Simplified support device for nozzles of a gas turbine stage

• US 20040033132A1
• Filed: 06/03/2003
• Published: 02/19/2004
• Est. Priority Date: 06/05/2002
• Status: Active Grant

• Current Assignee: Nuovo Pignone Holding SPA (Baker Hughes Company)
• Original Assignee: Nuovo Pignone Holding SPA (Baker Hughes Company)
• Inventors: Iacopetti, Piero
• Granted Patent: US 6,857,847 B2
• Time in Patent Office: Days
• US Class Current: 415/174.2
• CPC Class Codes: F01D 11/001 for sealing space between stator blade and rotor
• CPC Class Codes: F16J 15/444 with facing materials having honeycomb-like structure

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).

Claims

1. Simplified support device (110) for nozzles (112) of a gas turbine stage, the said Support device (110) being interposed in a rotor of the said gas turbine, between an upstream blading disc (122) and a downstream blading disc (124) of the said nozzles (112), and being provided with honeycomb-type alveolar seals (120), the said nozzles (112) of the said gas turbine stage comprising an annular body which is divided into nozzle segments (112), characterised in that, in the said simplified support device (110), the said honeycomb-type alveolar seals (120) are anchored directly to the said nozzle segments (112).

2. Support device (110) according to claim 1, characterised in that the said honeycomb-type alveolar seals (120) are connected to lower platforms (130) of the said nozzle segments (112).

3. Support device (110) according to claim 1, characterised in that, in the said nozzles (112), there are provided cooling holes (126) for air which cools the said upstream (122) and downstream (124) blading discs.

4. Support device (110) according to claim 2, characterised in that the said cooling holes (126) are provided in the vicinity of the said lower platforms (130) of the said nozzle segments (112).

5. Support device (110) according to claim 1, characterised in that it is used for nozzles (112) of the second stage of a low-pressure gas turbine.