Abstract: A blade of a turbomachine is provided, including at least one cooling channel in the interior of the blade for cooling the blade with the aid of a fluid flowing through the cooling channel, the cooling channel having at least one inlet and at least one outlet, between which the cooling channel extends along its longitudinal axis, and the cooling channel being radially delimited by at least one wall, at least one displacement body being situated in the cooling channel, so that an annular or tubular gap between the displacement body and the wall of the cooling channel results in the area of the displacement body/bodies, which is available for the through-flow of the fluid, or at least two or multiple subchannels being formed in the area of the displacement body/bodies. The invention also relates to a method for manufacturing a corresponding blade.

Abstract: The present invention relates to sealing element for sealing a radial gap relative to a counter element of a turbomachine, wherein the sealing element has a number of adjacent cells in the peripheral direction and/or in the axial direction, which are joined to one another by common walls, wherein an extension of a least one, in particular front-side, cross section of at least one cell in a first axial section of the sealing element in the peripheral direction and/or in the axial direction for sealing against a radial flange of the counter element is smaller than that in a second axial section of the sealing element that adjoins the first axial section upstream and/or in a second axial section that adjoins the first axial section downstream.

Abstract: A platelike projecting component portion of a component used in gas turbines or other similar applications includes a surface upon which hot gas acts and cooling bores through which a cooling medium is capable of flowing. Effective cooling is achieved by providing at least one plenum assigned solely to the component portion. The plenum is arranged so as to be directly adjacent to the surface upon which hot gas acts and through which the cooling medium is capable of flowing to provide convective heat transfer. The cooling bores are designed as blow-out orifices which emanate from the plenum and issue the cooling medium onto the surface upon which hot gas acts, thereby forming a cooling film.

Abstract: In a gas-turbine guide element (30) around which a hot air flow (23) flows and which, at least in a trailing edge region (21), in which the air flow (23) separates from the guide element (30), comprises at least two walls (10, 11) arranged essentially in parallel and connected to one another by ribs (16, 17, 20) in such a way as to form internal cooling passages (18, 19, 25, 26, 27), and which is cooled on the inside with cooling medium (28, 29) flowing through the cooling passages (18, 19, 25, 26, 27), the cooling medium discharging from the guide element (30) at the trailing edge (21) essentially parallel to and between the walls (10, 11), and in a method of producing it, easier reworking and less susceptibility to foreign particles are achieved owing to the fact that at least some of the ribs are arranged as choke ribs (24) so as to terminate essentially flush with the trailing edge (21).

Abstract: At least one adjustable restricting point is introduced into the cooling air path of a coolable gas turbine component, and means which make it possible to change this restricting point during the operation of the machine are provided. In this way it is possible to adapt the amount of cooling air fed to the component continuously to the specific operating conditions.

Abstract: In a cooled blade for a gas turbine, a cooling fluid, preferably cooling air, flows for convective cooling through internal cooling passages located close to the wall and is subsequently deflected for external film cooling through film-cooling holes onto the blade surface. The fluid flow is directed in at least some of the internal cooling passages in counterflow to the hot-gas flow flowing around the blade. Homogeneous cooling in the radial direction is achieved by providing a plurality of internal cooling passages and film-cooling holes arranged one above the other in the radial direction in the blade in such a way that the discharge openings of the film-cooling holes in each case lie so as to be offset from the internal cooling passages, and in particular the discharge openings lie between the internal cooling passages.

Abstract: A coolable blade for a gas turbine or the like, having a blade body and a blade root, in which case the blade body is composed of a suction-side wall and a pressure-side wall, which, while forming a cavity, are connected via a leading edge, at least partly via a trailing edge and via a blade tip, the cavity is subdivided by essentially radially running separating webs into passages which form a continuous, repeatedly deflected flow path for a cooling medium, at least one blow-out opening is provided for the cooling medium, and the separating web adjacent to the trailing edge has one or more through passages close to the blade tip.

Abstract: A platelike projecting component portion (1) of a gas turbine or the like, with a surface (2) upon which hot gas acts and with cooling bores (12) through which a cooling medium is capable of flowing. Effective cooling is achieved in that at least one plenum (10; 30; 50) assigned solely to the component portion (1) is provided, which is arranged so as to be directly adjacent to the surface (2) upon which hot gas acts and through which the cooling medium is capable of flowing convectively, and in that, to form a cooling film, the cooling bores are designed as blow-out orifices (12; 52) which emanate from the plenum (10; 30, 50) and which issue on the surface (2) upon which hot gas acts.

Abstract: In a method of forming a cooling bore in a wall of a workpiece, the configuration of a feed section and a diffuser section is selected, a throughbore is produced with a cross-sectional area within the cross-sectional area of the feed section, and the diffuser section is cut out by a beam- or jet-drilling method in such a way that the drilling beam or jet in the region of the feed section remains essentially within the cross-sectional area of the latter.

Abstract: A cooled vane for a gas turbine or similar device including a vane blade constructed of a suction side wall and a pressure side wall that are connected via a leading edge and a trailing edge with each other, which has an essentially radially extending cavity through which a cooling medium is capable of flowing. The vane blade has multiple cooling channels that, starting from the cavity, extend through a vane section adjoining the trailing edge and formed by sections of the suction side wall and the pressure side wall, and end at the trailing edge. A first row of cooling channels is associated with the suction side (SS) of the vane blade, and a second row of cooling channels is associated with the pressure side (DS) of the vane blade. The cooled vane has improved cooling efficiency and can be produced entirely with a casting process while complying with basic geometric conditions.

Abstract: Pins (23) consisting of a material having high thermal conductivity are introduced, alternately with blow-out orifices (22) for a coolant (9), into the material, to be cooled, of a component (141), in such a way that said pins project out of the component on the cooling side (12) of the latter. These pins are cooled in the region which projects out of the component whilst heat is supplied to them in the region which is embedded in the component. The alternating arrangement with blow-out orifices ensures that the flow (7) passes around the pins. This point is important particularly when the pins are arranged in a narrow gap, such as occurs especially in the cooling of the trailing edges of gas turbine blades. The necessary number of blow-out orifices and therefore the coolant consumption is reduced.

Abstract: In a cooled blade for a gas turbine, in which blade a cooling fluid, preferably cooling air, flows for convective cooling through internal cooling passages (141-143) located close to the wall and is subsequently deflected for external film cooling through film-cooling holes (161-163) onto the blade surface, and the fluid flow is directed in at least some of the internal cooling passages (141-143) in counterflow to the hot-gas flow (18) flowing around the blade, homogeneous cooling in the radial direction is achieved owing to the fact that a plurality of internal cooling passages (141-143) and film-cooling holes (161-163) are arranged one above the other in the radial direction in the blade (10, 20, 30) in such a way that the discharge openings of the film-cooling holes (161-163) in each case lie so as to be offset from the internal cooling passages (141-143), in particular lie between the internal cooling passages (141-143).

Abstract: In a gas-turbine guide element (30) around which a hot air flow (23) flows and which, at least in a trailing edge region (21), in which the air flow (23) separates from the guide element (30), comprises at least two walls (10, 11) arranged essentially in parallel and connected to one another by ribs (16, 17, 20) in such a way as to form internal cooling passages (18, 19, 25, 26, 27), and which is cooled on the inside with cooling medium (28, 29) flowing through the cooling passages (18, 19, 25, 26, 27), the cooling medium discharging from the guide element (30) at the trailing edge (21) essentially parallel to and between the walls (10, 11), and in a method of producing it, easier reworking and less susceptibility to foreign particles are achieved owing to the fact that at least some of the ribs are arranged as choke ribs (24) so as to terminate essentially flush with the trailing edge (21).