Abstract: A rotor device of a turbomachine, having a disc wheel and a plurality of rotor blades that are arranged circumferentially inside recesses of the disc wheel and that are fixed at the disc wheel in the axial direction by means of a securing appliance. At least one flow channel that extends at least substantially in the axial direction is assigned to each recess. The securing appliance has a plurality of recesses, wherein a number and arrangement of the recesses is chosen such that the entire cross-sectional surface of the securing appliance passable by the flow, which is defined as the sum of an overlap of the recesses with at least one flow channel as viewed in the axial direction, is substantially independent of a circumferential position of the securing appliance relative to the disc wheel.

Abstract: A method for producing a structural component including the following steps: a) forming of the structural component; b) removing material from the structural component; c) thermal treatment of the structural component following step b; d) removing further material from the structural component following step c.

Abstract: A rotor device of a turbomachine, having a disc wheel and a plurality of rotor blades that are arranged circumferentially inside recesses of the disc wheel and that are fixed at the disc wheel in the axial direction by means of a securing appliance. At least one flow channel that extends at least substantially in the axial direction is assigned to each recess. The securing appliance has a plurality of recesses, wherein a number and arrangement of the recesses is chosen such that the entire cross-sectional surface of the securing appliance passable by the flow, which is defined as the sum of an overlap of the recesses with at least one flow channel as viewed in the axial direction, is substantially independent of a circumferential position of the securing appliance relative to the disc wheel.

Abstract: A turbomachine, in particular a jet engine of an aircraft, with a rotor device and a stator device, wherein a sealing appliance is arranged preferably in the radial direction between the rotor device and the stator device, with the sealing appliance having a support arm that extends substantially in the axial direction and is connected to the rotor device in a torque-proof manner. The support arm has a sealing lip on the side that faces towards the stator device, and has a covering overlap with an adjoining surface of the rotor device at its inner side. At least one cooling air opening is arranged in the surface of the rotor device in an area of the covering overlap of the support arm of the sealing appliance with the rotor device.

Abstract: A jet engine with a cooling device for cooling engine components and formed by a secondary air system, and with a central shaft that rotates about an engine axis during operation. A further cooling device is provided that includes a first fluid guiding channel extending coaxially to the central engine axis and configured for conducting cooling fluid in a first axial direction, a second fluid guiding channel radially surrounding the first fluid guiding channel and being configured for conducting cooling fluid in a second axial direction that is opposite to the first axial direction, and a deflection area for deflecting the cooling fluid from the first fluid guiding channel into the second fluid guiding channel or from the second fluid guiding channel into the first fluid guiding channel in an end area of the first fluid guiding channel and of the second fluid guiding channel.