Code Leo

leoiconAt the heart of our solution is Code Leo, a high performance generalized flow solver. Featuring a cell-vertex finite volume procedure for efficient and accurate approximation and an advanced multi-grid residual propagation scheme for rapid convergence, Code Leo enables real world 3D unsteady simulations to be conducted an order of magnitude faster than existing solutions, with excellent predictive accuracy across a wide range of conditions. Designed to scale from simple 2D cascades to complex, 3D multi-stage time accurate simulations, Code Leo sets a new standard for predictive accuracy, robustness and speed.

Code Leo is designed to:

  • Cover a large range of Mach numbers (Low speed,  Transonic speed, and Supersonic speed)
  • Handle either steady or time accurate flow simulations
  • Use unstructured mesh to cover complex flow configurations of structured and unstructured meshes
  • Support multi-block code for flexibility to patch together complex geometries 

Deliver high numerical accuracy due to

  • The use of cell vertices finite volume approximation to the governing equations
  • Low artificial numerical damping

Deliver fast convergence through

  • Local time step
  • Convergence Acceleration Technique of Residual Propagation for unstructured mesh and Multi-grid scheme for structured mesh
  • Pre-conditioning with gauge pressure to speed up convergence for  low speed flow problem
  • Dual time stepping for fast time accurate simulations

Accommodate variable specific gas properties for  air or combustion products through table look up

Support a 2-equation turbulence model

  • k-w model of Wilcox¬ís 98 version with transition and surface roughness
  • Choice of wall function or wall integration
  • Constant wall temperature or constant heat flux condition for heat transfer computation

Solve additional convection-diffusion equations for multi-specie tracking

Work with either

  • Cartesian coordinates with translation wall or
  • Cylindrical coordinates with rotation for rotating machinery applications

Provide advanced capabilities for turbomachinery applications, including:

  • Non-reflective boundary conditions for both upstream and down-stream
  • Radial equilibrium exit pressure condition 
  • Cavity Model and Actuator Disc Model
  • Inlet boundary profile and exit static pressure profile
  • Mixing Plane method for steady multistage flow simulation
  • Sliding Boundary method for time accurate simulation of Rotor-Stator interaction
  • Ability to introduce film cooling air
  • Machine performance through post processing
  • 2D simulations with height ratio for design use 

Support efficient, large scale flow simulation through slave-based parallel computing, using standard MPI routines from Argonne National Laboratory

orangeplayVisit ADS University for a video tutorial on Code Leo