| Author(s): |
Hamada, Gabriel Y. R.
;
Lui, Hugo F. S.
;
Wolf, William R.
;
Junqueira-Junior, Carlos, Jr.
Total Authors: 4
|
| Document type: | Journal article |
| Source: | AIAA AVIATION FORUM AND ASCEND 2024; v. N/A, p. 12-pg., 2024-01-01. |
| Abstract | |
Boundary layers of adiabatic and isothermal walls of a supersonic turbine cascade are investigated including the effects of shock-boundary layer interactions (SBLIs). Large eddy simulations (LES) are performed for a linear cascade of blades with an inlet Mach number of M-infinity = 2.0 and Reynolds number based on the axial chord Re = 200 000. For the isothermal case, the wall to inlet temperature ratio is T-w/T-infinity = 0.75, representing a cooled wall. Different incident shock wave topologies occur on the suction and pressure sides of the airfoil. For the former, an oblique shock impinges on the boundary layer, leading to a larger separation bubble. On the other hand, a normal shock from a Mach reflection induces a small separation region near the wall for the pressure side. The incoming boundary layers are characterized by looking at the Clauser pressure gradient parameter and the shape factor profiles. The effects of pressure gradient, surface curvature and thermal boundary condition are assessed in terms of the mean density, temperature, and turbulent kinetic energy (TKE) profiles. Results show that the adiabatic wall boundary layers are more prone to separate than the isothermal ones, both upstream and downstream the SBLIs. Cooling increases the density of the gas near the wall, which in turn increases the levels of TKE. The mean temperature and density profiles are considerably modified due to the convex (suction side) and concave (pressure side) curvatures of the turbine blade. (AU) | |
| FAPESP's process: | 13/08293-7 - CCES - Center for Computational Engineering and Sciences |
| Grantee: | Munir Salomao Skaf |
| Support Opportunities: | Research Grants - Research, Innovation and Dissemination Centers - RIDC |
| FAPESP's process: | 21/06448-0 - High-fidelity numerical simulations applied in unsteady aerodynamics, turbulence and aeroacoustics |
| Grantee: | William Roberto Wolf |
| Support Opportunities: | Research Grants - Young Investigators Grants - Phase 2 |
| FAPESP's process: | 19/26196-5 - Large-eddy simulations of supersonic axial turbines |
| Grantee: | Hugo Felippe da Silva Lui |
| Support Opportunities: | Scholarships in Brazil - Doctorate |
| FAPESP's process: | 22/00464-6 - High-fidelity simulations and data-driven analysis of transitional and turbulent compressible flows over airfoils |
| Grantee: | Gabriel Yudi Ragni Hamada |
| Support Opportunities: | Scholarships in Brazil - Doctorate |