Transient Response of a Simulated Aeroengine with a Fusing Structure during a Fan-Blade Out Event

<table class="table-group" id="tab6"><tr><td><table class="table"><tr><td class="thead-hr" colspan="3"><hr/></td></tr><tr class="thead"><td class="align_left">Position</td><td class="align_center">Peak transient response (mm)</td><td class="align_center">Amplitude of steady response (mm)</td></tr><tr><td class="thead-hr" colspan="3"><hr/></td></tr><tr><td class="align_left">Fusing structure not activated</td><td class="align_center">63.9</td><td class="align_center">33.6</td></tr><tr><td class="align_left">Fusing structure activated</td><td class="align_center">80.5</td><td class="align_center">29.4</td></tr><tr><td class="align_left">Relative deviation</td><td class="align_center">25.90%</td><td class="align_center">−12.50%</td></tr><tr class="table-tr"><td colspan="3"><hr class="tbody-hr"/></td></tr></table></td></tr></table>

<div>Response of low-pressure compressor disk with a variable-stiffness fusing structure.</div>

International Journal of Aerospace Engineering

tab6

Table 6

Table 6: Transient Response of a Simulated Aeroengine with a Fusing Structure during a Fan-Blade Out Event 