| 摘要 |
17 B 11/227-0 The invention relates to a modular blade or vane for a gas turbine, which 5 comprises the modular components of: a platform element (53) with a planar or contoured surface defining a platform level (56) and a through-opening (66) therein, and an airfoil (32), extending through the platform element (53), wherein the airfoil (32) having: 10 a load carrying structure (33) extending along a longitudinal axis (55) of the airfoil (32), having a root portion (35) for fastening on a blade or vane carrier of the gas turbine, having a tip portion (36), and having at least one interior passage (46), extending from the root portion (35) to the tip portion (36) of the airfoil (32), an aerodynamically shaped shell (34) extending in a distance (37) over the 15 carrying structure (33) and defining the outer contour (40) of the airfoil (32), a longitudinally extending gap (48), defined between the carrying structure (33) and the shell (34), a number of through-holes (47) in the carrying structure (33) for directing a cooling medium (49) from the interior passage (46) into the gap (48), 20 characterized in that the shell (34) being integrally joined to said carrying structure (33) by a first joint in a region below the platform level (56) of the platform element (53); and the shell (34) being joined to the carrying structure (33) by at least one additional joint, wherein said at least one additional joint is a form-fit joint, allowing relative 25 movement in longitudinal direction between shell (34) and carrying structure (33). (Figure 3) B 11 /227-0 30%315 34 |
