Metallic annular connection structure for aircraft turbomachine
View Patent ↗A metallic annular connection structure between two parts for an aircraft turbomachine, with an arbitrary half-section including two primary branches and a base forming a first U opening up in the radial direction from a longitudinal axis, and two secondary branches forming a second U with one of the two primary branches opening up in the longitudinal direction. The primary and secondary branches and the base of the first U are made in a single piece.
1. An assembly for an aircraft turbomachine, comprising:
a metallic annular connection structure between two parts for the aircraft turbomachine, with an arbitrary half-section comprising:
two primary branches and a base forming a first U opening up in the radial direction from a longitudinal axis of the annular structure, two secondary branches forming a second U with one of the two primary branches opening up in the longitudinal direction,
wherein the primary branches and secondary branches and the base of the first U are made in a single piece;
wherein each arbitrary half-section further comprises two tertiary branches combining with other of the two primary branches to form a third U opening up longitudinally in a direction opposite to the direction of the second U, and wherein the primary branches, secondary branches, and tertiary branches and the base of the first U are made in a single piece; and
a first annular part made of a composite material, the annular end of which is housed in the second U.
2. An assembly according to claim 1 , further comprising a second annular part made of a composite material, one annular end of which is housed in the third U.
3. An aircraft turbomachine comprising an assembly according to claim 1 .
4. A turbomachine according to claim 3 , in which:
the metallic annular connection structure is centered on the longitudinal axis of the turbomachine;
the first annular part comprises means forming an envelope whose internal face defines an annular external delimitation surface of a secondary stream of the turbomachine; and
wherein the assembly further comprising a second annular part, one annular end of which is housed in the third U and which second annular part forms a thrust inverter structure.
5. A turbomachine according to claim 4 , further comprising an exhaust casing connected to the metallic annular connection structure arranged radially outwards from the exhaust casing, through connecting rods.