| 摘要 |
A protective device (10) for a turbomachine, in particular a gas turbine, having a containment ring (12) which is disposed on the radially inner side of a casing element (14) of the turbomachine and which at least substantially prevents the casing element (14) from being penetrated by a fragment of a component of the turbomachine in the event of a structural failure of this component is provided. The containment ring (12) is composed, at least in the circumferential direction, of a plurality of ring segments (16) which are form-fittingly interconnected. A second aspect of the present invention relates to an aircraft engine. |
