| 摘要 |
A turbine of a gas turbine, in particular of a gas turbine aircraft engine, having a rotor that has at least one moving blade ring and having a stator that has at least one guide blade ring, moving blades of the, or each, moving blade ring and/or guide blades of the, or each, guide blade ring being fashioned as hollow blades having at least one cavity, wherein on at least one side of at least one moving blade and/or guide blade fashioned as a hollow blade, in a blade wall holes are made that connect the, or each, cavity to the surrounding environment of the respective moving blade and/or guide blade, so that the respective cavity can be used as a resonator or sound muffler in order to reduce the sound radiated by the turbine during operation.
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