SHAFT FOR AN AIRCRAFT TURBOMACHINE

Abstract

Shaft (1) for an aircraft turbomachine (2) comprising a body (3) having an upstream portion (4) and a downstream portion (5) axially separated from each other by a flange (6), the flange (6) comprising an axial wall (7) disposed axially between two radial walls (8a, 8b) of equivalent and constant thickness, the shaft (1) further comprising upstream and downstream mounting diaphragms (10a, 10b) extending radially and respectively from the upstream and downstream portions (4, 5) of the body (3), each of the upstream and downstream diaphragms (10a, 10b) comprising a web (11) of constant thickness disposed radially between an external flange (12) and an internal base (13), a structurally critical diaphragm is determined from among the upstream and downstream diaphragms (10a, 10b), the quotient between the thickness (E1) of the radial walls (8a, 8b) of the ridge (6) and the thickness (E2) of the veil (11) of the critical diaphragm is greater than or equal to 1.5. Figure for abbreviation: 2