| 摘要 |
<p>A support device (110) for nozzles (112) of a gas turbine stage is presented, in which the support device (110) is interposed in a rotor of the gas turbine, between an upstream blading disc (122) and a downstream blading disc (124) of the nozzles (112), and which is provided with honeycomb-type alveolar seals (120). The nozzles (112) of the gas turbine stage comprise an annular body which is divided into nozzle segments (112) and the honeycomb-type alveolar seals (120) are anchored directly to these nozzle segments (112).</p> |
