Abstract: Cathodic protection of steel in a concrete column in sea water is simplified by providing a pre-assembled unit including a jacket to surround the column carrying a bulk sacrificial anode outside the jacket and optionally an inner sacrificial anode of a zinc mesh or strips on an inside surface. The jacket can also include a pre-assembled junction box and couplings to connect to the steel. The jacket is attached to the surface of the column at the water line so that the bulk anode is located below the surface of the water and supported relative to the concrete surface solely by the connection of the bulk anode to the covering layer. The bulk anode can be formed of aluminum so as to be less toxic in sea water.

Abstract: Cathodic protection of steel in a concrete column in sea water is simplified by providing a pre-assembled unit including a jacket to surround the column carrying a bulk sacrificial anode outside the jacket and optionally an inner sacrificial anode with a cast grout inside the jacket. The jacket can also include a pre-assembled junction box and couplings to connect to the steel. The jacket is attached to the surface of the column at the water line so that the bulk anode is located below the surface of the water. The bulk anode can be formed of aluminum so as to be less toxic in sea water. An activator is applied inside the jacket either as a wicking layer or as a chemical activating material. The jacket can act only as a form work which is then removed after casting of the grout.

Abstract: Gas turbine engine fan blade containment systems are disclosed. An example fan blade containment system includes a shield to be coupled to an aircraft structure and to at least partially surround a circumference of an aircraft engine. The shield is to be spaced from an outer surface the aircraft engine when the shield is coupled to the aircraft structure. A shield termination fitting is to couple a terminating end of the shield to the aircraft structure.

Abstract: Gas turbine engine fan blade containment systems are disclosed. An example fan blade containment system includes a shield to be coupled to an aircraft structure and to at least partially surround a circumference of an aircraft engine. The shield is to be spaced from an outer surface the aircraft engine when the shield is coupled to the aircraft structure. A shield termination fitting is to couple a terminating end of the shield to the aircraft structure.