Alstom Technology Limited

Ansaldo Energia Switzerland Ag

General Electric Technology Gmbh

Alstom (switzerland) Ltd

Ansaldo Energia IP UK Limited

Wilhelm Reiter

Hans Wettstein

Jürgen Gerhard Hoffmann

Stefan Rofka

Jost Imfeld

Giovanni Cataldi

Thomas Zierer

Maurus Herzog

Sven Olmes

Sigurd Kubel

Thomas Peter Sommer

Darrel Shayne Lilley

Michael Hoevel

Marcos Escudero-Olano

Manuel Arias Chao

A gas turbine with a sequential combustor arrangement as disclosed includes a first combustor with a first burner for admitting a first fuel into a combustor inlet gas during operation and a first combustion chamber for burning the first fuel, a dilution gas admixer for admixing a dilution gas to the first combustor combustion products leaving the first combustion chamber, a second burner for admixing a second fuel and a second combustion chamber. To assure a temperature profile after the dilution gas admixer and to increase the gas turbine's power and efficiency a vane and/or blade of the turbine has a closed loop cooling. The outlet of the closed loop cooling is connected to the dilution gas admixer for admixing the heated cooling gas leaving the vane and/or blade into the first combustor combustion products.

Sequential combustion arrangement with cooling gas for dilution

A sealing arrangement is provided at the interface between a combustor and a turbine of a gas turbine. The turbine includes guiding vanes at its inlet. The guiding vanes are each mounted within the turbine at their outer diameter by means of rear outer diameter vane hook and are each at their inner diameter in sealing engagement by means of a front inner diameter vane tooth with a honeycomb seal arranged at the corresponding inner diameter part of the outlet of said combustor. The rear outer diameter vane hook allows a relative movement of the guiding vane in form of a rotation around the rear outer diameter vane hook. The sealing adapts the front inner diameter vane tooth and the corresponding honeycomb seal in their configuration to the rotating relative movement of the guiding vane, such that the compression of said honeycomb seal through transients of the gas turbine is reduced.

Sealing arrangement at the interface between a combustor and a turbine of a gas turbine and gas turbine with such a sealing arrangement

The invention relates to an axial flow turbine and method of operating thereof. The turbine comprises a last stage of rotating blades located towards a downstream end of the turbine having a distal region at an end of the airfoil of the blades. A monitoring control system has at least one sensor in the distal region of at least one last stage blade for measuring at least one physical property of the airfoil and a control element that is capable of influencing at least one physical property of the distal region. The control system further includes a controller that adjusts the control element based on at least measured physical property so by controlling the at least one physical property.

Control system for an axial flow turbine

A single shaft steam turbine plant is disclosed with a first and a second low pressure steam turbine located at either end of the shaft. A generator and at least one high-pressure steam turbine are located on the shaft between low pressure steam turbines.

Steam turbine plant

A gas turbine includes a compressor for compressing the combustion air, at least one combustion chamber, in which a fuel is burned while compressed combustion air is supplied, and at least one first turbine arranged downstream of the combustion chamber and in which the hot combustion gases from the combustion chamber are expanded to perform work. Part of the compressed combustion air is branched off, cooled in a cooling air cooler, brought to a lower cooling air pressure by a second turbine and supplied to the gas turbine for cooling purposes.

Gas turbine with heat exchanger for cooling compressed air and preheating a fuel

A gas turbine system comprises a compressor that takes in suction air on the inlet side and compresses it to compressor end air that is available on the outlet side, a combustor in which a fuel is burned by using the compressor end air while resulting in the formation of hot gas, as well as a turbine in which the hot gas is expanded while providing work output. In a method for cooling this gas turbine system, compressed air is removed from the compressor, is fed as cooling air for cooling inside an internal cooling channel through thermally loaded components of the combustor and/or the turbine, is then compressed and added to the compressor end air. An improved cooling without disadvantage for the efficiency of the system is achieved in that, in the manner of a targeted leakage, a small part of the cooling air is fed for film cooling into the turbine stream through drilled film cooling openings provided on the components.

Method for cooling a gas turbine system and a gas turbine system for performing this method

A gas turbine system comprises a compressor that takes in suction air on the inlet side and compresses it to compressor end air that is available on the outlet side, a combustor in which a fuel is burned by using the compressor end air while resulting in the formation of hot gas, as well as a turbine in which the hot gas is expanded while providing work output. In a method for cooling this gas turbine system, compressed air is removed from the compressor, is fed as cooling air for cooling inside an internal cooling channel through thermally loaded components of the combustor and/or the turbine, is then recooled and subsequently compressed and added to the compressor end air. The influence of the cooling on the efficiency of the system is minimized by the fact that at least part of the compressor end air is used to recool the cooling air.

Growing community of inventors

Küssaberg, Germany

Wilhelm Reiter