Abstract: A rotary bearing assembly having a preset breaking point, particularly for a rotor of a turbo engine, includes a rotary bearing arranged between a nonrotating bearing carrier housing and a bearing carrier rotating about a rotational axis, the rotary bearing being fixed radially and axially at its outer bearing ring via a first tangential plane and a second tangential plane in the nonrotating bearing carrier housing. At predetermined stress, a breaking arrangement for the formation of a preset breaking point is provided, which is arranged in the first tangential plane and the second tangential plane, concentric with the rotational axis, between the outer bearing ring and the nonrotating bearing carrier housing.

Abstract: A compressor in a multi-stage axial form of construction, with a rotor which is mounted overhung and includes a plurality of moving-blade rings on blade carriers connected to one another, and with a blade arrangement, in which the moving-blade ring of the first stage forms the blade cascade arranged furthest upstream. At least one of the rotating blade carriers is produced in an MMC form of construction, that is to say as a metal component fiber-reinforced at least in regions, and the rotary bearing absorbing the large part of the radial loads occurring on the rotor has a predetermined breaking point which, when a defined radial load is exceeded, allows a radial shift of the rotor, with the result that the latter brushes against the stator.

Abstract: A compressor in a multi-stage axial form of construction, with a rotor which is mounted overhung and includes a plurality of moving-blade rings on blade carriers connected to one another, and with a blade arrangement, in which the moving-blade ring of the first stage forms the blade cascade arranged furthest upstream. At least one of the rotating blade carriers is produced in an MMC form of construction, that is to say as a metal component fiber-reinforced at least in regions, and the rotary bearing absorbing the large part of the radial loads occurring on the rotor has a predetermined breaking point which, when a defined radial load is exceeded, allows a radial shift of the rotor, with the result that the latter brushes against the stator.

Abstract: A rotary bearing assembly having a preset breaking point, particularly for a rotor of a turbo engine, includes a rotary bearing arranged between a nonrotating bearing carrier housing and a bearing carrier rotating about a rotational axis, the rotary bearing being fixed radially and axially at its outer bearing ring via a first tangential plane and a second tangential plane in the nonrotating bearing carrier housing. At predetermined stress, a breaking arrangement for the formation of a preset breaking point is provided, which is arranged in the first tangential plane and the second tangential plane, concentric with the rotational axis, between the outer bearing ring and the nonrotating bearing carrier housing.

Abstract: A brush seal (3) is provided to seal two differently pressurized spaces (R.sub.1, R.sub.2) on opposite sides of a rotor (1) cooperating with a stator (2), for example in a gas turbine engine, around a circumferential gap between the rotor (1) and the stator (2). The brush seal (3) includes seal bristles (5) having free ends extending annularly concentrically and parallel to a rotation axis of the rotor (1) and fixed ends received in a seal housing (6). A perimeter rim of the rotor (1) has an axis-concentric circumferential groove (7) therein, and the free ends of the seal bristles (5) reach into this circumferential groove (7). During operation of the rotor (1), fluid boundary layers are formed respectively between the seal bristles (5) and the side walls (9A, 9B) of the circumferential groove (7). The boundary layers (G.sub.I, G.sub.

Abstract: A bearing arrangement is provided for rotors of jet engines with a bearing, which is mounted on a rotor carrier via a bearing carrier. In the event of failure, for example if the blade of a compressor rotor breaks, damage to or destruction of the rotor carrier or of the housing should be prevented by the fact that a breaking piece, which breaks under a defined load, is arranged concentrically between the rotor carrier and the bearing carrier. In this way, the transfer of extreme radial loads to the rotor carrier or to the rotor housing enclosing it is largely avoided, provided that the rotating member has not yet come to a standstill. The bearing arrangement is particularly of interest for turbo jet engines for aeroplanes, where for example, in the case of damage to a fan-rotor blade, the effect of a destructive force of a rotor running at high speed on neighboring housing areas can be reduced.

Abstract: A nozzle wall for two-dimensional (2D) hot gas nozzles of rocket or jet engines has a multilayer structure, in which a thermally conductive layer is flexibly connected to a support structure and a sliding layer is arranged between them to permit parallel movement of the thermally conductive layer. Also, a manufacturing method for the nozzle wall allows successive operations to be automatic to allow quality control inspections between these operations.

Abstract: A radial compressor rotor, especially for static imbalance of a dual flow radial compressor impeller, having back-to-back blades in a gas turbine engine, is provided with at least one axial through hole in the rotor hub. The axial hole is filled in by an imbalance compensating insert which covers the ends of the hole between neighboring radial blade contour surfaces in an aerodynamically flush manner. The density and density distribution of the material of the insert is selected relative to the density and mass concentration of the material of the compressor impeller to achieve the desired imbalance compensating effect.