Patent ID: 7765658
Filing Date: 2010-08-03
Classification: B24B,B25B,Y10S,Y10T

Abstract:
1. A fixture assembly for positioning a plurality of blades relative to a rotor of a gas turbine engine, the blade retained in the rotor by loose-fitting dovetail joints, the blades having a dovetail root, an airfoil and a transversely extending platform therebetween, the fixture assembly comprising: a support for holding said rotor having the blades mounted thereto; a first positioning member, having a blade engagement portion for contacting a first portion of each blade platform protruding axially relative to the rotor; a second positioning member disposed so as to be on an opposite axial side of the rotor when the rotor is mounted in the support, the second positioning member having a blade engagement portion for contacting a second portion of each blade platform protruding axially relative to the rotor, the second portion being opposite to the first portion; and a centrally actuatable clamping assembly substantially coaxial to a rotor axis for axially clamping the first and second positioning members together when the rotor is mounted in the support, the first and second positioning members adapted to thereby transmit a pair of outwardly directed radial forces on the respective first and second portions of each of the blade platforms for radially positioning the blades outwardly against the rotor, thereby simulating a centrifugal force resulting from rotor rotation about said rotor axis.