Results 201 to 210 of about 1,092 (255)

Wall Stall in Compressor Cascades

Journal of Basic Engineering, 1966
The “wall stall” in compressor cascades has been observed by many research workers. There is a region of high loss in the corner bounded by the end wall and the suction surface of a blade. It is the separation of the flow in this region which is largely responsible for the increase in the axial velocity across the midspan section of the blades when ...
J. H. Horlock   +3 more
openaire   +1 more source

On the Efficiency of Secondary Flow Suction in a Compressor Cascade

Volume 7: Turbomachinery, Parts A, B, and C, 2010
An experimemtal investigation in a high speed compressor cascade has been carried out to show the effect of different types of secondary flow suction. In order to get deeper insight into the separated three dimensional flow topology and to determine appropriate suction positions, numerical simulations are performed additionally for the baseline cascade.
Liesner, K.   +4 more
openaire   +2 more sources

Experimental Investigation of Flow Control in Compressor Cascades

Volume 6: Turbomachinery, Parts A and B, 2006
A large part of the total pressure losses in a compressor stage is caused by secondary flow effects like the separation between the wall and the vane i.e., a corner separation. An experimental and numerical investigation in a highly loaded compressor cascade was performed to understand the fluid mechanic mechanism of this corner separation in order to ...
Hergt, A., Meyer, R., Engel, K.
openaire   +2 more sources

Losses In Turbine and Compressor Cascades

2005
The flow through a turbomachine is generally three-dimensional, viscous, highly unsteady, transitional, turbulent, and compressible. This complex flow is associated with total pressure losses caused by different flow and geometry parameters. To accurately predict the efficiency of a turbomachine, accurate flow calculation is required.
openaire   +2 more sources

The Jet-Flap Compressor Cascade

Journal of Basic Engineering, 1961
Scholz’s method for measurements on a two-dimensional cascade has been extended to include mass and energy input into the main flow by trailing-edge jets. Pressure recovery and mixing losses downstream of the cascade have been theoretically investigated and the need of low jet velocities has been emphasized.
openaire   +1 more source

Annular Cascade for Radial Compressor Development

Volume 7: Turbomachinery, Parts A, B, and C, 2011
A full-annulus cascade for radial compressor stator development has been designed and commissioned. The cascade has been developed for the rapid screening of novel stator concepts to facilitate risk mitigation in the early design phase and the validation/calibration of numerical predictions. The rig consists of two main parts.
Christian Aalburg   +5 more
openaire   +1 more source

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