Abstract: A brush seal for a turbo-machine for sealing a gap between a rotating and a stationary component is disclosed. Elastically flexible bristles are arranged in a plurality of rows that are adjacent to each other. A film or a disk is arranged between at least two rows of bristles, the film or the disk extending in the longitudinal direction of said bristles.

Abstract: A sealing ring for turbo engines is provided. The sealing ring includes individual sealing segments, between which springs are mounted. Locking elements are provided on the parting joint of the turbo engine to retain the sealing segments. In order to ensure that the sealing elements can be securely closed on the parting joint, the sealing segments are positively interconnected on the parting joint.

Abstract: The invention relates to a multistage brush seal of a steam turbine that comprises several brushes which in turn comprise several bristles. A plurality of brushes are arranged next to each other and are configured different from each other with regard to the length of the bristles, or to the bristle thicknesses, or to the bristle rigidities, or to the lay angle of the bristles, or to the height of a first guard ring in front of or behind the brush seal in the flow direction, which delimits this brush seal, or to a gap between the bristles and an opposing surface.

Abstract: The invention relates to a multistage brush seal of a steam turbine, the brush seal comprising several brushes which in turn comprise several bristles. Conventional multistage brush seals have a conservative configuration because a precise prediction regarding the pressure difference of a single stage is not possible. The aim of the invention is therefore to provide a brush seal that allows a more precise prediction in respect of the pressure difference in a single stage or brush and thus provides a more precise dimensioning of the brush seal while achieve possible savings. The invention proposes that the adjacently arranged brushes have a varying configuration in respect of different parameters.

Abstract: A sealing ring for turbo engines is provided. The sealing ring includes individual sealing segments, between which springs are mounted. Locking elements are provided on the parting joint of the turbo engine to retain the sealing segments. In order to ensure that the sealing elements can be securely closed on the parting joint, the sealing segments are positively interconnected on the parting joint.

Abstract: A brush seal for a turbo-machine for sealing a gap between a rotating and a stationary component is disclosed. Elastically flexible bristles are arranged in a plurality of rows that are adjacent to each other. A film or a disk is arranged between at least two rows of bristles, the film or the disk extending in the longitudinal direction of said bristles.

Abstract: There is described a blade for a turbomachine, such as a steam turbine. The blade has a blade tip, which is curved in relation to the blade airfoil profile. The curvature has the shape of a winglet, which is known from aircraft construction.