The Combustor department investigates reacting flows in jet engine and gas turbine combustors. In cooperation with industrial and academic partners, laser-optical measurement techniques are used to characterise the reacting flow field in realistic combustion chamber configurations and test conditions.
In addition, numerical simulation methods for reacting flows are developed.
Both experimental and numerical investigations contribute to the development of innovative, highly efficient and low-emission combustor configurations.
With the unique test beds operated by the Combustor testing department , the Institute of Propulsion Technology provides internal and first of all external partners the opportunity of testing gas turbine combustion systems for both aero and heavy duty applications under realistic conditions. Most operational parameters can be freely adjusted without the dependency on the operational envelope of the actual engine.
The research topics of the project group are transonic axial and radial compressors and the interdisciplinary, automated design. Included are projects regarding the low noise fan, low pressure compressor with very high pressure ratio and highly loaded axial and radial compressors.
3D design methods taking into account aerodynamic, aeroacoustic and aeroelastic boundary conditions are developed and experimentally verified.
The section Engine performs modelling of the individual components of gas turbine engines and of their interactions in the frame of the whole engine, as well as of the interdependencies of aircraft and engines during all stages of operation. Analysing and modelling the emission behaviour of aircraft and engines on this basis is another focal point of the section's work.