Secondary Combustion System

Abstract

The present application provides a secondary combustion system for introducing a fuel/air mixture into a flow of combustion gases in a combustor of a gas turbine engine. The secondary combustion system may include a manifold ring and a number of injectors extending from the manifold ring. Each of the injectors may include a number of jets in communication with the manifold ring. One or more of the jets may include an angled configuration for the introduction of the fuel/air mixture into the flow of combustion gases at an angle.

We claim: 
     
         1 . A secondary combustion system for introducing a fuel/air mixture into a flow of combustion gases in a combustor of a gas turbine engine, comprising:
 a manifold ring; and   a plurality of injectors extending from the manifold ring;   the plurality of injectors comprising a plurality of jets in communication with the manifold ring;   wherein one or more of the plurality of jets comprises an angled configuration for the introduction of the fuel/air mixture into the flow of combustion gases at an angle.   
     
     
         2 . The secondary combustion system of  claim 1 , wherein the manifold ring comprises an air manifold and a fuel manifold. 
     
     
         3 . The secondary combustion system of  claim 1 , wherein the angled configuration comprises an upstream configuration. 
     
     
         4 . The secondary combustion system of  claim 1 , wherein the angled configuration comprises a downstream configuration. 
     
     
         5 . The secondary combustion system of  claim 1 , wherein each of the plurality of jets comprises an entrance with an entrance diameter and an exit with an exit diameter. 
     
     
         6 . The secondary combustion system of  claim 5 , wherein the entrance diameter is equal to or greater than the exit diameter. 
     
     
         7 . The secondary combustion system of  claim 5 , wherein the entrance diameter is equal to or lesser than the exit diameter. 
     
     
         8 . The secondary combustion system of  claim 1 , further comprising an auxiliary injection system in communication with the plurality of injectors. 
     
     
         9 . The secondary combustion system of  claim 8 , wherein the auxiliary injection system is in communication with an auxiliary fuel compressor, an auxiliary air compressor, and/or an auxiliary diluent compressor. 
     
     
         10 . The secondary combustion system of  claim 8 , wherein the auxiliary injection system is in communication with a fuel reformer and a steam or catalytic component. 
     
     
         11 . The secondary combustion system of  claim 8 , wherein the auxiliary injection system is in communication with a low BTU gasifier. 
     
     
         12 . A secondary combustion system for introducing a fuel/air mixture into a flow of combustion gases in a combustor of a gas turbine engine, comprising:
 a manifold ring; and   a plurality of injectors extending from the manifold ring;   the plurality of injectors comprising a plurality of jets in communication with the manifold ring;   wherein the plurality of jets comprises an entrance with an entrance diameter and an exit with an exit diameter; and   wherein the entrance diameter is greater than the exit diameter.   
     
     
         13 . The secondary combustion system of  claim 12 , wherein one or more of the plurality of jets comprises an angled configuration for the introduction of the fuel/air mixture into the flow of combustion gases at an angle. 
     
     
         14 . The secondary combustion system of  claim 13 , further comprising an auxiliary injection system in communication with the injectors and wherein the auxiliary injection system is in communication with an auxiliary fuel compressor, an auxiliary air compressor, an auxiliary diluent compressor, a fuel reformer, a steam or catalytic component, and/or a low BTU gasifier. 
     
     
         15 . A secondary combustion system for introducing a fuel/air mixture into a flow of combustion gases in a combustor of a gas turbine engine, comprising:
 a manifold ring;   a plurality of injectors extending from the manifold ring;   the plurality of injectors comprising a plurality of jets in communication with the manifold ring; and   an auxiliary injection system in communication with the injectors.   
     
     
         16 . The secondary combustion system of  claim 15 , wherein the auxiliary injection system is in communication with an auxiliary fuel compressor, an auxiliary air compressor, and/or an auxiliary diluent compressor. 
     
     
         17 . The secondary combustion system of  claim 15 , wherein the auxiliary injection system is in communication with a fuel reformer and a steam or catalytic component. 
     
     
         18 . The secondary combustion system of  claim 15 , wherein the auxiliary injection system is in communication with a low BTU gasifier. 
     
     
         19 . The secondary combustion system of  claim 15 , wherein one or more of the plurality of jets comprise an angled configuration for the introduction of the fuel/air mixture into the flow of combustion gases at an angle. 
     
     
         20 . The secondary combustion system of  claim 15 , wherein the plurality of jets comprises an entrance with an entrance diameter and an exit with an exit diameter and wherein the entrance diameter is equal to or greater than the exit diameter.