Abstract: A blade construction for a turbo device, preferably a blade array of a low-pressure turbine, is disclosed. On the inlet-side profile surface of the blade a vortex generator is arranged downstream from the speed maximum. The vortex generator is formed by a surface undulation with at least one wave, the wave tail of which runs in the form of a wave trough and/or a wave peak in the blade vertical direction.

Abstract: A device and method for axially displacing at least one turbine rotor relative to at least one corresponding turbine stator in a multistage axial turbine is disclosed. The turbine shaft is provided with a split design and has a first axially displaceable shaft half, which is connected via a turbine disc to the turbine rotor and via a torque coupling to the second shaft half. By axially displacing the turbine rotor relative to the turbine stator and by controlling this axial displacement, the operation of the turbine is held in its possible optimum of efficiency.

Abstract: A blade construction for a turbo device, preferably a blade array of a low-pressure turbine, is disclosed. On the inlet-side profile surface of the blade a vortex generator is arranged downstream from the speed maximum. The vortex generator is formed by a surface undulation with at least one wave, the wave tail of which runs in the form of a wave trough and/or a wave peak in the blade vertical direction.

Abstract: A method for flow optimization in multi-stage turbine-type machines in which the inflow of a third of three consecutive blade rings is optimized, the first and the third blade ring having the same number of blades being situated on the same unit, rotor or stator, the second blade ring being situated on the other of the two units, rotor or stator, and an operating state, occurring during a high proportion of the operating time, being selected by ascertaining or predefining the appropriate operating parameters. In this operating state, the maxima of the obstruction, periodically occurring in the area of the outlet edges of the blade profiles of the second blade ring, are deflected onto the inlet edges of the blade profiles of the third blade ring within a predefined tolerance angle; the positions or the geometries of blade profiles of at least one of the three blade rings are modified as needed.

Abstract: A device and method for axially displacing at least one turbine rotor relative to at least one corresponding turbine stator in a multistage axial turbine is disclosed. The turbine shaft is provided with a split design and has a first axially displaceable shaft half, which is connected via a turbine disc to the turbine rotor and via a torque coupling to the second shaft half. By axially displacing the turbine rotor relative to the turbine stator and by controlling this axial displacement, the operation of the turbine is held in its possible optimum of efficiency.

Abstract: A method for flow optimization in multi-stage turbine-type machines in which the inflow of a third of three consecutive blade rings is optimized, the first and the third blade ring having the same number of blades being situated on the same unit, rotor or stator, the second blade ring being situated on the other of the two units, rotor or stator, and an operating state, occurring during a high proportion of the operating time, being selected by ascertaining or predefining the appropriate operating parameters. In this operating state, the maxima of the obstruction, periodically occurring in the area of the outlet edges of the blade profiles of the second blade ring, are deflected onto the inlet edges of the blade profiles of the third blade ring within a predefined tolerance angle; the positions or the geometries of blade profiles of at least one of the three blade rings are modified as needed.

Abstract: A blade row arrangement for turbo-engines has an axial construction with two guide blade rows fixedly positioned relative to one another and having a different number of blades while the blade pitch is constant in each case, and having a moving blade row arranged between the two guide blade rows. The blades of the first guide blade row, in a first partial area of the row, successively have an identical axial offset; the axial offset being selected as a function of the blade number ratio of the two guide blade rows such that it increases the effective flow-off cross-section when the first guide blade row has more guide blades than the second guide blade row and reduces the effective flow-off cross-section when the first guide blade row has less guide blades than the second guide blade row. The blades of the first guide blade row, in a second partial area of the row, successively have an axial offset which is opposite in relation to the blades in the first partial area.

Abstract: A blade row arrangement for turbo-engines has an axial construction with two guide blade rows fixedly positioned relative to one another and having a different number of blades while the blade pitch is constant in each case, and having a moving blade row arranged between the two guide blade rows. The blades of the first guide blade row, in a first partial area of the row, successively have an identical axial offset; the axial offset being selected as a function of the blade number ratio of the two guide blade rows such that it increases the effective flow-off cross-section when the first guide blade row has more guide blades than the second guide blade row and reduces the effective flow-off cross-section when the first guide blade row has less guide blades than the second guide blade row. The blades of the first guide blade row, in a second partial area of the row, successively have an axial offset which is opposite in relation to the blades in the first partial area.

Abstract: The invention relates to a radial-flow wheel for a turbo-engine comprising a hub and blades distributed on the hub-side outer circumference, the meridian section contour of the outer surface of the hub being a catenarian curve. This radial-flow wheel has the advantage of low frictional losses.