Abstract: The invention relates to a device for connection between two enclosures of a turbomachine, for enabling the circulation of a coolant between said enclosures, via said connection device, said connection device comprising an outer tube (2) having an opening (3) extending along the entire length of said outer tube (2), and also comprising an inner tube (6) extending inside the outer tube (2).

Abstract: The invention is related to a control system for controlling collective and cyclic pitch of rotor blades of a multi-blade rotor 1a in a rotary-wing aircraft, the control system comprising a swash plate assembly with at least one non-rotating plate and at least one rotating plate that is mounted rotatably to the at least one non-rotating plate, the at least one rotating plate and the at least one non-rotating plate being mounted to a non-rotating sliding sleeve, wherein a spherical bearing is provided on the non-rotating sliding sleeve, wherein at least one non-rotating stop arm is provided for non-rotatably connecting the at least one non-rotating plate to the non-rotating sliding sleeve.

Abstract: A blade cascade for a gas turbine, which has a first group with at least two, in particular at least three, first blade arrangements of the same type to one another, on which first element arrangements that are identical to one another and have at least one first element are movably mounted; and a second group with at least two, in particular at least three, second blade arrangements, which are of the same type to one another and are of different type from the first blade arrangements, on which second element arrangements, which are identical to one another and have at least one second element are movably mounted, wherein first and second element arrangements are different from each other.

Abstract: The invention relates to a turbomachine bearing support (1) supporting at least one bearing and extending according to a longitudinal principal axis of the turbomachine and comprising: a truncated part (11) having a diameter increasing from upstream to downstream; a flange part (12) which extends from the truncated part (11) as far as the bearing (5, 6) to which it is fixed by an axial flange (121), and having at its downstream end a radial internal flange (17) fixed to an oil inlet cover defining with the bearing (5, 6) an oil inlet container (170); oiled air clearance ducts (71) projecting downstream relative to the flange part (12) and on the oil inlet container (170) and to the other side upstream of the flange part (12) directly radially externally relative to the axial flange (121).

Abstract: An active clearance control system of a gas turbine engine includes an actuation cylinder, a puller engaged with an air seal segment and damped with respect to the actuation cylinder, and a full-hoop thermal control ring that at least partially supports the air seal segment. The puller may move the air seal segment between an extended radially contracted BOAS position and a retracted radially expanded BOAS position.

Abstract: A lift fan for use in short takeoff and vertical landing (STOVL) aircraft is disclosed and claimed. The lift fan is driven by bleed air from a main engine of the aircraft and may be controlled by an electromagnet. This eliminates the drag and torque on the main engine and reduces fuel cost and engine wear.

Abstract: An impeller is arranged to rotate about a central axis, and includes a disk-shaped portion arranged to extend radially with respect to the central axis, and a plurality of rotor blades arranged along a circumferential direction on one surface of the disk-shaped portion. Each rotor blade has one end arranged at an outer edge portion of the disk-shaped portion, and an opposite end arranged radially inward of the outer edge portion of the disk-shaped portion. The rotor blades include a plurality of first rotor blades each of which includes a first curvature portion and a plurality of second curvature portions. A center of the radius of curvature of the first curvature portion of each first rotor blade is arranged on a first side of the first rotor blade with respect to the circumferential direction. A center of the radius of curvature of each second curvature portion of each first rotor blade is arranged on a second side of the first rotor blade with respect to the circumferential direction.

Abstract: Methods of installing a blade in a wind turbine are provided, the wind turbine comprising a tower, a nacelle and rotor hub, the rotor hub comprising a guiding element. The method includes providing a blade holder, wherein the blade holder comprises a beam, the beam being attached to the blade holder. The method further includes providing lifting equipment for lifting the blade holder, attaching the blade holder to the blade, wherein the blade comprises a mount for mounting the blade to the rotor, connecting the lifting equipment to the blade holder, hoisting the blade holder with the blade towards the rotor hub, arranging the beam near the guiding element, bringing the guiding element and the beam in contact with each other and attaching the blade mount to the rotor hub. Wind turbines comprising a rotor hub, the rotor hub comprising a guiding element are also disclosed.

Abstract: A piston rod assembly for a pressurized fluid-powered actuator is provided. The assembly includes a piston rod having a fluid flow passage extending along an interior thereof, and a cap secured to the piston rod at a position along the fluid flow passage. Sealing means is positioned between the piston rod and the cap so as to provide a fluid-tight seal between the piston rod and the cap.

Abstract: A wind turbine blade is described wherein at least on planar member is provided on the blade surface, where the planar member is arranged such that it extends at an angle to the chord of the blade. The planar member acts to re-direct airflow over the blade, to improve wind turbine performance. The planar member may be a stall fence provided towards the blade root end, further acting to divert airflow towards the root end of the blade to prevent separation of attached airflow. Additionally or alternatively, the planar member may be a flow diverter provided towards the blade tip end, to increase airflow in the tip region for increased performance and/or to disrupt the formation of tip vortices.

Abstract: A composite beam for a wind turbine blade includes a preform layer, the preform layer including multiple elongate strength rods arranged longitudinally relative to one another in a single layer, each strength rod being disposed adjacent to and spaced from at least one adjacent strength rod. Each strength rod has a rectangular cross section and includes multiple, substantially straight collimated structural fibers fixed in a solidified matrix resin. The preform layer includes at least one carrier layer to which the multiple strength rods are joined by an adhesive. The carrier layer spaces adjacent strength rods a fixed distance apart to facilitate the flow of liquid bonding resin between adjacent strength rods of the preform layer to its joined carrier layer, the carrier layer being of a permeable material suitable to facilitate the flow of liquid bonding resin through the carrier layer.

Abstract: A power transmission assembly for a vehicle with prime mover, prime mover output shaft, and right and left traveling devices, comprises a power distribution unit that receives rotary power from the prime mover output shaft and distributes it between right and left transmission units, which each include: a center section with a closed fluid circuit, a lateral first portion, and a second portion perpendicular thereto; a hydraulic pump mounted on the first portion such that a pump shaft is parallel to the prime mover output shaft; a hydraulic motor on the second portion fluidly connected to the hydraulic pump via the closed fluid circuit, having a lateral motor shaft; and a speed reduction device on a distal side of the hydraulic motor that transmits power from the hydraulic motor to the right or left traveling device.

Abstract: A coning-resistant rotor and a seal assembly including a coning-resistant rotor are disclosed. An embodiment of the rotor includes a rotor base, a rotor head, and an axially-extending web interposed between the rotor base and rotor head, wherein the web includes axial and radial web regions defined by at least one circumferential groove provided in the web. In another embodiment, a rotor base includes a sealing surface and an inner diameter surface, and the inner diameter surface includes a channel with a taper.

Abstract: Multiple guide claws are formed integrally on a right side surface of a first nozzle ring of a variable nozzle unit and radially at intervals in a circumferential direction. Each guide claw has a guide groove with a U-shaped cross section, which is formed by lathe turning. A projecting portion is formed at an inner edge portion on the right side surface of the first nozzle ring. The projecting portion is formed on base portions of the multiple guide claws.

Abstract: An air compressor includes a rotating device pivotally connected to a piston body. The rotating device includes a gear body and a counterweight. The gear body is formed together with a counterweight, wherein the counterweight is provided with a crankshaft corresponding to the center of the gear body and a crankpin placed at a distance from the crankshaft. The counterweight is horizontally divided into two integrally formed halves, including a left half and a right half, with a common line connected between the center of the crankshaft and the center of the crankpin, wherein the left half has a weight different from the right half, so that the piston body gathers more rotational momentum from the counterweight at BDC to facilitate upstrokes, so that the piston body can conduct reciprocating motion more smoothly, and thus the service life of the air compressor can be increased.

Abstract: A turbine case cooling system and a method for supplying a cooling gas flow are provided. The cooling system has a turbine case and a turbine case cooling manifold. The cooling system also has a fluid or cooling conduit. The cooling conduit has an inlet in fluid communication with the bypass duct, and an outlet in fluid communication with the cooling manifold. The cooling conduit also has an ejector section which in use supplies a motive air flow radially into the cooling conduit to draw a bypass air flow from the bypass duct. The motive air flow mixes with the bypass air flow to form the cooling gas flow. The cooling conduit also has a diffuser section which in use conveys the cooling gas flow toward the outlet in a direction substantially perpendicular to the center axis of the gas turbine engine.

Abstract: A compressor for a motor-compressor set, comprising, on a rotating shaft, a balancing piston, a set of bladed wheels, a rear cavity of the piston adjacent to the balancing piston on a side opposite to the set of bladed wheels, a regulation valve suitable for coupling the rear cavity to the input of the set of bladed wheels, a suction pressure chamber coupled to the input of the set of bladed wheels, the rear cavity being arranged between the balancing piston and the suction pressure chamber. The compressor comprises a discharge pressure chamber arranged between the rear cavity of the piston and the suction pressure chamber, the discharge pressure chamber being coupled via a discharge line to a discharge area between the set of bladed wheels and the balancing piston.

Abstract: An article of manufacture having a nominal airfoil profile substantially in accordance with Cartesian coordinate values of X, Y, and Z set forth in a scalable TABLE 1, wherein the Cartesian coordinate values of X, Y, and Z are non-dimensional values convertible to dimensional distances by multiplying the Cartesian coordinate values of X, Y, and Z by a number, and wherein X and Y are coordinates which, when connected by continuing arcs, define airfoil profile sections at each Z height, the airfoil profile sections at each Z height being joined with one another to form a complete airfoil shape.

Abstract: A propeller which can be folded and stowed in compact form and then deployed for powered flight is disclosed. The deployable propeller has two or more blades, and each blade is composed of multiple segments which are disengaged when stowed and then interlock when deployed to form an efficient blade. The segmented deployable propeller retains all effective area to the spinner radius.

Abstract: A composite turbine blade for high-temperature applications such as gas turbines or the like includes a root for mounting the blade in a corresponding circumferential assembly groove of a rotor and an airfoil connected to said root. An inner carrying structure is provided extending at least over a portion of the root as well as at least a portion of said airfoil. The inner carrying structure is made of a high strength eutectic ceramic and the airfoil is made of a ceramic matrix composite (CMC) material.