OMNIS™/Turbo & Agile (incl FINE™/Turbo & Agile)

Structured & Unstructured seamlessly combined

The structured Turbo solver for rotating parts Omnis™/Turbo with Omnis™/AutoGrid structured meshes, offers unsurpassed speed and accuracy.

Combined with the unstructured Omnis™/Open-DBS solver, with Omnis™/Hexpress meshes, for peripherals such as volutes, inlets, etc.. the complete application is solved using the most optimal approach for each part.

Components range from multi-stage axial to radial to mixed-flow configurations: compressors, turbines, pumps, fans, propellers, contra-rotating propellers...

KJ66 static pressure 

Turnaround time 20x faster than any other solution on the market

The Omnis/Turbo CFD solution is optimized by scaling linearly on thousands of CPU cores, as well as on GPU (the latter provides a 2,4 times speed-up vs CPU).

Combined with our patented CPUBooster™ technology, a unique convergence acceleration technique, computation time is reduced even further, by a factor 3-5.

This package renders the solution up to 20 times faster than any other solution on the market.

Cavitation inception: Left, no local refinement - Right, dynamic mesh adaptation

Full-engine 3D CFD simulation

With the purpose to meet the future requirements of aircraft engines in terms of low emissions, high reliability and efficiency, a novel highly efficient fully-coupled RANS-based approach has been developed, enabling the simulation of a full aero-engine within a single code.

One of the advantages of a fully coupled approach over a component-by-component approach, is that the boundary conditions at the interfaces do not need to be guessed.

A Smart Interface methodology ensures a direct coupling between the different engine components, compressor- combustor-turbine, and allows the CFD models to vary between each component within the same CFD code.

For the simulation of the combustion process, the Flamelet Generated Manifold (FGM) method is applied. While the approach is superior to classical tabulated chemistry approaches and reliably captures finite-rate effects, it is also computationally inexpensive.

The Nonlinear Harmonic method is used to model the unsteady interaction between the blade rows as well as the influence of the non-homogeneities at the combustor outlet on the downstream turbine blade rows. This method is 2 to 3 orders of magnitude faster than a classical URANS simulation.

Aero-Vibro-Acoustics analysis

FINE™/Acoustics is a complete simulation suite for the analysis of a broad range of industrial applications involving Acoustics, Vibro-Acoustics and Aero-Acoustics.

Simultaneous tonal noise source and propagation analysis with the Non-Linear Harmonic method (NLH).

Broadband flow-noise source reconstruction based on steady RANS. Noise propagation with Boudnary Element Method (BEM) and Finite Element Method (FEM).

Automatic pump optimization with a limited number of design iterations​

Key Features

Meanline design

For all major turbomachinery configurations. Meanline options include: 

• COMPAL® for radial and mixed-flow compressors
• PUMPAL® for radial, mixed-flow, axial pumps
• RITAL™ for radial and mixed-flow turbines
• AXIAL™ for axial compressors and turbines

Detailed 3D design

For geometry and blading using AxCent®, including throughflow, 2D blade to blade and streamline curvature calculation.

• 2D and radial blading
• Agile links to COMPAL®, PUMPAL®, RITAL™,AXIAL™, OMNIS™/Turbo, pbFEA and MAX-PAC
• Bezier-based cross-section (axial) and geometry generation (radial)
• Blade generation sheets
• Blade lean
• CAD output (IGES, STEP, ACIS, Parasolid, STL)
• Circular-arc and line segment contours
• Fillets (single-radious, variable, elliptical)
• Ideal and real fluids
• Independent hub and shroud
• Multistreamtube (MST) calculation for both compressible and incompressible flow
• Radial stacking of up to 3-cross-sections at LE, TE or CG
• Rapid loading calculation for both compressible and incompressible flow
• Single-blade raw capability
• Suitable for compressors, fans, pumps and turbines
• Swept leading and trailing edges
• Throat area calculation
• Add: BANIG
• Add: Blade stacking of 2 to unlimited number of cross sections
• Enhanced flank milling -  confirming ruled surface
• Flow cuts and trims/extensions
• Flow injection and extraction
• Inlet boundary layer calculations
• Non-axisymmetric walls
• Parameterized blade types (MCA, DCA, Pritchard, Enhanced Pritchard)
• Parameterized blade types (NACA, Constant Passage, simple airfoil)
• Simple and independently-specified splitter blades (Independent was option)
• Stacking curve adjustment in meridional and tangential directions

Omnis™/AutoGrid

Parallel Mesh Generation

• Wizard mode: optimal mesh topology based on configuration
• Advanced geometry features: blade fillets, cooling systems, axisymmetric and non-axisymmetric effects
• Advanced configurations: multistage, bulb, unshrouded and by-pass
• Automated blocking and meshing of axisymmetric effects
• Python scripting technology

Omnis™/HEXPRESS

• Full Hexahedral Grids (no prism, no tetrahedra, no pyramid)
• Direct CAD import capabilities
• CAD manipulation and decomposition tools
• Mesh wizard for rapid solution set-up and easy back and forth operation
• Buffer cell and boundary layer insertion for high quality cells in boundary layer regions
• Automatic refinement procedures based on user defined sensors either next to solid walls or at specified area in the domain
• Multi domain capabilities allowing the treatment of CHT and multi-part geometry models
• Full non-matching multi-block connection, allowing multi-row turbomachinery meshing