Patent ID: 8303257

Claim:
An arrangement between blade elements ( 1 ) in a blade row in a gas turbine, each blade element ( 1 ) has at least one shroud element ( 13 ), and also a blade airfoil ( 9 ) which abuts on, and is connected to, the shroud element ( 13 ), and extends essentially in the radial direction with regard to a principal axis of the blade row, with the blade row installed, the shroud element ( 13 ), by two sides ( 4 , 5 ) which point in the circumferential direction (U), abut on a respectively adjacent shroud element ( 13 ) of the respectively adjacent blade element, forming an essentially radial gap ( 3 ) in each case, and at least one blade element ( 1 ), on a first side ( 4 ) which points in the circumferential direction (U), has a projection ( 6 ) which projects into the shroud element ( 13 ) of the abutting blade element ( 1 ) and extends in the circumferential direction (U), and at least one blade element ( 1 ), on a second side ( 5 ) which points in the circumferential direction (U), has a recess ( 7 ) which accommodates such a projection ( 6 ), wherein in the region of the projection ( 6 ) or of the recess ( 7 ) there is a stepped region ( 2 ) of the radial gap, the guiding of the radial gap ( 3 ) in the stepped region ( 2 ) is a labyrinth seal and the radial gap ( 3 ) in the stepped region ( 2 ) has at least one narrowing ( 18 ) and/or at least one widening ( 19 ) and has more than two changes of direction in the stepped region.