Abstract: 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.

Abstract: A low-pressure turbine of a gas turbine is disclosed. The turbine comprises a number of stages arranged one behind the other in an axial manner in the flow-through direction of the turbine. Each stage is formed from a fixed vane ring having a number of vanes and from a rotating blade ring having a number of blades. Each stage is characterized by a characteristic value vane-to-blade ratio that indicates the ratio of the number of vanes to the number of blades within a stage. One of the stages of the turbine is designed in such a manner that, in the event of noise-critical conditions of the turbine, the characteristic value vane-to-blade ratio of this stage is between a lower cut-off limit for mode k=?1 of the blade-passing frequency (BPF) of said stage and an upper cut-off limit for the mode k=?2 of the blade-passing frequency (BPF) of this stage.

Abstract: 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.

Abstract: A low-pressure turbine of a gas turbine is disclosed. The turbine comprises a number of stages arranged one behind the other in an axial manner in the flow-through direction of the turbine. Each stage is formed from a fixed vane ring having a number of vanes and from a rotating blade ring having a number of blades. Each stage is characterized by a characteristic value vane-to-blade ratio that indicates the ratio of the number of vanes to the number of blades within a stage. One of the stages of the turbine is designed in such a manner that, in the event of noise-critical conditions of the turbine, the characteristic value vane-to-blade ratio of this stage is between a lower cut-off limit for mode k=?1 of the blade-passing frequency (BPF) of said stage and an upper cut-off limit for the mode k=?2 of the blade-passing frequency (BPF) of this stage.