Wake Dissipation and Total Pressure Loss in a Two-Dimensional Compressor Cascade with Crenulated Trailing Edges

Wake dissipation and total pressure loss in a two-dimensional, subsonic, compressor cascade with crenulated trailing edges were investigated in the Cascade Test Facility. Three blade configurations, a baseline NACA 64-905 airfoil and two crenulated edge patterns were used. Hot wire anemometry and a...

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Bibliographic Details
Main Author: Veesart, Janet L
Format: Report
Language:English
Subjects:
ANGLES
BASE LINES
BOUNDARY LAYER
CASCADE TESTING
COEFFICIENTS
COMPRESSOR BLADE
COMPRESSOR BLADES
COMPRESSORS
COUNTERROTATION
CRENULATED TRAILING EDGES
CRENULATIONS
DISSIPATION
Fluid Mechanics
HOT WIRE ANEMOMETERS
LOSSES
PRESSURE
TEST AND EVALUATION
TEST FACILITIES
THESES
TRAILING EDGES
TWO DIMENSIONAL FLOW
VORTICES
WAKE
WAKES
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Summary:Wake dissipation and total pressure loss in a two-dimensional, subsonic, compressor cascade with crenulated trailing edges were investigated in the Cascade Test Facility. Three blade configurations, a baseline NACA 64-905 airfoil and two crenulated edge patterns were used. Hot wire anemometry and a total pressure rake were used to collect the flow data. The smaller crenulation configuration exhibited the greatest turning angle and the least total pressure losses. The most rapid wake dissipation was generated by the larger crenulations' counterrotating vortices accompanied by slightly higher pressure losses than those created by the small crenulations. Both crenulated blade configurations had better wake dissipation, increased turning angles, and smaller pressure loss coefficients than the uncrenulated baseline blade.