Alstom Technology Limited

Ansaldo Energia IP UK Limited

General Electric Technology Gmbh

Ansaldo Energia Switzerland Ag

Ulrich Robert Steiger

Ulrich Rathmann

Willy Heinz Hofmann

Carlos Simon-Delgado

Peter Marx

Thomas Heinz-Schwarzmaier

Axel Heidecke

Robert Marmilic

Jonas Hurter

Thomas Zierer

Sven Olmes

Anton Nemet

Sascha Justl

Roland Dueckershoff

Cyrille Bricaud

Karsten Franitza

Darrel Shayne Lilley

Christian Sommer

Ralf Jakoby

Manuel Arias Chao

Frank Gersbach

René Waelchli

Adrien Franz Studerus

Roland DÜCKERSHOFF

A labyrinth seal is provided for sealing the annular interspace between the rotor and the stator of a steam turbine or gas turbine. The labyrinth seal includes a multiplicity of sealing strips which are arranged in series in the axial direction and fastened on the stator and project into the interspace. The sealing strips interact, with sealing effect, with rotor-side sealing elements which are arranged in a staggered manner. An improved sealing effect is achieved by the sealing strips in the cold installed state being offset in relation to a symmetrical position, wherein the offset has the reverse direction and the same amount as the distance by which the sealing strip is displaced relative to adjacent rotor-side sealing elements as a result of thermal expansions of the stationary and rotating components and support structure when being heated from the cold installed state to a hot steady-state operating condition.

Labyrinth seal

A strip seal and method of configuration thereof for sealing portions of components of a gas turbine exposed to pressure pulsations. The strip seal has a sealing face that is configured to follow the contours of first portions of the components. The strip seal further has a pressure face that has a sinusoidal curvilinear shape with respect to the sealing face. The pressure face is configured to prevent localized movement of strip seal by configuring pressure face on its first side to contact sealing face at a plurality of points, on its second side to contact second portions of the components at a plurality of points.

Strip seal and method for designing a strip seal

A gas turbine arrangement and a method of operating are provided. The turbine includes an annulus, axially delimited between a rotor unit, and at least one stationary component. Cooling medium outlet openings, lead into the annulus, from the stationary component. The cooling medium flows into cooling medium inlet openings, in the rotor unit in a flow direction, which propagates through the annulus. At least one inner cavity, radially to the annulus, is delimited by the rotor unit and by the stationary component. The inner cavity is pressurized with a purging gas, and is fluidically connected to the annulus. The stationary component and the rotor unit include a constriction by which the inner cavity is separated from the radially outer annulus and via which the inner cavity is fluidically connected to the radially outer annulus. Flow guides, fastened on the stationary component on one side, project into the constriction.

Gas turbine arrangement and method for operating a gas turbine arrangement

A gas turbine () includes a combustion chamber () followed by a stator airfoil row () defining a plurality of guide vanes and separated by the combustion chamber () by a first gap (), and a rotor airfoil row () separated by the stator airfoil row () by a second gap (). The stator airfoils () of the stator airfoil row () are connected to guide vane boxes () collecting a cooling fluid (A) and injecting it through nozzles () in the second gap () to make it to enter rotor airfoil inlets (). The guide vane boxes () are provided with passages () connecting a zone () upstream of the guide vane boxes () to a zone () of the second gap () downstream of the guide vane boxes (). Moreover, the mouths () of the passages () facing the rotor airfoil row () are closer to a hot gases path than the nozzles ().

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 gas turbine is disclosed which includes an annular combustion chamber defined by an inner wall and an outer wall. A stator airfoil row can be defined by an annular inner stator wall and an annular outer stator wall housing a plurality of stator airfoils, and at least a rotor airfoil row defined by an annular inner rotor wall and an annular outer rotor wall housing a plurality of rotor airfoils. A gap is arranged, for example, between at least one of the inner stator wall and the inner combustion chamber wall, and the outer stator wall and the outer combustion chamber wall, upstream of said stator airfoil row. A border of at least one of the inner and outer stator wall facing the gap can be axisymmetric. A zone of at least one of the inner and outer stator wall downstream of the gap and upstream of the stator airfoils can be non-axisymmetric and defines bumps arranged to locally increase the static pressure of a fluid flow passing through said stator airfoil row to increase the uniformity of the static pressure.

Gas turbine stator/rotor expansion stage having bumps arranged to locally increase static pressure

A strip seal and method of configuration thereof for sealing two adjacent non-rotating gas turbine hot gas components exposed to pressure pulsations. The strip seal has at least two clamping projections distributed along discrete points of the strip seal length that extend out from a pressure face of the strip seal. The location of the projections are defined by two ratios. The first ratio, of less than 25, is the strip seal length extending free of clamping projections from any one of the ends of the strip seal to a clamping projection to the ratio of strip seal thickness. The second ratio, of less than 200, is the ratio of the strip seal length extending free of clamping projections between any two projections to the thickness of the strip seal. This seal arrangement ameliorates detrimental effects of induced resonance.

A gas turbine with a stator blade is disclosed. The stator blade is fastened on a blade carrier and includes a blade airfoil which extends inwards in the radial direction from an outer platform into a hot gas passage. A cooling medium can flow through an interior of the blade airfoil, such as cooling air, which flows through an access in the blade carrier into a first plenum which is arranged above the outer platform, and from there, via an inlet which is provided in the outer platform, flows into the interior of the blade airfoil.

Gas turbine with a stator blade

A turbomachine (), in particular a gas turbine, has a stator () and a rotor () and with at least one axial sealing device () arranged between them. On the stator side, the sealing device () has a radially stepped sealing contour () with regions () projecting and retracting in the direction of the rotor (), on the rotor side a plurality of sealing fins () projecting in the direction of the stator () being arranged, which engage in each case into adjacent retracting regions () of the stator-side sealing contour (). On the rotor side, at least one additional fin () projecting in the direction of the stator () is provided, which is positioned between two adjacent sealing fins () arranged on the rotor side and which lies opposite a projecting region of the stator-side sealing contour ().

Turbo machine

A gas turbine system includes a combustion chamber (), a turbine (), a radially inward and/or radially outward axial gap () between the combustion chamber () and the turbine (), at which gap inner and/or outer combustion chamber walls () and inner and/or outer turbine walls () end, and a cooling gas supply (), which via the gap () introduces a cooling gas into the turbine gas path () and/or into the combustion chamber gas path (). An end section () of the respective turbine wall () and/or of the respective chamber wall () adjoining the gap () is radially inwardly and/or radially outwardly, alternatingly formed.

Growing community of inventors

Baden-Dättwil, Switzerland

Ulrich Robert Steiger