Patent ID: 9476317
Filing Date: 2016-10-25
CPC Classification: F01D,F05D,Y10T

Claim Text:
1. A stage of a gas turbine engine, comprising: a bucket extending radially about a longitudinal axis of the gas turbine engine, the bucket comprising an airfoil and a tip portion extending from the airfoil, the tip portion comprising an upstream projection and a downstream projection extending away from the airfoil; a shroud facing the bucket and having a cylindrical shape, the shroud comprising a fore end portion comprising a radially inner surface spaced a first distance from the longitudinal axis of the gas turbine engine; and a forward step honeycomb seal positioned on the shroud downstream of the fore end portion and facing the bucket, the forward step honeycomb seal comprising: wherein the second distance is greater than the third distance; wherein the third distance is greater than the first distance; wherein the upstream surface and the downstream surface of the forward step portion are positioned axially between the upstream projection and the downstream projection; wherein the forward step portion is positioned axially closer to the upstream projection than the downstream projection; and wherein the forward step portion extends axially over a majority of an axial distance between the upstream projection and the downstream projection.