Burner for a combustion machine and combustion machine

Abstract

A burner for a combustion machine, having a pilot burner, which extends in the axial direction, having a nozzle chamber, having a burner region and having a cover plate which is arranged between the nozzle chamber and the burner region and which has an inlet opening, wherein an adapter is arranged, in order to guide air out of the nozzle chamber along a specified flow path in the direction of the combustion region, wherein a flow channel is formed as part of the flow path between the adapter and the cover plate and the adapter has a radially extending, annular section which, together with the cover plate, forms a radial section of the flow channel, in order to cool the cover plate by the air. A combustion machine has such a burner.

1 .- 13 . (canceled) 
     
     
         14 . A burner for a combustion machine, comprising:
 a pilot burner which extends in the axial direction,   a nozzle chamber,   a combustion region,   a cover plate which is arranged between the nozzle chamber and the combustion region and which has an inlet opening, and also nozzles which are arranged around the pilot burner in the nozzle chamber and which extend in each case in the axial direction and which have in each case a nozzle outlet which corresponds in each case to a recess which is introduced into the cover plate, and   an adapter which is arranged for guiding air from the nozzle chamber along a predetermined flow path in the direction of the combustion region,   wherein between the adapter and the cover plate a flow passage is formed as part of the flow path, and the adapter has a radially extending annular section which with the cover plate forms a radial section of the flow passage for cooling the cover plate by the air,   wherein the nozzles have in each case an end section which is arranged in the radial section.   
     
     
         15 . The burner as claimed in  claim 14 ,
 wherein the adapter has a head region into which the pilot burner projects.   
     
     
         16 . The burner as claimed in  claim 15 ,
 wherein between the pilot burner and the head region an annular passage is formed as part of the flow path.   
     
     
         17 . The burner as claimed in  claim 14 ,
 wherein a part of the cover plate is designed as an axial cone, on the upstream disposed end of which the inlet opening is arranged.   
     
     
         18 . The burner as claimed in  claim 17 ,
 wherein the adapter has a diagonally extending section which extends at a distance from the axial cone and consequently forms a conical shell-like diagonal section of the flow passage.   
     
     
         19 . The burner as claimed in  claim 14 ,
 wherein the flow passage is designed as an annulus.   
     
     
         20 . The burner as claimed in  claim 14 ,
 wherein the flow passage has an air inlet which lies on the outside in the radial direction.   
     
     
         21 . The burner as claimed in  claim 14 ,
 wherein an annular gap, into which a sealing ring is inserted, is formed in the radial direction between the pilot burner and the adapter.   
     
     
         22 . The burner as claimed in  claim 21 ,
 wherein the sealing ring is fastened on the pilot burner and is displaceable relative to the adapter, or the sealing ring is fastened on the adapter and is displaceable relative to the pilot burner.   
     
     
         23 . The burner as claimed in  claim 22 ,
 wherein the sealing ring has at least one bridge which extends in the axial direction and encompasses the sealing ring, wherein the bridge forms a sealing face which is seated on the adapter.   
     
     
         24 . The burner as claimed in  claim 14 ,
 wherein the adapter has at least one spacer which is seated on the cover plate.   
     
     
         25 . The burner as claimed in  claim 24 ,
 wherein the spacer is designed as a deformation of the adapter.   
     
     
         26 . A combustion machine, comprising:
 a burner as claimed in  claim 14 .   
     
     
         27 . The combustion machine of  claim 26 ,
 wherein the combustion machine comprises a gas turbine.