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Spreading Control of Coolant Jet at the Trailing Edge of Gas Turbine Blade with Arc-jet Exhaust Buffling

Khosravi, Pooya | 2022

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  1. Type of Document: M.Sc. Thesis
  2. Language: Farsi
  3. Document No: 56499 (45)
  4. University: Sharif University of Technology
  5. Department: Aerospace Engineering
  6. Advisor(s): Javadi, Khodayar
  7. Abstract:
  8. This research investigates the use of baffles in sector jets for film cooling of turbine blades. The goal of this study is to compare the cooling performance in three conditions: sector jet without baffles (one 90-degree arc), with one baffle (two 45-degree arcs), and with two baffles (three 30-degree arcs). The effect of using this type of cooling is also compared to the crossflow jet, which is the simplest type of cooling jet. In all conditions, the mass flow ratio is constant and equal to 1. The problem is solved for a turbine blade with the “AGTB-B1” airfoil. The problem is first solved with the Transition SST turbulence model, and the results are used as the initial conditions for the Large Eddy Simulation (LES) solution. Because the mixing of the cooling and mainstream flows is being studied, the Large Eddy Simulation approach can predict the phenomena better than RANS-based approaches. The results show that, in general, the cooling performance with the use of sector wall jets is much better than the crossflow jet. In the comparison between the three conditions, the sector jet with one baffle shows better and more uniform performance than the sector jet with two baffles. In aerodynamic parameters such as the L/D of the blade, the sector jet in the one-baffle condition performs better than the other conditions, with an L/D that is about 2.7% higher than the crossflow jet
  9. Keywords:
  10. Film Cooling ; Turbine Blades ; Cooling Effectiveness Coefficient ; Arc Shape Well Jets ; Large Eddy Simulation (LES) ; Boundary Layer Control ; Buffling

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