Engine component with set of cooling holes

Abstract

An apparatus and method an engine component for a turbine engine comprising an outer wall bounding an interior and defining a pressure side and an opposing suction side, with both sides extending between a leading edge and a trailing edge to define a chord-wise direction, and extending between a root and a tip to define a span-wise direction, at least one cooling passage located within the interior, a set of cooling holes having an inlet fluidly coupled to the cooling passage, an outlet located on one of the pressure side or suction side, with a connecting passage fluidly coupling the inlet to the outlet.

1 . An airfoil for a turbine engine comprising:
 an outer wall bounding an interior and defining a pressure side and an opposing suction side, with both sides extending between a leading edge and a trailing edge to define a chord-wise direction, and extending between a root and a tip to define a span-wise direction;   at least one cooling passage located within the interior;   a set of cooling holes having an inlet fluidly coupled to the cooling passage, an outlet located on one of the pressure side or suction side, with a connecting passage having a curvilinear centerline fluidly coupling the inlet to the outlet, and the connecting passage having a portion extending along the other of the pressure side or suction side.   
     
     
         2 . The airfoil of  claim 1  wherein the set of cooling holes is a first and second set of cooling holes wherein the first set of cooling holes has a first inlet fluidly coupled to the cooling passage and a first outlet located on the pressure side and the second set of cooling holes has a second inlet fluidly coupled to the cooling passage and a second outlet located on the suction side. 
     
     
         3 . The airfoil of  claim 1  wherein the at least one cooling passage is multiple cooling passages separated by an interior wall and the inlet is located along the interior wall. 
     
     
         4 . The airfoil of  claim 2  wherein a third set of cooling holes includes a third outlet proximate the leading edge along the outer wall. 
     
     
         5 . The airfoil of  claim 4  wherein at least one of the first, the second, or the third sets of cooling holes further comprises an interior surface having one of a smooth, jagged, or patterned profile. 
     
     
         6 . The airfoil of  claim 1  wherein the cooling passage is a leading edge cooling passage. 
     
     
         7 . The airfoil of  claim 1  wherein the set of cooling holes is multiple cooling holes. 
     
     
         8 . The airfoil of  claim 1  wherein at least some of the connecting passages include a transition location from which a diffusing section extends. 
     
     
         9 . The airfoil of  claim 8  wherein the transition location is located interiorly of the leading edge and is coincident with a camber line of the airfoil. 
     
     
         10 . The airfoil of  claim 8  wherein the transition location is located interiorly of one of the pressure or suction sides. 
     
     
         11 . The airfoil of  claim 1  further comprising a trench extending along one of the pressure or suction sides and located coincident with the outlets. 
     
     
         12 . The airfoil of  claim 1  wherein the cooling passage further comprises a thickened wall portion and the connecting passage passes through the thickened wall portion. 
     
     
         13 . The airfoil of  claim 12  wherein the thickened wall portion is formed to accommodate a full length of the set of cooling holes as it curves within the outer wall. 
     
     
         14 . The airfoil of  claim 13  wherein the thickened wall portion is a turbulator. 
     
     
         15 . The airfoil of  claim 1  wherein the connecting passage comprises a fork shape or shingled exit. 
     
     
         16 . The airfoil of  claim 1  wherein the set of cooling holes is a first and second set of cooling holes forming a crisscross pattern when viewed along a sight line extending from the leading edge in the span-wise direction. 
     
     
         17 . The airfoil of  claim 1  wherein the set of cooling holes is a first set of cooling holes alternating in location with respect to a second set of cooling holes with respect to the span-wise direction. 
     
     
         18 . An engine component for a turbine engine comprising:
 an outer wall bounding an interior and defining a pressure side and an opposing suction side, with both sides extending between a leading edge and a trailing edge to define a chord-wise direction, and extending between a root and a tip to define a span-wise direction;   at least one cooling passage located within the interior;   a set of cooling holes having an inlet fluidly coupled to the cooling passage, an outlet located on one of the pressure side or suction side, with a connecting passage having a curvilinear centerline fluidly coupling the inlet to the outlet, and the connecting passage having a portion extending along the other of the pressure side or suction side.   
     
     
         19 . The engine component of  claim 18  wherein the set of cooling holes is a first and second set of cooling holes wherein the first set of cooling holes has a first inlet fluidly coupled to the cooling passage and a first outlet located on the pressure side and the second set of cooling holes has a first inlet fluidly coupled to the cooling passage and a second outlet located on the suction side. 
     
     
         20 . The engine component of  claim 19  wherein a third set of cooling holes includes an outlet proximate the leading edge along the outer wall. 
     
     
         21 . The engine component of  claim 20  wherein at least one of the first, the second, or the third sets of cooling holes further comprises an interior surface having one of a smooth, jagged, or patterned profile. 
     
     
         22 . The engine component of  claim 18  further comprising a trench extending along one of the pressure or suction sides and located coincident with the outlets. 
     
     
         23 . The engine component of  claim 18  wherein the cooling passage further comprises a thickened wall portion and the connecting passage passes through the thickened wall portion. 
     
     
         24 . The engine component of  claim 18  wherein the set of cooling holes is a first and second set of cooling holes forming a crisscross pattern when viewed along a sight line extending from the leading edge in the span-wise direction. 
     
     
         25 . The engine component of  claim 18  wherein the set of cooling holes is a first set of cooling holes alternating in location with respect to a second set of cooling holes with respect to the span-wise direction. 
     
     
         26 . A method of cooling an engine component having an outer wall bounding an interior and defining a pressure side and an opposing suction side, with both sides extending between a leading edge and a trailing edge to define a chord-wise direction, and extending between a root and a tip to define a span-wise direction, where the leading edge extends in the span-wise direction and separates the pressure side from the suction side, the method comprising:
 flowing a cooling fluid through at least one cooling hole along one of the pressure or suction sides;   
       crossing the leading edge with the cooling fluid; and 
       emitting the cooling fluid through an outlet on the other of the pressure or suction side. 
     
     
         27 . The method of  claim 26  wherein the cooling fluid is introduced into an inlet to the cooling hole located within the interior. 
     
     
         28 . The method of  claim 26  further comprising:
 flowing a first portion of cooling fluid through at least one cooling hole along the pressure side; 
 emitting the first portion of cooling fluid through an outlet on the suction side; 
 flowing a second portion of cooling fluid through another cooling hole along the suction side; 
 crossing the leading edge with the second portion of cooling fluid; and 
 emitting the second portion of cooling fluid through an outlet on the pressure side. 
 
     
     
         29 . The method of  claim 26  further comprising flowing a cooling fluid through a stagnation cooling hole having an outlet located proximate the leading edge. 
     
     
         30 . The method of  claim 26  wherein the flowing a cooling fluid further comprises flowing the cooling fluid through one of a blade, strut, service tube, or vane.