An aircraft engine (10), has: an upstream stator (30) having upstream stator vanes (31) distributed about a central axis (11); and a downstream stator (40) having downstream stator vanes (41) distributed about the central axis (11), the downstream stator (40) located downstream of the upstream stator (30), a number of the upstream stator vanes (31) different than a number of the downstream stator vanes (41), the downstream stator vanes (41) including: a first vane (42), a major portion of a leading edge (41A) of the first vane (42) circumferentially overlapped by one of the upstream stator vanes (31); and a second vane (43) differing from the first vane (42) by a geometric parameter, the geometric parameter causing the second vane (43) to have one or more of: a stiffness greater than that of the first vane (42), and a major portion of a leading edge (41A) of the second vane (43) circumferentially overlapped by another one of the upstream stator vanes (31).