Abstract: 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 neighboring turbine blades to seal the gap and protrude axially over the blade root and over the locking plate.

Abstract: A gas turbine rotor blade and rotor disk arrangement is provided. The rotor blade and the rotor disk includes a coating in order to seal the gap which normally exists between the bottom part of the blade root and the bottom part of the disk slot. The coating may be applied to the blade root or to the disk itself on the bottom part of the disk slot. The coating is preferably an abradable nickel-alloy Bentonite coating. The coating may also be applied to only a portion of the areas being sealed, omitting a portion at the start of the slot or at the start of one of the lobes of the blade root, so that a lead-in is formed, whereby the blade can more easily be inserted into the slot.

Abstract: A turbine rotor with a rotor disc, a plurality of slots arranged on the rotor disc, a plurality of blades having blade roots and arranged in the slots, and a plurality of locking plates fitted in a position between the rotor disc and the blades are provided. The first gaps on radially outside edges and second gaps on radially inside edges, relative to an axis of rotation of the rotor disc, are formed between neighboring locking plates. At least one of the first gaps is smaller than the corresponding second gap, wherein at least one first gap and corresponding second gaps are intentionally introduced.

Abstract: 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.

Abstract: A gas turbine rotor blade and rotor disk arrangement is provided. The rotor blade and the rotor disk includes a coating in order to seal the gap which normally exists between the bottom part of the blade root and the bottom part of the disk slot. The coating may be applied to the blade root or to the disk itself on the bottom part of the disk slot. The coating is preferably an abradable nickel-alloy Bentonite coating. The coating may also be applied to only a portion of the areas being sealed, omitting a portion at the start of the slot or at the start of one of the lobes of the blade root, so that a lead-in is formed, whereby the blade can more easily be inserted into the slot.

Abstract: A turbine rotor with a rotor disc, a plurality of slots arranged on the rotor disc, a plurality of blades having blade roots and arranged in the slots, and a plurality of locking plates fitted in a position between the rotor disc and the blades are provided. The first gaps on radially outside edges and second gaps on radially inside edges, relative to an axis of rotation of the rotor disc, are formed between neighboring locking plates. At least one of the first gaps is smaller than the corresponding second gap, wherein at least one first gap and corresponding second gaps are intentionally introduced.