A two-dimensional thin-layer Navier-Stokes cascade flow solver for turbomachinery is
developed. A second-order finite-difference scheme and a second and fourth-difference
dissipation scheme are used. Periodic and non-reflecting inlet and outlet boundary conditions
are implemented into the approximate-factorization numerical method. Turbulence
is modeled through the one-equation Spalart-Allmaras model. A two-dimensional turbomachinery
cascade structured grid generator is developed to produce six-block H-type
grids.
The validity of this work is tested in various ways. A grid convergence study is
performed showing the effect of grid density. The non-reflecting inlet and outlet boundary
conditions are tested for boundary placement influence. Comparisons of the flow solver
numerical results are performed against experimental results. A Mach number sweep and
angle of attack sweep are performed on two similar transonic turbine cascades.
| Identifer | oai:union.ndltd.org:TORONTO/oai:tspace.library.utoronto.ca:1807/25568 |
| Date | 31 December 2010 |
| Creators | Epp, Duane R. |
| Contributors | Zingg, David W. |
| Source Sets | University of Toronto |
| Language | en_ca |
| Detected Language | English |
| Type | Thesis |
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