As part of new aircraft engine development, fracture critical components are identified and studied. The engines turbine disks require careful consideration due to the many sharp notches into which compressor blades are inserted. These dovetail notches have varying geometries dependent upon the stage of the compressor in which the turbine disk is located, and pose a difficult problem for the fracture mechanics analyst. This paper describes the fatigue behavior of cracks located at two 'dovetail' notch geometries. Fatigue tests with transparent polymer models produced changes in crack size and shape as a function of elapsed cycles. Numerical stress intensity factor solutions were determined for both through-cracks (using a finite element code), and corner cracks (using a boundary element code) located at the notch bore. The numerical stress intensity factor solutions were verified by predicting fatigue lives, crack sizes and shapes for the experimental results. These predictions showed that the numerically determined stress intensity factors accurately predict fatigue lives, as well as crack size and shape for the dovetail geometries.
Analysis of cracks at deep notches
Analyse von Rissen an tiefen Kerben
Engineering Fracture Mechanics ; 55 , 4 ; 605-616
1996
12 Seiten, 8 Bilder, 6 Tabellen, 18 Quellen
Article (Journal)
English
Eddy current standards. Cracks versus notches
Tema Archive | 1992
|NDT comparisons of in-service cracks, manufactured cracks and EDM notches
Tema Archive | 2007
|The stress intensity factor of small cracks at notches
TIBKAT | 1981
|Cracking-resistance diagrams of bodies with notches and cracks
British Library Online Contents | 2004
|Weight functions, CTOD, and related solutions for cracks at notches
Tema Archive | 2004
|