Burner

Abstract

An aerodynamically stabilized premix burner essentially comprises a swirl generator ( 100 ) for generating a rotating combustion air flow ( 141 ), and means for introducing at least one fuel ( 142 ) into said combustion air flow. Furthermore, the burner is equipped with means ( 112 ) for introducing an axial air flow into the center of the generated rotational flow ( 144 ). According to the invention, this axial flow can be controlled, thus enabling an influence on the position and intensity of a flame stabilizing recirculation zone ( 123 ).

1 . Burner for a heat generator, substantially including a swirl generator ( 100 ) for the tangential introduction of a combustion air flow ( 141 ) into an internal space ( 122 ) of the swirl generator, and also means for the introduction of at least one fuel ( 142 ) into the combustion air flow, and which burner has at a downstream end an abrupt widening of the cross section of an axial burner throughflow cross section toward a combustion space ( 50 ), and which burner furthermore has an injection device ( 112 ) for the introduction of an axial central flow ( 145 ) along a central burner axis ( 100   a ), wherein the said injection device ( 112 ) is operatively connected to adjustable elements ( 62 ,  64 ,  1122 ,  1126 ) for the alteration of a throughflow cross section and for the control of the mass flow of the central flow.  
     
     
         2 . Burner according to  claim 1 , wherein the adjustable elements ( 1122 ,  1126 ) are directly integrated into the burner.  
     
     
         3 . Burner according to  claim 1 , wherein the injection device ( 112 ) is connected to a central air supply duct ( 1129 ), and wherein the adjustable element ( 62 ,  64 ) is arranged in operative connection with an end of the central air supply duct ( 1129 ) remote from the injection device.  
     
     
         4 . Burner according to  claim 3 , wherein the central air supply duct ( 1129 ) is connected to an air bypass ( 61 ) at the end remote from the injection device, and wherein the adjustable element ( 62 ) is arranged between the central air supply duct and the air bypass.  
     
     
         5 . Burner according to  claim 3 , wherein the central air supply ( 1129 ) is in fluid connection with an overflow space ( 63 ); an air bypass ( 61 ) opens into the overflow space; and a throttle valve ( 64 ) acting as the adjustable element is arranged in the overflow space.  
     
     
         6 . Burner according to one of claims  1  or  2 , wherein the injection device is a throughflow member ( 1121 ) arranged in the burner substantially coaxially of a burner axis ( 100   a ) and having a narrowest throughflow cross section; and a central member ( 1122 ), adjustable in its axial position, is arranged as the adjustable element and has a control cone ( 1123 ), such that the narrowest throughflow cross section of the throughflow body defines with the control cone of the central member a throttle point with adjustable throughflow cross section.  
     
     
         7 . Burner according to one of claims  1  or  2 , wherein a throughflow member ( 1121 ) is arranged as an injection device substantially coaxially of a burner axis ( 100   a ); the throughflow member has at least one inner control bore ( 1128 ); an outer member ( 1126 ) at least partially overlapping the throughflow member is arranged coaxially of the throughflow member, which outer member has at least one outer control bore ( 1127 ); and the throughflow member ( 1121 ) and the outer member ( 1126 ) are arranged to be displaceable and/or rotatable relative to one another, such that the overlap between the inner control bore ( 1128 ) and the outer control bore ( 1127 ) is variable.  
     
     
         8 . Burner according to one of claims  1 - 7 , wherein the axial burner throughflow cross section of the internal space ( 122 ) at least partially increases in the region of the swirl generator ( 100 ).  
     
     
         9 . Burner according to one of claims  1 - 8 , wherein an internal space ( 122 ) of the swirl generator ( 100 ) has in longitudinal section at least approximately the shape of a cone.  
     
     
         10 . Burner according to one of claims  1 - 8 , wherein an internal space ( 122 ) of the swirl generator ( 100 ) has in longitudinal section at least approximately a cylindrical shape.  
     
     
         11 . Burner according to one of claims  1 - 10 , wherein a displacement member ( 105 ) is arranged in the internal space ( 122 ) of the swirl generator ( 100 ).  
     
     
         12 . Burner according to  claim 11 , wherein the displacement member ( 105 ) tapers toward the burner mouth.  
     
     
         13 . Burner according to one of claims  1 - 12 , wherein a mixing section ( 200 ) is arranged in the combustion space ( 50 ) between the swirl generator ( 100 ) and the burner mouth.  
     
     
         14 . Burner according to  claim 8  or  9 , with the internal space ( 122 ) of the swirl generator having the shape of a cone widening toward the burner mouth, wherein the injection device ( 112 ) is arranged at an upstream end, remote from the burner mouth, of the swirl generator ( 100 ).  
     
     
         15 . Burner according to  claim 11  or  12 , wherein the injection device ( 112 ) is arranged at a downstream end, facing toward the burner mouth, of the displacement member ( 105 ).  
     
     
         16 . Burner according to one of claims  1 - 15 , wherein the swirl generator is constructed from plural laterally, mutually offset partial members ( 101 ,  102 ,  103 ,  104 ), between which are formed tangential inlet slots ( 121 ) for the combustion air flow ( 141 ).  
     
     
         17 . Burner according to one of claims  1 - 15 , wherein the swirl generator is constituted as a monolithic hollow body, in which tangential inlet slots and/or rows of tangential inlet openings for the combustion air flow are machined.  
     
     
         18 . Burner according to one of claims  1 - 17 , for operation in a combustion chamber of a gas turbine plant.  
     
     
         19 . Process for the operation of a burner according to one of claims  1 - 18 , wherein the axial central flow ( 145 ) is strongly throttled at low burner load; and the central flow is little throttled or not throttled at high burner load.  
     
     
         20 . Process according to  claim 19 , wherein the burner load is determined by means of a fuel measurement signal (X m ).  
     
     
         21 . Process according to  claim 19 , the burner being operated in a combustion chamber ( 20 ) of a gas turbine plant, wherein the burner load is determined in dependence on a generator power and/or a fuel of the gas turbine plant, the setting of the front guide vane set of a compressor belonging to the gas turbine plant, and/or ambient conditions.  
     
     
         22 . Process for the operation of a burner according to one of claims  1 - 18 , wherein a material temperature of the burner is measured, and wherein the central flow is controlled in dependence on the measured material temperature.  
     
     
         23 . Process for the operation of a burner according to one of claims  1 - 18  in a combustion chamber ( 20 ) of a gas turbine plant, wherein combustion pulsations are measured, and wherein the central flow is controlled in dependence on the measured combustion pulsations.  
     
     
         24 . Process for the operation of a burner according to one of claims  1 - 18  in a multi-burner system of a gas turbine, wherein the central flow of individual burners is controlled in dependence on the measured combustion pulsations.