United Technologies Corporation

Raytheon Technologies Corporation

Allison Clark Nicklous

Daniel L Gysling

Joseph V Paturzo

Richard A Lomenzo

Steven Tyler Englerth

Zaffir A Chaudhry

Edward F Dreger, Iii

William F Caswell

An aero damping measurement system is provided. The system includes a shroud defining a tunnel, a hub disposed within the tunnel, and a plurality of blades coupled to the hub. The blades may rotate about the hub. A gas pressure probe may have a tip extending to the tunnel to deliver a pressurized burst into the tunnel. An aeromechanical identification system may include a pressurized gas source, a valve in fluid communication with the pressurized gas source, and the gas pressure probe may be in fluid communication with the valve. The valve may control a flow of a pressurized gas from the pressurized gas source into the gas pressure probe. A pressure sensor may be coupled to the gas pressure probe and configured to measure a pressure within the gas pressure probe.

Aeromechanical identification systems and methods

A system is provided for testing a component. This system includes a support structure, an excitation system and a sensor system. The support structure is configured to support the component. The excitation system includes a plurality of excitation devices arranged in an array. The plurality of excitation devices at least include a first excitation device, a second excitation device and a third excitation device. The excitation system is configured to respectively control each of the plurality of excitation devices to excite a vibratory response in the component. The sensor system is configured to output data indicative of the vibratory response.

Inducing and monitoring a vibratory response in a component

A system is provided for testing a component. This system includes a support structure, an excitation system and a sensor system. The support structure is configured to support the component. The excitation system includes a plurality of permanent magnets and a plurality of electromagnets. The permanent magnets are arranged in an array and configured for rigid connection to the component. Each of the electromagnets is associated with a respective one of the permanent magnets. The excitation system is configured to respectively control interaction of the electromagnets with the permanent magnets to excite a vibratory response in the component. The sensor system is configured to output data indicative of the vibratory response.

A method includes rotating a rotor, measuring a rotor rotational time for the rotor to complete a revolution, determining a blade interval by dividing the rotor rotational time by a number of blades carried on the rotor, establishing an active hold-off time interval as a percentage of the blade interval time, directing a beam of light at the blades of the rotor using a laser, sensing light reflected from the blades, generating an output signal as a function of the sensed light, establishing a signal amplitude threshold, analyzing an amplitude of the output signal to trigger the active hold-off time interval when the amplitude reaches the signal amplitude threshold, and generating a blade arrival signal as a function of triggered active hold-off time intervals. The output signal is not analyzed within each active hold-off time interval.

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Old Saybrook, CT, United States of America

Allison Clark Nicklous