The objective of this paper is to examine fretting fatigue of laser shock peened (LSP) titanium to quantify the influence of LSP on fretting fatigue life. Contact conditions such as loads and pad geometry are chosen to generate fretting fatigue stresses similar to those occurring in blade/disk contacts in gas turbine engines. LSP treated specimens attained 5-, 10- and 25-fold increase in lives compared to untreated specimens. Metallography of the contact area and fractographic analysis of worn pads detail the fretting behavior of LSP treated specimens. © 2009 Elsevier Ltd. All rights reserved.

Haradanahalli S. N. Murthy

Department of Aerospace Engineering

Contact areas

CONTACT CONDITIONS

Fractographic analysis

FRETTING BEHAVIORS

FRETTING FATIGUE

FRETTING FATIGUES

Gas turbine engine

LASER SHOCK PEENING

LASER SHOCKS

Ti-6Al-4V

Aluminum

FRETTING CORROSION

Gas turbines

Lasers

Pulsed laser applications

titanium

Titanium alloys

Fatigue of materials

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Tribology International

The titanium alloy Ti-6Al-4V was subjected to laser peening (without coating) at power densities of 3, 6 and 9 GW cm−2. The cross sectional profiles of microhardness and residual stress indicated softening in the bulk (away from the surface) at power density of 9 GW cm−2. This behavior was analyzed using a combination of Zerilli-Armstrong phenomenological model in conjunction with the concept of adiabatic heating. The implications of this analysis was supported by structural changes in terms of α → β transition (analyzed through synchrotron radiation) and microstructural changes in terms of primary α (equiaxed) to secondary α (lamellar) transformation, which is observed for the first time here. Based on this, optimum levels of peening to improve fatigue lives are suggested through relevant experiments. © 2019 Elsevier Ltd

Optics & Laser Technology

Mechanical properties of a laser peened Ti-6Al-4V

The effects of laser peening and shot peening on fretting fatigue in Ti–6Al–4V coupons

Engineering Failure Analysis

Fractographic investigation of fretting fatigue cracks in Ti–6Al–4V

Acta Astronautica

Fretting fatigue of single crystal/polycrystalline nickel subjected to blade/disk contact loading

Journal	Tribology International
ISSN	0301679X
Open Access	No