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.

A turbine blade for a gas turbine engine. The turbine blade includes a cooling path for a coolant, routing the coolant through an internal cooling cavity and out through a plurality of cooling holes formed proximate a trailing edge of the turbine blade. Each of the cooling holes including a diffusing region designed so that a coolant does not separate from a radially inward sidewall of the diffusing region.

A gas turbine engine component includes an exterior pressure side with a plurality of cooling holes located in the exterior pressure side. A relief cut surrounds at least one of the plurality of cooling holes.

An inner peripheral blade projects from the positive pressure surface of the blade surface part toward a positive pressure side, includes a front edge in a rotation direction of the inner peripheral blade that is formed in a curved shape to be separated from a reference line toward the front edge side in the rotation direction of the blade, the reference line connecting a lower end positioned on the positive pressure surface at a base end of the inner peripheral blade connected to the side surface of the hub with an outer edge of the inner peripheral blade that is extended from the side surface toward an outer edge side of the blade and positioned on the positive pressure surface, and satisfies H/L≥0.1, where L is a length of the reference line and H is a maximum value of a distance between the reference line and the front edge of the inner peripheral blade.

A turbine blade that allows an improvement in torque and power, and a turbine and gas turbine including the same are provided. The turbine blade includes an airfoil having a suction side and a pressure side, a platform coupled to a bottom of the airfoil, and a root protruding downward from the platform and coupled to a rotor disk, wherein the airfoil includes a cooling passage formed therein and a discharge hole connected to an upper portion of the cooling passage to discharge cooling air, and the discharge hole is inclined toward a tip of the turbine blade while extending from an inside to an outside thereof.

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.

A ceiling fan may include a column; a hub case coupled to the column and rotatable with respect to the column; and a plurality of blades disposed at the hub case, and arranged radially around the column. Each blade may include a lower blade having a first side coupled to the hub case and a second side, opposite to the first side, directed radially outwardly; an upper blade spaced apart from the lower blade, and having a first side coupled to the hub case and a second side, opposite to the first side, directed radially outwardly; and an air gap disposed between the lower blade and the upper blade. The blade may be formed as a tandem blade, thereby generating a greater lift force than a blade having one positive pressure surface and one negative pressure surface, such that an air volume may increase at a same power output.

A gas turbine engine component according to an example of the present disclosure includes, among other things, an external wall including adjacent bounding pedestals that extend from an external wall surface to establish a cooling passage, and including a common pedestal situated between the adjacent bounding pedestals to establish a first branched section and a second branched section of the cooling passage that join together at a merged section of the cooling passage. A method of fabricating a gas turbine engine component is also disclosed.

An impeller includes a hub and blades. In radial direction, an upper surface of the blade near the outer edge includes a groove structure, a lower surface of the blade relating to the groove structure includes a peak structure, the lower surface of the blade includes a recess structure aside the trailing edge or the leading edge. The recess structure is connected to the peak structure. The blade has at least five airfoils from the inner edge to the outer edge. The blade is defined by continuously connecting the at least five airfoils at different sections in sequence so as to form the groove structure and the peak structure respectively on the upper surface and the lower surface. The groove structure and the peak structure are aside the outer edge of the blade.

An impeller associated with a compressor of a gas turbine engine includes a plurality of impeller blades. Each impeller blade of the plurality of impeller blades has a leading edge and a trailing edge opposite the leading edge in a streamwise direction. Each impeller blade of the plurality of impeller blades extends in a spanwise direction from a hub at 0% span to a tip at 100% span, and each impeller blade of the plurality of impeller blades has a plurality of mean camber lines that each extend from the leading edge to the trailing edge at a respective spanwise location. The leading edge includes a partially swept leading edge surface defined between 70% span to 100% span that extends in the streamwise direction between 3% to 15% of a mean camber line at 100% span.