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)
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.