Abstract: Disclosed is an arrangement for coupling a fairing panel to an engine casing. The arrangement includes a pair of rigid brackets having a specific stiffness, wherein the pair of rigid brackets couple a first side of the fairing panel to a first side of the engine casing. The arrangement further includes a pair of flexible brackets comprising a first flexible bracket having a first stiffness and a second flexible bracket having a second stiffness more than the first stiffness. Moreover, the first stiffness and the second stiffness are less than the specific stiffness of the pair of rigid brackets. Furthermore, the pair of flexible brackets couple a second side opposite to the first side of the fairing panel to a second side opposite to the first side of the engine casing.

Abstract: The proposed solution concerns in particular an engine assembly with a casing part extending along a central axis, at least one cover part which at least partially covers an outside of the casing part, and for this, in relation to the central axis, extends along a circumferential direction which points along a circular path around the central axis, and at least one connecting element via which the at least one cover part is fixed relative to the casing part and which compensates for different thermal expansions of the casing part and the at least one cover part.

Abstract: Disclosed is an arrangement for coupling a fairing panel to an engine casing. The arrangement includes a pair of rigid brackets having a specific stiffness, wherein the pair of rigid brackets couple a first side of the fairing panel to a first side of the engine casing. The arrangement further includes a pair of flexible brackets comprising a first flexible bracket having a first stiffness and a second flexible bracket having a second stiffness more than the first stiffness. Moreover, the first stiffness and the second stiffness are less than the specific stiffness of the pair of rigid brackets. Furthermore, the pair of flexible brackets couple a second side opposite to the first side of the fairing panel to a second side opposite to the first side of the engine casing.

Abstract: The proposed solution concerns in particular an engine assembly with a casing part extending along a central axis, at least one cover part which at least partially covers an outside of the casing part, and for this, in relation to the central axis, extends along a circumferential direction which points along a circular path around the central axis, and at least one connecting element via which the at least one cover part is fixed relative to the casing part and which compensates for different thermal expansions of the casing part and the at least one cover part.

Abstract: 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.

Abstract: 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.