US 9,810,084 B1
Gas turbine engine turbine vane baffle and serpentine cooling passage
Brandon W. Spangler, Vernon, CT (US); Ryan Alan Waite, South Windsor, CT (US); Steven Bruce Gautschi, Naugatuck, CT (US); and Benjamin F. Hagan, Manchester, CT (US)
Assigned to UNITED TECHNOLOGIES CORPORATION, Farmington, CT (US)
Filed by United Technologies Corporation, Hartford, CT (US)
Filed on Feb. 6, 2015, as Appl. No. 14/615,509.
Int. Cl. F01D 9/06 (2006.01); F01D 25/14 (2006.01); F01D 25/12 (2006.01)
CPC F01D 9/065 (2013.01) [F01D 25/12 (2013.01); F01D 25/14 (2013.01); F05D 2240/126 (2013.01); F05D 2260/20 (2013.01); F05D 2260/202 (2013.01); F05D 2260/204 (2013.01)] 20 Claims
OG exemplary drawing
 
1. An airfoil for a gas turbine engine comprising:
pressure and suction side walls joined to one another at leading and trailing edges, the pressure and suction side walls surround an airfoil cavity and provide an exterior airfoil surface;
a baffle arranged in the airfoil cavity, the baffle includes a supply hole;
ribs extend from the pressure and suction side walls into the airfoil cavity and engage the baffle, the ribs configured to provide a serpentine cooling passage between the baffle and at least one of the pressure and suction side walls, the serpentine cooling passage has first and second passes joined by a bend, the ribs form a film cooling cavity between the first and second passes, and the supply hole fluidly connects the baffle to the film cooling cavity; and
film cooling holes extend through the at least one of the pressure and suction side walls, the film cooling holes in fluid communication with the film cooling cavity.