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: A bi-directional flow impulse type turbine arrangement (120) for use with a bi-directional reversing flow (F, F1, F2), and in particular for use with an oscillating water column power plant (110). The turbine arrangement (120) has a rotor (120), and first and second sets of guide vanes (140, 142) located on an opposite axial sides of the rotor (132) for directing the bi-directional reversing flow (F, F1, F2) to and from the rotor (132). The guide vanes (140, 142) are disposed at a greater radius and radially offset from the rotor blades (136). The turbine arrangement further comprises first and second annular ducts disposed respectively between the first and second sets of guide vanes (140, 142) and the rotor (132) for directing fluid from the guide vanes (140, 142) to the rotor blades (136).

Abstract: Disclosed are examples of flow-directing elements, airfoil inserts, and assemblies thereof. A flow-directing element has an inner buttress with an airfoil extending outwardly therefrom. The airfoil includes a cavity that extends within the airfoil to an exit port disposed in the inner buttress. A shelf disposed about the buttress defines the exit port, and the shelf includes a discourager extending into the cavity. An airfoil insert has a tubular body, with an outlet at one end. A plate affixed to the body at the outlet partially blocks the outlet, and includes a tab extending away from the body and defining a portion of an outlet periphery. Upon assembly of the flow directing element and the insert, the tab interacts with the discourager to direct a coolant to the exit port while restricting leakage of the coolant back into the cavity, between the airfoil insert and the flow-directing element.

Abstract: A flow machine having a housing, an axial diffuser, a rotor for deflecting a fluid between an axial direction and a radial direction, a spiral, and an axial diffuser insert which is at least partially received in the housing. A spiral contour is formed in the diffuser insert and, together with the housing, defines the spiral.

Abstract: Various fluid turbine systems and methods are described. The turbine can be a vertical axis wind turbine configured to generate power from wind energy. The turbine system can have a blade assembly. The blade assembly can have a plurality of blades rotatable about an axis. The turbine system can have a concentrator positionable upwind and in front of a return side of the blade assembly. The concentrator can define a convex surface facing the wind. The turbine system can also have a variable concentrator positionable upwind of a push side of the blade assembly. The variable concentrator can be adjustable between a first position and a second position, the variable concentrator being capable of deflecting more wind toward the turbine in the first position than in the second position.

Abstract: A rotary pressure transfer device utilizes a multi-channel, generally cylindrical rotor (15) that revolves with its flat end faces juxtaposed with flat end surfaces of a pair of flanking end covers (19, 21) in which inlet and outlet passageways are provided. The design is such that there are only oblique ramps (65) in the passageways on the high pressure side which create directional flow of liquid to cause rotor revolution in the desired direction. Passageways (27a, 27b) on the low pressure side may be shaped so that there is essentially axial or longitudinal flow entry and discharge of liquid between the channels and the passageways, or passageways (71) may be constructed to create directional flow that slightly retards rotor revolution in such desired direction.

Abstract: This invention relates to a fixture for use in a physical vapor deposition coating operation which comprises a support structure 14 comprising a circular base member 10, a circular top member 11 opposite the circular base member 10, and a plurality of structural members 12 joining said top member 11 to said base member 10; a plurality of panel members 13 aligned in a vertical direction around the outer periphery of said support structure 14 forming a cylinder-like structure; said panel members 13 including a plurality of apertures for holding workpieces 19 and 35 to which a coating is to be applied; and said apertures positioned on said panel members 13 so that said workpieces 19 and 35 are aligned in a staggered vertical direction. This invention also relates to a method for simultaneously coating a plurality of workpieces 19 and 35, such as gas turbine compressor blades and vanes, with erosion resistant coatings using the fixture of this invention.

Abstract: A guide vane arrangement 20 for a gas turbine engine (10, FIG. 1) includes a vane member 21 extending between inner and outer platforms 22, 24 which are respectively mounted on inner and outer mounting members 42, 34. One of the inner and outer platforms 22, 24 includes a resilient that abuts the respective inner or outer platform 22, 24 to permit relative movement between the inner or outer platform 22, 24 and the respective inner or outer mounting member 42, 34.

Abstract: A gas turbine engine nozzle is described. The gas turbine engine nozzle includes at least one nozzle vane having a first end and a second end. The first end is coupled to an inner sidewall and the second end is coupled to an outer sidewall. The gas turbine engine nozzle also includes at least one stress relief pocket defined within at least one of the inner sidewall and the outer sidewall proximate to the at least one nozzle vane. The at least one stress relief pocket is configured to reduce stress on the proximate nozzle vane.

Abstract: An air plenum is configured to direct air into a centrifugal compressor impeller in an ACM compressor. The air inlet plenum has a cylindrical outer wall, a forward circular end wall, and a rearward circular end wall. An air inlet radially extends from the cylindrical outer wall and is in flow communication therewith. An aperture in forward circular end wall is configured to seal receive about a rotating shaft. An aperture in rearward circular end wall is configured to receive the rotating shaft and allow air flow therethrough about the rotating shaft. A rectangular baffle extends radially inward from the cylindrical outer wall at a circumference thereof opposite the air inlet. The rectangular baffle may extend between the forward and rearward end walls.

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 centrifugal fan includes a space in which the dimension between a shroud-facing wall and a shroud, from the outer peripheral side to the inner peripheral side of the shroud, is substantially uniform, wherein the shroud-facing wall includes a recess extending in the circumferential direction, the recess being disposed at the inner peripheral side of the outer peripheral end of the shroud-facing wall forming the space having the uniform dimension so that the recess forms a space larger than the other part.

Abstract: The present invention provides a hybrid turbomachinery component for use in a gas turbine engine. The hybrid turbomachinery component may be operative to direct the working fluid of the gas turbine engine and/or addi energy to the working fluid and/or extract energy from the working fluid. One or more portions of the hybrid turbomachinery component are made from one material, and other portions of the hybrid turbomachinery component are made from another material.

Abstract: A method of tuning a compressor stator blade, having a base portion and an airfoil portion, to achieve a desired natural frequency, comprising: a) identifying the natural frequency of the compressor stator blade; b) determining a different target natural frequency for the compressor stator blade; and c) removing material from at least one of the side surfaces of the base portion of the compressor stator blade in an amount and in a configuration that achieves the target natural frequency.

Abstract: A vane assembly configured for turning a flow in a gas turbine engine includes a stationary main guide vane and an additional guide vane, wherein a leading edge of the additional guide vane is positioned upstream of a leading edge of the main guide vane and wherein the additional guide vane extends a distance along the main guide vane towards a trailing edge of the main guide vane forming a passageway between the additional guide vane and the main guide vane.

Abstract: An airfoil has a hollow shell providing external airfoil surfaces, and a corrugated core within the shell. The core contacts inner surfaces of the shell to support the shell. The airfoil is formed by consolidating a hollow shell pre-form and a corrugated core pre-form. At least a part of the hollow shell has a leading edge shell portion and/or a trailing edge shell portion which, before consolidation of the pre-forms, is a unitary body having a shape which wraps around the respective edge.

Abstract: A guide vane for a gas turbine includes a vane body having a leading edge and a trailing edge and a shroud extending at least between the leading edge and the trailing edge. The shroud has a first side wall and a second side wall extending essentially radially and in a longitudinal direction of the gas turbine. The first side wall has a groove disposed in a region of the trailing edge extending in a longitudinal direction of the shroud and is configured to receive a sealing plate. The first side wall also has a clearance extending from the groove in a region of the trailing edge, wherein a depth of the clearance in a circumferential direction of the gas turbine is equal to a depth of the groove, and wherein a width of the clearance in the longitudinal direction of the shroud is between one to three times the depth of the clearance.

Abstract: A ferrule of a stator with blades of an axial turbomachine consists of at least two segments having the general form of an arc of a circle and intended to be arranged end to end, so as to form the ferrule, where each segment contains on its outside a plurality of openings arranged at regular distances along the general arc of the circle of the segment, into each of which fits the end of a blade of the stator. Each end of a segment possesses a section of which the profile essentially corresponds with that of the end of the corresponding blade when the segment is placed on the blades of the stator, such that the joint between two adjacent segments corresponds with the profile of the corresponding blade.

Abstract: An annular circulation chamber is arranged in an interior of a compressor housing, which circulation chamber radially surrounds a main flow duct and extends from an intake region to an encircling circulation opening in a region of rotor blades of the compressor wheel. Between the circulation openings, the circulation chamber is delimited from the main flow duct by an annular contoured wall. The contoured wall is connected to the inner compressor housing by plural struts which are spaced apart from one another to different extents in the circumferential direction. As a result of the irregular distribution of the struts in the circumferential direction, generation of undesired vibration excitations can be reduced and/or eliminated.

Abstract: An aircraft engine comprising a compressor and at least one turbine is disclosed. The compressor and the turbine are each provided with vanes, each of which has a blade that forms a suction side and a pressure side, where at least one first of the blades is coated with a protective layer in order to reduce the erosion or wear. The layer is applied such that at least two areas are formed that adjoin each other at a boundary line. The first area has a protective layer that has a substantially constant first thickness and the second area is free of the protective layer or has the protective layer with a substantially constant second thickness, the second thickness differing from the first thickness. The boundary line has at least two points, of which the connecting line differs from the course of the boundary line between the two points.

Abstract: A fan includes a fan housing and an impeller. The fan housing includes a frame, a base disposed in the frame, a plurality of stationary blades disposed between the frame and the base, and a plurality of airflow-guiding elements extending inward from the frame and toward the base. The airflow-guiding elements and the stationary blades are alternately arranged. The impeller is disposed in the fan housing.

Abstract: The invention relates to a semi-finished product for producing a repaired blade for a gas turbine. Said semi-finished product comprises a first part (10) and a second part (12) firmly connected to the first part (10), the first part (10) having at least one recess (18) into which the second part (12) projects. The invention also relates to a method for repairing a blade of a gas turbine. Said method comprises the following steps: applying a first part (10) and making a recess (18), especially a groove (18) into said first part (10); applying a second part (12); inserting the second part (12) into the first part (10) in such a manner that the second part (12) or at least one section of the second part (12) projects into the recess (18) or groove (18); and connecting, especially welding, the first part (10) to the second part (12) in such a manner that the first part (10) and the second part (12) are non-detachably interconnected after said connection.

Abstract: A vane for a gas turbine engine comprising a cap arrangement comprising a cap insert and a cap adapted to receive the insert, the cap insert comprising a wall defining a through passage from top to bottom of the cap insert for receiving a cable or the like therethrough, the wall comprising a slot with a convoluted profile. Also a vane for a gas turbine engine comprising a cap and a cap insert as described.

Abstract: A pump assembly and components therefor including an impeller which has flow inducer elements on an inner surface of a front shroud thereof, a flow directing device or strainer having passageways for delivering material to the impeller and at least one flow circulating passageway and a pump casing having an intake section with flow distribution vanes in the region of a feed opening adjacent the intake section.

Abstract: A turbine blade or vane is provided. The turbine blade or vane includes an airfoil portion, a root portion arranged below the airfoil portion, a dove tail shaped securing portion arranged below the root portion have a surface including subregions that have locally different compressive residual stresses, and a convexly curved sub region arranged on the surface and adjacent to the concavely curved sub region. The concavely curved region has higher compressive residual stresses than the convexly curved region, and the level of the compressive residual stress in the concavely curved region is at least 30% of the component base material yield strength.

Abstract: An airfoil assembly is described comprising an airfoil, a band coupled to the airfoil for providing at least a portion of support for the airfoil in the airfoil assembly and a slot capable reducing stress in the airfoil wherein the slot is located in the band near a portion of the airfoil. A compression system is described comprising a stator assembly comprising a plurality of arcuate vane sectors arranged circumferentially around a longitudinal axis, each vane sector comprising an airfoil, an arcuate inner band and an arcuate outer band coupled to the airfoil, and a slot capable of reducing stress in the airfoil, the slot being located in the vane sector near a portion of the airfoil.

Abstract: Provided is an industrial gas turbine multi vane segment, which can be cast in one piece using a wax pattern method. The multi vane segment includes a platform; at least three airfoils, extending radially from the platform, having a combined airfoil volume, a chord length and an airfoil thickness; and a shroud with a shroud volume, disposed on an end of said airfoils radially distant from the platform. The ratio of the shroud volume to the combined airfoil volume defines a first ratio, while the multi vane segment has a first ratio greater or equal to 1.4:1. This ratio enables preferential solidification, during casting, of the airfoils before the shroud.

Abstract: A fluid flow machine includes a main flow path which is confined by a hub (3) and a casing (1) and in which at least one row of blades (5) is arranged, with a blade end with gap being provided on the blade row, with the blade end and the main flow path confinement performing a rotary movement relative to each other in a vicinity of the blade end, with at least part of the running gap (11) retracted radially from the main flow path confinement into the main flow path, with the running gap (11) at the retractions no longer being confined by the main flow path confinement, but by a peripheral guiding device (10) passed by the main flow and firmly connected to the main flow path confinement and having a row of profiles (12).

Abstract: A fluid handling and cogeneration system has an inlet conduit receiving a fluid, a housing having a inlet end, a outlet end and an interior surface. The housing encloses an inner body which together with the housing is arranged to form an annular space between the interior surface of the housing and an exterior surface of the inner body. The system also includes at least one diverter configured such that the fluid is directed to circulate around the inner body and traverse the annular space from the diverter toward the outlet end of the housing in an organized fashion. A generator is provided within the housing to harness the fluid traversing the annular space to generate electrical power.

Abstract: In a first aspect the invention relates to an intake device (3) for creating a uniform flow of liquid entering a pump (4), which flow of liquid is free from rotation and swirls about the inlet of said pump. The inlet device (3) comprises an inlet section (11) having an orifice (14) and a decreasing cross section area seen in the direction from said orifice (14) for gradually accelerating a flow of pumped liquid, a redirection section (12) for redirecting the flow of pumped liquid from a mainly horizontal direction to a mainly vertical direction, and an outlet section (13) arranged to be connected to an inlet (6) of a pump (4). The device is characterized in that at least a part of a circumferential wall edge of said inlet section (11) extending around said orifice (14) comprises a bevel (17). In a second aspect the invention also relates to a pump station comprising such an intake device.

Abstract: A multiple piece turbine airfoil having an outer shell with an airfoil tip that is attached to a root with an internal structural spar is disclosed. The root may be formed from first and second sections that include an internal cavity configured to receive and secure the one or more components forming the generally elongated airfoil. The internal structural spar may be attached to an airfoil tip and place the generally elongated airfoil in compression. The configuration enables each component to be formed from different materials to reduce the cost of the materials and to optimize the choice of material for each component.

Abstract: An electric drive machine includes an axle assembly having a central axle housing. An electric drive motor, having a motor housing, is oriented along an axis and disposed within the central axle housing. An air cooling system includes a blower fluidly connected to and positioned upstream of an opening of the central axle housing. An airflow path through the central axle housing includes an upstream segment and a downstream segment. The upstream segment extends from the opening to an airflow deflector, and is configured for airflow in a first direction along an axial path. The downstream segment extends from the airflow deflector to the motor housing, and is configured for airflow in a second direction, which is opposite the first direction, along a helical path.

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

Abstract: A turbine housing is provided. The turbine housing includes a tongue diverter to manage the interaction between exhaust gases entering the inlet of the housing and gasses flowing within the housing. The tongue member may also be arranged to produce a constant ratio throughout the turbine housing between the cross-sectional area of fluid passages and the distance between the centroid of that area and the axis of rotation of the turbine. The housing may comprise a pair of half shells that each form a portion of the tongue diverter.

Abstract: An inlet guide vane having a nominal profile substantially in accordance with Cartesian coordinate values of x, y, and z set forth in TABLE 1 reduces vibration of engine components at various operating conditions. A scaling factor can be applied to the values to make the airfoil larger or smaller. The TABLE 1 x and y values are distances in inches within a tolerance which, when connected by smooth curves, define airfoil profile sections at each distance z in inches, the profile sections being joined smoothly to form a complete airfoil shape. The tolerance in an embodiment is up to about 0.16 inches.

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: Composite aerofoils for gas turbine engines are commonly provided with a metal protection strip along the leading edge, to prevent erosion of the leading edge in use and to protect against impacts from foreign bodies. A problem with such strips is that they can cause serious damage to other parts of the engine if they become detached from the aerofoil. The invention provides an aerofoil having such a protection strip, characterised in that the protection strip includes one or more weakening features to reduce the ability of the protection member to withstand a compressive force applied along its length. The weakening features encourage the protection member to break up under impact, or if it becomes detached from the aerofoil, so that damage to other parts of the engine is minimised.

Abstract: An airfoil insert comprises an insert wall, a contact element and a flow director. The insert wall defines an interior extending inside the insert wall from a first end to second end, and an exterior extending outside the insert wall from the first end to the second end. The contact element is formed on the exterior of the insert wall. The flow director is formed on the insert wall at a boundary between the interior and the exterior. The flow director increases a heat transfer coefficient of convective flow along the insert wall by directing the convective flow to the exterior of the insert wall.

Abstract: A transition duct assembly for a gas turbine engine includes an outer diameter surface and an inner diameter surface. A substantially annular flowpath having a radial offset is defined between the inner diameter surface and the outer diameter surface. A curvature distribution of the inner diameter surface includes a first region of increasing slope in a radial direction and a second region of decreasing slope in the radial direction adjacent to and downstream of the first region. The first and second regions are configured to reduce flow separation along the outer diameter surface of fluid traveling along the substantially annular flowpath.

Abstract: A sealing means for sealing between segments of a component assembly. The sealing means comprises a sealing member having a mating surface for mating with the surface of the segment. The sealing means further comprises a location member removably attached to the sealing member along a transition region therebetween, and also a free end distal to the sealing member. The location member is configured to engage a location feature of the segment so as to locate the mating surface of the sealing member in a fixed position on the surface of the segment relative to the location feature. The location member is configured to be detached from the sealing member along the transition region and be removed from the segment after the sealing member has been bonded to the segment.

Abstract: A turbomachine comprising: an annular combustion chamber (40); a centrifugal compressor (10); an annular diffuser (20) enabling the flow of gas leaving the compressor to be diffused and directing this flow of gas towards the combustion chamber, the diffuser comprising: an upstream portion (21) oriented radially and presenting diffusion passages (22) connected to the outlet from the compressor; an intermediate portion (24) that is elbow-shaped; and a downstream portion (25) having a series of circularly spaced-apart flow-straightening vanes (26); and an outer casing (32) surrounding the outside of the combustion chamber and the downstream portion; in which the flow stream in the downstream portion (25) is delimited externally by the outer casing (32).

Abstract: An energy enhancing device for increasing the effectiveness of energy conversion from wind and other fluid flows is presented by improving methods of accelerating the fluid flow passing through a turbine device or energy converter. Their main application is for accelerating the speed of fluid flow for fluid turbines and other devices designed to extract power from winds, induced air currents, river, ocean, tidal and other water currents.

Abstract: An airfoil arranged for use in a fluid flow of varying direction relative to the airfoil, has arranged thereon a plural axis hinge for automatic adjustment of the angle of pitch of the airfoil. The airfoil can be applied to a rotary crossflow device for use in a fluid flow of varying apparent flow direction, an oscillating device for use in a fluid flow, a force generation device for use in a fluid flow of varying direction, or a flow control device for use in a fluid flow of alternating direction.

Abstract: The invention is related to a component of a turbine machine with diagonally extending recesses in the surface of the component. Thermally stressed components of a turbine machine can be protected against excessive heat input by active cooling or by applying thermal insulation layers. The invention increases the effect by providing diagonally extending slots in the surface of the component.

Abstract: Flow restrictors (4), (14) are widely utilised with regard to providing flow control in such situations as with respect to sealing and pressurisation of bearing chambers in gas turbine engines. The restrictor (4), (14) restricts a flow (5), (15) but with prior arrangements may be susceptible to deposition upon flank surfaces of the restrictor (4). These depositions may fragment and block an aperture (7), (17) of the restrictor (4), (14) reducing operational effectiveness. By provision of a deflector (18) having a deflector surface (19) flows (15) can be presented such that a greater proportion of the flow including droplets or other matter which may result in surface deposition or errosion will pass directly through an aperture (7, 17) rather than impinge upon the flank surfaces of the restrictor (14). Furthermore, the deflector (18) is dimensioned such that surfaces which may be susceptible to deposition have dimensions smaller than the aperture (17).

Abstract: A fluid deflector is for a fluid separator including a central axis and an enclosed wall having an open end and an inner circumferential separation surface extending about the axis to define an interior separation chamber. The fluid deflector includes a base disposeable proximal to the wall open end and having a central axis collinear with the separator axis. A plurality of vanes are connected with the base so as to be spaced circumferentially about the central axis. The vanes define a plurality of flow channels each bounded by a separate pair of adjacent vanes and having an inlet and an outlet. Each vane directs flow through a bounded channel generally radially inwardly from the channel inlet toward the channel outlet and generally circumferentially and radially outwardly from the channel outlet.

Abstract: A vane unit system having a plurality of vane units having at least one air foil projecting from a base. The base has a hole which receives a pin which extends between adjacent bases of vane units therein forming a rigid ring of vanes that are less susceptible to vane motion caused by pressure fluctuations within the compressor of a gas turbine. A blade assembly tool having a shape to fit within the slot in a casing that receives the vane units allows for the installation of vane units with interlocking pins without the necessity of having to remove the rotor from the casing.

Abstract: A pump assembly has a housing formed of at least two metallic housing parts (2) and at least one diffuser (12) arranged in the housing, wherein the diffuser (12) is fixed between the two housing parts in the axial direction, and the two housing parts (2) are directly or indirectly in metallic contact with one another, in a manner such that a force transmission in the axial direction between the housing parts (2) is effected via elements of metal.

Abstract: The invention relates to a turbine blade comprising a vane that runs along a blade axis and a platform region, located at the root of the vane having a platform that extends transversally to the blade axis. The aim of the invention is to configure a delimitation of a flow channel of a gas turbine in the simplest possible manner. Therefore, the platform is configured by an elastic sheet metal part that rests on the vane. Said part leads to a gas turbine comprising a flow conduit that runs along an axis of the gas turbine, said conduit having an annular cross-section for a working medium and a second vane stage that is situated downstream of a first vane stage, which runs along the axis.

Abstract: A high-lift airfoil embodying a combination of loading conventions in a single design specifically to reduce and control total pressure losses that occur in the flow channels between airfoils employed in turbomachinery applications is disclosed herein. The mixed-loading high-lift airfoil designs embody and exhibit the best total profile and secondary loss characteristics possessed by both aft-loaded airfoil and front-loaded airfoil conventions through controlling the development and interaction of boundary layers forming along the surfaces of the airfoils and the endwalls in such applications. The mixed-loading high-lift airfoil may be utilized in both rotating and non-rotating turbomachinery applications.