Abstract: Protection device for a stator of a turbine of the type comprising a series of annular sectors constrained to each other by means of connection means, each sector of the series of sectors comprises a first surface, suitable for contacting the stator which has at least one cavity for the cooling of the corresponding sector, and a second surface which faces a rotor of the turbine. In a rest configuration in which the turbine is not operating, the second surface of each sector has an axial section having an eccentricity with respect to the trace of the rotation axis of the turbine, whereas in an operating configuration in which the turbine is operating under regime conditions, the second surface of each sector has an axial section which is centered with the trace of the rotation axis of the turbine.

Abstract: Protection device (10) for a stator of a gas turbine of the type comprising a series of sectors (12) constrained to each other by connection means, each sector (12) has at least one cavity (14) having a bottom (15), in correspondence with at least one cavity (14), a corresponding sheet (20) equipped with a series of pass-through holes (21) and suitable for covering at least one cavity (14) is fixed on an outer surface of the relative sector (12), each sector (12) is cooled by means of a stream of air coming from the pass-through holes (21) of the corresponding sheet (20) which is passed on the bottom (15) and discharged from at least one outlet hole, the bottom (15) of each sector (12) comprises a series of protuberances (30) to increase the thermal exchange surface and increase the cooling efficiency of the protection device (10).

Abstract: Protection device for a stator of a turbine comprising a series of annular sectors (12) which can be coupled by connection means, each sector (12) comprising a first side surface (13) which has at least one cavity (14) equipped with a bottom (15), each bottom (15) of the at least one cavity (14) is convex and each sector (12) comprises at least one stiffening rib (16) positioned inside the at least one cavity (14) and having a variable section in a longitudinal direction to modulate the rigidity of each sector (12).

Abstract: Protection device for a stator of a turbine comprising a series of annular sectors (12) which can be coupled by connection means, each sector (12) comprising a first side surface (13) which has at least one cavity (14) equipped with a bottom (15), each bottom (15) of the at least one cavity (14) is convex and each sector (12) comprises at least one stiffening rib (16) positioned inside the at least one cavity (14) and having a variable section in a longitudinal direction to modulate the rigidity of each sector (12).

Abstract: An improved assembly (110) consisting of internal casing (112) and support device (114) for nozzles in a gas turbine stage, these nozzles being grouped together in sectors and each of these sectors being connected externally to an external casing of the gas turbine by means of the support device (114), this support device (114) being kept in position by the internal casing (112), there also being formed first cooling holes (122) on the internal casing (112) and second cooling holes (124) on the support device (114); the first cooling holes (122) of the internal casing (112) have an extension substantially parallel to the axis of the gas turbine.

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).

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).