US 12,338,746 B2
Aerodynamically mistuned airfoils for unsteady loss reduction
Francesco Bertini, Turin (IT); Davide Torzo, Turin (IT); Pratish Patil, Bengaluru (IN); John Joseph, Bengaluru (IN); Mahendran Manoharan, Bengaluru (IN); and Ganesh Seshadri, Bengaluru (IN)
Assigned to General Electric Company, Schenectady, NY (US); and GE Avio S.r.l., Turin (IT)
Filed by General Electric Company, Schenectady, NY (US); and GE Avio S.r.l., Turin (IT)
Filed on Apr. 15, 2024, as Appl. No. 18/635,858.
Application 18/635,858 is a division of application No. 17/951,653, filed on Sep. 23, 2022, abandoned.
Claims priority of application No. 202211015402 (IN), filed on Mar. 21, 2022.
Prior Publication US 2024/0254884 A1, Aug. 1, 2024
Int. Cl. F01D 5/14 (2006.01)
CPC F01D 5/142 (2013.01) [F05D 2220/323 (2013.01); F05D 2240/12 (2013.01); F05D 2240/30 (2013.01)] 12 Claims
OG exemplary drawing
 
1. An apparatus comprising:
a disk;
a first airfoil coupled to the disk, the first airfoil having a first geometry including a first curvature with a corresponding first axial pressure distribution; and
a second airfoil coupled to the disk adjacent to the first airfoil, the second airfoil having a second geometry including a second curvature with a corresponding second axial pressure distribution, the first axial pressure distribution different than the second axial pressure distribution, the second airfoil having a same root-to-tip span length as the first airfoil;
a first channel between the first airfoil and the second airfoil; and
a second channel adjacent to the first channel, the first airfoil and the second airfoil producing non-uniform wake characteristics in the first channel and the second channel during operation of the disk,
wherein the disk is a rotor disk of a gas turbine engine,
wherein the first geometry includes a first thickness-to-chord ratio and the second geometry includes a second thickness-to-chord ratio, the first thickness-to-chord ratio different than the second thickness-to-chord ratio, and
wherein (1) the first thickness-to-chord ratio is less than the second thickness-to-chord ratio and (2) the second axial pressure distribution is more aft loaded than the first axial pressure distribution.