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R. Berger, T. Rogge, R. Rolfes
This paper presents the development and results of modeling turbine blades of aircraft engines with manufacturing imperfections. Approaches are presented that provide a fast analysis of the structure including varying geometrical properties. In particular the starting dynamics and the lifetime are investigated. Resonance conditions during run-up of the aeroengine are identified and the vibration characteristics are analyzed. Maximum vibration amplitudes are determined by superposition of partial frequency responses by linear weighting functions. The estimation of lifetime is based on a semi-analytical approach. Assuming a quasistable condition the stresses and the corresponding damage can be analyzed analytically. The damage of the structure caused by fatigue and creep is described by a linear damage accumulation according to Palmgren-Miner and Robinson. Geometrical imperfections are incorporated within a pre-processing routine using Principal Component Analysis. The influence of the scattered parameters on the structural properties is evaluated including probabilistic analysis. The application of the methods on a turbine blade of an air-turbine shows that the characteristic structural properties are captured sufficiently accurately.
Deutscher Luft- und Raumfahrtkongress 2016, Braunschweig
Deutsche Gesellschaft für Luft- und Raumfahrt - Lilienthal-Oberth e.V., Bonn, 2016
21,0 x 29,7 cm, 5 Seiten
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