The NASA Rotor 37 is an isolated transonic axial compressor rotor. This case was initially included in a wider research program to cover a range of design parameters typical of high pressure compressor inlet stage of aircraft engines. Most numerical studies fail at predicting with accuracy the overall performance, e.g., the adiabatic efficiency and the losses distribution downstream of the blade. This case presents indeed several phenomena which are challenging to capture: laminar-to-turbulent transition on the blade, interaction of the boundary layer with the shock, secondary and tip-leakage flows. If LES appears a more adequate tool than RANS to predict such inherently unsteady phenomena, it remains delicate, especially because wall modeling is required. This section presents results obtained by Safran and UniBG of WMLES using the Discontinuous Galerkin approach.
NASA Rotor 37
Ghidoni A.
2021-01-01
Abstract
The NASA Rotor 37 is an isolated transonic axial compressor rotor. This case was initially included in a wider research program to cover a range of design parameters typical of high pressure compressor inlet stage of aircraft engines. Most numerical studies fail at predicting with accuracy the overall performance, e.g., the adiabatic efficiency and the losses distribution downstream of the blade. This case presents indeed several phenomena which are challenging to capture: laminar-to-turbulent transition on the blade, interaction of the boundary layer with the shock, secondary and tip-leakage flows. If LES appears a more adequate tool than RANS to predict such inherently unsteady phenomena, it remains delicate, especially because wall modeling is required. This section presents results obtained by Safran and UniBG of WMLES using the Discontinuous Galerkin approach.I documenti in IRIS sono protetti da copyright e tutti i diritti sono riservati, salvo diversa indicazione.
