Abstract: An apparatus and method for machining of components, namely for rotary machining of rotationally symmetrical components on radially interior machining surfaces of a component, is disclosed. The device has a drill rod extending essentially axially and has a tool mount extending essentially radially, carrying a lathe tool. The drill rod has a projection that extends essentially radially and can be coupled to the tool mount that extends essentially radially, where the radial dimensions of the projection of the drill rod and of the tool mount are adapted to the dimensions of a hub bore of the component to be machined, such that the drill rod and the tool mount in the uncoupled state can be inserted into the hub bore, and, in the coupled state, the lathe tool mounted in the tool mount can be brought into contact with the radially interior machining surfaces of the component.

Abstract: A method for producing a lightweight turbine blade for a gas turbine is disclosed. In an embodiment, the method includes casting of a blade element with a blade wall and at least one cavity enclosed by the blade wall. The blade wall is at least partially reduced in thickness by machining after the casting. This provides a method for producing a blade element, in which the wall thickness of the blade wall can be adapted to the mechanical load of the blade element, and the weight of the blade element can be reduced at the same time.

Abstract: A fan for an aircraft engine, particularly a gas turbine aircraft engine, is disclosed. The fan has a fan rotor with fan blades, which extend radially outwardly from a hub to an outer flow path wall of a fan flow path. The fan has an auxiliary rotor that is positioned upstream of the fan rotor and has auxiliary blades that extend radially outwardly from a hub and end at a distance from the outer flow path wall of the fan flow path. The auxiliary rotor and the fan rotor are designed as separate rotors, such that the auxiliary rotor can be operated at a higher speed than the fan rotor.

Abstract: A rotor of a turbo engine, e.g., a gas turbine rotor, has a rotor base member, the rotor base member having a groove extending in the circumferential direction of the rotor base member, and having a plurality of rotor blades, each rotor blade having a blade, a blade root and a blade platform positioned between the blade and the blade root, and the rotor blades being anchored in the groove of the rotor base member by their blade roots. The groove and the blade roots have a profile, such that the blade roots of the rotor blades are insertable by a tilting motion or swiveling motion into the circumferentially extending groove of the rotor base member, and in the circumferential direction, a width of the blade root corresponds approximately to a width of the blade platform of the specific rotor blade.

Abstract: A gas turbine, in particular an aircraft engine and to a method for generating electrical energy in a gas turbine is provided. The gas turbine comprises at least on engine core (18), in which a shaft (19) produces a shaft output. The turbine is equipped with means that generate electrical energy both from the shaft output produced by the engine core (18) and from the compressed air that is dissipated by the engine core (18).

Abstract: A planetary gear train is described which includes a sun gear, three or more planet gears, an annulus as well as a planet gear carrier, whereby the input is provided via the sun gear and the output is provided via the annulus or via the planet gear carrier, whereby each planet gear is mounted on both sides in a roller bearing, and whereby the planet gear carrier includes two axially spaced bearing washers as well as at least three webs that connect the bearing washers. Each roller bearing is configured as a single-row or multi-row cylindrical roller bearing, each planet gear has a flexurally elastic axis projecting axially on both sides beyond the gear body of the planet gear, and the connection between each roller bearing and the appertaining axis is configured to be spherically moveable.

Abstract: An apparatus and method for machining of components, namely for rotary machining of rotationally symmetrical components on radially interior machining surfaces of a component, is disclosed. The device has a drill rod extending essentially axially and has a tool mount extending essentially radially, carrying a lathe tool. The drill rod has a projection that extends essentially radially and can be coupled to the tool mount that extends essentially radially, where the radial dimensions of the projection of the drill rod and of the tool mount are adapted to the dimensions of a hub bore of the component to be machined, such that the drill rod and the tool mount in the uncoupled state can be inserted into the hub bore, and, in the coupled state, the lathe tool mounted in the tool mount can be brought into contact with the radially interior machining surfaces of the component.

Abstract: A rotor of a turbine-type machine, in particular a gas turbine rotor, is disclosed. The rotor has a rotor base body, where the rotor base body has a groove extending in the circumferential direction of the rotor base body, and has multiple rotor blades, or rotor blade segments, or an integrally bladed, circumferentially closed rotor blade ring. The rotor blades, or rotor blade segments, or rotor blade ring are/is anchored in the groove extending in the circumferential direction of the rotor base body by a blade base or ring base. The groove has a profiled groove wall leg on only one side, with the blade base of the rotor blades or the rotor blade segments, or ring base of the rotor blade ring, being in contact with the profiled groove wall leg with a correspondingly profiled supporting flank.

Abstract: A rotor of a turbine-type machine, in particular a gas turbine rotor, is disclosed. The rotor has a rotor base body, where the rotor base body has a groove extending in the circumferential direction of the rotor base body, and has multiple rotor blades or rotor blade segments. The rotor blades or rotor blade segments are each anchored in the groove extending in the circumferential direction of the rotor base body by a blade base. The groove has a profiled groove wall leg on only one side, with the blade base of the rotor blades or the rotor blade segments being in contact with the profiled groove wall leg with a correspondingly profiled supporting flank.

Abstract: A gas turbine, in particular an aircraft engine and to a method for generating electrical energy in a gas turbine is provided. The gas turbine comprises at least on engine core (18), in which a shaft (19) produces a shaft output. The turbine is equipped with means that generate electrical energy both from the shaft output produced by the engine core (18) and from the compressed air that is dissipated by the engine core (18).

Abstract: A rotor of a turbine-type machine, in particular a gas turbine rotor, is disclosed. The rotor has a rotor base body, where the rotor base body has a groove extending in the circumferential direction of the rotor base body, and has multiple rotor blades, or rotor blade segments, or an integrally bladed, circumferentially closed rotor blade ring. The rotor blades, or rotor blade segments, or rotor blade ring are/is anchored in the groove extending in the circumferential direction of the rotor base body by a blade base or ring base. The groove has a profiled groove wall leg on only one side, with the blade base of the rotor blades or the rotor blade segments, or ring base of the rotor blade ring, being in contact with the profiled groove wall leg with a correspondingly profiled supporting flank.

Abstract: A rotor of a turbine-type machine, in particular a gas turbine rotor, is disclosed. The rotor has a rotor base body, where the rotor base body has a groove extending in the circumferential direction of the rotor base body, and has multiple rotor blades or rotor blade segments. The rotor blades or rotor blade segments are each anchored in the groove extending in the circumferential direction of the rotor base body by a blade base. The groove has a profiled groove wall leg on only one side, with the blade base of the rotor blades or the rotor blade segments being in contact with the profiled groove wall leg with a correspondingly profiled supporting flank.

Abstract: A rotor of a turbo engine, e.g., a gas turbine rotor, has a rotor base member, the rotor base member having a groove extending in the circumferential direction of the rotor base member, and having a plurality of rotor blades, each rotor blade having a blade, a blade root and a blade platform positioned between the blade and the blade root, and the rotor blades being anchored in the groove of the rotor base member by their blade roots. The groove and the blade roots have a profile, such that the blade roots of the rotor blades are insertable by a tilting motion or swiveling motion into the circumferentially extending groove of the rotor base member, and in the circumferential direction, a width of the blade root corresponds approximately to a width of the blade platform of the specific rotor blade.

Abstract: A fan for an aircraft engine, particularly a gas turbine aircraft engine, is disclosed. The fan has a fan rotor with fan blades, which extend radially outwardly from a hub to an outer flow path wall of a fan flow path. The fan has an auxiliary rotor that is positioned upstream of the fan rotor and has auxiliary blades that extend radially outwardly from a hub and end at a distance from the outer flow path wall of the fan flow path. The auxiliary rotor and the fan rotor are designed as separate rotors, such that the auxiliary rotor can be operated at a higher speed than the fan rotor.

Abstract: Cooling air system for reducing the thermal load on components in the turbine high-pressure region of gas turbines, having blades/vanes which respectively have a plurality of separate flow chambers for different airflows, and having cooling air guidance from the high-pressure region of the compressor into the blading of the high-pressure region of the turbine. Each of the highly loaded blades/vanes has a front flow chamber, at least one central flow chamber and a rear flow chamber. The cooling guidance includes at least one heat exchanger for a part of the cooling air and a flow connection from the heat exchanger to the front and to the rear flow chambers of each blade/vane, with the cooling air guidance to the central flow chamber of each blade/vane bypassing the heat exchanger.

Abstract: A rotor for a turbomachine, having at least two bladed stages, the discs of which are detachably connected to one another, in which rotor, in order to avoid notch locations in the highly stressed discs, a first disc, at least at one side face, has a first flange which is connected to or restrained with a second flange of an adjacent disc by bolts.

Abstract: An engine with counter-rotating rotors, which are coaxially arranged and are driven via a shaft by a turbine whose working medium is supplied by a gas generator with an air inlet, the air inlet (3) being arranged between (in the axial direction) the rotors (1, 2) in order to reduce the noise annoyance (FIG. 1), the rotors driven by an epicyclic gear, the internal gearwheel driving the rear rotor the plant carrier driving the front rotor.

Abstract: A flow machine with rotor and stator in axial structure in flow-oriented terms, at least in sections, having moving blades at the rotor and housing-fixed guide vanes, whereby the latter are arranged as at least one guide vane ring with an inner and an outer cover band. The at least one guide vane ring is implemented as self-bearing component part having a closed reinforcement at the inner cover band that reinforces the component part to resist jamming axial deformation, comprises a segmented outer cover band and is positioned in the housing over at least three cover band segments with bearing units that respectively allow radial relative movements. An air guide shell that guides a cooling air stream along the inside of the housing and is provided with openings for the housing-fixed bearing elements of the at least one guide vane ring is arranged between the housing and the outer cover band of the at least one guide vane ring.

Abstract: In a gas generator of a gas turbine, the turbine is provided with more stages than aerodynamically necessary for reducing the turbine rotational speed. As a result thereof, the stresses of the turbine rotor are reduced, the latter can be made of ceramic material, and the turbine inlet temperature can be increased. In order to permit the compressor to continue to operate at optimum rotational speed, the compressor is coupled with the turbine by way of a transmission providing a speed-up. Owing to this arrangement, the thermal efficiency and therewith the economy of the gas turbine can be considerably increased and the heretofore occurring problems with the use of ceramic material in the turbine are solved in a simple manner.