An airfoil including: an airfoil portion having an airfoil surface; and a communication hole extending at least in the airfoil portion and a first opening open in the airfoil surface, through which the first opening is communicated with a second opening provided in a portion of the airfoil. On a cross-section perpendicular to the spanwise direction through a position of the first opening of the spanwise direction, an angle A1 satisfying a condition (a) exists within an angle range −10 degrees to 10 degrees with respect to an extension line obtained by extending a camber line of the airfoil portion from a leading edge. The condition (a) is a static pressure at a position of the first opening is equal to a static pressure at a position of the second opening when the airfoil portion receives a fluid flow from a direction of the angle A1 toward the leading edge.

A combination of an airfoil, turbine blade, or compressor blade with a flow separation control device includes an airfoil and a flow separation control device. The airfoil includes a body with an upper surface and a lower surface that extend from a leading edge to a trailing edge. The flow separation control device includes a plurality of openings on the upper surface of the body.

An airfoil assembly includes first and second fiber-reinforced composite airfoil rings that each have inner and outer platform sections, a suction side wall extending between the inner and outer platforms, a pressure side wall extending between the inner and outer platforms, and suction and pressure side mate faces along, respectively, edges of the suction and pressure side walls. The suction side mate face of the first fiber-reinforced composite airfoil ring and the pressure side mate face of the second fiber-reinforced composite airfoil ring mate at an interface to form an airfoil that circumscribes an internal cavity. A least one of the suction or pressure side mate faces includes protrusions along a trailing edge of the airfoil. The protrusions define a toothed exit slot for emitting cooling air from the internal cavity.

A vacuum pump includes a plurality of exhaust stages provided between an inlet port and an exhaust port so as to function as means for exhausting gas molecules, and a number of blades provided between the inlet port and an uppermost exhaust stage of the plurality of exhaust stages so as to rotate together with a rotary blade that constitutes the uppermost exhaust stage as a particle transport stage for transporting particles in an exhaust direction of the gas molecules, the number being smaller than the number of rotary blades that constitutes the uppermost exhaust stage.

A turbine blade, including a root, a vane including a leading edge and a trailing edge and a pressure-side wall and a suction-side wall, and including cooling vents at the trailing edge, this vane also including first and second serpentine circuits; each serpentine circuit including several ducts extending in the span direction, being connected to each other by angled portions; each serpentine circuit being supplied with air by its duct that is closest to the leading edge; and wherein the vents are supplied by the first and by the second serpentine circuit.

A centrifugal compressor impeller is disclosed for a charging device of an internal combustion engine. The impeller comprises a hub, a number of full blades arranged on the hub and being spaced in a circumferential direction of the impeller, and one splitter blade arranged between a pressure side of a first full blade and a suction side of a second full blade of the number of full blades. A leading edge of the splitter blade is arranged closer to the pressure side of the first full blade than the suction side of the second full blade. The present disclosure further relates to a charging device, an internal combustion engine, and a vehicle.

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, or Table IX. 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.

The invention relates to a blade or vane, particularly of a turbine stage of a gas turbine, in particular of an aircraft gas turbine, having a blade or vane root and a blade or vane element joined to the blade or vane root, wherein the blade or vane element has a pressure side and a suction side, and wherein the blade or vane root has at least one raised region on its radial outer side facing the blade or vane element. It is proposed according to the invention that the blade or vane has a first raised region on the pressure side and a second raised region on the suction side, wherein the highest point of the first raised region is disposed essentially directly adjacent to the pressure side, and the highest point of the second raised region is disposed essentially directly adjacent to the suction side.

An impeller includes a hub, and a plurality of blades supported by the hub, the blades being arranged in at least two blade rows. The impeller has a deployed configuration in which the blades extend away from the hub, and a stored configuration in which at least one of the blades is radially compressed, for example by folding the blade towards the hub. The impeller may also have an operational configuration in which at least some of the blades are deformed from the deployed configuration upon rotation of the impeller when in the deployed configuration. The outer edge of one or more blades may have a winglet, and the base of the blades may have an associated indentation to facilitate folding of the blades.

The present disclosure is directed to a rotor blade for a gas turbine system. The rotor blade includes a platform having a radially inner surface and a radially outer surface. A shank portion extends radially inwardly from the radially inner surface of the platform. The shank portion and the platform collectively define a shank pocket. An airfoil extends radially outwardly from the radially outer surface of the platform. The shank portion, the platform, and the airfoil collectively define a cooling passage extending from a cooling passage inlet defined by the shank portion or the platform and directly coupled to the shank pocket through the platform to a cooling passage outlet defined by the airfoil.