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

<table class="figure-group"><tr class="fig-image" id="a"><td><object data="https://static-preview.hindawi.com/articles/ijae/volume-2021/8357380/figures/8357380.fig.005a.svgz" name="8357380.fig.005a" type="image/svg+xml"></object></td></tr><tr class="fig-caption"><td><b>(a) </b>Rotor trace</td></tr><tr class="fig-image" id="b"><td><object data="https://static-preview.hindawi.com/articles/ijae/volume-2021/8357380/figures/8357380.fig.005b.svgz" name="8357380.fig.005b" type="image/svg+xml"></object></td></tr><tr class="fig-caption"><td><b>(b) </b>Displacement</td></tr><tr class="fig-image" id="c"><td><object data="https://static-preview.hindawi.com/articles/ijae/volume-2021/8357380/figures/8357380.fig.005c.svgz" name="8357380.fig.005c" type="image/svg+xml"></object></td></tr><tr class="fig-caption"><td><b>(c) </b>Amplitude spectrum</td></tr></table>

<div>Response of the low-pressure compressor disk in the simulated aeroengine system.</div>

International Journal of Aerospace Engineering

fig5

Figure 5

Figure 5: Transient Response of a Simulated Aeroengine with a Fusing Structure during a Fan-Blade Out Event 