Systems and methods of locating cooling features in a gas turbine component under thermal barrier coatings
AssigneeGeneral Electric Company
InventorsThomas J. Batzinger, Thomas E. Moldenhauer, Keith C. Belsom
Life of this patent
Estimating the term…
Abstract
The present application provides a cooling hole location system for locating a cooling hole in a gas turbine component, wherein the cooling hole is covered by a thermal barrier coating. The cooling hole location system may include a light source positioned on a first side of the gas turbine component and an optical detector positioned on a second side of the gas turbine component. The optical detector detects light from the light source visible through the thermal barrier coating covering the cooling hole.
Claims17
A cooling hole location system for locating a cooling hole in a gas turbine component, wherein the cooling hole is covered by a thermal barrier coating, comprising:
- a light source positioned on a first side of the gas turbine component;
- and
- an optical detector positioned on a second side of the gas turbine component;
- wherein the light source and/or the optical detector is maneuverable with respect to the gas turbine component;
- and
- wherein the optical detector detects light from the light source visible through the thermal barrier coating covering the cooling hole so as to determine location and orientation of the cooling hole.
A method of locating a cooling hole in a gas turbine component covered with a thermal barrier coating, comprising:
- positioning a light source on a first side of the gas turbine component;
- positioning an optical detector on a second side of the gas turbine component;
- transmitting light from the light source at the first side of the gas turbine component;
- and
- maneuvering the light source and/or the optical detector until the light is detected through the thermal barrier coating by the optical detector so as to determine location and orientation of the cooling hole.
A cooling hole location system for locating a gas turbine component cooling hole covered by a thermal barrier coating, comprising:
- a gas turbine component;
- a light source positioned on a first side of the gas turbine component;
- an optical detector positioned on a second side of the gas turbine component;
- and
- a machining system;
- wherein the light source and/or the optical detector is maneuverable with respect to the gas turbine component;
- wherein the optical detector detects light from the light source visible through the thermal barrier coating covering the cooling hole so as to determine location and orientation of the cooling hole;
- and
- wherein the machining system removes the thermal barrier coating covering the cooling hole.
Dependencies are inferred from the claim text.