Abstract
This paper is based on laser shock peening (LSP) system with a flat‐topped beam, using robot simulation software to determine the oblique shock angle of different areas of a certain turbine disk mortise. Three‐dimensional finite element analysis was used to study residual stress field of Ni‐based alloy GH4169 under flat‐topped laser oblique shocking. The effects of different laser energy and different shocking number on residual stress field of Ni‐based alloy GH4169 of LSP were studied. Three‐dimensional finite element analysis used super‐Gaussian beam distribution to construct spatial distribution model of shock wave induced by LSP. The simulation results were in good agreement with the experimental results. The research results will provide a theoretical basis for LSP of certain turbine disk mortise.
Highlights
Ni-based alloy GH4169 has excellent performance in high-temperature environments [1, 2] and is often used in the manufacture of aeroengine turbine discs. e turbine discs and the blades of the aeroengine are tightly connected by the tenon and mortise
Effect of Laser Energy on Residual Stress Field. ree different laser energies were used for comparative analysis, which were 5 J, 6 J, and 7 J, and other parameters were kept the same
As laser energy applied to the surface of material increased, the maximum compressive residual stress on the surface of material increased, respectively: −296.2 MPa, −373.8 MPa, and −443.5 MPa; the maximum compressive residual stress generated by 6 J increased by −77.6 MPa compared with 5 J, 26.6% amplitude of increase; the maximum residual compressive stress generated by 7 J compared with 5 J increased by −69.7 MPa, 18.6% amplitude of increase
Summary
Ni-based alloy GH4169 (equivalent to Inconel 718) has excellent performance in high-temperature environments [1, 2] and is often used in the manufacture of aeroengine turbine discs. e turbine discs and the blades of the aeroengine are tightly connected by the tenon and mortise. E turbine discs and the blades of the aeroengine are tightly connected by the tenon and mortise. In the process of aeroengine service, the turbine disc inside the aeroengine drives the blades to rotate at a high speed. During this process, the contact area will generate high-frequency vibration, which can produce a high level of stress concentration. E manufacturing process of the tenon and mortise is easy to form harmful tensile residual stress on surface and inside of material. It is generally believed that the compressive residual stress on the surface can inhibit the initiation and propagation of crack, which is beneficial to prolong the fatigue life [5, 6]. Compressive residual stress can be obtained by using some surface treatment techniques, such as low plasticity burnishing [7, 8], shot peening [9], and LSP [10, 11]
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