| 摘要 |
<p>A gas turbine engine blade (12) comprises a dovetail (30), a shank (26) extending from the dovetail (30), an airfoil (18), and a platform (22) between the shank (26) and the airfoil (18). The platform (22) comprises a side wall (42) extending between an upstream side (38) and a downstream side (40) of the platform (22). A first pin channel (54) extends from the upstream side (38) of the sidewall (42) and a second pin channel (56), co-axial with the first pin channel (54), extends from the downstream side (40) of the sidewall (42). The first channel (54) includes a radial notch (62) at the upstream longitudinal end of the first pin channel (54).</p> |
