Leading-edge redesign of a turbomachinery blade and its effect on aerodynamic performance
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DOI: 10.1016/j.apenergy.2011.12.091
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References listed on IDEAS
- Hamakhan, I.A. & Korakianitis, T., 2010. "Aerodynamic performance effects of leading-edge geometry in gas-turbine blades," Applied Energy, Elsevier, vol. 87(5), pages 1591-1601, May.
- Benini, Ernesto & Biollo, Roberto & Ponza, Rita, 2011. "Efficiency enhancement in transonic compressor rotor blades using synthetic jets: A numerical investigation," Applied Energy, Elsevier, vol. 88(3), pages 953-962, March.
- Ghorbanian, K. & Gholamrezaei, M., 2009. "An artificial neural network approach to compressor performance prediction," Applied Energy, Elsevier, vol. 86(7-8), pages 1210-1221, July.
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Cited by:
- Galindo, J. & Fajardo, P. & Navarro, R. & García-Cuevas, L.M., 2013. "Characterization of a radial turbocharger turbine in pulsating flow by means of CFD and its application to engine modeling," Applied Energy, Elsevier, vol. 103(C), pages 116-127.
- Gabl, Roman & Innerhofer, Daniel & Achleitner, Stefan & Righetti, Maurizio & Aufleger, Markus, 2018. "Evaluation criteria for velocity distributions in front of bulb hydro turbines," Renewable Energy, Elsevier, vol. 121(C), pages 745-756.
- Wang, Xiaojing & Zou, Zhengping, 2019. "Uncertainty analysis of impact of geometric variations on turbine blade performance," Energy, Elsevier, vol. 176(C), pages 67-80.
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Keywords
Blade profile; Leading edge; Design method; Pressure spike; Separation bubble; Turbomachine;All these keywords.
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