Abstract: Turbomachine modules, for example for an aircraft, include a turbine nozzle having several sectors (S), each sector having guide vanes extending between inner and outer platform elements, at least one of the platform elements of each sector carrying, on the one hand, at least one sealing blade configured to ensure fluid sealing between the platform element and the adjacent structural element, and, on the other hand, a device configured to hold the at least one sealing blade in a sealing position. The device includes a leaf spring having a middle portion fixed to the platform element, and opposite end portions which are supported on the sealing blade carried by the platform element.

Abstract: Turbomachine modules, for example for an aircraft, include a turbine nozzle having several sectors (S), each sector having guide vanes extending between inner and outer platform elements, at least one of the platform elements of each sector carrying, on the one hand, at least one sealing blade configured to ensure fluid sealing between the platform element and the adjacent structural element, and, on the other hand, a device configured to hold the at least one sealing blade in a sealing position. The device includes a leaf spring having a middle portion fixed to the platform element, and opposite end portions which are supported on the sealing blade carried by the platform element.

Abstract: An assembly for gas turbine, includes a first part and a second part installed circumferentially around a longitudinal axis of the turbine, where the first part has a first side face adjacent to a second side face of the second part, and where a first aperture made in first side face is facing a second aperture made in second side face, a sealing plate fitted inside the first aperture and the second aperture, at least one longitudinal face of the sealing plate includes at least two projections made either side of a longitudinal central area of the sealing plate, wherein each projection is of a height chosen so as to reduce a clearance between the sealing plate and the first and second apertures.

Abstract: An assembly for gas turbine, includes a first part and a second part installed circumferentially around a longitudinal axis of the turbine, where the first part has a first side face adjacent to a second side face of the second part, and where a first aperture made in first side face is facing a second aperture made in second side face, a sealing plate fitted inside the first aperture and the second aperture, at least one longitudinal face of the sealing plate includes at least two projections made either side of a longitudinal central area of the sealing plate, wherein each projection is of a height chosen so as to reduce a clearance between the sealing plate and the first and second apertures.