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Single and multiple circumferential casing groove for stall margin improvement in a transonic axial compressor

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conference contribution
posted on 2023-06-09, 21:42 authored by Ahmad Fikri Bin Mustaffa, Vasudevan KanjirakkadVasudevan Kanjirakkad
The stability limit of a tip-stalling axial compressor is sensitive to the magnitude of the near casing blockage. In transonic compressors, the presence of the passage shock could be a major cause for the blockage. Identification and elimination of this blockage could be key to improving the stability limit of the compressor. In this paper, using numerical simulation, the near casing blockage within the transonic rotor, NASA Rotor 37, is quantified using a blockage parameter. For a smooth casing, the blockage at conditions near stall has been found to be maximum at about 20% of the tip axial chord downstream of the tip leading edge. This maximum blockage location is found to be consistent with the location of the passage shock-tip leakage vortex interaction. A datum single casing groove design that minimises the peak blockage is found through an optimisation approach. The stall margin improvement of the datum casing groove is about 0.6% with negligible efficiency penalty. Furthermore, the location of the casing groove is varied upstream and downstream of the datum location. It is shown that the stability limit of the compressor is best improved when the blockage is reduced upstream of the peak blockage location. The paper also discusses the prospects of a multi-groove casing configuration.

History

Publication status

  • Published

File Version

  • Accepted version

Journal

Proceedings of the ASME Turbo Expo 2020

Publisher

ASME

Volume

2A

Article number

aGT2020-14974

Event name

ASME 2020 Turbo Expo

Event location

Virtual Conference

Event type

conference

Event date

21-25 September 2020

ISBN

9780791884065

Series

Turbomachinery

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

2020-09-28

First Open Access (FOA) Date

2021-01-19

First Compliant Deposit (FCD) Date

2020-09-29

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