Abstract: A ceramic shroud assembly includes a tip shroud having an outer platform supporting at least one seal tooth, a shroud cap less brittle than the outer platform and including a shroud cap base on the outer platform, and clockwise and counter-clockwise facing clockwise and counter-clockwise contact surfaces located at clockwise and counter-clockwise distal ends respectively of the base. A rotor assembly may include a circumferential row of turbine blades made of a ceramic material and extending radially outwardly from a disk of a turbine rotor. The turbine blades include airfoils having the airfoil tip shrouds and the shroud caps at blade tips. The clockwise and counter-clockwise contact surfaces of circumferentially adjacent ones of the shroud caps contact each other. The shroud and the platform may be made of a ceramic or ceramic matrix composite material and the shroud cap may be made of a metallic material.

Abstract: A turbine wheel having an axis of rotation and including: a disk having a periphery and a side face; a plurality of blades assembled on the disk, each blade having a blade root and a first hook oriented radially and defining a first groove that opens radially towards the axis of rotation of the turbine wheel. The disk includes a series of second hooks oriented radially and defining a second groove that opens radially towards the axis of rotation of the turbine wheel. An axial retaining ring for placing in the first and second grooves includes a tab for placing between two adjacent blade roots to limit movements of the ring in azimuth.

Abstract: A twist mechanism for twisting a rotary-wing blade (2). A twist member (8) is movable by an actuator (11) of the centrifugal force type, which twist member has at least one flyweight (14) for driving a rotary member (13) about a pivot axis (A). The flyweight (14) is radially movable on the rotary member (13) by movement means. The centrifugal force FC to which the flyweight (14) is subjected as a result of the blade (2) being caused to rotate induces drive torque CM for causing the rotary member (13) to pivot, thereby causing the twist member (8) to be moved. The twist member (8) is in engagement with the blade (2) at its free end and is connected to the rotary member (13) via remote mechanical transmission means (12).

Abstract: A hydraulic drive unit for use in a vehicle or other application incorporates a motor connected to a pump through a porting system and an output shaft driven by the motor. A mechanical brake is used to brake the motor, while a valve provides a hydraulic brake for preventing flow between the hydraulic motor and the hydraulic pump. A brake actuator is connected to both the mechanical brake and the hydraulic brake, whereby actuation of the brake actuator causes both the mechanical brake and the hydraulic brake to be actuated.

Abstract: A hydraulic cylinder includes a piston that defines a driving pressure chamber and a cushion pressure chamber within a cylinder tube, an air chamber defined inside a hollow piston rod, an orifice that leads a working fluid in the cushion pressure chamber into the air chamber when the cushion pressure chamber contracts during an extension operation, a check valve that returns a working fluid in the air chamber to the driving pressure chamber when a differential pressure between the air chamber and the driving pressure chamber rises to or above a predetermined value, and a valve housing that houses the check valve. A throttle gap is defined between an outer peripheral surface of the valve housing and an inner peripheral surface of the piston rod, and a working fluid ejected from the orifice during the extension operation flows into the air chamber through the throttle gap.

Abstract: Various systems and apparatuses are provided for a turbulence member for an annular seal cavity in a fluid handling device. In one example, the turbulence member includes an inner face positioned to cooperate with a seal assembly in the annular seal cavity to define an inner channel. The turbulence member also includes an outer face positioned to cooperate with a housing to define an outer channel in the annular seal cavity. The turbulence member also includes a front face extending between the inner face and the outer face, and a rear face spaced from the front face and extending between the inner face and the outer face. The turbulence member is configured to disrupt fluid flow within the annular seal cavity and inhibit formation of an air pocket adjacent to the seal assembly.

Abstract: The present application provides a steam turbine side support system for use with a steam turbine having a rotor. The steam turbine side support system may include a shell for the steam turbine, a number of side support arms extending from the shell in a perpendicular configuration with respect to the rotor, and a foundation in communication with the side support arms.

Abstract: The main rotor control system includes a rise/fall swashplate assembly that is coupled to three triplex actuators. The swashplate assembly is configured to provide full collective and cyclic pitch controls. Each triplex actuator includes three piston/cylinder assemblies in parallel. Selective actuation of each triplex actuator is controlled by a fly-by-wire system in conjunction with three flight control computers and three hydraulic power packs. Integrated three function valves can be associated with an individual manifold for each piston/cylinder assembly of each triplex actuator, the integrated three function valve be configured to insure safe operation of the triplex actuator during a failure of a certain piston/cylinder assembly.

Abstract: The present application provides a turbine inlet air filter system for filtering a flow of air about a compressor. The turbine inlet air filter system may include an inlet filter house and an inlet duct extending from the inlet filter house to the compressor. The inlet duct may include an air elbow with an elbow gate thereon.

Abstract: An airflow assembly, includes a plenum, a barrel, a fan support, a fan assembly, and a plurality of ribs. The plenum includes an opening structure defining a plenum opening. The barrel extends in a downstream direction from the opening structure, and defines a barrel space and a downstream edge. The fan support is at least partially positioned within the barrel space. The fan assembly is supported by the fan support and includes (i) a motor and (ii) a blade assembly configured to rotate about an axis. Each of the ribs extends between (i) the opening structure or the barrel and (ii) the fan support. The downstream direction is parallel to the axis. An upstream direction is opposite of the downstream direction and parallel to the axis. A plane intersects the axis and is perpendicular to the axis.

Abstract: A gas cylinder actuator with a safety device for controlled ejection of the piston stem, which has, on the side of the region for fixing the head portion to the jacket, a region in low relief on the inner face of the jacket, designed to interrupt the seal provided selectively either by the gasket elements associated with the piston or by the gasket elements associated with the head portion, and normally operating against the inner face of the jacket, in case of separation of the head portion with an outward movement of the piston.

Abstract: A vane assembly for use in a gas flow duct. The vane assembly includes multiple vanes arranged circumferentially about the duct. A throat angle of each of the vanes at mid-span is greater than the throat angle at the tips of the vane.

Abstract: A turbomachine for an aircraft including a mechanism forming a case fitted in a rear extension of an inner ferrule of an intermediate casing, and positioned around a central casing. The mechanism includes a structural upstream ferrule assembled on the inner ferrule and defining a front portion of a surface internally delimiting a secondary vein, and a main case extending on the upstream ferrule towards the rear. The turbomachine further includes a structural mechanism rigidifying the central casing, surrounded by the case, and extending towards the rear between the upstream ferrule and the central casing on which these mechanisms are assembled.

Abstract: A lightning protection system is provided for a wind turbine. The wind turbine has an electrically grounded structure part, a main shaft electrically and mechanically connected to the grounded structure part, a blade hub rotationally connected via a main bearing to the main shaft and blades connected to the blade hub. The lightning protection system includes a down-conductor attachable inside one of the blades and a high voltage conductor for guiding lightning current, wherein a first end of the high voltage conductor is in electrical communication with the down-conductor. The lightning protection system also includes a high voltage contact attachable inside the main shaft, wherein a second end of the high voltage conductor is in electrical communication with the high voltage contact. Lightning current is guided from the down-conductor via the high voltage conductor to the high voltage contact.

Abstract: In a multi-blade centrifugal fan including an impeller (7) rotatably disposed in a casing and composed of a disc-shaped hub (8), a plurality of blades (9), and an annular shroud (10), the blades (9) are curved in a concave shape on a pressure side in a cross-section perpendicular to a rotating shaft of the impeller (7) and have a curved shape that is backward-swept near a leading edge (9C) thereof and that is forward-swept near a trailing edge (9D) thereof, the inner diameter of the cascade of blades (9) increases gradually from the hub (8) toward the shroud (10), and the diameter of a maximum-curvature position (9B) where the curvature of the curved shape is maximized increases gradually from the hub (8) toward the shroud (10).

Abstract: A turbine vane of a gas turbine engine is provided with a hollow core in the leading edge of the outer platform thereof. The core is interconnected with the leading edge core of the airfoil whereby to create a cooling air stream having a dual purpose and cooling both the leading edge of the outer platform and of the airfoil and thereby reducing cooling air consumption. The cooling air enters the core of the outer platform through an inlet port and exits through cooling holes provided in the leading edge of the airfoil.

Abstract: A rotor disk for a turbomachine, which is connectable to at least one rotor blade and/or a shaft of the turbomachine, having at least one borehole, which has an elliptical inlet opening having a first passage cross-sectional area and an elliptical outlet opening having a second passage cross-sectional area, so that the second passage cross-sectional area is smaller than the first passage cross-sectional area.

Abstract: A liquid pressure circuit is provided in which connecting an accumulator (22) to a high pressure liquid path (Lh) by opening a cut-off valve (24a) and connecting a intake liquid path (Li) to the high pressure liquid path (Lh) by means of a switch valve (24b) enables a pump/motor (M) to be operated as a motor by liquid stored under pressure in the accumulator (22), connecting the accumulator (22) to the high pressure liquid path (Lh) by opening the cut-off valve (24a) and connecting the intake liquid path (Li) to a low pressure liquid path (Ll) by means of the switch valve (24b) enables the pump/motor (M) to be operated as a pump to thus store liquid of a tank (21) under pressure in the accumulator (22), and closing the cut-off valve (24a) and connecting the intake liquid path (Li) to the high pressure liquid path (Lh) by means of the switch valve (24b) enables the pump/motor (M) to rotate without load; it is therefore possible to switch between three circuits, that is, drive (motor operation), regeneration (p

Abstract: A composite fan case has a generally cylindrical composite shell, at least one band of sacrificial composite material circumscribing an outer surface of the composite shell, and a metallic rail mounted on the band of sacrificial material. Also disclosed is a method of construction the aforementioned case.

Abstract: A turbine bucket includes an airfoil portion; a platform at radially inner end of the airfoil portion; a shank portion extending radially-inwardly of the platform; and a mounting portion extending radially-inwardly of the shank portion. The shank portion and the mounting portion have at least one axially-extending seal-engaging surface formed as part of a separable, non-integral isolation element that isolates the bucket from forces caused by a near-flow-path seal engaging the at least one axially-extending seal-engaging surface.