Abstract: A housing structure for a turbomachine having a stationary blade ring annularly surrounding a flow channel, and having a seal carrier ring which also annularly surrounds the flow channel, the stationary blade ring and the seal carrier ring being connected to each other, and either the stationary blade ring or the seal carrier ring having a one-sidedly open receptacle in the radial direction in relation to the flow channel and a radially projecting engagement area which corresponds to the connected seal carrier ring or stationary blade ring and which is held in a form-fitting manner in the axial direction and in the radial direction in the direction of the closed side of the receptacle but is freely movable with respect to the connected receptacle and the seal carrier ring or stationary blade ring having this receptacle in the radially opposite direction in the direction of the receptacle opening.

Abstract: A component combination for a shell of a flow channel (10) of a turbomachine, in particular for a housing of a gas turbine or an aircraft engine, including at least two components, a first component (1) forming a closed ring. The closed ring is axially and/or radially held in a form-fitting manner against at least one second component (2) in relation to the flow channel and is able to be removed from or placed into this position only by elastically deforming the ring without changing the second component; the present invention also includes a method for manufacturing a component combination of this type and a corresponding turbomachine having a component combination of this type.

Abstract: A housing structure for a turbomachine, the housing structure annularly surrounding, at least partially, a flow channel (14) in which guide vanes and rotor vanes are arranged. The housing structure has an inner wall (2) that delimits the flow channel and an outer wall (1) that is closed off vis-à-vis the environment. A heat-protection plate (3) is arranged on the radial outside of the inner wall, and insulation (4) is arranged between the heat-protection plate and the outer wall. At least one cooling-air channel (6) is formed between the insulation and the radial inside of the outer wall, the cooling-air channel (6) having at least one air-guiding element (5) resting against the insulation.

Abstract: A housing structure for a turbo-engine, especially for a gas turbine or an aircraft engine, includes an outer housing wall and an inner housing wall, the inner and outer housing walls annularly enclosing a flow channel for the turbo-engine and being spaced apart radially from the flow channel. At least one heat shield is arranged between the inner and outer housing walls, and a bar or a fixture projects at least somewhat radially from the inner housing wall. The bar or the fixture has on at least one side a broadening element that includes a sealing face against which the heat shield is positioned in a sealing manner.

Abstract: A casing structure for a fluid flow machine, in particular for a gas turbine or an aircraft engine, including an outer casing wall and an inner casing wall, which annularly surround a flow channel of the fluid flow machine and are spaced apart in a radial direction with respect to the flow channel. At least one cavity is formed between the inner and outer casing walls. The cavity is axially divided into at least two regions which are separated from each other by an axial seal in such a way that different pressure conditions are created according to the axial position of these regions, which different pressure conditions correspond to the pressure conditions in the flow channel. A corresponding fluid flow machine such as, for example, an aircraft engine.

Abstract: A turbomachine having a flow channel and a housing radially surrounding the flow channel, a plurality of stationary and moving blades being situated in the flow channel, stationary blades being situated adjacent to the moving blades in the axial direction, and the stationary blades having at least one stationary blade hook which engages with at least one housing hook for the purpose of connecting the stationary blades to the housing. A sealing and lining element is situated in the radial direction between the moving blades adjacent to the stationary blades and the housing, and has a sealing structure interacting with blade tips of the moving blades. A heat protection element is provided in the area between the sealing and lining element and the housing, and a sealing element being situated on the heat protection element for the purpose of sealing contact with the housing hook.

Abstract: A turbomachine having a flow channel (6) and a housing (1, 2) which radially surrounds the flow channel, at least one sealing or lining element (11) being situated between the flow channel and the housing, at least one clamping ring (14) being provided, which is situated circumferentially around the flow channel and which is situated in such a way that it abuts at least one contact surface (22) of the at least one sealing or lining element (11).

Abstract: A gas turbine jet engine having a main flow channel (20) and a housing structure (22) which radially surrounds this main flow channel, in which a housing gas flow flows in the same direction as the main flow in the main flow channel, the housing structure having a flow conducting assembly (25), with the aid of which the flow of the housing gas flow to and/or along the main flow channel may be adjusted.

Abstract: A turbomachine is disclosed. The turbomachine includes a rotor, a plurality of blades arranged side by side on the rotor in a circumferential direction, and a plurality of sealing apparatuses each disposed on a respective blade shaft of the plurality of blades. Each of the plurality of sealing apparatuses includes first and second bottom plates protruding in a respective axial direction on the respective blade shaft and first and second bulkheads which extend in a radial direction along the respective blade shaft and form a double-walled seal in the axial direction. A respective rounded or parabolic transitional cross-section from the bottom plates to the bulkheads is provided and at least one of the bulkheads is offset with respect to a blade root edge of the respective blade shaft in a direction toward a radial longitudinal axis of the respective blade shaft.

Abstract: A turbomachine has a stator and a rotor, wherein the rotor has blades (21) and the stator has a housing (20) and stationary guide vanes (17), wherein the guide vanes (17) form guide vane rings (11, 12) that adjoin the housing (20) with radially outwardly positioned ends (18) and adjoin the rotor with radially inwardly positioned ends. The guide vane rings are spoke-centered with the aid of bearing journals or guide pins (24) allocated to the housing (20) and penetrating through the housing (20). The guide pins (24) extend at a slant relative to the radial direction and the axial direction of the turbomachine, wherein the ends (26) of the guide pins (24) reaching into the housing engage in forked elements (27) allocated to the radially outer ends (18) of the guide vane rings (11, 12).

Abstract: The invention relates to a turbomachine, more particularly a gas turbine. The turbomachine has a stator and a rotor, wherein the rotor has blades (21) and the stator has a housing (20) and stationary guide vanes (17), wherein the guide vanes (17) form guide vane rings (11, 12) that adjoin the housing (20) with radially outwardly positioned ends (18) and adjoin the rotor with radially inwardly positioned ends. The guide vane rings are spoke-centered with the aid of bearing journals or guide pins (24) allocated to the housing (20) and penetrating through the housing (20). According to the invention, the guide pins (24) extend approximately perpendicularly to the housing (20), wherein the ends (26) of the guide pins (24) reaching into the housing engage in forked elements (27) allocated to the radially outer ends (18) of the guide vane rings (11, 12).

Abstract: An arrangement for sealing structural members particularly in the case of turbo-engines is provided. A structural member is to be divided along a first plane into segments, which can be moved relative to one another, and is to be movable in a second plane which is angularly offset with respect to the first plane. Projections of the segments sealingly engage in a groove of an additional structural member. Expansion gaps, which are arranged between abutting edges of the segments, are to be sealed off longitudinally and transversely with respect to the course of the gap by sealing plates. In this case, each expansion gap is to be sealed off between a sealing plate arranged transversely to the course of the gap and an opposing surface of the groove acting as a sealing surface by means of a V-shaped insert.