Alstom Technology Limited

Martin Andrea Von Planta

Christian Steinbach

Thomas R Ruck

Fulvio Magni

Weiqun Geng

Frank Grimm

Slawomir Slowik

Dariusz Nowak

Mischa Schaerer

A Helmholtz damper for a combustor of a gas turbine includes first and second damping volumes. The combustor has a combustion chamber disposed in a housing and closed off by a front plate at which a plurality of burners are exchangeably fastened. The burners are supplied with fuel via fuel lances which extend from outside the housing through a bushing of the housing to the associated burner. The first damping volume has a first end and a second end, the first end of the first damping volume being configured to attach a connecting passage extending to a front panel such that the Helmholtz damper is connectable with the front plate of the combustion chamber in place of one of the burners. The second damping volume has a first end and a second end and is arranged in series with the first damping volume along an axis of the Helmholtz damper with the first end of the second damping volume being detachably connected to the second end of the first damping volume so as to form a combined larger damping volume. The second end of the second damping volume is configured to attach a connecting tube extending from the second damping volume and through the bushing in place of a respective one of the fuel lances.

Helmholtz damper for a combustor of a gas turbine and a method for installing the helmholtz damper

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 premix burner for producing an ignitable fuel/air mixture has a swirl generator with at least two burner shells (B) which complement one another to form a throughflow body, which in each case have a first burner shell section () with a partial cone shape and together enclose an axially conically widening swirl space and which mutually define, in the axial cone longitudinal direction, tangential air inlet slots (LS), through which the combustion feed air (L) passes into the swirl space, in which an axially spreading swirl flow forms, and includes fuel feeds which are arranged at least in sections along the tangentially running air inlet slots (LS). A second burner shell section () curved in opposition to the first burner shell section (), in each case designed in a partial cone shape, is added flush to the first burner shell section (), a third burner shell section () adjoins the second burner shell section () flush, the third burner shell section () having a curvature tangentially adapted to the second burner shell section (), and the third burner shell section () defines, on the one side in each case, one of the tangential air inlet slots (LS) and provides a leading edge () serving for the combustion feed air (L).

Premix burner for operating a combustion chamber

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Oettwil a.d.L., Switzerland

Martin Andrea Von Planta