Abstract: An engine component assembly is provided with an insert having cooling features. The engine component comprises a cooled engine component surface having a flow path on one side thereof and a second component adjacent to the first component. The second component, for example an insert, may have a plurality of openings forming an array wherein the openings extend through the second component at a non-orthogonal angle to the surface of the second component. The second engine component has a plurality of discrete cooling features disposed on a surface facing the first component and near the plurality of cooling openings.

Abstract: A blading member for fluid flow machines, for example, gas turbine engines. The blading member includes a platform member, at least one airfoil member, and at least one interlock member.

Abstract: An engine including a turbine section with a number of vane assemblies attached to a support housing. The assemblies are secured to the support housing with fasteners and retaining clips for the fasteners.

Abstract: A turbine engine fan case (48) comprises a composite body member (300) circumscribing an axis (500) and having an annular mounting portion (310, 410), a segmented polymer member (320, 330, 420, 440) along the annular mounting portion, and integrated therewith.

Abstract: A motor casing is provided with a motor rib which is annularly formed along a circumferential direction of a fan while protruding toward a main shroud, and the motor rib is provided with a notch portion in a portion near a high-pressure region in a scroll chamber. A part of moisture flowing into the scroll chamber infiltrates into an inner peripheral space of the motor rib across the motor rib in a low-pressure region in which a flow velocity of ventilation air is high in the scroll chamber. However, the moisture is pressed to the notch portion by ventilation air infiltrating into the inner peripheral space of the motor rib from the low-pressure region in the scroll chamber, and is then discharged to the scroll chamber from the notch portion.

Abstract: A rotor wheel for an engine includes a plurality of impeller vanes and a plurality of fluid passages defined by adjacent impeller vanes. The fluid passages are radially disposed across at least a portion of the rotor wheel. One or more impeller inserts may be disposed within one or more of the plurality of fluid passages, respectively. The impeller inserts define an impeller passage with a passage shape that controls a flow of fluid through the one or more of the plurality of fluid passages.

Abstract: A turbine nozzle box includes an annular outer ring plate, an annular nozzle unit, and an annular inner ring plate. The annular outer ring plate is operable to be disposed in a turbine such that an outer peripheral surface thereof is adjacent to an inner peripheral surface of an inner casing of the turbine. The annular nozzle unit is disposed adjacent to an inner peripheral surface of the outer ring plate. The annular inner ring plate is disposed such that an outer peripheral surface thereof is adjacent to an inner peripheral surface of the nozzle unit. The nozzle unit includes a plurality of segment blocks circumferentially installed at an arc angle. The segment blocks are disposed at an inlet end of a first-stage nozzle unit, and an outlet end of the first-stage nozzle unit is open.

Abstract: The present invention relates to a blade control apparatus and method for a wind power generator, and a wind power generator using the same, which includes a measurement unit configured to measure a change in electrical characteristic of a measurement section set in a conductive region having electrical conductivity. The conductive region is included in the blade for the wind power generator. Thus, the state of the blade may be easily checked without separate sensors, and the blade may be controlled in response to the state of the blade.

Abstract: The present disclosure is directed to a rotor blade assembly for a wind turbine. The rotor blade assembly includes a rotor blade having exterior surfaces defining pressure and suction sides, and leading and trailing edges extending in a generally span-wise direction between an inboard region and an outboard region. The inboard region includes a blade root having a rounded trailing edge. Further, the rotor blade assembly further includes at least one airflow separation element mounted to either or both of the pressure or suction sides of the rotor blade within the inboard region and adjacent to the rounded trailing edge. In addition, the at least one airflow separation element corresponds to a contour of the pressure side or the suction side of the rotor blade. As such, the at least one airflow separation element is configured to provide a fixed airflow separation location in the inboard region during standard operation.

Abstract: An outlet housing for an aircraft cabin air compressor includes a volute comprising radially inner and outer portions, and having first, second, third, and fourth circumferential regions. The first circumferential region is between the fourth and second circumferential region. The second circumferential region is between the first circumferential region and the third circumferential region. The third circumferential region is between the second circumferential region and the fourth circumferential region. A portion of the volute in the first circumferential region has a first wall thickness. A portion of the volute in the second circumferential region has a second wall thickness. A portion of the volute in the third circumferential region has a third wall thickness. A portion of the volute in the fourth circumferential region has a fourth wall thickness.

Abstract: A pre-diffuser and exit guide vane (EGV) system for a gas turbine engine includes an annular EGV assembly containing a number of guide vanes and having an annular opening bounded by a radially inner annular sealing surface at a first radius and a radially outer annular sealing surface at a second radius. First and second seals substantially matching the first and second radii respectively join the EGV assembly to an annular pre-diffuser having an annular opening bounded by radially inner and outer annular sealing surfaces at substantially the first and second radii. The seals seal the inner sealing surface of the EGV assembly to the inner sealing surface of the pre-diffuser and the second seal seals the outer sealing surface of the EGV assembly to the outer sealing surface of the pre-diffuser, such that the EGV assembly annular opening is in fluid communication with the annular opening of the pre-diffuser.

Abstract: A method for repairing an air cycle machine compressor housing includes removing a journal bearing support sleeve in an air cycle machine compressor housing, positioning a cylindrical insert within the air cycle machine compressor housing, wherein the cylindrical insert has an outer diameter greater than an outer diameter of at least one portion of the removed journal bearing support sleeve, an inner diameter less than an inner diameter of at least one portion of the removed journal bearing support sleeve, and a length greater than a length of the removed journal bearing support sleeve, welding the cylindrical insert to the air cycle machine compressor housing, and machining the welded cylindrical insert to form a replacement journal bearing support sleeve.

Abstract: A method is disclosed for manufacturing a rotating part which belongs to a hydraulic machine of an installation for converting hydraulic energy into electrical or mechanical energy. This rotating part includes blades distributed about an axis of rotation of the rotating part and extending from a leading edge to a trailing edge. This method can include manufacturing, in steel, a first part of each blade, which defines the leading edge thereof, manufacturing a second part of the blade in a material other than steel and attaching this to the first part of the blade so as to form a trailing edge.

Abstract: A method for repairing a cabin air compressor outlet housing includes removing a journal bearing support sleeve in a cabin air compressor outlet housing, positioning a cylindrical insert within the cabin air compressor outlet housing, wherein the cylindrical insert has an outer diameter greater than an outer diameter of at least one portion of the removed journal bearing support sleeve, an inner diameter less than an inner diameter of at least one portion of the removed journal bearing support sleeve, and a length greater than a length of the removed journal bearing support sleeve, welding the cylindrical insert to the cabin air compressor outlet housing, and machining the welded cylindrical insert to form a replacement journal bearing support sleeve.

Abstract: A vane assembly for a gas turbine engine is disclosed herein. The vane assembly includes an inner platform, an outer platform, and a ceramic-containing airfoil that extends from the inner platform to the outer platform. The ceramic-containing airfoil is manufactured to have radially discontinuous ribs spaced radially apart from one another between the inner platform and the outer platform.

Abstract: A wind turbine rotor blade (14) comprising a root portion (15) having a substantially cylindrical shape and a longitudinal axis (22), the root portion having a mounting face (25); a plurality of bores (26) in a wall of the root portion and extending from the mounting face into the root portion, the bores being configured to receive respective connecting means for connecting the wind turbine rotor blade to a wind turbine hub; wherein the plurality of bores are inclined at an angle relative to the longitudinal axis of the root portion to define a cone angle.

Abstract: A rotor for a supercharging device may include a compressor wheel and a turbine wheel. A sealing disc may be arranged between the compressor wheel and the turbine wheel. The sealing disc may include a first side interfacing with the compressor wheel and a second side interfacing with the turbine wheel. The compressor wheel and the turbine wheel may each define one of a holding contour and a counter-holding contour, which respectively interact with a corresponding one of a holding contour and a counter-holding contour defined on each of the first side and the second side of the sealing disc. The respective holding contour may correspond to the respective counter-holding contour, which may engage in one another and secure the compressor wheel, the sealing disc and the turbine wheel to one another.

Abstract: A wind turbine rotor blade is bonded together at the leading and trailing edges, and including a shear web or webs (the main vertical stiffening member that runs the span of the rotor blade) as an integral part, sharing the inner and outer skins of one or both sides of the blade. The integrated shear web(s) is made into the skin shell, and is an uninterrupted, continuous extension of the shell laminate that is joined to the shell component/components without requiring a secondary bond of any sort. The laminates in the shell and the shear web(s) may differ or be the same.

Abstract: A rotor of a turbomachine. The rotor includes at least one blade (4, 6, 8) that has a blade leaf (20) and a blade root (54, 55, 58), and a rotor base body (2), in particular a disk (2), that has an outwardly open, circumferential groove (12) for receiving the blade root (54, 55, 58). The circumferential groove (12) and the blade root (54, 55, 58) are shaped in a way that allows the blade root (54, 55, 58) to be secured in the circumferential groove (12) by the rotation of the blade (4, 6, 8) about an axis (Ar, AT).

Abstract: A turbine blade vibration damper is described. The damper has an axially-extending main body defining an inner surface and opposed damping surface. The main body also has an edge spanning from the inner surface to the damping surface and slotted apertures extending through the main body. The slotted apertures extend between the inner surface and damping surface. Adjacent pairs of slotted apertures have elongated shapes defining longitudinal axes that intersect at a point off the surface of the damper.