US 12,012,866 B1
Non-circular stress reducing crossover
Dana K. Bondarevsky, Sturbridge, MA (US); Christopher Corcoran, Planstville, CT (US); Bryan P. Dube, Chepachet, RI (US); Yuta Yoshimura, Meriden, CT (US); David D. Chapdelaine, Ellington, CT (US); and Christopher Paul Perron, Tolland, 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. 18/208,684.
Int. Cl. F01D 5/18 (2006.01)
CPC F01D 5/18 (2013.01) [F05D 2260/20 (2013.01)] 18 Claims
OG exemplary drawing
 
1. An airfoil for a gas turbine engine, the airfoil configured to extend in a radial direction relative to an engine axis from an inner diameter to an outer diameter and comprising:
a body having a base disposed at the inner diameter, a tip disposed at the outer diameter, a leading edge, a trailing edge, a pressure side wall extending between the leading edge and the trailing edge and between the base and the tip, and a suction side wall extending between the leading edge and the trailing edge and between the base and the tip; wherein the body defines an interior cavity;
a first wall disposed in the interior cavity, the first wall extending radially and adjoining the pressure side wall and the suction side wall to form a first cooling channel; and
a first hole through the first wall, the first hole connecting the first cooling channel to a second cooling channel, wherein the first hole has a tapering oval shape extending radially and tapering inward toward the base with an inner radius at a radially inner end and an outer radius at a radially outer end, wherein the inner radius is less than the outer radius.