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

Claim 0:
1. A blade for use in an aircraft engine, the blade comprising:
a hollow body including a first surface defining a cavity, the hollow body including an aperture extending through the first surface, the first surface including a first rib protruding away from the first surface, the first rib including a second surface; and
a cover plate including a second rib protruding from a third surface of the cover plate, the second rib including a fourth surface spaced apart from and facing the first surface, the second surface of the first rib spaced apart from and facing the third surface of the cover plate, the second and fourth surfaces positioned between the first and third surfaces, the second rib of the cover plate contacting the first rib of the hollow body to couple the cover plate to the first surface such that the cover plate encloses the aperture.