engleski

Damage Tolerant Design of the Aircraft Components

The closed form expression for estimation of the crack initiation life at combined HCF/LCF loading is derived in this paper, and the way of reshaping the crack growth rate formulae in the form enabling their use in fatigue design at non-stationary loading is demonstrated. This new derived formula suggests an additional damage increase when crossing from one stress block to another. So, fatigue design becomes more conservative, broaching the subject of reliability of recent fatigue assessment of the components under variable amplitude loading. Herein, the reshaped crack growth rate formula is applied for the fatigue design of aircraft components made of titanium alloy Ti-6Al-4V and subjected to combined HCF/LCF loading.

Crack initiation ; reshaping crack growth rate formulae ; Block crossing effect

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