Patent ID: 8613599
Filing Date: 2013-12-24
Classification: F01D,F05D,F16J

Abstract:
1. A turbine blade assembly, comprising: a disc with a rotation axis; a plurality of turbine blades each turbine blade including an airfoil, a blade root, and a platform between the airfoil and the blade root, the turbine blade being fixed to the disc by the blade root; a plurality of locking plates; and a plurality of bent seal strips, wherein the plurality of turbine blades are arranged adjacent to each other on the disc, such that a gap is present between two platforms of adjacent turbine blades and a root cavity is present between a plurality of portions of roots of adjacent turbine blades, wherein the plurality of turbine blades are secured axially to the disc by the plurality of locking plates, and wherein a bent seal strip of the plurality of bent seal strips is arranged in the gap between the two platforms of adjacent turbine blades to seal the gap and protrude axially over the blade root and over a locking plate of the plurality of locking plates, wherein the bent seal strip is in contact with the locking plate of the plurality of locking plates.