Thermal boundary condition effects on shock boundary layer interactions of a supersonic turbine cascade

Autor(es)

Hamada, Gabriel Y. R. ; Lui, Hugo F. S. ; Wolf, William R. ; Ricciardi, Tulio R. ; Junqueira-Junior, Carlos

• Tipo de documento: Artigo Científico
• Fonte: AIAA AVIATION 2023 FORUM; v. N/A, p. 9-pg., 2023-01-01.

Resumo

The effects of adiabatic and isothermal boundary conditions are investigated on the shock-boundary layer interactions (SBLIs) in a supersonic turbine cascade. Large eddy simulations (LES) are computed for an inlet Mach number of M-infinity = 2.0 and Reynolds number based on the axial chord Re = 200, 000. For the isothermal condition, 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 the boundary layer leading to a larger separation bubble. On the other hand, for the latter, a normal shock from a Mach reflection induces a small separation region near the wall. Results are presented in terms of pressure and skin friction coefficients, as well as mean velocity and temperature contours. Turbulence kinetic energy (TKE) budgets are also computed upstream and downstream of the separation regions to investigate the effects of thermal boundary conditions in the near-wall flows. Results demonstrate that the different thermal boundary conditions lead to variations in the suction side separation bubble length scales. Wall cooling causes steeper pressure variations due to deeper shock penetration on both sides of the airfoil. Moreover, the TKE budgets are considerably affected not only by the cooling but also due to pressure gradients induced by curvature effects of the blade. (AU)

• Processo FAPESP: 13/08293-7 - CECC - Centro de Engenharia e Ciências Computacionais
• Beneficiário: Munir Salomao Skaf
• Modalidade de apoio: Auxílio à Pesquisa - Centros de Pesquisa, Inovação e Difusão - CEPIDs
• Processo FAPESP: 21/06448-0 - Simulações numéricas de alta fidelidade aplicadas em aerodinâmica não-estacionária, turbulência e aeroacústica
• Beneficiário: William Roberto Wolf
• Modalidade de apoio: Auxílio à Pesquisa - Jovens Pesquisadores - Fase 2
• Processo FAPESP: 19/26196-5 - Simulações de grandes escalas de turbinas axiais supersônicas
• Beneficiário: Hugo Felippe da Silva Lui
• Modalidade de apoio: Bolsas no Brasil - Doutorado
• Processo FAPESP: 22/00464-6 - Simulações de alta fidelidade e análises baseadas em dados de escoamentos compressíveis sobre aerofólios envolvendo transição e turbulência
• Beneficiário: Gabriel Yudi Ragni Hamada
• Modalidade de apoio: Bolsas no Brasil - Doutorado