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Optical pyrometry for gas turbine aeroengines

Clive Kerr (School of Engineering, Cranfield University, Cranfield, UK)
Paul Ivey (School of Engineering, Cranfield University, Cranfield, UK)

Sensor Review

ISSN: 0260-2288

Article publication date: 1 December 2004



Fundamentally, it is advantageous to operate an aeroengine's thermodynamic cycle at as high a turbine entry temperature as practical for the current metallurgical limits of the turbine blades in order to achieve peak cycle efficiency and thus lower specific fuel consumption. However, achieving the highest possible turbine entry temperature requires accurate knowledge of the turbine blade temperatures for control purposes to prolong component life as frequent excursions beyond the design limits of the blades can severely reduce their service life. The optical pyrometry technique represents the best method for providing this crucial temperature data needed for blade condition‐based monitoring. This paper presents the general operating principles, system aspects and design considerations for the application of the optical pyrometer instrument for inflight service use on gas turbine aeroengines.



Kerr, C. and Ivey, P. (2004), "Optical pyrometry for gas turbine aeroengines", Sensor Review, Vol. 24 No. 4, pp. 378-386.



Emerald Group Publishing Limited

Copyright © 2004, Emerald Group Publishing Limited

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