Abstract: Unbalanced mass effects can occur at the low pressure compressor (5) of an aircraft engine. Stiffeners (20) are proposed to increase the stiffness of the assembly and therefore reduce possible cracks due to accidental unbalanced masses, one end (22) of the stiffener can be fixed to the engine casing (7) at the structural arm (10), and the other end (32) can be fixed to the compressor (5), preferably at the upstream face of the third guide vane (RD3). Advantageously, the stiffeners (20) are made of two parts fixed to each other; their manufacturing is optimized to limit the additional weight due to their presence.

Abstract: The invention relates to a bladed disk for a turbomachine, the disk including blades which extend into a conical stream and which are held in a peripheral groove of said disk by hammerhead type fasteners, each of said blades further including a platform whose radially-outer face defines the boundary of the gas flow stream and whose radially-inner face presents an upstream rib and a downstream rib disposed in planes that are perpendicular to the axis of rotation of said disk and that are radially adjacent respectively to an upstream ring and a downstream ring formed at the periphery of said disk on either side of said groove in order to provide leaktightness in these zones, wherein the thickness of the downstream rib in the axial direction is greater than the thickness of the upstream ring.

Abstract: The invention relates to a method of improving the retention capacity of a blade having an asymmetrical hammerhead connection and extending in a conical stream, with the root of the blade being retained in a peripheral groove in a disk, said groove having an upstream lip and a downstream lip presenting respective bearing surfaces that extend in planes that are asymmetrical relative to planes perpendicular to the axis of rotation of said disk, and against which the surfaces of the upstream and downstream flanks of said root come to bear, the bearing surface of said upstream lip being connected to the bottom wall of said groove via a rounded surface, and the upstream flank presenting, in the vicinity of said rounded surface, a heel situated inside a circle of radius R centered on the axis about which said blade tends to pivot when axial stress is applied thereto, said circle outlining, in the upstream lip, a crescent shape of thickness e, wherein: a) the connection between the bearing surface of the upstream

Abstract: The invention relates to a method of improving the retention capacity of a blade having an asymmetrical hammerhead connection and extending in a conical stream, with the root of the blade being retained in a peripheral groove in a disk, said groove having an upstream lip and a downstream lip presenting respective bearing surfaces that extend in planes that are asymmetrical relative to planes perpendicular to the axis of rotation of said disk, and against which the surfaces of the upstream and downstream flanks of said root come to bear, the bearing surface of said upstream lip being connected to the bottom wall of said groove via a rounded surface, and the upstream flank presenting, in the vicinity of said rounded surface, a heel situated inside a circle of radius R centered on the axis about which said blade tends to pivot when axial stress is applied thereto, said circle outlining, in the upstream lip, a crescent shape of thickness e, wherein: a) the connection between the bearing surface of the upstream li

Abstract: The invention relates to a bladed disk for a turbomachine, the disk including blades which extend into a conical stream and which are held in a peripheral groove of said disk by hammerhead type fasteners, each of said blades further including a platform whose radially-outer face defines the boundary of the gas flow stream and whose radially-inner face presents an upstream rib and a downstream rib disposed in planes that are perpendicular to the axis of rotation of said disk and that are radially adjacent respectively to an upstream ring and a downstream ring formed at the periphery of said disk on either side of said groove in order to provide leaktightness in these zones, wherein the thickness of the downstream rib in the axial direction is greater than the thickness of the upstream ring.