Asea Brown Boveri Ag

Alstom

Abb Alstom Power (schweiz) Ag

Abb Alstom Power (switzerland) Ltd.

Fathi Tarada

Bernhard Weigand

Gordon David Anderson

Kenneth Hall

Michael Hock

J&ouml;rgen Ferber

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.

Turbine blade wall section cooled by an impact flow

The arrangements and the methods serve for the efficient and reliable cooling of components,in particular in turbomachines, even in the event of a local increase in the static pressure,of a hot fluid which flows over the component. In order to ensure sufficient cooling of the components,the distance between the cooling holes,is in each case selected in such a way that the cooling holes,in the region of increased static pressure,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.

Cooling in gas turbines

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

Cooling arrangement for gas-turbine components

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).

Growing community of inventors

Kehrsatz, Switzerland

Fathi Tarada