The Boundary Layer Behaviour of Highly Loaded Compressor Cascade at Transonic Flow Conditions,
DEUTSCHE FORSCHUNGS- UND VERSUCHSANSTALT FUER LUFT- UND RAUMFAHRT E V BRUNSWICK (GERMANY F R)
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The design of efficient blade profiles for gas turbine compressors can no longer be effectively carried out through the use of correlations of 2D-cascade data. For the description of the real flow field three dimensional effects have to be taken into account. Modern theoretical calculation methods which involve the determination of blade profile pressure distribution and the associated boundary layer parameters, are now becoming accepted practice. However before the engine designer can have confidence in these new methods the predicted performance must be demonstrated to be in good agreement with experimental data. It is the purpose of the work reported in this contribution to present an accurate set of experimental measurements of blade profile pressure distributions and boundary layer parameters under quasi-3D-flow conditions and to compare these with the predicted performance for a high deflection transonic compressor cascade. It is shown that for conditions near minimum loss incidence the agreement between measured and predicted values is achieved to an adequate engineering standard and that the two most important aspects, choking flow and boundary layer separation H12 2.8 are well predicted. Also the data presented could be used to further update and improve the current prediction methods.
- Fluid Mechanics
- Jet and Gas Turbine Engines