US 12,404,775 B1
Turbine blade with cooling channels
Griffin D. Lavine, South Glastonbury, CT (US); Brandon W. Spangler, Vernon, CT (US); and David R. Pack, Gold Canyon, AZ (US)
Assigned to RTX CORPORATION, Farmington, CT (US)
Filed by RTX Corporation, Farmington, CT (US)
Filed on Sep. 16, 2024, as Appl. No. 18/886,974.
Int. Cl. F01D 5/18 (2006.01)
CPC F01D 5/187 (2013.01) [F05D 2260/20 (2013.01)] 20 Claims
OG exemplary drawing
 
1. A turbine engine rotor blade, comprising:
a root; and
an airfoil that extends spanwise between a tip and a base, the airfoil including a side wall with a side wall exterior surface and a side wall interior surface, wherein the side wall exterior surface extends between a leading edge of the airfoil and a trailing edge and spanwise between the tip and the base;
wherein the airfoil includes at least one first wall channel, and the first wall channel is defined by a base surface that is a portion of the side wall interior surface, a first interior wall surface, and a second interior wall surface, wherein a first interface surface extends between the base surface and the first interior wall surface, a second interface surface extends between the base surface and the second interior wall surface, and a third interface surface extends between the first interior wall surface and the second interior wall surface; and
wherein the base surface includes a base surface first segment, a base surface second segment, and a peak interface surface extending between the base surface first segment and the base surface second segment, and wherein the base surface first segment and the base surface second segment are disposed at an oblique angle;
wherein the third interface surface is spaced apart from the peak interface surface; and
wherein the first wall channel is oriented such that first interface surface is disposed closer to the side wall exterior surface than both the second interface surface and the peak interface surface.