Combustion chamber for a gas turbine plant

Abstract

A combustion chamber (1) for a gas turbine plant having a combustion chamber wall (10), through which combustion gases (G) flow in the direction of a downstream gas turbine, wherein the combustion chamber wall (10) has a dampening device (20) for dampening thermoacoustic vibrations caused by the combustion gases (G) and wherein the dampening device (20) comprises at least one Helmholtz resonator. The resonator volume (21) opens into the combustion chamber (1) with the resonator tube opening (M) in the combustion chamber. At least one supply opening (23) with which sealing air (S) for sealing the resonator tube opening (M) is introduced into the combustion chamber (1) via the resonator volume (21) and an at least one resonator tube (22, 22′, 22″) from a compressor plenum (2). The at least one resonator tube (22, 22′, 22″) from a compressor plenum (2). The at least one resonator tube (22′, 22″) has a tube axis (A) in the combustion chamber wall and the axis (A) lies outside of a surface normal (N) of the combustion chamber wall (10) at the site of the resonator tube opening (M).

1 . A burner with 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 side of the combustion chamber wall;   the resonator has at least one resonator tube in the combustion chamber wall, the tube co-operates with internal volume of the resonator, and the resonator tube has a mouth lying opposite the resonator volume on the inner side of the combustion chamber wall and exits into the combustion chamber;   at least one delivery port into the resonator configured for entry of barrier air in such manner as for barring the resonator tube mouth from a compressor plenum that surrounds the combustion chamber, wherein the barrier air is introduced into the combustion chamber via the resonator volume and then by the at least one resonator tube; and   the at least one resonator tube has a resonator tube axis in the combustion chamber wall such that, at the location of a resonator tube mouth, which is into the combustion chamber, the resonator tube axis lies outside a normal to the surface of and oblique to the combustion chamber inner wall.   
     
     
         2 . The burner with a combustion chamber as claimed in  claim 1 , wherein the resonator tube axis of the resonator tube is inclined away from a surface of the inner wall normal, in an upstream direction or a downstream direction of the combustion gases flowing through the combustion chamber. 
     
     
         3 . The burner with a combustion chamber as claimed in  claim 2 , wherein there is flow in the combustion chamber past the inner wall thereof from the upstream to the downstream directions;
 the resonator tube axes of upstream inclined direction resonator tubes of the Helmholtz resonator are inclined in the upstream direction, and the resonator tube axes of downstream inclined direction resonator tubes of the Helmholtz resonator are inclined in the downstream direction.   
     
     
         4 . The burner with a combustion chamber as claimed in  claim 1 , wherein the damping device comprises a multiplicity of Helmholtz resonators which are arranged over a circumference of the combustion chamber wall, that the resonators are distributed on at least one ring transversely to the combustion gases flowing through. 
     
     
         5 . The burner with a combustion chamber as claimed in  claim 4 , wherein the upstream inclined resonator tubes are assigned to the Helmholtz resonators of a first ring thereof and the downstream inclined resonator tubes inclined downstream are assigned to the Helmholtz resonators of a second ring lying downstream. 
     
     
         6 . A gas turbine plant comprising:
 the burner of  claim 1  for admixing of fuel and for combustion of the fuel/air mixture;   a compressor for the compression of sucked-in air, a combustion chamber following the compressor and receiving the air after compression of the air; and   an expansion turbine which follows the burner and which converts the combustion exhaust gases of the burnt fuel/air mixture into mechanical energy.