| 摘要 |
<p>The combustion device (1) for a gas turbine comprises a portion (9) provided with a first and a second wall (11, 12) provided with first passages (14) connecting the zone between the first and second wall (11, 12) to the inner of the combustion device (1) and second passages (15) connecting said zone between the first and second wall (11, 12) to the outer of the combustion device (1). Between the first and second wall (11, 12) a plurality of chambers (17) are defined, each connected with one first passage (14) and at least one second passage (15), and defining a Helmholtz damper.</p> |
