Abstract: In a rotary wing aircraft a bar (1) of composite matrix material has a longitudinal axis (8) perpendicular to a cross section with upper and lower surfaces (2, 3). At least one torsion box (17) comprises an upper and a lower layers (10, 21, 11, 22) respectively offset of a longitudinal axis (8) and of the upper and the lower surfaces (2, 3), said upper and lower layers (10, 21, 11, 22) being laterally joint, while cross sections are filled with the first group of fibers extending essentially parallel to the longitudinal axis (8).

Abstract: A ceramic core used to cast and cooling circuit in a thin wall turbine airfoil, where the ceramic core includes a row of metering and impingement forming pieces that discharge into a radial plenum, followed by a row of pedestals and a row of diffusion channels that then flow into a single discharge slot. The ceramic core has bumpers of both sides to position the core in a wax mold. The metering and impingement holes are offset from the cooling passage in the airfoil wall so that impingement of the hot surface of the wall occurs.

Abstract: A propeller of a pulsed airflow generator, in particular for a standalone portable blower, of the type made up of the assembly of two parts coaxially adjoining one another, i.e.: a first front part made as a single piece and comprising a plurality of twisted blades connected to a central ring, and a second rear part with a generally conical shape also made as a single piece, the central portion of said assembly having a conical shape and making up the rear portion of an air-inlet cone, said propeller being characterised in that said first and second rear parts are secured by a clamping device made up of a hub including two parts assembled coaxially and between which said two parts that make up the propeller are clamped, said hub being rotatably secured to the latter and maintaining said front and rear parts in the assembled position thereof.

Abstract: Flow control devices and structures designed and configured to improve the performance of a turbomachine. Exemplary flow control devices may include various flow guiding channels, ribs, diffuser passage-width reductions, and other treatments and may be located on one or both of a shroud and hub side of a machine to redirect, guide, or otherwise influence portions of a turbomachine flow field to thereby improve the performance of the machine.

Abstract: The present disclosure is directed to a pitch assembly for coupling a rotor blade to a hub of a wind turbine. In one embodiment, the pitch assembly includes a first pitch bearing having a first outer race and a first inner race rotatable relative to the first outer race via a first set of rolling elements, a second pitch bearing having a second outer race and a second inner race rotatable relative to the second outer race via a second set of rolling elements, and at least one spacer configured axially between and contacting the first and second pitch bearings. Further, at least a portion of the first pitch bearing and at least a portion of the second pitch bearing are axially aligned between the rotatable hub and the rotor blade in a generally span-wise direction.

Abstract: A gas turbine engine blade (22), including an airfoil substrate (10) having an exterior surface, wherein: a base (14) of the airfoil substrate is located at a 0% radial on an inner platform surface (20) and a tip (16) of the airfoil substrate is located at a 100% radial; wherein at the 0% radial a cross-sectional profile of the exterior surface is substantially characterized by nominal X and Y coordinates present in Table 1; and wherein at a 50% radial location a cross-sectional profile of the exterior surface is characterized by nominal X and Y coordinates present in Table 6.

Abstract: Implementations of the present disclosure are directed to turbine assemblies for turbocharger systems. In some implementations, turbine housings include a body that defines an inlet for fluid communication with a fluid source, and a wall, the wall dividing the inlet into an inner inlet and an outer inlet, and a fluid guide assembly disposed within the housing, the fluid guide assembly including a plurality of vanes that demarcate an inner volute and an outer volute within the housing, the inner volute being in fluid communication with the inner inlet and the outer volute being in fluid communication with the outer inlet, each vane of the plurality of vanes being fixed at a respective angle relative to a radial direction, the plurality of vanes guiding fluid flow from the outer volute to the inner volute.

Abstract: A locking arrangement comprises a locking member having a longitudinal axis that is contained in a working plane where shear forces are concentrated when the locking member is in a locking position. The working plane is arranged substantially parallel to the axis of rotation of the parts to be locked when in said locking position in which at least one part of the wind turbine is prevented from being rotated relative to at least another part around said axis of rotation. A Wind turbine generator is provided having a rotor with a rotor flange portion and a stator with a stator flange portion, with both flange portions being complimentarily shaped and defining a locking housing for receiving said locking member.

Abstract: A hydraulic device for changing the pitch of a propeller including a piston rod actuated by a hydraulic fluid, the piston rod including at its end a clevis mount able to provide a connection for transmitting the movements of the piston rod so as to change the pitch of at least one propeller, a thread nut held in position on the clevis of the piston rod by a fastener, the nut being able to collaborate with a threaded rod in order to provide a connection.

Abstract: A sealing device between two axisymmetric coaxial parts, includes an elastic segment, two holding elements located on each side of the annular segment, an annular spacer arranged between the two holding elements, wherein the annular spacer has a notch around its peripheral rim; the annular elastic segment has a hooking element at each of its free ends, adapted to cooperate with the notch of the annular spacer, and to hold the elastic segment in a pre-holding position by elastic return force.

Abstract: A turbomachine stage includes guide vanes and an airfoil platform forming a guide vane cascade, and rotor blades and an airfoil platform forming a rotor blade cascade. Airfoil platforms have cascade regions extending between circumferentially adjacent airfoils, and gap regions which radially and/or axially bound an axial gap extending axially between the guide vane cascade and the rotor blade cascade. A contour of at least one of these gap regions varies in the radial and/or axial direction around the circumference.

Abstract: Bolt holes 16 are formed in a joint part 14 of a turbine housing 12, with flanged bolts 40 screwed in the bolt holes 16. A flange part 32 of a bearing housing 30 is sandwiched between bearing surfaces 44a of the flanged bolts 40 and an inner end face 14b of the joint part 14. A sealing ring 48 is interposed in an annular space s. Before the flanged bolts 40 are fastened, there is formed a height difference G equivalent to a compression allowance h for the sealing ring 48, between an outer end face 60a of the joint part 14 and a bolt receiving surface 32a of the flange part 32. The flanged bolts 40 are screwed into the bolt holes 16 until the bearing surfaces 44a make tight contact with the outer end face 60a so as to resiliently deform the sealing ring 48.

Abstract: A turbine guide vane having an aerodynamically bent vane airfoil with a channel system equipped with a throttle element is provided herein. The channel system includes channel sections for the guidance of coolant. In order to provide an alternative turbine guide vane by means of which both a partial coolant flow flowing in the interior and a partial coolant flow guided out of the turbine guide vane are adjustable; therefore, in an embodiment, the throttle element is designed for the removal of coolant.

Abstract: A rotary machine includes a guide section formed in an annular flow path in communication with a suction volute at an inner circumferential side of the suction volute, at which a plurality of vanes are installed in a circumferential direction, and configured to guide a fluid introduced from the suction volute, and an impeller connected to the guide section in the axial direction and into which the fluid guided by the guide section is introduced. The suction volute has an annular opening section in communication with the guide section at the inner circumferential side, and an inner wall surface extending from the opening section toward the axial direction of the impeller in the axial direction to increase a width dimension in the axial direction and connected to a partition section at an opposite side of the suction nozzle.

Abstract: The present invention discloses a novel and improved method for repairing a shrouded blade and a reconditioned shrouded blade. More specifically, a way of measuring a set of previously-operated blades to determine their post-operation geometric characteristics is provided where an offset due to deformation of the hardface surfaces of the shroud is determined. The hardface surfaces of the shroud are rough-machined and blade-compatible material is added to the hardface surfaces. A first side hardface surface of the shroud is then machined to a desired dimension offset relative to an originally manufactured blade after which a second side hardface surface is machined such that the distance between the hardface surfaces satisfies the cross-shroud dimension, which is similar to that of an originally manufactured blade.

Abstract: A turbocharger includes: a bearing provided in a turbocharger body, and configured to rotatably support a turbine shaft in an insertion hole formed in the bearing; and an opposing portion which faces an end surface of the bearing in an axial direction of the turbine shaft. An end-surface guide portion is provided to any one of an opposing surface of the bearing which faces the opposing portion, and an opposing surface of the opposing portion which faces the bearing. The end-surface guide portion configured to make the insertion hole and an outer peripheral edge of the end surface of the bearing in radial directions of the turbine shaft communicate with each other extends forward in a rotational direction of the turbine shaft from a part of the end surface of the bearing which communicates with the insertion hole.

Abstract: A mechanical system for a turbomachine includes a turbomachine part to be attached and a plurality of threaded attachment elements mounted on the turbomachine part in sequence along a line. The attachment elements fix the turbomachine part to the turbomachine. At least some of the attachment elements are arranged to be prevented from rotating by mutual cooperation about their corresponding thread axes, by a rotation prevention system provided on each of these attachment elements called self-locking elements. The self-locked elements cooperate in pairs, each pair including two directly consecutive self-locked elements along the line. At least one of the pairs has a distance between the thread axes of its two self-locked elements less than the distance between one of these two thread axes and the axis of either of the two attachment elements arranged along the line on each side of the at least one of the pairs.

Abstract: The invention concerns a gas turbine engine component (27) comprising an outer ring (21), an inner ring (20), a plurality of circumferentially spaced elements (22) extending between the inner ring (20) and the outer ring (21), wherein a primary gas channel for axial gas flow is defined between the elements (22), wherein the component (27) has an inlet side for gas entrance and an outlet side for gas outflow, and an annular load transfer structure (23) positioned internally of the inner ring (20) for transferring loads between said elements (22) and a bearing structure (24) for a turbine shaft (11) positioned centrally in the component (27), wherein the annular load transfer structure (23) extends circumferentially along at least a part of an inner side of the inner ring (20) and inwards in a radial direction of the component (27), wherein the annular load transfer structure (23) has a first portion (23a) and a second portion (23b), and wherein the first portion (23a) is located closer to the inner ring (20) t

Abstract: The length of a cross flow fan in the rotational axis direction is longer than the length of an air outlet in the longitudinal direction, and the cross flow fan has a fan extension positioned beyond each end of the air outlet in the rotational axis direction. Deflectors are provided in the air-conditioning apparatus main body. An outlet airflow blown from each fan extension of the cross flow fan impinges upon a corresponding one of the deflector. Furthermore, the shape of blade portions of the fan extensions of the cross flow fan and the shape of blade portions opposing the air outlet are different from each other. The wind speed of the outlet airflow blown from the blade portion is lower than the wind speed of an outlet airflow blown from the blade portion.

Abstract: A component for a gas turbine engine according to an exemplary aspect of the present disclosure including, among other things, an airfoil that extends between a leading edge and a trailing edge and a cooling circuit disposed inside of the airfoil. The cooling circuit includes at least one core cavity that extends inside of the airfoil, a baffle received within the at least one core cavity, a plurality of pedestals positioned adjacent to the at least one core cavity and a first plurality of axial ribs positioned between the plurality of pedestals and the trailing edge of the airfoil.