Global Power and Propulsion (GPPS): Montreal18 - Proceedings
Published May 7, 2018 | Version v1
Conference paper Open

Optimization of High Subsonic, High Reynolds Number Axial Compressor Airfoil Sections for Increased Operating Range

Authors/Creators

  • 1. TU Braunschweig, Institute of Jet Propulsion and Turbomachinery, Germany
  • 2. Institute of Fluid Mechanics Braunschweig, Germany

Description

In this paper an increase of up to 4% in surge margin while having more than a one percent increase in peak isentropic efficiency for an optimized stator of a high subsonic axial compressor was achieved. Using a simplified design method coupled with an optimization algorithm, only stacked stator span wise blade elements were optimized and remaining the same rotor. Subsonic axial compressor can be exposed to different inflow situations along blade height with circumferential changes. In the present study, the optimization of each airfoil section is done by only varying three main parameters, which reduces computational time. The chosen approach combines a generalized parabolic arc mean camber with the so-called Class Function / Shape Function Methodology. The comparison to the original stator airfoil sections shows an increase in operating range of up to 22% with 33% lower minimum losses. A stator only investigation confirms the increased performance for all optimized airfoil sections.

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References

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