Abstract: Methods and apparatus for gas turbine frame flow path hardware cooling are disclosed. An example engine fan case includes an outer band and an inner band, the outer band and the inner band connected using a double-walled vane, the vane including openings to pass cooling air flow from the outer band to an airfoil of the fairing, and an end segment seal, the seal formed on an edge of the fairing using an auxetic material.

Abstract: In a method of forming a cooling bore in a wall of a workpiece, the configuration of a feed section and a diffuser section is selected, a throughbore is produced with a cross-sectional area within the cross-sectional area of the feed section, and the diffuser section is cut out by a beam- or jet-drilling method in such a way that the drilling beam or jet in the region of the feed section remains essentially within the cross-sectional area of the latter.

Abstract: The section of an electrical high-voltage system has a gas-filled housing of predominantly symmetrical design. Provided in the housing are a conductor extending along a plane of symmetry of the housing, and cooling means for producing a circulation flow which dissipates heat loss from the conductor. The cooling means contains two blowers. The blowers are arranged in the interior of the housing and designed in such a way that, during the operation of the system, two mirror-symmetrical circulation part flows are formed which are bounded by the plane of symmetry. These circulation part flows are in each case guided without recirculation along a housing side wall from the top of the housing or the bottom of the housing. By this means, the heat loss is given up particularly effectively to the housing side walls, and the conductor can be loaded with very high operating currents.

Abstract: A cooling wall comprises an outer surface, which is exposed to a hot-gas flow, an inner surface, and at least one film-cooling hole within the wall, which film-cooling hole has a diffuser section and an outlet at the outer surface. The diffuser section has first and second internal surfaces, the intersection edge between the first internal surface and the outer surface forming an upstream edge of the outlet, and the intersection edge between the second internal surface and the outer surface forming a downstream edge of the outlet. The diffuser section has side surfaces, which faces one another, connect the first and second internal surfaces and diverge from one another toward the outlet of the diffuser section. The first internal surface of the diffuser section is rounded toward the axis of the film-cooling hole.

Abstract: An arrangement and method for cooling a wall surrounded on one side by hot gas, for example, a guide blade of a turbine, where cooling air is directed into a space between the wall and a cooling insert wall, and allowed to flow through rows of holes in the wall to an outer surface of the wall. A rib is arranged upstream of the row of holes on the inner surface of the wall, and the cooling insert wall is shaped to bulge toward the wall at the hole location, so that a guiding surface parallel to an entry angle of the holes is provided. By causing the cooling air to flow in the entry angle of the holes before it reaches the holes, the cooling air forms stable inner-vortex pairs in the flow, and entry losses are reduced. Cooling air not flowing into a first row of holes is accelerated and guided past spacers and pins in the space, before being guided to downstream rows of holes.