| CPC F01D 5/186 (2013.01) [F05D 2220/32 (2013.01); F05D 2240/30 (2013.01); F05D 2260/202 (2013.01)] | 17 Claims |
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1. A blade for a gas turbine, comprising:
a blade wall having an outer surface and an inner surface that defines a cavity for receiving a gaseous cooling fluid, the blade wall having a first thickness between the outer surface and the inner surface;
a cooling hole foot formed on the inner surface, the cooling hole foot including a first foot surface that extends inclined relative to a base surface region of the inner surface surrounding the cooling hole foot, wherein the blade wall has a second thickness between the outer surface and the inner surface about the cooling hole foot is greater than the first thickness; and
a cooling hole extending between the first foot surface of the cooling hole foot and the outer surface to discharge cooling fluid from the cavity to the outer surface, a central axis of the cooling hole extending transverse to the first foot surface,
wherein the cooling hole has a circular cross-section, and
wherein an inner aperture of the cooling hole formed on the inner surface has an oval or elliptic circumference; and
wherein the cooling hole has a constant diameter from the inner aperture to the outer surface.
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