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

Claim 18:
19. A turbine engine comprising:
a rotor;
a component coupled to the rotor, the component having a plurality of component segments circumferentially arranged and radially extending from the rotor, each of the plurality of component segments having a passage segment extending between and opening onto a first circumferential end to define a first opening and a second circumferential end to define a second opening, wherein a confronting open pair is defined by the first opening and the second opening of adjacent component segments of the plurality of component segments; and
a damper element that extends between the confronting open pair, wherein the damper element comprises a tube having a spacer located between the adjacent component segments, wherein the passage segments collectively form a circumferential passage and the damper element extends through the circumferential passage.