A gas turbine engine stage, the stage extending along a rotation axis and comprising: - a static part; - a rotating part; and - a labyrinth seal arranged radially between said static part and rotating part (26, 27) and comprising: a) a layer of abradable material, which is arranged on said static part, is continuous in the axial direction and, in an initial assembly configuration, is radially delimited by a cylindrical surface having a constant diameter; b) at least three tabs (30, 31, 32), that radially project from said rotating part, are axially set apart from each other and end with respective tips (33, 34, 35), directly facing said layer of abradable material in the radial direction; said three tabs constituted by: - two side tabs (30, 32) and - one intermediate tab, which is arranged in an intermediate axial position between said side tabs (30, 32) and has a smaller radial height than that of said side tabs (30, 32); said intermediate tab having a sufficient radial height to at least nick into said cylindrical surface due to the effect of thermal expansion and of the relative rotation when the gas turbine engine, during operation, reaches a running operational configuration; the three tabs (30, 31, 32) being axially positioned in such a way that, in the running operational configuration: - the layer of abradable material is radially defined by a shaped surface defining two seats (39, 40), which have been fretted by the tips (33, 35) of said side tabs (30, 32) during operation and are axially separated from each other by a step of said shaped surface; and - the tip of said intermediate tab is arranged at said step. - a static part; - a rotating part; and - a labyrinth seal arranged radially between said static part and rotating part (26, 27) and comprising: a) a layer of abradable material, which is arranged on said static part, is continuous in the axial direction and, in an initial assembly configuration, is radially delimited by a cylindrical surface having a constant diameter; b) at least three tabs (30, 31, 32), that radially project from said rotating part, are axially set apart from each other and end with respective tips (33, 34, 35), directly facing said layer of abradable material in the radial direction; a) a layer of abradable material, which is arranged on said static part, is continuous in the axial direction and, in an initial assembly configuration, is radially delimited by a cylindrical surface having a constant diameter; b) at least three tabs (30, 31, 32), that radially project from said rotating part, are axially set apart from each other and end with respective tips (33, 34, 35), directly facing said layer of abradable material in the radial direction; - two side tabs (30, 32) and - one intermediate tab, which is arranged in an intermediate axial position between said side tabs (30, 32) and has a smaller radial height than that of said side tabs (30, 32); - the layer of abradable material is radially defined by a shaped surface defining two seats (39, 40), which have been fretted by the tips (33, 35) of said side tabs (30, 32) during operation and are axially separated from each other by a step of said shaped surface; and - the tip of said intermediate tab is arranged at said step.