The film effectiveness and coolant jet temperature profile on the suction side of a gas turbine blade were measured using a transient liquid crystal and a cold-wire technique, respectively. The blade has only one row of film holes oear the gill hole portion on the suction side of the blade. Tests were performed on a five-blade linear cascade in a low-speed wind tunnel. The mainstream Reynolds number based on cascade exit velocity was 5.3×105. Upstream unsteady wakes were simulated using a spoke-wheel type wake generator. Coolant blowing ratio was varied from 0.6 to 1.2. Wake Strouhal number was kept at 0 and 0.1. Results show that unsteady wake reduces film cooling effectiveness. Results also show that film injection enhances local heat transfer coefficient while the unsteady wake promotes earlier boundary-layer transition. The development of coolant jet temperature profiles could be used to explain the film cooling performance.
- International Gas Turbine Institute
Unsteady Wake Effect on Film Temperature and Effectiveness Distributions for a Gas Turbine Blade
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Teng, S, Sohn, DK, & Han, J. "Unsteady Wake Effect on Film Temperature and Effectiveness Distributions for a Gas Turbine Blade." Proceedings of the ASME 1999 International Gas Turbine and Aeroengine Congress and Exhibition. Volume 3: Heat Transfer; Electric Power; Industrial and Cogeneration. Indianapolis, Indiana, USA. June 7–10, 1999. V003T01A051. ASME. https://doi.org/10.1115/99-GT-172
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