Abstract: An arrangement for cooling a flow-passage wall surrounding a flow passage is described, having at least one rib element which induces flow vortices in a flow medium passing through the flow passage, is attached to that side of the flow-passage wall which faces the flow passage, and the shape and size of which are selected in accordance with a certain heat transfer coefficient and a certain pressure loss caused in the flow medium due to the latter flowing over the rib element.

Abstract: Described is a sealing arrangement for reducing leakage flows inside a rotary fluid-flow machine, preferably an axial turbomachine, having moving and guide blades, which are in each case arranged in at least one moving- or guide-blade row respectively and have blade roots, via which the individual moving and guide blades are connected to fastening contours. A sealing element having felt-like material is provided between at least two adjacent blade roots within a guide- or moving-blade row or between guide and/or moving blades and adjacent components of the fluid-flow machine.

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: 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: The arrangements according to the invention and the methods according to the invention serve to seal a gap 20 against a primary fluid 10 by means of a secondary fluid 11 in a fluid-dynamic and non-contact manner, which primary fluid 10 flows over the gap 20. The secondary fluid 11 forms a preferably rotating vortex flow 13 in the gap in at least one or more sections along the gap. The flow of the secondary fluid 11 is preferably guided in a chamber 26, which is arranged in the gap 20. The chamber 26 is designed as a rotary chamber along the entire gap 20 or also as a local chamber 226 extending only locally along the gap. The secondary fluid 11 may be supplied via supply conduits 40, in which the gap 120 itself may be utilized for supplying secondary fluid 115 to the chamber 126. As further elements for the guidance of the vortex flow, guiding lips 50, undercuts of the chamber contour 351, and guiding elements 160 may be arranged in the gap.

Abstract: A blade component of a gas turbine is disclosed around the outside of which hot air flows. The blade component is constructed as a hollow profile having outside walls and a tip cover, and having guiding walls arranged between the outside walls and connecting said outside walls. The blade component is cooled on the inside by cooling air flowing through cooling channels between the outside walls and the guiding walls. Cooling air flows through deflection areas in which the cooling air is deflected into flow stagnation zones. An efficient cooling of the blade component in the area of the stagnation zones is obtained in the area of the flow stagnation zones which are located at the outer corner of the deflection area. At least one drilled opening is provided in the outside wall through which drilled opening cooling air is able to flow at the stagnation zone from the cooling channel onto the outside of the blade component.

Abstract: Arrangement of holes for forming a cooling film on a wall (50) which is subjected to a flow of hot gas. Two rows (1, 2) of holes (10, 20) are provided which are arranged adjacent to one another, the diameter (d1) of the upstream holes (10) being smaller than the diameter (d2) of the upstream holes (20). The number of upstream holes (10) is equal to or smaller than the number of downstream holes (20). The use of such an arrangement of holes achieves the formation of an extremely effective cooling film with a simultaneously small consumption of cooling air.

Abstract: A hot-gas stream (40) flows along the surface of a segment arrangement for shroud bands, in particular in a gas turbine. The segment arrangement comprises segments (20, 20′) arranged next to one another and in each case separated from one another by a gap (12). The hot-gas stream (40), in at least one section (70) of the gap (12), has a velocity component perpendicular to the direction of the gap from a first segment (20) to a second segment (20′). In this case, in said section (70), along that edge (26) of the first segment (20) which faces the gap (12), at least one film-cooling bore (52) connects a cooling-air chamber (50), allocated to the first segment, to the surface (22) subjected to the hot-gas stream (40), and/or, in said section (70), along that edge (26′) of the second segment (20′) which faces the gap (12), at least one edge-cooling bore (56) connects a cooling-air chamber (50′), allocated to the second segment, to the inside (28′) of the gap (12).

Abstract: In an air-cooled turbine blade (10) which has a shroud-band element (11) at the blade tip, the shroud-band element (11) extending transversely to the blade longitudinal axis, hollow spaces (16, 16′, 17, 17′) for cooling being provided in the interior of the shroud-band element (11), which hollow spaces (16, 16′, 17, 17′) are connected on the inlet side to at least one cooling-air passage (18) passing through the turbine blade (10) to the blade tip and open on the outlet side into the exterior space surrounding the turbine blade (10), the hollow spaces (16, 16′, 17, 17′) and the shroud-band element (11) are matched to one another in shape and dimensions in order to reduce the weight of the shroud-band element (11).

Abstract: Turbomachine, in particular a compressor of a gas turbine, having rotor blades (11) and guide vanes (12), in which individual or all guide vanes (12) are configured as cooled vanes. The cooled vanes (12) have air guidance ducts (13) which emerge into outlet openings (14) in the region of the vane tips (15). Cooling air (K) is ejected through the outlet openings (14) and impinges at high velocity onto a rotor shaft (18). The cooling effect which can be achieved by this means is optimal and, in addition, leads to a raising of the compressor efficiency and the surge line.

Abstract: In a cooling system for the leading-edge region of a hollow gas-turbine blade, a duct (10) extends inside the thickened blade leading edge (5) from the blade root (1) up to the blade tip (2). The duct (10), via a plurality of bores (9) made in the blade leading edge, communicates with a main duct (3), through which the cooling medium flows longitudinally, and the flow through the duct (10) occurs longitudinally over the blade height, and the duct (10) is formed with a variable cross section. The cross section of the duct (10) increases continuously in the direction of flow of the cooling medium from the blade root up to the blade tip. In the case of blades having a cover plate (11), the duct (10) merges at its top end into a chamber (12), which is mounted below the cover plate and is in operative connection with a pressure source, the pressure of which is lower than the pressure in the main duct.

Abstract: Platform cooling having a guide-blade platform (30; 60) which is subjected to a hot-gas stream (20) and is separated by a gap (36; 66) from a combustion-chamber segment (40; 70) arranged upstream, one or more segment cooling bores (42; 72) being made in the combustion-chamber segment (40; 70), which segment cooling bores (42; 72) connect a cooling-air chamber (44; 74) to the gap (36; 66). The guide-blade platform (30; 60) has a surface (34; 64) on the downstream side in the region of the gap (36; 66), the axes of the one or more segment cooling bores (42; 72) running roughly tangentially to said surface (34; 64).

Abstract: In a cooling system for the leading-edge region of a hollow gas-turbine blade, a duct (3), through which flow occurs longitudinally, extends from the blade root up to the blade tip and is defined in the region of the blade body (4) by the inner walls of the leading edge (5), the suction side (6) and the pressure side (7) and by a web (8). The inner walls of the suction side and the pressure side are provided with a plurality of ribs (9), which run slantwise and at least approximately in parallel. The suction-side ribs and the pressure-side ribs are offset from one another over the blade height. The ribs (9) run radially inward from the web (8) in the direction of the leading edge (5), merge into the radial in the region of the leading edge and are led around the leading edge. The deviation of the ribs (9) from the slant into the radial is effected with the smallest possible radius.

Abstract: In a cooling system for the trailing edge region of a hollow gas turbine blade, there extends from the blade root (1) to the blade tip (2) a duct (3) through which the flow passes longitudinally and which, in the region of the blade body (4), is delimited by the inner walls of the trailing edge (5), the suction side (6) and the pressure side (7) and by a web (9), the inner walls of the suction side and of the pressure side being provided with a plurality of ribs (8) running at least approximately parallel. The ribs (8) run obliquely from the web (9) in the direction of the trailing edge (5) and are directed radially outward on at least one of the two inner walls. The suction-side ribs and the pressure-side ribs are offset relative to one another over the blade height. The ratio of the height (h) of the ribs (8) to the local height (H) of the duct (4) is constant over the longitudinal extent of the ribs.

Abstract: A coolable blade (10) essentially comprises a blade root (11) and a blade body (1), which is composed of a pressure-side wall (6) and a suction-side wall (5). They are connected to one another essentially via a trailing-edge region (4) and a leading-edge region (3) in such a way that at least one hollow space (2) used as a cooling-fluid passage is formed. An essentially radially running, diverging cooling passage (7) is arranged in the trailing-edge region (4).

Abstract: A coolable blade (10) essentially comprises a blade root (11) and a blade body (1), which is composed of a pressure-side wall (6) and a suction-side wall (5). They are connected to one another essentially via a trailing-edge region (4) and a leading-edge region (3) in such a way that at least one hollow space (2) used as a cooling-fluid passage is formed, in which ribs (7) are arranged. At least one rib (7) is configured in such a way that it has an apex (9) and two legs (14, 15), the legs (14, 15) of the rib being bent at an acute angle (8) relative to a radial plane (13). It is especially advantageous to arrange these ribs in a hollow space of double triangular shape having acute-angled triangular points in the region of the leading edge and the trailing edge.