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Casing-groove optimisation for stall margin in a transonic compressor rotor

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posted on 2023-06-07, 07:17 authored by Ahmad Fikri Bin Mustaffa, Vasudevan KanjirakkadVasudevan Kanjirakkad
Purpose This paper aims to understand the aerodynamic blockage related to near casing flow in a transonic axial compressor using numerical simulations and to design an optimum casing groove for stall margin improvement using a surrogate optimisation technique. Design/methodology/approach A blockage parameter (?) is introduced to quantify blockage across the blade domain. A surrogate optimisation technique is then used to find the optimum casing groove design that minimises blockage at an axial location where the blockage is maximum at near stall conditions. Findings An optimised casing groove that improves the stall margin by about 1% can be found through optimisation of the blockage parameter (?). Originality/value Optimising for stall margin is rather lengthy and computationally expensive, as the stall margin of a compressor will only be known once a complete compressor map is constructed. This study shows that the cost of the optimisation can be reduced by using a suitably defined blockage parameter as the optimising parameter.

History

Publication status

  • Published

File Version

  • Accepted version

Journal

International Journal of Numerical Methods for Heat and Fluid Flow

ISSN

0961-5539

Publisher

Emerald

Department affiliated with

  • Engineering and Design Publications

Research groups affiliated with

  • Thermo-Fluid Mechanics Research Centre Publications

Full text available

  • Yes

Peer reviewed?

  • Yes

Legacy Posted Date

2020-06-19

First Open Access (FOA) Date

2020-07-21

First Compliant Deposit (FCD) Date

2020-06-18

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