| 摘要 |
A turbine wheel for a turbine engine (such as a turbojet or turboprop) comprises a disk 14 carrying blades 122. Each blade comprises an impeller connected by a stilt 126 to a root 118, and has an upstream radial wall 130 and a downstream radial wall 128 which extend inwards from a platform 124. The roots of the blades are engaged in notches in the disk. Inter-blade cavities 116 each accommodate a sealing and vibration damping member 132, 156. Each member comprises a bottom wall 136, which extends on its periphery by a flanged edge 138, and a transverse partition wall 146 axially arranged at a distance from a downstream (or upstream, respectively) portion 142 of the member and axially opposite two upstream (or downstream, respectively) radial walls 130 so as to obstruct a flow of incoming air into the cavity between the two radial walls. The flanged edge may have two side flanks 144. The partition wall may be in the middle of the platforms. There may be a second partition wall 158. The member may have openings in the form of two notches 150, 154 on either side of a lug 148 on an upstream or downstream portion. |
