Abstract: A method for profiling blades of an axial turbomachine includes preparing a geometric model of a blade profile; determining an oscillation mode of the geometric model; calculating a time profile of a position-dependent disruptive pressure in a channel between two adjacent blade profiles over an oscillation period of the oscillation belonging to the oscillation mode, changing the geometric model and determining a different oscillation mode for the modified geometric model; and determining the damping of the oscillation using the disruptive pressure profile calculated previously and accepting the modified geometric model for the case that the damping of the oscillation turns out to be greater than calculated, otherwise repeating the last two steps with another modified geometric model.

Abstract: A bladed rotor system includes first and second sets of blades with respective airfoils each having at least one internal cavity. The airfoils of both the first and second sets of blades have identical outer shapes defined by an outer surface of an outer wall of the respective airfoils. The airfoils of the first set of blades are distinguished from the airfoils of the second set of blades by a geometry and/or position of at the least one internal cavity, which is unique to blades of a given set. The natural frequency of a blade of the first set differs from the natural frequency of a blade of the second set by a predetermined amount. The blades of the first set and the second set are alternately arranged in a periodic fashion in said circumferential row, to provide a frequency mistuning to stabilize flutter of the blades.

Abstract: A bladed rotor system includes first and second sets of blades with respective airfoils each having at least one internal cavity. The airfoils of both the first and second sets of blades have identical outer shapes defined by an outer surface of an outer wall of the respective airfoils. The airfoils of the first set of blades are distinguished from the airfoils of the second set of blades by a geometry and/or position of at the least one internal cavity, which is unique to blades of a given set. The natural frequency of a blade of the first set differs from the natural frequency of a blade of the second set by a predetermined amount. The blades of the first set and the second set are alternately arranged in a periodic fashion in said circumferential row, to provide a frequency mistuning to stabilize flutter of the blades.

Abstract: A method for profiling a turbine rotor blade for an axial flow machine, having the following steps: providing a geometric model of a blade profile, having a camber line of a profile section of the turbine rotor blade; determining boundary conditions for a flow flowing around the turbine rotor blade; changing the camber line such that the flow which is adjusted by the boundary conditions produces the maximum of the difference of the isentropic mach number between the pressure side and the suction side of the turbine rotor blade in a blade section which extends from the blade trailing edge in the direction towards the blade leading edge and the length of which is 65% of the length S of the blade chord.

Abstract: A method for profiling blades of an axial turbomachine includes preparing a geometric model of a blade profile; determining an oscillation mode of the geometric model; calculating a time profile of a position-dependent disruptive pressure in a channel between two adjacent blade profiles over an oscillation period of the oscillation belonging to the oscillation mode, changing the geometric model and determining a different oscillation mode for the modified geometric model; and determining the damping of the oscillation using the disruptive pressure profile calculated previously and accepting the modified geometric model for the case that the damping of the oscillation turns out to be greater than calculated, otherwise repeating the last two steps with another modified geometric model.

Abstract: A method for profiling a turbine rotor blade for an axial flow machine, having the following steps: providing a geometric model of a blade profile, having a camber line of a profile section of the turbine rotor blade; determining boundary conditions for a flow flowing around the turbine rotor blade; changing the camber line such that the flow which is adjusted by the boundary conditions produces the maximum of the difference of the isentropic mach number between the pressure side and the suction side of the turbine rotor blade in a blade section which extends from the blade trailing edge in the direction towards the blade leading edge and the length of which is 65% of the length S of the blade chord.

Abstract: A steam turbine arrangement and a method for operating a steam turbine, wherein the steam turbine is supplied with steam via a first valve in a first steam supply line and via a second valve in a second steam supply line. The valves are controlled asymmetrically so that in the event of unwanted vibrations measured by acceleration sensors one valve closes and the other valve opens in order to ensure the desired total mass flow.

Abstract: A turbine condenser includes an area with condenser tubes for liquefying waste steam from the steam turbine, a chamber formed by condenser walls for receiving the waste steam, and a diverted steam channelling system for channelling diverted steam into the chamber in the turbine condenser, wherein the diverted steam channelling system includes an annular nozzle extending into the turbine condenser, the outlet end of which has an uneven edge.

Abstract: A safety device for a turbine blade is provided. The safety device includes a shear pin, a clamping piece and a securing element, wherein the shear pin is arranged in a corresponding bore in the turbine blade foot and the clamping piece is designed having an upper limb and a lower limb, wherein the clamping piece exerts a radial force on the turbine blade foot for radial safeguarding.

Abstract: A diversion station is provided. The diversion station makes it possible to particularly effectively cool diverted water vapor by mixing it with water. The diversion station includes a mixing device, which comprises a so-called static mixer that is substantially made of a wire mesh. The wire mesh is produced by at least one wire that is substantially interlaced into loops. In the intended installation situation, the mixer is installed upstream of a water injection with regard to a flow direction specified by the water vapor such that the mixture of water and water vapor flows through the loops.

Abstract: A safety device for a turbine blade is provided. The safety device includes a shear pin, a clamping piece and a securing element, wherein the shear pin is arranged in a corresponding bore in the turbine blade foot and the clamping piece is designed having an upper limb and a lower limb, wherein the clamping piece exerts a radial force on the turbine blade foot for radial safeguarding.

Abstract: A diversion station is provided. The diversion station makes it possible to particularly effectively cool diverted water vapor by mixing it with water. The diversion station includes a mixing device, which comprises a so-called static mixer that is substantially made of a wire mesh. The wire mesh is produced by at least one wire that is substantially interlaced into loops. In the intended installation situation, the mixer is installed upstream of a water injection with regard to a flow direction specified by the water vapor such that the mixture of water and water vapor flows through the loops.

Abstract: A turbine blade is provided, comprising a stator-side end located toward a stationary stator cylinder of the turbine, a rotor-side end located toward an axial rotor of the turbine, a leading edge located between the stator-side end and the rotor-side end, a trailing edge located between the stator-side end and the rotor-side end and located down-stream of the leading edge with respect to a fluid flow direction, wherein the rotor-side and stator-side ends have a negative sweep angle as measured between the instantaneous tangent of the blade surface and the fluid flow direction.

Abstract: An array of blades for use in a turbomachine is provided comprising a plurality of blades mounted to a rotor disk. A plurality of first blades form a first set of blades and a plurality of second blades form a second set of blades. A blade-to-blade flow field defined between successive ones of the first set of blades is interrupted by the second set of blades to form an asymmetric blade-to-blade flow field around the array of blades. The trailing edges of the second set of blades are positioned forwardly from a line connecting the trailing edges of the first set of blades such that shock forces in the flow field around the array of blades will generally impinge on a stable region of the first set of blades.

Abstract: An array of blades for use in a turbomachine is provided comprising a plurality of blades mounted to a rotor disk. A plurality of first blades form a first set of blades and a plurality of second blades form a second set of blades. A blade-to-blade flow field defined between successive ones of the first set of blades is interrupted by the second set of blades to form an asymmetric blade-to-blade flow field around the array of blades. The trailing edges of the second set of blades are positioned forwardly from a line connecting the trailing edges of the first set of blades such that shock forces in the flow field around the array of blades will generally impinge on a stable region of the first set of blades.

Abstract: The invention relates to the use of a copper-titanium-cobalt-alloy which consists of 0.05-0.6% titanium; 0.05-0.6% cobalt; remainder copper, whereby the cobalt is partially replaced by iron. Due to its excellent characteristics with respect to electrical and thermal conductivity, mechanical strength, softening resistance and homogeneity, the alloy is used as the material for electronic components, in particular lead frames for transistors, integrated circuits or the like, and parts for electronic components for automobiles.

Abstract: The invention relates to a copper-chromium-titanium-silicon alloy which consists of 0.1 to 0.5% chromium, 0.05 to 0.5% titanium and 0.01 to 0.1% silicon, the remainder comprising copper and usual impurities. Because of its excellent properties as regards electrical and thermal conductivity, mechanical strength, resistance to softening, homogeneity and flexibility, the alloy is employed as a material for electronic components, in particular semiconductor carriers for transistors, integrated circuits or the like, and parts for electrical systems for cars.