Abstract: An example high-performance system includes an example high-performance component including a substrate and a multilayer abradable track adjacent to the substrate. The abradable track includes a plurality of alternating layers along a thickness of the abradable track. The plurality of alternating layers includes at least one relatively porous abradable layer and at least one relatively dense layer. A porosity of the relatively dense layer is lower than that of the at least one relatively porous abradable layer. The example high-performance system may include a rotating component configured to contact and abrade the multilayer abradable track. An example technique for forming the multilayer abradable track includes thermal spraying a first precursor composition toward the substrate to form a relatively porous abradable layer of a layer pair of a plurality of layer pairs of the multilayer abradable track, and a second precursor composition to form a relatively dense layer of the pair.

Abstract: A turbine shroud sector made of ceramic matrix composite, of longitudinal axis X and which includes a base with a radially internal face, a radially external face from which there extend upstream and downstream tabs for attachment to a shroud support structure. The base includes a first slot and a second slot, which is arranged radially on the outside of the first slot. The slots are formed in the lateral face. A first and a second sealing strip rest against a radially internal wall of the first and second slots. The first strip has the overall shape of an omega and the shroud sector exhibits a first clearance which is defined radially between a central part of the first strip and the radially internal wall of the first slot, and a second clearance which is defined radially between this central part and a radially external wall of the first slot.

Abstract: A vacuum pump and a damper for the vacuum pump are provided so as to increase vibration isolation in a twisting direction with a simple structure and prevent rupture of an O-ring and an elastic member by regulating a misalignment of flanges facing each other. Provided are a first flange and a second flange, each having a central opening, the flanges being shaped like rings opposed to each other; an O-ring and an intermediate ring that are disposed between the first flange and the second flange; O-rings disposed between the first flange and the intermediate flange and between the intermediate ring and the second flange; a plurality of elastic members that are disposed between the first flange and the second flange and are spread in the circumferential direction of central openings; and airtightness keeping means including positioning pins inserted into positioning holes sequentially provided on the first flange, the intermediate ring, and the second flange.

Abstract: A bearing compartment seal for a gas turbine engine includes at least one seal ring defining an axis and having a radially inward facing sealing surface and a seal runner having a support constructed of a first material and an interface portion constructed of a second material. The interface portion includes a radially outward facing surface. A first coefficient of thermal expansion of the second material is at most approximately equal to a second coefficient of thermal expansion of the at least one seal ring.

Abstract: A double flow turbojet including: a low pressure compressor; a series of casings downstream of this low pressure compressor to delimit a primary flow path for circulating a primary stream, and including an upstream edge delimiting an inlet opening; a high pressure compressor in the primary flow path; a shroud surrounding the series of casings to delimit a flow path for circulating an intermediate stream, and having an upstream edge delimiting a circular inlet opening situated upstream of the high pressure compressor; a secondary flow path casing surrounding the shroud to delimit a secondary flow path for circulating a secondary stream; an exhaust casing including radial arms collecting the air coming from the intermediate flow path.

Abstract: The disclosure relates to a mounting frame, an energy storage unit, a pitch system, a wind turbine and a method. The mounting frame for mounting accumulators in a hub includes: a base having a predetermined thickness, wherein the base includes a mounting surface in a thickness direction of the base; and two or more accumulator mounting elements disposed on the mounting surface at intervals, wherein each accumulator mounting element includes a supporting assembly and a holding assembly connected to the supporting assembly, the supporting assembly is connected to the mounting surface and extends in the thickness direction, and the holding assembly is adapted to clamp and fix the accumulator such that all the accumulators in the hub are mounted to the mounting frame.

Abstract: A rotor blade for a wind turbine, to a rotor for a wind turbine, to a wind turbine, to a method for producing a rotor blade, to a method for connecting a rotor blade to a rotor hub and to a method for repairing a rotor of a wind turbine. The rotor blade has a connection interface, the connection interface having at least one cutout for receiving a tension element for connecting the rotor blade to a further element of a wind turbine, an outer circumferential surface of the cutout being formed of a connection material and having an internal thread.

Abstract: A rotor arresting device, a wind turbine and a method for arresting and/or rotating a rotor. The rotor arresting device comprises a rotor, a rotational assembly, and a static assembly fixed in position, comprising a toothed disk, which can be arranged on the rotational assembly, having a plurality of arresting recesses arranged along a circumference, wherein two adjacent arresting recesses form a tooth, a first arresting module having at least one first arresting element, a second arresting module having at least one second arresting element, wherein the first and the second arresting module can be arranged on the static assembly, wherein the first and the second arresting element are arranged and designed to engage in arresting recesses of the toothed disk, wherein the spacing of the first arresting element from the second arresting element in the circumferential direction of the toothed disk is a non-integral multiple of a tooth tip spacing of the toothed disk.

Abstract: An apparatus and method an engine component for a turbine engine comprising an outer wall bounding an interior and defining a pressure side and an opposing suction side, with both sides extending between a leading edge and a trailing edge to define a chord-wise direction, and extending between a root and a tip to define a span-wise direction, at least one cooling passage located within the interior, a set of cooling holes having an inlet fluidly coupled to the cooling passage, an outlet located on one of the pressure side or suction side, with a connecting passage fluidly coupling the inlet to the outlet.

Abstract: An airfoil includes a ceramic airfoil that defines a leading edge, a trailing edge, a pressure side, a suction side, a first radial end, and a second radial end. The ceramic airfoil section has an internal cavity and a rib that divides the internal cavity into a first radial passage and a second radial passage. The first radial passage is open at both the first radial end and the second radial end, and the second radial passage is open at least at the second radial end. A cooling passage circuit includes a first radial leg through the first radial passage, a second radial leg though the second radial passage, and a turn leg outside of the internal cavity at the second radial end. The turn leg connects the first radial leg and the second radial leg.

Abstract: Provided is a safety stop valve arrangement of a hydraulic blade pitch system of a wind turbine, including an accumulator arrangement connected over a hydraulic line to a piston of the hydraulic blade pitch system; a redundant set of safety valves arranged between the accumulator arrangement and the piston; a small-orifice restriction nozzle arranged to determine a first rate of hydraulic fluid flow in response to a safety stop input; at least one speed-select valves arranged; and at least one large-orifice restriction nozzle arranged to determine a second rale of hydraulic fluid flow in response to a positive rotor acceleration input, wherein the second rate of fluid flow is faster than the first rate of fluid flow. A safety stop assembly of a wind turbine with hydraulic blade pitch systems and a method of performing a safety stop sequence is also provided.

Abstract: An inner shroud block component for a gas turbine. The inner shroud block has a surface with a plurality of wells formed therein. An array of protuberances extend away from a base surface of each of the wells. The array of protuberances produces convective cooling of the inner shroud block, resulting in increased cooling of the inner shroud block and better part life. The increased cooling capacity also allows the turbine to operate at higher temperatures, which results in additional power generation.

Abstract: A turbomachinery engine can include a fan assembly with a plurality of variable pitch fan blades. The fan blades are configured such that they define a first VPF parameter and a second VPF parameter. The first VPF parameter is defined as the hub-to-tip radius ratio divided by the fan pressure ratio. The second VPF parameter is defined as the bearing spanwise force divided by the fan area. In some instances, the first VPF parameter is within a range of 0.1 to 0.25, and the second VPF parameter is within a range of 2-30 lbf/in2. In other instances, the first VPF parameter is within a range of 0.1 to 0.4 and the second VPF parameter is within a range of 5.25-30 lbf/in2. In certain examples, the turbomachinery engine further includes a pitch change mechanism, a vane assembly, a core engine, and a gearbox.

Abstract: A turbine exhaust case (TEC) includes an outer case, an inner case, and a plurality of struts structurally connecting the inner case to the outer case. At least one of the struts has an airfoil body with a hollow core. A leading edge stiffener is provided at the radially inner end of the airfoil body. The leading edge stiffener projects into the hollow core and merges with a stiffener ring projecting from a radially inner surface of the inner case.

Abstract: A main shaft assembly of a wind turbine and method for manufacturing the same are provided. Accordingly, the main shaft assembly includes a structural/shaft body defining a cavity therein. The shaft body is configured to transmit a load of the wind turbine developed in response to the wind. An inner body is located within the cavity. The inner body is non-loadbearing with respect to the load. At least one sensor is coupled to the inner body and positioned within the cavity for detecting a deflection of the shaft body in response to the load.

Abstract: A shroud configured to be disposed around an impeller of a centrifugal compressor, the shroud has a wall extending circumferentially around a central axis, the wall having an inner face oriented toward a gaspath and an outer face opposed to the inner face, a bleed slot defined in the wall and extending along at least a portion of a circumference thereof, the bleed slot defining a bleed direction from the inner face and away from the gaspath, the bleed direction at the inner face of the wall being either parallel to the central axis or oriented toward the central axis. A method of manufacturing a shroud is provided.

Abstract: The turbine blade includes an airfoil, a root connected to the airfoil and having lobed edges spaced apart on laterally opposed sides of an axis extending axially through the root, and an air passage extending through the airfoil and the root. A first tab extends at least partially along and laterally outward from a first edge of the laterally opposed lobed edges, and a second tab extending at least partially along and laterally outward from a second edge of the laterally opposed lobed edges.

Abstract: A propeller fan includes a shaft portion disposed on a rotation axis, and a blade disposed on an outer peripheral side of the shaft portion and including a leading edge and a trailing edge. The blade includes a negative pressure surface in which a plurality of recesses are formed, and the plurality of recesses include a first recess and a second recess disposed on the trailing edge side than the first recess in a circumferential direction about the rotation axis as a center. The first recess has a depth larger than a depth of the second recess.

Abstract: A hub assembly or a rotor of a wind turbine includes a hub having openings to connect rotor blades thereto. The hub assembly includes a pitch bearing (3) and a pitch carrier positioned between the hub and the pitch bearing, the pitch carrier configured to support a pitch system for adjusting a blade pitch of the rotor blades. The pitch carrier includes a strip plate arranged between two opposite regions of a perimeter of the opening. A mounting structure attaches the strip plate to the hub.

Abstract: A rotor blade is provided for a gas turbine engine. This rotor blade includes a rotor blade pair including a mount, a first airfoil and a second airfoil. The mount includes a forked body with a first leg and a second leg. The first airfoil is connected to the first leg. The second airfoil is connected to the second leg and arranged circumferentially next to the first airfoil.