US 11,946,388 B2
Turbine engine with interlocking seal
Antonio Giusseppe D'Ettole, Rivoli (IT); Andrea Depalma, Rivalta di Turin (IT); Roberto Maddaleno, Lanzo Torinese (IT); and Matteo Renato Usseglio, Turin (IT)
Assigned to GE Avio S.r.l., Rivalta di Torino (IT)
Filed by GE Avio S.r.l., Rivalta di Turin (IT)
Filed on Jul. 13, 2022, as Appl. No. 17/863,470.
Application 17/863,470 is a continuation of application No. 16/936,567, filed on Jul. 23, 2020, abandoned.
Claims priority of application No. 102019000013854 (IT), filed on Aug. 2, 2019.
Prior Publication US 2022/0364473 A1, Nov. 17, 2022
Int. Cl. F01D 5/22 (2006.01); F01D 11/12 (2006.01)
CPC F01D 5/225 (2013.01) [F01D 11/125 (2013.01); F05D 2220/32 (2013.01); F05D 2240/30 (2013.01); F05D 2240/55 (2013.01)] 20 Claims
OG exemplary drawing
 
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.