The invention relates to a device for converting wind energy to at least mechanical energy, comprising a rotor with a number of rotor blades drivable rotatably about a rotation axis by wind and a duct disposed therearound, wherein a central axis of the duct substantially coincides with the rotation axis of the rotor, characterized by guide means disposed upstream of the rotor for guiding the wind in a substantially helical movement round the central axis during use of the device such that the wind is supplied in the substantially helical movement round the central axis to the rotor.

A method for calculating a trailing edge that is to be produced for a rotor blade of an aerodynamic rotor of a wind power installation, wherein the rotor blade has radial positions with respect to the rotor, the rotor blade has a local blade profile that is a function of the radial positions with respect to the rotor and the trailing edge has a jagged profile having a plurality of spikes, wherein each spike has a spike height and a spike width, and the spike height and/or the spike width is calculated as a function of the radial position thereof and/or as a function of the local blade profile of the radial position thereof.

A method of retrofitting a tooth unit to a trailing edge of a wind turbine rotor blade. A portion of the trailing edge of the rotor blade is cut out and removed. That can be affected when the rotor blade is still disposed on a hub of the wind power installation (that is to say in the mounted state). A tooth retrofitting unit is glued or adhesively fixed on the trailing edge of the wind turbine rotor blade in the cut-out and removed portion. The tooth retrofitting unit has a V-shaped profile and at its first side has two fixing arms and at an opposite side a plurality of teeth. The two fixing arms are adhesively secured to the trailing edge of the rotor blade to mount the tooth retrofitting unit.

A rotor blade for a wind turbine having a blade root, a transition piece and an aerodynamic part, wherein the blade root essentially is optimized for fixation of the blade to the hub and the aerodynamic part essentially is optimized to extract energy from the wind and wherein the transition part realizes a beneficial transition between the blade root and the aerodynamic part. The rotor blade can perform better both aerodynamically and structurally compared to a classic design when the blade part located near the axis, approximately the part between 0% L and 50% L is provided with one or more of the following characteristics: more twist than usual, attached flow stimulating measures at the suction side, flow blocking measures at the pressure side, thicker profiles than usual, a triangular shape of the profile back and back twist.

The invention relates to a device of a safety system and/or resource and energy-efficiency improvement system for influencing the flow around an aero- or hydrodynamic body, preferably an aerofoil, according to the principle of a back-flow flap, characterized in that: said device, together with the aero- or hydrodynamic body, in particular aerofoil, form at least a partial shift of the delimitation of the flap region by means of the back-flow flap and the delimiting component thereof when the back-flow flap is partially and/or completely raised, thus influencing the trailing edge separation vortex/vortices and/or the flap separation vortex/vortices; and in that the delimitation of the flap region shifts completely up to or beyond the profile trailing edge, or shifts only to a section in front of the profile trailing edge. The delimitation component is movably connected to the aerofoil by means of a basic element and is preferably permanently secured and/or releasably secured for maintenance purposes, thus ensuring a long service life for the rotor blade and/or wind turbine and/or flap system, preferably >5 years, particularly preferably >10 years, and most particularly preferably >=20 years, and/or thus optionally allowing simple removal/replacement.

A rotor blade for a wind turbine is provided, wherein the rotor blade includes serrations along at least a portion of the trailing edge section of the rotor blade. The serrations include a first tooth and at least a second tooth, and the first tooth is spaced apart from the second tooth. The area between the first tooth and the second tooth is at least partially filled with porous material such that generation of noise in the trailing edge section of the rotor blade is reduced. Furthermore, the embodiments relate to a wind turbine including at least one such a rotor blade.

The present disclosure is directed to tip extensions for wind turbine rotor blades and methods of installing same. The method includes removing a removable blade tip of a lightning protection system from the rotor blade so as to expose a down conductor of the lightning protection system. The method also includes securing a conductive extension to the down conductor. Moreover, the method includes sliding the first end of the tip extension over the conductive extension so as to overlap the rotor blade at the tip end. In addition, the method includes securing the removable blade tip to the conductive extension at the second end of the tip extension. Further, the method includes securing the tip extension to the rotor blade.

A spoiler for a rotor blade includes a base member, which base member has a mounting face for mounting onto a surface of the rotor blade, and an aerodynamic member for detachably connecting onto the base member. Further, a wind turbine includes a number of rotor blades attached to a hub, wherein at least one rotor blade has such a spoiler mounted on a surface strip of the rotor blade. Also, a method of constructing a wind turbine is provided. A rotor blade is manufactured. A base member of the spoiler is mounted onto the rotor blade. The rotor blade is connected to a hub of the wind turbine. An aerodynamic member of the spoiler is attached onto the base member, wherein at least the mounting of the base member onto the rotor blade is performed prior to the connecting of the rotor blade to the hub.

An airfoil (10) for a gas turbine engine in which the airfoil (10) includes an internal cooling system (14) with one or more internal cavities (16) having an insert (18) contained within an aft cooling cavity (76) to form nearwall cooling channels having enhanced flow patterns is disclosed. The flow of cooling fluids in the nearwall cooling channels (20) may be controlled via a plurality of cooling fluid flow controllers (22) extending from the outer wall (12) forming the generally hollow elongated airfoil (26). In addition, heat may be extracted in the midchord region (150) via one or more heat dissipating ribs (152) extending partially between an inner surface (144) of the suction side (38) and the insert (18). In at least one embodiment, the heat dissipating ribs (152) may extend in a generally chordwise direction and be positioned from an inner diameter (92) to an outer diameter (98) of the airfoil (10) between the cooling fluid flow controllers (22) and a rib (72) separating forward and aft cooling cavities (74, 76).

Various air deflector shapes, sizes and configurations for use in a load compensating device on an airfoil are provided. The air deflector arrangements are configured to alter the airflow around the air deflector in order to affect sound or acoustics associated with the air deflector when deployed during operation. Some example configurations that may alter the air flow around the air deflector include air deflectors having a plurality of apertures, air deflectors including a scalloped edge, and/or air deflectors including a plurality of protrusions extending from a portion of the air deflector.