Abstract: A fan is provided herein, including a housing, a hub, and a plurality of blades. The housing includes a top case and a bottom case. The hub is rotatably disposed between the top case and the bottom case in an axial direction. The blades extend from the hub in a radial direction, located between the top case and the bottom case. Each of the blades has a proximal end and a distal end. The proximal end is connected to the hub. The distal end is opposite from the proximal end, located at the other side of the blade, having at least one recessed portion. Each of the recessed portions form a passage for air.

Abstract: The invention relates to a wind driven power plant comprising a nacelle having a nacelle cover and a helicopter hoisting platform, the nacelle further comprising a hatch extension and a hatch cover, the hatch extension being arranged between the nacelle cover and the hatch cover, wherein the hatch extension has a channel-like shape, wherein the hatch cover is mounted on top of the hatch extension, and wherein a the hatch extension provides a distance between the hatch cover and the nacelle cover.

Abstract: An aircraft engine apparatus (1) includes: a rotating shaft (6); a fan (10) driven by the rotating shaft; a fan case surrounding the fan; aircraft equipment (28) disposed upstream of the fan and, in a radial direction of the rotating shaft, disposed inward of a peripheral edge of the fan case; a casing (2) that accommodates at least part of the rotating shaft and supports the fan case; a first motive force transmitter (9) coupled to the rotating shaft and the fan; a second motive force transmitter (32) disposed inward of the first motive force transmitter in the radial direction of the rotating shaft and coupled to the rotating shaft and the aircraft equipment; and a support member (12) disposed between the first motive force transmitter and the second motive force transmitter, the support member coupling the casing and the aircraft equipment and supporting the aircraft equipment.

Abstract: The present invention provides a bladed rotor wheel for a gas turbine engine comprising at least a rotatable forged disc, the rotatable forged disc comprising a front surface and a back surface, at least one rim surface, and a plurality of projections located on at least a portion of at least one of the front or back surface and/or on the rim surface; wherein the projections are 3D printed features protruding outwards from the front, back and/or rim surface; the projections are arranged forming a pattern so that a heat transfer capability is created at the front, back and/or rim surface; and the ratio of the distance between projections to the forged disc external radius is lower than 0.15. Furthermore, the present invention also provides a method for manufacturing a rotatable forged disc for a bladed rotor wheel.

Abstract: An airfoil vane includes an outer ceramic wall that defines an airfoil section and a cavity that extends through the airfoil section. A jumper tube is disposed in the cavity for transferring cooling air. The jumper tube includes a wall, a through-passage circumscribed by the wall, and a thermal barrier coating disposed on the wall.

Abstract: An apparatus and method for forming an engine component for a turbine engine, the engine component comprising a wall bounding an interior; a panel portion defining a portion of the wall, the panel portion comprising: an outer wall; an inner wall spaced from the outer wall to define a wall gap; and a structural segment formed within the wall gap comprising at least one structural element. The method including calculating a factor and adjusting a variable until the factor is between a given range.

Abstract: The invention relates to a method for the application of heating mats (10) on a wing/blade of a wind power station or other devices for the purpose of achieving deicing also during operation when necessary. Temperature measurement and de-icing take place by means of pulsed current to the heating mat (10). The invention also relates to an arrangement.

Abstract: An anti-vortex tube (AVT) retaining ring and bore basket is provided and includes a unitary body having an inboard portion, an outboard portion and an intermediate portion. The inboard portion includes a first ring-shaped body with an outer diameter. The outboard portion is configured to support an array of AVTs and includes a second ring-shaped body with an inner diameter larger than the outer diameter of the first ring-shaped body. The intermediate portion includes a flange extending between the outer and inner diameters of the first and second ring-shaped bodies, respectively.

Abstract: A damper seal for a turbine blade of a gas turbine engine, the damper seal having: an upper portion; a first downwardly curved portion; and a second downwardly curved portion, the first downwardly curved portion and the second downwardly curved portion extend from opposing end regions of the upper portion, the upper portion having a length extending between the opposing end regions of the upper portion and a width transverse to the length, wherein the upper portion is curved along the entire width as it extends along the length.

Abstract: A gas turbine engine includes a shaft and a heatshield that circumscribes the shaft. The heatshield defines a cylindrical body that has radially inner and outer sides and extends between first and second axial ends. The heatshield is exclusively supported on the shaft at the first and second axial ends. The heatshield includes at least one seal member on the radially outer side. A damper member is disposed at the radially inner side of the heatshield for attenuating vibration of the heatshield.

Abstract: A rotor assembly is provided for a piece of rotational equipment. This rotor assembly includes a rotor disk, a rotor blade and a seal element. The rotor disk is configured to rotate about a rotational axis. The rotor disk extends axially along the rotational axis to a rotor disk end face. The rotor blade includes an attachment. The attachment attaches the rotor blade to the rotor disk. The seal element is configured to seal a gap between the rotor disk and the attachment. The seal element has a longitudinal centerline that extends along an interface between the rotor disk and the attachment at the rotor disk end face.

Abstract: An air blower enabling efficient cooling is provided. The air blower (1) includes: an impeller (3); and a motor (5), wherein the impeller (3) includes a plurality of first blades (32) and a cup (33) arranged at the inner periphery side d of the plurality of first blades (32), the motor (5) includes a housing (51) arranged inside the cup (33), a stator (73), and a rotor (52) arranged inside the stator, and an outer peripheral surface (41c) of the cup (33) is provided with an opening part (43) facing an outer peripheral surface (51c) of the housing (51).

Abstract: A rotating machine includes a plurality of rotors. Each of the rotors includes a rotor bore protruding radially inward from a platform. A ring shaped cover plate is interfaced with each rotor bore via at least one snap. The at least one snap includes a first arm extending from the cover plate and having a convex facing contact surface, and multiple second arms extending axially from each rotor bore and having contact surfaces facing the convex surface.

Abstract: The present invention relates to a rotor (1) of a turbomachine turbine, comprising a rotor disc (2) and a plurality of blades (3) distributed at its periphery, said rotor disc (2) comprising a plurality of mainly axial cells (23), each blade (3) comprising a root (32), retained in one of the cells (23) of said rotor disc, each root being dimensioned so as to form a space (4) between the bottom of the cell (23) and the radially inner face (324) of the root. This rotor is remarkable in that said root comprises a mainly axial blind hole (5) opening onto the upstream face of the root and a plurality of mainly radial air ejection orifices (6), each air ejection orifice (6) opening into said blind hole (5) and onto the radially inner face (324) of the root located facing the bottom of the cell (23).

Abstract: A jointed wind turbine rotor blade includes a first blade segment and a second blade segment. A chord-wise joint separates the first and second blade segments, wherein internal joint structure joins the first and second blade segments across the chord-wise joint. A first heating system is configured within the first blade segment, and a second heating system is configured within the second blade segment. A disconnectable coupling is configured between the first and second blade segments at the chord-wise joint to supply power or a fluid medium from the first blade segment across the chord-wise joint for use by the second heating system in the second blade segment.

Abstract: A blade tip assembly for a wind turbine blade, comprising a conductive blade tip module, a receptor arrangement spaced from the conductive blade tip module, a coupler that electrically couples the conductive blade tip module to the receptor arrangement and an insulating member that insulates the coupler. The invention also can be expressed as a method for assembling a blade tip assembly for a wind turbine blade, the method comprising providing a blade tip module; providing the blade tip module with a coupler for electrically coupling the blade tip module to a down conductor of a lightning protection system; and encasing the coupler with an insulating member.

Abstract: Shaft assemblies, turbomachines, and methods of servicing a turbomachine are provided. A shaft assembly includes a first shaft having a first rabbet annularly defined therein. The first rabbet includes a first axially extending face and a first radially extending face. A second shaft coupled to the first shaft. The second shaft includes a second rabbet annularly defined therein and positioned opposite the first rabbet. The second rabbet includes a second axially extending face and a second radially extending face. A patch ring is mounted between the first rabbet and the second rabbet. The patch ring includes a main body positioned between and in contact with the first axially extending face and the second axially extending face. A first arm extends radially outward from the main body, and a second arm extends radially inward from the main body.

Abstract: A stator vane for a steam turbine includes: a vane body having an airfoil cross section including a pressure-side partition wall having a concave surface shape and a suction-side partition wall having a convex surface shape, the vane body having a hollow section formed between an inner surface of the pressure-side partition wall and an inner surface of the suction-side partition wall; and a first division wall dividing the hollow section into a first hollow section positioned at a leading edge side and a second hollow section positioned at a trailing edge side. The first hollow section is configured to be supplied with a fluid, or as a sealed space, and a slit is formed on at least one of the pressure-side partition wall or the suction-side partition wall, the slit being in communication with the second hollow section.

Abstract: A multilayer protective covering can protect a surface from lightning strikes. The covering includes a bottom conductive layer affixed to the surface and having a first opening that is aligned with a grounding connection so that the grounding connection is exposed through first opening and not in contact with the bottom conductive layer. The covering also includes a dielectric layer affixed to the bottom conductive layer and having second opening aligned with the grounding connection so that the grounding connection is exposed through second opening and not in contact with the dielectric layer. The covering additionally includes a top conductive layer affixed to the dielectric layer and covering the grounding connection. The top conductive layer directs electrical current from a lightning strike on the surface to the grounding connection.

Abstract: A double ring axial seal for a disk and blade; the disk including an array of blade slots at a perimeter of the disk configured to receive a root portion of the blade, the blade includes a platform located between the root portion and an airfoil extending from the platform opposite the root portion, the platform including a receiver with an overhang proximate the root portion and the platform including a hook opposite the receiver proximate the root portion; a disk slot formed on a first side of the disk proximate the array of blade slots; a first axial seal ring coupled with the disk slot and the receiver; the first axial seal ring having a cutout proximate an outer perimeter of the first axial seal ring, the cutout sized to receive the overhang of the blade platform.

Abstract: A second outer surface (49ab) of a top plate (49) is recessed from a first outer surface (49aa) of the top plate (49) in the direction away from the inner peripheral surface (34a) of a turbine casing (34) so that a step (50) is formed between the second outer surface (49ab) and the first outer surface (49aa). At least part of the discharge opening (53B) of a cooling hole (53) is disposed in the second outer surface (49ab). The cooling hole (53) extends so as to be tilted relative to the second outer surface (49ab) so that the cooling hole (53) discharges a cooling medium to the upstream side of a combustion gas flowing between the second outer surface (49ab) and the inner peripheral surface (34a) of the turbine casing (34).

Abstract: A rotor shaft adapted to rotate about a rotor axis thereof. The rotor shaft includes a rotor cavity configured concentrically to the rotor axis inside the rotor shaft. The rotor shaft further includes a plurality of cooling bores extending radially outward from the rotor cavity to feed cooling air into an internal cooling system in a blade. Each cooling bore includes a bore inlet portion and a distal bore outlet portion. The respective bore inlet portion ends in a plateau, projecting above the outer circumference contour of the rotor cavity. Thus, cooling bore inlets are shifted to a low stress area and the lifetime of the rotor is improved.

Abstract: A gas turbine engine is provided, with a compressor section including a fan driven by an engine shaft about a rotation axis, the engine shaft defining a bore extending axially therethrough from a hot gas inlet to a hot gas outlet, the hot gas inlet located downstream of the compressor section, a nose cone mounted to the fan and defining a cavity therewithin, a first impeller and a second impeller mounted within the cavity, the first impeller having an inlet facing a forward direction of the gas turbine engine, the inlet of the first impeller in fluid flow communication with an air inlet defined in an outer surface of the nose cone, the second impeller having an inlet facing a rearward direction of the gas turbine engine, the inlet of the second impeller being in fluid flow communication with the hot gas outlet of the engine shaft.

Abstract: A gas turbine engine includes a fan rotor, a compressor section, a combustor section, and a turbine section. The turbine section is positioned downstream of the combustor section. A fan drive turbine in the turbine section, and a shaft connects the fan drive turbine to the fan rotor. An inlet duct is connected to a cooling air source and connected to a cooling compressor downstream of the fan drive turbine. The cooling compressor is connected to an air source, and connected to a turning duct for passing compressed air in an upstream direction through the shaft. A method is also disclosed.

Abstract: A sealing plate for sealing cooling passages in a cooled turbine blade of a gas turbine engine and directing and controlling air flow through cooling passages is provided.

Abstract: An axial flow rotating machine includes: a rotor; a plurality of vanes; and a medium flow modification member. Each of the vanes has an inner shroud and one or more seal fins. An annular groove, which is recessed toward a radially inner side, in which the inner shroud and the seal fins are placed in a non-contact manner, is formed at a rotor shaft. A distance from an end of the inner shroud on a furthest axially downstream side to a downstream-side groove side surface is a distance (L). A distance (Lf) from a most-downstream seal fin to a medium flow modification surface is equal to or less than the distance (L) in the axially downstream side.

Abstract: A wheel assembly for a gas turbine engine includes a disk, an annular coverplate, and an anti-rotation feature. The disk is adapted to receive blades and rotate about an axis during use of the gas turbine engine. The annular coverplate is coupled with the disk and adapted to block axial movement of the blades. The anti-rotation feature is coupled with the disk and the annular coverplate to resist rotation of the annular coverplate relative to the disk.

Abstract: A turbine, a gas turbine, and a method of disassembling turbine blades, capable of ensuring stable sealing performance as well as facilitating disassembly of turbine blades are provided. The turbine may include a rotor disk including a plurality of slots formed therein, a plurality of turbine blades spaced apart from each other by a predetermined distance in a circumferential direction of the rotor disk on an outer peripheral surface, each of the turbine blades being inserted into an associated one of the slots, and a retainer sealing a cooling passage defined between the rotor disk and the turbine blade, wherein the turbine blade includes an airfoil-shaped blade part, a root part inserted into the rotor disk, and a platform part located between the blade part and the root part, and the root part includes a blade hook protruding therefrom to support the retainer.

Abstract: A gas turbine engine and a blisk are disclosed, including methods of making the same. The blisk may include a disk, spars of airfoils, platforms, and shanks of the airfoils integrally formed as a unit. Such blisk features may be integrally formed by a casting process or additive manufacturing. The blisk includes cooled airfoils, such that the spar includes standoffs, and a cover panel is bonded to an outer surface of the standoffs to define passages between the cover panel and the spar. Cooling air is fed through an inlet port formed in a base standoff to the passages of the spar through a cooling feed channel defined in the disk or shank portion.

Abstract: A wheel assembly for a gas turbine engine includes a disk, a blade-attachment system, and a plurality of blades. The disk is configured to rotate about an axis during operation of the gas turbine engine. The blade-attachment system is configured to couple the plurality of blades with the disk for rotation therewith.

Abstract: A cooling system configured to cool aspects of the turbine engine between a compressor and a turbine assembly is disclosed. In at least one embodiment, the cooling system may include one or more mid-frame cooling channels extending from an inlet through one or more mid-frame torque discs positioned downstream of the compressor and upstream of the turbine assembly. The inlet may be positioned to receive compressor bleed air. The mid-frame cooling channel may be positioned in a radially outer portion of the mid-frame torque disc to provide cooling to outer aspects of the mid-frame torque disc such that conventional, low cost materials may be used to form the mid-frame torque disc rather than high cost materials with capacity to withstand higher temperatures. The cooling fluid routed through the mid-frame cooling channel in the mid-frame torque disc may be exhausted into a cooling system (10) for the downstream turbine assembly.

Abstract: An assembly according to an exemplary aspect of the present disclosure includes, among other things, a disk, a cover plate providing a cavity at a first axial side of the disk, a passageway including an inlet provided by a notch in at least one of the disk and the cover plate in fluid communication with the cavity, and the passageway extending from the inlet to an exit provided at a second axial side of the disk opposite the first axial side, the exit in fluid communication with the inlet, and the passageway configured to provide fluid flow from the cavity to the exit.

Abstract: A turbomachine blade including a hollow body defining a cavity, and including a downstream trailing edge. The blade further includes at least one hole which communicates with the cavity and which opens downstream onto the trailing edge. The trailing edge extends along the main radial direction of the blade, and including a downstream convex face. The blade is characterised in that each hole opens onto a planar rear face of a flat region formed in the trailing edge.

Abstract: A rotor blade assembly group for an engine with a ring-shaped or disc-shaped blade carrier having multiple rotor blades that are provided along a circle line about a central axis of the rotor blade assembly group, wherein the blade carrier has a carrier section that extends radially inwards in the direction of the central axis with respect to the rotor blades, the carrier section comprises a connection area, at which a stiffening structure with at least two, first and second, stiffening elements is fixedly attached, and the first stiffening element is arranged at a first face side of the blade carrier and the second stiffening element is arranged at a second face side that is facing away from the first face side. The first and second stiffening elements are connected to the connection area of the blade carrier and in addition are connected to each other.

Abstract: A rotor blade assembly group for an engine with at least one blade carrier having at least one rotor blade that is provided with multiple rotor blades along a circle line about a central axis of the rotor blade assembly group, wherein the blade carrier has a carrier section that extends radially inwards in the direction of the central axis with respect to the rotor blade, the carrier section comprises a connection area at which a stiffening structure with at least two, first and second, stiffening elements is fixedly attached, and the stiffening element is arranged at a first face side of the blade carrier, and the second stiffening element is arranged at a second face side that is facing away from the first face side. The blade carrier is formed in a ring-segment-shaped or disc-segment-shaped-manner.

Abstract: A spoolie manifold including two or more spaced apart caps including outlets and one pair of caps connected together in flow communication by a jumper tube assembly. Jumper tube assembly including a jumper tube having first and second spoolies attached to opposite ends of the jumper tube. Ends may be welded into counterbores of the spoolies having spherical spoolie ends press-fitted into first and second sleeves in bores in pair of the caps and sleeves retained in bores with retainer clips. A duct connected in flow communication to an inlet of one of the caps. Spoolie manifold may include three spaced apart caps including a distributor cap between two port caps connected in flow communication to distributor cap by jumper tube assembly. Cap outlets may be feed strut ports in casing of turbine frame including hub spaced inwardly from casing and having spaced apart hollow struts with strut ports.

Abstract: A turbine blade, installed on a rotor disk of a turbine and configured to rotate the turbine by a force of flowing gas, includes a root configured to be coupled to the rotor disk; a platform integrally formed with an upper portion of the root, the platform having opposite sides respectively extending in an axial direction of the rotor disk; an airfoil integrally formed with an upper portion of the platform; and an angel wing configured to be removably coupled to each of the opposite sides of the platform. When coupled, the angel wing protrudes from the platform in the axial direction. The turbine blade, which may be included in the turbine of a gas turbine, is capable of improving the castability and adjusting a clearance between an airfoil and a turbine rotor disk such that space between the airfoil and the turbine rotor disk can be reliably sealed.

Abstract: Cooling a wind turbine generator It is described an arrangement (100, 200) for cooling a generator mounted in a nacelle of a wind turbine, the arrangement comprising: a cooling air inlet (105) at an outer wall (1?7) of the nacelle (103) for introducing cooling air (109) into a space region (111) inside the nacelle; an inlet fan (113) downstream the cooling air inlet (105) configured to pressurize the introduced cooling air within the space region (111); a filter system (115) downstream the inlet fan (113) and separating the space region (111) from another space region (117) inside the nacelle (103), the other space (117) region being in communication with generator portions (119) to be cooled; a duct system (129) adapted to guide a portion (130) of cooling air (132) heated by exchange of heat from the generator portions to the cooling air into the space region (111).

Abstract: A method of manufacturing a coated turbine vane (34) comprises manufacturing a turbine vane (34) having a platform (44) and an aerofoil (42) extending from the platform (44), a curved transition (60) connects the platform (44) to the aerofoil (42) and a recess (64) is provided in the curved transition (60) from the platform (44) to the aerofoil (42). A bond coating (70) is deposited on the platform (44), the aerofoil (42), the curved transition (60) and the recess (64). A ceramic thermal barrier coating (72) is deposited on the platform (44), the recess (64) and the curved transition (60) by plasma spraying. The recess (64) reduces the size of the step due to the ceramic thermal barrier coating (72) and hence improves the aerodynamics of the turbine vane (34).

Abstract: A gas turbine casing with an internal heat exchange system. The gas turbine extends between an inlet section and an exhaust section and defines a downstream direction from the inlet section to the exhaust section. The casing includes a forward end, an aft end downstream of the forward end, a first exterior surface facing radially outward, a second exterior surface facing radially inward, and an internal body at least partially defined between the first exterior surface and the second exterior surface. The heat exchange system includes an inlet and an outlet formed in an exterior surface of the casing proximate the aft end, a supply bore extending upstream from the inlet through the interior body of the casing, and a return bore extending downstream to the outlet through the interior body of the casing.

Abstract: A turbine rotor disk for a gas turbine engine includes a disk rotationally disposed about a central axis. The disk includes a number of blade posts, tabs and slots circumferentially disposed about a rim portion of the disk. The tabs each include a blade post transition portion, a slope portion radially inward of the blade transition portion and a face portion radially inward of the slope portion. The blade posts, tabs and slots are circumferentially oriented about the rim portion such that a tab or slot is positioned radially inward of each blade post.

Abstract: A turbine rotor disk for a gas turbine engine includes a disk rotationally disposed about a central axis. The disk includes a bore, a rim and a web disposed radially between the bore and the rim. The rim includes a first radially outermost rim portion and a second radially outermost rim portion disposed radially inward of the first radially outermost rim portion. First and second blade posts are disposed proximate the first radially outermost rim portion and spaced circumferentially. First and second tabs are disposed proximate the second radially outermost rim portion and positioned radially inward of the first and second blade posts. A slot is disposed circumferentially between the first tab and the second tab. The first tab and the second tab have an axial profile that includes a blade post transition portion, a slope portion radially inward of the blade transition portion and a face portion radially inward of the slope portion.

Abstract: A securing device for a turbine blade wherein the securing device prevents the turbine blade from moving radially and axially and includes a retaining piece that includes a projection which extends into a recess in the root of the turbine blade and which prevents the blade from moving axially.

Abstract: A cooling structure for a turbine includes a plurality of disks configured to rotate integrally with blades, the disks being arranged along a rotational axis; and the disks have disk holes defined therein and arranged in a circumferential direction for supplying cooling air for cooling the blades to downstream disks. At least one of the disk holes is set such that, when a rotational direction of the disk is defined as a positive direction and a direction opposite the rotational direction is defined as a negative direction, an outlet absolute circumferential velocity vector which is a component in the rotational direction of a velocity vector of the cooling air at an outlet of the disk hole is smaller than an inlet absolute circumferential velocity vector which is a component in the rotational direction of a velocity vector of the cooling air at an inlet of the disk hole.

Abstract: The invention relates to a device for cooling and/or liquefying, at a low-temperature, a working fluid containing helium or consisting of pure helium. The device includes a working circuit provided with a compressor station and a cold box. The compressor station includes one or more compression stages, each using one or more compressors that include a compressor wheel rigidly connected to an axle that is rotatably mounted on bearings. The axle of each compressor is rotated by an output shaft of a motor via a gear mechanism placed in a mechanical housing including lubricating oil. Said device is characterized in that the inner space of the mechanical housing contains a gaseous atmosphere consisting of a gaseous mixture having a mean molar mass that smaller than the molar mass of the air.

Abstract: a gas turbine engine structure includes a body radially spanning an inner portion and an outer portion. The structure body includes a first passage interior to the structure body. The first passage includes a first opening on one of a radially outward edge and a radially inward edge of the structure, and a second opening on the other of the radially outward edge and the radially inward edge of the structure. A second passage is also included interior to the structure. The second passage is approximately aligned with the first passage, and is disposed between the first passage and one of the first surface and the second surface of the structure. The second passage insulates the first passage from heat transfer through one of the first surface and the second surface.

Abstract: A gas turbine engine and a blisk are disclosed, including methods of making the same. The blisk may include a disk, spars of airfoils, platforms, and shanks of airfoils integrally formed as a unit. Such blisk features may be integrally formed by a casting process or additive manufacturing. The blisk includes cooled airfoils, such that the spar is hollow, and a cover panel is bonded to an outer surface of standoffs to define passages between the cover panel and the spar. Cooling air is fed to the hollow spar through a cooling feed channel defined in the disk or shank portion.

Abstract: A turbine airfoil for a rotating blade or stationary nozzle vane includes an airfoil body including a leading edge and a trailing edge. A coolant supply passage extends within the airfoil body, and a coolant return passage extends within the airfoil body. A first trench is in an external surface of the airfoil body, the first trench extending to the trailing edge and being in fluid communication with the coolant supply passage. A second trench is in the external surface of the airfoil body, the second trench extending to the trailing edge and being in fluid communication with the coolant return passage and the first trench. A cover seats in the airfoil body and encloses the trenches to form coolant passages with the airfoil body. In embodiments, two coolant passages to and back from the trailing edge may be used to allow for a recycling flow.

Abstract: A turbine blade for a gas turbine engine may include an outer, peripheral wall extending along a suction side and a pressure side of the blade from a leading edge to a trailing edge of the blade and from a root end to a tip end of the blade, a substantially vertical bifurcating internal wall extending between the leading edge and the trailing edge of the blade in between the suction side and the pressure side of the blade, a plurality of pressure side cooling fluid passages defined between the peripheral wall on the pressure side of the blade and the bifurcating internal wall and extending at least part way from the root end to the tip end of the blade, and a plurality of suction side cooling fluid passages defined between the peripheral wall on the suction side of the blade and the bifurcating internal wall and extending at least part way from the tip end to the root end of the blade.

Abstract: A fan assembly for use in a gas turbine engine includes a fan wheel and a plurality of blades extending radially from the fan wheel away from a central axis of the fan assembly. Each of the blades includes a root coupled with the fan wheel and an airfoil extending radially outwardly from the root. The blades are adapted to rotate about the central axis to push air.