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Computational aero-engine core-compressor aeroelasticity

Project CORCOMPA
Research Area Aero-engine unsteady flows and aeroelasticity
Principal Investigator(s) M. Imregun
Institution(s)
  • Imperial College London, UK
  • Rolls-Royce plc, UK

Abstract

Aero-engine compressors deliver a large quantity of air at high pressure. From an efficiency viewpoint, it is desirable to operate them at the highest possible pressure ratios but such operating points are inherently unstable because of their close proximity to undesirable aerodynamic phenomena of stall and surge. Rotating stall is a local  instability where reduced flow rate gives rise to flow separation and results in the formation of stall cells. These cells  begin to rotate around the annulus and hit the blades, thus causing high vibratory loads. Surge is a global instability in which flow reversal occurs throughout the machine, causing  high transient stresses in the blading. Deficiencies in understanding the exact mechanisms and a lack of modelling methodology prevent the determination of the dynamic loads and the ensuing blade response. Therefore, current designs are based on safe margins where the bladerow spacing is not optimum. The overall aim of the project is not only to understand the rotating stall and surge mechanisms and the links between them, but also to prove the feasibility of the large-scale modelling approach as a design tool. Here, an application is made to find additional computational resource to extend the scope of an existing study where a large-scale  model of a typical industrial core-compressor has already been built.
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