Abstract: The invention relates to a turbine blade arrangement consisting of rotating blades (4) respectively provided with a leg (8) which can be respectively inserted into a groove (9) on the outer circumference (2) of a turbine disk in a radial, positive fit and which are respectively provided with a profiled section (5) which has a lateral platform (6) located in an end area on the side of the disk. According to the invention, at least one part (10) of the platform is joined to the turbine disk by means of a retaining element (11) which is independent from the leg (8) of the blades in order to extend the profiled sections of the rotating blades.

Abstract: The invention relates to a device for casting a workpiece, especially a turbine blade with inner cooling, comprising a casting cavity (1) in which casting cores (2) which produce channels (3) that pass through the workpiece are provided. The aim of the invention is to improve a device of this type in such a way that there are no poorly cooled areas present in the workpiece. To this end, the casting cores (2) are placed in the casting cavity (1) in such a way that they rest against each other loosely.

Abstract: In gas turbines, compressed air is supplied via an air duct to combustion chambers and is heated there. Pressure losses in the air duct should be minimized in order to ensure good overall efficiency. This is achieved by the compressed air flowing with approximately constant velocity in the air duct from the compressor to the inlet into the combustion chamber. This is supported by the effective cross section of the air duct being almost constant over this distance.

Abstract: In order to provide a method of air guidance and a design for a gas turbine combustion chamber which permits improved cooling and reduced pressure losses and which avoids the overcooling phenomena by specific reaction to hot spots, a gas turbine combustion chamber includes a casing and at least one hollow element. The at least one hollow element is in connection with air guidance regions of the combustion chamber via at least two openings. As such, a tangential through-flow exists with a subsequent axial flow to the burner.

Abstract: Disclosed is a gas turbine blade, in which a ceramic covering, which is mechanically fastened to a metal platform, is arranged in a manner that the metal platform is protected against a hot gas in a hot gas duct of a gas turbine.

Abstract: A gas turbine with axially mutually displaceable guide parts that compensates for differing amounts of thermal expansion, comprising guide parts which can be displaced with respect to one another in the axial direction and enclose a funnel-like gas duct from outside. In order to optimize a rotor blade tip gap, the invention proposes to displace at least one of the funnel-like guide parts under control by means of a motor. As a result of the axial displacement, because of the funnel-like shape of the guide parts, the width of the rotor blade tip gap is changed.

Abstract: The present invention relates to a turbine blade, in particular for a gas turbine, having an airfoil profile and at least one platform for fastening to a primary component. According to the invention, each platform encloses an obtuse angle with a longitudinal axis of the airfoil profile. The design of the turbine blade as a single crystal is facilitated by this construction.

Abstract: A gas turbine is provided which has a combustor comprising a plurality of can-type combustor elements and an annular element. Isolated combustion takes place in the can-type combustor thereby generating individual component hot gas streams. The component hot gas streams are merged in the annular part. Combustion oscillations are substantially avoided by decoupling combustion flames. Accordingly, temperature and pressure homogenization as well as combustion stabilization by cross-ignition is effected.

Abstract: In a method of producing a turbine blade in hollow section, an especially low defect or scrap rate is to be ensured. To this end, a first core element is connected via a number of approximately cylindrical spacers to a further core element and/or to a casting mold, the cavities left in the casting mold by the core elements being filled by blade material, and the openings remaining in the turbine blade after the removal of the core elements and the spacers and produced by the spacers being closed by stopper elements.

Abstract: The present invention relates to a process for producing a turbine blade or vane (13; 14), which has at least one chamber (22; 23, 24, 25) and an inlet (30; 31) for applying a cooling medium to the chamber (22; 23, 24, 25), at least one inlet (30) running at an angle with respect to a longitudinal axis (37) of the turbine blade or vane (13; 14). According to the invention, to form the inlet (30) a core (35) with a projection (33) is used, which projection is arranged at a distance from a mold (40). Therefore, after removal from the mold the inlet (30) of the turbine blade or vane (13; 14) is closed, and is opened up by machining. The invention also relates to a turbine blade or vane, in particular for a gas turbine (10), which has at least one chamber (22; 23, 24, 25) and at least one inlet (30; 31) for applying a cooling medium to the chamber (22; 23, 24, 25).

Abstract: A shaped part (30) for forming a guide ring (21) for a gas turbine (1) is, on the one hand, to be produced with particularly little outlay and, on the other hand, is to be designed so that it can be cooled particularly effectively with steam as the coolant. For this purpose, according to the invention the shaped part (30) comprises a base plate (34) which, together with an associated metal guide plate (38, 44, 52), forms a flow passage (36) for a coolant which, in cross section, extends substantially over its entire width, with respect to the axial direction (x) of the guide ring (20, 21).

Abstract: In a gas turbine (1) having a number of rotor blades (12) in each case combined into rows of rotor blades and arranged on a turbine shaft (8) and having a number of stator blades (14) in each case combined into rows of stator blades and connected to a turbine casing, a particularly high efficiency is to be achieved with simple means, with reliable cooling of the turbine blades (12), (14). For this purpose, according to the invention at least some of the stator blades (14) have an inlet (48) for a cooling medium at their free end facing the turbine shaft (8).

Abstract: The present invention relates to a turbine blade or vane (13; 14), in particular for a gas turbine (10), which has at least one chamber (18; 29; 20; 21) which can be acted on by a cooling medium and, at a rear edge (26), has a gap (25), which is delimited by two walls (28, 29), for the cooling medium to be discharged. According to the invention, at least one of the walls (28; 29) can be remachined in order to change the cross section (A) of the gap (25). In this way, the cross section (A) can be adapted to the particular boundary conditions, and therefore the consumption of cooling medium can be minimized. The invention also relates to a process for producing a turbine blade or vane (13; 14) of this type.

Abstract: A gas turbine (5) according to the invention, which comprises a main combustion chamber (10), a cooling system for air cooling of at least the guide vanes (26, 29) and guide rings (28, 38) of various stages (25, 27) of the gas turbine (5), and a main gas passage, also includes a further combustion chamber (34), which is arranged downstream of the main combustion chamber (10) as seen in the hot-gas main direction (H). The cooling air (15) used to cool a stage (25) of the gas turbine which is arranged upstream of the further combustion chamber (34) is fed into this further combustion chamber (34). In this context, it is particularly advantageous for the cooling air (15) used to cool the various stages (25, 27) of the gas turbine (5) to be fed for combustion. This makes it possible, inter alia, to increase the output of the gas turbine (5) without having to increase the supply of fuel.

Abstract: In a turbine (1) having a moving-blade row which has a moving blade (12) on a turbine shaft (8), and having a guide blade (14) which has a guide-blade row, an especially high efficiency is to be achieved with simple means with the turbine blades (12, 14) being cooled in a reliable manner. To this end, the cooling-medium passage inside the guide blade (14), according to the invention, is split up into a first and a second partial-flow passage, the cooling medium flowing in the first partial-flow passage being used for cooling the guide blade (14), and the cooling medium flowing in the second partial-flow passage being passed on more or less free of losses.

Abstract: A gas turbine blade includes an inlet edge region of a platform. Eroded into it is a slot which runs parallel to the flow-on edge and into which cooling air is introduced in an impact-cooled manner from the platform under side and is discharged in a film-cooling manner from the platform top side. This results in an efficient cooling system for the flow-on edge region of the platform. The method for producing a gas turbine blade includes producing ducts leading into the slot using laser drilling, the slot wall of the slot being protected by a Teflon strip.

Abstract: A gas turbine blade is used for closed steam cooling. A partition, preferably designed as a metal sheet, divides a first part cavity in the axial direction. This is done in such a way that steam is capable of being guided out of the first subspace into an inlet edge cavity and from this into a second subspace with an impact-cooling effect, This has the advantage that closed steam cooling is designed to be particularly simple and cost-effective in manufacturing terms, while at the same time the inlet edge has an aerodynamically favorable shape.

Abstract: A hearing protector, including a sealing body with a channel, and a muffling device which is connected to the sealing body and connects to the channel. When the sealing body is placed in an auditory canal, the channel extends between the auditory canal and the atmosphere. The channel has a distal end part at the side of the auditory canal and a proximal end part at the side of the atmosphere. The muffling device connects to the proximal end part of the channel and includes a rotatable control element, provided with at least one through aperture. The muffling device also includes a housing element provided with at least one through aperture. The control element and the housing element are rotatable relative to each other between two or more discrete rotation positions with corresponding muffling value. The apertures in the control element and the housing element overlap each other to a greater or lesser extent depending on a mutual angle of rotation.

Abstract: The turbine blade has an internal space through which a coolant fluid is guided and in which stiffening ribs are formed to reinforce and support the external walls. Coolant screens that reduce the cooling of the stiffening ribs, are arranged in front of the stiffening ribs in order to reduce thermal stresses. The turbine blade is preferably a gas turbine blade.

Abstract: A turbine guide blade includes a platform which absorbs thermal loads and a fastening region adjoining the platform for absorbing mechanical loads. The fastening region has such a slim construction that it leaves a cold side of the platform readily accessible.