Abstract: A method for designing a stage for an axial turbomachine having a guide blade ring and a rotor blade ring arranged downstream of the guide blade ring is provided. The method includes: profiling a guide blade ring having guide blades arranged regularly over the circumference of the guide blade ring in accordance with basic aerodynamic and mechanical conditions; moving at least one profile section of at least one of the guide blades in the circumferential direction in such a way that the pitch angle for the at least one guide blade and a guide blade arranged adjacent thereto varies over the blade height in such a way that during operation of the axial turbomachine the departing flow formed downstream of the guide blade ring is irregularly formed over the circumference of the axial turbomachine, such that the vibration excitation of the rotor blades of the rotor blade ring is low.

Abstract: A method for designing a stage for an axial turbomachine having a guide blade ring and a rotor blade ring arranged downstream of the guide blade ring is provided. The method includes: profiling a guide blade ring having guide blades arranged regularly over the circumference of the guide blade ring in accordance with basic aerodynamic and mechanical conditions; moving at least one profile section of at least one of the guide blades in the circumferential direction in such a way that the pitch angle for the at least one guide blade and a guide blade arranged adjacent thereto varies over the blade height in such a way that during operation of the axial turbomachine the departing flow formed downstream of the guide blade ring is irregularly formed over the circumference of the axial turbomachine, such that the vibration excitation of the rotor blades of the rotor blade ring is low.

Abstract: A turbine blade fastening is provided. The turbine blade fastening include a blade root implemented in a fir tree design, which includes anchoring teeth implemented toward the blade casting tip such that the height of the anchoring teeth is reduced toward the blade casting tip. The anchoring teeth are designed for fitting into corresponding recesses in a rotor.

Abstract: A turbine blade system including a first turbine blade and a second turbine blade being arranged adjacent to each other shall be suited to allow a particularly secure and reliable operation of a turbine. To this end, the turbine blades are in contact in a first surface area and separated from each other in a second surface area, wherein the first turbine blade includes a pocket containing a damping piece in the second surface area.

Abstract: An arrangement for damping blade vibrations in a turbomachine is provided. The blade vibrations are due to an arrangement made of magnets and multiple induction plates and the undesired vibrations of the blade are damped by creating turbulent flows, wherein the induction plates are directed parallel to the rotation axis, and the magnetic field caused by the magnets is formed homogenously in the circumferential direction.

Abstract: A turbine blade fastening is provided. The turbine blade fastening include a blade root implemented in a fir tree design, which includes anchoring teeth implemented toward the blade casting tip such that the height of the anchoring teeth is reduced toward the blade casting tip. The anchoring teeth are designed for fitting into corresponding recesses in a rotor.

Abstract: A turbine-blade locking device having a wedge movable in an axial direction is disclosed. The wedge is movable in the axial direction by a tensioning device, as a result of which a force is produced in the axial direction. The force in the axial direction causes the turbine blade to be pressed against the blade holder.

Abstract: A turbine blade system including a first turbine blade and a second turbine blade being arranged adjacent to each other shall be suited to allow a particularly secure and reliable operation of a turbine. To this end, the turbine blades are in contact in a first surface area and separated from each other in a second surface area, wherein the first turbine blade includes a pocket containing a damping piece in the second surface area.

Abstract: A damping system for damping the vibrations of a blade union is provided. The blades arranged in a neighboring manner are coupled to one another via a coupling element, wherein the coupling element is arranged fixed in a first blade and extends into the second blade, wherein the coupling element is not arranged in the second blade but rather solely contacts there such that, as a consequence of centrifugal forces, a free end of the coupling element presses against the second blade and a friction force thus occurs, leading to an energy dissipation and vibrations being thus damped.

Abstract: An arrangement for damping blade vibrations in a turbomachine is provided. The blade vibrations are due to an arrangement made of magnets and multiple induction plates and the undesired vibrations of the blade are damped by creating turbulent flows, wherein the induction plates are directed parallel to the rotation axis, and the magnetic field caused by the magnets is formed homogenously in the circumferential direction.

Abstract: A turbine-blade locking device having a wedge movable in an axial direction is disclosed. The wedge is movable in the axial direction by a tensioning device, as a result of which a force is produced in the axial direction. The force in the axial direction causes the turbine blade to be pressed against the blade holder.