US 12,492,640 B2
Turbine engine including a vane support and a vane
Nicholas J. Kray, Mason, OH (US); Aaron M. Gilbert, West Newbury, MA (US); Heidi J. Stegemiller, Franklin, OH (US); Steven R. Manwaring, Lebanon, OH (US); and Kohki Nishida, Cincinnati, OH (US)
Assigned to GENERAL ELECTRIC COMPANY, Evendale, OH (US)
Filed by General Electric Company, Schenectady, NY (US)
Filed on May 30, 2024, as Appl. No. 18/678,281.
Prior Publication US 2025/0369361 A1, Dec. 4, 2025
Int. Cl. F01D 5/28 (2006.01); F01D 5/14 (2006.01)
CPC F01D 5/282 (2013.01) [F01D 5/141 (2013.01); F05D 2300/6033 (2013.01)] 20 Claims
OG exemplary drawing
 
1. A turbine engine for an aircraft, the turbine engine comprising:
a vane support including a vane-facing surface, a first hook, and a second hook, the first hook and the second hook extending from the vane-facing surface, the first hook and the second hook opposing each other and defining a channel therebetween; and
a vane including an airfoil and an outer band attached to the airfoil, the outer band including a support-facing surface, a first rail, and a second rail, the outer band being positioned in the channel with the first rail engaging the first hook and the second rail engaging the second hook,
wherein the vane-facing surface and the support-facing surface are shaped to form a contact configuration in which, during flexing of the vane under a first condition of the turbine engine, at least a portion of the support-facing surface contacts the vane-facing surface over a contacting region, the first condition being an operating condition of the turbine engine, and
wherein a gap is present between the support-facing surface and the vane-facing surface over the contacting region during a second condition of the turbine engine, the second condition being a non-operating condition of the turbine engine.