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This paper describes the application of high resolution pyrometry for surface temperature measurements of the blading in heavy duty gas turbines. First of all, it is essential to know the actual loading, since the cylindrical pyrometer probes are traversed into the hot gas path. Therefore, analytical methods for the calculation of the heat transfer, equivalent stresses and natural frequencies of the probes are described here. The second part presents results of measurements from the latest model V84.3A 60Hz 180 MW gas turbine in the Berlin full load test bed. Emphasis is put on the effect of combustor radiation, limited resolution of the pyrometer and 3D presentations of the data.

Like its predecessors, Siemens’ first Hybrid Burner Ring® machine (Becker et al., 1995) underwent an extensive experimental development and test programm prior to its introduction to the market. The present paper describes the philosophy of prototype testing, some of the challenges encountered in instrumenting the machine and the methodology and experimental techniques used to solve the problems. In particular, it describes some of the advanced implementations of blade vibration measurements, optical pyrometry and other temperature measurements, and techniques to determine efficiency. The experimental results confirm the design of the model V84.3A gas turbine and show some potential for further improvements.

Based on the experience gained with more than 80 machines operating worldwide in 50 and 60 Hz electrical systems respectively, Siemens has developed a new generation of advanced gas turbines which yield substantially improved performance at a higher output level. This “3A-Series” comprises three gas turbine models ranging from 70 MW to 240 MW for 50 Hz and 60 Hz power generation applications. The first of the new advanced gas turbines with 170 MW and 3600 rpm was tested in the Berlin factory test facility under the full range of operation conditions. It was equipped with various measurement systems to monitor pressures, gas and metal temperatures, clearances, strains, vibrations and exhaust emissions. This paper presents the aero-thermal design procedure of the highly thermal loaded film cooled first stage blading. The predictions are compared with the extensive optical pyrometer measurements taken at the Siemens test facility on the V84.3A machine under full load conditions. The pyrometer was inserted at several locations in the turbine and radially moved giving a complete surface temperature information of the first stage vanes and blades.