Combustion chamber for a gas turbine plant

Abstract

A combustion chamber ( 1 ) for a gas turbine plant, has a combustion chamber wall ( 10 ), which is flowed through by combustion gases in the direction of a downstream expansion turbine, the chamber wall ( 10 ) has a device ( 20 ) for damping thermoacoustic oscillations caused by the combustion gases. At least one resonator tube ( 22 ), interacts with the resonator volume ( 21 ) and opens out into the combustion chamber ( 1 ) with its mouth (M) opposite from the resonator volume ( 21 ) in the combustion chamber inner wall ( 10 ). At least one feed opening ( 23, 23′, 23″ ) for sealing air for sealing the resonator tube mouth (M) is introduced into the combustion chamber ( 1 ) from a compressor plenum ( 2 ), surrounding the combustion chamber. The at least one first feed opening ( 23′, 23″ ) is provided in a region of the combustion chamber wall ( 10 ) close to the resonator tube mouth (M) and is aligned such that the sealing air (S) through the feed opening ( 23′, 23″ ) flows over the resonator mouth (M).

1 - 6 . (canceled) 
     
     
         7 . A combustion chamber for a gas turbine plant, the combustion chamber includes:
 a combustion chamber wall, through which combustion gases flow in a direction of a following gas turbine;   the combustion chamber wall having a damping device for the damping of thermoacoustic vibrations caused by combustion gases, the damping device comprising at least one Helmholtz resonator which is configured such that a resonator volume thereof lies on a side of the combustion chamber wall that faces away from an inner wall of the combustion chamber;   the resonator has at least one resonator tube, the tube co-operates with the resonator volume, and the resonator tube has a mouth lying opposite the resonator volume in the combustion chamber inner wall and exits into the combustion chamber;   at least one delivery port configured for entry of barrier air into the combustion chamber in such manner as for barring the resonator tube mouth the barrier air from a compressor plenum that surrounds the combustion chamber, the plenum being of a compressor that is positioned upstream of the combustion chamber, and the at least one first delivery port being provided in a region of the combustion chamber wall near the mouth of the at least one resonator tube and the at least one first delivery port being oriented such that the barrier air flowing through the at least one first delivery port flows over the resonator tube mouth;   the resonator tube mouth is set back in the combustion chamber wall with respect to the combustion chamber inner wall and into an area set back away from the combustion chamber, the at least one first delivery port is oriented and configured for injecting the barrier air virtually parallel to the flow direction of the combustion gases and flows over the setback resonator tube mouth.   
     
     
         8 . The combustion chamber as claimed in  claim 7 , wherein the resonator comprises a plurality of resonator tubes and the resonator tubes have their respective mouths oriented such that the barrier air of the delivery port flows over the setback resonator tube mouths of the plurality of resonator tubes. 
     
     
         9 . The combustion chamber as claimed in  claim 8 , further comprising a second one of the delivery ports directed opposite to the first one of the delivery ports, the second one of the delivery ports being oriented such that the barrier air through the second one of the ports is injected virtually parallel to and opposite to the flow direction of combustion gases in the combustion chamber and the barrier air through the second ones of the delivery ports flows over the setback resonator tube mouths. 
     
     
         10 . The combustion chamber as claimed in  claim 7 , wherein the delivery port is oriented in the combustion chamber wall such that the delivery port axis is inclined with respect to the resonator tube mouth. 
     
     
         11 . The combustion chamber as claimed in  claim 7 , wherein the combustion chamber inner wall has in a region of setback areas overlaps with the setback areas of the combustion chamber wall. 
     
     
         12 . A gas turbine plant with a compressor for the compression of sucked-in air, with the combustion chamber as claimed in  claim 7  following the compressor; and
 the plant having a burner for admixing fuel and for the combustion of the fuel/air mixture, and an expansion turbine which follows the burner and which converts the combustion exhaust gases of the burnt fuel/air mixture into mechanical energy.