US 12,392,246 B2
Airfoil cooling circuit
Dana K. Bondarevsky, Sturbridge, MA (US); Dominic J. Mongillo, Jr., West Hartford, CT (US); Christopher Paul Perron, Tolland, CT (US); Yuta Yoshimura, Meriden, CT (US); and David D. Chapdelaine, Ellington, CT (US)
Assigned to RTX Corporation, Farmington, CT (US)
Filed by Raytheon Technologies Corporation, Farmington, CT (US)
Filed on Jun. 12, 2023, as Appl. No. 18/208,689.
Prior Publication US 2024/0410283 A1, Dec. 12, 2024
Int. Cl. F01D 5/18 (2006.01)
CPC F01D 5/187 (2013.01) [F05D 2240/301 (2013.01); F05D 2260/221 (2013.01)] 20 Claims
OG exemplary drawing
 
1. An airfoil for a gas turbine engine, the airfoil comprising:
a body defining an internal cavity, the body having a pressure side wall and a suction side wall, the pressure side wall and the suction side wall extending in a spanwise direction from a base region to a tip region and in a chordwise direction from a leading edge to a trailing edge;
a tip wall extending in the chordwise direction between the pressure side wall and the suction side wall and defining a radially outer boundary of the internal cavity in the tip region;
a first wall disposed in the interior cavity, the first wall extending in the spanwise direction from the base region to the tip wall and adjoining the pressure side wall and the suction side wall to form a first cooling channel;
a second wall disposed in the interior cavity and extending in the chordwise direction from the first wall toward the trailing edge, the second wall adjoining the pressure side wall and the suction side wall to form a second cooling channel;
a first hole through the first wall, the first hole connecting the first cooling channel to the second cooling channel, wherein all of a cooling fluid flow in the second cooling channel is received from the first hole; and
a second hole though the second wall connecting the second cooling channel to a third cooling channel, wherein an area of the second hole is at least 80 percent of the area of the first hole.