Abstract: A device such as a drum for positioning at least one guide blade row from a plurality of guide blade groups in a turbomachine, the device on the outer circumferential side including at least one flange for attachment to a housing section of the turbomachine and on the inner circumferential side including a plurality of uniformly distributed receptacles for accommodating holding elements of the guide blade groups and a plurality of recesses, the device having a depth-reduced inner circumferential section, relative to the accommodating grooves, between at least two adjoining receptacles, which extends in each case from the one receptacle to the other receptacle; a blade-device combination; a method for assembling such a blade-device combination; and a turbomachine.

Abstract: A gas turbine having a guide vane assembly (2) and a securing ring (1) for axially locking the guide vane assembly in position that has a radially outer rim (1A) which is configured in a housing-side groove (3.1), a radially inner rim (1B) which is configured outside of the groove, and a slot (10) which extends from the radially outer rim to the radially inner rim, and a first flank having a radially inner rim section (12) and an undercut portion (11), the radially inner rim section forming an angle (?) of at least 50° with the radially inner rim.

Abstract: A sealing element is described for positioning in a turbomachine, for the self-securing of a sealing element in a mounting position, its support structure having a safeguard which has a springy catch section, whose mounting surface is inclined at a smaller angle in the mounting direction than a securing surface in the opposite direction, a sealing unit, and a turbomachine.

Abstract: A component support of the turbomachine, in particular an aircraft engine, is described, which includes at least two essentially annular components on the stator side, which are in axial contact with each other and are preferably oriented coaxially to the machine axis, the first component having a plurality of radial, groove-like recesses, which are laterally overlapped by the second component with its projection-like bearing sections, and an uncontoured support ring surface section being provided between the adjacent bearing sections, a turbomachine also being described.

Abstract: A device for bounding a flow channel of a turbomachine, comprising a wall that, viewed in the circumferential direction of the turbomachine, has a multiplicity of wall segments, and including a multiplicity of outer segments that extend radially around the outside of the wall segments; each wall segment having a uniformly curved first cross-sectional contour; each outer segment including at least one second cross sectional contour that deviates from the uniformly curved first cross-sectional contour; the second cross-sectional contour having a multiplicity of depressions that are inwardly directed in the radial direction of the gas turbine; at least a portion thereof being attached to the radially outer surface of a corresponding wall segment.

Abstract: A sealing element is described for positioning in a turbomachine, for the self-securing of a sealing element in a mounting position, its support structure having a safeguard which has a springy catch section, whose mounting surface is inclined at a smaller angle in the mounting direction than a securing surface in the opposite direction, a sealing unit, and a turbomachine.

Abstract: A gas turbine having a guide vane assembly (2) and a securing ring (1) for axially locking the guide vane assembly in position that has a radially outer rim (1A) which is configured in a housing-side groove (3.1), a radially inner rim (1B) which is configured outside of the groove, and a slot (10) which extends from the radially outer rim to the radially inner rim, and a first flank having a radially inner rim section (12) and an undercut portion (11), the radially inner rim section forming an angle (?) of at least 50° with the radially inner rim.

Abstract: A component support of the turbomachine, in particular an aircraft engine, is described, which includes at least two essentially annular components on the stator side, which are in axial contact with each other and are preferably oriented coaxially to the machine axis, the first component having a plurality of radial, groove-like recesses, which are laterally overlapped by the second component with its projection-like bearing sections, and an uncontoured support ring surface section being provided between the adjacent bearing sections, a turbomachine also being described.

Abstract: A device such as a drum for positioning at least one guide blade row from a plurality of guide blade groups in a turbomachine, the device on the outer circumferential side including at least one flange for attachment to a housing section of the turbomachine and on the inner circumferential side including a plurality of uniformly distributed receptacles for accommodating holding elements of the guide blade groups and a plurality of recesses, the device having a depth-reduced inner circumferential section, relative to the accommodating grooves, between at least two adjoining receptacles, which extends in each case from the one receptacle to the other receptacle; a blade-device combination; a method for assembling such a blade-device combination; and a turbomachine.