The effect of coolant ejection from the trailing edge of a turbine blade is studied by means of numerical simulation codes. Two solvers based on explicit and implicit algorithms with and without multigridding are used in connection with H, HOH and HC grid types. A simple procedure to model the coolant jet at the trailing edge of the blade is presented which does not require excessive grid refinement. The features of the different approaches are discussed in terms of isentropic Mach number distribution on the blade, base pressures and wake profiles at various exit Mach numbers and coolant flow rates which match the experimental conditions. The coolant ejection effect on the shock pattern is discussed. The trailing edge ejection is found to have a marginal effect on the wake shape and on the measured and computed base pressures.
Aerodynamic Performance of a Transonic Turbine Guide Vane With Trailing Edge Coolant Ejection: Part II — Numerical Approach
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Michelassi, V, Martelli, F, & Amecke, J. "Aerodynamic Performance of a Transonic Turbine Guide Vane With Trailing Edge Coolant Ejection: Part II — Numerical Approach." Proceedings of the ASME 1994 International Gas Turbine and Aeroengine Congress and Exposition. Volume 1: Turbomachinery. The Hague, Netherlands. June 13–16, 1994. V001T01A089. ASME. https://doi.org/10.1115/94-GT-248
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