W501 d5/d5a df42 combustion system

Abstract

An improved combustion section for a gas turbine engine is disclosed. A fuel nozzle includes new features which provide improved injection patterns of oil fuel and cooling water, resulting in better control of combustion gas temperature and NOx emissions, and eliminated impingement of cooling water on walls of the combustor. A new combustor includes a plate-fin design which provides improved cooling, while the combustor also makes more efficient use of available cooling air and has an improved component life. A new transition component has a smoother shape which reduces stagnation of combustion gas flow and impingement of combustion gas on transition component walls, improved materials and localized thickness increases for better durability, and improved cooling features for more efficient usage of cooling air.

What is claimed is: 
     
         1 . A gas turbine engine comprising;
 a compressor section;   a plurality of fuel nozzles in a combustion section, said fuel nozzles providing fuel for combustion, where each of said fuel nozzles includes one or more fluid atomizing device with orifices configured to dispense liquid fuel and water in different atomized spray patterns and an integral heat shielding device;   a plurality of combustors in the combustion section, each of said combustors receiving the fuel from one of the fuel nozzles and burning the fuel, where each of said combustors includes a plurality of air-splitting cooling systems, and a slip-joint cross-flame duct for connecting adjacent combustors;   a plurality of transition components in the combustion section, each of said transition components receiving combustion gases from one of the combustors and delivering the combustion gases to a turbine section, where each of said transition components includes a reverse bulk flow effusion cooling system, and transition cylinder cooling system; and   a turbine section including a plurality of rotor assemblies, where each rotor assembly includes a rotor disk and a plurality of turbine blades.   
     
     
         2 . The gas turbine engine of  claim 1  wherein each of the fuel nozzles includes;
 an annular fuel-injecting lance comprising a first fluid circuit and a second fluid circuit, 
 wherein the first fluid circuit is centrally disposed within the lance, wherein the first fluid circuit extends along a longitudinal axis of the lance to convey a first fluid to a downstream end of the lance, 
 wherein the second fluid circuit is annularly disposed about the first fluid circuit to convey a second fluid to the downstream end of the lance, wherein one of the first and second fluids comprises a liquid fuel conveyed by one of the first and second fluid circuits during a liquid fuel operating mode of the combustion turbine engine, 
 wherein the other of the first and second fluids conveyed by the other of the first and second fluid circuits comprises a selectable non-fuel fluid; and 
 an atomizer disposed at the downstream end of the lance, the atomizer having a first injection orifice responsive to the first fluid circuit to form a first atomized injection cone, the atomizer further having a second injection orifice responsive to the second fluid circuit to form a second atomized injection cone, wherein the first and second injection orifices of the atomizer are respectively configured so that the first and second injection cones formed with the atomizer comprise concentric cones that intersect with one another over a predefined angular range. 
 
     
     
         3 . The gas turbine engine of  claim 1  wherein each of the fuel nozzles includes;
 a nozzle cap disposed at a downstream end of the fuel nozzle; 
 a heat shield mounted onto the nozzle cap; and 
 a plurality of cooling channels arranged between a forward face of the nozzle cap and a corresponding back side of the heat shield. 
 
     
     
         4 . The gas turbine engine of  claim 1  wherein each of the fuel nozzles includes a nozzle cap disposed at a downstream end of the fuel nozzle, wherein the nozzle cap comprises a bore arranged to accommodate a downstream portion of a fluid-injecting lance that extends along a longitudinal axis of the nozzle, the downstream portion of the fluid-injecting lance comprising a centrally-located atomizer to form a first atomized injection cone. 
     
     
         5 . The gas turbine engine of  claim 1  wherein each of the combustors includes a combustor basket including a basket liner having an input end receiving air and fuel and an output end through which a hot working gas exits the combustor basket, said combustor basket further including a double-wall exit cone coupled to the basket liner at the output end, said exit cone including an inner cone wall and an outer cone wall defining an annular exit cone channel therebetween, each of the inner cone wall and the outer cone wall including an inner surface and an outer surface, where the outer surface of the inner wall and the inner surface of the outer wall face the cone channel, said combustor basket further including a splash plate mounted to the outer wall and extending parallel to the output end of the basket liner so as to define an annular splash plate channel therebetween, wherein the outer cone wall is attached to the basket so as to allow air to be split between the exit cone and the splash plate. 
     
     
         6 . The gas turbine engine of  claim 1  wherein each of the combustors includes;
 a combustor basket formed from at least one outer wall defining a combustor chamber; 
 at least one platefin cooling system formed from a platefin member positioned radially inward from an inner surface of the at least one outer wall forming the combustor basket; 
 at least one first rib section which extends between the platefin member and the combustor basket, thereby separating a first cooling circuit from a second cooling circuit, wherein the first cooling circuit is upstream from the second cooling circuit; 
 wherein the first cooling circuit includes at least one first outlet positioned in the platefin member upstream from the at least one first rib section; and 
 wherein the second cooling circuit includes at least one second outlet positioned downstream from the at least one first rib section. 
 
     
     
         7 . The gas turbine engine of  claim 1  wherein the cross-flame duct comprises:
 a first duct extending along a longitudinal axis and configured to be coupled to a first combustor, the first duct comprising; 
 a first outer sleeve having a first end configured to be coupled to the first combustor and a second end on an opposite end from the first end, and 
 a first inner housing positioned within the first outer sleeve and having a first end adjacent the first combustor and a second end extending from the second end of the first outer sleeve; 
 a first cooling chamber positioned between an outer surface of the first inner housing and an inner surface of the first outer sleeve; 
 a second duct extending along the longitudinal axis and configured to be coupled to a second combustor, wherein the second duct is configured to slidably receive the first duct, the second duct comprising; 
 a second outer sleeve having a first end configured to be coupled to the second combustor and extending toward the first duct to slidably receive the second end of the first inner housing within a second end of the second outer sleeve, and 
 a second inner housing positioned within the second outer sleeve and having a first end adjacent the second combustor and a second end extending toward the second end of the second outer sleeve; and 
 a second cooling chamber positioned between an outer surface of the second inner housing and an inner surface of the second outer sleeve. 
 
     
     
         8 . The gas turbine engine of  claim 1  wherein each of the transition components includes a first end mounted to one of the combustors and receiving a hot working fluid, a second end opposite to the first end outputting the hot working fluid, and a transition section between the first end and the second end having an outer wall defining a chamber therein through which the hot working fluid flows, said outer wall having an inside surface and an outside surface, said transition section including a plurality of first effusion cooling holes extending through the outer wall and being angled in a direction so that an end of the effusion cooling holes at the inside surface is farther upstream relative to the working fluid flow than an end of the effusion cooling holes at the outside surface. 
     
     
         9 . The gas turbine engine of  claim 1  wherein each of the transition components includes a transition cylinder at a first end mounted to one of the combustors and receiving a hot working fluid, where the transition cylinder includes a plurality of circumferential or longitudinal slots on an outer surface, and a cylindrical sleeve fitted over the slots of the transition cylinder to form a plurality of circumferential or longitudinal cooling channels, and the sleeve includes a cooling air inlet hole aligned with each of the slots to allow cooling air to enter and pass through the cooling channels. 
     
     
         10 . A combustion system for a gas turbine engine, said combustion system comprising;
 a plurality of fuel nozzles in a combustion section, said fuel nozzles providing fuel for combustion, where each of said fuel nozzles includes one or more fluid atomizing device with orifices configured to dispense liquid fuel and water in different atomized spray patterns and an integral heat shielding device;   a plurality of combustors in the combustion section, each of said combustors receiving the fuel from one of the fuel nozzles and burning the fuel, where each of said combustors includes a plurality of air-splitting cooling systems, and a slip-joint cross-flame duct for connecting adjacent combustors; and   a plurality of transition components in the combustion section, each of said transition components receiving combustion gases from one of the combustors and delivering the combustion gases to a turbine section, where each of said transition components includes a reverse bulk flow effusion cooling system, and transition cylinder cooling system.   
     
     
         11 . The combustion system of  claim 10  wherein each of the fuel nozzles includes;
 an annular fuel-injecting lance comprising a first fluid circuit and a second fluid circuit, 
 wherein the first fluid circuit is centrally disposed within the lance, wherein the first fluid circuit extends along a longitudinal axis of the lance to convey a first fluid to a downstream end of the lance, 
 wherein the second fluid circuit is annularly disposed about the first fluid circuit to convey a second fluid to the downstream end of the lance, wherein one of the first and second fluids comprises a liquid fuel conveyed by one of the first and second fluid circuits during a liquid fuel operating mode of the combustion turbine engine, 
 wherein the other of the first and second fluids conveyed by the other of the first and second fluid circuits comprises a selectable non-fuel fluid; and 
 an atomizer disposed at the downstream end of the lance, the atomizer having a first injection orifice responsive to the first fluid circuit to form a first atomized injection cone, the atomizer further having a second injection orifice responsive to the second fluid circuit to form a second atomized injection cone, wherein the first and second injection orifices of the atomizer are respectively configured so that the first and second injection cones formed with the atomizer comprise concentric cones that intersect with one another over a predefined angular range. 
 
     
     
         12 . The combustion system of  claim 10  wherein each of the fuel nozzles includes;
 a nozzle cap disposed at a downstream end of the fuel nozzle; 
 a heat shield mounted onto the nozzle cap; and 
 a plurality of cooling channels arranged between a forward face of the nozzle cap and a corresponding back side of the heat shield. 
 
     
     
         13 . The combustion system of  claim 10  wherein each of the fuel nozzles includes a nozzle cap disposed at a downstream end of the fuel nozzle, wherein the nozzle cap comprises a bore arranged to accommodate a downstream portion of a fluid-injecting lance that extends along a longitudinal axis of the nozzle, the downstream portion of the fluid-injecting lance comprising a centrally-located atomizer to form a first atomized injection cone. 
     
     
         14 . The combustion system of  claim 10  wherein each of the combustors includes a combustor basket including a basket liner having an input end receiving air and fuel and an output end through which a hot working gas exits the combustor basket, said combustor basket further including a double-wall exit cone coupled to the basket liner at the output end, said exit cone including an inner cone wall and an outer cone wall defining an annular exit cone channel therebetween, each of the inner cone wall and the outer cone wall including an inner surface and an outer surface, where the outer surface of the inner wall and the inner surface of the outer wall face the cone channel, said combustor basket further including a splash plate mounted to the outer wall and extending parallel to the output end of the basket liner so as to define an annular splash plate channel therebetween, wherein the outer cone wall is attached to the basket so as to allow air to be split between the exit cone and the splash plate. 
     
     
         15 . The combustion system of  claim 10  wherein each of the combustors includes;
 a combustor basket formed from at least one outer wall defining a combustor chamber; 
 at least one platefin cooling system formed from a platefin member positioned radially inward from an inner surface of the at least one outer wall forming the combustor basket; 
 at least one first rib section which extends between the platefin member and the combustor basket, thereby separating a first cooling circuit from a second cooling circuit, wherein the first cooling circuit is upstream from the second cooling circuit; 
 wherein the first cooling circuit includes at least one first exhaust outlet positioned in the platefin member upstream from the at least one first rib section; and 
 wherein the second cooling circuit includes at least one second exhaust outlet positioned downstream from the at least one first rib section. 
 
     
     
         16 . The combustion system of  claim 10  wherein the cross-flame duct comprises:
 a first duct extending along a longitudinal axis and configured to be coupled to a first combustor, the first duct comprising; 
 a first outer sleeve having a first end configured to be coupled to the first combustor and a second end on an opposite end from the first end, and 
 a first inner housing positioned within the first outer sleeve and having a first end adjacent the first combustor and a second end extending from the second end of the first outer sleeve; 
 a first cooling chamber positioned between an outer surface of the first inner housing and an inner surface of the first outer sleeve; 
 a second duct extending along the longitudinal axis and configured to be coupled to a second combustor, wherein the second duct is configured to slidably receive the first duct, the second duct comprising; 
 a second outer sleeve having a first end configured to be coupled to the second combustor and extending toward the first duct to slidably receive the second end of the first inner housing within a second end of the second outer sleeve, and 
 a second inner housing positioned within the second outer sleeve and having a first end adjacent the second combustor and a second end extending toward the second end of the second outer sleeve; and 
 a second cooling chamber positioned between an outer surface of the second inner housing and an inner surface of the second outer sleeve. 
 
     
     
         17 . The combustion system of  claim 10  wherein each of the transition components includes a first end mounted to one of the combustors and receiving a hot working fluid, a second end opposite to the first end outputting the hot working fluid, and a transition section between the first end and the second end having an outer wall defining a chamber therein through which the hot working fluid flows, said outer wall having an inside surface and an outside surface, said transition section including a plurality of first effusion cooling holes extending through the outer wall and being angled in a direction so that an end of the effusion cooling holes at the inside surface is farther upstream relative to the working fluid flow than an end of the effusion cooling holes at the outside surface. 
     
     
         18 . The combustion system of  claim 10  wherein each of the transition components includes a transition cylinder at a first end mounted to one of the combustors and receiving a hot working fluid, where the transition cylinder includes a plurality of circumferential or longitudinal slots on an outer surface, and a cylindrical sleeve fitted over the slots of the transition cylinder to form a plurality of circumferential or longitudinal cooling channels, and the sleeve includes a cooling air inlet hole aligned with each of the slots to allow cooling air to enter and pass through the cooling channels. 
     
     
         19 . The combustion system of  claim 10  wherein the transition components have a shape which is optimized to reduce stagnation zones and impingement of the combustion gases on transition component walls.