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J. Rendle, S. Staudacher
The aviation industry and air traffic have been growing constantly for the last decades and an end of this trend is not predicted for the next decades. As a result of this the pressure on aero engine manufacturers is increasing to evaluate life-cycle related costs of future products as early as possible. One aspect of this is the assemblability of the product which is initially assembled at the OEM's production facility but later on it is also subject to Maintenance, Repair and Overhaul activities. Since assemblability has a significant influence on life-cycle-related cost a systematic method for the evaluation of assemblability during preliminary design is proposed in this paper. The developed method considers the boundary conditions that are necessary to evaluate the assemblability of an aero engine during preliminary design, which only exists at a low level of detail in this phase. The method considers requirements of the preliminary design concept, the assembly process, and the assembly system in order to derive characteristic inter-dependencies and assembly time allocations of the chosen concept. Subsequently, the developed method will be applied to a Low Pressure Turbine module to discuss the effect of the Level of Detail on the assembly time estimation.
Deutscher Luft- und Raumfahrtkongress 2015, Rostock
Deutsche Gesellschaft für Luft- und Raumfahrt - Lilienthal-Oberth e.V., Bonn, 2015
21,0 x 29,7 cm, 8 Seiten
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