The impeller includes a disc having a main surface extending outward in a radial direction toward one side in an axial direction, a plurality of blades defining a flow path extending to an outlet on one side from an inlet on the other side in the axial direction, and a cover disposed to cover the plurality of blades. At least one of an inlet side region and an outlet side region which are a connection portion between the blade and the main surface and a connection portion between the blade and the cover has a small fillet portion curved in an arc shape and having a small radius of curvature. An intermediate region formed between the inlet side region and the outlet side region has a large fillet portion having a large radius of curvature.

A rotor blade includes an airfoil having an airfoil shape. The airfoil shape has a nominal profile substantially in accordance with Cartesian coordinate values of X, Y and Z set forth in one of Table I, Table II, Table III, Table IV, Table V, Table VI, Table VII, Table VIII, Table IX, Table X, Table XI, or Table XII. The Cartesian coordinate values of X, Y and Z are non-dimensional values from 0% to 100% convertible to dimensional distances expressed in a unit of distance by multiplying the Cartesian coordinate values of X, Y and Z by a scaling factor of the airfoil in the unit of distance. The X and Y values, when connected by smooth continuing arcs, define airfoil profile sections at each Z value. The airfoil profile sections at Z values are joined smoothly with one another to form a complete airfoil shape.

A fan includes a hub, a plurality of fan blades arranged around the hub and connected to the hub, and a plurality of guiding parts. Each of the plurality of fan blades comprises a windward surface and a leeward surface facing away from the windward surface. Each of the plurality of guiding parts is arranged on each of the plurality of fan blades. Each of the plurality of guiding parts comprises a plurality of guiding portions. Each of the plurality of the guiding portions protrudes from or is recessed in the windward surface or the leeward surface.

An airfoil for a gas turbine engine defining a radial direction and an axial direction, the airfoil including: a flared portion extending from a suction surface of the airfoil at an outer edge of the airfoil along the radial direction; and a plenum disposed at the outer edge of the airfoil, the plenum having a suction-side sidewall and a pressure-side sidewall, wherein the suction-side sidewall has a first sidewall portion adjacent to a second sidewall portion disposed outside of the first sidewall portion along the radial direction, wherein the first sidewall portion defines a first angle, wherein the second sidewall portion defines a second angle, and wherein the first angle is greater than the second angle.

A rotor blade includes an airfoil having an airfoil shape. The airfoil shape has a nominal profile substantially in accordance with Cartesian coordinate values of X, Y and Z set forth in Table I. The Cartesian coordinate values of X, Y and Z are non-dimensional values from 0% to 100% convertible to dimensional distances expressed in a unit of distance by multiplying the Cartesian coordinate values of X, Y and Z by a scaling factor of the airfoil in the unit of distance. The X and Y values, when connected by smooth continuing arcs, define airfoil profile sections at each Z value. The airfoil profile sections at Z values are joined smoothly with one another to form a complete airfoil shape.

Turbine components, such as blades, having a shank portion with an uncoated, nominal profile substantially in accordance with Cartesian coordinate values of X, Y, and Z set forth in Table 1, Table 2, or Table 1 and Table 2. X and Y are distances in inches which, when connected by smooth continuing arcs, define shank portion profile section edges at each Z distance in inches. The shank portion profile section edges at the Z distances are joined smoothly with one another to form a complete shank shape.

The present application discloses an impeller for a centrifugal fan and a centrifugal fan. The impeller comprises a support member and several vanes. The support member has an inner wall that defines a hollow portion. The several vanes are arranged inside the hollow portion, each of the several vanes is connected with the inner wall and extends along the axial direction of the support member, and the several vanes are arranged along the circumferential direction of the support member. Each of the several vanes is bent and comprises a front edge, a tail edge, a convex suction surface, and a concave pressure surface, the suction surface and the pressure surface are arranged to oppose each other, and the front edge and the tail edge are arranged to oppose each other, wherein the tail edge is connected with the inner wall of the support member, and wherein several protrusions are provided on the suction surface, and the several protrusions are arranged to be close to the front edge. The protrusions can regulate the flow of a fluid immediately when the fluid contacts the vanes. During the flow regulation process, a large vortex in the fluid can be divided into several small vortices. Such small vortices have smaller friction resistance, and the kinetic energy dissipated from the motion of the small vortices themselves can be partially cancelled out, thereby reducing the noise of the impeller and improving the performance of the centrifugal fan.

The invention relates to a turbomachine turbine vane comprising a root having a blade (12) comprising a leading edge (16) and a trailing edge (17) and a lower surface wall (14) and an upper surface wall (13), as well as: a manifold for cooling (18) the leading edge (16); a supply line (19) for collecting air from the root and supplying the manifold (18); a side cavity (23) extending along the upper surface wall (13) and supplied with air from the root, to form a heat shield facing the supply line (19); and a circuit forming a trombone comprising a middle portion (24) extending along the supply line (19) and extending laterally to the upper surface wall (13), the middle portion (24) being supplied by the supply line at the tip of the blade (12).

The present technique presents a blade 1 for a gas turbine 10. The blade 1 includes an airfoil 100 having an airfoil tip part 100a and a pressure side 102 and a suction side 104 meeting at a leading edge 106 and a trailing edge 108 and defining an internal space 100s of the airfoil 100. A squealer tip 80, 90 is arranged at the airfoil tip part 100a. The squealer tip 80, 90 comprises a suction side rail 90. The suction side rail 90 comprises a chamfer part 90x and at least one squealer tip cooling hole 99. The chamfer part 90x comprises a chamfer surface 9. An outlet 99a of the at least one squealer tip cooling hole 99 is disposed at the chamfer surface 9.

A rotor blade assembly includes a first rotor blade and a second rotor blade positioned adjacent to one another. The first rotor blade and the second rotor blade each include a platform and an airfoil extending radially outward from a root coupled to the platform to a tip. The airfoil includes a part-span shroud. The part-span shroud extends from the airfoil and is disposed between the root and the tip. The part-span shroud includes a pressure side portion extending from the pressure side surface and a suction side portion extending from the suction side surface. A damper is in contact with both the part span shroud of the first rotor blade and the part span shroud of the second rotor blade at an interference joint. The damper is movable relative to the part span shroud of both the first rotor blade and the second rotor blade.