Abstract
In this work the D3Q19 Hybrid Recursive Regularized Pressure based Lattice Boltzmann Method presented by Farag et al. (2021) is assessed for the simulation of complex transonic internal flows. A Lattice Boltzmann solver presented by Jacob et al. (2018) treating the mass and momentum conservation equations is coupled with a finite volume scheme for the resolution of the conservative form of the total energy equation as shown by Zhao et al. (2020), leading to a fully numerically conservative scheme. The well documented case of the high-pressure turbine guide vane cascade with the VKI LS89 profile is examined. To the authors’ knowledge, this is the first numerical aero-thermal investigation of this configuration using a Lattice Boltzmann approach. An appropriate numerical domain along with a grid refinement technique are used to accommodate a Cartesian grid while ensuring flow periodicity downstream of the cascade in the pitch-wise direction. This is verified thanks to the time-averaged profiles of the exit isentropic Mach number and exit isentropic Reynolds number. The solid boundary is introduced in the Cartesian grid with a cut-cell immersed boundary technique where the boundary nodes of the domain are outside of the solid. An efficient treatment for these nodes is used to accurately represent the near wall flow dynamics. An explicit power-law velocity wall model is used to accurately predict the near wall velocities. A logarithmic temperature wall function is also added to this method to improve the convective heat transfer estimation on the blade surface. The results of this study are compared to experimental and numerical results found in literature, proving the LBM to be a viable approach for compressible internal flows.
