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Research ane Development
Adjoint Flow Solver
The adjoint method allows the computation of sensitivities (derivatives) of flow variables or quantities derived from them with respect to geometrical parameters. This is more efficient than the direct computation of derivatives from flow solutions, e.g. by finite differences, if the number of parameters is large compared to the number of objective functionals.
Multi Domain Methods
In the design process of turbomachinery special components like casing treatments and coolant channels are used to enhance its efficiency and performance. In recent years, further developments in the computer technology have led to advanced CFD codes like TRACE being able to analyze complex three-dimensional flow behavior of such complex geometries.
Turbulence & Transition
Virtually all turbomachinery flows involve turbulent phenomena, including transition from laminar to turbulent states. Thus, the adequate representation of transition and turbulence is crucial for the predictive accuracy of thecomputational method used in the turbomachinery design process.
The Combustion Group has been created in 2009 in the Numerical Methods Department with the objective of expanding the multi-physics capabilities of TRACE and carry out advanced research in the development and implementation of state-of-the-art combustion models for RANS/LES simulations in multi-component configurations, in close cooperation with industrial and academic partners.
High order methods
Due to the relative motion between adjacent blade rows the aerodynamic flow fields in turbomachinery are inherently unsteady. On the other hand these flows are also highly three-dimensional. However the modern design process of turbomachinery components relies primarily on steady-state numerical simulations with simplified assumptions and modeling, which severely limit the potential of improvements. In order to identify the remaining options for design improvements and also to be able to fully exploit future computational resources, efficient time integration schemes and and space discretization with high order methods are required. Currently numerical algorithms of second-order accuracy are typically employed in the simulation of turbomachinery flows.
The understanding of aero- and thermodynamics of the turbine is of essential relevance for the design of blade cooling methods. A state the art heat transfer modelling is under development in TRACE to improve the prediction accuracy of the behaviour of thermal and momentum boundary layers.
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