Abstract: A gas turbine engine includes an engine core, a power gearbox, and a lubrication system. The engine core is configured to drive rotation of at least one shaft. The power gearbox is configured to transfer torque from the at least one shaft to other parts of the gas turbine engine. The lubrication system is configured to deliver lubrication to the power gearbox to reduce friction and cool rotating components within the power gearbox.

Abstract: A blade outer air seal includes a base portion that extends between a first circumferential side and a second circumferential side and from a first axial side to a second axial side. A first hook extends from the base portion and circumferentially spaced from a second hook. The first and second hooks extend along an axial length of the base portion. The first circumferential side has a protrusion and the second circumferential side has a groove.

Abstract: A blade 20 for a horizontal-axis wind turbine rotor comprises a radially-outer, energy-extraction portion 32 and a radially-inner, ventilation portion 30. The radially-inner ventilation portion 30 is shaped to ventilate a central area 34 of a wake of the rotor during use such that it contains more kinetic energy compared to the wake from a conventional rotor design. The increased wind flow velocity at the centre 34 of the wake generates additional shear stresses, with corresponding turbulence development, which gives rise to increased wake diffusion.

Abstract: A hydraulically actuated liftable and lowerable hook of a crane has a hydraulic system comprises at least one working machine with a hydraulic motor driving a winch. At least one drive machine comprising a pump is connected directly or indirectly to at least one of the working machines by means of two connections via corresponding working lines, which serve as a feed or return depending on the operating state of the working machine. A lowering brake valve is provided in one working line and is connected to the other working line via a control line such that the lowering brake valve is displaceable against a restoring force by pressure, which prevails in the other working line and is forwarded via the control line, from the blocking position of said valve into a through-flow position for lowering the hook by means of a primary winch.

Abstract: A site-specific customizable nacelle for a wind turbine includes a plurality of walls arranged together to form an inner volume. The walls include a base wall, side walls, a front wall, a rear wall, and a top wall. Each of the walls is constructed of one or more outer skin layers positioned adjacent to one or more inner skin layers and infused together via a resin material. Further, the nacelle includes a plurality of reinforcement members secured to one or more of the plurality of walls on an interior side or an exterior side of at least one of the one or more outer skin layers or the one or more inner skin layers at locations requiring additional reinforcement. As such, the reinforcement members can be tailored according to a particular wind turbine site.

Abstract: Assembly forming a labyrinth seal for a turbomachine, comprising: at least one abradable material of which the inner surface defines a stair shape with a sequence of treads and risers; a plurality of fins extending radially toward said inner surface, the fins each comprising, at least in part, an upstream side wall forming a riser facing the corresponding fin such that, when seen in axial cross-section, the tangent at the top of the upstream side wall of at least one fin and the straight line passing through the downstream side wall of said at least one abradable material intersect, the angle between said tangent and said straight line being strictly between 5 and 15°.

Abstract: Provided is a rotary machine including a rotating resinous impeller, a rotary shaft penetrating the impeller, and a fastening portion screwed to the rotary shaft, in which the rotary shaft includes a penetrating shaft portion facing an inner peripheral surface of the impeller, a tip shaft portion screwed to the fastening portion, and a fastening reception portion sandwiching the impeller between the fastening reception portion and the fastening portion, the penetrating shaft portion has a non-circular portion and an outline of a cross section of the non-circular portion orthogonal to a rotational axis deviates from a perfect circle about the rotational axis, and the impeller includes a connecting portion engaging with the non-circular portion.

Abstract: A section for a gas turbine engine according to an example of the present disclosure includes, among other things, a rotor having a hub carrying a plurality of blades, the hub rotatable about a longitudinal axis, and a seal extending outwardly from the hub to establish a sealing relationship with a plurality of vanes distributed about the longitudinal axis. A flow guide assembly is secured to an engine static structure such that a flow path is defined between the hub and the flow guide assembly. The flow path has an inlet portion defined along the seal and an outlet portion, and the flow guide assembly includes an acoustic liner that extends along the flow path.

Abstract: A blade outer air seal segment including a radially outward surface, a radially inward surface oriented away from the radially outward surface, and a cooling channel located between the radially outward surface and the radially inward surface. The blade outer air seal segment also including a stress-relief boss extending into the cooling channel and an inlet orifice fluidly coupled to the cooling channel through the stress-relief boss.

Abstract: A centrifugal compressor according to an exemplary aspect of the present disclosure includes, among other things, an impeller provided in a main flow path and configured to pressurize a main flow of fluid. The compressor also includes a secondary flow path configured to provide a secondary flow by recirculating a portion of the main flow. The amount of the main flow that becomes the secondary flow is less than or equal to 15%. A method is also disclosed.

Abstract: A gas turbine engine includes a compressor section and a turbine section. The turbine section includes at least one turbine rotor having a radially extending turbine blade. The turbine section is rotatable about an axis of rotation. A blade outer air seal is positioned radially outwardly of a radially outer tip of the at least one turbine blade. The blade outer air seal has axially spaced forward and aft portions and a central web between the axially spaced portions. An attachment block is supported on structure within the engine. The attachment block mounts the blade outer air seal. A passage extends into a central chamber within the attachment block, and communicates with cooling holes through a radially inner face of the attachment block to direct cooling air at the central web of the blade outer air seal. A blade outer air seal is also disclosed.

Abstract: A work machine is provided. The work machine includes a changeover valve capable of disabling area limiting control by bypassing an area limiting control solenoid proportional valve disposed in a pilot line through which pilot pressure generated by a hydraulic pilot type operation device is guided to a directional control valve and the work machine can perform the area limiting control while ensuring response of a work implement. When a first fluid temperature T1 is higher than a first predetermined temperature Ta and a control changeover switch 66 specifies disabling of the area limiting control, a controller brings a plurality of changeover valves into a bypass position. When the first fluid temperature T1 is equal to or lower than the first predetermined temperature Ta, the controller brings the changeover valves into a communication position and places the solenoid proportional valves in a fully open position.

Abstract: A heating, ventilating, and air conditioning (HVAC) system that includes a fan. The fan includes a plurality of blades coupled to a hub. A shroud is coupled to the plurality of blades, wherein the shroud focuses a flow of air along a rotational axis of the fan and reduces the flow of the air radially outward from the fan.

Abstract: A balance system for an assembled engine includes a rotor mounted on a shaft for rotation within an engine casing having an inner case and an outer case; and a weight system mounted on the shaft of the rotor and having at least one weight positionable relative to the rotor around a circumference of the shaft; wherein the inner case has an inner access port, the outer case has an outer access port, and the inner access port, the outer access port and the weight system are positioned on the same radial plane of the rotor, whereby the weight system can be accessed through the outer port and the inner port to adjust circumferential position of the at least one weight relative to the rotor.

Abstract: A fan includes a fan frame, an impeller, and at least a supporting member. The fan frame includes a bottom plate and a cover plate spaced from the bottom plate. The bottom plate and the cover plate together define a first accommodating space. The cover plate has an air inlet disposed in an axial direction. A side of the fan frame is provided with at least an air outlet. The impeller is disposed in the first accommodating space and includes a hub and a plurality of blades. A cross-sectional area of the hub increases gradually along a direction from the cover plate to the bottom plate. The blades are disposed around the periphery of the hub. The supporting member is disposed between the bottom plate and the cover plate for supporting the cover plate.

Abstract: A cooling circuit to receive a cooling fluid includes at least one shaped cooling pin disposed in the cooling circuit. The at least one shaped cooling pin has a first end and a second end extending along an axis. The first end has a first curved surface defined by a minor diameter and the second end has a second curved surface defined by a major diameter. The first curved surface is to be upstream in the cooling fluid and the minor diameter is less than the major diameter.

Abstract: A rotor assembly includes a plurality of rotor disks that each have a rim portion. The plurality of rotor disks includes a first rotor disk and at least one first bleed air passage that extends through a forward rim portion of the first rotor disk. At least one second bleed air passage that extends through an aft rim portion of the first rotor disk.

Abstract: A blade (10) for a turbomachine is provided. The blade (10) includes an airfoil (16) having at least one thickening (22) on a pressure side (20) of the airfoil (16). The thickening (22) has a region (B) of constant thickness (D). A turbomachine, a compressor and a turbine having stator vanes and/or rotor blades including at least one such blade (10) is also provided.

Abstract: A shroud for a cooling fan that is being positionable within the chassis of an off-highway machine. The shroud includes an inlet, an outlet, an elliptical lip section positioned adjacent to the outlet, and a plurality of apertures extending through the elliptical lip section. Each aperture of the plurality of apertures is positioned greater than 10 degrees away from an adjacent aperture of the plurality of apertures.

Abstract: Disclosed are a blade ring segment for a turbine section, a turbine section having the blade ring segment, and a gas turbine having the turbine section. Multiple blade ring segments is installed in a turbine casing accommodating turbine blades rotated by combustion gas from a combustor. The blade ring segment includes an inner panel provided in the turbine casing and having multiple air holes through which cooling air fed from the outside of the turbine casing flows, an outer panel disposed on one side of the inner panel, and a cooling structure protruding from one side of the outer panel so as to form a flowing channel in a zigzag pattern so that cooling air fed through the air holes flows therethrough.