To support the task of improving the efficiency in turbomachinery CFD is applied to calculate the flow
through thermal turbomachinery. The flow analysis shall help to reduce the losses inside the blade
passages as well as in all flow guiding parts. For this purpose several self-developed and commercial
CFD codes are in use.
Developed at the Institute for Thermal Turbomachinery and Machine Dynamics. The code is written in the
object orientated programming language C++ and hence its easy to maintain or to implement new
objects, for e.q. new boundary conditions or turbulence models.
The main features of the code are:
structured grids in multiblock alignment
finite volume spatial high order upwind scheme
high order discretization in time
fully implicit treatment of the equation system (ADI) with multigrid techniques (FAS)
various eddy viscosity turbulence models
nonreflecting boundary conditions
phase lagged boundary conditions for unequal blade counts in stage calculations
Developed at European Center for Research and Advanced Training in Scientific Computation,
Developed at the Institute of Propulsion Technology,
more information (english):
more information (german):
Roe2D and Roe3D:
Predecesor of LINARS, developed at the Institute for Thermal Turbomachinery and Machine Dynamics.
Fully implicit time-marching Navier-Stokes solver using a cell-centered finite-volume scheme. It is able
to consider multi-block grids, moving grids and rotor-stator interaction.
Solver for Unsteady CAScade flows (code developed at the Institute for Thermal
Turbomachinery and Machine Dynamics), Thin-layer Reynolds-averaged Navier-Stokes code using a
third-order accurate, upwind-biased Osher scheme. The algebraic Baldwin-Lomax and the one-equation
Baldwin-Barth turbulence model are implemented together with different models for laminar-turbulent transition.
Moving and deforming grids for aeroelasticity investigations can be considered.