Abstract: An aircraft gas turbine with a fan disk on which are fastened fan blades spread over the circumference and forming an intermediate space with one another, with a sealing disk arranged at the rear of the fan disk and with an inlet cone mounted at the front of the fan disk, as well as with filler elements arranged in the intermediate spaces, where the sealing disk has an annular groove and where the filler elements are at the rear inserted into the annular groove and at the front held underneath a rim area of the inlet cone, characterized in that the filler elements are designed as bending beams and that on the radially inner side of the filler element at least one rib-like reinforcing area is provided, extending in the axial direction and longitudinally to the filler element.

Abstract: An aircraft gas turbine with a fan disc at which fan blades, distributed around the circumference and forming an intermediate space in between each other, are attached, with a sealing disc that is arranged on the back side of the fan disc, and with an inlet cone that is mounted at the front side of the fan disc, as well as with filling elements that are arranged in the intermediate spaces, wherein the inlet cone includes strip-shaped lugs which are configured in one piece with the same and which can be inserted into the intermediate spaces, with their free ends being inserted into a ring groove that is formed at the sealing disc, and in that a filling element is arranged on each strip-shaped lug.

Abstract: An aircraft gas turbine with a fan disc at which fan blades 31, distributed around the circumference and forming an intermediate space in between each other, are attached, with a sealing disc that is arranged on the back side of the fan disc, and with an inlet cone that is mounted at the front side of the fan disc, as well as with filling elements that are arranged in the intermediate spaces, characterized in that the inlet cone includes strip-shaped lugs which are configured in one piece with the same and which can be inserted into the intermediate spaces, with their free ends being inserted into a ring groove that is formed at the sealing disc, and in that a filling element is arranged on each strip-shaped

Abstract: An aircraft gas turbine with a fan disk on which are fastened fan blades spread over the circumference and forming an intermediate space with one another, with a sealing disk arranged at the rear of the fan disk and with an inlet cone mounted at the front of the fan disk, as well as with filler elements arranged in the intermediate spaces, where the sealing disk has an annular groove and where the filler elements are at the rear inserted into the annular groove and at the front held underneath a rim area of the inlet cone, characterized in that the filler elements are designed as bending beams and that on the radially inner side of the filler element at least one rib-like reinforcing area is provided, extending in the axial direction and longitudinally to the filler element.