Patent ID: 11946388
Assignee: GE AVIO S.R.L.
Field: Engines, pumps, turbines (Mechanical engineering)
Classification: CPC F | IPC F

Claim 0:
1. A turbine engine comprising:
an inner rotor defining and rotating about an axially extending longitudinal axis;
an outer rotor circumscribing at least a portion of the inner rotor and rotating about the longitudinal axis, wherein the outer rotor rotates about the inner rotor;
at least one component coupled to and rotating with the outer rotor or the inner rotor, the at least one component comprising a plurality of circumferentially arranged and radially extending component segments, wherein each of the component segments includes a passage segment located at an inner band and extending between and opening onto a first circumferential end to define a first opening and a second circumferential end to define a second opening; and
a damper element comprising a tube extending at least partially into the passage segments of a confronting open pair defined by the first opening and the second opening of adjacent component segments, wherein the damper element includes a spacer located between the adjacent component segments.