Abstract: In a jet engine having a fan (9) of conventional type, a second combustion chamber (5) is provided downstream of the turbine (4), and a second turbine (6) acts downstream of this second combustion chamber (5). The hot gases (16) partly expanded in the first turbine (4) are brought up to temperature again in the second combustion chamber (5), whereby, at a low absolute hot-gas temperature, more output is then available in the engine. A bypass flow nozzle (10) is coaxially arranged with a compressor unit (1, 2) such that the compressed intake air mass flow (12) is divided up into an inner flow entering the compressor unit (1, 2) and a bypass flow expanding in the bypass flow nozzle (10), wherein the ratio of bypass and inner flow is high in order to achieve a substantial contribution to the total thrust of the engine by the bypass flow.

Abstract: A process for producing a casting core which is used for forming within a casting a cavity intended for cooling purposes, through which a cooling medium can be conducted, the casting core having surface regions in which there is incorporated in a specifically selective manner a surface roughness which transfers itself during the casting operation to surface regions enclosing the cavity and leads to an increase in the heat transfer between the cooling medium and the casting.

Abstract: A cooling passage of a component subjected to high thermal loading, which is formed as a cavity (2, 20, 30), running in a longitudinal direction (L) and curved orthogonally to the longitudinal direction (L), between a first wall (5) and a second wall (6), which in each case are connected to one another in a laterally adjacent manner, which has ribs (7, 17, 27), which are arranged on the first wall (5) and the second wall (6) such that they alternate in a longitudinal direction (L) and are staggered relative one another and, at least in sections, assume a non-orthogonal angle relative to a projected center axis (10′), and through which a cooling fluid (K) can flow in a longitudinal direction (L), in which case, when the profile of the cavity (2, 20, 30) is curved orthogonally to the longitudinal direction (L), the ribs (7, 17, 27) are formed in such a way that, in each case locally with regard to the adjacent rib of the opposite wall, they maintain a distance (a) which is half a respective local rib spac

Abstract: The arrangements according to the invention and the method according to the invention serve to cool platforms in turbomachines. To this end, in two platforms 210, 210′ arranged directly next to one another and having a separating gap 211 running between the platforms, at least one cooling passage 230 is arranged along the separating gap 211. In this case, the cooling passage 230 runs approximately parallel to the surface of the platforms 210, 210′. The cooling passage 230 is preferably designed as a slit-like recess in at least one side wall adjacent to the separating gap 211. If blades 220, 220′ are arranged on the platforms 210, 210′, the cooling passage 230 expediently runs approximately centrally between the blades. In addition, the cooling passage 230 preferably has a course similar to the course of the blade profile.

Abstract: The arrangements according to the invention and the methods according to the invention serve to seal a gap 20 against a primary fluid 10 by means of a secondary fluid 11 in a fluid-dynamic and non-contact manner, which primary fluid 10 flows over the gap 20. The secondary fluid 11 forms a preferably rotating vortex flow 13 in the gap in at least one or more sections along the gap. The flow of the secondary fluid 11 is preferably guided in a chamber 26, which is arranged in the gap 20. The chamber 26 is designed as a rotary chamber along the entire gap 20 or also as a local chamber 226 extending only locally along the gap. The secondary fluid 11 may be supplied via supply conduits 40, in which the gap 120 itself may be utilized for supplying secondary fluid 115 to the chamber 126. As further elements for the guidance of the vortex flow, guiding lips 50, undercuts of the chamber contour 351, and guiding elements 160 may be arranged in the gap.