Combustor with distributed air and fuel mixing

Abstract

A combustor includes a liner defining a combustion chamber and receiving a fuel and air mixing body. The mixing body has a central fuel supply, and radial distribution passages communicating fuel from the central fuel supply radially outwardly relative to a central axis of the central fuel supply and to mixing passages. The radial distribution passages have injection ports in the mixing passages. The mixing passages extend from a rear face of the mixing body to an inner face facing into the combustion chamber. Air inlets in the mixing body communicate air into the mixing passages, and there is cellular material in the mixing passages at a location at which the fuel is injected into the mixing passages. A gas turbine engine is also disclosed.

What is claimed is: 
     
         1 . A combustor comprising:
 a liner defining a combustion chamber and receiving a fuel and air mixing body, the mixing body having a central fuel supply, and radial distribution passages communicating fuel from the central fuel supply radially outwardly relative to a central axis of the central fuel supply and to mixing passages, the radial distribution passages having injection ports in the mixing passages, the mixing passages extending from a rear face of the mixing body to an inner face facing into the combustion chamber, air inlets in the mixing body for communicating air into the mixing passages, and cellular material in the mixing passages at a location at which the fuel is injected into the mixing passages; and   wherein the radial distribution passages extend outwardly from the central fuel supply to communicate into each of a plurality of radially spaced sets of the mixing passages such that there is a single radial distribution passage bringing fuel to each of said mixing passages.   
     
     
         2 . The combustor set forth in  claim 1 , wherein a source of fuel is connected to the central fuel supply, and the source of fuel being gaseous hydrogen. 
     
     
         3 . The combustor as set forth in  claim 2 , wherein there are at least three radially spaced sets of the mixing passages with an innermost set, an intermediate set and an outermost set. 
     
     
         4 . The combustor as set forth in  claim 1 , wherein there are at least three radially spaced sets of the mixing passages with an innermost set, an intermediate set and an outermost set. 
     
     
         5 . The combustor as set forth in  claim 4 , wherein there are different cross-sectional areas for at least one of the at least three sets of radially spaced mixing passages. 
     
     
         6 . The combustor as set forth in  claim 5 , wherein the innermost set of the radially spaced mixing passages having a smaller cross-sectional area then at least one of the intermediate set and the outermost set. 
     
     
         7 . The combustor as set forth in  claim 6 , wherein both the outermost set and intermediate set of the radially spaced mixing passages having a greater cross-sectional area then the innermost set of the radially spaced mixing passages. 
     
     
         8 . The combustor as set forth in  claim 1 , wherein there are different cross-sectional areas for at least one of the plurality of radially spaced sets of the mixing passages. 
     
     
         9 . The combustor as set forth in  claim 8 , wherein an innermost set of the plurality of radially spaced jets having a smaller cross-sectional area then at least one other of the plurality of radially spaced sets. 
     
     
         10 . The combustor as set forth in  claim 9 , wherein at least two of the plurality of radially spaced sets having a greater cross-sectional area then the innermost set of radially spaced mixing passages. 
     
     
         11 . A gas turbine engine comprising:
 a compressor section and a turbine section;   a combustor intermediate said compressor section and said turbine section, the combustor including a liner defining a combustion chamber and receiving a fuel and air mixing body, the mixing body having a central fuel supply, and radial distribution passages communicating fuel from the central fuel supply radially outwardly relative to a central axis of the central fuel supply and to mixing passages, the radial distribution passages having injection ports in the mixing passages, the mixing passages extending from a rear face of the mixing body to an inner face facing into the combustion chamber, and there being air inlets in the mixing body for communicating air into the mixing passages, and cellular material in the mixing passages at a location at which the fuel is injected into the mixing passages; and   wherein the radial distribution passages extend outwardly from the central fuel supply to communicate into each of a plurality of radially spaced sets of the mixing passages such that there is a single radial distribution passage bringing fuel to each of said mixing passages.   
     
     
         12 . The gas turbine engine set forth in  claim 11 , wherein a source of fuel is connected to the central fuel supply, and the source of fuel being gaseous hydrogen. 
     
     
         13 . The gas turbine engine as set forth in  claim 12 , wherein there are at least three radially spaced sets of the mixing passages with an innermost set, an intermediate set and an outermost set. 
     
     
         14 . The gas turbine engine as set forth in  claim 11 , wherein there are at least three radially spaced sets of the mixing passages with an innermost set, an intermediate set and an outermost set. 
     
     
         15 . The gas turbine engine as set forth in  claim 14 , wherein there are different cross-sectional areas for at least one of the at least three sets of radially spaced mixing passages. 
     
     
         16 . The gas turbine engine as set forth in  claim 15 , wherein the innermost set of the radially spaced mixing passages having a smaller cross-sectional area then at least one of the intermediate set and outer set. 
     
     
         17 . The gas turbine engine as set forth in  claim 16 , wherein both the outermost set and intermediate set of the radially spaced mixing passages having a greater cross-sectional area then the innermost set of the radially spaced mixing passages. 
     
     
         18 . The gas turbine engine as set forth in  claim 11 , wherein there are different cross-sectional areas for at least one of the plurality of radially spaced sets of the mixing passages. 
     
     
         19 . The gas turbine engine as set forth in  claim 18 , wherein an innermost set of the plurality of radially spaced sets having a smaller cross-sectional area then at least one other of the plurality of radially spaced sets. 
     
     
         20 . The gas turbine engine as set forth in  claim 19 , wherein at least two of the plurality of radially spaced sets both the outermost set and having a greater cross-sectional area then the innermost set of radially spaced mixing passages.