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A Holistic Approach for the Generic Preliminary Design of Axial Compressor and Turbine Annulus Contours

  • 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.

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Metadaten
Author: Marcel MischkeORCiD, Michael Pohl, Klaus HöschlerGND, André Huppertz
URN:urn:nbn:de:101:1-2020121112463561159960
URL:https://publikationen.dglr.de/?tx_dglrpublications_pi1%5bdocument_id%5d=530097
DOI:https://doi.org/https://doi.org/10.25967/530097
Title of the source (English):Conference Paper of the DLRK 2020
Publisher:Deutsche Gesellschaft für Luft- und Raumfahrt - Lilienthal-Oberth e.V.
Place of publication:Bonn
Document Type:Conference publication peer-reviewed
Language:English
Year of publication:2020
Tag:Gas Path; Annulus Contour; Generic Preliminary Design; Turbine; Compressor
Volume/Year:Deutscher Luft- und Raumfahrtkongress 2020
Number of pages:12
Article number:530097
Faculty/Chair:Fakultät 3 Maschinenbau, Elektro- und Energiesysteme / FG Flug-Triebwerksdesign
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