Abstract: This invention discloses a hydraulic power unit, which is capable of strongly jetting a working fluid, may be used to implement a new hydraulic engine. The hydraulic engine generates rotational power by using environmentally friendly electric energy, and has improved performance and a long life span. The hydraulic power unit includes: an inner tube comprising a hollow portion, wherein a fluid inlet and a fluid outlet are formed in the inner tube; a vibration tube comprising a hollow portion, an elastic tube layer and a metal tube layer, and the hollow portion of the vibration tube is connected in line to the hollow portion of the inner tube; an oscillator that is disposed to contact a back end of the vibration tube; an outer check member that is disposed to contact the fluid outlet; and an inner check ring that is disposed to contact the fluid inlet.

Abstract: To provide a centrifugal compressor having a high pressure ratio, which can achieve a large flow rate while suppressing a decrease in efficiency, the centrifugal compressor being adapted to compress and discharge a gas, which has been sucked in by rotation of an impeller (10) pivotally supported in a casing (11), mainly by centrifugal force, the inlet radius/outlet radius ratio (R1/R2) of the impeller (10) is set at 0.7?R1/R2?0.85, and the inclination angle (74 ) of a back board portion in a hub (10a) of the impeller (10) is set at 5°???15°.

Abstract: A blade row for a turbomachine, in particular a gas turbine, is disclosed. The blade row has a number of first blade arrangements each having at least one first blade and a first shroud with a first extension in the circumferential and/or axial direction and at least a number of additional blade arrangements each having at least one additional blade and one additional shroud with an additional extension in the same direction, which is different from the first extension.

Abstract: A turbomachine rotor includes: a rotor body having an outer surface; and a patterned abrasive or abradable coating formed over the outer surface of the rotor body, the patterned abrasive or abradable coating for directing a flow of a working fluid across the turbomachine rotor.

Abstract: A rotor assembly having a first component and a second component. The second component is secured within a bore of the first component by a first adhesive and a second adhesive. The first adhesive forms an annular seal between the first component and the second component, and the second adhesive extends from the first adhesive and has a lower viscosity than that of the first adhesive.

Abstract: Systems and methods according to these exemplary embodiments provide welding techniques for impeller blades associated with impellers in centrifugal compressors. According to one exemplary embodiment, a connection area of the impeller blade has a “hammer”-shaped cross-sectional area which facilitates beam welding of the connection area to a slot in the surface or body to which the blade is to be connected.

Abstract: A blade for a rotor of a turbine includes an airfoil, a shroud and a platform. The platform includes a top plate, a shank and a fixing part. An upstream wall projects in the circumferential direction away from the shank and extends from the top plate toward the fixing part, the upstream wall at least partially covering an upstream side of the shank. A downstream wall projects in the circumferential direction away from the shank and extends from the top plate toward the fixing part, the downstream wall at least partially covering a downstream side of the shank. A recess is disposed in at least one of the upstream wall and the downstream wall. The recess has an open side facing in a same direction as a respective one of the upstream wall and the downstream wall, in which the recess is disposed, is projecting.

Abstract: A full hoop stator vane cluster includes an inner hoop and an outer hoop both being substantially cylindrical and coaxial. A plurality of airfoils extend radially between the hoops, and a plurality of vane splines extend radially outward from the outer hoop for attaching the vane cluster to a gas turbine engine.

Abstract: A cooling fan of the present invention includes: a bottomed cylindrical boss portion; and a plurality of blades provided on an outer circumferential surface of the boss portion, the blades radiating in a radial direction, in which a ring member for connecting the blades with each other is provided on a side radially inner from tips of the blades. According to the present invention, it is possible to provide a cooling fan capable of preventing the worsening of the noise characteristic and also of enhancing the versatility even if the blades are made thinner.

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

Abstract: A turbine blade 10a which is a stop blade is provided with a cutout portion 50 which is formed in one circumferential side surface 22a of a shank portion 22 at the center in the axial direction of a turbine rotor 100, a cutout portion 60 which is formed in one circumferential side surface 22a of the shank portion 22 from one end portion 22b to the cutout portion 50 in the axial direction of the turbine rotor 100, and a through passage 70 which is formed to pass from the cutout portion 50 to an effective blade part and in which a moving member 170, which moves a stopper member 160 to the effective blade part in the cutout portion 50, is inserted.

Abstract: Hybrid turbine airfoil components containing a ceramic material, in which detailed features of the components are formed of materials other than ceramic materials. The components include a first component formed of a ceramic-based material and a second component formed of a metallic material. The first component comprises an airfoil portion and a nub, and the second component is separately formed and attached to the first component by casting the metallic material around the nub of the first component. The second component includes a platform portion between the airfoil portion and the nub of the first component and a dovetail portion on the nub of the first component. Each of the platform and dovetail portions has at least one off-axis geometric feature that results in the second component having a more complex geometry than the first component.

Abstract: The fan impeller (10) comprises a hub (14) and blades (12) extending radially outward from the hub, the blades having a flattened airfoil profile cross section with a leading edge (24) and a trailing edge (26) between which a chord is defined. The blade (12) has a relative thickness that reached its maximum value (Emax) in the first quarter of the length of the chord measured from the leading edge (24), the relative thickness being defined by the ratio between the thickness of the blade and the length of the chord. The invention finds an application particularly in motor vehicle engine cooling fan impellers.

Abstract: A turbine flowpath apparatus for a gas turbine engine includes: a flowpath component exposed at least partially to a primary combustion gas flowpath of the engine, the flowpath component comprising low-ductility material; a metallic annular stationary structure surrounding the flowpath component, including a bearing surface which bears against the flowpath component, so as to restrain the flowpath component from axial movement in a first direction; and a spring element disposed between the flowpath component and the stationary structure which resilient urges the flowpath component in the first direction against the bearing surface.

Abstract: A connection between an annular sleeve on a gas turbine engine first rotor component includes an annular tapered conical slot extending axially inwardly into the sleeve from an annular opening and tapers axially into the sleeve from the opening. An annular rim of a second rotor component is received within the conical slot and includes a rim inner conical surface mating with and contacting a sleeve inner conical surface in part bounding the conical slot. A sleeve cylindrical outer surface in part bounds the conical slot in the sleeve and a rim outer cylindrical surface on the annular rim contacts the sleeve cylindrical outer surface. An annular lip may extend radially inwardly from the sleeve and sleeve inner conical surface at the annular opening to the conical slot. The connection may be used between a first stage disk and an interstage seal.

Abstract: An example airfoil assembly includes a base having an airfoil projecting radially therefrom. The base extends laterally away from the airfoil. The airfoil extends axially from an airfoil leading edge portion to an airfoil trailing edge portion. The base has a humped area forward the airfoil leading edge portion.

Abstract: A device for use in a molten metal pump helps alleviate jams between rotating rotor blades and a stationary pump base. The device includes inlet perimeters that partially define one or more openings, and one or more rotor blades, wherein each rotor blade has a portion that directs molten metal into a pump chamber, and a portion that directs molten metal outwards. Each rotor blade may also include a recess that makes an opening larger to enable more molten metal to pass through the openings.

Abstract: A turbine blade system including a first turbine blade and a second turbine blade being arranged adjacent to each other shall be suited to allow a particularly secure and reliable operation of a turbine. To this end, the turbine blades are in contact in a first surface area and separated from each other in a second surface area, wherein the first turbine blade includes a pocket containing a damping piece in the second surface area.

Abstract: A method for optimizing the contact surfaces of abutting shroud segments of adjacent blades of a rotor blade row of a gas turbine includes providing a 3-D model of an individual blade. A geometry of the individual blade is calculated using the 3-D model while considering centrifugal forces, temperature stresses and pressure loads experienced in a loaded state of the blade during operation. The contact surfaces of the abutting shroud segments of adjacent blades are optimized in the loaded state of the blade. The optimization includes the surfaces of functionally serving interlocking surfaces and functionally serving wedge surfaces disposed on each side of the interlocking surfaces. A geometry of the interlocking surfaces and of the wedge surfaces in an unloaded state corresponding to the optimized contact surfaces in the loaded state of the blade is calculated.

Abstract: One embodiment of the present invention is a gas turbine engine. Another embodiment is a gas turbine engine vane system. Other embodiments include apparatuses, systems, devices, hardware, methods, and combinations for gas turbine engine vanes. Further embodiments, forms, features, aspects, benefits, and advantages of the present application shall become apparent from the description and figures provided herewith.

Abstract: A rotating blade row is provided for the final stage of a steam turbine has blades with an integrated shroud. The shroud of each blade has a projection in the axial direction, in each case on its pressure side, which prevents droplets in the working fluid of the steam turbine from reaching the shroud fillet of the respective subsequent blade in the flow direction. The shroud fillet is therefore protected against erosion damage caused by droplets impact erosion. The projection is positioned and of such a size that mass equilibrium is ensured between the suction side and the pressure side of the shroud, and stress equilibrium is ensured between the projection on the pressure side and the suction-side shroud. The projection furthermore has a recess between its greatest axial extent and the leading edge.

Abstract: A centrifugal multiblade fan includes a rotatable shaft, blades, a side shroud, and a main shroud. A front edge has a shape inclined radially outward in a direction from the main shroud toward the side shroud. When viewed from an axial direction, a corner part on a positive pressure surface-side is located on a tangential line of a positive pressure surface reference curve at a positive pressure surface side reference corner part, and when viewed from the axial direction, a curvature radius of a negative pressure surface becomes larger in a direction from the side shroud toward the main shroud.

Abstract: The invention relates to a structure and aerodynamic module comprising two blades each extending along a longitudinal axis, each blade each comprising a leading edge, a trailing edge, a radially inner edge and a radially outer edge, the module also comprising a radially inner platform mechanically connecting the radially inner edges of the two blades, and a radially outer platform mechanically connecting the radially outer edges of the two blades such that the two blades and the radially outer and inner platforms delimit a flow stream, the two blades and the platforms being made from a composite material and the two blades being fixed on the radially outer and inner platforms using screw-nut assemblies.

Abstract: A water current power generation system is provided, including a plurality of flotation tubes joined by a body structure; a plurality of ballast chambers joined by a body structure; a plurality of induction type power generation units disposed within housings associated with one or more of the flotation chambers, ballast chambers and body structure; and a plurality of propellers disposed in mechanical communication with each of the induction type generator units. In one presently preferred embodiment, a plurality of propellers disposed in communication with a plurality of induction type generator units, wherein the propellers each include one or more concentrically disposed rings, with each of the concentrically disposed rings having an inner ring member, an outer ring member, and a plurality of curved fin members separated by gap spaces disposed between the inner and outer ring members.

Abstract: A small scale, high speed turbomachine is described, as well as a process for manufacturing the turbomachine. The turbomachine is manufactured by diffusion bonding stacked sheets of metal foil, each of which has been pre-formed to correspond to a cross section of the turbomachine structure. The turbomachines include rotating elements as well as static structures. Using this process, turbomachines may be manufactured with rotating elements that have outer diameters of less than four inches in size, and/or blading heights of less than 0.1 inches. The rotating elements of the turbomachines are capable of rotating at speeds in excess of 150 feet per second. In addition, cooling features may be added internally to blading to facilitate cooling in high temperature operations.

Abstract: A fan wheel (1) is designed as a radial or diagonal fan, comprising a top plate (2) with an inlet port (4), a base plate (6) and a plurality of fan blades (8) distributed around the inlet port (4) and around an axis of rotation (Z). Blade ducts extend (10) respectively between the adjacent fan blades (8). The blade ducts lead radially or diagonally outward from the area of the inlet port (4) and form blow-out ports in the outer region. The blade ducts (10) are designed, with respect to their effective flow cross-section, as large enough that during operation, a turbulent flow with a Reynolds number markedly greater than 2300 is achieved. The top plate (2) or the base plate (6) or both feature a rotationally asymmetrical geometry with a continuous profile, at least in angular sections encompassing the fan blades (8).

Abstract: A method of forming a pattern on a turbomachine component includes adding material to selected surface regions of the turbomachine component, the material is arranged in a predetermined pattern.

Abstract: A damping structure for a turbomachine rotor. The damping structure includes an elongated snubber element including a first snubber end rigidly attached to a first blade and extending toward an adjacent second blade, and an opposite second snubber end defining a first engagement surface positioned adjacent to a second engagement surface associated with the second blade. The snubber element has a centerline extending radially inwardly in a direction from the first blade toward the second blade along at least a portion of the snubber element between the first and second snubber ends. Rotational movement of the rotor effects relative movement between the first engagement surface and the second engagement surface to position the first engagement surface in frictional engagement with the second engagement surface with a predetermined damping force determined by a centrifugal force on the snubber element.

Abstract: A blade is provided and includes a platform and a root configured to be connected to a blade carrier. Airfoil portions extend from opposite sides of the platform. Each airfoil portion defines an operating surface being the surface facing the other airfoil portion. An operating surface of one of the airfoil portions defines a suction side and the other operating surface of the other airfoil portion defines a pressure side.

Abstract: Provided are turbine blades and a gas turbine capable of damping the vibrations caused by an excitation force and facilitating mounting/disassembly. Included are a shroud portion disposed at an end portion of an airfoil portion; a holder casing that can slide relative to the shroud portion, that can also be attached thereto/detached therefrom, and that forms a space with the shroud portion therebetween; and an elastic portion that is disposed in the space, that biases the shroud portion in a direction that separates it from the holder casing, and is disposed in a movable manner relative to the shroud portion; and a pressing portion that is disposed between the elastic portion and the holder casing and that can be moved toward and away from the shroud portion.

Abstract: An improved coaxial rotor assembly for a helicopter includes an upper rotor system having a multiple of upper rotor blades each having outer tips and mounted on and extending outwards from a central rotor shaft and a lower rotor system having a multiple of lower rotor blades each having outer tips and mounted on and extending outwards from the central rotor shaft with the upper rotor system spaced an axial distance from the lower rotor system on the central rotor shaft. A rotor blade support ring extends circumferentially around each of the upper and lower rotor systems which movably engages and supports the outer tips of the upper and lower rotor blades in spaced apart relation such that the upper and lower rotor systems rotate in opposite directions and the rotor blade support ring means prevents contact between the upper and lower rotor systems during operation thereof.

Abstract: The present application provides a turbine bucket. The turbine bucket may include a shank, a radial seal pin slot positioned on the shank, and a seal pin positioned within the radial seal pin slot. The seal pin may include a pair of shouldered ends.

Abstract: A method of heat treating an Ni-base superalloy article is disclosed. The method includes hot-working an article comprising an NiCrMoNbTi superalloy comprising, in weight percent, at least about 55 Ni to produce a hot-worked microstructure; solution treating the article at a temperature of about 1600° F. to about 1750° F. for about 1 to about 12 hours to form a partially recrystallized warm-worked microstructure; and cooling the article. The method also includes precipitation aging the article at a first precipitation aging temperature of about 1300° F. to about 1400° F. for a first duration of about 4 hours to about 12 hours; cooling the article to a second precipitation aging temperature; precipitation aging the article at a second precipitation aging temperature of about 1150° F. to about 1200° F. for a second duration of about 4 hours to about 12 hours; and cooling the article from the second precipitation aging temperature to an ambient temperature.

Abstract: A tip shroud that includes a plurality of damping fins, each damping fin comprising a substantially non-radially-aligned surface that is configured to make contact with a tip shroud of a neighboring rotor blade. At least one damping fin may comprise a leading edge damping fin and at least one damping fin may comprise a trailing edge damping fin. The leading edge damping fin may be configured to correspond to the trailing edge damping fin.

Abstract: The use of a shroud to surround a set of turbine blades works best when the blades are shaped to maximize the unique distribution of velocity of such a shroud. Parameters for the construction of such blades for both water and wind turbines are presented.

Abstract: A propulsor apparatus for a mobile platform, for example an aircraft is provided. The propulsor apparatus includes an aerodynamically shaped propeller duct that houses at least a portion of a turboprop engine, and fully houses a propeller driven by the engine. Inside the propeller duct is a circumferential ring that closely surrounds the propeller such that only a small clearance is provided between the outermost tips of the propeller blades and an inner surface of the circumferential ring. The circumferential ring includes sound deadening material that attenuates noise generated by the tip vortices created at the outermost tips of the propeller blades. The propeller duct and circumferential ring are supported by a plurality of structural rods that couple to structure of the mobile platform, for example to the spars within a wing of an aircraft. The apparatus and method significantly reduces the noise associated with a turboprop engine.

Abstract: A turbine stage includes a circumferentially distributed row of adjacent airfoils between which there is a flow passage. The passage has a surface, which in its unmodified form, defines a datum plane. A channel, located in the passage, extends in the direction of an airfoil pressure face from a point towards a leading edge line to a point towards a trailing edge line. The channel includes two channel walls angled relative to the datum plane. Relative to the datum plane, the channel has a low point, two high points, and a channel height, which is measured between the low point and the highest one of the high points. The channel provides a means to reduce secondary flow losses.

Abstract: A turbine blade is provided comprising: an airfoil including upper and lower ends; a root coupled to the airfoil lower end; a shroud coupled to the airfoil upper end; and at least one sealing rail extending radially outwardly from an upper surface of the shroud and extending generally along a circumferential length of the shroud. The sealing rail may comprise a mid-section, opposing end sections and at least one intermediate section located between the mid-section and one of the opposing end sections. An axial thickness of the rail may vary.

Abstract: A process for inhibiting delamination in a bend of a component formed of a continuous fiber-reinforced composite material having layers containing arrays of unidirectional fibrous elements in a matrix material. A preform of the component is formed by laying-up prepreg tapes corresponding to layers of the component. Each tape contains a matrix precursor, a binder, and an array of the fibrous elements. The tapes are laid-up so that the fibrous elements of at least a first tape traverse the bend, and the fibrous elements lie in planes that are not perpendicular to the axis of curvature of the bend. The preform then undergoes thermal processing, during which delamination of the layers in the bend is inhibited as a result of none of the fibrous elements lying in a plane perpendicular to the axis of curvature of the bend.

Abstract: Turbine shroud ring sector for a turbomachine intended to be supported at the upstream end by a downstream support (8) of a turbine casing (3) with circular sliding, comprising a first stop (11) able to collaborate with a second stop (12) borne by an element (13) of said turbomachine adjacent to said shroud ring in order to immobilize it circularly, said sector (4) comprising, on an end facing said element (13), a recess (10) able to allow said second stop (12) to pass to come into contact with said first stop (11), said recess being cut substantially in the form of a rectangle having, at the bottom of the recess (10), corners that are rounded in a circular arc of radius r, wherein the bottom of the recess (10) has a convex shape tangential to the circular arcs of the rounded corners and with a curvature that evolves between a radius of curvature r where it meets the rounded corners and a radius of R, greater than the radius r, at a point situated between the two rounded corners.

Abstract: A compressor wheel (20) for an air boost device and a method for designing the wheel are provided. The compressor wheel (20) comprises a hub (24) and a plurality of blades (22, 23) connected to the hub (24). The plurality of blades (22, 23) have a ratio (f/N) of natural frequency to maximum rotational speed of less than 4.0 and are made from a titanium alloy. The plurality of blades (22, 23) can comprise a plurality of full blades (22) and a plurality of splitter blades (23).

Abstract: A bucket for use in the low-pressure section of a steam turbine engine is provided. The bucket has a vane length of at least about 52 inches. The bucket is comprised of a dovetail section disposed near an inner radial position of the bucket, a tip shroud disposed near an outer radial position of the bucket and a part span shroud disposed at an intermediate radial position. The intermediate radial position is disposed at a location between the inner and outer radial positions the intermediate radial positioning adapted to promote aerodynamic performance of the part span shroud. The bucket is comprised of a chromium steel.

Abstract: In a steam turbine including a turbine rotor 7; a moving blade 1 secured to the turbine rotor 7; a shroud 3 provided on an outer circumferential side distal end of the moving blade 1; and an outer circumferential side stationary wall 4 internally embracing the turbine rotor 7 and forming an outer circumferential side passage wall of a steam path, the shroud 3 has an inner circumferential surface 14 so formed that a moving blade outlet flare angle ?3 is greater than a moving blade inlet flare angle ?2; an angle ?1 formed between the outer circumferential side stationary wall 4 and the turbine central axis 50 is generally equal to the moving blade inlet flare angle ?2; and an angle ?4 formed between the outer circumferential side stationary wall and an turbine central axis 50 is generally equal to the moving blade outlet flare angle ?3.

Abstract: A water current power generation system is provided, including a plurality of flotation tubes joined by a body structure; a plurality of ballast chambers joined by a body structure; a plurality of induction type power generation units disposed within housings associated with one or more of the flotation chambers, ballast chambers and body structure; and a plurality of propellers disposed in mechanical communication with each of the induction type generator units. In one presently preferred embodiment, a plurality of propellers disposed in communication with a plurality of induction type generator units, wherein the propellers each include one or more concentrically disposed rings, with each of the concentrically disposed rings having an inner ring member, an outer ring member, and a plurality of curved fin members separated by gap spaces disposed between the inner and outer ring members.

Abstract: In one embodiment, a turbine blade platform may be disposed between two turbine blades. The platform may include a first exterior side configured to interface with a first turbine blade. The platform also may include a second exterior side disposed generally opposite the first exterior side and configured to interface with a second turbine blade.

Abstract: A wind turbine blade includes an arcuate partial annulus arc shroud secured to a tip of the blade.

Abstract: An axial flow wind turbine having forwardly swept blades with an annular ring interconnecting the blade tips. A rearwardly directed rake profile is also provided together with unequal blade spacing.

Abstract: A turbine blade includes an airfoil and integral platform at the root thereof. The platform is contoured in elevation from a bank adjacent the pressure side of the airfoil to a trough commencing behind the airfoil leading edge.

Abstract: The invention relates to a wind wheel (1) for a low-speed wind power installation, comprising a plurality of rotor blades (2). In order to use said wind wheel during weak and gusty winds, the wind wheel (1) comprises at least one acceleration ring (3) connecting the rotor blades (2), for air acceleration in the normal direction in relation to the plane of the wind wheel (1).

Abstract: A rotor structure is provided for a wind turbine and includes a central hub from which a plurality of blades radially extends. The blades have distal free ends that are surrounded by and coupled to a circumferentially arranged hood for rotation therewith. As such, with the rotor mounted to a generator of the wind turbine, when air flows caused by winds get into wind facing surfaces of the blades, the air flows are accelerated by either a divergent configuration, a convergent configuration, or a convergent-divergent configuration of the hood to remarkably enhance the performance of wind power generation and reduce the overall size of the rotor of the wind turbine.