DTIC ADA273778: Effects of Crenulations on Three pdf

DTIC ADA273778: Effects of Crenulations on Three

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An experimental investigation into the effect of compressor blade trailing edge geometry on three-dimensional flows in a linear cascade was conducted at the AFIT linear cascade test facility. Hot-wire/hot-film anemometry along with total pressure instrumentation was used to analyze crenulation generated vortices and their interaction with the three-dimensional flows in the cascade. The effects of this interaction on the performance parameters associated with the cascade were quantified. The results-indicate that wake mixing is better for crenulated trailing edges and that the precise geometry of the crenulations is critical to performance. One crenulation geometry was found to increase wake mixing while slightly reducing the total pressure losses

• Creator/s: Defense Technical Information Center
• Date: 12/1/1993
• Year: 1993
• Book Topics/Themes: DTIC Archive, Spacy, William L, II, AIR FORCE INST OF TECH WRIGHT-PATTERSON AFB OH SCHOOL OF ENGINEERING, *VORTICES, *TRAILING EDGES, *THREE DIMENSIONAL FLOW, *AXIAL FLOW COMPRESSOR BLADES, *CASCADES(FLUID DYNAMICS), TEST AND EVALUATION, INTERACTIONS, LAYERS, PARAMETERS, EDGES, AIRFOILS, PRESSURE, INSTRUMENTATION, SECONDARY FLOW, COMPRESSOR BLADES, AXIAL FLOW, HOT WIRE ANEMOMETERS, TEST FACILITIES, FLOW, LOSSES, MIXING, GEOMETRY, AXIAL FLOW COMPRESSORS, WAKE, BOUNDARIES, WIRE, FACILITIES, FILMS, THESES, BOUNDARY LAYER

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