Gas turbine engine having a metallic test sample and a method of determining the service life of a gas turbine engine component using a metallic test sample
AssigneeROLLS-ROYCE plc
InventorGrant J. GIBSON
Life of this patent
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Abstract
A method of determining the service life of a gas turbine engine component comprises providing, within a gas turbine engine, a component having an air washed surface, the component comprises a metal, wherein the air washed surface receives a supply of cooling air from a chamber within the gas turbine engine. The method also comprises mounting a metallic test sample within the chamber so as to be located in the supply of air which is delivered to the air washed surface. The metallic test sample is constructed of the same metal as the component. The method further comprises removing the metallic test sample and determining the degree of corrosion of the metallic test sample.
Claims22
A gas turbine engine, comprising:
- a component having a gas path facing surface and an air cooled surface, wherein the air cooled surface is arranged to receive a supply of cooling air, the gas path facing surface is arranged to receive a supply of hot gas, the component comprises a metal;
- a chamber in fluid communication with the air cooled surface, in operation the chamber is arranged to supply air to the air cooled surface or the chamber is arranged to receive air which has been supplied to the air cooled surface;
- a metallic test sample mounted within the chamber so as to be located in the air which is to be delivered to the air cooled surface or to be located in the air delivered by the air cooled surface, wherein the metallic test sample is constructed of the same metal as the component or a similar metal to the component.
A method of determining the service life of a gas turbine engine component, comprising:
- providing, within a gas turbine engine, a component having a gas path facing surface and an air cooled surface, wherein the air cooled surface is arranged to receive a supply of cooling air, the gas path facing surface is arranged to receive a supply of hot gas, the component comprises a metal;
- supplying air to the air cooled surface;
- supplying hot gas to the gas path facing surface;
- supplying air from a chamber within the gas turbine engine to the air cooled surface or supplying air from the air cooled surface to a chamber within the gas turbine engine;
- mounting a metallic test sample within the chamber so as to be located in the supply of air which is delivered to the air cooled surface or to be located in the supply of air which is delivered by the air cooled surface, wherein the metallic test sample is constructed of the same metal as the component or a similar metal to the component;
- removing the metallic test sample and
- determining the degree of corrosion of the metallic test sample.
A method of determining the service life of a gas turbine engine component, comprising:
- providing, within a gas turbine engine, a component having an air washed surface, the component comprises a metal;
- supplying air to the air washed surface;
- supplying air from a chamber within the gas turbine engine to the air washed surface or supplying air from the air washed surface to a chamber within the gas turbine engine;
- mounting a metallic test sample within the chamber so as to be located in the supply of air which is delivered to the air washed surface or to be located in the supply of air which is delivered by the air washed surface, wherein the metallic test sample is constructed of the same metal as the component or a similar metal to the component;
- removing the metallic test sample and
- determining the degree of corrosion of the metallic test sample.
Dependencies are inferred from the claim text.