A joint assembly for a wind turbine rotor blade includes a male structural member extending longitudinally through female structural members configured with a plurality of rotor blade segments. The female structural member includes first bore holes on opposing sides thereof that are aligned in a chord-wise direction. The male structural member includes second bore holes on opposing sides thereof that are aligned with the first bore holes. At least one chord-wise extending gap is defined between an outer side surface of the male structural member and an inner side surface of the female structural member. A chord-wise extending pin extends through the first and second bore holes to join the male and female structural members. At least one flanged bushing is arranged in the first and second bore holes such that a flange of the bushing extends within the chord-wise extending gap.

A turbine impeller includes: a hub portion coupled to an end of a rotational shaft; a plurality of main blades disposed at intervals on a peripheral surface of the hub portion; and a short blade disposed between two adjacent main blades among the plurality of main blades. An inter-blade flow channel is formed between the two adjacent main blades so that a fluid flows through the inter-blade flow channel from an outer side toward an inner side of the turbine impeller in a radial direction. In a meridional plane, a hub-side end of a leading edge of the short blade is disposed on an inner side, in the radial direction, of a hub-side end of a leading edge of the main blade.

A wind turbine blade is reinforced while suppressing possible stress concentration resulting from a load imposed on a blade root portion of the wind turbine blade in a flap direction. The wind turbine blade includes a blade main body extending from the blade root portion toward a blade tip portion and an FRP reinforcing layer formed so as to cover at least a part of the outer surface of the blade root portion of the blade main body. The FRP reinforcing layer includes a plurality of laminated fiber layers and a resin with which the plurality of fiber layers is impregnated. The FRP reinforcing layer is formed such that, in a cross section along a longitudinal direction of the blade main body, both ends of the plurality of laminated fiber layers in the longitudinal direction are tapered.

Provided is an improved architecture for rotary kinetic fluid motors and pumps, in which working fluid gains or loses pressure by flowing through an alternating sequence of radial-flow impellers and radial-flow fluid vortices, the impellers and fluid vortices all rotating around a single axis and in a common direction at staggered speeds, each vortex being the product of rotating fluid that is flowing radially through a bladeless annular volume.

Provided is a method for bonding dissimilar metals to each other, the method comprising: dissimilar metal layer-forming steps (P2), (P3), (P4) for supplying, to form dissimilar metal layers; a second metal layer-forming step (P5) for supplying, on the surface of the dissimilar metal layers, a filler material formed of a second metal, and heating the filler material formed of the second metal to a temperature equal to or higher than a melting point of the second metal, to form a second metal layer formed of the second metal; and a second material-to-be-bonded welding step (P6) for welding a second material to be bonded that is formed of the second metal, onto the second metal layer.

Provided is a method for bonding dissimilar metals to each other, the method comprising: dissimilar metal layer-forming steps (P2), (P3), (P4) for supplying, to form dissimilar metal layers; a second metal layer-forming step (P5) for supplying, on the surface of the dissimilar metal layers, a filler material formed of a second metal, and heating the filler material formed of the second metal to a temperature equal to or higher than a melting point of the second metal, to form a second metal layer formed of the second metal; and a second material-to-be-bonded welding step (P6) for welding a second material to be bonded that is formed of the second metal, onto the second metal layer.

The present invention relates to a radial turbomachine with axial thrust compensation, comprising: a fixed casing (3); a plurality of main concentric bladed rings (9,9,9,9) arranged in the fixed casing (3) around a central axis (X-X); a plurality of concentric auxiliary bladed rings (15, 15, 15) arranged in the fixed casing (3) around the central axis (X-X) and radially alternated with the main bladed rings (9,9,9,9). A rotor (2, 2) comprising a rotor disc (6, 6) and a rotation shaft (4, 4, 4) integral with the rotor disc (6, 6) is rotatable in the fixed casing (3) around the central axis (X-X) and carries, on a front face (7, 7), the main bladed rings (9,9,9,9). The main (9,9,9,9) and auxiliary (15, 15, 15) bladed rings delimit, with the rotor disc (6, 6), a plurality of concentric front main chambers (30, 33, 35, 36) at different pressures. A plurality of concentric rear annular main chambers (41,41,41,41), each in fluid communication with a respective front main chamber (30, 33, 35, 36) and at the same pressure as the respective front main chamber (30, 33, 35, 36), is delimited between a rear face (8, 8) of the rotor disc (6, 6) and the fixed casing (3). A rear annular area (A_1p, A_2p, A_3p, A_4p, A_4p) of the rotor disc (6, 6) delimiting one of the rear annular main chambers (41,41,41,41) is equal to or substantially equal to a front area (A_1f, A_2f, A_3f, A_4f) of the rotor disc (6, 6) delimiting a respective front main chamber (30, 33, 35, 36), so that the force exerted by the pressure of the working fluid in each rear annular main chamber (41,41,41,41) substantially balances the force exerted by the pressure of the working fluid in the respective front main chamber (30, 33, 35, 36).

A fluid transfer assembly for use in a gas turbine engine includes a rotor shaft, a stationary assembly circumscribing the rotor shaft, and a rotating component coupled to the rotor shaft and positioned radially inward of the stationary assembly. The rotating assembly includes a hub coupled to the rotor shaft, a plurality of rotor blades coupled to the hub, and a shroud coupled to the plurality of rotor blades.

A fluid transfer assembly for use in a gas turbine engine includes a rotor shaft, a stationary assembly circumscribing the rotor shaft, and a rotating component coupled to the rotor shaft and positioned radially inward of the stationary assembly. The rotating assembly includes a hub coupled to the rotor shaft, a plurality of rotor blades coupled to the hub, and a shroud coupled to the plurality of rotor blades.

An assembly for joining together modules of a modular wind turbine blade. According to one embodiment the assembly is formed by a plurality of bolts that are secured between pairs of first and second inserts respectively housed in the composite material of first and second modules. According to one embodiment each assembly is formed by first and second lateral caps, upper wedge and a lower wedges located between the first and second lateral caps, and transverse screws joining the upper and lower wedges that together are formed around the corresponding bolt. When a force F1 is applied to the wedges, the lateral caps respond with forces F.sub.2 that urge the first and second modules away from one another to longitudinally stress the bolt.