Method for extracting rotor dynamic orbit from blade tip clearance and time of arrival measurements

A system for determining rotor-dynamic orbit information comprising:

• a gas turbine engine having at least one engine stage;
• an engine case supporting the at least one engine stage, each at least one engine stage including a rotor having a plurality of blades;
• at least one blade tip sensor operatively coupled to the engine case surrounding the plurality of blades within the at least one engine stage, the at least one blade tip sensor in operative communication with the plurality of blades;
• at least one compensation sensor in operative communication with the at least one blade tip sensor;
• and
• an orbit controller in operative communication with the at least one blade tip sensor and the at least one compensation sensor, wherein the at least one compensation sensor is configured to sense the location of the at least one blade tip sensor relative to the engine case and configured to indicate the relative motion of the at least one blade tip sensor.

A process for determining rotor-dynamic orbit information comprising:

• providing an engine case supporting at least one engine stage, each at least one engine stage including a rotor having blades;
• operatively coupling at least one blade tip sensor to the engine case;
• the at least one blade tip sensor in operative communication with the blades;
• coupling at least one compensation sensor in operative communication with the at least one blade tip sensor;
• and
• placing an orbit controller in operative communication with the at least one blade tip sensor and the at least one compensation sensor, wherein the at least one compensation sensor is configured to sense the location of the at least one blade tip sensor relative to the engine case and configured to indicate the relative motion of the at least one blade tip sensor.