| 摘要 |
<p>A thermal protection device for equipment (14) positioned in an engine compartment (9) of an aircraft turbomachine comprises at least one heat shield (16) arranged at least partially between said equipment and a thermally radiative wall (12) of said engine compartment exposed to a heating source. Said shield (16; 26; 36) comprises air-channeling means (16a, 19) connected to a cooling air source (11) and configured to direct said cooling air toward said equipment (14).</p> |
