Patent ID: 9328621
Filing Date: 2016-05-03
CPC Classification: B23P,B25B,F01D,F05D,Y10T

Claim Text:
1. A method of assembling a rotor assembly for a gas turbine engine, the method comprising: providing a plurality of rotor blades each including a root and a platform, the platform extending from the blade in opposed circumferential directions; providing a rotor disc including a plurality of slots spaced circumferentially about the disc; providing a plurality of blade seal members for sealing circumferential gaps between adjacent said platforms when the rotor blades are installed on the rotor disc; partially inserting the roots of the rotor blades in the respective slots of the rotor disc; placing the respective seal members radially between the platforms and the rotor disc, each seal member being positioned circumferentially between adjacent said rotor blades using a tool having an array of circumferentially spaced resilient fingers radially abutting the respective seal members against radially inner facing surfaces of the platforms; seating the rotor blades in the respective slots of the rotor disc substantially simultaneously with attachment of the respective seal members to the platforms, by a relative movement between the rotor disc and the tool having the rotor blades with the attached seal members, thereby forming the rotor assembly; and then moving the tool away from the rotor assembly to withdraw the respective resilient fingers from a radial clearance between the rotor disc and respective lands of the platforms with the blade seal members remaining in respective platform cavities radially between the platforms and the disc and circumferentially between adjacent blades.