Cooling arrangement for gas-turbine components

A segment arrangement for platforms for supporting airfoils in a gas turbine in which a hot gas stream flows along the surface of platforms, the segment arrangement comprising:

• first and second segments arranged adjacent to one another and in each case separated from one another by a gap, the first and second segments having cooling-air chambers, the gap having a first section and a second section, the hot-gas stream at the first section of the gap having a velocity component substantially perpendicular to the direction of the gap when the hot gas stream is flowing from the first segment to the second segment, the hot-gas stream having a velocity component perpendicular to the direction of the gap from the second segment to the first segment, and in the second section, along that edge of the second segment which faces the gap, at least one film-cooling bore in the second segment, for conducting cooling air to the surface subjected to the hot-gas stream, and at least one of said segments having at least one edge cooling bore therein along the edge that faces the gap for conducting cooling air from one of the cooling-air chambers to the inside of the gap.

A segment arrangement for platforms for supporting airfoils in a gas turbine, in which a hot-gas stream flows along the surface of the platforms, the segment arrangement comprising:

• a plurality of segment arranged adjacent 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, having a velocity component substantially perpendicular to the direction of the gap when the hot-gas stream is flowing from a first segment to a second segment, wherein, said section includes a plurality of film-cooling bores along the edge of the first segment which faces the gap for conducting cooling air to the surface subjected to the hot-gas stream for displacing the gas stream away from the edge of the gap, and in which the film-cooling bores are of cylindrical shape on the side facing the cooling-air chambers and have a funnel-shaped opening on the hot-gas side.

A segment arrangement for platforms for supporting airfoils in a gas turbine, in which a hot-gas stream flows along the surface of the platforms, the segment arrangement comprising:

• a plurality of segments arranged adjacent 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, having a velocity component substantially perpendicular to the direction of the gap when the hot-gas stream is flowing form a first segment to a second segment, wherein, said section includes a plurality of film-cooling bores along the edge of the first segment which faces the gap for conducting cooling air to the surface subjected to the hot-gas stream for displacing the gas stream away from the edge of the gap, and in which the film-cooling bores and edge-cooling bores are from the edge of the gap, and in which the film-cooling bores and edge-cooling bores are staggered laterally.