Abstract: A rotating seal rotatable about a rotational axis is provided. The rotating seal includes a body having a first surface disposable to face the rotational axis and a second surface disposable to contact with a stationary element. The body defines a cooling channel including one or more entrance channels respectively extending from the first surface, one or more exit channels and a plenum. The plenum extends circumferentially through the body and has a hot side adjacent to the second surface. The plenum is fluidly interposed between the one or more entrance channels and the one or more exit channels whereby fluid exiting the one or more entrance channels and entering the plenum impinges against the hot side.

Abstract: A device for controlling thrust vectoring of a cyclorotor includes a control cam positionable relative to a drive shaft of a cyclorotor along each of a first axis and a second axis, where the drive shaft is rotatable about a third axis. The device may further include a frame having a plurality of sides, where the frame is disposed at least partly around the drive shaft of the cyclorotor, a first positioning assembly disposed on a first side of the frame, where the first positioning assembly is structurally configured to move the frame along the first axis, and a second positioning assembly disposed on a second side of the frame, where the second positioning assembly is engaged with the control cam and structurally configured to move the control cam relative to the frame along the second axis.

Abstract: An improved stator assembly is disclosed. The stator assembly may comprise an exit guide vane, an OD ring, and an ID ring. The exit guide vane may couple at one end to the OD ring and at an opposite end to the ID ring. The exit guide vane may comprise a leading edge opposite of a trailing edge. The OD ring and the ID ring may couple to a diffuser assembly of a gas turbine engine. The stator assembly may further comprise an aft OD seal, a forward OD seal, an ID seal, and a diffuser assembly seal to reduce airflow leaks around the stator assembly.

Abstract: A vane assembly includes a plurality of vane units and a connecting part. Each vane unit includes a base having a through-hole positioned between opposing longitudinal faces of the base. The connecting part includes a lacing bar that is insertable into and through the through-holes for coupling at least two adjacent vane units into the vane assembly. In the vane assembly the connecting part is arranged through the through holes of the plurality of vane units clamping the vane units on the lacing bar.

Abstract: An assembly is provided for a turbine engine. This assembly includes a static structure, a conduit and a conduit bracket. The static structure includes a port. The conduit extends longitudinally through the port. The conduit bracket couples the conduit to the static structure. The conduit bracket includes a base mount, a conduit mount and a damper. The base mount is attached to the static structure. The conduit mount is attached to the conduit. The damper is between the base mount and the conduit mount. The damper includes a first leg, a second leg and a web. The first leg projects laterally out from the base mount. The second leg projects laterally out from the conduit mount. The web is longitudinally between and connected to the first leg and the second leg.

Abstract: A two-part or multi-part rotor blade and also to a method which is associated with it. The rotor blade is split into at least one rotor blade component which is close to the hub and one rotor blade component which is remote from the hub at a separation point in the longitudinal direction, wherein the rotor blade component which is close to the hub and the rotor blade component which is remote from the hub can be connected at the separation point for operation of the wind turbine. A ratio of profile thickness to profile depth, called relative thickness, at the separation point lies within a range of from 0.4 to 0.5. An improved two-part or multi-part rotor blade in spite of the unexpectedly high relative thicknesses.

Abstract: A wind turbine including: at least a rotor blade including an aerodynamic device for influencing the airflow flowing from the leading edge section of the rotor blade to the trailing edge section of the rotor blade, wherein the aerodynamic device is mounted at a surface of the rotor blade, an actuator of the aerodynamic device for actuating the aerodynamic device at least between a first protruded configuration and a second retracted configuration, a pressure supply system for operating the actuator by means of a pressurized fluid, an acoustic receiver for measuring an acoustic signal in the pressure supply system, and a diagnostic unit connected to the acoustic receiver and configured for deriving an operative status of the aerodynamic device based on the acoustic signal, is provided.

Abstract: A diffuser system for a centrifugal compressor is provided. The diffuser system includes a nozzle base plate (206) that defines a diffuser gap (212), support blocks (216, 246), and a drive ring (220) rotatable relative to the support blocks. The drive ring includes cam tracks (224, 242) and bearing assemblies (226, 234) positioned proximate an outer circumference of the drive ring. The diffuser system further includes drive pins (214) extending through the support blocks and the nozzle base plate. The first end of each drive pin includes a cam follower (218) mounted into a cam track on the drive ring. The second end of each drive pin is coupled to a diffuser ring (208). Rotation of the drive ring causes axial movement of the drive pins by movement of the cam followers in the cam tracks. This results in movement of the diffuser ring to control fluid flow through the diffuser gap.

Abstract: A rotor blade having a rotor blade trailing edge which extends between a rotor blade root and a rotor blade tip over a rotor blade length, and having a profile depth which is established between the rotor blade trailing edge and a rotor blade leading edge. For the purpose of improving efficiency, at least one profile element having a continuous profile section, for the purpose of changing the profile depth of the rotor blade, is able to be attached at or in the region of the rotor blade trailing edge, wherein the extension of the profile section beyond the rotor blade trailing edge is determined in a manner dependent on a standardized load-dependent dimensioning of the profile depth of the rotor blade and a load level which is established at an erection location of the wind turbine.

Abstract: The invention relates to a rotor (2, 15) for a fluid pump (1), in particular for use in the medical sphere, the rotor being compressible for bringing to the place of use and thereafter being expandable. The compressibility is assisted by the provision of cavities (27, 28, 29), in particular also production of the rotor at least partially from a foam.

Abstract: This disclosure relates to an arrangement 10 for variably adjusting the cross-section of a compressor inlet. Furthermore, the disclosure relates to a charging device having such an arrangement 10. The arrangement 10 comprises a compressor housing 100 with a main body 140 and an inlet cover 120. The inlet cover 120 defines a compressor inlet 110. The arrangement 10 further comprises an adjustment mechanism 200 which is arranged in the compressor housing 100. The adjustment mechanism 200 comprises an actuation ring 210 and a plurality of orifice elements 220. Each orifice element 220 is coupled to the actuation ring 210 via a respective coupling element 230 and is rotatably supported in the compressor housing 100 via a respective shaft 240. Furthermore, the arrangement 10 comprises at least one wear reducing feature providing a wear reduced operation of the adjustment mechanism 200.

Abstract: A rotor blade for a wind turbine, to a wind turbine comprising a tower, a nacelle and a rotor, and also to a wind farm. The rotor blade comprises an inner blade section that extends from a rotor blade root in the longitudinal direction of the rotor blade, and a trailing edge segment, arranged on the inner blade section, for increasing the profile depth of the rotor blade along a section in the longitudinal direction of the rotor blade. The rotor blade has a pressure-side surface and a suction-side surface, which are each formed in certain regions by parts of the inner blade section and of the trailing edge segment. One or more air outlets and air inlets extending substantially in the longitudinal direction of the rotor blade are formed on both the pressure-side surface and the suction-side surface of the rotor blade, in the region of the trailing edge segment, said air outlets and air inlets being interconnected in a fluid-guiding manner.

Abstract: A method for producing a metal bladed element of a turbine engine, in particular of an aircraft, includes steps of producing the bladed element, depositing a coating made of wear-proof material on at least one portion of the bladed element and verifying, preferably visually, the conformity of the bladed element. Verifying the conformity of the bladed element includes implementing a verification element on the bladed element. The bladed element is configured according to a conformity threshold value to conceal a non-conformity of the coating, if the non-conformity has at least one dimension less than the threshold value, and to show at least one portion of this non-conformity if the at least one dimension is greater than the threshold value.

Abstract: A wind turbine blade is provided comprising a main blade portion and a light detection and ranging (LIDAR) element. The main blade portion has a shell defining an outer aerodynamic surface of the blade. The LIDAR element is disposed within a volume bounded by the outer aerodynamic surface and comprises at least one LIDAR system configured to transmit light beams away from the blade and to detect reflected light beams incident upon the blade.

Abstract: According to one embodiment, a system for reducing interference noise of rotor and stator blades includes rotor blades, stator blades, loudspeakers, one or more reference microphones, and a controller. The rotor blades rotate about a central axis. The loudspeakers are discretely arranged on a circle that has a center positioned on the central axis. Each loudspeaker generates a control sound. The controller causes the loudspeakers to generate control sounds of a same phase and a same amplitude. The control sounds correspond to the loudspeakers. The r is selected based on a preset attenuation level concerning the interference noise, and the k, where a is a length of the rotor blades, b is a radius of the circle, r=a/b, k is an upper limit wavenumber.

Abstract: A protective shield for a rotor blade of a wind turbine is provided. The shield protects the leading edge section of the rotor blade from erosion, and covers at least a part of the leading edge of the rotor blade. The shield is preformed with a shape which approximately corresponds to the contour of the leading edge section where it is destined to be mounted to. The shield includes a mark which allows to accurately position the shield at a predetermined position on the surface of the rotor blade or which allows to accurately position a tool at a predetermined position on the surface of the shield. A method of accurately positioning a protective shield on the surface of a rotor blade of a wind turbine and a method of documenting how precisely the shield has actually been attached to the surface of the rotor blade is also provided.

Abstract: A stator configuration for a gas turbine engine including a splitter segment. Also included is a first stator extending radially outwardly from the splitter segment. Further included is a second stator extending radially inwardly from the splitter segment, the splitter segment, the first stator and the second stator being a single, integrally formed structure.

Abstract: An aeronautical propulsion device including a fan and a plurality of variable guide vanes is provided. The fan includes a plurality of fan blades for providing a flow of air and the plurality of variable guide vanes are configured for directing air to or from the fan in a desired direction. Each of the plurality of guide vanes defines an inner end along the radial direction and is attached to a housing of the portion device at the inner end in a rotatable manner. The propulsion device further includes a pitch change mechanism positioned in the housing and mechanically coupled to at least one of the plurality of guide vanes for changing a pitch of the at least one of the plurality of guide vanes.

Abstract: The invention relates to a wind turbine that includes a rotor rotating about a horizontal axis of rotation substantially parallel to the direction of the wind, the rotor having a front face facing into the wind and substantially perpendicular to the axis of the wind, and a rear face situated toward a support of the rotor. At least two distinct families of blades are distributed on the rotor, each family of blades including at least two blades having a free end and a blade root end connected to said rotor. Each family of blades includes a catching blade guiding the wind toward a force blade having a surface arranged substantially perpendicular to the axis of the wind, the blade root ends of each family of blades are successively offset on an exterior surface of the rotor along the axis of rotation thereof.

Abstract: A gas turbine engine, has: a case extending circumferentially around a central axis of the gas turbine engine; a boss protruding from the case away from the central axis, the boss defining an internal passage; a tubular member received within the internal passage of the boss and secured to the boss; an annular gap extending all around the tubular member and located between the tubular member and the boss; and a fitting hydraulically connecting a fluid source to the tubular member, the fitting having a portion received within the tubular member and encircled by both of the annular gap and the tubular member, the fitting sealingly engaged to the tubular member.