US 2012/0237333 A1 · COOLED GAS TURBINE ENGINE COMPONENT

Abstract

A gas turbine engine component is disclosed having a cooling fluid passageway that provides relatively cool fluid to a surface of the gas turbine engine component. The cooling fluid passageway can be shaped in cross section to reduce a stress present in the gas turbine engine component. One form of the shape is non-circular. The gas turbine engine component can be formed such that an overhanging material otherwise formed by the intersection of a cooling fluid passageway and a surface of the gas turbine engine component is absent. The gas turbine engine component can also have a depression formed near the surface of the gas turbine engine component such that the cooling fluid passageway exits into an upstream portion and a downstream portion of the depression.

Claims23

Dependent claims

An apparatus comprising:

a film cooled gas turbine engine component having a passage defined by a passage surface for flowing a cooling air to a hot side, the passage extending at an acute angle to the hot side surface and the passage surface having a hot side surface side;
and
an edge break formed in the gas turbine engine component and having an edge break surface extending from the hot side surface to the hot side surface side of the passage, the side of the passage opposite the hot side surface side continuing to the hot side, the edge break representing an overhanging material absent from the gas turbine engine component when an edge break surface is formed.

Dependencies are inferred from the claim text.

Cooled gas turbine engine component

Life of this patent

Cooled gas turbine engine component

Life of this patent

Abstract

Claims23