402 Analysis of Shot-Peening Phenomenon for Stainless Steels (II) : Finite Element Modeling of Impact Analysis by Rigid Sphere

2010 ◽  
Vol 2010.63 (0) ◽  
pp. 123-124
Author(s):  
Teruaki Yamada ◽  
Masatoshi Kuroda ◽  
Kazuya Mori
Author(s):  
Raoudha Seddik ◽  
Akram Atig ◽  
Rabii Ben Sghaier ◽  
Raouf Fathallah

2017 ◽  
Vol 28 (2) ◽  
pp. 187-199 ◽  
Author(s):  
John Z. Wu ◽  
Christopher S. Pan ◽  
Bryan M. Wimer ◽  
Charles L. Rosen

Author(s):  
T. J. Moffat ◽  
W. L. Cleghorn

Finite element modeling of bird impacts has been developed and calibrated using the 3-D impact analysis code MSC/DYTRAN. These modeling efforts have shown that the Arbitrary Lagrange Euler (ALE) formulation within MSC/DYTRAN is capable of capturing the physics of the bird impact problem, producing impact pressures and damage similar to that of a real bird. This work is divided into two areas. First, a review of the literature was carried out to identify the physical processes, pressures and damage associated with real bird impacts. Second, finite element modeling of two simple bird impacts cases were carried out using MSC/DYTRAN. A comparison of the finite element predictions with the experimental data showed excellent agreement, and demonstrated the robustness of the ALE formulation.


Author(s):  
S. A. Meguid ◽  
Luke A. Maricic

Surface enhancement techniques such as shot peening are extensively used to increase the fatigue life of components in gas turbine engines. Due to the combined thermomechanical nature of the loading encountered within an engine, aeroengine designers have avoided incorporating the beneficial effects in their analysis. This can lead to overdesign and early retirement of critical engine components. A finite element modeling procedure is introduced that incorporates the shot peening residual stresses on a fir-tree turbine disk assembly. Unlike traditional equivalent loading approaches, the method models the actual impact of shots on the assembly and is the first time this approach is used to introduce peening residual stresses in turbine disks. In addition, the stability of these residual stresses in response to cyclic thermomechanical loadings at the contact interface is also studied. The results reveal that thermomechanical overload can nearly fully relax the shot peening residual stresses within the first cycle due to the combined effects of decreased material yield strength and plastic deformation. This work will enable aeroengine designers to assess critical surface treated components for structural integrity, optimal design, and residual life.


2017 ◽  
Vol 130 ◽  
pp. 234-247 ◽  
Author(s):  
Lamine Dieng ◽  
Darine Amine ◽  
Yannick Falaise ◽  
Sylvain Chataigner

1991 ◽  
Vol 3 (1) ◽  
pp. 235-253 ◽  
Author(s):  
L. D. Philipp ◽  
Q. H. Nguyen ◽  
D. D. Derkacht ◽  
D. J. Lynch ◽  
A. Mahmood

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