Integrated casting core-shell structure for making cast component with novel cooling hole architecture

Abstract

Integrated core-shell investment casting molds that provide tongue or groove structures corresponding, respectively, to groove or tongue structures in the surface of the turbine blade or stator vane, including in locations that are otherwise inaccessible provide a pathway to restrict cooling flow between turbine blades to the flowpath.

What is claimed is: 
     
         1 . A first turbine blade or stator, comprising:
 one or more surfaces having one or more grooves and/or tongues thereon, the one or more grooves and/or tongues adapted to fit with one or more complementary tongues and/or grooves on an object, wherein the grooves and/or tongues of the first turbine blade or stator are seal slots adapted to contain seals to restrict cooling flow from the first turbine blade or stator to a second turbine blade or stator.   
     
     
         2 . The first turbine blade or stator of  claim 1 , wherein the first turbine blade or stator is a single crystal metal turbine blade or stator. 
     
     
         3 . The first turbine blade or stator of  claim 1 , wherein the object is the second turbine blade or stator. 
     
     
         4 . The first turbine blade or stator of  claim 1 , wherein the first turbine blade or stator comprises a platform, the platform having a first lateral end and a second lateral end opposed to the first lateral end, wherein a tongue of the one or more grooves and/or tongues of the first turbine blade or stator is placed into the first lateral end and a groove of the one or more grooves and/or tongues of the first turbine blade or stator is placed into the second lateral end. 
     
     
         5 . The first turbine blade or stator of  claim 4 , wherein the seal slots are located on the platform or on a fore or aft skirt. 
     
     
         6 . The first turbine blade or stator of  claim 1 , wherein the seal slots are located on a pressure side of the first turbine blade or stator. 
     
     
         7 . The first turbine blade or stator of  claim 1 , wherein the seal slots are located on a suction side of the first turbine blade or stator. 
     
     
         8 . The first turbine blade or stator of  claim 1 , wherein the object is a gas turbine airfoil. 
     
     
         9 . The first turbine blade or stator of  claim 8 , wherein the gas turbine airfoil is cast with one or more cooling holes connecting an interior cavity of the first turbine blade or stator to an external surface thereof. 
     
     
         10 . The first turbine blade or stator of  claim 8 , wherein the gas turbine airfoil contains a baffle having a plurality of holes. 
     
     
         11 . The first turbine blade or stator of  claim 1 , wherein the object is a blade shank containing a cast-in cooling hole. 
     
     
         12 . The first turbine blade or stator of  claim 1 , wherein the object is a turbine blade platform containing a cast-in cooling hole. 
     
     
         13 . The first turbine blade or stator of  claim 12 , wherein the turbine blade platform comprises a reservoir. 
     
     
         14 . The first turbine blade or stator of  claim 13 , further comprising one or more cooling holes connecting the reservoir to an outer surface of the first turbine blade or stator.