SYMPOSIA PAPER Published: 01 January 2003

Evaluating Fatigue Life of Compressor Dovetails by Using Stress Singularity Parameters at the Contact Edge


Fretting fatigue life of compressor dovetail for gas turbine was investigated using stress singularity theory. It is found that the crack initiation of fretting fatigue between blade dovetail and wheel dovetail occurs at the contact edge of blade dovetail. The parameters of stress singularity obtained from maximum principal stress distribution are capable to evaluate the fretting fatigue strength with the cyclic load having a constant angle against the contact surface under a variable contact pressure. The ratio of between the intensity range of stress singularity and the critical intensity range of stress singularity, Δ Hl/Δ Hc, is an effective parameter to predict the fretting fatigue life of compressor dovetail.

Author Information

Yoshimura, T
Hitachi, Ltd., Ibaraki, Japan
Machida, T
Hitachi, Ltd., Ibaraki, Japan
Hattori, T
Hitachi, Ltd., Ibaraki, Japan
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Developed by Committee: E08
Pages: 423–433
DOI: 10.1520/STP10774S
ISBN-EB: 978-0-8031-5476-6
ISBN-13: 978-0-8031-3456-0