Abstract
The formation and the interaction of inlet distortions is a safety risk in the operation of an aircraft engine. The numerical simulation of an aircraft, including the engine nacelle and the turbo-machine inside, is not possible during the design process as it is too time-consuming. To gain insight into the effects, and the impact on the engine, in particular, experiments are necessary. Due to the complexity of generating and measuring distortion patterns screens are usually used. The screens generate a total pressure drop that is constant in space and time. In this paper the interaction of a transonic compressor stage with two complex, but more realistic distortion patterns is investigated. A delta wing represents a longitudinal vortex, which is representative of e.g. a ground vortex. A stalled engine inlet is modelled by a bevelled beam that generates a massive separation bubble, which is ingested into the rotor. The interaction of the distortion and the compressor is measured at different speeds and operating points. The influence of the delta wing seems small and is difficult to measure due to the small size of the distorted area. In contrast, the beam causes a global alteration of the flow. It changes the behaviour of the rotor around the whole circumference and along the whole span.
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Wartzek, F., Holzinger, F., Brandstetter, C., Schiffer, HP. (2016). Realistic Inlet Distortion Patterns Interacting with a Transonic Compressor Stage. In: Radespiel, R., Niehuis, R., Kroll, N., Behrends, K. (eds) Advances in Simulation of Wing and Nacelle Stall. FOR 1066 2014. Notes on Numerical Fluid Mechanics and Multidisciplinary Design, vol 131. Springer, Cham. https://doi.org/10.1007/978-3-319-21127-5_17
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DOI: https://doi.org/10.1007/978-3-319-21127-5_17
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