Abstract
It is advantageous to operate the thermodynamic cycle of anaeroengine at as high a turbine entry temperature as practical forthe current metallurgical limits of the turbine blades, in order toachieve peak cycle efficiency and thus lower specific fuelconsumption. However, achieving the highest possible turbine entrytemperature requires accurate knowledge of the turbine bladetemperatures for control purposes to prolong component life, asfrequent excursions beyond the design limits of the blades canseverely reduce their service life. The optical pyrometry techniquerepresents the best method for providing these crucial temperaturedata needed for blade condition based monitoring. However, thismethod of non-contact temperature measurement is subject to a numberof errors inherent to the gas turbine operating environment. In thispaper we present the general operating principles and an overview ofthe measurement errors associated with optical pyrometry, togetherwith a discussion of the techniques to prevent, limit and compensatefor such errors resulting from the turbine environment.
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