A wind turbine blade assembly includes a rotor blade having exterior surfaces defining a pressure side, a suction side, a leading edge and a trailing edge, each extending between a blade tip and a root. The rotor blade additionally defining a span and a chord. The blade assembly further includes a plurality of micro boundary layer energizers positioned on a surface of the pressure side of the rotor blade. The plurality of micro boundary layer energizers extending one of above or below a neutral plane of the rotor blade. The micro boundary layer energizers are shaped and positioned chordwise to delay separation of a boundary layer at a low angle of attack. A wind turbine including the blade assembly is additionally disclosed.

Provided is a wind turbine component for a wind turbine, in particular for a wind turbine tower and/or a rotor blade, to a wind turbine tower, to a rotor blade, to a wind turbine and to a method for producing a wind turbine component. Provided is a wind turbine component for a wind turbine, in particular for a wind turbine tower and/or a rotor blade, comprising a first wall element with a first inner surface and a first outer surface arranged opposite the latter, a corrugated structural element, wherein the structural element is arranged on the first inner surface or on the first outer surface, wherein the first wall element is connected to the structural element.

A bushing (116) for a wind turbine rotor blade (104) is provided, the bushing (116) comprising a first bushing end (117) and an opposite second bushing end (118) and a bushing bore (119) which extends in a region between the first bushing end (117) and the second bushing end (118) and comprises a bore longitudinal axis (120); wherein, along the bore longitudinal axis (120) in the direction of the second bushing end (118), the bushing bore (119) comprises a threaded portion (127), and wherein the bushing (116) comprises a bushing runout (128) that follows the threaded portion (127), the bushing runout comprising a widening portion (131) of the bushing bore (119), in which a diameter (132) of the bushing bore (119) enlarges at least monotonically while an increase in diameter decreases at least monotonically.

The present disclosure relates generally to a fan nacelle assembly circumferentially surrounding a fan section, the fan nacelle assembly including an inner wall including an inner wall axial length, and an outer wall an outer wall axial length, wherein the outer wall axial length is greater than the inner wall axial length.

Bushing for a wind turbine rotor blade, flange insert, wind turbine rotor blade and wind turbine

The invention relates to a bushing (116) for a wind turbine rotor blade (104), the bushing (116) comprising a first bushing end (117) and an opposite second bushing end (118); a bushing bore (119) which extends in a region between the first bushing end (117) and the second bushing end (118) and comprises a bore longitudinal axis (120);
wherein, along the bore longitudinal axis (120) in the direction of the second bushing end (118), the bushing bore (119) comprises a threaded portion (127), and wherein the bushing (116) comprises a bushing runout (128) that follows the threaded portion (127), said bushing runout comprising a widening portion (131) of the bushing bore (119), in which a diameter (132) of the bushing bore (119) enlarges at least monotonically while an increase in diameter decreases at least monotonically.

The invention also relates to a flange insert (113), a wind turbine rotor blade (104) and a wind turbine (100).

A wind turbine blade assembly includes a rotor blade having exterior surfaces defining a pressure side, a suction side, a leading edge and a trailing edge, each extending between a blade tip and a root. The rotor blade additionally defining a span and a chord. The blade assembly further includes a plurality of micro boundary layer energizers positioned on a surface of the pressure side of the rotor blade. The plurality of micro boundary layer energizers extending one of above or below a neutral plane of the rotor blade. The micro boundary layer energizers are shaped and positioned chordwise to delay separation of a boundary layer at a low angle of attack. A wind turbine including the blade assembly is additionally disclosed.

A compressor wheel that can be employed in devices such as turbochargers. The compressor wheel includes an axially extending hub having an inlet end, a shaft bore extending from the inlet end and an arcuate outer surface opposed to the shaft bore. The axially extending hub is composed of a metal and has a porous region located proximate to the arcuate outer surface of the axially extending hub. The compressor wheel also includes a blade array disposed on the arcuate outer surface of the axially extending hub. The blade array has an outer surface and an inner region. The blade array comprises a plurality of circumferentially-spaced, radially and axially extending blades disposed thereon and is composed, at least in part of a polymeric material. Polymeric material located in the inner region of the blade array extends into the porous region defined in the axially extending hub.

A compressor wheel that can be employed in devices such as turbochargers. The compressor wheel includes an axially extending hub having an inlet end, a shaft bore extending from the inlet end and an arcuate outer surface opposed to the shaft bore. The axially extending hub is composed of a metal and has a porous region located proximate to the arcuate outer surface of the axially extending hub. The compressor wheel also includes a blade array disposed on the arcuate outer surface of the axially extending hub. The blade array has an outer surface and an inner region. The blade array comprises a plurality of circumferentially-spaced, radially and axially extending blades disposed thereon and is composed, at least in part of a polymeric material. Polymeric material located in the inner region of the blade array extends into the porous region defined in the axially extending hub.

Provided is a wing structure comprising a wing body formed from fiber-reinforced plastic (FRP), and an erosion suppression layer provided so as to cover at least a portion of a front edge of the wing structure. The erosion suppression layer contains a thermal spraying layer configured so as to maintain, by having a prescribed surface roughness, a liquid film formed on the erosion suppression layer.

A number of variations may include a method of optimizing inlet guide vane performance comprising: modifying an inlet guide vane to include at least one of a twist, a curve, a surface texture, a sealing feature, a tip leakage reduction feature, an airfoil having at least one component, or at least one channel.