Abstract: A vibration damper structure and a fan thereof. The vibration damper structure includes a support body, a fixing seat and an elastic member. The support body has a lower end. The fixing seat has a tubular section. The tubular section has a protrusion end corresponding to the lower end of the support body and a receiving space. The receiving space has a bottom section. The elastic member is disposed in the receiving space of the tubular section and positioned between the support body and the fixing seat. Two ends of the elastic member are respectively in contact with the lower end of the support body and the bottom section of the receiving space. The vibration damper structure is applied to the fan to greatly reduce the vibration of the fan in operation.

Abstract: Methods of providing an undercut on a support member for a coversheet and coversheet support systems having undercuts are provided. A coversheet support system may include a spar. The spar may include a support member on an outer surface of the spar. The support member may extend outward from the outer surface of the spar. The support member may include an outer surface and an undercut. The undercut may be located in a portion of the support member between the outer surface of the spar and the outer surface of the support member. In addition, the coversheet support system may include a coversheet. The coversheet may be metallurgically bonded to the outer surface of the support member.

Abstract: A vibration damper structure and a series fan thereof. The vibration damper structure includes a first support body, a second support body and an elastic member. The first support body has a first upper end and a first lower end. The second support body has a second upper end and a second lower end. The elastic member is disposed between the first and second support bodies. The elastic member has a first support end in contact with the first lower end and a second support end in contact with the second lower end. The vibration damper structure is applied to the series fan to greatly reduce the vibration of the series fan in operation.

Abstract: A wind turbine blade device includes a rotating unit including a blade module concentrically connected to a rotating shaft thereof and having a plurality of radially curved channels each having inlet and outlet ends. The inlet and outlet ends of the radially curved channels are configured to respectively permit flow of the flow body into and out thereof. An outer tube includes a tube body surrounding the rotating unit, and a plurality of rib plates provided in the tube body. The outlet end of each radially curved channel corresponds to one of the rib plates, and each radially curved channel forms an included angle with a corresponding rib plate such that the flow body flowing out of the outlet end can impact upon the corresponding rib plate.

Abstract: A gas turbine engine comprising a fan, a bypass duct positioned downstream of the fan and defined by an inner casing and an outer casing, a series of outlet guide vanes arranged downstream of the fan, the outlet guide vanes extending between the inner casing and the outer casing of the bypass duct; and a bifurcation positioned downstream of the outlet guide vanes and extending between the inner casing and the outer casing. The bifurcation comprises a leading edge, and the leading edge of the bifurcation is shaped so as to protrude axially forward by a varying distance from the inner casing to the outer casing so as to improve uniformity of a static pressure field formed, in use, immediately upstream of the bifurcation.

Abstract: A trailing edge cooling system for a turbine blade is disclosed. The system may include a cooling circuit including an outward leg, and a return leg positioned adjacent the outward leg. The outward and return leg each may extend toward and away, respectively, from a trailing edge of the turbine blade. The cooling circuit may also include a plurality of turn legs. The plurality of turn legs may include a turn leg positioned directly adjacent the trailing edge of the turbine blade, and a distinct turn leg positioned axially adjacent the turn leg, and opposite the trailing edge of the turbine blade. The distinct turn leg may be oriented non-parallel to at least one of the outward leg and the return leg.

Abstract: A rotary wing with a curved outer surface, inlet openings and an edge foil for use in helicopters to improve lift and efficiency, maximizing the gross weight lift and the horizontal flight speed capabilities and minimizing performance penalties and unstable, inefficient operation.