| 摘要 |
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). |
