Using shock control bumps to improve transonic fan/compressor blade performance

John, A., Qin, N. and Shahpar, S. (2019) Using shock control bumps to improve transonic fan/compressor blade performance. Journal of Turbomachinery, 141 (8). 081003. ISSN 0889-504X

Abstract

Metadata

Authors/Creators:
  • John, A.
  • Qin, N.
  • Shahpar, S.
Copyright, Publisher and Additional Information: © 2019 ASME. This is an author produced version of a paper subsequently published in Journal of Turbomachinery. Uploaded in accordance with the publisher's self-archiving policy. Article available under the terms of the Creative Commons Attribution Licence (http://creativecommons.org/licenses/by/4.0)
Dates:
  • Accepted: 14 February 2019
  • Published (online): 2 March 2019
  • Published: August 2019
Institution: The University of Sheffield
Academic Units: The University of Sheffield > Faculty of Engineering (Sheffield) > Department of Mechanical Engineering (Sheffield)
Depositing User: Symplectic Sheffield
Date Deposited: 28 Feb 2019 11:24
Last Modified: 02 Mar 2020 01:39
Status: Published
Publisher: ASME
Refereed: Yes
Identification Number: https://doi.org/10.1115/1.4042891

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