Influence of Mach Number on Profile Loss of Axial-Flow Turbine Blades
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The current profile loss prediction methods for axial turbine blades predict a monotonic increase in profile losses at outlet Mach numbers above 1.0. However, linear cascade testing in the literature has revealed a more complex behaviour. An objective of this investigation was to help clarify the flow features that are most influential on the profile losses in the transonic and supersonic regimes. Four linear cascades of turbine blades were investigated both experimentally and computationally. Linear cascade measurements were carried out using the High Speed Wind Tunnel (HSWT) at Carleton University. It was found that the base pressure was strongly linked to the profile losses in the transonic and supersonic regimes. The position of the trailing edge shock impingement on the adjacent blade and its associated effect on the boundary layer were also found to influence the profile losses.
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Copyright © 2015 the author(s). Theses may be used for non-commercial research, educational, or related academic purposes only. Such uses include personal study, research, scholarship, and teaching. Theses may only be shared by linking to Carleton University Institutional Repository and no part may be used without proper attribution to the author. No part may be used for commercial purposes directly or indirectly via a for-profit platform; no adaptation or derivative works are permitted without consent from the copyright owner.
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kibsey-influenceofmachnumberonprofilelossofaxialflow.pdf | 2023-05-04 | Public | Download |