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Markham J, Cosgrove J, Scire J, et al. Aircraft engine-mounted camera system for long wavelength infrared imaging of in-service thermal barrier coated turbine blades. Rev Sci Instrum. 2014;85(12):124902doi: 10.1063/1.4903266.
Markham, J., Cosgrove, J., Scire, J., Haldeman, C., & Agoos, I. (2014). Aircraft engine-mounted camera system for long wavelength infrared imaging of in-service thermal barrier coated turbine blades. The Review of scientific instruments, 85(12), 124902. https://doi.org/10.1063/1.4903266
Markham, James, et al. "Aircraft engine-mounted camera system for long wavelength infrared imaging of in-service thermal barrier coated turbine blades." The Review of scientific instruments vol. 85,12 (2014): 124902. doi: https://doi.org/10.1063/1.4903266
Markham J, Cosgrove J, Scire J, Haldeman C, Agoos I. Aircraft engine-mounted camera system for long wavelength infrared imaging of in-service thermal barrier coated turbine blades. Rev Sci Instrum. 2014 Dec;85(12):124902. doi: 10.1063/1.4903266. PMID: 25554314.
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Rev Sci Instrum. 2014 Dec;85(12):124902. doi: 10.1063/1.4903266.

Aircraft engine-mounted camera system for long wavelength infrared imaging of in-service thermal barrier coated turbine blades.

The Review of scientific instruments

James Markham, Joseph Cosgrove, James Scire, Charles Haldeman, Ian Agoos

Affiliations

  1. Advanced Fuel Research, Inc., 87 Church Street, East Hartford, Connecticut 06108, USA.
  2. New York Institute of Technology, Northern Blvd, Old Westbury, New York 11568, USA.
  3. Pratt & Whitney, 400 Main Street, East Hartford, Connecticut 06108, USA.

PMID: 25554314 DOI: 10.1063/1.4903266

Abstract

This paper announces the implementation of a long wavelength infrared camera to obtain high-speed thermal images of an aircraft engine's in-service thermal barrier coated turbine blades. Long wavelength thermal images were captured of first-stage blades. The achieved temporal and spatial resolutions allowed for the identification of cooling-hole locations. The software and synchronization components of the system allowed for the selection of any blade on the turbine wheel, with tuning capability to image from leading edge to trailing edge. Its first application delivered calibrated thermal images as a function of turbine rotational speed at both steady state conditions and during engine transients. In advance of presenting these data for the purpose of understanding engine operation, this paper focuses on the components of the system, verification of high-speed synchronized operation, and the integration of the system with the commercial jet engine test bed.

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