Dual-wall impingement, convection, effusion combustor tile

Abstract

A gas turbine engine includes a combustor having a dual-wall impingement convention effusion combustor tile assembly. The dual-wall tile assembly provides a cooling air flow channel and attachments for securing the tile to the cold skin liner of the combustor. Cooling is more efficient in part due to the dual wall construction and in part due to reduced parasitic leakage, and the design is less sensitive to attachment features which operate at lower temperatures.

1 .- 20 . (canceled) 
     
     
         21 . A gas turbine engine having a combustor comprising:
 a liner having an inner surface, the inner surface having a plurality of arcuately shaped surfaces; and   a plurality of tile assemblies, each tile assembly including a first wall element and a second wall element spaced radially from the first wall element, each of the plurality of tile assemblies secured to the inner surface of the liner via at least one securing member for securing each tile assembly to the liner, each tile assembly forming a cooling plenum between the inner surface of the liner and the first wall element;   wherein a first tile assembly of the plurality of tile assemblies is positioned on a first surface of the plurality of arcuately shaped surfaces, and a second tile assembly of the plurality of tile assemblies is positioned on a second surface of the arcuately shaped surfaces adjacent to and radially offset from the first surface, such that a first edge of the first tile assembly is positioned proximate a second edge of the second tile assembly and the first edge and the second edge are radially offset from each other forming a radial gap.   
     
     
         22 . The gas turbine of  claim 21 , further comprising a plurality of pedestal members positioned between the first wall element and the second wall element, such that an interconnected plurality of air channels is formed between the first wall element and the second wall element in each tile assembly. 
     
     
         23 . The gas turbine of  claim 22 , wherein each tile assembly of the plurality of tile assemblies includes the first wall element formed as a first substantially planar or curved member, the second wall element formed respectively as a second substantially planar or curved member, wherein the plurality of pedestal members form spacers for offsetting the first substantially planar or curved member from the second substantially planar or curved member. 
     
     
         24 . The gas turbine of  claim 23 , wherein the at least one securing member is connected to one of the first substantially planar or curved member and the second substantially planar or curved member. 
     
     
         25 . The gas turbine of  claim 22 , wherein each pedestal member of the plurality of pedestal members is square-shaped. 
     
     
         26 . The gas turbine of  claim 21 , wherein the first wall element includes a plurality of cooling entry holes that are arranged on the first wall element in a first array comprising multiple rows of the cooling entry holes, and the second wall element includes a plurality of exit holes that are arranged on the second wall element in a second array comprising multiple rows of the exit holes. 
     
     
         27 . The gas turbine of  claim 26 , wherein the cooling plenum passes air orthogonally from the cooling plenum through the plurality of cooling entry holes and to the interconnected plurality of air channels between the first wall element and the second wall element, and through the plurality of exit holes. 
     
     
         28 . The gas turbine of  claim 27 , further comprising a rail formed on each tile assembly and extending around an outer perimeter of each tile assembly, the rail extending from the first wall element and engaging the inner surface of the liner to form the cooling plenum of each tile assembly. 
     
     
         29 . The gas turbine of  claim 21 , wherein each tile assembly of the plurality of tile assemblies is a single piece tile. 
     
     
         30 . The gas turbine of  claim 21 , wherein each tile assembly is formed of a ceramic composite material or a metallic material. 
     
     
         31 . The gas turbine of  claim 21 , wherein each of the first wall element and second wall element of each tile assembly includes a small dilution port and/or a large dilution port that is larger than the small dilution port. 
     
     
         32 . The gas turbine of  claim 21 , wherein the at least one securing member further comprises a mounting stud passing through the liner and secured at one end to one of the first wall element and second wall element, the mounting stud secured at another end to a wall of the liner. 
     
     
         33 . The gas turbine of  claim 21 , wherein the single piece tile is a single piece cast tile. 
     
     
         34 . The gas turbine of  claim 21 , wherein the single piece tile is a direct metal laser sintered tile. 
     
     
         35 . The gas turbine of  claim 21 , wherein the plurality of pedestal members is a two-dimensional array of pedestals arranged in a pattern forming the interconnected plurality of air channels, the two-dimensional array of pedestals forming multiple rows of pedestals positioned side-by-side and extending in a first direction, and forming multiple rows of pedestals positioned side-by-side and extending in a second direction that is approximately orthogonal to the first direction. 
     
     
         36 . The gas turbine of  claim 21 , wherein the first surface and the second surface are stepped forming a stepped location between the first surface and the second surface, and the first edge and the second edge are proximate the stepped location such that the radial gap is formed at the stepped location. 
     
     
         37 . A combustor for a gas turbine engine, comprising:
 a liner having an inner surface, the inner surface having arcuately shaped surfaces;   two tile assemblies, each tile assembly including a first wall element and a second wall element spaced radially from the first wall element, each of the plurality of tile assemblies secured to the inner surface of the liner via a respective securing member for securing each tile assembly to the liner, each tile assembly forming a cooling plenum between the inner surface of the liner and the first wall element;   wherein one of the two tile assemblies is positioned on a first surface of the arcuately shaped surfaces, and another of the two tile assemblies is positioned on a second surface of the arcuately shaped surfaces adjacent to and radially offset from the first surface, such that one edge of one of the two tile assemblies is positioned proximate one edge of the other of the two tile assemblies, and the edges are radially offset from each other forming a radial gap.   
     
     
         38 . The combustor of  claim 37 , further comprising a plurality of pedestal members positioned between the first wall element and the second wall element, such that an interconnected plurality of air channels is formed between the first wall element and the second wall element in each tile assembly. 
     
     
         39 . The combustor of  claim 38 , wherein each tile assembly of the two tile assemblies includes the first wall element formed as a first substantially planar or curved member, the second wall element formed respectively as a second substantially planar or curved member, wherein the plurality of pedestal members form spacers for offsetting the first substantially planar or curved member from the second substantially planar or curved member. 
     
     
         40 . The combustor  claim 39 , wherein the respective securing member is connected to one of the first substantially planar or curved member and the second substantially planar or curved member.