A robust reacting flow solver with detailed transport, chemistry, and steady-state preserving splitting schemes based on OpenFOAM and Cantera

2020 ◽  
Author(s):  
Dezhi Zhou ◽  
Suo Yang
Keyword(s):  
Steady State ◽  
Reacting Flow ◽  
Splitting Schemes ◽  
Flow Solver

A Hybrid Coupling Scheme and Stability Analysis for Coupled Solid/Fluid Turbine Blade Temperature Calculations

1998 ◽  
Author(s):  
Andreas Heselhaus
Keyword(s):  
Heat Conduction ◽  
Steady State ◽  
Turbine Blade ◽  
Gas Flow ◽  
Guide Vane ◽  
Thermal Design ◽  
Navier Stokes ◽  
Coupling Scheme ◽  
Flow Solver ◽  
Turbine Blade Cooling

Efficient thermal design of turbine blade cooling needs to take wall temperature effects on heat transfer into account. This can only be achieved by a coupled calculation of hot gas flow and blade heat conduction. In this paper principle and stability proof of an algorithm are presented that allows to couple a steady state finite element heat conduction solver with a blockstructured steady state finite volume (FV) Navier-Stokes time marching flow solver. The stability of the developed coupling procedure as well as the instability of an alternative algorithm is shown analytically and numerically. The benefits of coupled calculating are shown for a convectively cooled turbine guide vane blade. In the example treated, temperature differences of more than 100 K arise compared to the same calculation performed in an uncoupled way.

Applications of an Inviscid Q3D Linearized Flow Solver Towards the High Operating Line Flutter Region of a Transonic Fan

1998 ◽  
Author(s):  
Tomas J. Börjesson ◽  
Torsten H. Fransson
Keyword(s):  
Steady State ◽  
Three Dimensional ◽  
Mode Shapes ◽  
Flow Solver ◽  
Operating Line ◽  
Flutter Boundary ◽  
Euler Model ◽  
Transonic Fan ◽  
Phase Angles ◽  
Operating Points

The capabilities of an inviscid quasi three-dimensional linearized unstructured flow solver to correctly predict the stall flutter limit, flutter modes and critical inter-blade phase angles on a transonic rotating shroudless fan model where experimental data exist have been investigated. Three operating points were chosen for investigation at 70% and 95% speed. At 70% speed two points were investigated: one close to the torsional flutter boundary (at the intermediate operating line) and one at the flutter boundary. The 95% speed point was at the flexural flutter boundary. Steady state and unsteady calculations were made at several stream sections per operating point. At each stream section unsteady calculations were performed over the entire range of inter-blade phase angles with different mode shapes (real mode, rigid torsion and rigid bending) at different frequencies. Thus the model was “provoked” with “unphysical” mode shapes and frequencies to be compared to the unsteady solution obtained with the mode shapes and frequencies observed from the experiments. Furthermore all unsteady calculations were made with different mesh densities and solutions from different “tuned” and “untuned” steady-state solutions. The main conclusion of the validation of the inviscid Q3D Euler model on the Fan C Model Rotating Rig is that the model generally predicts flutter, flutter modes and the critical inter-blade phase angles to be close to the experimentally determined ones.

An Unstructured Reacting Flow Solver With Coupled Implicit Solution of the Species Conservation Equations

2008 ◽  
Author(s):  
Ankan Kumar ◽  
Sandip Mazumder
Keyword(s):  
Species Conservation ◽  
Domain Size ◽  
Reacting Flow ◽  
Computational Domain ◽  
Conservation Equations ◽  
Flow Solver ◽  
As Species ◽  
Minimum Residual ◽  
Volume Method ◽  
Coupled Solution

Many reacting flow applications mandate coupled solution of the species conservation equations. A low-memory coupled solver was developed to solve the species transport equations on an unstructured mesh with implicit spatial as well as species-to-species coupling. First, the computational domain was decomposed into sub-domains comprised of geometrically contiguous cells—a process termed internal domain decomposition (IDD). This was done using the binary spatial partitioning (BSP) algorithm. Following this step, for each sub-domain, the discretized equations were developed using the finite-volume method, written in block implicit form, and solved using an iterative solver based on Krylov sub-space iterations, i.e., the Generalized Minimum Residual (GMRES) solver. Overall (outer) iterations were then performed to treat explicitness at sub-domain interfaces and non-linearities in the governing equations. The solver is demonstrated for a laminar ethane-air flame calculation with five species and a single reaction step, and for a catalytic methane-air combustion case with 19 species and 22 reaction steps. It was found that the best performance is manifested for sub-domain size of about 1000 cells, the exact number depending on the problem at hand. The overall gain in computational efficiency was found to be a factor of 2–5 over the block Gauss-Seidel procedure.

Steady state solutions in a model reacting flow problem

1993 ◽  
Vol 48 (1-4) ◽  
pp. 273-286 ◽  
Author(s):  
J. David Logan ◽  
Thomas S. Shores
Keyword(s):  
Steady State ◽  
Flow Problem ◽  
Reacting Flow ◽  
Steady State Solutions

scholarly journals Preliminary Parameter Characterization for Numerical Optimisation of Ducted Propellers

2019 ◽  
Vol 1 (2) ◽  
pp. Manuscript
Author(s):  
Jean-Marc Laurens ◽  
Margot Remaud ◽  
Pierre-Michel Guilcher
Keyword(s):  
Steady State ◽  
Potential Flow ◽  
Steady State Flow ◽  
Flow Solver ◽  
Flow Problems ◽  
Performance Predictions ◽  
Preliminary Study ◽  
Unsteady Problems ◽  
Numerical Optimisation ◽  
Ducted Propellers

In this paper, a preliminary parameter characterization for the numerical optimisation of ducted propellers was performed. The ENSTA Bretagne in-house solver used is based on the potential flow theory. Although the potential flow solver is able to solve unsteady problems, in this preliminary study only steady state flow problems are considered. Different parameters were analysed, such as the gap between the propeller tip and the inner duct surface as well as the propeller location in the duct tube. The analyses were carried out on a standard advance coefficient range. A quick study showed that a neutral NACA profile for the duct section could provide higher performance predictions than the classical accelerating Kort nozzle 19A.

The In Situ Adaptive Tabulation (ISAT) Algorithm for Reacting Flow Computations With Complex Surface Chemistry

2013 ◽  
Author(s):  
Sandip Mazumder ◽  
Ankan Kumar
Keyword(s):  
Steady State ◽  
Surface Chemistry ◽  
Catalytic Combustion ◽  
Catalytic Converter ◽  
Differential Algebraic Equations ◽  
Heterogeneous Reactions ◽  
Reacting Flow ◽  
In Situ Adaptive Tabulation ◽  
The Impact

The In Situ Adaptive Tabulation (ISAT) procedure, originally developed for the efficient computation of homogeneous reactions in chemically reacting flows, is adapted and demonstrated for reacting flow computations with complex heterogeneous (or surface) reactions. The treatment of heterogeneous reactions within a reacting flow calculation requires solution of a set of nonlinear differential algebraic equations at boundary faces/nodes, as opposed to the solution of an initial value problem for which the original ISAT procedure was developed. The modified ISAT algorithm, referred to as ISAT-S, is coupled to a three-dimensional unstructured reacting flow solver, and strategies for maximizing efficiency without hampering accuracy and convergence are developed. These include use of multiple binary tables, use of dynamic tolerance values to control errors, and periodic deletion and/or re-creation of the binary tables. The new procedure is demonstrated for steady-state catalytic combustion of a methane-air mixture on platinum using a 24-step reaction mechanism with 19 species, and for steady-state three-way catalytic conversion using a 61-step mechanism with 34 species. Both reaction mechanisms are first tested in simple 3D channel geometry with reacting walls, and the impact of various ISAT parameters is investigated. As a final step, the catalytic combustion mechanism is demonstrated in a laboratory-scale monolithic catalytic converter geometry with 57 channels discretized using 354,300 control volumes (4.6 million unknowns). For all of the cases considered, the reduction in the time taken to perform surface chemistry calculations alone was found to be a factor of 5–11.

Numerical simulation of high speed reacting shear layers using AUSM+- up scheme-based unstructured finite volume method solver

2017 ◽  
Vol 08 (03) ◽  
pp. 1750020 ◽  
Author(s):  
M. Deepu ◽  
M. P. Dhrishit ◽  
S. Shyji
Keyword(s):  
Finite Volume ◽  
High Speed ◽  
Splitting Method ◽  
Time Integration ◽  
Chemical Species ◽  
Shear Layers ◽  
Supersonic Stream ◽  
Reacting Flow ◽  
Two Dimensional ◽  
Flow Solver

Development of an Advection Upstream Splitting Method (AUSM[Formula: see text]-up) scheme-based Unstructured Finite Volume (UFVM) solver for the simulation of two-dimensional axisymmetric/planar high speed compressible turbulent reacting shear layers is presented. The inviscid numerical flux is evaluated using AUSM[Formula: see text]-up upwind scheme. An eight-step hydrogen–oxygen finite rate chemistry model is used to model the development of chemical species in a supersonic reacting flow field. The chemical species terms are alone solved implicitly in this explicit flow solver by rescaling the equation in time. The turbulence modeling has been done using RNG-based [Formula: see text]–[Formula: see text] model. Three-stage Runge–Kutta method has been used for explicit time integration. The nonreacting two-dimensional Cartesian version of the same solver has been successfully validated against experimental and numerical results reported for the wall static pressure data in sonic slot injection to supersonic stream. Detailed validation studies for reacting flow solver has been done using experimental results reported for a coaxial supersonic combustor, in which species profile at various axial locations has been compared. Present numerical solver is useful in simulating combustors of high speed air-breathing propulsion devices.

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