US 12,065,944 B1
Airfoils with mixed skin passageway cooling
Brandon W. Spangler, Vernon, CT (US); Dominic J. Mongillo, Jr., West Hartford, CT (US); and Jaime G. Ghigliotty Rosado, Cabo Rojo, PR (US)
Assigned to RTX Corporation, Farmington, CT (US)
Filed by Raytheon Technologies Corporation, Farmington, CT (US)
Filed on Mar. 7, 2023, as Appl. No. 18/118,706.
Int. Cl. F01D 5/18 (2006.01)
CPC F01D 5/186 (2013.01) [F05D 2220/323 (2013.01); F05D 2230/21 (2013.01); F05D 2230/60 (2013.01); F05D 2260/202 (2013.01); F05D 2300/17 (2013.01)] 25 Claims
OG exemplary drawing
 
1. A turbine engine airfoil element comprising:
an airfoil having:
a pressure side and a suction side;
a plurality of spanwise passageways including:
a plurality of main body passageways along a camber line; and
a plurality of skin passageways along the pressure side and comprising:
first skin passageways each having a plurality of film cooling outlets to the pressure side; and
second skin passageways each lacking film cooling outlets to the pressure side; and
linking passageways along the pressure side between the first skin passageways and the second skin passageways,
wherein:
for at least one of the second passageways two respective pluralities of said linking passageways connect to two said first passageways; and
the first skin passageways and second skin passageways are separately directly fed from one or more inlets of the airfoil element.