Abstract: The segments of a segmented wind turbine rotor blade are screwed together at respective connection ends via a plurality of connecting bolts. Sleeve-shaped pressure pieces are arranged between the rotor blade segments, each of which is mounted on a connecting bolt. A plurality of first metal sheets is provided, each first metal sheet being arranged between a respective connection end and several pressure pieces, so that an electrically conductive connection is formed between several pressure pieces via a first metal sheet. The first metal sheets, which are associated with the first connection end, are each arranged along the circumference of the rotor blade offset from the first metal sheets, which are associated with the second connection end. Further, a metal sheet for a segmented wind turbine rotor blade is disclosed.

Abstract: A nacelle for a wind turbine includes: a nacelle housing; a rotor hub; and a rotor bearing for bearing the rotor hub on the nacelle housing, wherein the rotor bearing has at least one inner ring element and at least one outer ring element, wherein at least one oil-lubricated sliding bearing element is formed between the inner ring element and the outer ring element. A sealing element is formed between the nacelle housing and the rotor hub and/or between the nacelle housing and a rotor shaft.

Abstract: The present invention relates to a method for continuously manufacturing an abradable sealing element, this element comprising a support substrate covered by a coating comprising at least two successive layers, each comprising a sublayer of abradable material and a sublayer of erosion-control material. This method is noteworthy in that it comprises the steps consisting in: —a) placing at least one support substrate on a rotary carousel around which are placed at least two thermal spray torches enabling the sublayer of abradable material and that of erosion-control material to be deposited, —b) rotating the carousel so as to bring said support substrate successively opposite one then the other of the two torches and to carry out the deposition of the various sublayers and to repeat this operation so as to obtain said sealing element.

Abstract: A vane arrangement for a compressor is disclosed. The vane arrangement comprises a generally annular vane deck and at least one vane. The generally annular vane deck extends at least partway around a longitudinal axis, defining a deck thickness b in the axial direction. The at least one vane projects from a first surface of the vane deck. The at least one vane comprises a leading edge, a trailing edge, and first and second pressure surfaces. The leading edge is proximate the longitudinal axis. The trailing edge is distal the longitudinal axis. The first and second pressure surfaces extend between the leading edge and the trailing edge. The at least one vane defines a neck thickness t, proximate the leading edge, in a plane normal to the longitudinal axis, wherein t/b?about 0.21.

Abstract: A part made of composite material, in particular for an aircraft turbine engine, includes a body produced from fibers woven in three dimensions and immersed in a resin, in particular an organic or polymer resin. The part has at least one crack sensor capable of detecting a crack in the part, at least one link element connected to the sensor and configured to transmit a signal(S), in particular to a member outside of the part, when a crack in the part is detected. The crack sensor has at least one conductive wire woven with the fibers of the body, and the link element is configured to measure the resistance of the conductive wire and to wirelessly transmit the signal.

Abstract: An example wind turbine is provided that includes a shaft assembly, strut mounts coupled to the shaft assembly, airfoils directly or indirectly coupled to the strut mounts, and a generator assembly connected to the shaft assembly. The shaft assembly defines a central longitudinal axis of the wind turbine. The airfoils are capable of being positioned in a fully extended orientation and a fully retracted orientation. Rotation of the airfoils results in rotation of at least a portion of the shaft assembly to generate electrical current with the generator assembly.

Abstract: A propulsion unit with a propeller includes a nacelle; a propeller rotatably mounted in the nacelle by means of a hub. The propeller has blades mounted in a blade cuff that is pivotable about a pitch axis relative to the hub. Each blade is pivotable relative to the cuff about a folding axis. A folding device includes an actuator for folding the blades. The folding device includes a control member rotationally affixed to the blade cuff and driven by the actuator. A connecting rod is pivotably mounted, on the one hand, on a root the associated blade and, on the other hand, on the movable control member.

Abstract: A rotor assembly comprises a rotor having a plurality of blades and an axis about which the rotor rotates, each blade being spaced from the axis of the rotor such that there is a gap between the axis and an inner edge of each blade through which fluid can flow, and inner and outer edges of each blade lying in and defining a blade plane and each blade being offset from the axis of the rotor such that the axis does not lie in the blade plane; a casing partially surrounding the rotor, the casing having a first opening to permit a fluid flow into or out of the casing in a direction generally perpendicular to the rotor axis; and a second opening at an axial end of the casing to permit a fluid flow into or out of the casing in a direction generally parallel to the rotor axis.

Abstract: A wind guide may include a top portion, a plurality of vanes coupled to an underside of the top portion, the vanes extending radially outward from a center of the top portion and extending along the underside of the top portion, and a bottom portion coupled to the plurality of vanes, opposite the top portion, to form a plurality of air channels each having a cross section that decreases towards the center of the top portion, the bottom portion comprising a circular plurality of exits disposed near a center of the bottom portion to allow air to exit the wind guide.

Abstract: The invention relates to a method of prolonging pitch bearing lifetime for a wind turbine as well as the pitch bearing itself. The method comprises the steps of: —stopping the rotor (4) from rotating; —removing a plurality of first fastening means used for mounting the blade (5) to the outer bearing ring (24); —mounting a strengthening arc structure (10) on said outer bearing ring (24), opposite the blade (5); —installing a plurality of second fastening means, thereby connecting said blade (5) and said strengthening arc structure (10) to said outer bearing ring (24).

Abstract: A turbine component includes a first structure exposed to a hot gas path and a second structure integral with the first structure but isolated from the hot gas path. A first fluid passage in the first structure delivers a thermal transfer fluid, e.g., air, through the first structure to cool the first structure. A second fluid passage is defined within the second structure and is in fluid communication with the first fluid passage. After heat transfer in the first structure, the thermal transfer fluid is hotter than a temperature of the second structure and thus increases the temperature of the second structure. The heat transfer to the second structure reduces a temperature difference between the first structure and the second structure that would, without heating, cause thermal stress between the structures. The heating of the second structure reduces the need for early maintenance and lengthens the lifespan of the component.

Abstract: A rotor for power driving includes a hub, a plurality of first fixed jibs, a plurality of second fixed jibs, and a plurality of outer vanes. The hub is adapted to be coupled with a shaft to rotate together in a single rotational direction. The first fixed jibs are arranged around the hub circumferentially. Each second fixed jib is engaged on an end of a corresponding first fixed jib. Each outer vane is elastically fixed at a corresponding second fixed jib and extends in a direction different from the single rotation direction when not acted upon by external forces such that the plurality of outer vanes, when acted upon by external forces, are elastically movable relative to corresponding second fixed jibs to drive the shaft to rotate along the single rotational direction and can rebound after removal of the external forces.

Abstract: A method is for operating a wind turbine. The wind turbine includes a nacelle including a nacelle component, in particular a rotor bearing, and a nacelle air flow influencing unit. The nacelle air flow influencing unit is configured to influence an air flow entering, flowing through and/or exiting the nacelle. The method includes: determining an operating condition of the nacelle component, determining a cooling demand of the nacelle component dependent on the determined operating condition of the nacelle component, controlling an operation of the nacelle air flow influencing unit dependent on the cooling demand of the nacelle component to adapt the air flow to the cooling demand of the nacelle component.

Abstract: A multi-piece radial turbine rotor includes a hub, turbine blades, and a flowpath ring that couples the turbine blades to the hub. Joints between the components of the rotor are adapted for inspection during manufacture to identify potential defects in the joints.

Abstract: A thrust propeller variable pitch actuator is controlled by a governor that uses propeller pitch as a variable to increase or decrease torque—not to maintain the propeller speed or RPM but instead to maintain certain established electric current supplied to rotate the thrust propeller.

Abstract: A bypass turbomachine is disclosed. The turbomachine includes a longitudinal axis having an upstream blower impeller and a downstream air-flow straightening assembly of a secondary annular passage delimited radially on the inside by a radially inner shroud and radially on the outside by a radially outer shroud, blades extending between the radially inner and outer shrouds and being attached at a first end portion to the radially inner shroud and at a second end portion to the radially outer shroud, the blades including a useful portion extending between the first and second end portions and defining a lower face and an upper face. For each blade, in a plane perpendicular to the longitudinal axis, each aerodynamically useful portion is bent into a C-shape in the circumferential direction.

Abstract: A system and method are provided for determining deflection of a tower of a wind turbine, the wind turbine including a nacelle with a machine head and a rotor atop of the tower. A fixed location relative to the tower is established, and a total deflection of a geographic location (“geo-location”) of the fixed location is determined. Components of the total deflection are determined that are generated by non-thrust loads acting on the tower. The non-thrust loads deflection components are subtracted from the total deflection to determine a thrust loads deflection component corresponding to deflection of the tower from operational thrust loads on the rotor.

Abstract: A gas turbine is provided, the gas turbine engine including a turbomachine having an inlet splitter defining in part an inlet to a working gas flowpath and a fan duct splitter defining in part an inlet to a fan duct flowpath. The gas turbine engine also includes a primary fan driven by the turbomachine defining a primary fan tip radius R1, a primary fan hub radius R2, and a primary fan specific thrust rating TP; and a secondary fan downstream of the primary fan and driven by the turbomachine, the secondary fan defining a secondary fan tip radius R3, a secondary fan hub radius R4, and a secondary fan specific thrust rating TS; wherein the gas turbine engine defines an Effective Bypass Area, and wherein a ratio of R1 to R3 equals R 1 R 3 = ( EFP ) ? ( 1 - RqR ( Sec . - Fan ) 2 ) ( 1 - RqR Prim . - Fan 2 ) ? ( T P T S ) ? ( EBA ) .

Abstract: A centrifugal compressor of an aircraft engine includes an impeller and a shroud extending circumferentially around the impeller. A bellmouth disposed upstream of the impeller extends circumferentially and includes: a conduit section extending from a first end to an upstream-most location of the bellmouth, the first end of the conduit section secured to the shroud, and a peripheral section extending from the upstream-most location to a second end located radially outwardly of the first end, the peripheral section located radially outwardly of the conduit section and axially overlapping the conduit section. A stiffening member is located on the peripheral section of the bellmouth proximate the second end. The stiffening member extends circumferentially and provides the bellmouth with a dynamic vibration mode outside a range of dynamic vibration modes of the aircraft engine during operation.

Abstract: An adjustable length crank arm includes a first component having a longitudinal length, a second component coupled to the first component, the second component having a longitudinal length. A total length of the crank arm can be adjusted by changing an amount of longitudinal overlap that exists between the first component and the second component. The adjustable length crank arm can include a first wedge and a second wedge and at least a portion of each of the first wedge and the second wedge is longitudinally captured between the first component and the second component.