Numerical simulation of shock wave/tip leakage vortex interaction for a transonic axial fan rotor
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Yan Xue
Abstract
This paper presents the steady numerical investigation on SW/TLV interaction with SST turbulence model at two characteristic operating conditions for a transonic fan rotor, NASA Rotor 67. The main purpose of the present work is to reveal the main flow structures and properties during the SW/TLV interaction, and a theoretical criterion for vortex stability is engineeringly utilized to determine such shock wave-induced vortex stability. The validations for all numerical schemes have been conducted by comparing the RANS solutions with detailed experimental data before the analyses of flow phenomenon and mechanism. The simulation results indicate that numerical methods used in NUAA-Turbo 2.0 solver, independently developed by our team, enable to accurately capture the complex flow structures including shock wave and vortex systems within the blade passages, especially in the tip region. Similar to wing-tip vortex created by vortex generator, the TLV has the same wake-type characteristics. The flow pattern generated by such interaction is characterized by the bulged-forward shock front followed by a subsonic flow region and a slight expansion of vortex core. No apparent vortex breakdown was examined by both intuitive visualization of three-dimensional vortex structure and a theoretical criterion.
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Author contributions: All the authors have accepted responsibility for the entire content of this submitted manuscript and approved submission.
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Research funding: None declared.
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Conflict of interest statement: The authors declare no conflicts of interest regarding this article.
References
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Articles in the same Issue
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- Effect of multi-hole arrangement on the effusion cooling with backward injection
- Research on a component characteristic adaptive correction method for variable cycle engines
- Optimization of a circumferential groove in a centrifugal compressor
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- Numerical simulation of shock wave/tip leakage vortex interaction for a transonic axial fan rotor
- Experimental research on suppressing unbalanced vibration of rotor by integral squeeze film damper
- The influence of the geometry of V-gutter bluff body on transient vortex shedding
- Design and validation of a two-dimensional variable geometry inlet
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Articles in the same Issue
- Frontmatter
- Design and aerodynamic performance analysis of a variable geometry axisymmetric inlet for TBCC
- Effect of multi-hole arrangement on the effusion cooling with backward injection
- Research on a component characteristic adaptive correction method for variable cycle engines
- Optimization of a circumferential groove in a centrifugal compressor
- Comparative study of numerical approaches to adaptive gas turbine cycle analysis
- Numerical simulation of shock wave/tip leakage vortex interaction for a transonic axial fan rotor
- Experimental research on suppressing unbalanced vibration of rotor by integral squeeze film damper
- The influence of the geometry of V-gutter bluff body on transient vortex shedding
- Design and validation of a two-dimensional variable geometry inlet
- Computational assessment of performance parameters of an aero gas turbine combustor for full flight envelope operation
- Investigation of effect of atomization performance on lean blowout limit for gas turbine combustors by comparison of utilizing aviation kerosene and methane as fuel
- Design optimization of a supersonic through-flow fan rotor based on the blade profiles
