The results of numerical modeling of the residual stress field formation under the action of laser-induced shock waves were verified using the residual stress profiles obtained experimentally by a hole drilling method (GOST R 71316-2024).
The verified numerical model was used to estimate residual stresses in a thin (about 0.3 mm) leading edge of the compressor blade of a gas turbine engine (GTE) and to formulate recommendations for laser shock peening of parts of similar geometry.
It was shown that the proposed regimes of laser shock peening of thin edges of a gas turbine engine blade eliminate its bending and the formation of tensile stresses in the treatment zone, and therefore can be recommended for strengthening the blades of aircraft engines during their manufacture.
Kostina, M. Zhelnin, A. Vedernikova, M. Bartolomei. Finite-element simulation of residual stresses induced by laser shock peening in TC4 samples structurally similar to a turbine blade // Frattura ed Integrità Strutturale. – 2024. – Vol. 18. – No. 67. – P. 00-11. – DOI: 10.3221/IGF-ESIS.67.01
Bartolomey M.L., Izyumova A.Yu., Gachegova E.A., Vshivkov A.N., Plekhov O.A. Numerical analysis of residual stresses during double-sided symmetric laser impact hardening of thin plates made of VT6 titanium alloy // Computational Continuum Mechanics. – 2024. – Vol. 17. – No. 4