In this thesis, the operation of the MiniLab experimental test rig equipped with an SR-30 single-stream turbine engine was established, and its performance was evaluated at several operating points. As part of the work, a LabVIEW program was developed to enable the acquisition, display, processing, and storage of measurement data, as well as the calculation of selected engine performance parameters. The connections between the sensors and the data acquisition card were upgraded, and the thrust measurement system was calibrated. Based on the measured pressures, temperatures, rotational speed, volumetric fuel flow, and thrust, the characteristics of the compressor and turbine, air mass flow, fuel-to-air ratio, thrust-specific fuel consumption, and calculated net thrust were determined. The obtained results were compared with values reported in the literature. The analysis identified small deviations, particularly in the temperature measurements, which affect the reliability of the calculated efficiencies and power values of individual components. Despite the limitations of the measurement system, a useful basis was established for further laboratory measurements, improvements to the measurement equipment, and continued research work on the MiniLab experimental test rig.
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