US 12,319,419 B2
Fluid-filled thrust link apparatus and associated method
Ryan T. Roehm, Evendale, OH (US); Brandon W. Miller, Evendale, OH (US); Robert Eugene Dyson, West Chester, OH (US); Arthur W. Sibbach, Boxford, MA (US); Donald S. Yeager, West Chester, OH (US); and John C. Schilling, Evendale, OH (US)
Assigned to General Electric Company, Evendale, OH (US)
Filed by General Electric Company, Evendale, OH (US)
Filed on Nov. 14, 2024, as Appl. No. 18/947,832.
Application 18/947,832 is a continuation of application No. PCT/US2024/048431, filed on Sep. 25, 2024.
Claims priority of provisional application 63/585,166, filed on Sep. 25, 2023.
Prior Publication US 2025/0100700 A1, Mar. 27, 2025
Int. Cl. B64D 27/40 (2024.01)
CPC B64D 27/40 (2024.01) [B64D 27/406 (2024.01)] 20 Claims
OG exemplary drawing
 
1. A thrust link for an aircraft engine, the thrust link comprising:
a first wall having a forward portion and an aft portion at opposite ends of the thrust link, the forward portion coupled to the aircraft engine, the aft portion coupled to the aircraft engine, a pylon, or an aircraft associated with the aircraft engine; and
a second wall within an interior area surrounded by the first wall, the second wall spaced apart from the first wall, a space between the first wall and the second wall defining a channel within the interior area, the channel including a fluid, the fluid pressurized based on a damping ratio to withstand a resonant vibration frequency generated by the aircraft engine.