| 摘要 |
An exemplary embodiment of the invention is a gas turbine engine blade spacer has an axially extending backbone (300), spaced apart forward, mid and aft dovetail lands (302, 304 and 308), respectively, disposed along the backbone, the backbone (300) and the forward, mid, and aft dovetail lands (302, 304 and 308) having bottom curved backbone surfaces (310). Each of the forward, mid and aft dovetail lands has a riser (312) that extends above the backbone (300) and has a riser flat top (314). In the exemplary embodiment disclosed herein, a spacer tab (320) extends generally axially forward of the forward land (302) and includes intersecting axially and radially extending tab apertures (316 and 318). A void (330) extends around the backbone (300) and between the forward and aft dovetail lands (302 and 308) and the void filled with an elastomeric material (332). The spacer has a constant shape and size cross-section between the forward and aft dovetail lands. The invention has a particular use with circular arc dovetail slots and roots for which the spacer is a circular arc shaped spacer and the backbone (300), and the forward, mid and aft dovetail lands (302, 304 and 308) are curved along a circular arc normal to and about a radial axis (RA). The spacer tab (320) has a rectangular cross-section (321), extends axially out of a forward face (322) of the forward land (302), and has a tab flat top (324) that is co-planar with the riser flat tops (314) of the risers (312). <IMAGE> |
