Safran Aircraft Engines

Vincent Gérard Michel Moreau

Tangi Brusq

Sabrina Benkaci

Emmanuel Wilfrid Léon Berche

A method for maintaining a bladed wheel of a high-pressure turbine of a turbomachine having a disc with cavities, and blades extending radially from a radially internal root mounted in a cavity of the disc, the root being supported on the disc by means of surfaces of the root and of the disc forming bearing surfaces. At least one foil is removably mounted between the root of at least one blade and the disc, at the corresponding bearing surfaces. The method includes measuring a radial clearance between the tip of at least one blade, meaning the radially external end of the blade, and a shroud of the turbomachine situated facing the bladed wheel, and if the radial clearance is greater than a determined value, removing the foil.

Method for maintaining a bladed wheel of a high-pressure turbine of a turbomachine

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.

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Moissy-Cramayel, France

Vincent Gérard Michel Moreau