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Stall margin improvement in a low-speed axial compressor rotor using a blockage-optimised single circumferential casing groove

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posted on 2023-06-09, 23:45 authored by Ahmad Fikri Bin Mustaffa, Vasudevan KanjirakkadVasudevan Kanjirakkad
The stall margin of tip-critical axial compressors can be improved by using circumferential casing grooves. From previous studies, in the literature, the stall margin improvement due to the casing grooves can be attributed to the reduction of the near casing blockage. The pressure rise across the compressor as the compressor is throttled intensifies the tip leakage flow. This results in a stronger tip leakage vortex that is thought to be the main source of the blockage. In this paper, the near casing blockage due to the tip region aerodynamics in a low-speed axial compressor rotor is numerically studied and quantified using a mass flow-based blockage parameter. The peak blockage location at the last stable operating point for a rotor with smooth casing is found to be at about 10% of the tip chord aft of the tip leading edge. Based on this information, an optimised single casing groove design that minimises the peak blockage is found using a surrogate-based optimisation approach. The implementation of the optimised groove is shown to produce a stall margin improvement of about 5%.

History

Publication status

  • Published

File Version

  • Published version

Journal

Journal of the Global Power and Propulsion Society

ISSN

2515-3080

Publisher

Global Power and Propulsion Society

Volume

5

Page range

79-89

Pages

89.0

Department affiliated with

  • Engineering and Design Publications

Full text available

  • Yes

Peer reviewed?

  • Yes

Legacy Posted Date

2021-05-05

First Open Access (FOA) Date

2021-05-05

First Compliant Deposit (FCD) Date

2021-05-05

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