| 摘要 |
An ice strike sheathing ring ( 4 ) including several fiber compound layers for the fan casing of an aircraft gas turbine features breaking points ( 7 ) at a certain regular distance, so that, in case of destruction of the ice strike sheathing ring due to extreme ice strike, fragments of small size will be produced which together with the engine airflow will pass the exit guide vanes downstream of the fan without blocking the engine airflow or reducing engine thrust. With fiber compound layers enclosing a cavity or a core, the breaking points designed as slots ( 9 ) and/or assembly holes ( 8 ) are located in the inner wall ( 20 ) of the ice strike sheathing ring facing the engine airflow, while the outer wall ( 21 ) of the ice strike sheathing ring adjoining the fan casing is firmly attached to the latter via an adhesive film and a threaded safety connection.
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