Abstract: A method of fabricating a guide vane. The method produces a fiber preform by 3D weaving a single piece, the preform including a first portion extending along the longitudinal axis and constituting the preform for an airfoil of the vane, and at a longitudinal end of the first portion, a second portion constituting the preform for the platform of the vane, the second portion being produced as a first layer and a second layer facing the first layer and separated from the first layer by unlinking without cutting while producing the preform; folding the first and second layers such that each of them lies in a plane perpendicular to the longitudinal axis, substantially symmetrically to each other relative to the first portion, and such that a first region of the first layer covers a second region of the second layer in front of a front edge of the first portion; conforming the preform in a mold; and densifying the preform with a polymer matrix.

Abstract: A wind compressor system having one or more wind turbines and a plurality of wind compressors located proximate the one or more wind turbines. The wind compressors optimize the energy created by the wind turbines by redirecting and converging the wind from the wind compressor to the wind turbines. Each of the wind compressors comprises an obstruction having a size and shape adapted to converge the wind currents by means of a Venturi effect toward the one or more turbines thereby increasing the velocity and force of the wind hitting the wind turbine. A plurality of transporters coupled to the wind compressors. The transporters configured to move at least one wind compressors to a location that maximizes the force of the wind encountered by the turbine.

Abstract: A wind compressor system having one or more wind turbines and a plurality of wind compressors located proximate the one or more wind turbines. The wind compressors optimize the energy created by the wind turbines by redirecting and converging the wind from the wind compressor to the wind turbines. Each of the wind compressors comprises an obstruction having a size and shape adapted to converge the wind currents by means of a Venturi effect toward the one or more turbines thereby increasing the velocity and force of the wind hitting the wind turbine. A plurality of transporters coupled to the wind compressors. The transporters configured to move at least one wind compressors to a location that maximizes the force of the wind encountered by the turbine.

Abstract: A compressor is provided that can avoid fretting damage to improve fatigue strength reliability. The present invention is characterized in that a portion on the circumferential outside and radial outside of a radial outside contact end portion 9a with a dovetail portion 4a is removed from a wheel 7. Specifically, the wheel 7 is formed with a groove portion 10 in an area that is located on the circumferential outside of the radial outside contact end portion 9a of a blade securing portion 15 with the dovetail portion 4a and that includes a radial outside of the contact end portion 9a. Rigidity on the wheel side of the contact end portion 9a between the dovetail portion 4a and the wheel 7 is reduced to reduce the occurrence of stress, thereby avoiding the lowering of fatigue life reliability resulting from fretting.

Abstract: An assembly for use in a gas turbine engine includes an inner diameter (ID) shroud having a plurality of ID slots and an outer diameter (OD) shroud having a plurality of OD slots and positioned radially outward from the ID shroud. A plurality of stator airfoils extend from the ID shroud to the OD shroud. Each of the stator airfoils is positioned at least partially in one of the ID slots and is positioned at least partially in one of the OD slots. A bumper is positioned proximate a first end of each of the stator airfoils so as to limit movement of the stator airfoils in a radial direction.

Abstract: A control system for controlling at least two variable-geometry devices of a turbomachine, and a turbomachine including such a control system, the system including an actuator that actuates both devices; one of the devices including at least one stage of variable-pitch stator vanes, and the other device being an air-bleed valve for a turbomachine body. The system is configured to control progression opening of the vane stage and progressive closing of the air-bleed valve as an actuation parameter of the actuator increases. As a result, the control system serves advantageously to control two devices using a single control system.

Abstract: An axial flow turbine diaphragm is constructed without welding or other metal joining techniques as an annular array of static blade units. Each blade unit comprises an aerofoil and radially inner and outer platforms integral with the aerofoil. The radially inner platform consists of a segment of the inner diaphragm ring and the radially outer platform consists of a segment of the outer diaphragm ring. At least the outer ring segment has engagement features that mechanically engage with complementary engagement features on neighbouring outer ring segments in the annular array of blade units, the engagement features acting to mechanically interlock neighbouring outer ring segments and produce a self-supporting turbine diaphragm.

Abstract: A turbine vane for a turbine machine comprising an intermediate section having a nominal airfoil profile substantially in accordance with Cartesian coordinate values of X, Y and Z set forth in Table I wherein Z is a radial distance along a stacking axis that is normal to a centerline of the turbine machine and contain the X and Y values with Z value beginning at innermost aerodynamic point and the Z values represent a radial height of the vane and the X and Y values define the nominal airfoil profile at each radial height Z.

Abstract: A stator assembly or a stator stage is disclosed. The stator assembly includes an endless case that is coupled to or includes at least one lug for engaging an anti-rotation stator segment. The anti-rotator segment includes one curved side edge and one straight or linear side edge. The case also accommodates a plurality of middle stator segments, each having curved side edges on both sides. Finally, a third type of stator segment is a “neighbor” stator segment with one curved side edge and one linear side edge that abuttingly engages the linear side edge of the anti-rotation stator segment. The straight or linear side edges of the anti-rotation stator segments and the neighbor stator segments enable an endless case to be loaded with stator segments from an axial direction. None of the stator segments need to be installed from a radial direction.

Abstract: A stator includes: a plurality of stator pieces around which coils are wound; a stator holder which supports the plurality of stator pieces by arranging the plurality of stator pieces in a peripheral wall portion in an annular shape; and a housing which is disposed on an outer side of the stator holder to support the stator holder, wherein the stator holder includes a flange portion which continuously protrudes outward in a radial direction thereof from an edge of one end side in an axial line direction thereof and is fixed to the housing, and a reinforcing portion which suppresses vibration in the radial direction of the stator holder on an outer peripheral surface of the peripheral wall portion.

Abstract: A turbine engine stator stage includes a plurality of vanes with each of the plurality of vanes having a camber angle. The plurality of vanes is arranged in a plurality of groups with each group including a pre-determined sequence of vanes. The ordering of vanes within each group is determined by the camber of the individual vanes. This results in an arrangement of vanes within the stator stage which can modify the flow characteristics of the air entering the stator stage to reduce the circumferential pressure variation in the flow region immediately downstream of the stator stage.

Abstract: A gas turbine engine includes first and second stages having a rotational axis. A circumferential array of airfoils is arranged axially between the first stage and the second stage. At least one of the airfoils have a curvature provided equidistantly between pressure and suction sides. The airfoils extend from a leading edge to a trailing edge at a midspan plane along the airfoil. An angle is defined between first and second lines respectively tangent to the intersection of the midspan plane and the curvature at airfoil leading and trailing edges. The angle is equal to or greater than about 10°.

Abstract: A steam turbine singlet nozzle airfoil with integral outer sidewall is engaged with an inner ring and an outer ring in a nozzle assembly. The interface of the outer sidewall with the outer ring may include a plurality of mechanical hooks on one or both of the upstream face and the outer radial face of the outer sidewall that engage with complimentary structures on the outer ring. The outer interface may further include low energy welds along limited distances of one or both of the upstream or downstream interface of the outer sidewall and the outer ring. An inner radial end of the singlet nozzle airfoil is pinned into position and fastened to the inner ring. Without a need for high heat welds, distortion of the airfoil and the steam flow path and the associated rework is eliminated and stage performance is improved.

Abstract: In a rotor blade cylindrical portion or a stator portion in which thread grooves are formed, convex surfaces (thread groove peak surfaces) configuring the peak sections of the thread grooves are cut by a desired amount over the entire circumference (a circumferential direction of the thread grooves) of a certain range in an axial direction. As a result, the gap on the lower side of the thread groove portion can partially be expanded by cutting the thread groove peak surfaces by a desired amount.

Abstract: A gas turbine is provided including a compressor, a combustion chamber, a guide vane row and a rotor airfoil row. The guide vane row includes a plurality of guide vane airfoils having a blade and an inner platform. The ratio between the pitch and the leading edge diameter of the guide vane airfoils is between 6.3-7.6 and the ratio between the platform length and the leading edge diameter of the guide vane airfoils is between 4.0-5.5.

Abstract: A turbo machine comprising a rotor assembly comprising at least one impeller, a bearing connected to the rotor assembly, wherein the bearing is configured to rotatably support the rotor assembly, and a stator comprising at least one diffuser connected to an exit portion of the at least one impeller, wherein the at least one diffuser comprises a plurality of diffuser vanes, wherein at least one of the plurality of diffuser vanes comprising a camber line defined by a function comprising an inflection point.

Abstract: A two-stage high pressure turbine includes a second stage vane 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.

Abstract: An airfoil array includes a laterally extending endwall 56 with a series of airfoils such as 28 or 38 projecting from the endwall. The airfoils cooperate with the endwall to define a series of fluid flow passages 74. The endwall has a trough 100 toward a pressure side of the passage and a more elevated profile toward a suction side of the passage for reducing secondary flow losses.

Abstract: A rotary displacement pump of an undulatory disk type; with a pump housing (24) comprising a front end plate (56) and a rear end plate, the pump housing enclosing a stator (40, 48), a rotor (42), a scraper (44) and a scraper guide (46), a shaft (8) extending through at least the rear end plate; the stator including a generally semi-circular arc-formed first stator member (40) and a generally semi-circular arc-formed second stator member (48), the stator, the pump housing and the scraper together with the scraper guide defining an inlet and outlet chamber, wherein at least part of the end faces of the first and second stator members being situated in the outlet chamber are oblique so as to provide an obtuse-angled transition to the inner faces of the front end plate and the rear end plate.

Abstract: Provided is a compressor for use in a gas turbine engine, capable of preventing a creation of rust on an inner surface of the compressor casing, without complicating assembling process. The casing 15 of the compressor 3 accommodates rotor and stator blade wheels 13 and 17. The stator blade wheels 17 are supported on the inner surface of the casing 15 through outer flanges 30 thereof. Seal rings 52 are provided at inner surface portions of the casing 15 opposing the radially outward ends of the rotor blade wheels 13. The inner surface of the casing 15 is covered by the seal rings 52 and the outer flanges 30 of the stator blade wheels 17.

Abstract: A stator angular sector for a turbine engine compressor and including: an outer shroud and an inner shroud; and at least one vane extending radially between the shrouds and connected thereto at its radial ends. At one of its axial ends the outer shroud includes a cavity opening out to the axial end and extending between a radially-inner tongue of the outer shroud to which the radially-outer end of the vane is connected, and a radially-outer tongue of the outer shroud carrying a mounting mechanism for mounting the stator angular sector to a casing of the engine. An abutment-forming insert is housed at least in part in the cavity, the abutment-forming insert configured to limit radial movements of the radially-inner tongue by contact and thus to modify vibratory behavior of the radially-inner tongue.

Abstract: A fan device includes a rotor 20 and recesses 40 to be filled with claylike weights 70. The rotor 20 includes an impeller 23 and a shaft 10. The impeller 23 has a hub 21 and vanes 22. The recesses 40 are provided on a surface 212 that crosses an axial direction of the hub 21. Each recess 40 has a first area 41 and a second area 42. The first area 41 is circumferentially arranged and extends in a substantially circumferential direction. The second area 42 is connected to an outer circumferential side of the first area 41 and has a shorter length in the circumferential direction than the first area 41. The weight 70 is closely adhered to wall surfaces 421 and 422 formed along a radial direction in the second area 42 so as to prevent separation thereof.

Abstract: A motor-driven compressor includes an electric motor having a stator core, a compression mechanism driven by the electric motor, a motor housing accommodating the electric motor, and a cluster block engaged with the stator core in the motor housing. The stator core of the electric motor and the motor housing are assembled by shrink fit. The cluster block accommodates a connecting terminal for electrical connection between a conductor connected to a motor drive circuit and a lead wire drawn from the electric motor. The cluster block has a terminal hole for receiving the connecting terminal and has an opening that is provided separately from the terminal hole.

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: The present application provides a diffuser for use with a gas turbine. The diffuser may include hub, a number of struts extending from the hub, and a number of airfoils extending from the hub.

Abstract: Provided is a turbine blade cascade endwall that is capable of suppressing a vortex generated on a suction surface of a turbine stator blade and that is capable of reducing secondary-flow loss due to this vortex. A turbine blade cascade endwall that is positioned on a tip side of a plurality of turbine stator blades arranged in a ring form is provided with a pressure gradient alleviating part that alleviates a pressure gradient generated in the blade height direction at a suction surface of the turbine stator blades due to a clearance leakage flow, leaking out of a gap between a tip of a turbine rotor blade located on the upstream side of the turbine stator blades and a tip endwall disposed facing the tip of this turbine rotor blade.

Abstract: A floor standing pedestal fan for creating an air current includes a base housing an impeller and a motor for rotating the impeller to create an air flow, an air outlet, and a telescopic duct for conveying the air flow to the air outlet.

Abstract: A turbomachine stage including guide vanes, radially inner and/or radially outer airfoil platforms, which together form a guide vane cascade, and further including rotor blades, radially inner and/or radially outer airfoil platforms, which together form a rotor blade cascade adjacent to the guide vane cascade. Radially outer airfoil platforms have cascade regions extending between circumferentially adjacent airfoils, and gap regions which radially and/or axially bound an axial gap extending axially between the guide vane cascade and the rotor blade cascade. A contour of at least one of these gap regions varies, in particular periodically, in the radial and/or axial direction around the circumference.

Abstract: A turbomachine stage includes guide vanes and an airfoil platform forming a guide vane cascade, and rotor blades and an airfoil platform forming a rotor blade cascade. Airfoil platforms have cascade regions extending between circumferentially adjacent airfoils, and gap regions which radially and/or axially bound an axial gap extending axially between the guide vane cascade and the rotor blade cascade. A contour of at least one of these gap regions varies in the radial and/or axial direction around the circumference.

Abstract: The turbine (1) according to the present invention includes: a blade body (50) having a blade (59) provided at one of a rotor rotatably supported and a stator provided around the rotor and extending in a radial direction toward the other side from one side and a shroud (51) extending in a circumferential direction at a tip portion in the radial direction of the blade (59); and an accommodating concave body (11) provided at the other of the rotor and the stator, extending in the circumferential direction, accommodating the shroud (51) with a gap (G) interposed therebetween, and relatively rotating with respect to the blade body (50), wherein leakage flow (L) leaked from main flow (M) flowing along the blade (59) flows into the gap (G); and wherein the shroud is provided with a guide curved surface formed between a peripheral surface (53C) facing the accommodating concave body (11) and a trailing edge end portion (56) formed closer to the main flow (M) side in a downstream of the leakage flow (L) than the perip

Abstract: A gas turbine engine with a compressor rotor having compressor impulse blades that delivers gas at supersonic conditions to a stator. The stator includes a one or more aerodynamic ducts that each have a converging portion and a diverging portion for deceleration of the selected gas to subsonic conditions and to deliver a high pressure oxidant containing gas to flameholders. The flameholders may be provided as trapped vortex combustors, for combustion of a fuel to produce hot pressurized combustion gases. The hot pressurized combustion gases are choked before passing out of an aerodynamic duct to a turbine. Work is recovered in a turbine by expanding the combustion gases through impulse blades. By balancing the axial loading on compressor impulse blades and turbine impulse blades, asymmetrical thrust is minimized or avoided.

Abstract: The present invention comprises a gas turbine engine with a compressor for generating compressed air, a turbine comprising upstream and downstream rows of vanes, vane carrier structure surrounding at least one row of vanes and plenum structure at least partially surrounding the vane carrier structure capable of impinging compressed air onto the vane carrier structure. The gas turbine engine further comprises fluid supply structure including first fluid path structure defining a first path for compressed air to travel to the plenum structure, second fluid path structure defining a second path for compressed air to travel toward the downstream row of vanes, and fluid control structure selectively controlling fluid flow to the first and second fluid path structures.

Abstract: The turbine includes: a shaft body supported rotatably; a plurality of turbine blade members; a casing covering the shaft body and the turbine blade row; an outer ring member that is provided on an inner periphery of the casing and includes an inner peripheral portion in which a cross-section having a uneven shape is continuous in a circumferential direction; a plurality of turbine vane members that each has a shroud fitted into the inner peripheral portion of the outer ring member and a turbine vane main body extending from the shroud to a radially inward side; and a plate member that connects at least some of the plurality of turbine vane members and covers one side of the shrouds in the axial direction, thereby sealing a shroud gap formed between the shrouds adjacent to each other in the circumferential direction.

Abstract: A gas turbine engine component is provided including at least one ring element, and a plurality of circumferentially spaced load carrying vanes extending in a radial direction of the ring element. The load carrying vanes have an internal structure with an anisotropic load carrying property, and the internal structure is configured so that a main load carrying direction is in parallel with the extension direction of the load carrying vane. The component includes a stiffening structure bridging the distance between at least two adjacent load carrying vanes in the circumferential direction of the ring element, and the at least two adjacent load carrying vanes are attached to the stiffening structure.

Abstract: A centrifugal compressor, including: a housing, the housing including: an inlet, a flow channel, an impeller outlet, and an air diffusing channel; a centrifugal impeller disposed inside the housing; a rotating wall, the rotating wall including a front cascade; and a rotating disc, the rotating disc including a rear cascade. The impeller outlet is disposed adjacent to a rear part of the centrifugal impeller and is connected to the flow channel via the air diffusing channel. The rotating wall is disposed between the centrifugal impeller and the housing. The front cascade is disposed inside the front part of the rotating wall and is connected to a dynamic driving device. The rotating disc is disposed inside the housing adjacent to the air diffusing channel and is in a rigid connection with the rotating wall.

Abstract: An electric pump includes a pump portion, a motor portion including a rotor formed in a cylinder form sharing an axis with a rotation shaft provided at the pump portion and a stator formed in an annular form arranged at an outer periphery of the rotor with a clearance between the stator and the rotor, and a driver portion arranged at a position between the pump portion and the motor portion when viewed in a direction orthogonal to an axial direction of the rotation shaft, the driver portion controlling the motor portion, the driver portion arranged in a state where a portion of the driver portion overlaps with at least a portion of the pump portion or with at least a portion of the motor portion when viewed in the axial direction.

Abstract: An electric blower includes a stator, a rotor, a bracket, rotary fan, air guide, a fan case covering air guide and rotary fan. Air guide includes a partition plate, a diffuser, a partition slope, and a guide vane. Diffuser vanes configure closed passages. Passage lengths of closed passages include a first passage length and a second passage length that is different from the first passage length.

Abstract: A turbine nozzle is constructed from a plurality of associated circumferential turbine nozzle segments each of which incorporates at least one pre-formed annular-segment passage bounded at a first azimuthal boundary by a first portion of a first bounding nozzle vane, and at a second azimuthal boundary by a second portion of a second bounding nozzle vane, with the at least one pre-formed annular-segment passage therebetween, wherein when assembled in the turbine nozzle, a first portion of a first bounding nozzle vane of one circumferential turbine nozzle segment is joined to a second portion of a second bounding nozzle vane of another adjacent circumferential turbine nozzle segment so as to form therebetween a nozzle vane of the turbine nozzle, wherein the minimum through-flow area of the associated at least one pre-formed annular-segment passage is substantially unaffected by the assembly of the circumferential turbine nozzle segments to form the turbine nozzle.

Abstract: A pump assembly to move water past a reverse osmosis membrane, the pump assembly having a first pump and a second pump each including a bore having a longitudinal axis and surrounding a chamber. First and second partition members extend longitudinally of the chamber. The second partition is moveable relative to the first partition member, and divides the chamber into a first sub chamber and a second sub chamber. A shaft is attached to the second member to cause angular movement thereof about the axis to change the volumes of the sub chambers. End caps are fitted to ends of each chamber to contain pressure, and ducting is provided to provide for the flow of water. The shaft of the first pump is coupled to the shaft of the second pump so that the first pump second partition angularly oscillates in phase with the second pump second partition.

Abstract: A turbine is provided including an annular turbine blade body (50) disposed on a flow path, a diaphragm outer ring (11) installed at a tip side of the blade body via a clearance, and seal fins (12A, 12B, 12C) formed to protrude from the diaphragm outer ring (11) and configured to form small clearances (13A, 13B, 13C) with the annular turbine blade body (50), wherein dead water region-filling sections (15, 17, 19) are formed in cavities (C1, C2, C3) in which main vortexes (SU1, SU2, SU3) are generated, such that a dead water region that the main vortexes (SU1, SU2, SU3) cannot reach is filled.

Abstract: The invention relates to a casing, particularly of an axial turbomachine compressor. This casing comprises a support of cylindrical overall shape made of composite material, a metal ring fitted by bonding to the internal surface of the support, and a layer of abradable material fitted by plasma spray onto the internal surface of the metal ring. The metal ring is preferably made of stainless steel and is preferably perforated. The perforation allows better keying of the adhesive and allows the degassing thereof. The external surface of the metal ring is preferably sandblasted prior to bonding. Its internal surface is also preferably sandblasted prior to the plasma spraying of the abradable material.

Abstract: In the area of the support struts and/or the aerodynamic fairings downstream of the stator vanes, the cross-section of the bypass duct of a turbofan engine is enlarged such that the pressure variations caused by the stagnation effect of the installations and reacting on the fan are reduced, enabling the fan to be operated with more efficiency and stability and finally the losses of the overall system and the fuel consumption to be reduced. The cross-sectional enlargement is accomplished by modifying the course of the wall in a limited area, actually by gradually enlarging the flow cross-section in the bypass duct in the axial and in the circumferential direction, with this enlargement being confined to the area around the leading edge of the support struts and/or the aerodynamic fairings.

Abstract: A hermetically sealed compressor in which heat generation and insulation breakdown are hardly to occur at the connection portion between a lead wire of a motor and an external terminal is configured as follows. The compressor main body and the motor are integrally structured. The flow path of a fluid to be compressed is communicated with the internal space of the motor. The stator (10) of the motor is formed by winding each of a plurality of independent coils (A1, A2, B1, B2, C1, C2) in multiple turns. Each of the coils (A1, A2, B1, B2, C1, C2) is provided with a separate external terminal (18).

Abstract: A vertical axis wind turbine formed from a concentric arrangement of fixed stator blades to provide fluid flow acceleration into an arrangement of rotatable blades secured to a generator for invoking electrical power generation. The stator blades are maintained in a fixed position by use of an upper and lower stator plate. The rotor blades include an upper and lower plate, the upper plate coupled to the upper stator plate, and the lower rotor plate coupled to the generator. The amount of stator and rotor blades may be scaled in number and size depending upon the type of generator to be driven and associated mechanical energy to be obtained. The stator blades are designed for air deflection in a direction for optimal rotor blade rotation by accelerating air flow into a pre-swirl before the flow contacts the rotor blades. Each stator blade is oriented at a sufficient stagger angle so that an angle of the relative velocity does not exceed the stall angle of said rotor blade.

Abstract: A wind turbine comprising: a shaft (2); a plurality of blade arrangements (8), each of which is rotatable around the shaft and has a blade (7), said blade arrangements and blades forming a blade rotor which is rotatable around the shaft; at least first and second bearing arrangements (6) spaced axially along the shaft, said blade rotor being connected to said first and second bearing arrangements; and a direct drive generator comprising a stator (10), which is rotationally fixed to the shaft, and a generator rotor (9) having a rim; wherein the first and second bearing arrangements each transmit radial forces from the blade rotor to the shaft, and at least one of the first and second bearing arrangements transmits bending moments to the shaft, each of the blade arrangements being connected to a point at or adjacent the rim of the generator rotor so as to transmit torque generated by the blade arrangement directly thereto, and wherein the generator rotor (9) is within the blade rotor.

Abstract: An inner diameter vane seal for a gas turbine engine comprises an annular, ring-like body having inner and outer diameter rims, forward and aft faces and an air passage. The outer diameter rim extends circumferentially for engaging inner diameter ends of stator vanes. The inner diameter rim extends circumferentially and is spaced radially from the inner outer diameter rim. The forward and aft faces extend radially between the outer diameter rim and the inner diameter rim. The air passage extends from the forward face to the aft face between the inner and outer diameter rims.

Abstract: An assembly for a stator stage of a turbomachine is disclosed. The assembly includes: an outer shroud presenting a series of openings for mounting each stationary vane by welding between the edge of an opening and the outline of the platform of the vane, the outline of the outer segment of an opening surrounding, in radial projection, the outline of the inner segment thereof, the shroud not having any other holes; and at least one stationary vane with its top including a non-pierced platform received in one of the openings prior to the welding step, such that an inside face of the platform bears against a bearing face of the shroud, the outline of the platform presenting a shape that is identical to the shape of the outline of the opening.

Abstract: A cross-flow fan includes a plurality of fan blades. The fan blade has an inner edge portion arranged on an inner circumferential side and an outer edge portion arranged on an outer circumferential side. In the fan blade, a blade surface extending between the inner edge portion and the outer edge portion and constituted of a positive pressure surface and a negative pressure surface is formed. The fan blade has such a blade cross-sectional shape that a large-thickness portion at which a thickness between the positive pressure surface and the negative pressure surface is greatest is arranged closer to the inner edge portion. A recess recessed in the blade surface is formed at a position closer to the inner edge portion where the large-thickness portion is arranged, than to the outer edge portion.

Abstract: A gas turbine engine includes first and second stages having a rotational axis. A mid turbine frame is arranged axially between the first and second stages. The mid turbine frame includes a circumferential array of airfoils, and the airfoils each have a curvature provided equidistantly between pressure and suction sides. The airfoils extend from a leading edge to a trailing edge at a midspan plane along the airfoil. An angle is defined between first and second lines respectively tangent to the intersection of the plane and the curvature at airfoil leading and trailing edges. The angle is equal to or greater than about 10°, for example. In one example, an airfoil aspect ratio is less than 1.5.

Abstract: A compressor unit includes a motor and a compressor in a casing of a gastight form. The casing houses the motor and the compressor. The motor includes a rotor surrounded by a stator which has an encapsulation formed on the inner diameter as a separating can, so that a medium being handled does not damage the stator. The separating can includes a polymer matrix which is reinforced using a plurality of fibers. The polymer matrix is at least partly a ceramic fiber reinforced polymer matrix. The plurality of fibers are formed as continuous filaments. The continuous filaments include the length of at least 30 mm.