US 12,241,384 B2
Rotor blade system of turbine engines
Wei-Min Ren, Schenectady, NY (US); Letian Wang, Atlanta, GA (US); Kevin E. Turner, Liberty Township, OH (US); and Yoon Seok Choi, Evendale, OH (US)
Assigned to GENERAL ELECTRIC COMPANY, Evendale, OH (US)
Filed by General Electric Company, Schenectady, NY (US)
Filed on Apr. 4, 2024, as Appl. No. 18/627,026.
Application 18/627,026 is a division of application No. 17/661,796, filed on May 3, 2022, granted, now 11,959,395.
Prior Publication US 2024/0271534 A1, Aug. 15, 2024
Int. Cl. F01D 5/16 (2006.01)
CPC F01D 5/16 (2013.01) [F05D 2220/30 (2013.01); F05D 2240/30 (2013.01); F05D 2260/961 (2013.01)] 20 Claims
OG exemplary drawing
 
1. A rotor blade system comprising:
a rotor; and
a plurality of blades coupled to the rotor, the plurality of blades arranged in an airfoil distribution pattern, the airfoil distribution pattern comprising one or more baseline blades and one or more intentionally mistuned blades having a first side and a second side opposite the first side, the one or more intentionally mistuned blades including an intentional mistuning feature that includes an under-platform damper positioned under a platform of the one or more intentionally mistuned blades and positioned only on the first side of the one or more intentionally mistuned blades.