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Autor(en):
M. Mischke, M. Pohl, K. Höschler, A. Huppertz
Zusammenfassung:
An essential aspect in the whole engine modelling of modern aircraft engines is the preliminary design of the meridional gas path definition. Especially the annulus dimensioning and topological characterisation of engine core subsystems are usually time-consuming. This paper presents a holistic and parametric approach to predesign the geometric 2D annulus contours of compressor and turbine subsystems without complex thermodynamic calculations. It is based on distribution functions of the axial and radial dimensions, as well as the variations of compressor and turbine stages and realises a time-efficient re-dimensioning and topological variation of the complex annulus geometry. Parametric methods for an optimised arrangement of the blade stages in a turbomachinery subsystem configuration are shown and integrated into a mathematical model.
Veranstaltung:
Deutscher Luft- und Raumfahrtkongress 2020
Verlag, Ort:
Deutsche Gesellschaft für Luft- und Raumfahrt - Lilienthal-Oberth e.V., Bonn, 2020
Medientyp:
Conference Paper
Sprache:
englisch
Format:
21,0 x 29,7 cm, 12 Seiten
URN:
urn:nbn:de:101:1-2020121112463561159960
DOI:
10.25967/530097
Stichworte zum Inhalt:
Gas Path, Annulus Contour, Generic Preliminary Design, Turbine, Compressor
Verfügbarkeit:
Kommentar:
Zitierform:
Mischke, M.; Pohl, M.; et al. (2020): A Holistic Approach for the Generic Preliminary Design of Axial Compressor and Turbine Annulus Contours. Deutsche Gesellschaft für Luft- und Raumfahrt - Lilienthal-Oberth e.V.. (Text). https://doi.org/10.25967/530097. urn:nbn:de:101:1-2020121112463561159960.
Veröffentlicht am:
11.12.2020