Alstom Technology Limited

General Electric Company

General Electric Technology Gmbh

Frank Grimm

Fulvio Magni

Douglas Pennell

Weiqun Geng

Martin Andrea Von Planta

Dariusz Nowak

Sebastiano Sorato

Lindsay Dawn Axford

Mischa Schaerer

Andreas Lechner

Adrian Mettler

Douglas Anthony Pennell

A combustor system for a GT system may include: a plurality of burners, each burner including an inflow region for receiving a combustion air flow and a mixing zone disposed downstream of the inflow region for receiving the air flow and a fuel flow; a combustion chamber disposed downstream of the mixing zone; a fuel flow valve system disposed to control the fuel flow to each of the plurality of burners; a combustion sensor configured to determine a combustion parameter; and an exhaust sensor configured to determine an exhaust parameter. A control system may be connected to the combustion sensor, the exhaust sensor and fuel flow valve system. The control system, in response to the gas turbine system operating at a low partial load, redistributes the fuel flow to at least one burner of the plurality of burners as a function of a predetermined emission limit.

Low partial load emission control for gas turbine system

A premix burner is provided for a gas turbine, in the form of a double-cone burner, which has two partial cone shells which are arranged nested one inside the other, forming air inlet ducts between them, through which combustion air from the outside flows into a conical inner space of the premix burner. Linear rows of holes of injection openings, which extend transversely to the flow direction of the combustion air, are arranged on the outer walls of the air inlet ducts and through which a gaseous fuel is injected into the combustion air which flows past transversely to them. A method for reworking such premix burners is also provided.

Premix burner for a gas turbine

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

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Baden, Switzerland

Frank Grimm