[en] The suction side boundary layer regimes in a modern high-speed, low-pressure turbine cascade under off-design conditions are investigated using high-fidelity direct numerical simulations with the Argo DG solver on the SPLEEN C1 geometry at Rec = 70k. Three outlet Mach numbers (M a = 0.70, 0.90, 0.95) reveal a Kelvin-Helmholtz driven laminar separation
bubble with tonal noise at M a = 0.70, an acoustic interaction with the separation bubble that governs reattachment at M a = 0.90, and a shock-dominated flow with passage normal shock modulation at M = 0.95. These results show how shear layer instabilities, acoustic waves, and shocks alter the suction side boundary layer across the flight envelope of a high-speed LPT.
Lopes, Gustavo; VKI - Von Karman Institute for Fluid Dynamics > Turbomachinery Department ; University of Genova > DIME
Lavagnoli, Sergio; VKI - Von Karman Institute for Fluid Dynamics > Turbomachinery Department
Hillewaert, Koen ; Université de Liège - ULiège > Aérospatiale et Mécanique (A&M) ; Université de Liège - ULiège > Département d'aérospatiale et mécanique > Design of Turbomachines and Propulsors (DoTP) ; Cenaero
Dellacasagrande, Matteo; University of Genova > DIME
Lengani, Davide; University of Genova > DIME
Language :
English
Title :
Boundary Layer Transition Mechanisms in a High-Speed Low-Pressure Turbine Blade
