TY  - JOUR
AB  - 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.
VL  - 24
IS  - 4
SN  - 0260-2288
DO  - 10.1108/02602280410558412
UR  - https://doi.org/10.1108/02602280410558412
AU  - Kerr Clive
AU  - Ivey Paul
PY  - 2004
Y1  - 2004/01/01
TI  - Optical pyrometry for gas turbine aeroengines
T2  - Sensor Review
PB  - Emerald Group Publishing Limited
SP  - 378
EP  - 386
Y2  - 2024/04/19
ER  -