Abstract: A composite material casing of varying thickness, in particular for a gas turbine fan, is made by forming fiber reinforcement and densifying the reinforcement with a matrix. The fiber reinforcement is made by winding superposed layers of a fiber texture onto a mandrel, the texture being made by three-dimensional weaving with varying thickness.

Abstract: A twin fan turbomachine with two contrarotating fans, one upstream and one downstream, driven by two contrarotating coaxial shafts each of which connects one fan impeller to at least one low-pressure turbine impeller located downstream, the downstream fan impeller being connected by its downstream part to its drive shaft.

Abstract: A method for manufacturing a hollow blade for a turbomachine including drilling channels into a blank of the blade, placing inserts into the channels, forging the blank, and removing the inserts by chemical dissolution, and the blade is an aluminum alloy and the inserts are a copper alloy.

Abstract: The present invention relates to a structural or non-structural turbojet engine fan casing connecting arm that also acts as a flow straightener downstream of the fan rotor. Its distinctive feature is that it is constructed to form an acoustic attenuator. In particular, it comprises a closed cavity and perforations on one of the faces so as to form a Helmholtz resonator. The arm forms part of the intermediate casing.

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: A twin fan turbomachine with two contrarotating fans, one upstream and one downstream, driven by two contrarotating coaxial shafts each of which connects one fan impeller to at least one low-pressure turbine impeller located downstream, the downstream fan impeller being connected by its downstream part to its drive shaft.

Abstract: The present invention relates to a structural or non-structural turbojet engine fan casing connecting arm (8B) that also acts as a flow straightener downstream of the fan rotor (3). Its distinctive feature is that it is constructed in such a way as to form an acoustic attenuator. In particular, it comprises a closed cavity and perforations (83) on one of the faces (8B in, 8Bex) so as to form a Helmholtz resonator. The arm forms part of the intermediate casing (8).

Abstract: A composite material casing of varying thickness, in particular for a gas turbine fan, is made by forming fiber reinforcement and densifying the reinforcement with a matrix. The fiber reinforcement is made by winding superposed layers of a fiber texture onto a mandrel, the texture being made by three-dimensional weaving with varying thickness.