The IMPROVE research project comprises the numerical and experimental investigation of a disruptive novel airfoil design concept for compressor blades.

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The AKTIVER project (Active Flow control in compressor components of future Aircraft Engines) focuses on the research and design of innovative concepts for flow control in aerodynamically highly loaded intakes and compressors of future aircraft engines.

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The preliminary design of turbomachinery is a complex process. Therefore the evalution and revision of the current and development of new mechanical pre-design methods of turbine components are the main tasks of this project.

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The DRIVER project aims to explore a new design concept for highly loaded axial compressors using tandem airfoils with high flow turning and efficiency, with further new technologies to be developed to influence the flow in the endwall regions in a loss-reducing manner.

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Particle entrainment in aero-engines is unavoidable and stable operation can be compromised by impurities. The project aims are to improve the understanding of the physical flow behaviour of particle-laden flows.

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The sealing between static and rotating components in axial turbomachines in the hub area of ​​compressor stators is usually carried out with the help of an inner shroud or by using cantilevered vanes. The choice of configuration is influenced by aerodynamic, mechanical and economic factors and must therefore be assessed in a multidisciplinary environment.

You can find detailed information here.

The "RoBoFlex" project aims to investigate the manifestation of "real geometry effects" in the annulus (gaps, steps, edges, blade misalignment) under variable conditions starting from the Aerodynamic Design Pont (ADP). The qualitative and quantitative assessment of these phenomena and their influence on performance is the subject of current research.

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The aviation industry is working on increasing the efficiency of aircraft engines. One way of increasing the stage loading of turbocompressors is to use tandem blades. The aim of the project "Unsteady Tandem Flow" is to numerically and experimentally investigate the flow through tandem blades in a multistage axial compressor, whose dimensionless coefficients are representative for high-pressure compressors of aircraft engines.

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Experimental investigations on innovative blade geometries and flow treatments are carried out at the HSRC axial compressor test rig. As part of the research topic "Numerical calibration of pressure probes", a methodology is to be developed with which pressure probes can be numerically calibrated.

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Alternative fuels can be used to achieve a rapid reduction in the climate impact of aviation, In addition to electric aircraft engines or the use of hydrogen as a fuel. In the project, funded by Munich Aerospace e.V., the behavior of a small gas turbine with regard to performance, engine health, and the resulting emissions will be investigated using alternative fuels.

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Foreign Object Damage (FOD) occurs when foreign hard particles are sucked into aircraft engines during flight, posing a persistent and critical problem due to the inevitability of FOD and its associated consequences.

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The main goal of this project is the reduction of the Tip Leakage Flow impact on compressor. Tip Leakage Flow is a result of secondary flows on the rotor tip and can cause significant losses, as it curls up into a vortex, leading to passage blockage and reduction of the surge margin.

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Significant reductions in emissions and increases in efficiency are hardly possible by optimising conventional aero-engine components. Disruptive approaches for new propulsion systems are therefore necessary. The use of electrical energy promises high drive system efficiency.

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The aim of the project Hy2C is to perform a robustness study on a highly efficient tandem stage compressor , FRANCC designed at LTF. 

You can find detailed information here.