A Numerical Study of the 3D Flowfield in a Transonic Compressor Rotor with a Modelling of the Tip Clearance Flow,
CAMBRIDGE UNIV (ENGLAND)
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Modelling the complex flowfield in a transonic axial compressor rotor is a considerable but worthwhile challenge for flow prediction methods. This paper describes a computer code aimed at solving the equations of three dimensional viscous compressible flow in turbomachine geometries. The code is applied to the study of the flowfield in a transonic axial compressor rotor at design speed at both maximum flow and towards stall. The rotor was designed at DFVLR and tested using laser two-focus velocimetry. The rotor has a hub-tip ratio of 0.5 and design speed of 20260 rpm. At the design point the rotor pressure ratio is 1.626 and the mass flow 17.1 kgs. The predicted flowfield is compared with the laser measurements and the performance of the code discussed. In addition the discussion highlights the changes in the predicted endwall and tip clearance flows as the rotor operating point is moved towards stall.
- Fluid Mechanics
- Jet and Gas Turbine Engines