Abstract: A sample disc for ultrasonic disc testing equipment includes a cut-out defining a lateral face extending along a radius of the sample disc and along an axis of symmetry of the sample disc. At least one planar sample defect is created through this lateral face of the disc.

Abstract: A rotor for an axial flow turbomachine is provided, having a number of a plurality of disc-shaped or drum-shaped rotor components and at least one pin-shaped tie-rod extending through the rotor components, wherein a counter-bearing is screwed onto each of the projecting ends of the tie-rod for axially bracing the rotor components arranged therebetween. The tie-rod has at least two axially adjacent tie-rod elements which are each connected to one another in a detachable manner by connector. Elastic stretching characteristics of the two tie-rod elements are matched to each other such that, with the rotor components being clamped between the two counter-bearings, a clamping of the counter-bearing and the connection element and the rotor components arranged therebetween is at least partially released.

Abstract: A method for assembling and disassembling a rotor having a number of rotor components of an axial flow turbomachine and such a rotor is provided. The rotor has a number of a plurality of disc-shaped or drum-shaped rotor components and at least one pin-shaped tie-rod extending through the rotor components, wherein a counter-bearing is screwed onto each of the projecting ends of said tie-rod for axially bracing the rotor components arranged therebetween. In order to achieve shorter service intervals, a connector is screwed onto the tie-rod between both counter-bearings, wherein, after the release of one of the two counter-bearings, the rotor components arranged between the connector and the other of the two counter-bearings are braced with each other by the connector.

Abstract: A gas turbine component for example a turbine blade or a rotor disk is provided. In order to extend the service life of the corresponding component by reducing the thermally or mechanically induced stress concentration in the direct surroundings of a duct opening onto a surface, at least one groove-like recess is provided near the effective zone of the opening.

Abstract: A rotor section for a rotor of a gas turbine, a rotor blade, and a blocking element are provided. The rotor section includes a rotor disk including rotor blades that are inserted thereon in holding grooves and that are secured against sliding along the holding grooves by means of a sealing element arranged at the end face. In order to specify a reliable, simple, and easy-to-design construction for the circumferential fixing of the sealing elements, it is proposed that each sealing element be secured by one blocking element, which engages in a hole arranged at the end face in the rotor blade root.

Abstract: A rotor section for a rotor of a gas turbine is provided. The rotor section includes a rotor disk with rotor blades inserted in retaining grooves thereupon, the rotor blades being secured against displacement along the retaining grooves by means of a sealing element which is arranged on the end face. In order to disclose a reliable construction which can be designed in a straightforward and simple manner for the circumferential fixing of the sealing element, each sealing element is secured by means of a blocking element in each case which in this case engages in a hole which is arranged in the rotor blade root on the end face.

Abstract: A rotor of a thermal turbomachine, particularly a gas turbine, is provided. The rotor includes a plurality of individual rotor components that are held together by a tie-bold and combined into a unit. The tie-bolt is supported by the assembly of the surrounding rotor components including the tie-bolt and the rotor disks. A hollow shaft which is made up of two tubular sections and a support wheel further support the rotor.

Abstract: A rotor of a thermal fluid flow machine, especially a gas turbine, is provided. The rotor includes a plurality of rotor components that are held together by a common tie-bolt that extends through the center of the rotor components. The tie-bolt is fixed in at least one of the rotor components using at least one star spring that surrounds the tie-bolt in a circumferential direction.

Abstract: A rotor for an axial flow turbomachine is provided. The rotor includes a plurality of rotor discs that are arranged in stacks and clamped together with at least one tie rod. At least one of the rotor discs of the rotor comprises a smaller outer diameter than one of the neighboring rotor discs and that the difference in diameter is compensated by a drum surrounding the rotor disc with the smaller outer diameter as a ring. The drum may be made of a heat resistant material. The rotor discs surrounded by the drum may be made of a less expensive material. Furthermore, the drum may include at least one more blade ring than the rotor discs that are surrounded by the drum.

Abstract: A gas turbine component for example a turbine blade or a rotor disk is provided. In order to extend the service life of the corresponding component by reducing the thermally or mechanically induced stress concentration in the direct surroundings of a duct opening onto a surface, at least one groove-like recess is provided near the effective zone of the opening.

Abstract: A rotor section for a rotor of a gas turbine is provided. The rotor section includes a rotor disk with rotor blades inserted in retaining grooves thereupon, the rotor blades being secured against displacement along the retaining grooves by means of a sealing element which is arranged on the end face. In order to disclose a reliable construction which can be designed in a straightforward and simple manner for the circumferential fixing of the sealing element, each sealing element is secured by means of a blocking element in each case which in this case engages in a hole which is arranged in the rotor blade root on the end face.

Abstract: A novel ferritic martensitic alloy is provided. The ferritic martensitic alloy enables the use temperature to be increased from 500° C. to 550° C., where the strength is maintained or is even maximized and the toughness, especially for low temperatures, is maintained compared to the known iron-based alloys. Tunsten is preferably not used.

Abstract: A rotor section for a rotor of a gas turbine, a rotor blade, and a blocking element are provided. The rotor section includes a rotor disk including rotor blades that are inserted thereon in holding grooves and that are secured against sliding along the holding grooves by means of a sealing element arranged at the end face. In order to specify a reliable, simple, and easy-to-design construction for the circumferential fixing of the sealing elements, it is proposed that each sealing element be secured by one blocking element, which engages in a hole arranged at the end face in the rotor blade root.

Abstract: A rotor for an axial flow turbomachine is provided. The rotor includes a plurality of rotor discs that are arranged in stacks and clamped together with at least one tie rod. At least one of the rotor discs of the rotor comprises a smaller outer diameter than one of the neighboring rotor discs and that the difference in diameter is compensated by a drum surrounding the rotor disc with the smaller outer diameter as a ring. The drum may be made of a heat resistant material. The rotor discs surrounded by the drum may be made of a less expensive material. Furthermore, the drum may include at least one more blade ring than the rotor discs that are surrounded by the drum.

Abstract: A rotor of a thermal turbomachine, particularly a gas turbine, is provided. The rotor includes a plurality of individual rotor components that are held together by a tie-bold and combined into a unit. The tie-bolt is supported by the assembly of the surrounding rotor components including the tie-bolt and the rotor disks. A hollow shaft which is made up of two tubular sections and a support wheel further support the rotor.

Abstract: A rotor of a thermal fluid flow machine, especially a gas turbine, is provided. The rotor includes a plurality of rotor components that are held together by a common tie-bolt that extends through the center of the rotor components. The tie-bolt is fixed in at least one of the rotor components using at least one star spring that surrounds the tie-bolt in a circumferential direction.