Simplified support device for nozzles of a gas turbine stage
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United States of America Patent
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Feb 22, 2005
Grant Date -
Feb 19, 2004
app pub date -
Jun 3, 2003
filing date -
Jun 5, 2002
priority date (Note) -
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Abstract
A simplified support device (110) for nozzles (112) of a gas turbine stage, of the type 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 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).
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