| 摘要 |
<p>The invention relates to an aircraft engine annular shroud (40, 100), characterized in that it comprises: - on its internal surface (41, 110), a peripheral annular groove (42, 101) able to accept a plurality of blade roots (46, 104); - an insertion opening (43, 102) for inserting the blade roots (46, 104) into the annular groove (42, 101); - closure means (60, 106, 107) for closing off the insertion opening (43, 102).</p> |
