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Organisationseinheit der BAM
- 9 Komponentensicherheit (52)
- 9.4 Integrität von Schweißverbindungen (49)
- 9.0 Abteilungsleitung und andere (7)
- 5 Werkstofftechnik (6)
- 5.1 Mikrostruktur Design und Degradation (5)
- 9.6 Additive Fertigung metallischer Komponenten (5)
- 8 Zerstörungsfreie Prüfung (3)
- 8.5 Röntgenbildgebung (3)
- 4 Material und Umwelt (2)
- 9.3 Schweißtechnische Fertigungsverfahren (2)
Paper des Monats
- ja (1)
Eingeladener Vortrag
- nein (40)
The knowledge of fatigue crack propagation data in terms of their effective values is important for a conservative and safe life assessment of components subjected to cyclic loading. To overcome issues related to the precise consideration of the crack-closure effects on experimental data obtained at small R ratios, closure-free data have been obtained at R ≈ 0.8 by different experimental procedures. The statistical analysis of the intrinsic fatigue crack propagation threshold obtained experimentally has shown a small data scatter and good agreement between procedures. When compared with effective values obtained from analytical corrections of closure-affected data, the data obtained at R ≈ 0.8 should lead to a conservative life estimation.
Die Anwendung bruchmechanischer Methoden zur schadenstoleranten Bauteilauslegung ist für zyklische Lasten im Bereich der Paris-Geraden Stand der Technik. Technisch relevant sind jedoch häufig geringere Lasten im Schwellenwertbereich der d𝑎/d𝑁-Δ𝐾-Kurve. Aufgrund des großen Einflusses von Rissschließeffekten ist dessen Bestimmung jedoch nicht nur aufwändig, sondern auch potenziell fehlerbehaftet. Die Bauteilauslegung erfolgt zweckmäßigerweise auf der Basis effektiver, d. h. rissschließkorrigierter Rissfortschrittsdaten. Von großer Bedeutung ist auch der intrinsische Schwellenwert, unterhalb dessen keine Risserweiterung mehr eintritt. In diesem Forschungsprojekt erfolgte eine Untersuchung des Einflusses verschiedener Prüfverfahren und Umgebungsbedingungen auf die Ermittlung des Schwellenwerts gegen Ermüdungsrissausbreitung Δ𝐾th. Es wurden statistisch abgesicherte Empfehlungen zur experimentellen Ermittlung des intrinsischen Schwellenwerts Δ𝐾th,eff abgeleitet. Dieser dient auch als Eingangsparameter einer weiterentwickelten Prozedur zur Bauteilauslegung auf der Basis bei einem Lastverhältnis von 𝑅 ≈ 0,8 ermittelter, effektiver, Rissfortschrittsdaten. Es zeigte sich, dass die bei einem Lastverhältnis von 𝑅 ≈ 0,8 in Laborluft bei höherer Prüffrequenzen (≥90 Hz) ermittelten Schwellenwerte eine konservative Abschätzung des intrinsischen Schwellenwerts erlaubten. Bei Lastverhältnissen 𝑅 ≪ 0,8 wurde ein teilweise stark ausgeprägter Einfluss extrinsischer Effekte auf das Rissfortschrittsverhalten festgestellt. Eine Untersuchung der Bruchflächen ergab Oxidschichtdicken in der Größenordnung mehrerer hundert Nanometer. Bei Reduktion der Prüffrequenz auf ≈55 Hz und Prüfung in feuchter Luft (60 % r.F. und 80 % r.F.) konnte auch bei 𝑅 = 0,8 Rissschließen beobachtet werden. Die weiterentwickelte Prozedur zur Bauteilauslegung auf Basis effektiver Rissfortschrittsdaten lieferte aber stets konservative Ergebnisse in einem tolerierbaren Fehlerbereich und ist deshalb zur Anwendung geeignet. Die im Projekt gewonnenen Erkenntnisse tragen zu einer robusten Bauteilauslegung auf bruchmechanischer Basis bei. Der stark reduzierte Versuchsumfang bei Nutzung effektiver Rissfortschrittsdaten gegenüber der Ermittlung von spannungsverhältnisabhängigen Rissfortschrittskurven beschleunigt und vereinfacht die Bauteilauslegung auf Basis bruchmechanischer Methoden.
Aero-engine turbine disks are safety-relevant components which are operated under high thermal and mechanical stress conditions. The actual part qualification and certification procedures make use of spin-tests conducted on production-similar disks. The aim of this work is to present part of a fracture mechanics-based procedure under development which aims at replacing the tests on production-similar disks with lab tests on fracture mechanics specimens. The finite element simulation of the cracked disk considers the real thermal and mechanical loading conditions. In order to design a lab representative specimen, beside the crack driving force, expressed in terms of 𝐽-integral, also the constraint to plastic deformation e.g., stress triaxiality, at the crack-tip must be similar for the same crack in the specimen and in the disk. This has been achieved and as expected, both the highest 𝐽 -integral and constraint factor are calculated at the same location along the crack front for both disk and specimen. The results of the structural integrity assessment in the form of a Failure Assessment Diagram (FAD) show good agreement between designed specimen and disk both in terms of expected failure mode and value of the critical speed. In addition, probabilistic aspects are also considered in the calculations.
This third part of the review on defects as root cause of fatigue failure addresses cavities (pores, micro-shrinkages, unmelted regions), defective microstructures and microcracks as material defects and defects due to local damage during manufacturing, service and maintenance such as dents, scratches and localized corrosion. In addition, damage due to contact fatigue and the effect of surface roughness are discussed in the context of fatigue failure. Also addressed is the competition between different kinds of defects in controlling the initiation and early growth of fatigue cracks.
According to the definition of the ASM handbook [1,3], a defect is "an imperfection. that can be shown to cause failure by a quantitative analysis and that would not have occurred in the absence of the imperfection". The topic of the present three-part review is a discussion of defects which can cause failure in cyclically loaded structures. The features discussed comprise material defects such as non-metallic inclusions, pores or micro-shrinkages, etc. and geometric defects such as surface roughness and secondary notches which have their origin in manufacturing, and defects such as surface damage due to scratches, impact events or contact fatigue as well as corrosion pits which arise in service. In this first part, the discussion is prefaced by an introduction to basic aspects which are essential for a deeper understanding of the characteristics and mechanisms how the defects influence fatigue crack initiation and propagation. These include the life cycle of a fatigue crack from initiation up to fracture, crack arrest, multiple crack initiation and coalescence, and the material and geometrical properties affecting these.
Defects as a root cause of fatigue failure of metallic components. II: Non-metallic inclusions
(2019)
This second part of the review on defects as root cause of fatigue failure comprises the origin, the nature and the effects of non-metallic inclusions. Topics addressed are the different kinds of inclusions formed during the manufacturing process, various types of mis-match causing local stresses and, as a consequence, fatigue crack initiation, and effects of characteristics such as size, morphology, localization, spatial distribution and orientation of the defects on the fatigue behavior. Methods for inclusion counting and sizing are discussed along with statistical aspects necessary to be considered when evaluating structural components.
The Topic of the presentationis a discussion on defects which can cause failure in cyclically loaded metallic components. Although also touching Features such as material defects such as pores or micro-shrinkages, etc. and geometric defects such as surface roughness and secondary notches (which are not considered in the design process) which origin in manufacturing, and others the presentation concentrates on non-metallic inclusions. It is prefaced by an introduction to the life cycle of a fatigue crack from initiation up to fracture. Special emphasis is put on the fact that only cracks which are not arrested during one of their distinct Propagation stages can grow to a critical size.