Abstract: A flange of a blade root platform is separated from an adjacent edge of the blade by a groove that prevents direct transmission of forces created by the bolted attachment of the platform flange to the adjacent part of the blade and reduces stress concentrations.

Abstract: The flange (11) of a blade root platform (10) is separated from an adjacent edge (31) of the blade (4) by a groove (18), that prevents direct transmission of forces created by the bolted attachment of the platform flange (11) to the adjacent part of the blade (4) and reduces stress concentrations.

Abstract: A structural frame for a turbomachine, such as an intermediate frame or an exhaust frame, the frame including at least two coaxial rings, an inner ring and an outer ring, together with radial arms interconnecting the rings. At least one of these elements includes a plurality of parts that are fastened together by bolting.

Abstract: An extension of an intermediate casing for an aircraft jet engine, intended to project towards the downstream end from an external shell of said intermediate casing is disclosed. This extension includes an annular connecting downstream end forming an annular groove open radially towards the outside, intended to receive nacelle covers. The annular connecting downstream end is produced by a plurality of angular sectors.

Abstract: The invention relates to an intermediate casing (21) for an aircraft jet engine, comprising an outer shell (23) and also front and rear flanges (25, 27) which are arranged radially inside with respect to the outer shell, the casing (21) also comprising structural arms (17) which extend radially between the flanges as far as the shell (23), the rear flange being equipped with receiving means (34) for receiving a fixing bracket for fixing a rod for absorbing the thrust forces, and the first receiving means comprising bosses (36) coming from the rear flange, through which bosses through-orifices (38) are formed which are passed through by fixing screws of the bracket. According to the invention, at least one of the bosses (36) extends as far as making contact with one of the structural arms (17).

Abstract: A structural frame for a turbomachine, such as an intermediate frame or an exhaust frame, the frame including at least two coaxial rings, an inner ring and an outer ring, together with radial arms interconnecting the rings. At least one of these elements includes a plurality of parts that are fastened together by bolting.

Abstract: The invention relates to an intermediate casing (21) for an aircraft jet engine, comprising an outer shell (23) and also front and rear flanges (25, 27) which are arranged radially inside with respect to the outer shell, the casing (21) also comprising structural arms (17) which extend radially between the flanges as far as the shell (23), the rear flange being equipped with receiving means (34) for receiving a fixing bracket for fixing a rod for absorbing the thrust forces, and the first receiving means comprising bosses (36) coming from the rear flange, through which bosses through-orifices (38) are formed which are passed through by fixing screws of the bracket. According to the invention, at least one of the bosses (36) extends as far as making contact with one of the structural arms (17).

Abstract: The invention relates to a device for decoupling a bearing bracket in a turbomachine, said bearing bracket having an upstream part and a downstream part respectively comprising a plurality of upstream holes and downstream holes through which stress-limiting screws pass, which device comprises, between each upstream hole and the stress-limiting screw that passes through it, a clearance that prevents any contact between the upstream hole and the stress-limiting screw, and is a device wherein the upstream part and the downstream part of the bearing bracket are in mutual contact via surfaces that form a dual centering means.

Abstract: The invention relates to an extension (30) of an intermediate casing for an aircraft jet engine, intended to project towards the downstream end from an external shell of the intermediate casing, this extension comprising an annular connecting downstream end (64) forming an annular groove (66) open radially towards the outside, intended to receive nacelle covers. According to the invention, the annular connecting downstream end (64) is produced by means of a plurality of angular sectors (76a, 76b).