Abstract: The present application provides a rotor for use in a turbine engine. The rotor may include a first rotor disc, a second rotor disc adjacent to the first rotor disc, and a belly band seal positioned between the first rotor disc and the second rotor disc. The belly band seal may include a band seal with a locking tab brazed thereon.

Abstract: An assembly of at least two members. One of the members supports the other member, the assembly defining an axial direction, a radial direction, and a circumferential direction, an inner member of the at least two members being received radially inside an outer member of the at least two members, wherein the inner member and the outer member am attached to each other by a support arrangement, the support arrangement including at least one floating support assembly as a displaceable coupling between an inner member support point provided at the inner member and an outer member support point provided at the outer member. A displacement of support points in a radial direction results in an interrelated relative displacement of the support points in an axial direction end vice versa.

Abstract: Nickel-iron-cobalt based alloys are disclosed having sufficient castability for centrifugal casting essentially free from casting defects, cracking, and microstructure variability, and coefficients of thermal expansion up to about 9×10?6/° C. for about 100-400° C. and increasing from about 400-500° C. to up to about 10×10?6/° C., or up to about 6×10?6/° C. between about 100-300° C. and increasing from about 300-500° C. to up to about 10×10?6/° C. Articles are disclosed including unitary cast structures free of internal welds, brazing, and bolting, essentially annular conformations, diameters of at least about 500 mm, cross-sectional wall areas of at least about 2,000 mm2, and compositions including nickel-iron-cobalt based alloys. Methods for forming the articles are disclosed including rotating centrifugal molds with the compositions in molten states, forming the articles in near net shape.

Abstract: A gas turbine rotor cover includes a body, the body having an inner side facing towards a central axis and an outer side facing away from the central axis, wherein the gas turbine rotor cover is configured and arranged to extend in an axial direction and a circumferential direction relative to the central axis. An inner layer of insulation is attached to the inner side of the body and extends along at least part of the length of the body in the axial direction and/or an outer layer of insulation is attached to the outer side of the body, and extends along at least part of the length of the body in the axial direction. A gas turbine containing the gas turbine rotor cover is also disclosed.

Abstract: The application describes a method of operating a gas turbine during a cool-down phase. The gas turbine provides a compressor, a combustor downstream of the compressor, and a turbine downstream of the combustor, with the turbine providing a turbine vane carrier. The method includes feeding a flow of cooling air from the compressor to the turbine vane carrier, measuring a temperature of the flow of cooling air and measuring a temperature of the turbine vane carrier. In the method, the flow of cooling air is fed at a first flow rate when the temperature of the turbine vane carrier is lower than the temperature of the cooling air, and the flow of cooling air is fed at a second flow rate when the temperature of the turbine vane carrier is higher than the temperature of the cooling air, wherein the first flow rate is higher than the second flow rate.

Abstract: Nickel-iron-cobalt based alloys are disclosed having sufficient castability for centrifugal casting essentially free from casting defects, cracking, and microstructure variability, and coefficients of thermal expansion up to about 9×10?6/° C. for about 100-400° C. and increasing from about 400-500° C. to up to about 10×10?6/° C., or up to about 6×10?6/° C. between about 100-300° C. and increasing from about 300-500° C. to up to about 10×10?6/° C. Articles are disclosed including unitary cast structures free of internal welds, brazing, and bolting, essentially annular conformations, diameters of at least about 500 mm, cross-sectional wall areas of at least about 2,000 mm2, and compositions including nickel-iron-cobalt based alloys. Methods for forming the articles are disclosed including rotating centrifugal molds with the compositions in molten states, forming the articles in near net shape.

Abstract: The present application provides a rotor for use in a turbine engine. The rotor may include a first rotor disc, a second rotor disc adjacent to the first rotor disc, and a belly band seal positioned between the first rotor disc and the second rotor disc. The belly band seal may include a band seal with a locking tab brazed thereon.

Abstract: A turbo machine, such as a gas turbine, includes a rotor, which rotates about a horizontal machine axis, and which is enclosed by a coaxial enclosure. The turbo machine includes a metal casing, whereby an electrical heating system is provided on the lower half of the metal casing. A safe operation is achieved by having the heating system configured as a redundant system.

Abstract: The present disclosure relates to a system to compensate for mechanical forces on a rotating rotor of an electric machine, to a method for compensating mechanical forces on a rotating rotor of an electric machine, and to a use of a corresponding system. Disclosed is a system for compensating torsions at a rotating rotor. The system includes at least one measuring device for measuring specific properties of the rotor, an analyzer unit for analyzing the measurement data of the measuring device, a compensation means for compensating the torsions at the rotor, the compensation means comprise a power supply unit generating a signal adapted in amplitude and frequency to the measured properties of the rotor, and to apply the generated signal to the rotor, and the power supply unit is a frequency converter.

Abstract: A gas turbine includes a compressor section and a turbine section extending along an axis; an outer casing and an inner casing, delimiting an annular cavity between one another in the turbine section; a cooling circuit, configured to direct cooling fluid flow from the compressor section to the annular cavity of the turbine section through cooling inlets in the outer casing; and baffles arranged in the annular cavity between respective cooling inlets and the inner casing and configured to intercept at least part of the cooling fluid flow when fed through the respective cooling inlets and to prevent intercepted cooling fluid flow from directly impinging on the inner casing.

Abstract: A vane carrier is provided for a compressor or a turbine section of an axial turbo machine, especially one of a gas turbine, steam turbine, compressor, expander, comprises least a first and second functional means. The first functional means is a cylinder made of a material with a coefficient of thermal expansion (CTE) below 1.3×10?5 [1/K]. The cylinder is provided for carrying a plurality of vanes on its inner side. The second functional means is a support structure made of a material different to and less expensive than the material of said first functional means. The support structure is provided for defining an axial and lateral position of the first functional means within an outer casing of the axial turbo machine.

Abstract: An assembly of at least two members. One of the members supports the other member, the assembly defining an axial direction, a radial direction, and a circumferential direction, an inner member of the at least two members being received radially inside an outer member of the at least two members, wherein the inner member and the outer member am attached to each other by a support arrangement, the support arrangement including at least one floating support assembly as a displaceable coupling between an inner member support point provided at the inner member and an outer member support point provided at the outer member. A displacement of support points in a radial direction results in an interrelated relative displacement of the support points in an axial direction end vice versa.

Abstract: A gas turbine rotor cover includes a body, the body having an inner side facing towards a central axis and an outer side facing away from the central axis, wherein the gas turbine rotor cover is configured and arranged to extend in an axial direction and a circumferential direction relative to the central axis. An inner layer of insulation is attached to the inner side of the body and extends along at least part of the length of the body in the axial direction and/or an outer layer of insulation is attached to the outer side of the body, and extends along at least part of the length of the body in the axial direction. A gas turbine containing the gas turbine rotor cover is also disclosed.

Abstract: The application describes a method of operating a gas turbine during a cool-down phase. The gas turbine provides a compressor, a combustor downstream of the compressor, and a turbine downstream of the combustor, with the turbine providing a turbine vane carrier. The method includes feeding a flow of cooling air from the compressor to the turbine vane carrier, measuring a temperature of the flow of cooling air and measuring a temperature of the turbine vane carrier. In the method, the flow of cooling air is fed at a first flow rate when the temperature of the turbine vane carrier is lower than the temperature of the cooling air, and the flow of cooling air is fed at a second flow rate when the temperature of the turbine vane carrier is higher than the temperature of the cooling air, wherein the first flow rate is higher than the second flow rate.

Abstract: An engine casing element comprises at least one clearance control cavity, the clearance control cavity being delimited by a clearance control cavity inner wall and having a clearance control cavity longitudinal extent. At least one insert member is arranged inside the clearance control cavity. The insert member is arranged and configured to effect at least one of a flow guide function and a heat transfer enhancement function.

Abstract: A turbo machine, especially gas turbine, comprises a rotor, which rotates about a horizontal machine axis, and which is enclosed by a coaxial enclosure comprising a metal casing, whereby an electrical heating system is provided on the lower half of said metal casing. A safe operation is achieved by having said heating system configured as a redundant system.

Abstract: The present disclosure relates to a system to compensate for mechanical forces on a rotating rotor of an electric machine, to a method for compensating mechanical forces on a rotating rotor of an electric machine, and to a use of a corresponding system. Disclosed is a system for compensating torsions at a rotating rotor. The system includes at least one measuring device for measuring specific properties of the rotor, an analyser unit for analysing the measurement data of the measuring device, a compensation means for compensating the torsions at the rotor, the compensation means comprise a power supply unit generating a signal adapted in amplitude and frequency to the measured properties of the rotor, and to apply the generated signal to the rotor, and the power supply unit is a frequency converter.

Abstract: Provided is a control method for a gas turbine plant having a first and a second combustors in series, such that combustion gases produced in the first combustor flows into the second combustor. The second combustor having a fuel lance with internal partitions, for injecting at least one fuel and a gas having a mixture of inert gas and support air into the second combustor. The partitions enable the gas to carry, and/or veil, at least one of the fuels as the fuel exits the lance. A variable of the second combustor is measured and the inert gas to support air mixture varies in response to variations of the variable so as to at least partially compensate for the operational effects of the variable on the operation of the second combustor.

Abstract: A vane carrier is provided for a compressor or a turbine section of an axial turbo machine, especially one of a gas turbine, steam turbine, compressor, expander, comprises least a first and second functional means. The first functional means is a cylinder made of a material with a coefficient of thermal expansion (CTE) below 1.3×10?5 [1/K]. The cylinder is provided for carrying a plurality of vanes on its inner side. The second functional means is a support structure made of a material different to and less expensive than the material of said first functional means. The support structure is provided for defining an axial and lateral position of the first functional means within an outer casing of the axial turbo machine.

Abstract: The disclosure relates to a turbo-machine comprising a stator and a rotor arranged rotatable inside the stator as well as at least one electric heating device which is arranged on the surface of at least part of the stator for active clearance control. Besides the turbo-machine, a method for operating the active clearance control comprising electric heating devices is disclosed.