Turbulent separated inert and reactive flows over a triangular bluff body

Application Challenge AC2-12 © copyright ERCOFTAC 2019

CFD Simulations

Overview of CFD simulations

A series of numerical simulations was undertaken to study both inert and reactive flow over a the triangular bluff-body in order to replicate the experimental data and assess the different approaches and turbulence and combustion models [4,11]. The conventional Reynolds-averaged approach (RANS) with a family of the Launder-Sharma and realizable k-ε models has been used to calculate the non reactive flow. The details of the calculation approaches are described in [4,11]

A lean premixed propane/air bluff-body stabilized flame (Volvo test rig) was calculated using the Scale-Adaptive Simulation method (SAS) and Large-Eddy simulations (LES) as well as the conventional and unsteady Reynolds-averaged approach (RANS/URANS). RANS and SAS were closed by the standard k-ε and the k-ω Shear Stress Transport (SST) turbulence models, respectively. The conventional Smagorinsky and the k-equation sub-grid scale models were used for the LES closure. Effects of the sub-grid scalar flux modeling using the classical gradient hypothesis and Clark’s tensor diffusivity closures both for the inert and reactive LES flows are discussed. The Eddy Dissipation Concept (EDC) was used for the turbulence-chemistry interaction. Additionally, several RANS calculations were performed using the Turbulence Flame Speed Closure (TFC) model in Ansys Fluent to assess effects of the heat losses by modeling the conjugate heat transfer (hereafter CHT) between the bluff-body and the reactive flow. Also, the numerical results published by Ma et al. [12] and Jones et al. [13] are briefly discussed in the Best Practice Advise Section. Effects of the turbulent Schmidt number on the RAS results were discussed as well. Numerical results are compared with available experimental data. Reasonable consistency between experimental data and numerical results provided by RANS/URANS, SAS and LES was observed. In general, there is satisfactory agreement between present LES-EDC simulations, numerical results by other authors and measurements without requiring any major modification to the EDC closure constants, which gives a quite reasonable indication of the adequacy and accuracy of the method and its further application in turbulent premixed combustion simulations.

Effects of the turbulent Schmidt number on the RAS results were discussed as well. Numerical results are compared with available experimental data. Reasonable consistency between experimental data and numerical results provided by RANS/URANS, SAS and LES was observed. In general, there is satisfactory agreement between present LES-EDC simulations, numerical results by other authors and measurements without requiring any major modification to the EDC closure constants, which gives a quite reasonable indication of the adequacy and accuracy of the method and its further application in turbulent premixed combustion simulations.

Solution strategy

The calculations reported herein were performed using the finite-volume method implemented both in the commercial Ansys Fluent (AF hereafter) [15] and the open source OpenFOAM (OF hereafter) [16] (edcPisoFoam [12]) CFD codes. In the present study the RANS/URANS, SAS and LES approaches were used. It is worth noting that RANS results were obtained by AF, while URANS, SAS and LES results were obtained by OF.

Ansys Fluent

Using the factorized finite-volume method, the steady, incompressible Navier-Stokes equations were solved with a scheme-of second-order accuracy in space and time. The velocity and pressure fields were matched with a centered computational template based on the SIMPLEC algorithm within the spirit of Rhie and Chou. The convective terms were represented according to the second-order upwind scheme (SOU).

OpenFoam

The numerical method had second-order accuracy in space and time. The linear-upwind interpolation scheme (SOU) and linear (second-order central differences, CDS-2) interpolation were applied for approximating convective terms and other spatial derivatives, respectively, for the URANS) calculations. For the Scale-Adaptive and Large-Eddy simulations, the total variation diminishing (TVD) and normalized variable (NVD) schemes were used for the scalars to avoid unphysical overshoots and second law violations. A second-order implicit Euler method (BDF-2) was used for time integration together with the dynamic adjustable time stepping technique to guarantee a local Courant number less than 0.75 for URANS, SAS and LES.

To calculate the species reaction rate for each computational cell in the domain the robust LSODA algorithm [17] was used. Some results of the detailed validation and verification study of the new integrator were provided in Appendix A of Ref. [12]. The relative tolerance, absolute tolerance and maximum number of iterations to meet the target accuracy were set to 10−5, 10−5 and 103, respectively.

Computational domain

The RANS/URANS grid

RANS/URANS calculations were performed for two-dimensional (2D) configurations only. The two-dimensional computational domain is presented in Fig. 7 and consisted of an inlet buffer domain (size of 0.2 m × 0.24 m) and a channel passage (size of 1.5 m × 0.12 m). It was decided to attach an inlet buffer domain to the main computational area, allowing the inlet velocity and temperature profiles to form implicitly during computations [11]. The integration domain was split into three blocks to generate a high-quality unstructured quad/triangular mesh: – the inlet buffer and a part of the channel without bluff-body. The channel part was resolved with 135 and 45 nodes in the horizontal and vertical directions, respectively, with exponential refinement of cells toward the bluff body; – the central part of the channel passage with size of 0.2 m × 0.12 m, including the obstacle, as described in Fig. 7a. The bluff body sides contained 90 grid points, while the horizontal and vertical sides of the domain were resolved with 75 and 45 nodes, respectively, to obtain smooth mesh transition toward the flame holder; – the remaining downstream part of the channel with resolution of 135 and 45 nodes in the horizontal and vertical directions, respectively, with exponential decreasing of nodes toward the outlet. The viscous boundary layers were attached to the obstacle and the channel walls. The first element length, the growth factor and the total number of rows were set to 10−5 m, 1.2 and 11, respectively, for the triangular cylinder and 5×10−4 m, 1.2 and 5, respectively, for the channel walls. The distribution of the non-dimensional distance to the wall y∗ was about 1 both for the obstacle and the channel walls. Hereafter, this grid has label M1.

Contributed by: D.A. Lysenko and M. Donskov — 3DMSimtek AS, Sandnes, Norway