Abstract: The invention proposes a securing device (26) for securing a turbocharger (12) comprising a turbocharger casing (14) to a base (28). The securing device (26) has a first foot (30) which can be fixed in the base (28) and a second foot (32) which can be fixed in the base (28), it being possible for the two feet (30, 32) to be connected to the turbocharger casing (14) at an axial distance from one another. The second foot (32) has a casing connection region (34), which can be connected to the turbocharger casing (14), and a base connection region (36), which can be connected to the base (28). The casing connection region (34) is designed in the form of a partial circle arc or circle arc. An axial strut arrangement (38) connects the casing connection region (34) and the base connection region (36) and includes an angle ? in the range from 0° to 60° with the base (28).

Abstract: The shaft (1) is connected to the shaft attachment (2) by means of a thread. A bore (20) with an internal thread is incorporated in the shaft attachment and the shaft has a corresponding stem (10) which can be introduced into the threaded bore and has an external thread. An axial stop (11, 21) is arranged in each case on the shaft and on the shaft attachment. The internal and external threads have torque-transmitting flanks which are flat toward the axis and which can be connected to one another frictionally by means of radial pressure by mutual rotation of shaft and shaft attachment with interaction between the axial stops.

Abstract: A device for fastening a turbocharger to a base, with a fastening foot (12) which is integrally formed in one piece on a gas outlet casing (10) of the turbocharger and which has long holes (16) spaced from one another and preferably arranged in a star-shaped manner in relation to one another. In order to fasten the turbocharger, sliding shoes (26) are capable of being inserted into the long holes (16) and have continuous orifices, through which can be led fastening elements (30, 30′) capable of being fixed in the base.

Abstract: The invention relates to a journal bearing for the shafts of high-speed rotors, and provides simple, and therefore low-cost, centering of squeeze film dampers for high-speed rotors, with improved long-term behavior, less installation space requirements and adequate concentricity accuracy. A centering element divides the annular gap into two partial annular gaps, with the bearing housing being configured in at least two parts and with a first bearing housing part bounding the first partial annular gap radially toward the outside and a second bearing housing part bounding the second partial annular gap radially toward the outside.

Abstract: The object of the invention is to provide a safe and reproducible compressor impeller fastening for high speed turboengines, which, moreover, possesses more accurate concentricity.This is achieved, according to the invention, in that both the hub cone (9) and the shaft cone (11) each have a mean diameter (23, 24) and these mean diameters (23, 24) are arranged at an axial distance (25) from the mass center of gravity (14) of the compressor impeller (4), said distance corresponding at least to half the mean diameters (23, 24). On the shaft side of the hub cone (9), the through bore (8) of the hub (6) is designed at least partially as a cylindrical bore (16).

Abstract: The object of the invention is to provide simple and cost-effective, internal rupture protection for the axial turbine of an exhaust-gas turbocharger. At the same time, the functional reliability of the exhaust-gas turbocharger is to be increased. According to the invention, this is achieved in that the rupture-protection ring (8) is designed as an integral, essentially radially extending, part of the gas-inlet-side wall (5) of the gas-outlet casing (2) and is connected to the gas-inlet casing (1) either directly or via an axial extension piece (6) arranged upstream.

Abstract: An exhaust gas turbine for an exhaust gas turbocharger has a nozzle ring having an inner ring and an outer ring supporting a plurality of guide vanes. The nozzle ring is diagonally supported between a covering ring and the inlet casing, with the outer ring bearing against the covering ring and the inner ring bearing against the inlet casing. The outer ring provides an axial expansion gap with gas inlet casing and a radial expansion gap with the gas outlet casing. The nozzle ring is free to expand into the axial and radial gaps as a result of thermal expansion, without causing stress to the adjacent components.

Abstract: The object of the invention is to provide an improved bearing support arrangement for rapidly rotating rotors, with which arrangement the service life of the bearing device is increased and both its fabrication costs and the expenditure on assembly are reduced. This is achieved according to the invention in that the bearing support arrangement (10) is of one-piece design. It comprises an outer flange (11) connected to the housing (2), a gimbal ring (12) and an inner bearing bush (13) which receives the bearing or the bearings (3). In each case a circumferential slot (14, 15) is formed both between the gimbal ring (12) and the outer flange (11) and between the gimbal ring (12) and the bearing bush (13). The gimbal ring (12) is respectively connected to the bearing bush (13) and to the outer flange (11) via two inner and two outer webs (16, 17) which interrupt the respective circumferential slot (14, 15).

Abstract: A circular-cylindrical filter muffler includes damping elements (3) arranged with their damping surfaces (11, 12) parallel to the central axis (13) of the filter muffler housing (2), which is cast as a monobloc. The damping elements are arranged in grooves (8) of the housing walls. The damping elements (3) include a damping plate (9) which encases an absorption element (10). In the assembled state the damping plates (9) form, with the coarse filter segments (15) arranged on them on the circumference of the filter muffler, a coarse filter ring which is surrounded by an annular filter (4). The advantages of the invention are, in addition to the simplified production and assembly of the components, the reduction of different components and the lower weight along with improved muffling.

Abstract: A contact seal for turboengines is disclosed which is suitable for high circumferential speeds and high temperatures. The contact seal is of at least a two-part design and includes a thin carrier ring and a sealing ring. The sealing ring is constructed from a wear, oil, and heat resistant material, while the carrier ring includes an elastic material which is completely reversible even under high loads, and preferably is constructed of spring steel. The carrier ring has an inner fastening pan and an outer carrying part. The carrying part is positively connected to the sealing ring. The carrying part is designed to be inclined in the direction of the sealing face.

Abstract: The axial mounting with skewing compensation for a turbomachine has a fastening flange (1) and a bearing housing (2) which is in one piece with the latter and which is subdivided into a middle housing part (9) and an outer housing part (10) by means of at least one pair of slots (4,7) in two respective planes. The slots (4,7) are widened in a lobe-like manner at their ends, and these ends respectively limit at least one pair of webs (5,8) located diametrically opposite one another in the said planes. These webs (5,8) perform the function of rigid joints for damping angular deflections of the shaft which are caused by operating loads. The webs (5,8) of the two planes are offset relative to one another by 90.degree., generally by the amount of half their circumferential division.

Abstract: The present invention relates to a damping element for independent blades of a turbomachine in which the blades fastened in the rotor are connected together, preferably in the radially outer region, the connection between two blades consists of an elastically deformable platelet curved towards the center of the rotor, which platelet engages in retention features on the suction side of one blade and on the pressure side of a second, neighboring blade. The retention features on the blades can be either recesses or protruding lugs, in or on which the platelets are supported.