Back to results
US 2016/0108755 A1Published application
Gas turbine engine component
AssigneeUnited Technologies Corporation
InventorsJesse M. Carr, Bryan P. Dube
Life of this patent
Estimating the term…
Abstract
A gas turbine engine component includes an exterior pressure side with a plurality of cooling holes located in the exterior pressure side. A relief cut surrounds at least one of the plurality of cooling holes.
Claims20
A gas turbine engine component comprising:
- an exterior pressure side;
- a plurality of cooling holes located in the exterior pressure side;
- and
- a relief cut surrounding at least one of the plurality of cooling holes.
1 more element
A gas turbine engine comprising:
- a turbine section configured to rotate about an axis of rotation;
- a combustor section;
- and
- a component located in at least one of the turbine section and the combustor section including:
- an exterior pressure side;
- a plurality of cooling holes located in the exterior pressure side;
- and
- a relief cut surrounding at least one of the plurality of cooling holes.
5 more elements
A method of forming a component comprising:
- forming a cooling hole in an exterior pressure side of a component;
- and
- removing a portion of the exterior pressure side of the component to form a relief cut.
Dependencies are inferred from the claim text.