Patent ID: 11913352
Assignee: GENERAL ELECTRIC COMPANY
Field: Engines, pumps, turbines (Mechanical engineering)
Classification: CPC F  Y | IPC F

Claim 16:
17. A blade for use in an aircraft engine, the blade comprising:
receiving means defining a cavity, an aperture extending through the receiving means, the receiving means including a first rib protruding away from the receiving means, the first rib including a first surface; and
a covering means including a second rib protruding from a second surface of the covering means, the second rib including a third surface spaced apart from and facing the receiving means, the first surface of the first rib spaced apart from and facing the second surface of the covering means, the first and third surfaces positioned between the receiving means and the second surface, the second rib contacting the first rib to couple the covering means to the receiving means such that the covering means encloses the aperture.