Izhar Ullah, L. Wright, Chao-Cheng Shiau, Je-Chin Han, Zhihong Gao, Andrea Stanton
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FILM COOLING COMPARISON OF FULL-SCALE TURBINE VANES USING THE PRESSURE SENSITIVE PAINT TECHNIQUE
This work is an experimental study of film cooling effectiveness on two real scale turbine vanes in a 3-vane annular cascade. The cascade is connected to a high flow steady compressor to provide the mainstream flow. The inlet velocity is maintained at 35 m/s at the center line of the annular cascade. Two heavily cooled, real scale turbine vanes are tested with cooling holes on the pressure and suction surfaces. Vane 1 has 645 cooling holes distributed around the vane. Vane 2 has an additional two row of holes at the near leading edge SS of the vane. The MFR is varied from 3.12% to 4.82%. Increasing the MFR increases the film effectiveness. The introduction of additional rows of cooling holes resulted in re-distribution of coolant from the pressure surface to the suction surface. This study provides designers with more insight into how to place rows of cooling holes to have improved effectiveness.
期刊介绍：
The Journal of Turbomachinery publishes archival-quality, peer-reviewed technical papers that advance the state-of-the-art of turbomachinery technology related to gas turbine engines. The broad scope of the subject matter includes the fluid dynamics, heat transfer, and aeromechanics technology associated with the design, analysis, modeling, testing, and performance of turbomachinery. Emphasis is placed on gas-path technologies associated with axial compressors, centrifugal compressors, and turbines.
Topics: Aerodynamic design, analysis, and test of compressor and turbine blading; Compressor stall, surge, and operability issues; Heat transfer phenomena and film cooling design, analysis, and testing in turbines; Aeromechanical instabilities; Computational fluid dynamics (CFD) applied to turbomachinery, boundary layer development, measurement techniques, and cavity and leaking flows.
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