US 12,497,908 B2
Turbine engine including a fan assembly having a damper
Abhijeet Yadav, Bengaluru (IN); Nicholas J. Kray, Mason, OH (US); Nitesh Jain, Bengaluru (IN); Brandon W. Miller, Middletown, OH (US); and Ravindra Shankar Ganiger, Bengaluru (IN)
Assigned to GENERAL ELECTRIC COMPANY, Evendale, OH (US)
Filed by General Electric Company, Schenectady, NY (US)
Filed on Mar. 13, 2024, as Appl. No. 18/603,694.
Prior Publication US 2025/0290431 A1, Sep. 18, 2025
Int. Cl. F01D 25/04 (2006.01); F02C 3/04 (2006.01)
CPC F01D 25/04 (2013.01) [F02C 3/04 (2013.01); F05D 2260/96 (2013.01)] 20 Claims
OG exemplary drawing
 
1. A turbine engine experiencing 1P vibrations, the turbine engine comprising:
a turbo-engine having a longitudinal centerline axis;
a compressor generates compressed air;
a combustor that receives fuel and the compressed air, and combusts the compressed air and the fuel to generate combustion gases;
a turbine that receives the combustion gases and rotates; and
a fan assembly, driven by the turbine, that rotates about the longitudinal centerline axis, the fan assembly comprising:
a fan disk aligned with the longitudinal centerline axis;
a fan blade with a fan blade centerline axis orthogonal to the longitudinal centerline axis, the fan blade subjected to 1P loading and generating the 1P vibrations;
a fan blade root fixed to the fan blade and connected to the fan disk, the fan blade root aligned with the fan blade centerline axis and conducting the 1P vibrations; and
a damper having a side aligned with the fan blade centerline axis and being positioned radially between the fan blade root and the fan disk, the damper damping the 1P vibrations, such that the 1P vibrations in the fan disk have a reduced amplitude with respect to the 1P vibrations in the fan blade root.