Characterization of boundary layers on isothermal and adiabatic curved surfaces of a supersonic turbine cascade

Autor(es)

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

• Tipo de documento: Artigo Científico
• Fonte: AIAA AVIATION FORUM AND ASCEND 2024; v. N/A, p. 12-pg., 2024-01-01.

Resumo

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)

• 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