Alstom Technology Limited

Thorsten Christoph Motzkus

Urs Benz

Ulrich Rathmann

Jonas Hurter

Daniel Burri

A lance of a gas turbine burner includes an inner duct having inner nozzles; an annular outer duct encircling the inner duct and having outer nozzles; and a spacer disposed between a terminal portion of the inner duct and a terminal portion of the outer duct, the spacer being fixed to both the inner duct and the outer duct.

Lance of a gas turbine burner

A seal for stemming leakage flows between adjacent components, especially of a gas turbine, has an elastically deformable, thin-walled sealing element and a thin-walled cover element which is U-shaped in cross section and between its legs and its base partially accommodates the sealing element. The legs of the cover element are arranged in the sealing arrangement, which features the seal, between two oppositely disposed walls of the other component in a movable manner relative to these walls which, together with the sealing surface of the other component, form a groove which is U-shaped in cross section. Forces, which act laterally upon the seal, are absorbed by the cover element and via the legs are diverted into the other component so that the integrity of the seal is maintained even in the case of lateral forces.

Seal and seal arrangement for confining leakage flows between adjacent components of turbo-machines and gas turbines

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 device for fastening a second burner (SEV burner) () in a sequentially operated gas turbine arrangement, in which a fuel/air mixture is burnt in a first burner, so as to form hot gases which can subsequently be supplied, partly expanded, for a second combustion to the SEV burner (), in which the burner is designed essentially as a flow duct, with a flow duct wall, which has an orifice (), through which a fuel supply () can be introduced into the interior of the SEV burner (), and on which are provided in the axial direction of the orifice (), in each case opposite one another, two fastening structures (), into which in each case a carrying structure for the further fastening of the SEV burner () to an external carrier () can be introduced. The carrying structure includes a unitary carrier plate () on which countercontours for fastening to the two fastening structures () lying opposite the orifice () are provided and which provides a recess which corresponds at least to the size of the orifice () in the flow duct wall, so that, in the state fastened to the external carrier (), the carrier plate () does not cover the orifice () of the flow duct wall.

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Wettingen, Switzerland

Thorsten Christoph Motzkus