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A Framework for Applied Component Zooming in Gas Turbines
Zitatschlüssel 2019_woelki_dlrk
Autor Woelki, D. and Peitsch, D.
Seiten 490174
Jahr 2019
DOI 10.25967/490174
Ort Darmstadt, Germany
Journal Deutscher Luft- und Raumfahrtkongress
Monat 10
Notiz Technische Universität Berlin:
D. Woelki, D. Peitsch
Herausgeber Deutsche Gesellschaft für Luft- und Raumfahrt - Lilienthal-Oberth e.V.
Zusammenfassung Much of academic research on gas turbines is conducted at component level. Promising concepts such as enhanced blade design or active flow control are often investigated on isolated domains, e.g. single compressor stages. Possible interactions with adjacent components, such as effects on secondary power and air provision or the thermodynamic cycle are rarely or just subsidiary considered. Nevertheless, the early inclusion of those effects is crucial for a reliable assessment of novel concepts' benefits. For example, the reduction of aero engine component weight or the increase of turbo-component stage efficiency is intangible regarding the quantified benefit on system level. This gap can be closed by a technique called component zooming. Here, a gas turbine performance model representing the cycle and components basic interaction is coupled with more detailed models which are capable of specific investigations on component level. This paper presents a suitable architecture of frameworks for component zooming in general. In order to maintain high applicability especially for academic purposes, focus is put on flexibility in manifold sense: Adaptability to arbitrary concepts and zoomed components, expandability of available workflows, expandability to new disciplines, exchangeability of used software (e.g. commercial or in-house) and portability to common platforms. Various examples will demonstrate the capabilities of component zooming performed with such a framework. The first case discusses zooming on the secondary air system (SAS) of gas turbines. Another case demonstrates the coupling of engine performance with models for an initial assessment of aero engine components weight reduction benefit, e. g. realized by tandem blades or flow actuation in duct components. The resulting change in overall mass of the engine leads to basic, pragmatic options for aircraft operators.
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