Abstract: In a process for producing a turbine blade or vane, providing a casting mold for casting the turbine blade or vane, the casting mold including a blade or vane platform and a main blade or vane part, and a position of the main blade or vane part relative to the blade or vane platform determining a first angle of incidence; providing additional machining stock to the blade or vane platform at predetermined locations; machining the casting using a process which is specified for the first angle of incidence; rotating the casting around a longitudinal axis for an angle which is equal to the difference between said first angle of incidence and a second angle of incidence, and subjecting said rotated casting to said machining process to remove at least partially the additional machining stock.

Abstract: A seal arrangement for reducing the seal gaps within a rotary flow machine, preferably an axial turbomachine, has rotor blades and guide vanes, which are respectively arranged in at least one rotor blade row and guide vane row and have respective blade/vane roots (2,3) which protrude into fastening contours within the rotor blade and guide vane rows. A sealing element (4) of plastically deformable material is provided between at least two adjacent blade/vane roots (2,3) along a rotor blade row or guide vane row or between a blade/vane root (2,3) of a rotor blade or guide vane and a rotary flow machine component directly adjoining the blade/vane root.

Abstract: A seal arrangement for reducing the seal gaps within a rotary flow machine, preferably an axial turbomachine, having rotor blades and guide vanes, which are respectively arranged in at least one rotor blade row and guide vane row and have respective blade/vane roots (2,3) which protrude into fastening contours within the rotor blade and guide vane rows, is described. The invention is characterized in that a sealing element (4) in plastically deformable material is provided between at least two adjacent blade/vane roots (2,3) along a rotor blade row or guide vane row or between a blade/vane root (2,3) of a rotor blade or guide vane and a rotary flow machine component directly adjoining the blade/vane root.

Abstract: In a process for producing a turbine blade or vane, a casting (10′) which is in the basic shape of the turbine blade or vane is produced in a casting mold, and the casting (10′) is then subjected to material-removing machining in order to complete the turbine blade or vane.

Abstract: A device for fastening and fixing components to a cylindrical wall. The cylindrical wall may be both the convex-cylindrical outer contour of a cylinder and the concave-cylindrical inner contour of a hollow cylinder, in which the component is fixed in the radial, axial and circumferential directions. The fastening and fixing is effected by shaped elements which are attached to the component and by a counterpart to each shaped element on the wall. In each case a shaped element and a counterpart interlock, such that the component has at least three shaped elements, of which at least one shaped element has a defined accuracy of fit with its associated counterpart in the radial direction and has clearance in the axial and circumferential directions. At least one shaped element has a defined accuracy of fit with its associated counterpart in the axial direction and has clearance in the radial and circumferential directions.

Abstract: In a hollow-cast component, a core opening (13) created during manufacturing is closed with a closure piece (14). This closure piece is located inside a recess (15) in the component, whereby the recess is arranged so that it is imbedded completely in the cast material, and completely covers the core opening. Because of this installation, the closure piece is fixed in a form-fitting manner in the direction of two spatial axes, so that the closure piece only needs to be secured with an additional joint in the installation direction. It is preferred that the installation direction is normal in relation to the direction of maximal stress of the closure piece, so that a joint is subject to a relatively small stress and therefore can be produced with little expenditure and a high degree of operational safety.

Abstract: In a heat shield (10), in particular for the stator of gas turbines, which heat shield (10) is composed of a plurality of individual segments (10a, b; 20a, b), whose end surfaces (15a, b) respectively abut one another so as to form a gap (12), and which have cooling holes (13a, b) for cooling purposes in the region of the end surfaces (15a, b), through which cooling holes (13a, b) a cooling fluid is blown out into the gap (12), cooling is ensured, even when the gap is closed, by a chamber (11), which is widened relative to the gap (12) and into which the cooling holes (13a, b) open, being arranged in the region of the gap (12).

Abstract: A fastening device for a heat-protection shield of a gas turbine is provided with a center mounting element which has a defined installation clearance with a mounting slot in the radial direction. In the normal operating state, this mounting element has no function, such that thermal differential expansions in the radial direction between the heat-protection shield and its counterpart are possible without impairment within the limits of this defined clearance. The mounting element does not start to bear against the counterpart until the radial differential expansion exceeds the size s. The deformation of the heat-protection shield toward a component moving in a relative manner is thus limited and excessive grazing of the components against one another is avoided.

Abstract: In a heat shield (10), in particular for the stator of gas turbines, which heat shield (10) is composed of a plurality of individual segments (10a, b; 20a, b), whose end surfaces (15a, b) respectively abut one another so as to form a gap (12), and which have cooling holes (13a, b) for cooling purposes in the region of the end surfaces (15a, b), through which cooling holes (13a, b) a cooling fluid is blown out into the gap (12), cooling is ensured, even when the gap is closed, by a chamber (11), which is widened relative to the gap (12) and into which the cooling holes (13a, b) open, being arranged in the region of the gap (12).

Abstract: In a hollow-cast component, a core opening (13) created during manufacturing is closed with a closure piece (14). This closure piece is located inside a recess (15) in the component, whereby the recess is arranged so that it is imbedded completely in the cast material, and completely covers the core opening. Because of this installation, the closure piece is fixed in a form-fitting manner in the direction of two spatial axes, so that the closure piece only needs to be secured with an additional joint in the installation direction. It is preferred that the installation direction is normal in relation to the direction of maximal stress of the closure piece, so that a joint is subject to a relatively small stress and therefore can be produced with little expenditure and a high degree of operational safety.

Abstract: In a gas turbine group which consists essentially of a compressor (2), a first combustion chamber (3), a first turbine (4), a second combustion chamber (5) and a second turbine (6), the first combustion chamber (3) is configured as an annular combustion chamber. This annular combustion chamber (3) is operated by a number of premixing burners (11) which are distributed at the periphery. The first turbine (4) is designed in such a way that its exhaust gases have a temperature level which is above the self-ignition temperature of the fuel (13) used in the second combustion chamber (5). This second combustion chamber (5) consists of a burnerless, annular combustion space in which a number of vortex-generating elements (14) are integrated. The turbomachines, namely compressor (2), first turbine (4) and second turbine (6) are disposed on a rotor shaft (1), this rotor shaft (1) being supported in two bearings (9, 15).

Abstract: In a process for operating a fluid flow engine, a conditioning medium is conducted through the rotor, which consists of several shaft parts (1, 2) welded together; this medium is capable of evening out the temperature difference established between the stator (3) and the rotor in the transient operating ranges, depending on whether heating or cooling of the rotor is suited to the characteristic curve of the stator temperature course.

Abstract: In a gas turbine group which consists essentially of a compressor (2), a first combustion chamber (3), a first turbine (4), a second combustion chamber (5) and a second turbine (6), the first combustion chamber (3) is configured as an annular combustion chamber. This annular combustion chamber (3) is operated by a number of premixing burners (11) which are distributed at the periphery. The first turbine (4) is designed in such a way that its exhaust gases have a temperature level which is above the self-ignition temperature of the fuel (13) used in the second combustion chamber (5). This second combustion chamber (5) consists of a burnerless, annular combustion space in which a number of vortex-generating elements (14) are integrated. The turbomachines, namely compressor (2), first turbine (4) and second turbine (6) are disposed on a rotor shaft (1), this rotor shaft (1) being supported in two bearings (9, 15).