US 11,933,186 B2
Vibrational damping assembly for use in an airfoil
Karol Filip Leszczynski, Henrykow Urocze (PL); and Przemyslaw Michal Jakubczak, Warsaw (PL)
Assigned to GE Infrastructure Technology LLC, Greenville, SC (US)
Filed by General Electric Company, Schenectady, NY (US)
Filed on Apr. 28, 2022, as Appl. No. 17/731,653.
Claims priority of application No. 440813 (PL), filed on Mar. 31, 2022.
Prior Publication US 2023/0313705 A1, Oct. 5, 2023
Int. Cl. F01D 25/06 (2006.01); F01D 5/16 (2006.01); F01D 25/30 (2006.01)
CPC F01D 25/06 (2013.01) [F01D 5/16 (2013.01); F01D 25/30 (2013.01); F05D 2230/64 (2013.01); F05D 2240/12 (2013.01); F05D 2260/96 (2013.01)] 9 Claims
OG exemplary drawing
 
1. A turbomachine airfoil assembly comprising:
a turbomachine airfoil comprising a leading edge, a trailing edge, and a first side wall and a second side wall extending between the leading edge and the trailing edge, the first side wall and the second side wall defining an interior of the turbomachine airfoil, wherein the turbomachine airfoil is an auxiliary airfoil coupled to a strut disposed within an exhaust flow passage of an exhaust diffuser of a turbomachine; and
a vibrational damping assembly disposed in the interior of the turbomachine airfoil and coupled to one of the first side wall or the second side wall, the vibrational damping assembly comprising:
at least one pin coupled to the turbomachine airfoil, the at least one pin having a pin body and a disk coupled to the pin body; and
at least one plate disposed between the disk and the turbomachine airfoil, wherein the at least one plate is movable between the disk and the turbomachine airfoil relative to the at least one pin and relative to the turbomachine airfoil to dampen vibrations experienced by the turbomachine airfoil.