Abstract: Cooled exhaust hood plates are provided in areas of high velocity steam flow within an exhaust steam flow of a steam turbine. Coolant is directed within double walled exhaust hood plates to cool plate surfaces adjacent to the high velocity exhaust steam flow. The cooled exhaust hood plates cool and condense the exhaust steam in proximity. Condensation will occur in low velocity area near the exhaust hood plate to reduce the boundary layer and improve the flow through the hood, improving overall turbine performance.

Abstract: The guide device for the diffusor at the compressor impeller outlet of a radial compressor has guide blades with stepped inlet edges. The step is implemented by setting back the hub-side inlet edge. This meridional stepping divides the guide blades into two component blades, of which the first component blade is made longer than the second component blade. The set-back of the inlet edge of the hub-side component blade and the associated superposition of the noise fields which are produced on the front and rear inlet edge of the diffusor leads to improvement of the acoustic properties of the compressor.

Abstract: A two-phase, homogenizing or mixing stage for a centrifugal pump assembly homogenizes the fluids being circulated therethrough. The mixing stage produces high shut-in head pressure and a very high maximum flow rate. The mixing stage has a diffuser with fixed diffuser vanes that extend radially or tangentially at acute angles. The vanes may be curved in both the axial and radial directions to force fluids impinging thereon to have a radially inward component to create turbulence. The turbulence mixes and homogenizes the gas and liquid fluids to improve the overall performance of centrifugal pump assemblies that operate in two-phase fluids. The mixing stage also has an impeller adjacent the diffuser. The impeller vanes likewise extend radially and tangentially therefrom at acute angles and may be curved.

Abstract: A cooling fan comprises an impeller which includes 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 comprises a blade suction surface, and substantially the entire blade suction surface is visible from the forward looking aft direction.

Abstract: An exemplary compressor wheel housing for a turbocharger compressor wheel includes a substantially cylindrical shroud surface definable with respect to a radial dimension and an axial dimension along a rotational axis of a compressor wheel with an origin coincident with a z-plane of the compressor wheel wherein the axial position of the shroud surface decreases with increasing radial position to a compressor wheel blade outer edge radius and a diffuser surface extending radially outward and axially downward from the cylindrical shroud surface wherein the diffuser surface includes a minimum diffuser surface axial position at a radial position less than about 1.25 times the compressor wheel blade outer edge radius and wherein the diffuser surface includes a greater axial position at a radial position beyond that corresponding to the minimum axial position. Various other exemplary methods, devices, systems, etc., are also disclosed.

Abstract: An axial flow fan according to the present invention comprises an impeller which rotates about a central axis and including a plurality of blades, a hollow member accommodating therein the impeller, a base portion which is arranged at the hollow member and supports the base portion in a rotatable manner, a plurality of inner air guide members each connected to the base portion, and a plurality of outer air guide members each connected to the hollow member. The inner air guide members and the outer air guide members each include a first edge member and a second edge portion. A length of the first edge member and that of the second edge member of the outer air guide member are greater than those of the first edge member and the second edge member of the inner air guide member.

Abstract: In a transonic region with a Reynolds number not more than a critical Reynolds number, a flow velocity distribution on an extrados of an airfoil has a single supersonic maximum value within a range of up to 6% from a leading edge on a chord, or a shape factor has a maximum value in a region of 6 to 15% from the leading edge on the chord, the value being nearly constant in a region of 30 to 60% and gradually can increase up to 2.5 in a region downstream of 60% of chord. A pressure loss in a low Reynolds number region can be drastically reduced, while conventionally keeping low the pressure loss in a high Reynolds number region. Moreover, this pressure-loss reduction effect in the low Reynolds number region is exerted even if an inflow angle is changed in a wide range.

Abstract: In accordance with at least some embodiments, a single rotor ducted fan is disclosed. The single rotor ducted fan comprises a duct having an intake diameter and an impeller having a hub with blades that extend radially from the hub. The blades have a maximum tip diameter. The bellmouth diameter is less than the maximum tip diameter.

Abstract: A ducted fan for a VTOL vehicle includes a substantially cylindrical duct having an inlet at an upper end and an outlet at a lower end, and an air mover unit located within the substantially cylindrical duct. The duct also includes inner and outer wall portions and a substantially annular upper lip connecting the inner and outer wall portions, thus defining the inlet. The substantially annular upper lip has opposed fore and aft portions and opposed side portions and is provided with at least first and second openings, respectively, at each of the opposed side portions. The first and second arrays of openings permit flow of air into at least first and second respective chambers formed within the duct, the first and second chambers connected by at least one passageway to thereby enable substantial equalization of surface pressure at the opposed side portions of the substantially annular upper lip.

Abstract: Miniature (mesoscale) axial-flow pumps including an inlet guide, a stator spaced apart from the inlet guide, and a rotor rotatably disposed between the inlet guide and the stator.

Abstract: A centrifugal compressor having a wide operating range, being economically efficient and high reliability in terms of a stable operation is provided. A centrifugal compressor including a partition wall for dividing a flow channel in the diffuser section and the volute section into a plurality of channels in the direction of circulation of the fluid so as to define a hub-side flow channel and a shroud-side flow channel; and a flow rate adjusting valve for lowering the flow rate of the fluid flowing in the shroud-side flow channel to increase the flow rate in the hub-side flow channel when the flow rate of the fluid compressed by an impeller is low and not lowering the flow rate of the fluid flowing the shroud-side flow channel to allow the fluid to flow both in the shroud-side flow channel and the hub-side flow channel when the flow rate of the fluid compressed by the impeller is high is employed.

Abstract: A bucket for a turbine is described. The bucket includes a dovetail portion configured to couple the bucket to a turbine wheel, the dovetail portion having a lower surface. The bucket also includes a shank portion that extends from the dovetail portion and an airfoil having a root and a tip portion, an airfoil shape, and a nominal profile substantially in accordance with Cartesian coordinate values of X, Y, and Z set forth in Table I. The bucket also includes a plurality of cooling passages. The plurality includes no more than five cooling passages that extend between the root and the tip portion of the airfoil. Each of the cooling passages exits the airfoil at the tip portion, the plurality of cooling passages are positioned in a camber line pattern.

Abstract: Due to variations arising during manufacturing, axial fans often are slightly imbalanced, resulting in noise during operation, which is undesirable in many contexts, for example when the fan is used for ventilation purposes in a motor vehicle. A fan with improved vibration and noise damping can be achieved by elastically suspending the fan wheel within a first ring formed of a hard plastic, the first ring having a tubular extension formed of a softer plastic, and serving to mechanically connect the first ring to a surrounding annular carrier part. Optionally, the first ring and extension unit can include a spring element. Preferably, the first ring and tubular extension are produced by a multi-component forming technology such as two-plastic technology. The fan is preferably driven by an electronically commutated motor (ECM).

Abstract: A centrifugal blower having at least one radial plane dividing its scroll into sub-sections which may vary as to cut-off points and axial and radial dimensions as well as axial displacement to meet requirements of individual application system flow paths.

Abstract: A gas turbine transition duct apparatus is provided comprising first and second turbine transition ducts and a strip seal. The strip seal may comprise a sealing element and a spring structure.

Abstract: There is provided an axial flow compressor that improves reliability on an increase in a blade loading on a last-stage stator vane of the axial flow compressor due to a partial load operation of a gas turbine. An annular flow passage is formed by a rotor having multiple rotor blades fitted thereto and a casing having multiple stator vanes fitted thereto, two or more of the stator vanes are disposed downstream of a last-stage rotor blade that is the rotor blade disposed. at the most downstream side in a flow direction of the annular flow passage, a blade loading on a first stator vane disposed at the most upstream side is set to be smaller than a blade loading of a second stator vane disposed downstream of the first stator vane by one row.

Abstract: A turbomachine includes a housing, and a plurality of turbomachine nozzles. At least one of the plurality of turbomachine nozzles includes a body having a first surface and an opposing second surface that extend between a first end and a second end. At least one of the first and second surfaces includes a profile having an angle of between about 3° and about 8° between a first line passing through the first end and a first position located between about 28% and about 38% from the first end and a second line passing through the first position and a second position located between about 53% and about 63% from the first end, and an angle of between about 10° and about 20° between the second line and a third line passing through the second position and a third position located between about 74% and about 84% from the first end.

Abstract: A fan apparatus includes an impeller, a motor rotating the impeller, a plurality of stator blades arranged opposite to the impeller in an axial direction. The stator blades each include a curved portion at which the stator blades each are curved with respect to the direction in which the stator blades extend.

Abstract: Second-stage nozzles have vanes including airfoil profiles substantially in accordance with Cartesian coordinate values of X, Y and Z set forth in inches in Table I with the X, Y and Z values commencing at the radially innermost aerodynamic section of the airfoil and then made relative to that section for the Z coordinate values. The X, Y and Z values may be scaled as a function of the same constant or number to provide a scaled-up or scaled-down airfoil section for the nozzle.

Abstract: A laminate air seal for a gas turbine engine includes at least one fabric layer made of fiberglass, ceramic fiber, basalt and/or carbon, and a polymeric resin that is stable at an operating temperature of the gas turbine engine. The resin may be preimpregnated into the fabric layers, or introduced into the fabric during assembly and formation of the laminate. The resin may be polyimide, bismaelimide (BMI) or cyanate ester. A particular resin selected may depend, in part, on the operating temperatures in that region of the gas turbine engine. In some embodiments, the laminate seal may include a coating to increase lubricity of the seal. In one embodiment, the laminate air seal is used to seal a gap between a pylon fairing and an exhaust nozzle of the turbine engine.

Abstract: The present invention relates to a hydraulic pump (10) hydraulic portion body (1) capable of cooperating with a pump electric motor body (1c), said hydraulic portion body (1) including a pre-filter body (1a) comprising: an upper portion (2), and a lower portion (3), and said upper portion (2) and lower portion (3) of said pre-filter body being independent of each other and mounted in a sealed (6a) removable attachment (6b, 6c), the orientation of both of said upper portions (2) and lower portion (3) of the pre-filter body relatively to each other being adjustable in rotation relatively to each other according to several positions, preferably in at least 3 different positions, still preferably at least 4 different positions, still preferably according to any position.

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: A discharge diffuser that includes: a forward section and a dump cavity, the forward section being configured to direct discharge from the compressor to the dump cavity; an inner diffuser wall that defines an inner radial flowpath of the upstream section; and an outer diffuser wall that defines an outer radial flowpath of the upstream section; wherein at an aft lip of the inner diffuser wall, the discharge diffuser comprises an overhanging step.

Abstract: A centrifugal air blower guides returning air from a fan rotated by a rotational drive source out of interference with air delivered by a fan. The centrifugal air blower includes a rotational drive source having a rotational drive shaft, a housing including a holder which holds the rotational drive source in surrounding relation thereto, and a fan coupled to the rotational drive shaft of the rotational drive source. The housing has a disk-shaped flange extending from the holder, and the flange has a plurality of air guides disposed on a surface thereof and extending toward a peripheral edge of the flange.

Abstract: A guiding device (2) includes a base (21), a cover (23) and a sidewall (22) cooperatively defining an annular space therein and a passage therethrough. An air inlet (221) is defined in the sidewall communicating with the space for an airflow flowing into the space. A plurality of guiding plates (24) are arranged in the space around the passage. An air outlet (29) is defined between two neighboring guiding plates for the airflow flowing out the space into the passage. The airflow is distributed into a plurality of even streams by the guiding plates. An atomizer (4) is connected with the space via the air inlet. The atomizer produces a high-pressured water vapor which is taken by the airflow to cool an aluminum profile produced by an extrusions press (6) and moving through the passage.

Abstract: A fan assembly for creating an air current is described. The fan assembly includes a nozzle mounted on a base housing a device for creating an air flow through the nozzle. The nozzle includes an interior passage for receiving the air flow from the base, a mouth through which the air flow is emitted, the mouth being defined by facing surfaces of the nozzle, and spacers for spacing apart the facing surfaces of the nozzle. The nozzle extends substantially orthogonally about an axis to define an opening through which air from outside the fan assembly is drawn by the air flow emitted from the mouth. The fan provides an arrangement producing an air current and a flow of cooling air created without requiring a bladed fan. The spacers can provide for a reliable, reproducible nozzle of the fan assembly and performance of the fan assembly.

Abstract: A turbomachine exhaust casing with connection roots between the structural arms of the casing and the annular endplates of the hub of the casing, each of said the roots having a profile that is optimized so as to reduce the level of stress in the connection portions, and thus increase the lifetime of the exhaust casing.

Abstract: A heat dissipating fan structure of a dual motor includes: a base device, having a fan base, and the fan base having a fan motor; a fan, connected and rotated by the fan motor, and the fan having a plurality of vanes; a support frame device, installed at the fan base, and having a frame-fan motor; a frame-fan device, connected and rotated by the frame-fan motor, and having a frame-fan frame, and a plurality wing plates disposed around the frame-fan frame, and the wing plates being disposed around the external periphery of the fan and perpendicular to the vane, so that the plurality wing plates on the frame-fan base can produce an auxiliary airflow to increase the airflow of the fan and give a better heat dissipating effect.

Abstract: An air guide apparatus includes a body installed at a discharge side of a rotary fan for sucking air, a plurality of first vanes arranged at one surface of the body to guide air sucked by the rotary fan toward the outer circumferential surface of the body, and a plurality of second vanes arranged on the other side of the body to guide air which has been guided by the first vanes from the outer circumferential surface of the body toward a central portion, formed in a spiral shape from the central portion of the body toward the outer circumferential surface of the body, and having disconnected portions formed at middle portions thereof.

Abstract: A centrifugal turbomachinery in accordance with the present invention can lower a fluid loss in a return flow path. In the centrifugal turbomachinery, a plurality of centrifugal impellers is attached to a rotating shaft, and the centrifugal turbomachinery is provided with a diffuser having a plurality of blades introducing a fluid boosted by a front stage impeller to a rear stage impeller, and a return flow path means. The return flow path means has a side plate arranged in a back surface side of the front stage impeller, a plate opposing the side plate and arranged in a front surface side of the rear stage impeller, and a plurality of blades arranged between the side plate and the plate so as to be spaced in a peripheral direction. A maximum diameter portion of the side plate is changed in the peripheral direction.

Abstract: An airfoil with turning flow comprises a first surface, a second surface, a leading edge and a trailing edge. The first and second surfaces extend from the leading edge to a trailing edge. A chord extends from a midpoint of the leading edge to a midpoint of the trailing edge, defining a duct angle of at least fifteen degrees with respect to a turbine axis. An axial length of the chord defines an aspect ratio of at most one with respect to an average radial span of the leading and trailing edges. In a region of the trailing edge, an axial angle is at most four degrees and a circumferential angle is at most ten degrees, where the circumferential angle is defined in a direction opposite the turning flow.

Abstract: An internal heating arrangement for a centrifugal impeller for a gas turbine engine is provided having at least one heating passage extending through into the rotor for directing air bled from the rotor exit along the backface and forwardly through the impeller.

Abstract: A straightener blade for a turbomachine, comprising a platform arranged at a radially external end of the blade and adapted to be engaged in a annular groove of a housing, and a threaded rod radially extending outwardly from the platform and adapted to pass through an orifice of the housing in order to receive a fixing nut, the upstream and downstream edges of the platform each comprising a protrusion extending in the plan of the platform in order to limit the rotation of the platform in the groove when the nut screwed on the threaded rod is tightened.

Abstract: Gas turbine systems having flexible chordal hinge seals are provided. According to an embodiment, a turbine system comprises: a nozzle segment comprising a stator vane extending between an inner band segment and an outer band segment; an inner support ring adjacent to the inner band segment; and an inner chordal hinge seal in operable communication with the nozzle segment, the inner chordal hinge seal comprising a flexible inner rail extending inwardly from the inner band segment, the inner rail having a projection for sealingly engaging the inner support ring.

Abstract: A pump stage is disclosed for use with an electrical submersible pump. The stage includes an impeller and diffuser, each having a hub, blades and an outside ring. In such pump stage, the stage flow area is constructed from separate segments manufactured from wear resistant material. Furthermore, each separate segment is retained by the hub using an external compression fit ring.

Abstract: A diffuser for a turbo machine, such as an exhaust diffuser for an industrial gas turbine engine, the diffuser including a plurality of struts connecting the inner shroud of the diffuser to the outer shroud, where the struts have trailing edges with a step shape to reduce the losses and improve the performance of the diffuser. The stepped shaped trailing edge includes three or more steps with the middle step being the longest in the chordwise direction and the remaining steps being symmetric about the chord of the strut.

Abstract: A fan structure, suitable for rack-mounting adjacent to heat-generating electrical equipment, features an improved noise-damping outflow baffle containing a plurality of non-return flaps, serving to prevent reverse flow of air when fan activity is interrupted. In a preferred embodiment, four generally sickle-shaped flaps are used, each connected, along a straight edge thereof, by a pair of elastomeric hinge connections to a surrounding frame. The hinge connections urge the flaps closed whenever they are not forced by airflow into an open orientation. The axes of rotation of the flaps are chosen to keep them from jamming against one another. Since the flaps act as vanes, tending to straighten out an originally helical flow of air induced by the fan, they minimize the pressure drop which has therefore been associated with outflow baffles. The use or elastomers at critical points in the structure reduce noise and clatter.

Abstract: A centrifugal pump with a volute and at least one stage with an associated impeller and removable diffuser assembly comprises: multiple diffuser segments, each diffuser segment comprising a central passage from an inner curvilinear surface to an outer curvilinear surface and a curvilinear leading engagement surface between a leading end of its curvilinear inner surface and its curvilinear outer surface; multiple curvilinear volute mounting surfaces within the volute, each curvilinear mounting surface receiving a corresponding diffuser segment to mount the diffuser segments in a generally annular pattern about the impeller to form the removable diffuser assembly, with the curvilinear inner surface of each diffuser segment proximate an outer periphery of the impeller and the curvilinear leading engagement surface of each diffuser segment engaging a trailing portion of the curvilinear outer surface of an adjacent one of the diffuser segments; and a volute connecting passage within the volute for coupling the cen

Abstract: Provided is a centrifugal compressor having improved operation performance to improve durability. The centrifugal compressor includes an impeller connected to a rotary shaft and configured to radially eject a fluid suctioned in an axial direction upon rotation thereof; a shroud configured to cover front and rear sides of the impeller and having a suction port formed to face one surface of the impeller at a center of one side thereof; a volute chamber formed at an outer periphery of the shroud in a circumferential direction thereof and configured to guide the fluid ejected by the impeller to an ejection port; and a regulator installed at one side of the shroud and configured to selectively communicate a space formed at the other surface of the impeller with the outside.

Abstract: On a turbofan engine, at least one of the downstream guide vanes (1) of the downstream guide vane assembly (2) arranged behind the fan in the bypass duct, and a fairing element (3) arranged behind a downstream guide vane, are provided as a combined—one-piece and aerodynamically shaped—vane and fairing element (4) functioning as both a downstream guide vane and a fairing element for installations arranged in the bypass duct or an aerodynamically shaped supporting strut. The one-piece configuration of a fairing element with upstream vane, i.e. the integration of fairing elements provided with a specific outer contour into the downstream guide vane assembly, results in lower pressure losses and reduced fuel consumption as well as reduced pressure effect on the fan and, consequently, increased operating stability of the fan, higher fan efficiency and reduced sound emission.

Abstract: Tip shrouds on last stage buckets for condensing steam turbines may create significant blockage and form a vortex at the wall of the steam guide of the diffuser, causing the steam flow to separate from the wall of the steam guide. Vortex formation reduces the effective flow area for the remaining fluid to diffuse, causing poor recovery. An inward radial depression is provided of a predetermined depth and distance along an outer steam guide, which redirects the tip leakage flows slightly downward, reducing a shroud blockage effect. This deflection assists the main flow in rejoining the steam guide, thereby making the diffuser more effective.

Abstract: A turbine exhaust system includes an exhaust hood inner casing that involves the turbine rotor; an exhaust hood outer casing that forms an exhaust hood, together with the exhaust hood inner casing; a flow guide that forms an annular diffuser flow path; and exhaust hood upper part flow guides each of which serves as means for separating annular plane upper part exhaust steam within a range including a vertical upward flow out of exhaust steam radially discharging from the flow guide into the exhaust hood, from other exhaust steam, to thereby introduce the separated steam to the condenser, wherein exhaust steam introduction-side end faces thereof are located further toward the upper side than the horizontal plane containing the central axis of the turbine rotor.

Abstract: A heat dissipation fan includes a housing, a first rotor, a second rotor, a base and a plurality of static blades. The first rotor has a shaft and a plurality of rotor blades. The second rotor is coupled to the first rotor and has a plurality of rotor blades. The base is disposed in the housing for supporting the first and second rotors. The static blades are disposed between the housing and the base, wherein a rear portion of each static blade extends along an axial line of the heat dissipation fan for improving the working efficiency of the second rotor.

Abstract: An aero acoustic fan assembly is provided and generally includes a fan wheel, a frame, and first and second air outlet diffusing structures. The fan wheel generally, and typically includes an axial air inlet delimited by an air inlet cone, an annular air outlet, a back plate, and front plate opposite the back plate. The frame within supports the fan wheel for rotation about a central axis thereof. The first air outlet diffusing structure is supported by a portion of the frame, adjacent the back plate of the fan wheel and includes a peripheral region. The second air outlet diffusing structure is similarly supported by a portion of the frame, adjacent the front plate of the fan wheel, and also includes a peripheral region, air exiting the annular air outlet of the fan wheel passing between the peripheral regions of the diffusing structures.

Abstract: A Mixer/Ejector Wind Turbine (“MEWT”) system is disclosed which routinely exceeds the efficiencies of prior wind turbines. In the preferred embodiment, Applicants' MEWT incorporates advanced flow mixing technology, single and multi-stage ejector technology, aircraft and propulsion aerodynamics and noise abatement technologies in a unique manner to fluid-dynamically improve the operational effectiveness and efficiency of wind turbines, so that its operating efficiency routinely exceeds the Betz limit. Applicants' preferred MEWT embodiment comprises: an aerodynamically contoured turbine shroud with an inlet; a ring of stator vanes; a ring of rotating blades (i.e., an impeller) in line with the stator vanes; and a mixer/ejector pump to increase the flow volume through the turbine while rapidly mixing the low energy turbine exit flow with high energy bypass wind flow.

Abstract: A fan assembly for creating an air current includes a bladeless fan assembly including a nozzle and a device for creating an air flow through the nozzle. The nozzle includes an interior passage and a mouth receiving the air flow from the interior passage. A Coanda surface located adjacent the mouth and over which the mouth is arranged to direct the air flow. The fan provides an arrangement producing an air current and a flow of cooling air created without requiring a bladed fan, that is, the air flow is created by a bladeless fan.

Abstract: An airfoil diffuser for a centrifugal compressor formed by a diffuser passage area and a plurality of diffuser blades located within the diffuser passage area. The diffuser passage area is defined between a hub plate and a shroud of the centrifugal compressor. Each of the diffuser blades has a twisted configuration in a stacking direction as taken between the hub plate and an outer portion of the shroud located opposite to the hub plate. As a result of the twisted configuration, the diffuser blade inlet blade angle decreases from the hub plate to the outer portion of the shroud and solidity measurements at leading edges of the diffuser plates vary between a lower solidity value measured at the hub plate of less than 1.0 and a high solidity value measured at the outer portion of the shroud of no less than 1.0.

Abstract: A turbine rim cavity seal with a variable gap clearance control in a gas turbine engine. A stator vane includes an inner shroud with an inter-stage sealing housing extending inward and separating a front rim cavity from an aft rim cavity. Front and aft rotor disks are located on the sides of the stator vane and include labyrinth seal teeth extending upward to form a seal with an abrasive material supported on the underside of the housing cavity. The abrasive material includes a slanted sealing surface. A hydraulic actuator moves the rotor disks in an axial direction to control the seal gap and regulate the purge air flow into the front rim cavity and leakage flow through the seal into the aft rim cavity. In another embodiment, the sealing surface is stepped as well as slanted.

Abstract: A nozzle assembly for directing cooling fluid in a vane comprising a hollow airfoil containing at least two cooling chambers. The chambers are separated by a generally radial rib. A metering plate mount is attached to the rib. A metering plate, having at least one aperture for tuning the cooling fluid flow within the airfoil, is adjacent the metering plate mount.

Abstract: A stator vane for a gas turbine engine having a cooling circuit that passes through the airfoil and both of the inner and the outer diameter endwalls to provide cooling for the airfoil and endwalls. Each endwall includes an intricate cooling circuit and is connected to the serpentine flow circuit within the airfoil to pass cooling air back and fourth from one endwall to the other through one of the legs in the serpentine flow circuit of the airfoil. A row of exit cooling holes is located in one or both of the endwalls and is connected to the last leg of the serpentine circuit to discharge cooling air. The airfoil and endwalls cooling circuit forms a series of passages that meander through the vane before discharging out through the exit holes.