Gas turbine engine component cooling passage and space eating core

Abstract

A gas turbine engine includes a structure that has walls that provide a cooling passage and a cooling surface. A non-ferrous obstruction is relative to the walls. The obstruction includes a portion spaced from the cooling surface to provide a gap which is configured to receive a cooling fluid.

What is claimed is: 
     
         1 . A gas turbine engine component comprising:
 a structure having walls providing a cooling passage having a cooling surface;   a non-ferrous obstruction arranged in the cooling passage engaging the cooling surface to locate the obstruction relative to the walls, and the obstruction including a portion spaced from the cooling surface to provide a gap configured to receive a cooling fluid.   
     
     
         2 . The gas turbine engine component according to  claim 1 , wherein the structure is an airfoil. 
     
     
         3 . The gas turbine engine component of  claim 2 , wherein the structure a turbine blade or a turbine vane. 
     
     
         4 . The gas turbine engine component according to  claim 1 , wherein the structure is a blade outer air seal. 
     
     
         5 . The gas turbine engine component according to  claim 1 , wherein the structure is a platform that supports an airfoil. 
     
     
         6 . The gas turbine engine component according to  claim 1 , wherein the structure is a combustor liner. 
     
     
         7 . The gas turbine engine component according to  claim 1 , wherein the structure is an exhaust liner. 
     
     
         8 . The gas turbine engine component according to  claim 1 , wherein the obstruction is arranged to block a flow of the cooling fluid through the cooling passage. 
     
     
         9 . The gas turbine engine component according to  claim 1 , wherein the obstruction includes a refractory metal. 
     
     
         10 . The gas turbine engine component according to  claim 1 , wherein the obstruction provides multiple gaps adjacent to the cooling surface. 
     
     
         11 . The gas turbine engine component according to  claim 1 , wherein the structure includes a nickel alloy, and the obstruction is provided by a material that is different than the nickel alloy. 
     
     
         12 . The gas turbine engine component according to  claim 1 , wherein the structure is formed by casting about a core, and a portion of the core forms the obstruction. 
     
     
         13 . The gas turbine engine component according to  claim 1 , wherein the structure includes multiple cooling passages and multiple obstructions, wherein one of the multiple obstructions is arranged in each of the multiple cooling passages. 
     
     
         14 . A core structure for providing a gas turbine engine cooling passage, comprising:
 first material provided on a second material and together provide a perimeter, the first material provided along multiple portions of the perimeter with the second material separating the multiple portions.   
     
     
         15 . The core structure according to  claim 14 , wherein the first and second materials are different than one another. 
     
     
         16 . The core structure according to  claim 15 , wherein the first material is ceramic. 
     
     
         17 . The core structure according to  claim 16 , wherein the second material includes a refractory metal. 
     
     
         18 . The core structure according to  claim 14 , wherein the second material is configured to remain in a cooling passage of a cast component. 
     
     
         19 . The core structure according to  claim 18 , wherein the second material is configured to provide an obstruction in the cooling passage. 
     
     
         20 . The core structure according to  claim 14 , wherein the perimeter is configured to provide a cooling surface of a cast component.