Abstract: A turbine component (25) includes a root (21), a tip (22), and an airfoil portion (7) having a leading and a trailing edge (8,9), an external suction side and pressure side wall (13, 14) between the leading and trailing edge. The walls enclose a central cavity (1-6) for the passage of cooling air, the cavity being partitioned into a leading edge- and a trailing edge region (7a, 7b) by at least one longitudinally extending first web (15) connecting the suction side wall with the pressure side wall and a second longitudinally extending web (16), connecting the first web with the suction side wall, thereby defining a first and second entry chamber (2, 3). The first web (15) is provided with at least one cross-over hole (H1) between the first entry chamber and the leading edge chamber (1), whereas the second web has no openings.

Abstract: A gas turbine airfoil (1) includes a pressure sidewall (15) and a suction sidewall (16), extending from a root to a tip and from a leading edge region to a trailing edge and having at least one cooling passage between the pressure sidewall (15) and the suction sidewall (16) for cooling air to pass through and cool the airfoil from within. One or several of the cooling passages (3) extend along the leading edge of the airfoil (1) and several film cooling holes (1,2) extend from the internal cooling passages (3) along the leading edge region to the outer surface of the leading edge region. The film cooling holes (1,2) each have a shape that is diffused in a radial outward direction of the leading edge of the airfoil (1) at least over a part of the length of the film cooling hole (1,2).

Abstract: The invention describes a device for separating dust and dirt out of flowing media. A curved flow path (1) is imposed on the flow (21), and heavy foreign bodies are separated out of the main flow by centrifugal force. The partial stream required to carry away the foreign bodies is aftertreated in a filter (11) and returned in purified form. Unlike with conventional filters, which have to process the entire flow of media, pressure losses during the separation of dust are minimized, and on the other hand no medium is lost for removing the dust load.

Abstract: A hot gas path assembly, suitable for use in the hot gas path of a gas turbine, has as a hot gas duct wall an impact-cooled gas-impermeable element and a transpiration-cooled gas permeable element. The gas-permeable element is a run-on covering for the sealing tip, and the gas-impermeable element is a blade foot of a turbine blade. Coolant is led in series through an impact-cooling element to cool the gas-impermeable element, and through the gas-permeable element for transpiration cooling and, if appropriate, also cools the sealing tip. Coolant thus is utilized particularly efficiently. Subdividing walls are arranged for the lateral subdivision of the coolant path, particularly in the circumferential direction, into segments. Because of the subdivision, in the event of damage to the gas-permeable element in one segment, the other segments remain essentially uninfluenced. Redundant cooling orifices may ensure coolant flow even when flow resistance in a transpiration-cooled element rises.

Abstract: A cooled blade or vane for a gas turbine has a main blade or vane part which starts from a blade or vane root and a blade or vane shank and has a leading edge and a trailing edge, as well as, inside the main blade or vane part, a plurality of cooling ducts, which extend in the radial direction, are connected in series in terms of flow and of which a first cooling duct has a main stream of a cooling medium flowing through it along the leading edge. A second cooling duct has a main stream of a cooling medium flowing through it along the trailing edge, from the blade or vane root to the tip of the main blade or vane part. The outlet of the first cooling duct is in communication, via a first diverting region, a third cooling duct arranged between the first and second cooling ducts, and a second diverting region, with the inlet of the second cooling duct.

Abstract: In an emergency cooling system (17) for a component (1) which is subject to thermal load in operation, in, e.g., a turbine, the component (1) has a wall (3) which, in operation, is acted on by heat on a first wall side (14) and is acted on by a flow of cooling fluid (11) on a second wall side (15). The wall (3) has at least one emergency cooling opening (12) which is closed off by a plug (16) and through which cooling fluid flows from the second wall side (15) to the first wall side (14) when the plug (16) is absent. The plug (16) is designed so as to melt at a predetermined temperature. The plug (16) is a body which is produced separately from the component (1), the plug (16) being inserted into the emergency cooling opening (12), in which it is connected to the component (1).

Abstract: A gas turbine arrangement includes a rotor, a hot-gas passage, through which a hot-gas stream (12) flows while the gas turbine is operating, at least one first row of turbine blades or vanes (1), which have an airfoil(3) with a suction side (11) and a pressure side (10), and a platform (4), and at least one second row of turbine blades or vanes (2), which are arranged upstream of the first row of turbine blades or vanes (1) in the direction of the hot gases (12), and in the axial direction of the rotor and likewise have a platform (4). There is at least one seal (5, 6), through which a cooling air leakage stream (7) emerges while the gas turbine is operating, between the first row of turbine blades or vanes (1) and the second row of turbine blades or vanes (2), in the region of the respective platforms (4). An element guides the leakage stream (7) of cooling air along the surface of the platform (4) to the pressure side (10) of the first row of turbine blades or vanes (1).

Abstract: The invention describes a device for separating dust and dirt out of flowing media. A curved flow path (1) is imposed on the flow (21), and heavy foreign bodies are separated out of the main flow by centrifugal force. The partial stream required to carry away the foreign bodies is aftertreated in a filter (11) and returned in purified form. Unlike with conventional filters, which have to process the entire flow of media, pressure losses during the separation of dust are minimized, and on the other hand no medium is lost for removing the dust load.

Abstract: A gas turbine arrangement includes a rotor, a hot-gas passage, through which a hot-gas stream (12) flows while the gas turbine is operating, at least one first row of turbine blades or vanes (1), which have an airfoil(3) with a suction side (11) and a pressure side (10), and a platform (4), and at least one second row of turbine blades or vanes (2), which are arranged upstream of the first row of turbine blades or vanes (1) in the direction of the hot gases (12), and in the axial direction of the rotor and likewise have a platform (4). There is at least one seal (5, 6), through which a cooling air leakage stream (7) emerges while the gas turbine is operating, between the first row of turbine blades or vanes (1) and the second row of turbine blades or vanes (2), in the region of the respective platforms (4). An element guides the leakage stream (7) of cooling air along the surface of the platform (4) to the pressure side (10) of the first row of turbine blades or vanes (1).

Abstract: A hot gas path assembly, suitable for use in the hot gas path of a gas turbine, has as a hot gas duct wall an impact-cooled gas-impermeable element and a transpiration-cooled gas permeable element. The gas-permeable element is a run-on covering for the sealing tip, and the gas-impermeable element is a blade foot of a turbine blade. Coolant is led in series through an impact-cooling element to cool the gas-impermeable element, and through the gas-permeable element for transpiration cooling and, if appropriate, also cools the sealing tip. Coolant thus is utilized particularly efficiently. Subdividing walls are arranged for the lateral subdivision of the coolant path, particularly in the circumferential direction, into segments. Because of the subdivision, in the event of damage to the gas-permeable element in one segment, the other segments remain essentially uninfluenced. Redundant cooling orifices may ensure coolant flow even when flow resistance in a transpiration-cooled element rises.

Abstract: A sealing assembly for contactless sealing between static components and moving components of a gas turbine comprises a gas-permeable, abrasion-tolerant sealing element arranged opposite a sealing tip and secured in a support. In operation, a coolant can flow through the sealing element, for example a honeycomb element, due to its gas permeability, so the sealing element is cooled. A redundant coolant passage opens upstream of the sealing element on the hot-gas side of the assembly, so that coolant emerging therefrom flows over the sealing element on its hot-gas side. If the flow of coolant through the sealing element fails because flow through the sealing element becomes blocked, cooling is taken over by film coolant flowing out of the redundant cooling passage. Coolant mass flow is metered in via feeds, which effect the primary pressure loss in the device. The feeds may be designed as through-openings in an impingement cooling element.

Abstract: The present invention relates to an emergency cooling system (17) for a component (1) which is subject to thermal load in operation, in particular a component belonging to a turbine. The component (1) has a wall (3) which, in operation, is acted on by heat on a first wall side (14) and is acted on by a flow of cooling fluid (11) on a second wall side (15). The wall (3) has at least one emergency cooling opening (12) which is closed off by a plug (16) and through which cooling fluid flows from the second wall side (15) to the first wall side (14) when the plug (16) is absent. The plug (16) is designed so as to melt at a predetermined temperature.

Abstract: A heat shield of a turbo machine is provided with a microstructure. In a preferred embodiment, the microstructure element comprises a plateau, which is arranged on a rib in such a way that the structure has a “T”-shaped cross section. The ribs are preferably embodied as plates set on edge on the heat shield and are aligned with their surface perpendicular to the circumferential direction (U) of the turbo machine. This results in low bending dimensional rigidity in the circumferential direction. In this way, it is possible to accommodate scraping of a component involved in relative motion in the circumferential direction without plastic deformation. Moreover this arrangement gives the maximum possible resistance to a leakage flow. When used at high temperatures, it is furthermore advantageous to provide ways to enable a coolant to be supplied to the microstructure.

Abstract: The invention relates to a method for producing a cooled cast part for a thermal turbo machine by using a known casting process. Between a wax model of the cast part and a ceramic core, a wax seal is applied by hand above a step, only on an additional shoulder. The material that is created during the casting process at this point by the shoulder and the wax seal can be ground off without causing rough areas on the step to form. This simplifies the welding or soldering of a cooling plate to the step.

Abstract: The invention relates to a method for producing a cooled cast part (1) for a thermal turbo machine by using a known casting process. Between a wax model (10) of the cast part (1) and a ceramic core (6), a wax seal (8) is applied by hand above a step (7), only on an additional shoulder (9). The material that is created during the casting process at this point by the shoulder (9) and the wax seal (8) can be ground off without causing rough areas on the step (7) to form. This simplifies the welding or soldering of a cooling plate to the step (7).