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 method for improving the performance of a gas turbine, in which a hub annually surrounding a rotor is machined when the rotor is in the non-stacked state and hot shield elements that are arranged on the hub are exchanged. The method includes a) dismantling of the rotor together with the surrounding hub from the gas turbine; b) horizontal mounting of the rotor in the non-destacked state; c) removing of all heat shield elements of the row which is arranged as the last row in the flow downstream direction; d) mechanical machining, in particular complete removing of the hub projection; e) machining of at least some of the existing cooling air bores and/or producing of new cooling air bores, and f) mounting of new heat shield elements, the design of which differs from that of the heat shield elements which were removed in step c).

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 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 retaining element for retaining a heat shield element on a support structure comprises at least one fixing section adapted to fix the retaining element to the support structure and at least one retaining section adapted to engage with an engaging groove present on a periphery of the heat shield element. A projection is arranged on the retaining element in such a manner that it projects in the direction of the heat shield element when retaining a heat shield element.

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: A heat shield according to the invention on a support structure comprises a number of heat shield elements, which are configured and arranged on the support structure such that they abut each other leaving gaps. The support structure of the heat shield according to the invention has a peripheral direction and an axial direction, the heat shield elements abutting each other in the peripheral direction of the support structure leaving a gap, hereafter referred to as a peripheral gap, and in the axial direction of the support structure leaving a gap, hereafter referred to as an axial gap. Both the peripheral gaps and the axial gaps are also sealed by sealing elements, the sealing elements sealing the axial gaps being at a different distance from the support structure from the sealing elements sealing the peripheral gaps.

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 retaining element for retaining a heat shield element on a support structure comprises at least one fixing section adapted to fix the retaining element to the support structure and at least one retaining section adapted to engage with an engaging groove present on a periphery of the heat shield element. A projection is arranged on the retaining element in such a manner that it projects in the direction of the heat shield element when retaining a heat shield element.

Abstract: A device (10) for the demounting of blades (12), which are pushed in with a blade root (20) on a wheel disk (14) of a blade wheel (16) of a turbine or of a compressor, is designed with a support (24) which is designed to be brought to bear against at least one component of the turbine, and is designed with an actuator (28) which is coupled to the support (24) and is designed for moving the blade root (20) mechanically out of the wheel disk (14).

Abstract: A heat shield according to the invention on a support structure comprises a number of heat shield elements, which are configured and arranged on the support structure such that they abut each other leaving gaps. The support structure of the heat shield according to the invention has a peripheral direction and an axial direction, the heat shield elements abutting each other in the peripheral direction of the support structure leaving a gap, hereafter referred to as a peripheral gap, and in the axial direction of the support structure leaving a gap, hereafter referred to as an axial gap. Both the peripheral gaps and the axial gaps are also sealed by sealing elements, the sealing elements sealing the axial gaps being at a different distance from the support structure from the sealing elements sealing the peripheral gaps.

Abstract: A device (10) for the demounting of blades (12), which are pushed in with a blade root (20) on a wheel disk (14) of a blade wheel (16) of a turbine or of a compressor, is designed with a supporting means (24) which is designed to be brought to bear against at least one component of the turbine, and is designed with an actuator means (28) which is coupled to the supporting means (24) and is designed for moving the blade root (20) mechanically out of the wheel disk (14).