieve a balance between increased airflow and noise reduction when an axial flow fan is mounted in the server equipment. The fan module for taking in and discharging air includes a stator located on an upstream side with respect to airflow and an axial flow fan located on the downstream side. When the fan module is viewed from the rotational-axial direction of the axial flow fan, if a leading edge of a rotor vane constituting part of the axial flow fan passes a trailing edge of a stator vane constituting part of the rotor, a skew is formed in which the leading edge of the rotor vane constantly intersects the leading edge of the rotor vane at a single point.

Abstract: A gas turbine includes forward and aft rows of rotatable blades, a row of stationary vanes between the forward and aft rows of rotatable blades, an annular intermediate disc, and a seal housing apparatus. The forward and aft rows of rotatable blades are coupled to respective first and second portions of a disc/rotor assembly. The annular intermediate disc is coupled to the disc/rotor assembly so as to be rotatable with the disc/rotor assembly during operation of the gas turbine. The annular intermediate disc includes a forward side coupled to the first portion of the disc/rotor assembly and an aft side coupled to the second portion of the disc/rotor assembly. The seal housing apparatus is coupled to the annular intermediate disc so as to be rotatable with the annular intermediate disc and the disc/rotor assembly during operation of the gas turbine.

Abstract: Provided is a dual rotor wind turbine having two rotor assemblies. In the dual rotor wind turbine, an inlet guide vane is placed at a lower location in front of each rotor assembly and a rotor shaft of the rotor assemblies is placed in back of a vertical shaft, so that the rotor shaft is offset from the vertical shaft. Thus, the gravity center of the wind turbine is located in a lower portion of the wind turbine, so that a stable balance of the wind turbine can be realized and the vertical shaft can be smoothly rotated relative to a fixed shaft.

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 segment of a component for use in a gas turbine includes a leading edge; a trailing edge; a pair of opposed lateral sides between the leading and trailing edges; and a seal slot provided in each lateral side. The seal slot includes a surface having a channel extending in an axial direction defined from the leading edge to the trailing edge, at least one inlet to the channel, and at least one outlet from the channel. The at least one outlet is spaced downstream from the at least one inlet in the axial direction. The segment may be an inner shroud segment or a nozzle segment.

Abstract: A nozzle for a turbine includes a duct member having a substantially uniform wall thickness. Nozzles made of different materials can be used.

Abstract: A wind power engine including a stator having stator blades, and a rotor having rotor blades. The rotor is positioned inside the hollow area of the stator and is rotationally movable with respect to the stator about an axis of rotation. The stator blades are positioned in such a way that an air flow coming from the outside of the stator is oriented towards the rotor and the rotor blades. The oriented airflow allows the rotor blades to drive the rotor about the axis of rotation. At least certain rotor blades have a concave-shaped profile on one of their faces.

Abstract: A turbine section of a gas turbine engine is provided. The turbine section is annular about a longitudinal axis and includes first turbine with a first inlet and a first outlet; a second turbine with a second inlet and a second outlet; an inter-turbine duct extending from the first outlet to the second inlet and configured to direct an air flow from the first turbine to the second turbine; and a first guide vane disposed within the inter-turbine duct.

Abstract: A blade profile section for an air turbine starter includes an airfoil which defines an airfoil profile section through a leading edge and a trailing edge. The airfoil profile section is defined by a set of X-coordinates and Z-coordinates defined in any of Table I, Table II, Table III or Table IV scaled by a desired factor. The X-coordinate is the tangential direction, and the Z-coordinate is a radial direction between an airfoil root and an airfoil tip.

Abstract: A vane segment for a gas turbine engine according to an exemplary aspect of the present disclosure includes an inner vane platform relative an axis, the inner vane platform having a non-axisymmetric surface contour.

Abstract: An inlet guide vane assembly includes an active control feedback system and a plurality of inlet guide vanes. The inlet guide vanes are variable between a plurality of positions. Each of the plurality of inlet guide vanes is positioned in response to an output of the activate control feedback system.

Abstract: An airfoil or vane for a combustive power plant includes an inner core formed from a first composite material having discontinuous fibers. An outer sleeve is formed from a second composite material having continuous fibers. The first composite material is different from the second composite material. The outer sleeve generally surrounds and is bonded or otherwise connected to the inner core. A method of fabrication includes injecting or otherwise introducing thermoplastic fiber composite material including chopped or otherwise discontinuous fibers into a mold to form the core and platforms of an airfoil assembly. The injected thermoplastic fiber composite material is then cured in the mold. The cured thermoplastic fiber composite material is then removed from the mold. A layup including one or more surface plies of a thermoset continuous fiber composite material is then applied to the core material. The surface plies are then compressed and cured in a mold.

Abstract: A vane profile section for an air turbine starter includes an airfoil which defines an airfoil profile section through a leading edge and a trailing edge, the airfoil profile section defined by a set of X-coordinates and Z-coordinates.

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 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 wind power generation apparatus includes a wind collecting hood, a rotary shaft, a rotary structure and a wind guiding structure. The wind collecting hood is a hollow circular barrel to form an airflow passage. The rotary shaft is located in the airflow passage of the wind collecting hood. The rotary structure is mounted onto the rotary shaft. The wind guiding structure is fastened to the wind collecting hood and located at the front end of the rotary structure. The wind guiding structure directs direction of airflow and accelerates the airflow to become swirling airflow to directly blow the rotary structure at optimal angles, thus capability of driving the rotary structure to rotate by wind is increased and starting wind power of the rotary structure is reduced. The rotary structure is still rotated at where the wind is smaller to provide electric power.

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: 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 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 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 vane structure for a gas turbine engine according includes a multiple of CMC airfoil sections integrated between a CMC outer ring and a CMC inner ring.

Abstract: A method of operating an axial turbine, having a stage including stationary blades and moving blades, each stationary blade having a radial height of an outlet thereof higher than the radial height of an inlet thereof, each moving blade being located downstream of a corresponding one of the stationary blades along a flow direction of a working fluid, the moving blades being constructed such that a moving blade front-end peripheral velocity Mach number exceeds 1.0, the method including restraining a radial velocity component of a working fluid flowing through an outer peripheral portion of the stationary blade from the stationary blade inlet to the stationary blade outlet, whereby the working fluid having passed through the stationary blade flows substantially parallel to the central axis of the turbine from the stationary blade outlet to the moving blade inlet.

Abstract: A gas turbine stator vane is effective for suppressing a secondary flow in a region sandwiched between a suction surface side and a pressure surface side, as well as for suppressing augmentation of a horseshoe-shaped vortex occurring near a leading edge of the vane. The stator vane includes a vane profile portion having a pressure surface concaved to a chord line of the vane, and a suction surface convexed to the chord line; an outer-circumferential end wall positioned at an outer circumferential side of the vane profile portion; and an inner-circumferential end wall positioned at an inner circumferential side of the vane profile portion. An outer-circumferential end wall inner surface that is an inner-circumferential surface of the outer-circumferential end wall has an inward convexed shape and an outward convexed shape, at the suction surface side of the vane profile portion.

Abstract: An apparatus for improving the performance of a radial compressor 36 forming part of an inlet system of an engine 10 is disclosed in which the configuration and positioning of a flow management device 137 used to generate pre-whirl is optimized so as to produce a pressure drop below a maximum acceptable level. An inlet duct ‘I’ connected to the radial compressor 36 has a tapered end portion so that a flow management device 137 of a larger diameter d2 can be accommodated than the diameter d1 of an inlet port ‘IP’ to the radial compressor 36.

Abstract: A centrifugal compressor for compressing a fluid comprises a compressor wheel having a plurality of circumferentially spaced blades, and a compressor housing in which the compressor wheel is mounted. The compressor housing includes an inlet duct through which the fluid enters in an axial direction and is led by the inlet duct into the compressor wheel, and an inner surface located radially adjacent the tips of the blades. A bleed port is defined in the inner surface of the compressor housing at a location intermediate the leading and trailing edges of the blades, for bleeding off a bleed portion of the fluid, the bleed port leading to a recirculation flow channel that feeds the bleed portion back into the inlet duct. Highly cambered vanes are disposed in the recirculation flow channel for turning the bleed portion to take out and in some cases reverse the swirl in the bleed portion.

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 gas turbine engine assembly includes a housing including an annular duct wall that at least partially defines a mainstream hot gas flow path configured to receive mainstream hot gas flow. The assembly further includes a stator assembly including a stator vane that extends into the mainstream hot gas flow path and a turbine rotor assembly downstream of the stator assembly that includes a turbine disk and a turbine blade extending from the turbine disk into the mainstream hot gas flow path. The stator assembly and turbine assembly define a turbine disk cavity, and the turbine disk cavity includes a recirculation cavity configured to recirculate gas ingested from the mainstream hot gas flow path back into the mainstream hot gas flow path.

Abstract: A guide vane for a gas turbine with a vane base body which is of single-piece design and comprises a profiled vane blade extending between a vane root and a cover plate and also the vane root formed integrally with the vane blade and the cover plate formed integrally with the vane blade, is intended, in a relatively simple way to be able to be matched to the individual conditions of use with especially little outlay on apparatus and logistics. For this purpose, according to the invention, a flow-routing body with an advance guide blade that is connected upstream of the vane blade as seen in the direction of flow of the working medium of the gas turbine is joined to the vane base body.

Abstract: Disclosed is a method of producing a stator blade for use in a turbo-molecular pump. The method includes subjecting a metal plate to a slitting process to form a blade element having an upstream edge surface and a downstream edge surface, wherein a laser beam is emitted onto the metal plate at an incident angle oblique to a principal surface of the metal plate. Thus, the upstream edge surface and/or the downstream edge surface can be formed to extend obliquely relative to the principal surface of the metal plate, in a simple manner, while eliminating a need for a burr removal operation which would otherwise be necessary in a punching-based slitting process.

Abstract: Gas turbine engine systems involving fairings with locating data are provided. In this regard, a representative a fairing assembly for a gas turbine engine includes: a first locating component having a leading edge, first and second sides extending from the leading edge, and a recess oriented parallel to the leading edge, the recess having a first datum surface, the first locating component being operative to be positioned between a portion of a strut and a portion of an interior surface of a fairing sheath such that the first datum surface establishes a desired orientation of the fairing sheath relative to the strut.

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 cooling system having one or more pin fins with reduced mass for a gas turbine engine is disclosed. The cooling system may include one or more first surfaces defining at least a portion of the cooling system. The pin fin may extend from the surface defining the cooling system and may have a noncircular cross-section taken generally parallel to the surface and at least part of an outer surface of the cross-section forms at least a quartercircle. A downstream side of the pin fin may have a cavity to reduce mass, thereby creating a more efficient turbine airfoil.

Abstract: The present invention relates to a blower for vehicles, which includes guide walls formed on a bypass passageway formed between a scroll case and an outer case to send the indoor air and the outdoor air to a lower suction opening of the scroll case, thereby reducing suction noise by guiding a uniform flow of air introduced into the lower suction opening, preventing deformation of the outer case, and preventing a droop of the air filter by supporting a lower portion of an air filter when an intake duct injection-molded in a vertically parted mold is applied thereto.

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 motor-fan assembly for a vacuum cleaner configured to remove debris from a surface. The motor-fan assembly includes a fan, a motor including an output shaft coupled to the fan, the motor operable to rotate the fan, and a diffuser. The diffuser includes a disc, a wall that surrounds the disc, and a plurality of vanes that are coupled to an outer surface of the wall and extend radially outward from the outer surface of the wall.

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: A turbine nozzle includes a row of vanes extending radially between annular outer and inner bands. The outer band includes a pair of radial flanges defining an annular seal groove therebetween. One of the flanges is crenelated to improve nozzle life.

Abstract: A turbine reduces variations in mass flow at throats even when the flow rate of fluid is low or high. The turbine includes a turbine rotor having turbine blades; a turbine housing accommodating the turbine rotor 80 and whose cross-sectional area of a scroll portion formed between the turbine housing and the turbine rotor gradually decreases; a plurality of fixed vanes fixed along a curved line dividing the scroll portion into an inner scroll part and an outer scroll part; throats formed between the adjacent fixed vanes and communicate between the inner scroll part and the outer scroll part; and a switch valve which switches a flow path in the turbine housing either to the inner scroll part or to both the inner scroll part and the outer scroll part, in which flow path areas of the throats are reduced in a downstream direction of the scroll portion.

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: A vane includes a composite airfoil having one or more outer pockets and one or more outer spars received therein respectively. The outer spars extending radially inwardly from an outer bridge of the outer vane mount outwardly supporting airfoil. The spars may be integrally formed with the bridge and adhesively bonded to the composite airfoil within the pockets with a passage extending between an airfoil base and an airfoil tip. A metallic leading edge tip may be disposed along the leading edge of the composite airfoil. A gas turbine engine annular fan frame incorporates the vanes in an annular row of composite outlet guide vanes extending radially between and connecting radially inner and outer rings of the fan frame.

Abstract: A method and system for harvesting wind energy. The system may include a wind turbine disposed subjacent to a roof assembly of building. A plurality of conduits are adjacent to and extending below the wind turbine, wherein each of the plurality of conduits defines a first portion and a second portion, wherein the first portion defines a larger cross-sectional area than the second portion.

Abstract: A case assembly for a gas turbine engine is provided that includes an outer case with circumferentially spaced individual bosses that include a recess. A vane assembly is received in the outer case. An axial retention ring has uninstalled and installed conditions. The axial retention ring outside of the recess is in the uninstalled condition and received in the recess in the installed condition. An anti-rotation feature, such as a ring, is arranged between the bosses in a locking condition to prevent rotation of the axial retention ring between the installed and uninstalled conditions.

Abstract: An inlet case for a small gas turbine engine, where the inlet case is formed as a hybrid piece with a metallic inner shroud cylinder and plastic guide vanes and plastic outer shroud molded around the metallic inner shroud cylinder. The metallic inner shroud cylinder carries an electric generator and provides for a good convective heat transfer surface to carry heat away from the electric generator and into the inlet air flow entering the engine. The plastic guide vanes and outer shroud allow for a light weight inlet case assembly that is also much easier to form the airfoil shapes than a machined metallic inlet case. The plastic guide vanes and outer shroud are injection molded around the metallic inner shroud cylinder to produce a rigid single inlet case. The metallic cylinder includes axial extending slots that receive the lower ends of the guide vanes during the injection molding process.

Abstract: An inner shroud portion and an outer shroud portion dividedly formed per stationary blade are formed integrally with each stationary blade. A plurality of the stationary blades adjacent to each other in a circumferential direction are coupled together by a band member at the outer shroud portions. The inner shroud portions are held between seal holders which are formed as two divided members in the flowing direction of a working fluid, which are fastened by a bolt, and which have a length corresponding to the plurality of the stationary blades. The plurality of stationary blades, the inner and outer shroud portions, the band member, and the seal holders assembled in this manner constitute a unit. A plurality of the units are connected in the circumferential direction to constitute a stationary blade ring of an axial compressor.

Abstract: A gas turbine engine blade or vane having a first platform, an airfoil, and a compound fillet extending about a region where the airfoil joins the first platform is disclosed. The compound fillet has a first conic surface and a second conic surface, with the first conic surface tangent to the airfoil and to an offset platform surface and the second conic surface tangent to the first conic surface and the first platform. The two conic surfaces are of different sizes, with different radii, and the conic surfaces can vary in size about the periphery of the joint between the airfoil and the first platform.