Raytheon Technologies Corporation

United Technologies Corporation

Christopher T Bergman

Mark F Zelesky

Charles W Haldeman

Shayan Ahmadian

Sebastian Martinez

A method of measuring a gas turbine engine component of a gas turbine engine according to an example of the present disclosure includes, among other things, providing at least one gas turbine engine component including a coating on a substrate, detecting infrared radiation emitted from at least one localized region of the coating at a first wavelength in a first electromagnetic radiation frequency range, detecting infrared radiation emitted from the substrate corresponding to the at least one localized region at a second, different wavelength in a second electromagnetic radiation frequency range that differs from the first electromagnetic radiation frequency range, and determining a heat flux relating to the at least one localized region based upon a comparison of the first wavelength and the second wavelength.

Heat flux measurement system

A turbine section according to an example of the present disclosure includes, among other things, a component including a coating on a substrate, and at least one sensor positioned a distance from the component, the at least one sensor configured to detect radiation emitted from at least one localized region of the coating at a first wavelength and configured to detect radiation emitted from the substrate corresponding to the at least one localized region at a second, different wavelength. The first wavelength and the second wavelength are utilized to determine a heat flux relating to the at least one localized region. A method of measuring a gas turbine engine component is also disclosed.

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Wethersfield, CT, United States of America

Christopher T Bergman