Ansaldo Energia Switzerland Ag

Alstom Technology Limited

General Electric Technology Gmbh

Ansaldo Energia IP UK Limited

General Electric Company

Giovanni Cataldi

Franz Joos

Carlos Simon-Delgado

Stefan Rofka

Meisam Sistaninia

Felix Guethe

Jonas Hurter

Sven Olmes

Joerg Oesterheld

Wilhelm Reiter

Gijsbertus Oomens

Manfred Wirsum

Andreas Rueter

Charles Matz

Thomas Peter Sommer

Martin Schaefer

Christopher Michael Robson

Gaurav Pathak

Guenter Filkorn

Mauro Corradi

Oliver Joseph Taheny

Luca Alberti

Robert Przybyl

Marco Christof Pawlowski

Gordon McColvin

Janos Farkas

Jean Laragne

Matteo Rocchi

Christophe Simonet

Diego Ugel

Tobias Herzog

Christian Faehndrich

Pancrazio Abate

Nikolas Wiedemann

Johannes Richter

David Nicolai Kaufmann

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.

Belly band seals

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.

Floating support assembly for compensating for axial thermal expansion

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&#xd7;10/&#xb0; C. for about 100-400&#xb0; C. and increasing from about 400-500&#xb0; C. to up to about 10&#xd7;10/&#xb0; C., or up to about 6&#xd7;10/&#xb0; C. between about 100-300&#xb0; C. and increasing from about 300-500&#xb0; C. to up to about 10&#xd7;10/&#xb0; 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 mm, 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.

Nickel-iron-cobalt based alloys and articles and methods for forming articles including nickel-iron-cobalt based alloys

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.

Gas turbine rotor cover

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.

Gas turbine cool-down phase operation methods for controlling turbine clearance by adjusting air flow rate

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.

Turbo machine and method for operating such turbo machine

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.

System for compensating rotor vibrations

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&#xd7;10[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.

Vane carrier for a compressor or a turbine section of an axial turbo machine

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.

Operation of a gas turbine

In a method of operating a compressor of a gas turbine, where compressor air sucked in from the environment is cooled down by evaporation cooling before entering the compressor, before starting operation of the compressor, maximum possible temperature drops which could be achieved by evaporation cooling are determined dependent on different ambient conditions and/or are provided as a data set. These temperature drops are correlated with a compressor map containing maximum temperature distortions at different ambient conditions and different rotation frequencies of the compressor which have to be met in order to avoid pumping. The evaporation cooling is then only operated when current ambient condition result in a maximum possible temperature drop from which a predetermined fraction of between 50% and 100% does not exceed the maximum distortion which can be taken from the compressor map for these ambient conditions and the current rotation frequency of the compressor. Safe operation of the compressor can be achieved without the need or monitoring temperature distortions in the sucked in air stream.

Method for the operation of a compressor of a gas turbine with evaporative cooling of the compressor induction air

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Zurich, Switzerland

Giovanni Cataldi