United Technologies Corporation

Raytheon Technologies Corporation

Rtx Corporation

Shayan Ahmadian

Mark F Zelesky

Hoyt Y Chang

Carey J Clum

Kevin W Schlichting

Charles W Haldeman

Sebastian Martinez

Christopher T Bergman

Steven Bruce Gautschi

Alexander Staroselsky

Joel H Wagner

Thomas J Martin

Christopher W Robak

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 coating system including a reflective cool down chamber with at least one arcuate wall; and an infrared lamp directed at the arcuate wall.

System and method for low thermal shock-fast cooling of thermal barrier coating

A combustor may include a combustor shell, a particle collection panel, and a combustor panel. The combustor shell may define a plurality of first impingement holes, the particle collection panel may include a plurality of particle collection chambers and may define a plurality of second impingement holes, and the combustor panel may define a plurality of effusion holes. The particle collection panel may be disposed inward of the combustor shell and the combustor panel may be disposed inward of the particle collection panel. Each particle collection chamber may have a closed inward end and an opening defined in an outward end. The particle collection chambers may be configured to entrap particulates.

Combustor with particle collection panel having a plurality of particle collection chambers

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.

A tangential on-board injector (TOBI) for a gas turbine engine is provided. The TOBI includes a body having an entrance and an exit, the body having an outer curved wall and defining an air passageway between the entrance and the exit and a purge cavity configured on an exterior surface of the body with a purge cavity entry fluidly connecting the air passageway to the purge cavity. The purge cavity is configured such that particles in an airflow through the passageway will enter the purge cavity.

Tangential on-board injectors for gas turbine engines

A particle separator for removing particles in a flow of air is provided. The particle separator having: a conduit for directing air towards a curved section of the conduit; and a drum in fluid communication with the conduit proximate to the curved section of the conduit, wherein particles in the air travelling towards the curved section will contact a surface of the drum.

Apparatus and method for air particle separation in a gas turbine engine

An engine and particle decelerator is provided herein. The engine having: an inlet opening for directing air towards a compressor of the engine; and a particle decelerator located between the inlet opening and the compressor such that air travelling towards the compressor from the inlet opening must travel through the particle decelerator and wherein an area of the particle decelerator is greater than an inlet and an outlet of the particle decelerator.

Apparatus and method for air particle separator in gas turbine engine

A system and method for prognostic health monitoring of thermal barrier coatings is provided. The system may comprise monitoring a thermal barrier coated gas turbine engine component, and measuring the infrared radiation emitting from the component. The measured thermal radiation data may be analyzed and compared to known material thermal radiation data in order to determine the health of the thermal barrier coating. The compiled comparison results may be compared against a historical statistical study to then determine the overall health of the thermal barrier coating. The system may comprise generating a health monitoring alert in response to the health of the thermal barrier coating indicating an imminent failure.

Growing community of inventors

Vernon, CT, United States of America

Shayan Ahmadian