Abstract: The invention relates to a method for welding rotors for power generation having a plurality of rotor discs arranged along a rotor axis. The method includes providing forged and NDT tested rotor discs and machining the discs for weld seam preparation. The weld seam preparation has an inner narrow TIG welding gap and an adjoining outer SAW welding gap. The method further includes stapling the discs on top of each other; and checking the run-out of the stapled discs relative to each other and as a whole and, if necessary, adjusting the staple. In addition the method includes melting the root of the weld without weld filler using TIG welding; increasing the weld height by narrow gap TIG welding with parent metal weld filler to allow tilting of the rotor in horizontal position; tilting the rotor in horizontal position; finalizing the welding by filling the outer SAW welding gap using SAW welding; and checking the welds of the rotor by NDT using ultrasonic testing.

Abstract: A gas turbine engine includes a compressor with rotor blades having roots connected into seats of a compressor drum. The rotor blade roots and/or the compressor drum have longitudinal passages for a cooling fluid, connecting higher pressure areas to lower pressure areas of the gas turbine engine.

Abstract: The invention relates to a method for welding rotors for power generation having a plurality of rotor discs arranged along a rotor axis. The method includes providing forged and NDT tested rotor discs and machining the discs for weld seam preparation. The weld seam preparation has an inner narrow TIG welding gap and an adjoining outer SAW welding gap. The method further includes stapling the discs on top of each other; and checking the run-out of the stapled discs relative to each other and as a whole and, if necessary, adjusting the staple. In addition the method includes melting the root of the weld without weld filler using TIG welding; increasing the weld height by narrow gap TIG welding with parent metal weld filler to allow tilting of the rotor in horizontal position; tilting the rotor in horizontal position; finalizing the welding by filling the outer SAW welding gap using SAW welding; and checking the welds of the rotor by NDT using ultrasonic testing.

Abstract: A rotor (1) of a gas turbine compressor comprises a multiplicity of welded-together rotor disks (3a, 3b, 4, 5), of which two or more rotor disks (3a, 3b), in a radially outer region (9?), are welded together, and, in a radially inner central region (9), are abutment-joined together. Via the abutment-joining of two rotor disks (3a, 3b), a heat flow (8) radially outward from the center of the rotor (1) is achieved so that the material temperature of the rotor (1) can be kept below a predetermined level during operation. As a result, the service life of the rotor (1) can be increased. In one embodiment, one rotor disk (3a), on its surface, additionally has a recess (7) which can be cooled from outside. The rotor disks (3a, 3b) according to the invention, which are welded and abutment-joined together, can especially be used at the last point in the flow direction of the compressor.

Abstract: A rotor (1) of a gas turbine compressor comprises a multiplicity of welded-together rotor disks (3a, 3b, 4, 5), of which two or more rotor disks (3a, 3b), in a radially outer region (9?), are welded together, and, in a radially inner central region (9), are abutment-joined together. Via the abutment-joining of two rotor disks (3a, 3b), a heat flow (8) radially outward from the center of the rotor (1) is achieved so that the material temperature of the rotor (1) can be kept below a predetermined level during operation. As a result, the service life of the rotor (1) can be increased. In one embodiment, one rotor disk (3a), on its surface, additionally has a recess (7) which can be cooled from outside. The rotor disks (3a, 3b) according to the invention, which are welded and abutment-joined together, can especially be used at the last point in the flow direction of the compressor.

Abstract: A gas turbine engine includes a compressor with rotor blades having roots connected into seats of a compressor drum. The rotor blade roots and/or the compressor drum have longitudinal passages for a cooling fluid, connecting higher pressure areas to lower pressure areas of the gas turbine engine.

Abstract: A rotating machine (10), in particular a compressor or turbine, has a rotor shaft (11) which is rotatable about an axis (20) and is provided with at least one slot (14). The mechanical stresses in the region of the slot are reduced in that the at least one slot (14) has a slot bottom (17) with an elliptic cross-sectional contour (24).

Abstract: A rotor shaft, particularly for a gas turbine, includes a cooling air supply disposed inside the rotor shaft and a plurality of cooling air ducts connected to the cooling air supply and extending essentially radially outward toward an outside of the shaft, wherein each of the cooling air ducts has an elliptic cross section.

Abstract: A rotor shaft, particularly for a gas turbine, includes a cooling air supply disposed inside the rotor shaft and a plurality of cooling air ducts connected to the cooling air supply and extending essentially radially outward toward an outside of the shaft, wherein each of the cooling air ducts has an elliptic cross section.

Abstract: A rotating machine (10), in particular a compressor or turbine, has a rotor shaft (11) which is rotatable about an axis (20) and is provided with at least one slot (14). The mechanical stresses in the region of the slot are reduced in that the at least one slot (14) has a slot bottom (17) with an elliptic cross-sectional contour (24).