Alstom Technology Limited

General Electric Technology Gmbh

Ansaldo Energia Switzerland Ag

Jonas Hurter

Ian William Boston

Rolf Dittmann

Robert Marmilic

Ernst Pauli

Alexander Zagorskiy

Pierre Meylan

Markus Stemann

Urs Benz

Matthias Hoebel

Franz Joos

Kenneth W Cornett

Felix Guethe

Ulrich Robert Steiger

Giovanni Cataldi

Dominick Greg More

Gijsbertus Oomens

Manfred Wirsum

Sergey Vladimirovich Trifonov

Peter Graham Amos

Thorsten Christoph Motzkus

Valter Bellucci

Joerg Pross

Thomas Kueenzi

Hans-Martin Hocke

Nicolas Campino Johnson

Christoph Niederberger

Stefan Gross

Nicolas Johnson Campino

Kennet W Cornett

Dominick Gregory More

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 gas turbine, a plurality of burners, which are arranged concentrically to the rotational axis in a regular arrangement, each directing hot gas through an associated combustion chamber outlet into a turbine, at the inlet of which a second plurality of stator blades are arranged in a ring, uniformly spaced apart around the rotational axis. Cooling openings are provided, which are distributed over the circumference, through which cooling air is injected into the hot gas flow at the combustion chamber outlet. An improvement of the flow conditions in the hot gas is achieved by the cooling openings being divided into first cooling opening groups and second cooling opening groups. The arrangement of the first cooling opening groups corresponds to the arrangement of the stator blades, and in that the arrangement of the second cooling opening groups corresponds to the regular arrangement of the burners.

Turbine stator nozzle cooling structure

A turbomachine with at least one combustion chamber and at least one turbine which lies downstream of it. The turbine has at least one support element and a lining element connected to the support element and formed as a heat shield. A gap sealed by means of a seal, is formed between the at least one combustion chamber and the turbine, an exchangeable insert is arranged in the gap on the end face on the support element and protects at least the support element against hot gases which penetrate into the gap, and against oxidation which is associated with it.

Turbomachine, especially gas turbine

A seal () includes a first component () and second component (), the first component including a first material having a high thermal and oxidation and wear resistance, and the second component () including a second material that is different from the first material and has a high spring load maintenance. The seal () is applied to a combustion chamber for a gas turbine, where the first component () extends between the casing wall of the combustion chamber and adjacent liner segments (). The spring load of the second component () provides a seal also in the case of vibrations in a combustion chamber. The lifetime of the seal () is increased due to the individual materials, which are optimally chosen for the functions of high thermal and wear resistance and spring load maintenance respectively. The seal is further applied to the sealing between adjacent stationary blade platforms in gas turbines.

High temperature seal and methods of use

A sealing element for sealing a component gap with respect to a flow, in particular for use in a fluid-flow machine, specifically in a turbomachine is provided. In addition a fluid-flow machine is provided including such a sealing element for sealing a component gap. The sealing element includes a hollow profile enclosing a cavity. Arranged in the hollow profile are a first opening and a second opening, which are spaced apart from each other in the longitudinal direction of the hollow profile. The first opening is formed as an inlet opening for a cooling fluid into the cavity of the hollow profile, the second opening is formed as an outlet opening for the cooling fluid from the cavity of the hollow profile. With the sealing element arranged in a fluid-flow machine, the sealing element can consequently be internally cooled by means of the cooling fluid. Furthermore, the sealing element uses the pressure gradient occurring in the flow in the direction of flow to form a stable cooling fluid flow.

Sealing element for use in a fluid-flow machine

A combustion chamber for an industrial gas turbine has thermal protective elements which are installed along the inner circumference of its casing. The thermal protective elements are cooled by cooling air which is added to the fuel in the region in front of a front casing section after the cooling. A brush seal is installed between the front casing section and the thermal protective elements, where the brush seal is configured in segments. The combustion chamber can be sealed against leakages of cooling air in all operating states of the combustion chamber.

Combustion chamber for a gas turbine

The present invention relates to a sealing body for sealing an outer component with respect to an inner component, in particular for a combustion chamber of a gas turbine. The outer component has a passage opening, through which the inner component projects out of the outer component. In the installed state, the sealing body is arranged in the region of the passage opening, surrounds the inner component in a circumferentially continuous manner, bears in a circumferentially continuous manner, by means of an inner sealing zone, against an outer sealing surface of the inner component and bears in a circumferentially continuous manner, by means of an outer sealing zone, against an inner sealing surface of the outer component. The sealing body is produced by deformation from at least one metal sheet that is in strip form and is circumferentially continuous. The inner sealing zone and the outer sealing zone are formed at a profiled section of the sealing body along the entire circumference.

Profiled sealing body with spring section

A thermal turbomachine is disclosed having at least one row of rotor blades. At least one first rotor blade has a greater radial length than the others and at the blade tip is equipped with a first abrasive layer. At least one rotor blade which has a shorter radial length than the first rotor blade is equipped with a second abrasive layer at the blade tip. The first abrasive layer has a better cutting capacity and a lower thermal stability than the second abrasive layer. During commissioning of the thermal turbomachine, the first abrasive layer is in contact with the abradable layer of the stator, and during continuous operation of the thermal turbomachine the second abrasive layer is in contact with the abradable layer of the stator.

Thermal turbomachine

Suitable means for driving a flow are arranged in annular or ring-segment-shaped cavities that are formed in particular in multi-shell casings of turbomachines. Arranged inside the cavity are ejectors that are supplied via suitable means with a motive-fluid flow which in turn excites the flow, preferably a circumferential flow or a helical flow. The invention is suitable in particular for avoiding casing distortions when turbomachines are at rest.

Turbomachine

Combustion driven pressure pulsations may limit the range of operating conditions where a modern gas turbine can operate with low emission and high efficiency performance. The control of acoustic vibrations has been consequently growing as an essential issue in gas turbine design, development and maintenance. The basic idea of the present invention is to use cooling air leakage through the gaps () of combustor liner segments () to get acoustic damping of combustion pulsations. The main component of the design is the sealing device () which covers the gap () between the two liner segments () and (). The sealing device () collects in the plenum () some of the cooling air () flowing between the outer casing () and the inner liner structure (). For this purpose the sealing device () is provided with openings () along the side walls () which allow the cooling air () to enter the plenum (). In the plenum () the cooling air () is distributed along the gap () and discharged through openings (), distributed along the top side () of the sealing device (). The jets () discharged through the openings () achieve the additional effect to dampen acoustic pulsations in the combustion chamber ().

Device for efficient usage of cooling air for acoustic damping of combustion chamber pulsations

In order to avoid the 'buckling' of multi-shell turbomachine casings during a cooling phase following the shutdown, it is proposed to provide means in order to suitably discharge warm medium which collects at a point of the casing cavity situated at the highest geodetic level. In an embodiment, it is proposed to allow the corresponding lines to open out in the stack of a power plant; the stack draft effect assists the flow even further. Regulating members are advantageously provided in the lines in order to shut off these lines during operation of the turbomachine on the one hand and in order not to arrange the flow through the casing cavities too intensively on the other hand.

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Baden, Switzerland

Jonas Hurter