Abstract: A ventilation device that enhances the effective longitudinal thrust of a fan assembly installed within a tunnel or other internal space. The nozzle trailing edge (6) is tilted so that it forms an angle (13) with respect to the fan centreline (7), with the surface of the nozzle throughbore being non-cylindrical in shape. The discharged flow (5) is turned away from the surrounding surfaces by a convergent-divergent bellmouth (1).

Abstract: A ventilation device that enhances the effective longitudinal thrust of a fan assembly installed within a tunnel or other internal space. The nozzle trailing edge (6) is tilted so that it forms an angle (13) with respect to the fan centreline (7), with the surface of the nozzle throughbore being non-cylindrical in shape. The discharged flow (5) is turned away from the surrounding surfaces by a convergent-divergent bellmouth (1).

Abstract: A ventilation device that enhances the effective longitudinal thrust of a fan assembly installed within a tunnel, by turning the discharged flow away from the surrounding tunnel surfaces and tilting the nozzle trailing edge (6) so that it forms an angle (16) to the nozzle centreline (8).

Abstract: A ventilation device that enhances the longitudinal thrust of a fan (2) installed within a tunnel, by the introduction of a convergent nozzle (7) to accelerate the outlet flow (8). An angled transition piece (6) can turn the flow by a specific angle (36). Multiple fans can be connected to common inlet and outlet plenums, supplying one or more convergent nozzles. Bi-directional flow can be achieved by fitting convergent nozzles to both sides of a fan, with bypass dampers optionally installed between the fan and the two nozzles. The nozzle trailing edge can be shaped with multiple lobes, chevrons or tongues, and the fan centre-body can be shaped with multiple lobes. A fire suppression agent such as water mist can be supplied into the ductwork between the fan and the nozzle trailing edge. Acoustic silencing can be achieved using the absorbent material on the nozzle and fan centre-body.

Abstract: The invention relates to an impact flow for wall sections including a plurality of impact openings which are arranged on a plane in a flat or curved support. The support is fitted it a distance from the wall section, and the impact surface of the wall section that is to be cooled is configured as a bulged relief. The bulge elements are arranged around the impact surface of the impact beam. The surfaces of the bulge elements facing the impact beam include two curves which blend into one another.

Abstract: The arrangements and the methods serve for the efficient and reliable cooling of components 210, in particular in turbomachines, even in the event of a local increase in the static pressure 234 of a hot fluid which flows over the component. In order to ensure sufficient cooling of the components 210, the distance between the cooling holes 240 is in each case selected in such a way that the cooling holes 240 in the region of increased static pressure 234 of the hot fluid are at a smaller distance from one another than in the regions of lower static pressure. A typical design of the invention is shown in FIG. 3.

Abstract: A hot-gas stream (40) flows along the surface of a segment arrangement for shroud bands, in particular in a gas turbine. The segment arrangement comprises segments (20, 20′) arranged next to one another and in each case separated from one another by a gap (12). The hot-gas stream (40), in at least one section (70) of the gap (12), has a velocity component perpendicular to the direction of the gap from a first segment (20) to a second segment (20′). In this case, in said section (70), along that edge (26) of the first segment (20) which faces the gap (12), at least one film-cooling bore (52) connects a cooling-air chamber (50), allocated to the first segment, to the surface (22) subjected to the hot-gas stream (40), and/or, in said section (70), along that edge (26′) of the second segment (20′) which faces the gap (12), at least one edge-cooling bore (56) connects a cooling-air chamber (50′), allocated to the second segment, to the inside (28′) of the gap (12).

Abstract: Platform cooling having a guide-blade platform (30; 60) which is subjected to a hot-gas stream (20) and is separated by a gap (36; 66) from a combustion-chamber segment (40; 70) arranged upstream, one or more segment cooling bores (42; 72) being made in the combustion-chamber segment (40; 70), which segment cooling bores (42; 72) connect a cooling-air chamber (44; 74) to the gap (36; 66). The guide-blade platform (30; 60) has a surface (34; 64) on the downstream side in the region of the gap (36; 66), the axes of the one or more segment cooling bores (42; 72) running roughly tangentially to said surface (34; 64).