Turbinentriebwerk und Montageverfahren für ein Turbinentriebwerk

摘要

A gas turbine engine (20) has a rotor stack (32) carried by a central shaft (28). A number of retainer segments (210A) each have a first surface (214) engaging the rotor stack (32) and a second surface (212) engaging the central shaft (28) so as to transmit a precompression force from the central shaft (28) to the rotor stack (32).