Importance

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Abstract

In a combustion chamber (14) of a gas-turbine group which is arranged downstream of a first turbine (11) and upstream of a second turbine (12) and has a burnerless combustion space, extending between the outflow plane of the first turbine (11) and the oncoming-flow plane of the second turbine (12), and a fuel injector (2) which comprises a fuel-nozzle holder (8), extending transversely to the main flow (1) approximately up to the center axis, and a fuel nozzle (9) arranged in the direction of flow in the center axis and connected to the fuel-nozzle holder (8), the combustion chamber (14) working with premixing combustion, and the inlet temperature of the exhaust gas of the first turbine (11) into the combustion chamber (14) being above the self-ignition temperature of the fuel (13), the fuel injector (2) has means for simultaneously evening out the velocity profile and for lowering the temperature of the flow in the wake region. These means are feed passages (5), arranged inside the fuel injector, and openings (6) for an additional mass air flow (3). Thus the formation of a region of recirculating flow, which leads to an undesirable flame effect before the actual combustion zone, is prevented.

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