Abstract: Systems and methods include providing an aircraft with a direct drive dual-concentric valve (D3V) having a body, an outer secondary spool coaxially located within a bore of the body and linearly displaceable relative to the body, an inner primary spool coaxially located within a bore of the secondary spool and linearly displaceable relative to the secondary spool and the body. A plurality of piezo stacks is coupled to a first end of the primary spool, and applying a voltage to at least one of the piezo stacks causes an output stroke of the plurality of the piezo strokes for displacing the primary spool. The secondary spool is displaced together with the primary spool relative to the body if displacement of the primary spool relative to the secondary spool cannot occur.

Abstract: An unducted thrust producing system, includes a rotating element, a stationary element. An inlet may be located forward or aft of the rotating element and the stationary element. An exhaust may be located forward, aft, or between the rotating element and the stationary element.

Abstract: A turbine vane of a turbine engine such as a turboprop or a turbojet, the vane comprising a root supporting a blade, the vane including at least one air-circulation duct for cooling the air during operation, the duct including, at the vane root, an inlet portion for collecting the cooling air, the inlet portion extending away from a lower surface of the vane root opposite the blade. At least one inlet portion is provided with a helical element for rotating the cooling air in order to improve the cooling efficiency thereof.

Abstract: A built-in air pump with rapid inflation and deflation for an inflatable product includes a first channel, a second channel and a centrifugal fan. A first air hole and a third air hole are formed in the first channel. A second air hole and a fourth air hole are formed in the second channel. The suction end of the centrifugal fan is abutted against the first channel, and the exhaust end of the centrifugal fan is abutted against the second channel. When in inflation, the first air hole and the second air hole are communicated with the outside of the inflatable product, and the third air hole and the fourth air hole are communicated with an inner cavity of the inflatable product.

Abstract: A blower is disclosed. The blower of the present disclosure comprises: a fan for producing air flow; a lower body providing an inner space in which the fan is installed, and having an intake hole through which air passes; an upper body placed on the lower body to form a flow passage which communicates with the inner space of the lower body, and having a space which is formed to pass through the upper body in the forward and backward direction, wherein the upper body includes a slit which is formed through the upper body and through which air flowing through the flow passage of the upper body is discharged to the space, and the slit comprises: a rear slit adjacent to the rear end of the upper body; and a front slit adjacent to the front end of the upper body.

Abstract: The present invention relates to a compressor and, more specifically, to an air compressor for a vehicle, which can support a rotor disk and form a cooling flow channel by a first cover and a second cover, and thus can improve cooling efficiency while increasing manufacturability.

Abstract: A centrifugal compressor includes: a housing including an intake flow path; a compressor impeller arranged in the intake flow path; an accommodation chamber formed upstream of the compressor impeller in a flow of intake air in the housing; a movable member arranged in the accommodation chamber; and an annular path formed in the housing, the annular path being connected to an outside of the housing, a heating medium supplied from the outside of the housing flowing through the annular path, at least a part of the annular path being located between the accommodation chamber and a leading edge of the compressor impeller.

Abstract: A method for positioning a ram air turbine during its assembly on a primary structure of an aircraft. The method includes the steps of: placing a first distance sensor on a first element among a first flap and the ram air turbine, a second distance sensor on a second element among a second flap and the ram air turbine, the first and second distance sensors being configured to respectively emit first and second signals corresponding to measured values over time of a distance between each of the first and second distance sensors and at least one mobile target attached to the ram air turbine or the first and second flap, pivoting the mast between the retracted and deployed positions, analyzing the first and second signals, and, if necessary, repositioning the ram air turbine according to the step of analyzing the first and second signals.

Abstract: A gas (or steam) turbine is disclosed including: a rotor with at least one array of rotor blades, a stator with a casing and a shroud ring; the shroud ring extends around the array of blades rotor and the casing extends around the shroud ring. The shroud ring has radial size independent from temperature due to its material and is movably coupled with the casing so to allow the casing of the stator to thermally expand and contract during operation of the turbine while maintaining the shroud ring radial size. Also, the rotor thermally expands and contracts during operation of the turbine, and, at working temperature, tip regions of the rotor blades are in close proximity to an inner region of the shroud ring so that clearance is small or zero at working condition.

Abstract: A gas turbine engine including a rotating shaft and a bearing assembly. The bearing assembly is configured to support the rotating shaft. The bearing assembly has a first bearing and a second bearing. The first bearing is configured to support an axial load of the rotating shaft when a forward thrust of the rotating shaft is greater than ten percent. The second bearing is configured to support the axial load of the rotating shaft when a thrust of the rotating shaft is between ten percent forward thrust and ten percent aft thrust, inclusive of the end points.

Abstract: An air inlet manifold and a gas turbine including the same, capable of preventing transmission of vibration from the gas turbine to the air inlet manifold, while at the same time preventing air leakage, and the air inlet manifold is installed to be spaced apart from the compressor and relatively movable, as the anti-vibration pad in a compressed state is interposed between the air inlet manifold and the compressor.

Abstract: A rotor assembly includes a first component, a second component, and a splined balance weight. The first component is arranged circumferentially around a central axis. The second component is arranged circumferentially around the central axis. The splined balance weight is located radially between the first component and the second component.

Abstract: A method of activating an ice removal system of a wind turbine comprises: monitoring the output power of the wind turbine; monitoring an output from an ice sensor provided on the wind turbine indicative of an atmospheric icing condition; and activating the ice-removal system when the output power is below an expected output power and the output from the ice sensor indicates that an atmospheric icing condition has ended.

Abstract: Components are fastened with inserts that are placed into a hole in the component and bonded with an adhesive. A decoupling element is provided on the front face of the insert. This diverts the forces around the highly stressed front face of the inserts. The insert may be of a material with a lower stiffness compared with the adhesive. This arrangement may reduce stress peaks and increase the load capacity of the connection. A tool may be provided that reduces air inclusion between the insert and the component during fitting. The connection arrangement can be used when components of different stiffnesses have to be securely connected to one another. This applies to, among other things, fastening of fibre composite components or mineral components to metal components.

Abstract: A mass damper module (600) for a wind turbine installation comprises: an attachment interface (603a-d) adapted to removably attach the mass damper module to structural lifting parts (303a-d) of a nacelle (300) of the wind turbine installation; and an active tuned mass damper (601) controllable to damp vibration of the wind turbine installation when the mass damper module is so attached to the nacelle and the nacelle is attached to a tower (200) to form the wind turbine installation.

Abstract: A planetary gear box (and method of assembly), where the gear box includes a sun gear, a plurality of planet gears, a ring gear, a plurality of planet pins, an axially forward carrier plate and an axially rearward carrier plate. Each planet pin is fixed respectively at its axially forward end on the axially forward carrier plate and at its axially rearward end on the axially rearward carrier plate of the planetary gear box. The planet pin is of two-part design and forms a radially outer pin part and a radially inner pin part, which are connected to one another in a manner precluding relative rotation therebetween, wherein the radially outer pin part forms a bearing with the planet gear, and only the radially inner pin part is fixed at its axial ends to the forward and rearward carrier plates.

Abstract: A gearbox assembly includes a plurality of planet gears. At least one planet gear of the plurality of planet gears includes a layshaft that supports a first stage planet gear and a second stage planet gear. The at least one planet gear is characterized by a Radial Stage Distance greater than or equal to 30 millimeters and less than or equal to 100 millimeters. The Radial Stage Distance is Rrm1?Rrt2. Rrm1 is a first stage rim inner radius of the first stage planet gear and Rrt2 is a second stage root radius of the second stage planet gear.

Abstract: A gas turbine engine according to an example of the present disclosure includes, among other things, a propulsor section including a propulsor that delivers flow to a core flowpath and a compressor section including first and second compressors. The core flowpath passes through the first compressor. The core flowpath in the first compressor has an outer diameter relative to the engine longitudinal axis. The outer diameter has a slope angle relative to the axis.

Abstract: A gas turbine engine includes a propulsor section including a propulsor, a compressor section including a first compressor and a second compressor, a geared architecture, a turbine section including a first turbine and a drive turbine, and a power density of greater than or equal to 4.75 and less than or equal to 5.5 lbf/in3, wherein the power density is a ratio of a thrust provided by the engine to a volume of the turbine section.

Abstract: The present invention relates to an impeller comprising: a shroud having a plurality of spiral upper slot units formed therein; a hub located to face the shroud; and a plurality of blades connected to the hub and inserted into the upper slot units to be coupled to the shroud, wherein the blade includes a body portion formed to be inclined to one side and an upper end portion, which is bent upward from the body portion and has a second concave surface formed in one side and a second convex surface formed on the other side thereof, and the upper slot unit includes an upper slot bottom for forming a space in which the upper end portion is inserted; an upper slot wall divided into a first upper slot wall located at the second concave surface side and a second upper slot wall located at the second convex surface side; and a second inclined surface formed to be inclined from the first upper slot wall so as to face the second concave surface.