Abstract: Provided is a silo combustion chamber comprising a vertically extending flame tube that can be lit from above and through which circulation takes place in a downward motion, the outer surface of the flame tube being provided with a plurality of cooling fluid supply openings and the inside thereof being lined with ceramic heat shield elements, the lowest heat shield elements being supported on a metal supporting ring; a conically tapered mixing tube arranged downstream from the flame tube, into which the lower region of the flame tube is set; and an outer housing that surrounds the flame tube and the mixing tube, forming an annular supply channel, the lowest heat shield elements completely covering the radially inwardly oriented surfaces of the supporting ring. Also provided is a method for retrofitting a silo combustion chamber.

Abstract: Provided is a silo combustion chamber comprising a vertically extending flame tube that can be lit from above and through which circulation takes place in a downward motion, the outer surface of the flame tube being provided with a plurality of cooling fluid supply openings and the inside thereof being lined with ceramic heat shield elements, the lowest heat shield elements being supported on a metal supporting ring; a conically tapered mixing tube arranged downstream from the flame tube, into which the lower region of the flame tube is set; and an outer housing that surrounds the flame tube and the mixing tube, forming an annular supply channel, the lowest heat shield elements completely covering the radially inwardly oriented surfaces of the supporting ring. Also provided is a method for retrofitting a silo combustion chamber.

Abstract: A seal arrangement (15; 26; 43; 50) for sealing an annular gap (14) between a high-pressure steam space (12) and an adjacent low-pressure steam space (13). The gap is defined between two turbine casings (10, 11) each split into two casing halves, the seal arrangement (15; 26; 43; 50) has a seal element (24; 47; 58) which is formed in a segmented and annular manner and extends between the two turbine casings (10, 11) and engages in an annular receiving groove (9, 23; 30, 34; 49; 54) by means of at least one of its radial end regions. The seal arrangement (15; 26; 43; 50) has at least one segmented ring (16, 20; 27, 31; 44; 51; 55) with a first circumferential surface (17, 21; 28, 32; 45; 52, 56) releasably attached to one of the turbine casings (10, 11) in the region of the annular gap (14), and has an opposite second circumferential surface (18, 22; 29, 33; 46; 53, 57) with the annular receiving groove (9, 23; 30, 34; 54) or, in a one-piece form, with the radially projecting annular seal element (47; 58).

Abstract: A layer system including a substrate and a layer is provided. The layer system has a hole at least in the layer, and wherein at least one recess is present in a surface of the layer in a vicinity around the hole or directly adjoining a boundary line of the hole.

Abstract: A process for producing a layer system is provided wherein the layer system has at least a substrate, a ceramic layer, which is applied to a surface structured in a targeted manner, in which process the intermediate layer, in particular the metallic layer, is applied in such a way that the recesses form during the coating. By introducing recesses into a surface, the stresses in the ceramic layer on the metallic substrate are reduced in such a manner that a longer lifespan for the ceramic layer is achieved.

Abstract: A valve for shutting off and/or controlling the throughflow of fluid flows is provided. A valve housing, having a valve seat contact surface, a valve cover with a valve cover thickness which is provided with a material allowance, and the valve body form together a first, maximum lift; and when the worn region of the valve seat contact surface is removed, the valve cover thickness can be removed such that the first, maximum lift remains the same or remains the same with only minor deviations; and/or the valve housing, valve seat contact surface, valve cover with the valve cover thickness, and the valve body is provided with a material allowance form a first, particularly maximum lift; and when the worn region of the valve seat contact surface is removed, the valve body can be removed such that the first, maximum lift remains the same or with only minor deviations.

Abstract: A turbine guide vane system, in particular for a gas turbine is provided. The turbine guide vane system includes a number of guide vane rows and a guide vane carrier, to enable particularly simple replacement of guide vanes, while maintaining a particularly high degree of efficiency, and thus designed for particularly short repair durations. For this purpose, the guide vane carrier has a number of segments, wherein a segment extends over the entire radial extension of the guide vane carrier and the connection of the remaining segments may be detached, and wherein the turbine guide vane carrier includes at least two sections along the axial extension thereof that are connected to one another and have a different number of segments.

Abstract: A seal arrangement (15; 26; 43; 50) for sealing an annular gap (14) between a high-pressure steam space (12) and an adjacent low-pressure steam space (13). The gap is defined between two turbine casings (10, 11) each split into two casing halves, the seal arrangement (15; 26; 43; 50) has a seal element (24; 47; 58) which is formed in a segmented and annular manner and extends between the two turbine casings (10, 11) and engages in an annular receiving groove (9, 23; 30, 34; 49; 54) by means of at least one of its radial end regions. The seal arrangement (15; 26; 43; 50) has at least one segmented ring (16, 20; 27, 31; 44; 51; 55) with a first circumferential surface (17, 21; 28, 32; 45; 52, 56) releasably attached to one of the turbine casings (10, 11) in the region of the annular gap (14), and has an opposite second circumferential surface (18, 22; 29, 33; 46; 53, 57) with the annular receiving groove (9, 23; 30, 34; 54) or, in a one-piece form, with the radially projecting annular seal element (47; 58).

Abstract: A valve diffuser (3) for a valve (1), wherein the valve diffuser (3) has a valve seat (8) to make contact with a valve body. The valve seat (8) has a bushing (10) for making contact with a valve body. The bushing is formed from a different reinforced material wherein the valve diffuser (3) and preferably stellite.

Abstract: A layer system including a substrate and a layer is provided. The layer system has a hole at least in the layer, and wherein at least one recess is present in a surface of the layer in a vicinity around the hole or directly adjoining a boundary line of the hole.

Abstract: A process for producing a layer system is provided wherein the layer system has at least a substrate, a ceramic layer, which is applied to a surface structured in a targeted manner, in which process the intermediate layer, in particular the metallic layer, is applied in such a way that the recesses form during the coating. By introducing recesses into a surface, the stresses in the ceramic layer on the metallic substrate are reduced in such a manner that a longer lifespan for the ceramic layer is achieved.

Abstract: A core die is provided. The core die includes a first half and a second half where a cavity is formed between the two. Pins are arranged on the halves and the pins are replaceable. By virtue of the modular inner structure of a core die, the core die may be matched to the desired changes of the core, by small changes, more quickly and more easily than would be the case if the core die had only one part or if the pins were a fixed component of the core die halves.

Abstract: A turbine guide vane system, in particular for a gas turbine is provided. The turbine guide vane system includes a number of guide vane rows and a guide vane carrier, to enable particularly simple replacement of guide vanes, while maintaining a particularly high degree of efficiency, and thus designed for particularly short repair durations. For this purpose, the guide vane carrier has a number of segments, wherein a segment extends over the entire radial extension of the guide vane carrier and the connection of the remaining segments may be detached, and wherein the turbine guide vane carrier includes at least two sections along the axial extension thereof that are connected to one another and have a different number of segments.

Abstract: The invention relates to a gas turbine, with a flow path for a hot gas, enclosed by a channel wall with at least one measuring probe, arranged in the channel wall, for determination of a parameter of the hot gas, said measuring probe comprising a temperature-resistant measuring tip in contact with the hot gas and a measuring line, arranged outside the flow path in a protective sleeve. According to the invention, such a gas turbine with a structurally uncomplicated protective sleeve for measuring lines from measuring probes, in which the measuring lines can be economically fitted and securely protected from excessively high operating temperatures, may be achieved, whereby the protective sleeve has a flow of coolant running therethrough which may be taken from a coolant supply connected to the protective sleeve.

Abstract: A lead arrangement (1), in particular a high voltage lead arrangement, for being installed in a combustor unit to connect an ignition system of the combustor unit to an external power source and to deliver an ignition voltage to the ignition system, comprises: a tube (3) having a tube wall (4) and an lumen surrounded by the tube wall, at least one lead (5) extending through the lumen of the tube, and a mineral isolator material (7) disposed between the lead and the tube wall.

Abstract: The invention relates to a method for cooling a gas turbine comprising a rotor, said method being carried out after the operation of the gas turbine and whereby the rotor is driven at least intermittently during a cooling phase at a reduced nominal speed. To provide a gas turbine with a reduced down time, a liquid is introduced at least intermittently into the air stream upstream of the compressor during the cooling phase.

Abstract: The invention relates to a gas turbine, with a flow path for a hot gas, enclosed by a channel wall with at least one measuring probe, arranged in the channel wall, for determination of a parameter of the hot gas, said measuring probe comprising a temperature-resistant measuring tip in contact with the hot gas and a measuring line, arranged outside the flow path in a protective sleeve. According to the invention, such a gas turbine with a structurally uncomplicated protective sleeve for measuring lines from measuring probes, in which the measuring lines can be economically fitted and securely protected from excessively high operating temperatures, may be achieved, whereby the protective sleeve has a flow of coolant running therethrough which may be taken from a coolant supply connected to the protective sleeve.

Abstract: The invention relates to a method for cooling a gas turbine comprising a rotor, said method being carried out after the operation of the gas turbine and whereby the rotor is driven at least intermittently during a cooling phase at a reduced nominal speed. To provide a gas turbine with a reduced down time, a liquid is introduced at least intermittently into the air stream upstream of the compressor during the cooling phase.

Abstract: The exhaust gas of a turbine engine can include water vapor. Aspects of the invention relate to various systems for recovering water from the exhaust gas of a gas turbine engine. In one system, a portion of the exhaust gas can be routed to an absorption chiller. In another system, a portion of the exhaust gas can be routed to a direct contact heat exchanger. In a third system, a portion of the exhaust gas can be routed to a fin-fan cooler. In each of these systems, the portion of gas can be cooled below its dew point temperature to release a portion of its humidity as liquid water. Aspects of the invention can be used with the turbine exhaust of simple and combined cycle power plants. A water recovery system according to aspects of the invention can minimize or eliminate a power plant's dependence on local water sources.

Abstract: The exhaust gas of a turbine engine can include water vapor. Aspects of the invention relate to various systems for recovering water from the exhaust gas of a gas turbine engine. In one system, a portion of the exhaust gas can be routed to an absorption chiller. In another system, a portion of the exhaust gas can be routed to a direct contact heat exchanger. In a third system, a portion of the exhaust gas can be routed to a fin-fan cooler. In each of these systems, the portion of gas can be cooled below its dew point temperature to release a portion of its humidity as liquid water. Aspects of the invention can be used with the turbine exhaust of simple and combined cycle power plants. A water recovery system according to aspects of the invention can minimize or eliminate a power plant's dependence on local water sources.