The present disclosure relates to a heat dissipation system, a wind generating set, and a heat dissipation supporting platform. The heat dissipation system includes: a supporting platform, the supporting platform including a body portion, the body portion including an inlet, an outlet, a flow channel communicating the inlet with the outlet, and a mounting position for mounting a functional device, the inlet, the outlet and the flow channel together form a medium circulation passage; and a heat exchange apparatus which communicates with the medium circulation passage and delivers the cooling medium into the medium circulation passage, the cooling medium flowing through the inlet and the flow channel and flowing out from the outlet to exchange heat with the functional device.

A direct drive wind turbine with a cooling system has a generator with a rotor and a stator and a bearing with an inner ring and an outer ring connecting the rotor and the stator rotatively. The cooling system includes at least one heat sink which is in thermal communication with the inner ring of the bearing and a heat dissipater which is in thermal communication with the heat sink.

An apparatus for dampening of acoustic noise generated by air-cooling of at least one turbine component provided with the nacelle of a wind turbine is provided. Apparatus for dampening of acoustic noise generated by air-cooling of at least one wind turbine component provided with the nacelle of a wind turbine, comprising at least one acoustic dampener, with the acoustic dampener including at least one acoustic dampening channel structure having at least one acoustic dampening channel connected with at least one inlet opening of the acoustic dampening channel structure and at least one outlet opening of the acoustic dampening channel structure.

A turbine rotor blade is provided with a blade root, platform adjoining it, and turbine blade on that side of the platform which faces away from the blade root, with at least one opening for feeding coolant into the turbine rotor blade interior on an underside of the blade root, which opening merges into a coolant duct. An axial rotor section for a rotor is provided, having an outer circumferential surface adjoining two end-side first side surfaces with rotor blade holding grooves distributed over the circumference and extending along an axial direction, wherein a turbine rotor blade is arranged in every holding groove, wherein a multiplicity of sealing elements are at the side of a side surface of the rotor section, and lie opposite the end sides of blade roots to form a gap. Multiple outlet holes for impingement cooling of the sealing elements are provided in the end surface.

A component for a gas turbine engine, comprising: first and second walls; a coolant channel defined by the space between the first and second walls; and a first rib extending between the first and second walls to the end of the coolant channel in a coolant flow direction, such that the coolant channel is bifurcated in the coolant flow direction.

A separation assembly comprises a housing, a jet that expels a fluid within the housing, and a turbine assembly positioned within the housing and positioned so as to be contacted by the fluid expelled from the jet. The fluid causes the turbine assembly to rotate about a center rotational axis within the housing. The turbine assembly comprises a first turbine portion and a second turbine portion that are separately formed from each other and attachable together. The first turbine portion comprises a plurality of first vanes and the second turbine portion comprises a plurality of second vanes.

Provided is a blade for a wind turbine, the blade including a joint section configured to connect the blade to a hub of the wind turbine; an active add-on member which is actuated by a corresponding trim actuator to alter aerodynamic properties of the blade; and a channel configured to supply a medium from the joint section to the active add-on member. A wind turbine and a method of preventing icing of the blade is also provided.

A gas turbine engine article includes an article wall that defines leading and trailing ends and first and second sides that join the leading and trailing ends. The article wall defines a cavity. A cooling passage network is embedded in the article wall between inner and outer portions of the article wall. The network has an inlet orifice through the inner portion to receive cooling air from the cavity, a plurality of sub-passages, at least one outlet orifice that is connected to the sub-passage region, and a manifold region that has a plenum upstream of the sub-passages. The outer portion of the article wall has a sloped impingement surface located opposite the inlet orifice. The sloped impingement surface is angled to divert flow of cooling air from the inlet orifice toward the plenum.

A gas turbine engine article includes an article wall that defines leading and trailing ends and first and second sides that join the leading and trailing ends. The article wall defines a cavity. A cooling passage network is embedded in the article wall between inner and outer portions of the article wall. The network has an inlet orifice through the inner portion to receive cooling air from the cavity, a plurality of sub-passages, at least one outlet orifice that is connected to the sub-passage region, and a manifold region that has a plenum upstream of the sub-passages. The outer portion of the article wall has a sloped impingement surface located opposite the inlet orifice. The sloped impingement surface is angled to divert flow of cooling air from the inlet orifice toward the plenum.

A separation assembly comprises a housing, a jet that expels a fluid within the housing, and a turbine assembly positioned within the housing and positioned so as to be contacted by the fluid expelled from the jet. The fluid causes the turbine assembly to rotate about a center rotational axis within the housing. The turbine assembly comprises a first turbine portion and a second turbine portion that are separately formed from each other and attachable together. The first turbine portion comprises a plurality of first vanes and the second turbine portion comprises a plurality of second vanes.