Gas turbine engine component with embedded data
AssigneeSolar Turbines Incorporated
InventorsAngelo Vincent Marasco, Jeffrey Stephen Carullo
Life of this patent
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Abstract
A component for a gas turbine engine is disclosed. The component includes at least a first portion and a second portion, and a data representing matrix. The second portion includes a second portion surface. The data representing matrix is formed directly on the second portion surface and includes a plurality of contrasting cells arranged in a geometric pattern representing information about the component including test data, a serial number, and a part number. The plurality of contrasting cells includes a plurality of first cells and a plurality of second cells that contrast from the plurality of first cells.
Claims20
A component for a gas turbine engine, the component comprising:
- at least a first portion and a second portion, the second portion being a connection end of the component and including a second portion surface;
- and
- a data representing matrix formed directly on the second portion surface, the data representing matrix including
- a plurality of contrasting cells arranged in a geometric pattern representing information about the component including test data, a serial number, and a part number, the plurality of contrasting cells including
- a plurality of first cells, and
- a plurality of second cells that contrast from the plurality of first cells, and
- a finding pattern formed by a grouping of contrasting cells of the plurality of contrasting cells to locate and orient the data representing matrix for a data representing matrix reader.
A rotor blade for a gas turbine engine including a rotor disk, the rotor blade comprising:
- a platform;
- an airfoil extending from the platform in a first direction, the airfoil including
- a leading edge,
- a trailing edge,
- a pressure side extending from the leading edge to the trailing edge, and
- a suction side opposite the pressure side extending from the leading edge to the trailing edge;
- a blade root extending from the platform in a second direction, opposite the first direction, the blade root including
- a rotor disk contacting surface that contacts the rotor disk when the rotor blade is installed in the gas turbine engine, and
- a root surface adjacent the rotor disk contacting surface;
- and
- a data representing matrix formed on the blade root, the data representing matrix being an optical machine-readable representation of information about the rotor blade including airflow data, a serial number, and a part number formed on the root surface.
A data representing matrix formed on a root surface of a rotor blade for a gas turbine engine, the data representing matrix comprising:
- a plurality of first cells;
- a plurality of second cells with a different surface texture than the plurality of first cells to contrast the plurality of second cells from the plurality of first cells;
- a finding pattern formed by an optical and machine-readable grouping of second cells of the plurality of second cells to locate and orient the data representing matrix for a data representing matrix reader;
- a timing pattern formed by an optical and machine-readable grouping of alternating first cells of the plurality of first cells and second cells of the plurality of second cells to identify a number of rows and columns of the data representing matrix for the data representing matrix reader;
- and
- a remainder of the plurality of first cells and the plurality of second cells arranged in an optical and machine-readable geometric pattern representing information about the rotor blade including airflow data, a serial number, and a part number.
Dependencies are inferred from the claim text.