Abstract: A turbine vane, especially a turbine vane of the last stages, respectively includes a lower area which is radially and externally arranged, an upper area which is radially and internally arranged, and a radial cooling air channel extending between the upper area and the lower area. Cooling air can be introduced into the channel via an inlet in the lower area, and can be at least partially discharged via an outlet in the upper area. The cooling channel includes a radial inner channel through which the cooling air flows from the lower area to the upper area, and an outer channel which is adjacent to the inner channel on the circumferential side thereof. The outer channel communicates with the inner channel and includes an outlet which is arranged in the lower area. Part of the cooling air flows back in the direction of the lower area via the outer channel and emerges via the outlet.

Abstract: The invention relates to a gas turbine, for energy generation, with a compressor, arranged coaxially to a rotor, mounted such as to rotate, for the compression of an inlet gaseous fluid, at least partly serving for combustion of a fuel in a subsequent annular combustion chamber, with generation of a hot working medium, with an annular diffuser arranged coaxially to the rotor, between the compressor and the annular combustion chamber, for distribution and deflection of the fluid, whereby a part of the fluid is diverted as cooling fluid for the turbine stages after the combustion chamber, by means of a dividing element, arranged in the fluid flow.

Abstract: The invention relates to a combustion chamber of a gas turbine, inside of which a supplied fuel is reacted with supplied combustion air in order to produce a working medium. The inside of the combustion chamber wall is provided with a lining formed from a number of heat shield elements. The or each heat shield element, together with the combustion chamber wall, forms an interior space that can be subjected to the action of a coolant. The aim of the invention is to provide a combustion chamber with a comparatively simple design that has a high system efficiency. To this end, the invention provides that a flow element is placed in the respective interior space while serving to effect a locally specific control of the flow of coolant.

Abstract: The invention relates to a segmented inner ring for holding guide blades. According to the invention, a lateral wall opposing the front side of the inner ring and pertaining to a shaft shoulder formed-on the rotor shaft extends radially, and respectively one half of a labyrinth seal is formed on the front side of the inner ring and on the shaft shoulder. The aim of the invention is to apply an arrangement of stacked labyrinth seals, known from airplane turbines, to a stationary gas turbine having a separation plane. To this end, a method is used to mount an inner ring of a gas turbine. The invention also relates to a stationary gas turbine comprising a segmented inner ring.

Abstract: The invention relates to a turbine and a method for dismantling a blade of a turbine. Said turbine comprises a rotor that extends in an axial direction and an accessible combustion chamber, which communicates with an annular hot-gas conduit, in which a plurality of blades that form a blade row is arranged. Each blade has a blade root that is fixed to the internal housing and a blade heard that lies opposite said root and faces the rotor, said head being fixed to a fixing ring of the turbine that encircles the rotor. The aim of the invention is to reduce the down time of a turbine during repair, inspection and/or maintenance work. To achieve this, the blade root and/or the blade head can be fixed by means of a manually detachable clamping device.

Abstract: A turbine engine with a turbine shaft which has a number of disks arranged adjacent to one another, to each of which a number of blades are fastened in a star arrangement, wherein these blades can be cooled with at least one coolant which flows through coolant channels inside the blades is provided.

Abstract: The invention relates to a gas turbine. The aim of the invention is to provide an axial sealing between a vane ring and a moving blade ring, which has an excellent sealing effect, is easy to install and inexpensive to produce. For this purpose, a sealing element is used that extends across at least a fourth of the hot gas channel circumference. Preferably, said sealing element extends across approximately half the circumference and is inserted in grooves of the vane support and the vane platforms.

Abstract: The invention relates to a combustion chamber, in particular of a gas turbine, comprising an external wall structure that surrounds an internal area and an internal wall, which is formed by the surface of a housing that is located in the internal area. Said combustion chamber can be cooled essentially by convection by an air stream that flows between the external wall structure and the internal wall, whereby the air stream is conducted in a closed cooling air canal. The housing can be mounted in the internal area of the combustion chamber by means of a suspension device, which comprises a large number of fixing elements that are arranged on the periphery of the housing and are braced against the wall structure.

Abstract: The invention relates to a method for producing a monocrystalline component, having a complex moulded structure with different structure parts, from a molten metal. According to the method, said molten metal is located in a negative mould, corresponding to the moulding structure and said negative mould moves with the formation of a solidification front on a temperature drop, which is adapted to the crystallization speed of the molten metal and which includes the melting point. Said method is characterized in that at least one of the structure parts of the moulded structure experiences an individual temperature drop. If the solidification front has to grow through a structure part, which is inappropriately oriented in relation to the solidification front, said structure part or zone can experience an individual temperature drop. This enables monocrystalline components, having a complex moulded structure, to be produced in a reliable and economic manner.

Abstract: A turbine (1) with a rotationally symmetrical rotor (4) on rotary bearings which has on its outer perimeter moving blade retaining grooves running transverse to the outer perimeter and set at the same angular distance from one another, having a moving blade (13) that has a vane (24) and a moving blade foot (19) which corresponds to the moving blade retaining groove (18) and which is inserted in one of the moving blade retaining grooves (18), wherein a platform (23) is located between the moving blade foot (19) and the vane (24) and extends transverse to the moving blade foot (19), having a baffle cooling element (22) which is located between two directly adjacent moving blades (13) between its platforms (23) and the rotor (4) and through which a cooling fluid can flow to cool the platform (23).

Abstract: In order to develop a flow control body (6) for separate control of a cooling fluid inflow and a cooling fluid outflow for combustion chambers with a closed cooling system for turbines such that a simplified cooling fluid flow control is made possible in the combustion chamber wall, it is proposed with the invention that the flow control body (6) has a non-rotationally symmetrical cross-sectional shape (7) in a flow control section.

Abstract: The invention relates to a heat shield arrangement for a hot gas conducting structure, in particular a metal component of a gas turbine unit or combustion chamber, with the heat shield elements anchored adjacently on a support structure to cover a surface. Said heat shield elements each comprise a lateral groove, arranged in the region of the edge of the surface thereof facing the hot gas, at least two adjacent shield elements are connected by at least one seal element mounted in the groove. The seal element is embodied as a sealing flap, which may be displaced from a first position to a second position and vice versa, whereby the first position is an open position without a sealing effect and the second position is a closed position with a sealing effect. According to said method the sealing flap is moved from the first to the second position by the movement of a heat shield element.

Abstract: A gas turbine combustion chamber comprises a manhole as access to a combustion chamber interior, which may be sealed with a manhole cover. The manhole comprises an inner cooling chamber and may thus take particularly high thermal loads.

Abstract: A turbine blade or vane includes an inner contour profile which is matched to the contour profile of the outer transition region, so that a substantially uniform blade or vane wall thickness is achieved.

Abstract: Components must often be released again from their holder for maintenance. Since the fastenings are often very complicated, it takes a considerable amount of time to release them. A fastening system is one where components can be fastened in a rotationally locked manner to a holder, and released again in a simple, reliable and quick manner.

Abstract: This invention relates to a combustion chamber arrangement for a gas turbine, with a number of individual combustion chambers which open into an annular gap, leading to a turbine chamber, whereby burners are arranged before the individual combustion chambers, connected to the individual combustion chambers through a turbine housing. According to the invention, said combustion chamber arrangement may be further developed, such that the cooling efficiency of the individual combustion chambers may be significantly improved, with an embodiment of simple construction, whereby at least one collar, arranged on one side of the turbine housing, facing the turbine chamber, running radially in the direction of the turbine chamber, at least partly surrounds a section of at least one individual combustion chamber whilst leaving a gap space.

Abstract: The invention relates to a combustion chamber for a gas turbine having at least one closed-circuit-cooled burner insert which can be disposed in an inlet opening of the combustion chamber for the purpose of feeding and/or igniting a combustible gas/air mixture, and having an outlet opening. The object of the present invention is therefore to create an arrangement enabling simplified manufacture and assembly to be achieved.

Abstract: A screw includes a head and a shank, and includes a coolant passage which has an inflow opening and an outflow opening. The cooling pasage does not pass axially through the entire head and shank. By avoiding a coolant flow which passes axially through the entire screw, especially effective utilization of a coolant is achieved, in particular by coolant which also flows on the outer surface of the screw.

Abstract: The invention relates to an annular combustion chamber for a gas turbine wherein the annular combustion chamber extends in an axial direction, encloses a combustor and has on its inside facing the combustor a bearing structure on which a lining element secured to this lines the annular combustion chamber. The object is to disclose an annular combustion chamber with a lining element that meets the mechanical requirements while at the same time taking account of the system's maintenance-friendliness. The object is achieved in that the annular combustion chamber has a lining element wherein on the rear side facing away from the combustor of two edge areas on the lining element a plurality of interlocking means are located which have a hook width and wherein the lining element is secured to the corresponding bearing structure such that in order to release the lining element from the bearing structure the lining element is moved by the extent of the hook width of the interlocking means in the axial direction.

Abstract: In order to develop a combustion chamber with a closed cooling system for a turbine with an inner wall and an outer wall (1) bounding the combustion area, wherein there is an intermediate space between the inner wall and the outer wall (1) through which cooling fluid can flow, and which comprises a cooling fluid feed system opening out into the intermediate space and a cooling fluid discharge system for discharging the cooling fluid from the intermediate space, so that it has a reduced extension in the radial direction, it is proposed with the invention that the cooling fluid discharge system should comprise channel-type drainage structures (8) running essentially along the axial orientation of the combustion chamber, which are interrupted by inlet structures (4) of the cooling fluid feed system arranged between the drainage structures (8).