Patent ID: 11913355
Assignee: GENERAL ELECTRIC COMPANY
Field: Engines, pumps, turbines (Mechanical engineering)
Classification: CPC F  Y | IPC F

Claim 7:
8. A gas turbine engine comprising:
a disk;
a first pitch controlled airfoil coupled to the disk;
a second pitch controlled airfoil coupled to the disk, the second pitch controlled airfoil circumferentially adjacent to the first pitch controlled airfoil; and
a part-span shroud including:
a first portion extending from the first pitch controlled airfoil, the first portion including a first surface, the first surface being convex;
a second portion extending from the second pitch controlled airfoil towards the first pitch controlled airfoil, the second portion including a second surface the first pitch controlled airfoil circumferentially adjacent to the second pitch controlled airfoil, the second surface being concave; and
an interface formed by the first surface and the second surface, the interface to react to circumferential loads between the first pitch controlled airfoil and the second pitch controlled airfoil, the interface to enable the first pitch controlled airfoil to rotate relative to the second pitch controlled airfoil.