Finite element analysis of surface deformations induced by Laser Shock Peening of a gas turbine engine compressor blade fabricated from VT6 titanium alloy


Аuthors

Kozhevnikov G. D.*, Korolev D. D., Lyakhovetsky M. A., Tokachev D. A., Tregulov D. F.

Moscow Aviation Institute (National Research University), 4, Volokolamskoe shosse, Moscow, А-80, GSP-3, 125993, Russia

*e-mail: kozhevnikov.mai@yandex.ru

Abstract

One of the key challenges in manufacturing engines and aircraft structures is ensuring fatigue strength. This study investigates Laser Shock Peening (LSP), a technique used to improve fatigue strength by inducing compressive residual stresses on component surfaces. The focus is on numerically modeling the LSP process and assessing the effects of various parameters, such as laser pulse intensity, duration, and the impact of repeated shocks on surface deformation. The numerical results show good alignment with experimental data at laser intensities up to 8 GW/cm² for different pulse durations It has been demonstrated that the numerical model does not account for the impact of saturation of surface deformations as a result of repeated impacts. This research aims to validate the LSP numerical model for predicting surface deformations, which can help optimize processing parameters.

Keywords:

fatigue, titanium alloy, residual stresses, laser shock peening, finite element modeling, surface deformations, compressor blades

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