Abstract: The variable pitch propeller control system can have a source of adjustable, actuation hydraulic pressure, a feather valve openable to provide an actuation path of the actuation hydraulic pressure between the source and the actuator, and closeable to connect the actuator to a drain below the actuation hydraulic pressure and close the actuator path, and a bypass path parallel to the actuator path, the bypass path having a restricted flow area relative to a flow area of the actuator path.

Abstract: A nozzle for a turbine system includes an airfoil, an inner sidewall, and an outer sidewall. Each of the inner sidewall and outer sidewall each includes a peripheral edge defining a pressure side slash face, a suction side slash face, a leading edge face, and a trailing edge face. At least one of the inner sidewall pressure side slash face, the inner sidewall suction side slash face, the outer sidewall pressure side slash face, or the outer sidewall suction side slash face includes a first swept surface extending at a first angle relative to a nominal slash face angle and a second swept surface extending at a second angle relative to the nominal slash face angle. The first and second swept surfaces meet at a joining line that is circumferentially aligned with a stiffening member extending circumferentially on a respective sidewall.

Abstract: A variable vane includes a first vane portion and a second vane portion adjacent the first vane portion. The second vane portion includes a trunnion projecting outward from a radial end of the second vane portion. The second vane portion is configured to rotate about a trunnion axis of the trunnion from a first rotational position to a second rotational position.

Abstract: A centrifugal compressor includes a shaft defining an axis, an impeller mounted to the shaft for rotation about the axis, and a diffuser section including a first wall, a second wall, and an opening defined between the first wall and the second wall. The opening of the diffuser section is arranged in fluid communication with the impeller. The first wall is rotatable about the axis and rotation of the first wall about the axis is mechanically driven.

Abstract: A wind turbine includes a hub connected to a rotatable shaft extending in an axial direction and at least one bearing supporting the shaft against a housing, wherein the housing includes an electrically conductive cage section, which surrounds at least partially an axial segment of the shaft, wherein the cage section is connected to the shaft by at least one first conduction means and at least one second conduction means, wherein the at least one first conduction means and the at least one second conduction means are arranged spaced both from each other in the axial direction, wherein the at least one bearing is arranged between the segment of the shaft and the cage section of the housing at an axial position in between the at least one first conduction means and the at least one second con-duction means.

Abstract: A method for manufacturing a turbine engine part in which a first rough casting element includes a first face and a second face opposite to each other is assembled by the second face on an orifice which has a second element of the part. The method includes machining a through-cavity in the first element which opens at the first face and from the second face of the first element and machining the first face of the first element so as to form an area suitable for ensuring the attachment of a conduit on the first element. The machining of the cavity and of the first face is achieved by using a machining reference frame based on the second element.

Abstract: A blade for a gas turbine includes an external structure including a plurality of seating grooves which are separately disposed in a chord direction toward a trailing edge from a leading edge, an internal structure received in the external structure and including a plurality of protrusions protruding toward an internal side of the external structure, a plurality of porous strips combined to the seating groove in an attachable/detachable way, and a coolant channel formed for a coolant to flow among the porous strip, the neighboring protrusions, and an external side of the internal structure.

Abstract: A turbine blade includes a blade extending from a platform to a free end and having an airfoil-shaped cross section, the blade including a leading edge, a trailing edge, a pressure side extending from the leading edge to the trailing edge, and a suction side extend-ing from the leading edge to the trailing edge, one or more internal cooling passages through which cooling air flows, a trailing edge slot formed along the trailing edge and con-nected to the internal cooling passage, and a pin-fin array including a plurality of pin-fins positioned in the internal cooling passage connected to the trailing edge slot, each pin-fin including a main body and chamfered or filleted portions respectively connected to the pressure side and the suction side at respective ends of the main body, wherein among the pin-fins of the pin-fin array, a portion of the pin-fins have relatively large chamfered or filleted portions as compared with remaining pin-fins.

Abstract: A rotor for a gas turbine engine has: a first rotor disk; an interstage flange that extends from the first rotor disk to a flange end portion that has an axial end surface and first radial outer and inner surfaces; a circumferential groove, formed in the flange end portion and extending from the axial end surface toward the first rotor disk; radial outer and inner slots formed in the first radial outer and inner surfaces along the circumferential groove and extend through the first radial outer and inner surfaces; and a valve member disposed within the circumferential groove and is secured within the circumferential groove when the flange end portion is connected to a second rotor disk, wherein the valve member deflects from rotor rotational speeds to seal or unseal the radial outer slot.

Abstract: A pultruded fibrous composite strip for wind turbine spar caps, a spar cap having such a strip, and a wind turbine blade having such spar cap. The strip has longitudinally extending unidirectional fibers and an elongate body having first and second edge regions separated in the longitudinal direction of the strip by an intermediate region. The intermediate region has first and second mutually opposed longitudinally extending and parallelly disposed planar surfaces. The strip's thickness is measurable perpendicular to the planar surfaces and the width is measurable parallel to the planar surfaces and perpendicular to the longitudinal direction of the strip. In the strip, the first and/or the second edge regions, starting from the intermediate region and extending longitudinally, simultaneously tapers along the width and the thickness of the strip.

Abstract: A ducted fan module with variable-pitch blades for a turbo engine includes a rotor carrying a plurality of blades, a stationary casing, and a blade pitch changing and control system. The rotor includes a central shaft and a surrounding blade support ring. A front end of the blade support ring is connected to a front end of the central shaft, creating a rearward-opening annular space between the blade support ring and the central shaft. A tubular part is connected to the stationary casing and extends into the annular space.

Abstract: An oil tank filling system for filling the oil tank of a gas turbine engine that includes an aft core cowl. The system includes an oil tank that has an oil tank top and an oil tank bottom and is located within a core of the engine, an oil access port located on the aft core cowl, and an oil tank filling pipe that leads from the oil access port to a tank filling port located at or adjacent the oil tank bottom. The system is configured so that oil that is supplied to the oil access port flows to and into the oil tank using gravitational force. A method of filling the oil tank of a gas turbine engine and a gas turbine engine that includes the oil tank filling system.

Abstract: A wind turbine and associated control method includes a controller configured with a high speed shaft brake in the generator gear train. The controller receives an input signal corresponding to rotational speed of the high speed shaft, wherein upon the high speed shaft reaching a predefined rotational speed and under a braking condition that calls for the rotor to come to a complete standstill, the controller generates an activate signal to activate the brake. An interlock system is in communication with the low speed shaft sensor and the controller and is configured to override the activate signal when the rotational speed of the low speed shaft is above a threshold value.

Abstract: A turbofan having a nacelle comprising a slider mobile in translation between advanced position and retracted positions to open a window between a duct and the exterior, a plurality of blades, each one being rotatably mobile on the slider between stowed and deployed positions, and a maneuvering system moving each blade and comprising for each blade, a shaft rotatably mobile on the slider and onto which the blade is fixed, for each shaft, a balance beam fixed to the shaft and having first and second ends, for three consecutive balance beams, two connecting rods where the first connecting rod is mounted articulated between the first balance beam and the second balance beam, and where the second connecting rod is mounted articulated between the second balance beam and the third balance beam, and an actuation system rotating one of the connecting rods in one direction and in the other.

Abstract: A pump assembly and components therefor including an impeller which has flow inducer elements on an inner surface of a front shroud thereof, a flow directing device or strainer having passageways for delivering material to the impeller and at least one flow circulating passageway and a pump casing having an intake section with flow distribution vanes in the region of a feed opening adjacent the intake section.

Abstract: A pneumatic engine, comprising: a rotating outer ring (1), an intermediate shaft (2), a direct drive power core (3), and left and right baffles (4) and (5) where the rotating outer ring (1), the direct drive power core (3), and the left and right baffles (4) and (5) are coaxially provided on the intermediate shaft (2), the rotating outer ring (1) is integrally connected to the left and right baffles (4) and (5) to engage with the intermediate shaft (2) via a bearing, and a closed space is formed, the intermediate shaft (2) is provided with a master air inlet (21) and a master air outlet (22), the direct drive power core (3) is provided with a logarithmic spiral line runner, multiple drive grooves (11) are provided on an inner ring surface of the rotating outer ring (1). The pneumatic engine has a simple structure, high transmission efficiency and strong endurance.

Abstract: A platform for use between adjacent propulsion rotor airfoils joined to a rotor disk to provide an inner flowpath boundary includes: an axially extending I-beam supporting a radially outer skin having a flowpath surface; the I-beam including an inner I-flange disposed at an inner edge of an axially extending I-web, and an outer I-flange disposed at an outer edge of the I-web; the I-beam including a laterally-extending forward end flange at a forward end of the I-web, and a laterally-extending aft end flange at an aft end of the I-web; and the radially outer skin disposed on top of and joined to the radially outer I-flange such that the forward end flange and the aft end flange abut the outer skin.

Abstract: A rotor blade for a compressor of a gas turbine engine includes an airfoil extending from a root to a tip and having a leading edge and a trailing edge. The airfoil has a span that extends from 0% at the root to 100% at the tip and a mean camber line that extends from the leading edge to the trailing edge. The airfoil has a total camber distribution that increases from the root to a maximum value of total camber between 5% of the span and 20% of the span.

Abstract: A centrifugal pump for delivering a medium comprising solid admixtures includes a blade-free space arranged in front of an impeller. The centrifugal pump has a suction-side arrangement that permits variable sizing of the blade-free space. The suction-side arrangement permits the efficiency of the centrifugal pump to be increased while avoiding blockages.

Abstract: An impeller that rotates about a central axis extending vertically includes a base portion and blades. The base portion spreads perpendicularly to the central axis. The blades are on an upper surface of the base portion at intervals in a circumferential direction. The base portion includes an irregular portion that is radially outward and in which irregularities are repeated in the circumferential direction. The irregular portion includes one or more first irregular regions and a second irregular region. The first irregular regions include first recesses with a same shape and first projections with a same shape, the first recesses and projections being alternately arranged one by one. The second irregular region is positioned between the first irregular regions and includes at least one among a second recess with a different shape from the first recesses and a second projection with a different shape from the first projections.