| 摘要 |
A turbine blade assembly, in particular for a gas turbine, is provided. The turbine blade assembly includes a disc with a rotation axis, turbine blades, each turbine blade including an airfoil, a blade root and a platform between the airfoil and the blade root by which it may be fixed to the disc, locking plates and bent seal strips. The turbine blades are arranged adjacent to each other on the disc, such that gaps are present between the platforms of adjacent turbine blades and root cavities are present between the portions of the roots of adjacent turbine blades. The turbine blades are secured axially to the disc by the locking plates. The seal strips are arranged in the gaps between the platforms of neighbouring turbine blades to seal the gap and protrude axially over the blade root and over the locking plate.
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