Turbomachine combustors having different flow paths

Abstract

An example turbomachine assembly includes a first combustor configured to combust fuel and compressed air and a second combustor configured to combust fuel and compressed air. Flow moves through the first combustor in a first direction and flow moves though the second combustor in a second direction different than the first direction. The first combustor is axially spaced from the second combustor.

1 . A turbomachine assembly, comprising:
 a first combustor configured to combust fuel and compressed air; and   a second combustor configured to combust fuel and compressed air, wherein flow moves through the first combustor in a first direction and flow moves though the second combustor in a second direction different than the first direction, the first combustor axially spaced from the second combustor.   
     
     
         2 . The turbomachine assembly of  claim 1 , wherein products of combustion from the first combustor are expanded to drive a first spool, and products of combustion from the second combustor are expanded to drive a second spool different than the first spool. 
     
     
         3 . The turbomachine assembly of  claim 1 , including a fuel manifold configured to supply fuel to both the first combustor and the second combustor. 
     
     
         4 . The turbomachine assembly of  claim 1 , wherein the first direction is opposite a general direction of flow through the turbomachine, the general direction of flow extending from a fan section of the turbomachine to an exhaust section of the turbomachine. 
     
     
         5 . The turbomachine assembly of  claim 1 , wherein the first combustor comprises a plurality of reverse flow combustors annularly distributed about an axis of the turbomachine. 
     
     
         6 . The turbomachine assembly of  claim 1 , wherein the turbomachine is a gas turbine engine. 
     
     
         7 . The turbomachine assembly of  claim 1 , wherein a compressor directly provides compressed air to the first combustor, and a turbine section directly provides compressed air to the second combustor. 
     
     
         8 . The turbomachine assembly of  claim 7 , wherein the turbine section includes variable vanes. 
     
     
         9 . A turbomachine assembly, comprising:
 a compressor section;   a first combustor section that receives a flow of compressed fluid from the compressor section;   a first turbine section that receives a product of combustion from the first combustor section;   a second combustor section that receives a flow of compressed fluid from the first turbine section; and   a second turbine section that receives a product of combustion from the second combustor section, wherein flow moves through the first combustor in a first direction and flow moves though the second combustor in a second direction different than the first direction.   
     
     
         10 . The turbomachine assembly of  claim 9 , wherein the first turbine section is a higher pressure turbine than the second turbine section. 
     
     
         11 . The turbomachine assembly of  claim 9 , wherein the first turbine section drives a first spool, and the second turbine section drives a second spool different than the first spool. 
     
     
         12 . The turbomachine assembly of  claim 11 , wherein the first spool is rotatably coupled to a high-pressure compressor of the compressor section, and the second spool is rotatably coupled to a low-pressure compressor of the compressor section. 
     
     
         13 . The turbomachine assembly of  claim 12 , including a third turbine section that is rotatably coupled to a fan with a third spool. 
     
     
         14 . The turbomachine assembly of  claim 9 , including a common manifold configured to supply fuel to both the first combustor and the second combustor. 
     
     
         15 . The turbomachine assembly of  claim 9 , wherein the first direction is opposite the second direction. 
     
     
         16 . A method of operating a turbomachine, comprising:
 moving a mixture of fuel and compressed air through a first combustor section in a first direction; and   moving a mixture of fuel and compressed air through a second combustor section in a second direction different than the first direction.   
     
     
         17 . The method of  claim 16 , communicating products of combustion from the first combustor section to a turbine section and communicating compressed air from the turbine section to the second combustor section. 
     
     
         18 . The method of  claim 16 , communicating fuel to the first combustor section and the second combustor section using a common manifold. 
     
     
         19 . The method of  claim 16 , driving a first turbine section with the first combustor section and driving a second turbine section with the second combustor section, the first turbine section and the second turbine section configured to drive different spools.