Transonic Turbine Vane Endwall Film Cooling Using the Pressure-Sensitive Paint Measurement Technique
| Autor: | Ardeshir Riahi, Chao-Cheng Shiau, İzzet Şahin, Izhar Ullah, Je-Chin Han, Alexander V. Mirzamoghadam, Curtis K. Stimpson |
|---|---|
| Rok vydání: | 2020 |
| Předmět: |
Gas turbines
020301 aerospace & aeronautics Momentum (technical analysis) Materials science Mechanical Engineering Pressure-sensitive paint 02 engineering and technology Mechanics 01 natural sciences Turbine 010305 fluids & plasmas Coolant symbols.namesake 0203 mechanical engineering Mach number 0103 physical sciences symbols Transonic |
| Zdroj: | Journal of Turbomachinery. 142 |
| ISSN: | 1528-8900 0889-504X |
| DOI: | 10.1115/1.4045990 |
| Popis: | This work focuses on the parametric study of film cooling effectiveness on the turbine vane endwall under various flow conditions. The experiments were performed in a five-vane annular sector cascade facility in a blowdown wind tunnel. The controlled exit isentropic Mach numbers were 0.7, 0.9, and 1.0, from high subsonic to transonic conditions. The freestream turbulence intensity is estimated to be 12%. Three coolant-to-mainstream mass flow ratios (MFR) in the range 0.75%, 1.0%, and 1.25% are studied. N2, CO2, and Argon/SF6 mixture were used to investigate the effects of density ratio (DR), ranging from 1.0, 1.5, to 2.0. There are eight cylindrical holes on the endwall inside the passage. The pressure-sensitive paint (PSP) technique was used to capture the endwall pressure distribution for shock wave visualization and obtain the detailed film cooling effectiveness distributions. Both the high-fidelity effectiveness contour and the laterally (spanwise) averaged effectiveness were measured to quantify the parametric effect. This study will provide the gas turbine designer more insight on how the endwall film cooling effectiveness varies with different cooling flow conditions including shock wave through the endwall crossflow passage. |
| Databáze: | OpenAIRE |
| Externí odkaz: |
|