Abstract: A computing device fan mounting system includes a chassis, a fan housing, and a fan mount. The chassis includes a receiving opening. The fan housing defines a first opening and a second opening. The fan mount includes a first peg engaged with the first opening, a second peg engaged with the second opening, and a pin engaged with the receiving opening.

Abstract: A rotor of a member of a turbomachine, for example a rotor of a turbine, the rotor including a first element, a second element defining with the first element a ventilation cavity, the rotor including a spacer that is introduced and secured between the first element and the second element and that includes a row of through-passages that are configured to permit injection of cooling fluid into the ventilation cavity.

Abstract: A gas turbine engine includes a high pressure compressor disposed about a central longitudinal axis, a combustor, and a diffuser case. The diffuser case includes an outer ring providing a first platform and an inner ring providing a second platform. The first platform and the second platform are axially between the high pressure compressor and the combustor with respect to the central longitudinal axis. A plurality of circumferentially spaced struts extend radially from the first platform to the second platform and each include first and second circumferential sides. A plurality of heat shields are disposed on a leading edge defined at a forward end of a respective one of the plurality of struts.

Abstract: An apparatus and method for a component for a turbine engine, which generates a hot gas flow, and provides a cooling fluid flow, comprising a wall separating the hot gas flow from the cooling fluid flow and having a heated surface along which the hot gas flows and a cooled surface facing the cooling fluid flow and at least one cooling hole comprising a connecting passage extending between an inlet at the cooled surface and an outlet located at the heated surface, with the connecting passage comprising a diffusing section.

Abstract: The invention relates to distributor blading (10) having a blade (12), including a pressure-side wall (16) and a suction-side wall (14), and an insert (20) placed in the blade (12) and including: a closed wall (22) having an outer skin (24) extending opposite the pressure-side walls (16) and suction-side walls (14), the outer skin (24) and the wall of the facing blade (12) being separated by an air gap (30), a series of reinforcements (25) formed in the closed wall (22) and leading into the outer skin (24), and a series of through-openings formed in the reinforcements (25), the heights of impact (h) between said through-openings and the pressure-side wall (16) or the facing suction-side wall (14) being greater than the air gap (30).

Abstract: A cooling device includes a cooler disposed inside a shell, an inlet nozzle that is configured to feed a fluid into the shell, an outlet nozzle that is configured to feed the fluid passing through the cooler so as to flow outward, and a guide member that is configured to change a flowing direction of the fluid. The guide member has a collision surface which spreads in an inclined direction inclined with respect to the flowing direction of the fluid fed into the shell from the inlet nozzle, and which collides with the fluid, and an uneven portion formed in at least a portion of a peripheral edge portion of the collision surface.

Abstract: A tail rotor blade for a helicopter includes a blade body defining a longitudinally extending spar cavity, a leading edge forward of the spar cavity, and a trailing edge aft of the spar cavity. Upper and lower airfoil surfaces extend from the leading edge to the trailing edge on opposite sides of the spar cavity. The upper and lower airfoil surfaces define between one another a constant airfoil segment and transition airfoil segments disposed longitudinally adjacent to the constant airfoil segment on inboard and outboard sides of the constant airfoil segment.

Abstract: A fan is equipped with a boss, a first blade member, and a second blade member. The boss has: a first end and a second end an axial direction; an inclined surface inclined, in a direction from the second end to the first end, toward an axial center extending in the axial direction; and an outer peripheral surface located between the inclined surface and the second end. The boss is rotatable about the axial center. The first blade member is connected to the outer peripheral surface of the boss. The second blade member is connected to at least one of the inclined surface or the outer peripheral surface located between the inclined surface and a connecting portion where the first blade member is connected to the outer peripheral surface.

Abstract: In this pump, the angle between the imaginary tangent plane to the lip and passing through the axis and an imaginary straight line, perpendicular to the axis and passing through the point furthest from the axis of intersection of the upper surface of a finger with the lateral leading surface of this finger, is between 110 and 140°.

Abstract: A blade track assembly and methods thereof includes an anti-rotation device having an arcuate body and tabs extending for engagement within an anti-rotation slot of the blade track. The anti-rotation device may be formed to include an annular shape connected at a flange of the casing to reduce spatial requirements while blocking against rotation of the blade track.

Abstract: An airfoil array includes an endwall. A first airfoil and a second airfoil each extend radially from the endwall and have a first side and an opposite second side that extend along an axial chord between a leading edge and a trailing edge. A first profiled region protrudes from the endwall along the first side of the first airfoil. A second profiled region protrudes from the endwall along the leading edge of the second side of the second airfoil adjacent the leading edge of the second airfoil. A third profiled region recessed into the endwall approximately equidistant from the first side of the first airfoil and the second side of the second airfoil.

Abstract: A wind wheel includes a main shaft, a wind plant hub, and a plurality of blades. Each blade includes a short elbow part with axial and sleeve segments connected at 30°-45° angle and a long wing-shaped part, connected to the sleeve segment with an end shaft and by support devices with bearings. The short elbow part is made of steel, and is a distance of 1.5-5 meters or 0.20-1.5 meters from a connection thereof to the hub, and at a juncture of the axial and sleeve segments has a 10°-80° elbow bend opposite a direction of rotation of the wind wheel. The sleeve segment of the short elbow part has a cylindrical skeleton with three double support rings and is connected to the wing-shaped part of the blade, a root end of which is supplied with a hollow steel shaft with three removable protuberances with the bearings.

Abstract: A blower having high efficiency and low noise by actively controlling airflow in the blower, and an air conditioner having the blower is provided. The air conditioner has a blower. The blower includes a fan having a hub and at least one blade provided on an outer circumferential surface of the hub, a motor to rotatably drive the hub, a shroud configured to surround the periphery of the fan and at least one actuator installed in the shroud and configured to form an airflow along an inner circumferential surface of the shroud.

Abstract: A set of impellers that are axially adjacent to each other and that have respective axial through holes are assembled. At least a first and a second axial tie rods are used. At least one connection element being axially adjacent to two impellers respectively at its two sides and having an axial through hole is provided. The connection element is used for securing, at one side of its axial through hole, an end of the first axial tie rod and, at the other side of its axial through hole, an end of the second axial tie rod. Typically, the connection element is one of the impellers of the set.

Abstract: A pump assembly includes an impeller (18), which for rotation is connected to an electrical drive motor (20) which can be driven in two rotation directions (A, B) and a valve (10) situated in an inlet of the pump assembly. The valve includes a valve element (48) movable between at least two switch positions and is connected for movement to a drive element (36, 60) subjected to the flow produced by the impeller (18). The valve element (48), in at least a first of the two switch positions, closes an inlet channel (44, 46) of the pump assembly (12) and is arranged such that the movement direction into this first switch position corresponds to the flow direction (S1, S2) through this inlet channel (44, 46). A hydraulic system is provided with two circuits and such a pump assembly. The valve serves as a switch-over valve between the two circuits.

Abstract: An airfoil includes a first wall and a second wall that at least partially define a channel, and a trip strip coupled to the first wall, where at least a part of the trip strip forms a corrugated pattern. A gas turbine engine includes a compressor section, a combustor section, and a turbine section, where the turbine section includes an airfoil, where the airfoil includes a first wall and a second wall that at least partially define a channel, and a trip strip coupled to the first wall, where at least a part of the trip strip forms a corrugated pattern.

Abstract: An assembly is provided for rotational equipment such as a gas turbine engine for an aircraft propulsion system. This assembly includes a stator, a rotor and a seal assembly. The rotor extends axially along a centerline. The rotor includes a linkage, a first rotor disk, and a second rotor disk. The linkage extends axially from the first rotor disk to the second rotor disk. The linkage is removably attached to the second rotor disk. The seal assembly is configured for sealing a gap radially between the stator and the linkage. The seal assembly includes a hydrostatic non-contact seal.

Abstract: A blade-fold bushing system includes a splined bushing comprising a first plurality of teeth, a castellated bushing comprising a second plurality of teeth and a shaft portion configured to coaxially fit within the splined bushing, and a lock bushing coaxially aligned with the castellated bushing. A support tool for use with a blade-fold bushing system includes an outer head comprising a third plurality of teeth configured to mesh with the first plurality of teeth of the splined bushing, and an inner head comprising a fourth plurality of teeth configured to mesh with the second plurality of teeth of the castellated bushing.

Abstract: The present disclosure is related to turbine wheel assemblies for gas turbine engines. Such turbine wheel assemblies may include ceramic matrix composite airfoil components mounted with different types of coupling to a central disc.

Abstract: A multi-piece fan spacer for a gas turbine engine includes at least one lug comprising a platform portion, a connection portion radially inward of the platform portion, and a support connecting the platform portion to the connection portion. The multi-piece fan spacer includes a plurality of platforms. Each of the platforms is connected to at least one axially adjacent platform portion.