Gas turbine engine component with cooling holes having variable roughness
AssigneeUnited Technologies Corporation
InventorJinQuan Xu
Life of this patent
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Abstract
A gas turbine engine component has an engine component body and at least one hole formed within the engine component body and extends between a hole inlet and a hole outlet. The hole has a first portion with a first roughness and a second portion having a second roughness that is less than the first roughness. The first portion is upstream of the second portion. A gas turbine engine and a method of forming a cooling hole are also disclosed.
Claims28
A gas turbine engine component comprising:
- an engine component body;
- and
- at least one hole formed within the engine component body and extending between a hole inlet and a hole outlet, wherein the hole has a first portion extending along a first length and having a first roughness and a second portion extending along a second length and having a second roughness that is less than the first roughness, and wherein the first portion is upstream of the second portion and the second length is greater than the first length.
A gas turbine engine component comprising:
- an engine component body;
- and
- at least one hole formed within the engine component body and extending between a hole inlet and a hole outlet, wherein the hole has a first portion having a first roughness and a second portion having a second roughness that is less than the first roughness, and wherein the first portion is upstream of the second portion, and wherein surface roughness gradually and continuously decreases along an inner hole surface of the at least one hole in a direction extending from an inlet of the first portion to an outlet of the second portion.
A gas turbine engine comprising:
- a compressor section;
- a combustor section downstream of the compressor section;
- a turbine section downstream of the combustor section;
- and
- wherein at least one of the combustor section and the turbine section include a component having a body with at least one hole formed within the body and extending between a hole inlet and a hole outlet, and wherein the hole has a first portion having a first roughness and extending along a first length starting from the hole inlet and a second portion having a second roughness that is less than the first roughness and the second portion extending along a second length from an end of the first portion to the hole outlet, and wherein the first portion is upstream of the second portion and the second length is greater than the first length.
A method of forming a cooling hole for a gas turbine engine comprising the steps of:
- forming at least one hole in an engine component body to extend between a hole inlet and a hole outlet;
- and
- forming the hole with a first portion extending along a first length and having a first roughness and a second portion extending along a second length and having a second roughness that is less than the first roughness, wherein the first portion is upstream of the second portion and wherein the second length is greater than the first length.
Dependencies are inferred from the claim text.