Gas turbine engine serpentine cooling passage

Abstract

A gas turbine engine component includes a structure having a cooling passage providing upstream and downstream portions separated from one another by an inner wall and fluidly connected by a bend. The downstream portion includes an outer wall opposite the inner wall to provide a downstream region extending between the inner and outer walls. A turbulence promoter extends from the outer wall adjacent to the bend in the downstream portion. The turbulence promoter is absent from a stagnation region adjoining the inner wall adjacent to the bend in the downstream portion

What is claimed is: 
     
         1 . A gas turbine engine component comprising:
 a structure having a cooling passage providing upstream and downstream portions separated from one another by an inner wall and fluidly connected by a bend, the downstream portion included an outer wall opposite the inner wall to provide a downstream region extending between the inner and outer walls; and   a turbulence promoter extending from the outer wall adjacent to the bend in the downstream portion, the turbulence promoter absent from a stagnation region adjoining the inner wall adjacent to the bend in the downstream portion.   
     
     
         2 . The gas turbine engine component according to  claim 1 , wherein the downstream region includes a downstream width defined by the inner and outer walls, the downstream width corresponding to the sum of a stagnation width and a vena contracta width, wherein the stagnation region provides the stagnation width and the vena contracta region provides the turbulence promoter. 
     
     
         3 . The gas turbine engine component according to  claim 1 , wherein the bend is greater than 90°. 
     
     
         4 . The gas turbine engine component according to  claim 3 , wherein the bend is between 135° and 225°. 
     
     
         5 . The gas turbine engine component according to  claim 4 , wherein the bend is 180°. 
     
     
         6 . The gas turbine engine component according to  claim 1 , wherein the turbulence promoter is provided by chevron-shaped trip strips. 
     
     
         7 . The gas turbine engine component according to  claim 6 , wherein the chevron-shape is provided by multiple legs meeting at an apex, the apex pointing in the direction of incoming flow through the passage. 
     
     
         8 . The gas turbine engine component according to  claim 1 , wherein the turbulence promoter corresponds to a first turbulence promoter, and comprising a second turbulence promoter provided in the downstream region extending from the inner wall to the outer wall downstream from the first turbulence promoter. 
     
     
         9 . The gas turbine engine component according to  claim 1 , wherein the turbulence promoter corresponds to multiple turbulators comprising pins. 
     
     
         10 . The gas turbine engine component according to  claim 1 , wherein the gas turbine engine component comprises an airfoil including pressure and suction walls spaced apart from one another and joined at leading and trailing edges, the airfoil includes the cooling passage arranged between the pressure and suction walls. 
     
     
         11 . The gas turbine engine component according to  claim 10 , wherein the cooling passage extends in the radial direction from a root supporting the airfoil toward a tip of the airfoil. 
     
     
         12 . A gas turbine engine comprising:
 a compressor section and a turbine section, and a combustor section arranged between the compressor and turbine sections;   one of the compressor and turbine sections comprising an airfoil, the airfoil including:
 pressure and suction walls spaced apart from one another and joined at leading and trailing edges extending in a radial direction, the airfoil has a cooling passage arranged between the pressure and suction walls that extends toward a tip of the airfoil, the cooling passage providing upstream and downstream portions separated from one another by an inner wall and fluidly connected by a bend, the downstream portion includes an outer wall opposite the inner wall to provide a downstream region extending between the inner and outer walls; and 
 a turbulence promoter extending from the outer wall adjacent to the bend in the downstream portion, but the turbulence promoter absent from a stagnation region adjoining the inner wall adjacent to the bend in the downstream portion. 
   
     
     
         13 . The gas turbine engine according to  claim 12 , wherein the airfoil provides a turbine blade. 
     
     
         14 . The gas turbine engine according to  claim 12 , wherein the downstream region includes a downstream width defined by the inner and outer walls, the downstream width corresponding to the sum of a stagnation width and a vena contracta width, wherein the stagnation region provides the stagnation width and the vena contracta region provides the turbulence promoter. 
     
     
         15 . The gas turbine engine according to  claim 12 , wherein the bend is greater than 90°. 
     
     
         16 . The gas turbine engine according to  claim 15 , wherein the bend is 180°. 
     
     
         17 . The gas turbine engine according to  claim 12 , wherein the turbulence promoter is provided by chevron-shaped trip strips. 
     
     
         18 . The gas turbine engine according to  claim 12 , wherein the turbulence promoter corresponds to multiple turbulators comprising pins.