Abstract: An airfoil cooling structure, an airfoil having the airfoil cooling structure, and a turbine blade/vane element including the airfoil are disclosed. The airfoil cooling structure includes a cooling path formed inside the airfoil and having a first surface and a second surface opposite to the first surface, and an additive manufactured (AM) feature disposed in the cooling path, manufactured by additive manufacturing, and including a plurality of column parts intersecting with each other so as to abut against the first surface and the second surface.

Abstract: A centrifugal slurry pump impeller including a back shroud and a front shroud each with opposed inner and outer faces and an outer peripheral edge and a central axis, a plurality of pumping vanes extending between the inner main faces of the back and front shroud, each pumping vane including opposed main side faces, a leading edge in the region of the central axis and a trailing edge in the region of the outer peripheral edges of the back and front shrouds with a passageway between adjacent pumping vanes, each passageway including a blended region between each of the main side faces of the pumping vanes and the inner faces of the front and back shrouds wherein a surface of the inner face of at least one of the front and back shrouds includes a raised portion located between the blended regions of adjacent pumping vanes.

Abstract: A system includes an isobaric pressure exchanger (IPX) configured to exchange pressure between a first fluid and a second fluid. The IPX includes a rotor configured to rotate about a longitudinal axis of the rotor. The rotor forms rotor ports arranged substantially symmetrically around the longitudinal axis at a distal end of the rotor. The IPX further includes an end cover configured to be disposed at the first distal end of the rotor. The end cover forms end cover ports. The rotor ports are arranged for hydraulic communication with the end cover ports. The IPX further includes an insert disposed between two of the rotor ports or between two of the end cover ports.

Abstract: The present invention concerns an adjustment mechanism (200) for variable adjustment of an inlet cross-section (321) of a compressor inlet (322). The adjustment mechanism comprises a plurality of rotatably mounted baffle elements (210) which are arranged in a circumferential direction (26) and are adjustable between a first position and a second position. At least one baffle element (210) of the plurality of baffle elements (210) comprises an eddy-reducing feature (220).

Abstract: A marine vessel propeller to convert engine rotational power into propulsive thrust is of a built-up propeller (BUP) type having a circular array of propeller blades, wherein each propeller blade is a single piece including a blade part and a base part. The base part has a generally circular inner surface with a number of radially extending cylindrical indents provided with planar end wall and fastening holes arranged through the base part at a location of the indents. A cylindrical insert is provided with a hole parallel to a longitudinal axis of the insert and arranged to fit into the indent, such that the propeller blades are attachable to a propeller shaft using exemplary fastening bolts through the fastening holes and inserts. A propeller blade and method for installing a marine vessel propeller are also disclosed.

Abstract: A coating for a blade root/disk interface includes a layer of soft metal matrix, and a solid lubricant distributed through the soft metal matrix. Examples of materials include CuAl as the soft metal matrix and MoS2 as the solid lubricant, although others are also disclosed.

Abstract: Disclosed is a multi-phase abradable coating including a ceramic matrix and a dislocator phase.

Abstract: A fan case assembly adapted for use with a gas turbine engine includes a fan track liner and an annular case. The fan track liner extends circumferentially at least partway about a central axis of the gas turbine engine. The annular case is configured to support the fan track liner at a radial position relative to the central axis. The fan case assembly further includes an air recirculation duct configured to redirect air around the fan track liner.

Abstract: A wind turbine blade comprising a blade shell that extends in a spanwise direction from a root end of the blade to a tip end of the blade, the blade shell defining an internal blade volume within which at least one blade feature is located, the blade being provided with an RF position-identification means configured for detection by an RF detection means external to the blade to enable determination of a reference position for the blade and/or the blade feature. Aspects of the invention also relate to a method of detecting a reference position for a wind turbine blade.

Abstract: Systems and methods for a turbo blanket. Specifically, embodiments are related to a flexible turbo blanket with an alloy layer, insulation layer, and mesh screen layer.

Abstract: A main-body casing having an inlet port or an outlet port, a rotatable rotor shaft, and a rotor coupled to the rotor shaft are provided. A recess portion opened toward the inlet port is formed in the rotor and a fastening portion (a first shaft portion and a second shaft portion) of the rotor shaft is exposed to the recess portion. A cover portion, which is fastened to the fastening portion by a cover-portion fixing bolt and covers at least a part of the recess portion, is formed having a container shape and has a reinforcing portion located in a periphery of the fastening portion that prevents deflection by increasing rigidity. The cover portion also has a contact-pressure generating portion which is pressed by fastening to the fastening portion in a fastening direction and causes a contact pressure to be generated in the fastening direction.

Abstract: A support system may secure a wind turbine above an angled roof. The angled roof may have a first angled surface, an opposite second angled surface, and a peak between the first angled surface and the second angled surface. The support surface may have a first weighted ballast located along a portion of the first angled surface and a second weighted ballast located along a portion of the second angled surface. The support system may have a connector extending between and connecting a portion of the first weighted ballast and a portion of the second weighted ballast. The connector may extend over the peak. The support system may have a mounting portion on the connector for securing a wind turbine to the connector. The first weighted ballast and the second weighted ballast may be sized and weighted to maintain the wind turbine above the peak during wind conditions.

Abstract: Provided is an axial fan including: a motor; and an impeller for sending air in an air-blowing direction, wherein the impeller includes: a base covering the motor; and plural blades mounted on an outer peripheral surface of the base, a wind receiving surface of the blade includes a concave portion recessed toward a downstream side in the air-blowing direction, a bottom point of the concave portion is located downstream in the air-blowing direction relative to a first imaginary line perpendicular to the air-blowing direction, the first imaginary line being drawn in a radial direction from a joint position of the blade where the wind receiving surface and the outer peripheral surface of the base merge, and the bottom point is displaced from inward to outward in the radial direction, in going from upstream to downstream in the air-blowing direction, until reaching a radially central part of the blade.

Abstract: A subsea fluid pressure-increasing machine includes an elongated member that is rotatable about a longitudinal axis. The machine also may include a plurality of impellers each having a leading edge, a trailing edge, a suction side, and a chord line defined by a line between the leading and trailing edges. Each impeller is fixedly mounted to the member such that a chord angle defined by an angle between the chord line and the rotation direction is less than or equal to a stall angle at which a maximum force is exerted on a fluid in a direction primarily parallel to the longitudinal axis when the member is rotated in the rotation direction. At least some of the impellers comprise one or more features that effectively reduce a pressure peak or specific loading of the suction side such that the axial length of the impeller is configured to be reduced without exceeding a desired specific load.

Abstract: The invention relates to a method for manufacturing a turbine engine blade (16) including an active-surface wall (17) and a passive-surface wall (18) separated from one another, this blade (16) including a tip that has a closing wall grouping together the active-surface (17) and passive-surface (18) walls in the region of this tip to define the bottom (23) of a bathtub tip shape located at the tip of the blade, the method comprising a moulding step implementing a core defining the bathtub tip shape. According to the invention, there is a step of adding metal to the bottom (23) of the bathtub tip by means of a Direct Laser Additive Manufacturing (CLAD) method, to deposit material onto the bottom of the bathtub tip to form therein an inner partition (28) supported by the bottom thereof (23).

Abstract: A fan guard for a fan container includes a housing and a plurality of wings. The housing has a hollow interior defined by a cylindrical inner surface. The housing extends longitudinally between a first housing end and a second housing end. The plurality of wings is positioned within the hollow interior of the housing. Each wing of the plurality of wings extends radially, from a center of symmetry of the cylindrical inner surface to the cylindrical inner surface. Each wing of the plurality of wings is radially curved between the first housing end and the second housing end.

Abstract: A passive flow modulation device for a machine defining an axial direction and a radial direction, the passive flow modulation device including: a first ring with a first coefficient of thermal expansion; a second ring disposed coaxially with the first ring and positioned at least partially inward of the first ring along the radial direction, spaced from the first ring along the axial direction, or both, the first ring, the second ring, or both defining at least in part one or more passages, the second ring with a second coefficient of thermal expansion that is less than the first coefficient of thermal expansion to passively modulate a size of the one or more passages during operation.

Abstract: A gear assembly for use with a turbomachine comprises a sun gear, a plurality of planet gear layshafts that each support a first stage planet gear and a second stage planet gear, and a ring gear. The sun gear is configured to rotate about a longitudinal centerline of the gear assembly, and the plurality of planet gear layshafts comprise an interior passage that receives one or more lubrication supply lines.

Abstract: Methods, apparatus, systems and articles of manufacture are disclosed. An example apparatus includes a compressor comprising a rotor defining a radial direction and a circumferential direction, the rotor including a slot; a first blade and a second blade disposed in the slot, the first blade including a first platform and a first dovetail, the second blade including a second platform and a second dovetail; and a hollow block disposed circumferentially between the first blade and the second blade in the slot, the hollow block including: a platform interface portion to interface with the first platform and the second platform, the platform interface portion including a central opening defined by a circumferential face of the platform interface portion; and a hollow dovetail interface portion to couple the first dovetail and the second dovetail.

Abstract: A pressure exchanger (1) including a housing (2), a drive shaft (3) and a cylinder drum (4) rotatably arranged in the housing (2) is described, the cylinder drum (4) including two front faces and at least one cylinder (5) between the front faces, wherein the housing (2) includes a port flange (7, 8) at each end of the cylinder drum (4) and at least at one end of the cylinder drum (4) a pressure shoe (18) is arranged between the cylinder drum (4) and the port flange of this end. Such a pressure exchanger should be operated in a cost-effective manner. To this end an adjustable stop arrangement (19) is arranged between the pressure shoe (18) and the cylinder drum (4).