Safran Aircraft Engines

Safran

Jérémy Philippe Pierre Edynak

Olivier Bazot

Jérémy Guivarc'h

Pierre Jean Faivre D'arcier

Pierre Faivre D'Arcier

Thibaut Dominique Augustin Girard

Lola Auliac

Farhana Hussain

Fanny Marie Libes

An interface member equips a control ring of a high-pressure compressor of an engine. This control ring has at least one housing intended to partially house a guide shoe. This interface member includes a central wall to which two holding tabs are secured, delimiting a through-housing having dimensions substantially identical to the initial dimensions of the housing, and suitable for being inserted into the housing, after it has been machined to receive same following a deformation, until the holding tabs keep it stationary relative to the control ring.

Interface member for reconditioning a control ring of an engine compressor, and associated reconditioning method

Seal () for an inter-blade platform intended to extend circumferentially about an axis and to be mounted between two axial ends of the inter-blade platform, including a first part () in contact with a first blade adjacent to a first circumferential end of the platform, and a second part () in contact with a second blade adjacent to a second circumferential end of the platform, the first part () and the second part () of the seal () being fixed to each other such that a displacement in the circumferential direction of one of the two parts () of the seal () causes a displacement of the other part () of the seal () in the same direction, when the two parts () of the seal () are fixed to each other.

Inter-blade platform seal

A turbo-engine module comprises a turbo-engine housing, and a thermal protection shell of the housing. The thermal protection shell is configured to cover at least partially the housing in order to protect same thermally. The module comprises a wear protection strip which is situated between the housing and the thermal protection shell, in a junction region of the housing and the thermal protection shell.

Turbo-engine housing, equipped with a thermal protection shell and an anti-wear strip

A flexible metal foil can be fixed on the inside part of a variable pitch vane control ring of a turbojet compressor, so as to close all through holes in which lever pins and their surrounding bushes are housed. As a result, the foil can retain the shank of the bush if the bush breaks. The use of such foil does not impose the development of a new model of control ring and its impact on the mass is small enough so that it does not affect engine performances. Therefore it avoids problems related to the breakage of bushes without having to make major changes to the existing system.

Growing community of inventors

Moissy-Cramayel, France

Jérémy Philippe Pierre Edynak