Abstract: A guide vane for a turbomachine, having a blade airfoil and at least one platform, to which the blade airfoil is connected. A cooling channel system is provided for cooling the platform and the blade airfoil. The platform has, on the side thereof facing the airfoil, at least one sealing lip for sealing to a rotating system of the turbomachine. At least one cooling channel extends through the sealing lip, which cooling channel forms part of the cooling channel system.

Abstract: A guide vane for a turbomachine, having a blade airfoil and at least one platform, to which the blade airfoil is connected. A cooling channel system is provided for cooling the platform and the blade airfoil. The platform has, on the side thereof facing the airfoil, at least one sealing lip for sealing to a rotating system of the turbomachine. At least one cooling channel extends through the sealing lip, which cooling channel forms part of the cooling channel system.

Abstract: A gas turbine having a turbine stage is presented. The gas turbine has a guide vane that can be operated cooled by a cooling medium, and a cooling medium feed device for feeding the cooling medium into the interior of the guide van, which, in the region of its rear edge, has on the pressure side at least one cooling medium outlet opening, through which the cooling medium can flow out of the interior of the guide vane into the main flow. The cooling medium feed device has a mass flow control device for controlling the mass flow through the at least one cooling medium outlet opening, with which the mass flow through the at least one cooling medium outlet opening can be increased during operation of the gas turbine under part-load compared to operation of the gas turbine under full load.

Abstract: A method for producing a hole with side-delimiting flanks in a component using a laser beam is provided. A laser beam is directed onto the component. A side flank of the hole is traced with the laser beam. A partial volume of the hole is formed by vaporizing the component material. This is repeated until the whole volume is formed. The laser beam may be oriented so that it includes an angle of more than 8° with the traced side flank.

Abstract: A turbine blade is provided having a blade and a modular platform which follow one another along a longitudinal axis of the turbine blade. In order to provide a modular turbine blade that has an especially plain and simple design and that ensures an especially reliable, long-lasting, durable connection of the individual components among each other, the blade has an extension and the platform has an outer platform part and an at least two-part inner platform part which is radial in relation to the longitudinal axis and which lie laterally against the extension of the blade, and the outer platform part is designed as an endless platform frame that surrounds the outer edge of the inner platform part.

Abstract: A turbine blade is provided, having a fastening section, a platform, and a blade, which follow one another along a longitudinal axis of the turbine blade, wherein the platform, in radial relation to the longitudinal axis, has an inner platform part and an outer platform part, wherein the outer platform part is designed as a closed platform frame that encloses the outer edge of the inner platform part. An associated method for producing a turbine blade is also provided.

Abstract: A gas turbine having a turbine stage is presented. The gas turbine has a guide vane that can be operated cooled by a cooling medium, and a cooling medium feed device for feeding the cooling medium into the interior of the guide van, which, in the region of its rear edge, has on the pressure side at least one cooling medium outlet opening, through which the cooling medium can flow out of the interior of the guide vane into the main flow. The cooling medium feed device has a mass flow control device for controlling the mass flow through the at least one cooling medium outlet opening, with which the mass flow through the at least one cooling medium outlet opening can be increased during operation of the gas turbine under part-load compared to operation of the gas turbine under full load.

Abstract: A method including mechanical removal and electrical discharge machining (EDM) working allowing symmetrical or asymmetrical holes to be produced with exact contours in a layer system including a metallic substrate and a non-metallic outermost layer is provided. In a first step, an outer region of the hole is worked by mechanical removal. In a final method step, when the underlying substrate or a metallic adhesion promoting layer has been reached an electrical discharge machining tool is used.

Abstract: There is described a method with which, on the basis of a three-dimensional recording of a component to be reworked, its surface configuration can be determined and stored temporarily so that, after it has been coated, it can be produced in its original surface form, or in its surface form then required, in certain regions, i.e. locally in the area of film-cooling openings. An especially precise and quick three-dimensional recording can be achieved by the use of the triangulation method. In this case, a reference pattern depicted on the component by a projector is recorded by two camera arranged at an angle. From the images from the cameras, the coordinates describing the surface three-dimensionally can then be determined by a control system using the triangulation method.

Abstract: A turbine blade is presented including a vane that runs along a blade axis and a platform region, which is located at the root of the vane and has a platform that extends transversally to the blade axis. An improved cooling of a platform region and the transition region is provided from a turbine blade to a platform of a turbine blade. The platform includes a first platform wall that does not support the vane and a second platform wall that supports the vane. At the root of the vane and over the course of the transition region from the turbine blade to the platform, the first platform wall is aerodynamically curved and the course of the second platform wall has a receding shoulder in relation to the first platform wall, as a continuation of the vane.

Abstract: A turbine vane or blade including an interior structure is provided. In addition, turbulence elements connected directly upstream of openings disposed at the rear edge of the blade of the turbine vane or blade are also provided. These are disposed in a sequence, each having a flow side against which a coolant flows and which is at least partially arched in a concave manner. Preferably, the turbulence elements are configured in a crescent-shaped manner. This makes it possible to enlarge the openings without resulting in an increased consumption of coolant. A casting core is also provided. The openings required in the casting core for the production of the webs of a turbine vane or blade may now be placed at further distances than before.

Abstract: The invention relates to a turbine blade comprising a vane that runs along a blade axis and a platform region, located at the root of the vane having a platform that extends transversally to the blade axis. The aim of the invention is to configure a delimitation of a flow channel of a gas turbine in the simplest possible manner. Therefore, the platform is configured by an elastic sheet metal part that rests on the vane. Said part leads to a gas turbine comprising a flow conduit that runs along an axis of the gas turbine, said conduit having an annular cross-section for a working medium and a second vane stage that is situated downstream of a first vane stage, which runs along the axis.

Abstract: There is described a vane wheel of a turbine comprising at least one vane, the footing thereof being held on a wheel disk. At least one cooling channel is arranged between the wheel disk and the vane footing. The vane wheel having a plurality of turbulators is embodied on at least one of the walls of the cooling channel, the turbulators being configured in such a way that the turbulence and thus the heat transfer of a cooling fluid flowing through the cooling channel are increased.

Abstract: The invention relates to a turbine blade comprising a vane that runs along a blade axis and a platform region, located at the root of the vane having a platform that extends transversally to the blade axis. The aim of the invention is to configure a delimitation of a flow channel of a gas turbine in the simplest possible manner. Therefore, the platform is configured by an elastic sheet metal part that rests on the vane. Said part leads to a gas turbine comprising a flow conduit that runs along an axis of the gas turbine, said conduit having an annular cross-section for a working medium and a second vane stage that is situated downstream of a first vane stage, which runs along the axis.

Abstract: A method for producing a hole with side-delimiting flanks in a component using a laser beam is provided. A laser beam is directed onto the component. A side flank of the hole is traced with the laser beam. A partial volume of the hole is formed by vaporizing the component material. This is repeated until the whole volume is formed. The laser beam may be oriented so that it includes an angle of more than 8° with the traced side flank.

Abstract: The invention relates to a turbine blade comprising a vane that runs along a blade axis and a platform region, which is located at the root of the vane having a platform that extends transversally to the blade axis. The aim of the invention is to configure a delimitation of a flow channel of a gas turbine in the simplest possible manner. Therefore, the platform is configured by an elastic sheet metal part that rests on the vane. Said part leads to a gas turbine comprising a flow conduit that runs along an axis of the gas turbine, said conduit having an annular cross-section for a working medium and a second vane stage that is situated downstream of a first vane stage, which runs along the axis.

Abstract: There is described a method with which, on the basis of a three-dimensional recording of a component to be reworked, its surface configuration can be determined and stored temporarily so that, after it has been coated, it can be produced in its original surface form, or in its surface form then required, in certain regions, i.e. locally in the area of film-cooling openings. An especially precise and quick three-dimensional recording can be achieved by the use of the triangulation method. In this case, a reference pattern depicted on the component by a projector is recorded by two camera arranged at an angle. From the images from the cameras, the coordinates describing the surface three-dimensionally can then be determined by a control system using the triangulation method.

Abstract: A turbine blade (2), with a root section (4), with a tip section (6) and with a blade leaf (12) which is provided with a number of coolant ducts (22) through which a coolant (K) is capable of flowing, outlet ducts (34) which issue in outlet ports (24) branching off, in the leading edge region (28) of the blade leaf (12), from a coolant duct (22) running essentially in the longitudinal direction (L) of the turbine blade (2) and spaced apart from the leading edge (14), the outlet ports (24) being arranged along at least two rows oriented essentially parallel to the leading edge (14), and the outlet ducts (34) being oriented, in the region of their respective outlet port (24), obliquely with respect to the longitudinal direction (L) of the turbine blade (2), in such a way that the coolant (K) flowing out in a root-side subsection (38) of each row possesses, in the region of the outlet ports (24), a velocity component pointing toward the tip section (6) of the turbine blade (2), and the coolant (K) flowing out in

Abstract: The invention relates to a turbine blade comprising a vane that runs along a blade axis and a platform region, which is located at the root of the vane and has a platform that extends transversally to the blade axis. The aim of the invention is to guarantee the improved cooling of a platform region and the transition region from a turbine blade to a platform of a turbine blade, thus ensuring the cooling of the delimitation of a flow channel in a gas turbine. To achieve this, the platform comprises a first platform wall that does not support the vane and a second platform wall that supports said vane. According to the inventive concept, at the root of the vane and over the course of the transition region from the turbine blade to the platform, said first platform wall is aerodynamically curved and the course of the second platform wall has a receding shoulder in relation to the first platform wall, as a continuation of the vane.

Abstract: There is described a vane wheel of a turbine comprising at least one vane, the footing thereof being held on a wheel disk. At least one cooling channel is arranged between the wheel disk and the vane footing. Said vane wheel having a plurality of turbulators is embodied on at least one of the walls of the cooling channel, said turbulators being configured in such a way that the turbulence and thus the heat transfer of a cooling fluid flowing through the cooling channel are increased.