Gas turbine engine and fuel injection system

Abstract

One embodiment of the present invention is a unique gas turbine engine. Another embodiment is a unique fuel injection system for a gas turbine engine. Other embodiments include apparatuses, systems, devices, hardware, methods, and combinations for gas turbine engines and fuel injection systems for gas turbine engines. Further embodiments, forms, features, aspects, benefits, and advantages of the present application will become apparent from the description and figures provided herewith.

1 . A gas turbine engine, comprising:
 a compressor system;   a turbine system; and   a combustion system fluidly disposed between the compressor system and the turbine system, the combustion system including a combustion liner and a fuel injection system operative to inject fuel into the combustion liner, wherein the fuel injection system includes:   a pilot injection module having a pilot nozzle and a pilot swirler for the pilot nozzle, wherein the pilot swirler is operative to induce swirl to enhance mixing of fuel and air for the pilot injection module; and   a main injection module disposed radially outward of the pilot injection module, wherein the main injection module includes a main fuel injector; a main swirler; and a deswirler, wherein the main fuel injector includes a plurality of nozzles operative to discharge fuel radially outward; wherein the main swirler is operative to induce swirl to enhance mixing of fuel and air for the main fuel injector; and wherein the deswirler is operative to reduce swirl induced by the main swirler.   
     
     
         2 . The gas turbine engine of  claim 1 , wherein the deswirler is located radially outward of the main swirler. 
     
     
         3 . The gas turbine engine of  claim 1 , wherein the main fuel injector includes a plurality of plain-jet nozzles. 
     
     
         4 . The gas turbine engine of  claim 3 , further comprising a main fuel manifold, wherein at least one of the plain-jet nozzles extends outward in a radial direction from the main fuel manifold. 
     
     
         5 . The gas turbine engine of  claim 3 , wherein at least one of the plain-jet nozzles has a discharge opening disposed in the main swirler. 
     
     
         6 . The gas turbine engine of  claim 1 , further comprising a first fuel supply line; and a second fuel supply line that is fluidly independent of the first fuel supply line, wherein the pilot nozzle is fluidly coupled to the first fuel supply line; and wherein the main fuel injector is fluidly coupled to the second fuel supply line. 
     
     
         7 . The gas turbine engine of  claim 1 , wherein the fuel injection system is configured to selectively supply fuel to one or both of the pilot injection module and the main injection module. 
     
     
         8 . A fuel injection system for a gas turbine engine, comprising:
 a main injection module including a plurality of plain-jet nozzles; a main swirler;   and a deswirler; wherein at least one of the plain-jet nozzles is operative to discharge fuel radially outward; wherein the main swirler is operative to induce swirl to enhance mixing of fuel and air for the main injection module; and wherein the deswirler is operative to reduce swirl induced by the main swirler; and   a pilot injection module disposed radially inward of the main injection module, wherein the pilot injection module includes a pilot nozzle and a pilot swirler for the pilot nozzle, wherein the pilot swirler is operative to induce swirl to enhance mixing of fuel and air for the pilot injection module.   
     
     
         9 . The fuel injection system of  claim 8 , wherein the deswirler includes a non-swirling air passage. 
     
     
         10 . The fuel injection system of  claim 8 , wherein the main injection module includes an annular discharge nozzle for discharging a fuel air mixture. 
     
     
         11 . The fuel injection system of  claim 8 , wherein the main injection module includes a discharge nozzle for discharging a fuel air mixture, further comprising a plurality of air injection openings positioned to inject air into the main injection module upstream of the discharge nozzle. 
     
     
         12 . The fuel injection system of  claim 8 , further comprising a ramp configured to direct an air fuel mixture from the main injection module in a radially outward direction. 
     
     
         13 . The fuel injection system of  claim 12 , wherein the ramp is conical. 
     
     
         14 . The fuel injection system of  claim 8 , further comprising a separating member disposed around the pilot nozzle and positioned between the pilot nozzle and the main injection module. 
     
     
         15 . The fuel injection system of  claim 14 , wherein the separating member is configured to shield the pilot nozzle from combustion heat. 
     
     
         16 . The fuel injection system of  claim 8 , wherein the at least one of the plain-jet nozzles is configured to inject fuel directly into the main swirler. 
     
     
         17 . A fuel injection system for a gas turbine engine, comprising:
 a pilot injection module having a pilot nozzle operative to produce a pilot combustion zone; and   a main injection module having a fuel distribution manifold; a plurality of main nozzles extending from the fuel distribution manifold for injecting fuel; a main swirler; and a deswirler, wherein the main swirler is operative to induce swirl into fuel and air in the main injection module; and wherein the deswirler is operative to reduce swirl induced by the main swirler.   
     
     
         18 . The fuel injection system of  claim 17 , further comprising a heat shield disposed around the pilot injection module and positioned between the pilot injection module and the main injection module. 
     
     
         19 . The fuel injection system of  claim 17 , wherein the main nozzles are plain-jet nozzles oriented with a directional component extending radially outward of the pilot nozzle. 
     
     
         20 . The fuel injection system of  claim 17 , wherein the main injection module is configured to produce a main combustion zone disposed radially outward of the pilot combustion zone.