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US 2013/0294889 A1Published application
Gas turbine engine components with film cooling holes having cylindrical to multi-lobe configurations
AssigneeHoneywell International Inc.
InventorsMalak Fouad Malak, Rajiv Rana, Luis Tapia, David Chou, Jong Liu
Life of this patent
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Abstract
An engine component includes a body; and a plurality of cooling holes formed in the body, at least one of the cooling holes having a multi-lobed shape with at least a first lobe, a second lobe, and a third lobe.
Claims20
An engine component, comprising:
- a body;
- and
- a plurality of cooling holes formed in the body, at least one of the cooling holes having a multi-lobed shape with at least a first lobe, a second lobe, and a third lobe.
A turbine section of a gas turbine engine, comprising:
- a housing defining a hot gas flow path;
- a plurality of circumferential rows of airfoils disposed in the hot gas flow path;
- a plurality of cooling holes arranged within at least one of the plurality of circumferential rows of airfoils, wherein a first cooling hole of the plurality of cooling holes includes a multi-lobed shape.
A turbine section of a gas turbine engine, comprising:
- a housing defining a hot gas flow path;
- a plurality of circumferential rows of airfoils disposed in the hot gas flow path;
- a plurality of cooling holes arranged within at least one of the plurality of circumferential rows of airfoils, wherein a first cooling hole of the plurality of cooling holes includes
- an upstream portion with a cylindrical shape and
- a downstream portion coupled to the downstream portion and having with a multi-lobed shape, wherein the multi-lobed shape is formed by at least three ovals with overlapping first ends and splayed second ends.
2 more elements
Dependencies are inferred from the claim text.