T. Immery, M. Schnös, M. Vieweg, E. Nicke

The geared turbofan aircraft engine is an efficient type of aircraft engine. By using a gearbox, the fan can run at a different rotational speed in comparison to the shaft connecting low pressure compressor and turbine. To assess the in-house tools for preliminary design, a geared turbofan, with the same requirements as the Pratt&Whitney 1000G, is designed, including thermodynamic cycle, turbine, compressor, burner and structural mechanics. The goal of this study is the design of the compression system, composed of the low-pressure compressor, the inter-compressor duct and the high-pressure compressor. The following steps have been carried out to design the compression system: first, a preliminary design of both compressors is realized, following by a detailed design, conducted with throughflow calculations and the use of a database of optimal airfoils [1]. Three stages have been chosen for the low-pressure compressor and eight stages for the high-pressure compressor. In order to reach the target conditions for all operating points from the specifications, the schedule for the variable guide vanes has also been decided on. The final design is validated with 3D CFD calculations. Additionally, the interaction of the inter-compressor duct with the low-pressure and the highpressure compressor is investigated.

Deutscher Luft- und Raumfahrtkongress 2018, Friedrichshafen

Deutsche Gesellschaft für Luft- und Raumfahrt - Lilienthal-Oberth e.V., Bonn, 2018

Conference Paper

englisch

21,0 x 29,7 cm, 9 Seiten

urn:nbn:de:101:1-2018100815325763563810

10.25967/480126

Design, Compressor

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Immery, T.; Schnös, M.; et al. (2018): Design of the Compression System of a Geared Turbofan. Deutsche Gesellschaft für Luft- und Raumfahrt - Lilienthal-Obert e.V.. (Text). https://doi.org/10.25967/480126. urn:nbn:de:101:1-2018100815325763563810.

08.10.2018