Abstract: A device for sealing between the guide vanes (1) and the rotor (17) of turbomachines, especially gas turbines has inner rings (3) suspended on the vane footing (14) of the guide vanes (1) in a thermally elastic manner with soldered honeycomb seal (4) and labyrinth tips (5) arranged on the rotor (17). First flow channels, which are connected to the cavities (21) of the cooled guide vanes (1), through which said cavities cooling air flows, are led through the vane footings (14). The first flow channels are connected to at least one of second flow channels led through the inner ring (3) to the vicinity of the honeycomb seal (4). The second flow channels open into at least one of third flow channels that are open at the rear edge of the inner ring (3) or are led to an annular groove (10) open toward the honeycomb seal (4) on the underside of the inner ring (3).

Abstract: A fuel gas processed and preheated in a processing unit (6) is burned in a gas turbine unit or in a boiler plant. A continuously operating detector (9) for determining the condensate content in the processed fuel gas is arranged in a line (5) connecting the processing unit (6) with the burner immediately before the burner. This detector (9) is connected to an alarm device (10) and to a shut off device (11).

Abstract: A rhomboidal blade includes a blade footing (2) of rhomboidal cross section and a blade body (1) for axial turbo engines is worked out from a solid blank (3) by machining. The blank (3) is cut off as a bar from a hot-rolled, bar-shaped input stock, whose cross section has the shape of a rhomboid which is adapted to the shape of the cross section of the rhomboidal blade footing (2). The blank is larger on all size than the maximum cross section of the blade by only the minimum oversize (5) for machining.

Abstract: A symmetrical component of a turbine unit, whose wall is exposed to a hot medium on one side and is subject to nonuniform thermal stress over the circumference, is cooled by a flow of cooling air being guided along the other side of the component. A ring (5) is provided with slots (7) or other openings for the passage of the cooling air. The ring (5) protrudes into the flow of the cooling air. The overall cross section of the slots (7) that are arranged in the sections of the ring (5) that are adjacent to the areas of the component that are subject to the higher stress is larger than the overall cross section of the slots (7) that are arranged in the sections of the ring (5) that are adjacent to the areas of the component that are subject to a lower stress.

Abstract: To prevent surge of a turbocompressor (K), a anti-surge valve (27) provided at the compressor outlet is controlled by a controller (R). The input signal for the controller (R) is generated as a function of the instantaneous flow and the end pressure of the compressor (K) such that the controller responds more slowly to working point shifts in the direction of the surge limit line and more rapidly to working point shifts in the opposite direction. This is achieved by arranging an asymmetric time element or a gradient sensor in the circuit generating the input signal for the controller (R).

Abstract: To protect a turbocompressor (3) with a downstream process from operation in the unstable working range, a machine controller is used, which optionally contains—besides a surge limit controller (15)—an intake pressure controller (11), an end pressure controller (20) and a bypass controller (9). A control matrix is determined from the position of a control unit (fuel gas control valve 6) determining the flow to the process, optionally taking into account additional influencing variables such as the compressor intake pressure and the compressor discharge pressure.

Abstract: A coupling apparatus (4) for connecting two rotatable shafts (2a, 3a) of a turbocompressor (1) includes a first and a second coupling part (4a, 4b) which form part of the shaft (2a, 3a) or are designed for firm connection to one end section of the shafts (2a, 3a) each. A third coupling part (4c) is designed in disc-shape and is arranged between the first and the second coupling part (4a, 4b). The first, second and third coupling part (4a, 4b, 4c) are firmly connectable to one another. The third coupling part (4c) has a section (41) which projects beyond the first or second coupling part (4a, 4b) in the radial direction and is designed as a bearing disc of an axial bearing (7).

Abstract: A turbocompressor (1) has an electric motor (2), a multistage radial turbocompressor (3) and a common shaft (13). A section of the shaft (13) is formed as the armature (2b) of the electric motor (2) and a further section of the shaft (13) is formed as the rotor (3e) of the radial turbocompressor (3), with the rotor (3e) including a compressor shaft and compressor wheels (3b) connected thereto. A plurality of electromagnetic radial bearings (5) are arranged spaced apart in the direction of the shaft (13) for the journalling of the shaft (13), and a single electromagnetic radial bearing (5) is arranged between the armature (2b) of the electric motor and the compressor wheel (36). The electric motor (2), the radial turbocompressor (3), the shaft (13) and the radial bearings (5) are inside a common housing sealed gas-tight to the outside. The housing (6) consists of a plurality of part housings (6e, 6f, 6g) which are connected together.

Abstract: The blades (3) of a turbine of axial design are inserted into an undercut blade groove (2) of the turbine rotor (1) in a positive-locking manner and are secured by a blade lock. The blade lock comprises a mounting space (7), which is in connection with the blade groove (2) and into which a filler piece (8), which is in positive-locking relationship with the blade foot (6) of the blades (3), and a wedge (9) are inserted. The cross section of the mounting space (7) receiving the filler piece (8) is widened conically beginning from the blade groove (2). The cross section of the filler piece (8) is adapted to the cross section of the mounting space (7).

Abstract: A compressor, especially for compressing the fuel gas for a gas turbine, is controlled by a throttling member (9) arranged on the intake side of the compressor as a function of the gas consumption of the user (7) such that the flow cross section is reduced during a reduction in gas consumption. The intake-side throttling member may be additionally controlled as a function of the pressure on the intake side of the compressor. Additional control circuits, especially an end pressure controller (19), which maintains the end pressure by acting on the guide vanes or on the speed of rotation of the compressor, and/or a pump surge limiter (33), which acts on a blow-by valve (29) connecting the outlet side to the intake side of the compressor (3), may be additionally present.

Abstract: A pipeline duct through a discharge opening (17) of a vane support housing (1) and an opening (6) in an outer wall (3) of a compressor housing of a gas turbine. The upper part of the pipe (2) is firmly clamped with a flange (14) and seals (7) between the bleeder connection (15) and the outer wall (3) by means of fastening elements (16). The lower part of the pipe (2) is sealed by a piston ring (8). The piston ring (8) is guided by two fastening rings (9, 10), which are mounted in the vane support housing (1) by fastening elements (16). The fastening rings (9, 10) make possible a free movement of the pipe (2) and the housing (3) in relation to the vane support housing (1) in the horizontal direction due to their free spaces (11, 12, 13).

Abstract: The removal of cooling air from the diffuser part of a radial stage of a compressor of a gas turbine is provided. The end stage of the compressor has a radial rotor disk (2) with a bladed diffuser (3). With the corresponding fastening elements (7) for the parts (20.1, 20.2) on the diffuser housing side, the diffuser blading (3) is used at the same time to connect the vane support (1) to the rear bearing housing (21). Compressed cooling air can be removed through either/both round holes (6.1) or/and slots (6.2), which are milled on the suction side of the diffuser vane (3). Through the removal openings (6.1, 6.2), the cooling air enters the blind holes (19) of the diffuser vane (3) and then further, through holes (19.1) in the diffuser housing outside (20.2), the cooling air discharge (10) arranged in the compressor housing.