Alstom Technology Limited

General Electric Technology Gmbh

Asea Brown Boveri Inc.

Ansaldo Energia IP UK Limited

Helmar Wunderle

Peter Graf

Stefan Tschirren

Beat Von Arx

Pierre Meylan

Marc Rauch

Stefan Schlechtriem

Hans Schwarz

Silvio Glaser

Peter Baldischweiler

Ai Ling Chin

A method is described for improving the sealing between rotor and a plurality of blades. The rotor has a plurality of generally axially extending profiled recesses into which a ring of blades, which have corresponding blade root profiles, are inserted in a form-fitting and/or frictionally locking manner into these recesses in a generally axial insertion direction. Between the recesses the rotor has tangential surface sections or circumferential surface sections which extend in the axial direction and circumferential direction and are generally indirectly covered by lower shrouds of circumferentially adjacently arranged blades in the radial direction. At least one of the tangential surface or circumferential surface sections is provided with a step in the radial direction, and a corresponding recess, which adjoins as flush as possible, is provided in the underside of the shroud of the blade which is arranged above it. Corresponding rotors or blades are also described.

Method for improving the sealing on rotor arrangements

The invention relates to an annular combustor () for a gas turbine (), into which combustor () burners () open on an inlet side, and which combustor () extends in the axial direction from the inlet side to an outlet side () and is lined on the insides with cooled liner segments () for protection from the hot gases. In such a combustor, increased mechanical stability and flexibility in design and also simplification in manufacture and fitting are achieved by the liner segments () being subdivided in the axial direction into a plurality of parts () arranged one behind the other.

Annular combustor for a gas turbine

At least one Helmholtz damper is arranged at a combustion chamber for a gas turbine in order to damp thermoacoustic oscillations; the damping volume of this Helmholtz damper is in communication with the combustion chamber via a connecting passage. Optimum damping is achieved in a simple way by virtue of the Helmholtz damper being designed in such a manner that its damping frequency is adjustable.

Combustion chamber for a gas turbine

In a burner arrangement for the annular combustion chamber of a gas turbine, a plurality of burners are arranged above one another, in each case in pairs in the radial direction, on concentric rings. In a burner arrangement of this type, the mechanical integrity of the turbine casing is increased and operation of the combustion chamber is optimized by virtue of the two burners in a pair of burners being oriented out of the parallel position, in such a manner that their burner axes converge in the direction of flow.

Burner arrangement for the annular combustion chamber of a gas turbine

In a gas turbine combustion chamber with an annular flame tube, the latter is essentially composed of wall pieces (18) which overlap in the circumferential direction. The wall pieces (18) are elements, curved in the turbine axial direction, the cooling air being directed in a circumferential direction along the external sides thereof facing towards the collector volume (6). The cooling air flowing out of the overlap gaps (22) is deflected in a cascade (29) before entry into the combustion volume (15).

Gas turbine combustion chamber with improved air flow

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Waldshut-Tiengen, Germany

Helmar Wunderle