| 摘要 |
<p>A turbine blade assembly, in particular for a gas turbine, is disclosed which comprises a disc (1) with a rotation axis (6), turbine blades (22) each turbine blade (22) having an airfoil (7), a blade root (11) and a platform (14) between the airfoil (7) and the blade root (11) by which it can be fixed to the disc (1), locking plates (9) and bent seal strips (10). The turbine blades (22) are arranged adjacent to each other such on the disc (1), that gaps are present between the platforms (14) of adjacent turbine blades (22) and root cavities (8) are present between the portions of the roots (11) of adjacent turbine blades (22). The turbine blades (22) are secured axially to the disc (1) by the locking plates (9). The seal strips (10) are arranged in the gaps between the platforms (14) of neighbouring turbine blades (22) to seal the gap and protrude axially over the blade root (11) and over the locking plate (9). Furthermore, a gas turbine with an inventive turbine blade assembly is described. Besides, a seal strip (10), in particular for use in a gas turbine blade assembly, is disclosed which comprises a straight portion (15) and a portion (16) with a bending. The portion (16) with the bending is narrower regarding its width than the straight portion (15).</p> |
