Alstom Technology Limited

Slawomir Slowik

Andreas Boegli

James Ritchie

Christian Steinbach

Thomas R Ruck

Alexander Mahler

Martin Andrea Von Planta

Heinrich Stuessi

A premixing burner has a swirl generator with at least two burner shells () which jointly enclose an axia conically widening swirl space and delimit tangential air inlet slits () through which combustion supply air passes into the swirl space in which an axially propagating swirl flow is formed, and with fuel injection devices at least partially along the tangentially running air inlet slits (). The fuel injection devices include a fuel line () separate from the burner shell () and which is firmly attached to the burner shell () so as to be longitudinally movable with respect to the burner shell () and releasable perpendicularly to the surface of the burner shell (). In the burner shell (), orifices () are provided, into which issue fuel injectors () which are provided along the fuel line () and which project beyond the circumferential edge of the fuel line ().

Premixing burner for generating an ignitable fuel/air mixture

A turbomachine blade is disclosed having a shroud element, wherein plastic deformations and lifting of the shroud element on one side result during operation under centrifugal load. This load may result in high-temperature creep of the blade. A sealing strip which is arranged on the shroud element can be configured with a thickness varying in a circumferential direction. The mass of the shroud element and thus the asymmetrical centrifugal load and the lifting of the shroud element on one side resulting therefrom can be reduced by material removal at regions lying on the outside in the circumferential direction.

Turbomachine blade

A method of reconditioning a rotating blade () with a shroud () following the operation in a gas turbine, includes the application of a barrier () placed on the edge of the shroud () facing the edge of a shroud () of an adjacent blade having creep deformation. The barrier () prevents hot gas ingestion into a shroud cavity (). It is pre-fabricated or built-up layer-by-layer by welding or laser cladding or other methods. Additionally, the mass of the shroud () is reduced in order to re-establish the initial mass of the shroud. A thermal barrier coating () is additionally applied to the surfaces of the shroud () that are exposed to the hot gas of the turbine. The method significantly increases the lifetime of the blade ().

Method of reconditioning a turbine blade

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Stetten, Switzerland

Slawomir Slowik