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Investigation and Maintaining the Flow Stability in a Compressor Exposed to Novel Fuel Burning Technologies

Lupe [1]

In order to significantly reduce the fuel consumption of future aircraft engines, revolutionary technologies must be applied. The TREVAP joint project investigates and evaluates novel concepts for future turbofan aircraft engines based on thermodynmic cycles that could not be implemented so far. The project thus follows the goals for reducing emissions formulated in the European strategy document "Flightpath 2050". In particular, concepts for pressure gain combustion are being investigated. For this purpose, a hybrid concept with piston components and a pressure gain combustion based upon a Wave Rotor Combustor (WRC) are being analyzed. The hybrid concept provides for a piston compressor instead of the conventional high-pressure compressor while the geometry of the combustion chamber remains unchanged. The use of a free piston leads to a cyclic compression of the air coming from the low pressure compressor. In contrast, the WRC replaces the conventional combustion chamber. The unsteady flow stems from the periodic, rapid opening and closing of the rotating combustion chambers. Both concepts influence the pressure field at the compressor outlet especially the compressor flow in the last stages.

At the Chair for Aero Engines the effect of both pressure gain combustion concepts on the performance and especially the operation of a multi-stage compressor is being investigated. Furthermore, possibilities to stabilize the flow under given boundary conditions are shown and evaluated. For this purpose, transient flow simulations are carried out and the effect of pressure gain combustion is mapped using an appropriate boundary condition at the compressor outlet.

The research project is funded by the Federal Ministry for Economic Affairs and Energy.

Person of contact: Niklas Kolb (M.Sc.)

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