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 turbine diffuser is disclosed. The turbine diffuser includes a diffuser segment having a forward end and an aft end with a flange disposed at the aft end of the diffuser segment. The diffuser segment is joinable to an adjacent diffuser segment via the flange, which includes a seal retainer that is securedly connectable in a radial direction with a seal.

Abstract: A rotor hub mounting arrangement for removably mounting a plurality of turbine rotor blades to the rotor hub in a compact and secure manner. The rotor hub includes an internal mounting assembly, preferably comprised of a series of interconnected mounting plates, positioned adjacent a series of foil shaped openings in the rotor hub into which the root end of turbine blades can be inserted and removably mounted to the internal mounting assembly.

Abstract: A cast turbine blade is disclosed and includes an internal cooling passage that passes (e.g., zig-zags or meanders) through the blade from an inlet in the blade root to an outlet in the blade tip. The cooling passage can have a zone at a bend that is at a distance which is remote from the inlet of the cooling passage when the distance from the inlet is measured around the passage, but that is closer to the inlet when the distance from the inlet is measured in a straight line. During casting of the blade, the cooling passage can be defined by a core or cores having a leachable material, the cores being removed after casting by a chemical leaching process. A supplementary passage is also provided for connecting the remote zone to the inlet during the leaching process. The supplementary passage can likewise be defined by a leachable core, or it may be machined into the blade after casting.

Abstract: An article of manufacture having a nominal profile substantially in accordance with Cartesian coordinate values of X, Y and Z set forth in a table. The table selected from the TABLE. Wherein 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 being joined smoothly with one another to form a complete airfoil shape.

Abstract: A bleed valve for a gas turbine engine, the valve comprises a diffuser having a plurality of holes through which a bleed fluid flows and into a fluid stream. The diffuser is characterized in that at least some of the holes are at least partially tangentially angled relative to the bleed fluid flow through the valve so that the bleed air forms a vortex to enhance mixing with the fluid stream.

Abstract: A turbine airfoil cooling system of a turbine engine having a hollow, disc post body positioned between adjacent roots of turbine airfoils and aligned with the roots to cool inner aspects of the turbine engine. The hollow, disc post body may be configured to pass cooling fluids through impingement orifices in the hollow, disc post body to impinge on inner surfaces of platforms of the turbine airfoils. The cooling fluids may then be directed to the internal cooling systems of the turbine airfoils rather than being discharged as film cooling fluids through the platforms of the turbine airfoils.

Abstract: A method of operating a wind turbine above a predefined wind velocity comprising the step of operating a control parameter of the wind turbine within a tolerance band from a reference set-point curve of that control parameter. A wind turbine and a cluster of wind turbines is also contemplated.

Abstract: An engine cooling fan shroud structure (20) for a vehicle includes a skirt (12?) defining a frame. The frame has a certain wall thickness and defines an opening (22) therein constructed and arranged to permit air to pass through the skirt. The skirt includes motor mount structure (14) supported in the opening and constructed and arranged for mounting a fan motor thereto. The frame defines passageways (18) there-through to reduce an amount of material of the skirt. A film material (28) has a wall thickness substantially less than the certain wall thickness and covers the passageways such that air may flow mainly through the opening.

Abstract: A gas turbine engine is provided comprising an outer casing and a plurality of circumferentially positioned vane segments. The outer casing is provided with a circumferential casing slot. The plurality of circumferentially positioned vane segments are coupled to the outer casing. Each vane segment comprises at least one vane airfoil, a radially inner shroud coupled to a first end of the airfoil, a radially outer shroud coupled to a second end of the airfoil, and a strongback fixedly coupled to axially spaced-apart portions of the outer shroud such that a gap is provided between the strongback and the outer shroud. The strongback may comprise axially spaced-apart first and second end portions received in the casing slot.

Abstract: A turbine assembly for a turbocharger includes a variable nozzle formed by a sliding half-collar piston. A first-stage nozzle has a plurality of first vanes supported by a first nozzle ring and extending axially therefrom. A second-stage nozzle has a second nozzle ring connected to the ends of the first vanes, and a plurality of second vanes extending axially therefrom. The piston regulates flow through the second-stage nozzle, while the first-stage nozzle remains open when the piston is fully closed. The second nozzle ring at least partially divides the first vanes from the second vanes. The half-collar piston includes recesses that receive the second vanes and only partially surround the girth of each second vane.

Abstract: An upstanding bladed rotor is journalled from support structure and a windshield assembly is also journalled from the support structure for angular displacement about an upstanding axis about the rotor. The windshield assembly includes a wind-shielding portion which extends generally about one half the periphery of the rotor and further includes a wind vane operative to maintain the assembly in predetermined position relative to wind incident upon the rotor with the wind-shielding portion in position to shield generally one lateral half of the rotor from the incident wind.

Abstract: A turbomachine blade (1) includes a blade body (2) and a corrosion and erosion protective multilayered coating (11) bonded thereto, the multilayered coating (11) including an erosion resistant first layer (3) at least covering a corrosion and erosion critical area (5) of the blade body (2) and a sacrificial second layer (4) provided over the first layer (3) at least covering the first layer (3), preferably covering the blade totally. A method of manufacturing such a turbomachine blade includes the steps of providing a blade and depositing the erosion resistant first layer on the blade body so as to cover at least the corrosion and erosion critical area, followed by depositing the sacrificial second layer over the first layer at least covering the first layer.

Abstract: A damping arrangement for guide vanes, in particular for guide vanes of a gas turbine or an aircraft engine, is disclosed. Referring to this damping arrangement, the radially external ends of the guide vanes of a guide vane grid or a guide vane ring are mounted to a housing. The radially internal ends of the guide vanes form an inner shroud. At least one seal bearing is mounted to the inner shroud of the guide vanes. At least one spring element is installed between the inner shroud of the guide vanes and the, or each, seal bearing. The, or each, spring element is configured as a leaf spring.

Abstract: A tip turbine engine (10) and a method of operating the engine provides increased efficiency while eliminating or educing the number of axial compressor (122) stages by moving the core airflow inlet (27) aft of the fan (24). As a result, the core airflow entering the core airflow inlet is the fan exhaust, which is already at an increased pressure. A portion of the fan exhaust is guided radially inward, then axially forward and then radially outward through compressor chambers (72) in the hollow fan blades (28) for further, centrifugal compression.

Abstract: Structural beam of a wind turbine blade comprising a body-root and a body-trunk in the form of a box with a section decreasing towards the blade tip, comprising various piles each formed by various layers of carbon fiber impregnated with a synthetic resin, located on the upper and lower areas, intercalated between various layers of fiber glass impregnated with synthetic resin arranged along its perimeter, including between two piles, at least one layer of reinforcing material on each of the side areas enveloped by an adhesive resin film. The invention also comprises a procedure for the manufacture of the structural beam which, amongst other stages, includes the application of the layers mentioned onto a mold and the beam curing process.

Abstract: A blade for the use in the generation of power has a leading edge and a trailing edge. A first shell portion of the blade extends from the leading edge to the trailing edge. A second shell portion of the blade also extends from the leading edge to the trailing edge. A root portion of the blade is positioned proximate the wind turbine and a tip portion which extends from the root portion away from the wind turbine. A trailing edge insert is positioned between the first shell portion and the second shell portion proximate the root portion. The trailing edge insert has a surface which extends between and separates the first shell portion from the second shell portion at the trailing edge, such that the insert provides a high lift profile for increased blade efficiency.

Abstract: Improved annular components and improved methods for assembling annular components into a turbine engine are described with respect to an axial compressor having a plurality of annular compressor rotor airfoil assemblies (120) as an example. Each compressor rotor airfoil assembly comprises an annular rotor portion (122), a spacer portion (124) extending axially therefrom and a plurality of airfoils (52) extending radially therefrom. The plurality of airfoils may be integrally formed with the annular portion. The compressor rotor airfoil assemblies are stacked sequentially on a center-tie (134) or outer circumferential tie. The spacer portion of one compressor rotor airfoil assembly (120a) abuts the annular rotor portion of the adjacent compressor rotor airfoil assembly (120b) to retain one another on the center-tied outer circumferential tie. By stacking the compressor rotor airfoil assemblies sequentially and then retaining them, the typical split cases, flanges and rotor bolts may be eliminated.

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: The invention refers to a coated turbine blade for a gas turbine, having blade walls divided into sections with locally adapted material temperatures. The cooler material temperatures of the blade walls are at the points where the support ribs merge into the blade walls. The regions with higher material temperatures of the blade walls are at the positions where cavities are arranged inside the blade walls. This is achieved via a ceramic thermal barrier coating having different layer thicknesses that allow different material temperatures. The region of the surface of the blade wall which faces the working medium and lies opposite an internal rib has a thicker thermal barrier coating than a region of the surface of the blade wall which is cooled via a cooling medium that flows in the cavities. This results in homogenization of the material temperature in the connecting regions, which results in prolonged blade life.