Experiments to measure losses of a linear cascade of transonic turbine blades are reported. Detailed measurements of the boundary layer at the rear of the suction surface of a blade and examination of wake traverse data enable the individual components of boundary layer, shock and mixing loss to be determined. Results indicate that each component contributes significantly to the overall loss in different Mach number regimes. Traverses in the near wake of the blade indicate the way in which the wake develops and facilitate examination of the development of the mixing loss.
- International Gas Turbine Institute
An Examination of the Contributions to Loss on a Transonic Turbine Blade in Cascade
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Mee, DJ, Baines, NC, Oldfield, MLG, & Dickens, TE. "An Examination of the Contributions to Loss on a Transonic Turbine Blade in Cascade." Proceedings of the ASME 1990 International Gas Turbine and Aeroengine Congress and Exposition. Volume 5: Manufacturing Materials and Metallurgy; Ceramics; Structures and Dynamics; Controls, Diagnostics and Instrumentation; General. Brussels, Belgium. June 11–14, 1990. V005T16A012. ASME. https://doi.org/10.1115/90-GT-264
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