Two recent research endeavors in turbomachinery at NASA Glenn Research Center have focused on compression system stall inception and compression system aerothermodynamic performance. Physical experiment and computational research are ongoing in support of these research objectives. TURBO, an unsteady, three-dimensional, Navier-Stokes computational fluid dynamics code commissioned and developed by NASA, has been utilized, enhanced, and validated in support of these endeavors. In the research which follows, TURBO is shown to accurately capture compression system flow range-from choke to stall inception-and also to accurately calculate fundamental aerothermodynamic performance parameters. Rigorous full-annulus calculations are performed to validate TURBO s ability to simulate the unstable, unsteady, chaotic stall inception process; as part of these efforts, full-annulus calculations are also performed at a condition approaching choke to further document TURBO s capabilities to compute aerothermodynamic performance data and support a NASA code assessment effort.
Unsteady Full Annulus Simulations of a Transonic Axial Compressor Stage
AIAA 47th Aerospace Sciences Meeting and Exhibit ; 2009 ; Orlando, FL, United States
2009-05-01
Report
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English
Unsteady Full Annulus Simulations of a Transonic Axial Compressor Stage
British Library Conference Proceedings | 2009
|Steady and Unsteady Flow-Simulations of an Axial Transonic Compressor Stage
British Library Conference Proceedings | 2008
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