Abstract: A casing for a turbine engine compressor, including: cavities in a thickness of the casing, extending in parallel to one another from an inner face of the casing along a circumference thereof, the cavities not being in communication with one another. The cavities, which are elongate and extend along a main direction of orientation between two side walls, are closed upstream and downstream by upstream and downstream faces respectively, and an upstream border and a downstream border are formed at the intersections between same and the inner face of the casing. The upstream border of the cavities takes a form of a wavy line including at least two alternate undulations over a length thereof between the side walls.

Abstract: The present invention relates to a pump (10) comprising a shaft (15) supported for rotation by a bearing (38) carried by a bearing carrier (48), said bearing carrier having a generally outer radial portion (52) which is fixed relative to a pump housing (12) and a generally inner radial portion (54) which is fixed relative to the bearing, wherein the carrier is stiff in a radial direction between said inner and outer portions and flexible in an axial direction for restraining radial movement of the bearing and allowing axial movement.

Abstract: A cooling system (10) for a turbine airfoil (12) of a gas turbine engine, wherein the airfoil (12) has a bowed configuration is disclosed. The airfoil (12) may be configured such that the leading edge (16) or trailing edge (18), or both, may have midsections that are positioned further upstream than outer ends of the leading and trailing edges (16, 18). One or more cooling channels (28) of the cooling system (10) may have a larger cross-sectional area proximate to an end of the airfoil (12) than at a midspan location. One or more cooling channels (28) may have one or more corner blockers (30) that extend chordwise in the cooling channel (28) and extend from a corner (54) toward a centerline axis (34), thereby reducing a cross-sectional area of the cooling channel (28). The corner blockers (30) may be positioned within the cooling system (10) to maintain the flow of cooling fluids through the airfoil (12) within desired design parameters.

Abstract: A rim seal arrangement for a gas turbine engine includes a first seal face on a rotor component, and a second seal face on a stationary annular rim centered about a rotation axis of the rotor component. The second seal face is spaced from the first seal face along an axial direction to define a seal gap. The seal gap is located between a radially outer hot gas path and a radially inner rotor cavity. The first seal face has a plurality of circumferentially spaced depressions, each having a depth in an axial direction and extending along a radial extent of the first seal face. The depressions influence flow in the seal gap such that during rotation of the rotor component, fluid in the seal gap is pumped in a radially outward direction to prevent ingestion of a gas path fluid from the hot gas path into the rotor cavity.

Abstract: Nacelle air management systems for a high bypass ratio engine are provided. The nacelles air management systems may include an outer cowl and an inner cowl that are configured to provide dual bypass flow channels around an engine core. These systems may be employed to accommodate larger engine fans. The nacelle air management system may also include one or more blocker doors are configured to at least partial obstruct and/or direct air from the dual bypass flow channels to create reverse thrust.

Abstract: A thermal management article, a method for forming a thermal management article and a thermal management method are disclosed. Forming a thermal management article includes forming a duct adapted to be inserted into a groove on the surface of a substrate, and attaching the duct to the groove so that the top outer surface of the duct is substantially flush with the surface of the substrate. Thermal management of a substrate includes transporting a fluid through the duct of a thermal management article to alter the temperature of the substrate.

Abstract: Embodiments are disclosed of a turbomachinery component having an outer part that is captured between a cap and a base of the component. In one form, the outer part is placed in compression between the cap and the base. The outer part can be formed prior to being placed between the cap and the base. In some forms, the outer part can be formed partially or completely while engaged with the component. A fugitive spacer can be placed between the outer part and an extension of the component. In various embodiments, the extension can reach into an opening of the outer part and the cap can be coupled with the extension.

Abstract: A method for operating a wind farm is provided. The method includes determining a wind condition, determining a wake-effect between at least two wind turbines forming at least a sub-set of the wind farm, each of the at least two wind turbines having a yaw system, and determining a desired yaw angle setpoint for each of the at least two wind turbines so that a total power production of at least the sub-set is expected to be increased compared to independently operating the yaw systems of each of the at least two wind turbines. Furthermore, a wind farm is provided.

Abstract: An aircraft control system includes a co-axial, counter-rotating propeller shaft assembly. Also included is a first rotor operatively coupled to the propeller shaft assembly, the first rotor having a first plurality of blades mounted thereto, wherein the first plurality of blades are disposed at a substantially identical nominal pitch during rotation of the first rotor. Further included is a second rotor operatively coupled to the propeller shaft assembly, the second rotor having a second plurality of blades mounted thereto, wherein a pitch of the second plurality of blades is configured to cyclically change during rotation of the second rotor.

Abstract: A bladed rotor for a turbomachine, in particular a gas turbine, having a plurality of blades distributed around the circumference thereof; the blade distribution being made up of a natural-number sector count of first angular sectors and second angular sectors; a first blade count of first blades being arranged in the first angular sectors, and a second blade count of second blades being arranged in the second angular sectors, said second blade count being different from said first blade count; and the sector count being odd (Z=2n+1, n=1, 2, 3, . . . ) and/or greater than two (Z>2).

Abstract: A seal system, for an apparatus that includes a rotatable portion with airfoils coupled thereto and a stationary portion with an inner surface, includes an abradable portion including at least one abradable layer of an abradable material formed over the inner surface. The seal system also includes an abrading portion disposed over at least a portion of a substrate of the airfoil. The abrading portion includes at least one abrading layer formed on at least a portion of the substrate and a plurality of abrasive particles embedded within the abrading layer. The plurality of abrasive particles includes at least one of substantially all of one of tantalum carbide (TaC), aluminum oxide (Al2O3), and ziconia (ZrO2), cubic boron nitride (cBN) and Al2O3 in predetermined ratios, cBN, Al2O3 and ZrO2 in predetermined ratios, Al2O3 and ZrO2 fused together in predetermined ratios, and TaC and Al2O3 in predetermined ratios.

Abstract: A turbine blade having a root and a tip and an airfoil with a core section made of composite material and a protective sheath or layer joined to the composite core at a location or locations exposed to erosion is described with the composite core of the airfoil being continuous from a location in vicinity of the root to a location in vicinity of the tip of the blade and including a section which widens with distance from the rotational axis along the length of the airfoil and which ends at the location in vicinity of the tip of the blade. The protective sheath or layer is secured by interference fit with widening section of the core.

Abstract: A protective coating for a surface exposed to hot gas flow comprises a thermal layer, a conducting layer and an abrasive layer. The thermal layer comprises alumina having a sufficient amount of impurities to lower the thermal layer thermal conductivity. The layer is formed from a powder having a thermal conductivity no more than 10 BTU in/hr ft2° F., and overlies the surface. The conducting layer overlies the thermal layer. The abrasive layer comprises abrasive particles bonded in a metal matrix that is electroplated onto the conducting layer.

Abstract: One embodiment includes an air pump assembly (10) with an impeller (12), a housing (16), and a diverter (18). The impeller (12) has an axis of rotation (R). The housing (16) surrounds the impeller (12) and has an inlet passage (42) with a longitudinal axis (L1) arranged generally orthogonal to the axis of rotation (R) of the impeller (12). The diverter (18) helps reduce turbulent fluid-flow in the inlet passage (42).

Abstract: An arrangement for reducing noise which is generated by a wind turbine blade is provided. The wind turbine blade has a first panel and a second panel. The first and the second panel are arranged at a trailing edge of the wind turbine blade, wherein the first panel is adjacent to the second panel. The first panel includes a first transition zone and the second panel includes a second transition zone. The first transition zone and the second transition zone are engaged in a way that whistle tones produced by a gap of the wind turbine blade, the gap being located between the first panel and the second panel, is reduced or even avoided.

Abstract: A vane for an axial-flow compressor has a pressure surface generating positive pressure and a suction surface generating negative pressure, and both are located on one side of the chord line. The pressure surface includes a bulging portion, having a maximum curvature of 1.5 or more between a chordal position of 70% and 95%, in a central section of the vane's span. This configuration increases the flow velocity around the bulging portion of the pressure surface to locally decrease the static pressure. By flow continuity the flow velocity on the suction surface that faces the pressure surface is decreased, and thus locally the static pressure on the suction surface is increased. Secondary flow from the pressure surface with positive pressure to the suction surface with negative pressure from the hub region, is suppressed due to the locally increased static pressure on the suction surface.

Abstract: A impeller for a centrifugal pump has an inducer section. The inducer section has first and second pluralities of blades, each having a plurality of polygonal cross-sections defined by a plurality of vertices. The pluralities of vertices are defined by tables of vertex locations. A method of making a centrifugal pump includes forming an impeller that has an inducer section, as described above, and an impeller section. The impeller is fluidly connected downstream of the inducer section and has third, fourth, and fifth pluralities of blades, each having a plurality of polygonal cross-sectional areas defined by a plurality of vertices. The pluralities of vertices are defined by tables of vertex locations.

Abstract: A scatter guard is interposed between a turbine inlet of a turbocharger and a downpipe and is a ring member that has a pair of opposing flanges, one flange being used to connect the ring to the turbocharger and the other flange being used to connect the ring to the down pipe, each connection being made via a band clamp. One or more spokes are located within the ring and are used to absorb an incoming escaped turbine either to outright stop the turbine or to shatter the turbine into numerous smaller and far less harmful pieces. The inside diameters at each end of the ring may be different to relative to one another in order to eliminate the need to use a step-down adapter whenever the diameter of the turbine inlet and the downpipe mismatch. Alternately, the scatter guard can be used in conjunction with the step-down adapter.

Abstract: A method of repairing a damaged dovetail on a peripheral portion of a turbine wheel includes the steps of removing buckets from the dovetail; removing a damaged dovetail from the peripheral portion of the turbine wheel, leaving a rotor wheel body having a peripheral rim; disposing a replacement ring about the peripheral rim, the replacement ring and the rim defining therebetween a pair of end grooves and a center section; and welding the replacement ring to the peripheral rim, with weld material applied only within the end grooves, leaving a void in the center section.

Abstract: A housing has walls that define a volute passage and a diffuser passage fluidly connected to the volute passage. The volute passage has a first subsection and a second subsection, each having cross-sectional areas defined by tabular data. A centrifugal pump has a rotor and a housing, the housing having walls defining a volute passage and a diffuser passage fluidly connected to the volute passage. The volute passage has a first subsection and a second subsection, each having cross-sectional areas defined by tabular data.