The invention relates to a ventilation device for a turbomachine turbine casing, comprising a plurality of line sets (16) configured to spray air over the turbine casing, the line sets being arranged next to one another, each line set comprising a main ring (161) in which air circulates, the main ring (161) comprising orifices (17) configured to spray a stream of air towards the turbine casing, the line set comprising a shield (162) configured to isolate the main ring (161) from a stream of air returning from the turbine casing towards the line sets after having been sprayed towards the turbine casing, the said shield (162) enveloping the main ring (161) and having orifices aligned with the orifices of the main ring (161).

A turbine blade for a gas turbine employs film cooling to enhance cooling performance. The turbine blade includes an outer surface; and at least one film cooling hole formed in the outer surface, each film cooling hole including a cooling channel extending inside the turbine blade to guide cooling air toward the outer surface, an outlet communicating with one end of the cooling channel to discharge cooling air to the outer surface, and a plurality of protrusions formed on an inside surface of the outlet and arranged along a longitudinal direction of the outlet. The protrusions protrude inwardly to a predetermined height from the inside surface of the outlet and extend from the cooling channel to the outer surface, in an arrangement of at least one protrusion formed on an inside wall of the outlet or on each of two opposing inside walls of the outlet.

Disclosed is a vane assembly. An outer ring segment surrounds a rotor extending through an inner central portion of a casing. Vanes are fitted into the outer ring segment in a direction perpendicular to an axial direction of the rotor. A fixing portion is fitted into the outer ring segment to fix the vanes to the outer ring segment.

A component for a gas turbine engine is disclosed. The component includes a platform and a rail having an outer radial surface and an inner radial surface, with the inner radial surface connected to the platform. The rail includes a plurality of apertures spaced circumferentially between the outer radial surface and the inner radial surface, the apertures disposed to form a truss-like structure.

A guide vane for a diffuser of a radial compressor which is arranged downstream of a receiving area for a compressor wheel is disclosed. The guide vane has a skeleton line where the skeleton line is elliptical at least in a sub-region.

A core element of an investment core for use in a casting process used to produce an airfoil includes an investment core body, an extension connected to and protruding from the investment core body, and a connection portion connected to the investment core body and to the extension. The investment core body comprises a ceramic material. A shape of the extension comprises a tube with a centerline axis passing through a center of the extension. A shape of a cross-section of the extension taken along a plane perpendicular to the extension centerline axis comprises an ellipse. The extension is connected to the investment core body by the connection portion.

The invention concerns a conical hula seal wherein an inner part of the conical hula seal is closer to a conical hula seal longitudinal axis than an outer part of the conical hula seal, and wherein the conical hula seal extends in a circumferential direction relative to the conical hula seal longitudinal axis. A gas turbine which includes the conical hula seal is also disclosed, along with a method of operating a gas turbine which includes a conical hula seal that seals a gap between a first vane and a picture frame, the method including purging the gap with a cooling fluid.

Embodiments of the invention relate generally to rotary machines and, more particularly, to the control of wheel space purge air in gas turbines. In one embodiment, the invention provides a turbine bucket comprising: a platform portion; an airfoil extending radially outward from the platform portion; a platform lip extending axially from the platform portion; and a plurality of voids disposed along a surface of the platform lip.

The invention relates to a ventilator wheel which is produced in the form of a radial or a diagonal ventilator wheel, and comprises a bottom disc and a plurality of ventilator blades arranged, on said bottom disc, so as to be distributed about an axial rotational axis, said bottom disc comprising a circumferential radial outer edge section that, when viewed in cross-section, extends in a curved shape in at least some sections and thus forms an elliptical transition of said bottom disc from a radial extension into an axial extension.

An airfoil includes pressure and suction side walls that extend in a chord-wise direction between leading and trailing edges. The pressure and suction side walls extend in a radial direction to provide an exterior airfoil surface. A core cooling passage is arranged between the pressure and suction walls in a thickness direction and extends radially toward a tip. A skin passage is arranged in one of the pressure and suction side walls to form a hot side wall and a cold side wall. The hot side wall defines a portion of the exterior airfoil surface and the cold side wall defines a portion of the core passage. The core passage and the skin passage are configured to have a same direction of fluid flow. A resupply hole fluidly interconnects the core and skin passages. A centerline of the resupply hole is arranged at an acute angle relative to the direction of fluid flow in the core passage and is configured to provide a low turbulence flow region in the skin passage.