Abstract
The temperature gradient along the turbine vane can lead to significant uncertainty when the Pressure Sensitive Paint (PSP) technique is applied to film cooling measurements in compressible flow conditions. The current study presents a calibration surface based on temperature ratio to correct the temperature-induced errors using single-luminophore PSP. An endoscope-based PSP system and thermocouples were adopted to investigate the cooling performance and temperature over a turbine vane pressure side (PS) surface in a transonic wind tunnel. Carbon dioxide (DR =1.53) as coolant was discharged into the flow passage through seven rows of holes (i.e., three rows of circular holes and five rows of 7-7-7 shaped holes) with the mass flow ratio (MFR) of 0.6%, 0.9%, 1.06% and 1.21%. The errors of PSP results were greatly reduced at different temperature ratios with the assistance of temperature corrections. This method makes it more suitable for film cooling diagnosis using PSP in compressible flow conditions.
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