Patent ID: 11959395
Assignee: GENERAL ELECTRIC COMPANY
Field: Engines, pumps, turbines (Mechanical engineering)
Classification: CPC F | IPC F

Claim 19:
20. The turbine engine of claim 19, wherein the intentional mistuning feature is a first intentional mistuning feature and the one or more intentionally mistuned blades include a second intentional mistuning feature that is selected from the group consisting of:
a reduced chord length from a trailing edge in a tip region of the one or more intentionally mistuned blades relative to a chord length of the one or more baseline blades,
at least one of a varied spanwise location of an internal cavity of the one or more intentionally mistuned blades relative to a spanwise location of an internal cavity of the one or more baseline blades, a varied chordwise location of the internal cavity of the one or more intentionally mistuned blades relative to a chordwise location of the internal cavity of the one or more baseline blades, a varied radial height of the internal cavity of the one or more intentionally mistuned blades relative to a radial height of the internal cavity of the one or more baseline blades, or a varied axial length of the internal cavity of the one or more intentionally mistuned blades relative to an axial length of the internal cavity of the one or more baseline blades,
a mass in the internal cavity of the one or more intentionally mistuned blades,
a powder material in the internal cavity of the one or more intentionally mistuned blades,
a tuned impact damper in the internal cavity of the one or more intentionally mistuned blades,
a friction damper in the internal cavity of the one or more intentionally mistuned blades,
one or more shock control bumps on the one or more intentionally mistuned blades,
an under-platform damper positioned under a platform of the one or more intentionally mistuned blades, or
combinations thereof.