Abb Research Ltd.

Asea Brown Boveri Ag

Martin Valk

Thomas Sattelmayer

Klaus Dobbeling

Christian Steinbach

Jakob Keller

Paul Marlow

Robin McMillan

The invention relates to a two-stage pressure atomizer nozzle with a nozzle body (30) having a mixing chamber (39) which is connected to an outside space via a nozzle outlet bore (33), and with a first feed duct (42) with a feed bore (41) for a liquid (37) to be atomized, through which feed bore said liquid (37) can be fed, free of swirling and under pressure, at least one further feed duct (36) for a portion of the liquid (37) to be atomized or for a second liquid (37') to be atomized opening into the chamber (39), through which feed duct said liquid (37, 37') can be fed under pressure and with swirling. The feed bore (41) of the first feed duct (42) lies on one axis (34) with the nozzle outlet bore (33). It is defined in that the outlet-side diameter (d.sub.a) of the nozzle outlet bore (33) is at most as large as the diameter (d.sub.z) of the feed bore (41) and the length (L) of the nozzle outlet bore (33) is at least twice to at most ten times the outlet-side diameter (d.sub.a) of the nozzle outlet bore (33).

Pressure atomizer nozzle

The burner arrangement for a gas turbine comprises at least one burner (2), which is arranged in the plenum of the gas turbine and leads with an inner injection space into a combustion chamber and to which compressed air is admitted on the outside from a compressor stage of the gas turbine. Furthermore, a fuel lance (9) for the alternative feeding of liquid and/or gaseous fuels is allocated to the burner (2), which fuel lance (9) has a central liquid-fuel tube (19) and a pilot gas tube (11) concentrically surrounding the liquid-fuel tube (19), the tubes (11, 19) ending in associated outlet openings (22, 23, 23a-c) in a lance head (12) at the tip of the fuel lance (9). In order to provide protection from an ingress of hot gases and/or hot liquid fuel into the outlet openings (22, 23, 23a-c) of the tubes (11, 19) when these tubes are not being used, an additional opening (17) is provided in the lance head (12) in the immediate vicinity of the outlet openings (22, 23, 23a-c), through which additional opening (17) compressed air flows out into the injection space (8). Furthermore, means are provided which direct compressed air from the plenum, surrounding the burner (2), to the additional opening (17).

Burner arrangement for a gas turbine for preventing the ingress of

In a burner (1) for a heat generator, having a throughflow passage (3) for the throughflow of a combustion-air flow (12), a hentral main fuel lance (5) acts inside the said throughflow passage (3). A number of mixing elements (6) are arranged in an annular manner around this main fuel lance (5), and the remaining annular throughflow cross section is covered concentrically hereto by swirl generators. The mixing elements (6) are fed with a fuel (13a) and a partial combustion-air quantity (12a). The mode of operation of these mixing elements (6) corresponds to that of a pilot stage, whereby the flame stability is increased, while the NOx emissions remain at a low level.

Burner

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Munchen, Germany

Martin Valk