| 摘要 |
There is provided a method of assembling a gas turbine engine using a concentricity ring to compensate for assembly tolerances. The blade tips of the gas turbine during turbine rotation define a tip surface of rotation concentric the shaft axis. Due to cumulative tolerances in part manufacture and assembly, the shaft axis is invariably radially eccentric the engine axis at the axial position of the turbine an assembly eccentricity within the range between zero and a predetermined allowable assembly tolerance. The method relates to the step of positioning a concentricity ring with: an outer cylindrical surface engaging the internal cylindrical surface of the engine housing; and an inner cylindrical surface engaging the external cylindrical surface of the turbine shroud, the outer and inner cylindrical surfaces of the concentricity ring being eccentric a ring eccentricity within the range between zero and said predetermined allowable assembly tolerance to rectify the assembly eccentricity of the moving and static components in a simple expeditious manner. |
