You are here:
Fan and Compressor
Service & Links
Combustor and turbine of a turbomachine are exposed to particularly high gas temperatures. The Heat Transfer design is concerned with determining metal temperatures. High accuracy knowledge of metal temperatures is crucial for the cooling design as well as the choice of an appropriate material.
Hybrid Structured-Unstructured U-RANS Solver
At present, most components in regular shape can be meshed with high-quality structured grids. However, the generation of structured grids is very difficult for some parts or areas, such as casing treatments or coolant channels, even if multi-block topologies are applied. This problem can be alleviated remarkably if a CFD solver allows using any type of grid topology. The grid may consist of structured or unstructured blocks entirely or even a so-called hybrid structured-unstructured grid topology. The word hybrid implies here a combination of structured and unstructured grids, both of which are used to respectively discretize a portion of the flow domain where appropriate.
In order to find optimized turbomachinery components, the flow solver TRACE is used as a aerodynamic evaluation tool, inside the optimization toolkit AutoOpti.
Aerodymics forms the basis of all turbomachine research fields such as aeroacoustics, aeroelasticity, heat transfer (fluid – solid walls) as well as combustion. The main goal of aerodynamic analysis is to establish the steady-state (time-mean) or unsteady 3D flow field inside all turbomachine components (compressor, turbine, combustion chamber, ducts, cavities, seals).
The calculation of noise generation and propagation of the basic equations in a realistic three-dimensional configuration is a computationally intensive endeavor. As in all computational aeroacoustic applications (CAA), one must pay particular attention to ensure adequate spatial and temporal resolution of the low-amplitude acoustic waves. Actual wave propagation characteristics as well as mesh and time step size requirements of the TRACE code have been established in earlier studies.
DLR-Institute of Propulsion Technology-Engine Acoustics Department
DLR-Institut für Lufttransportsysteme
Copyright © 2013 German Aerospace Center (DLR). All rights reserved.