Burner arrangement for a gas turbine for preventing the ingress

Details Burner arrangement for a gas turbine for preventing the ingress Burner arrangement for a gas turbine for preventing the ingress

1997-12-03

2000-03-21

Kim, Ted

Power plants

Combustion products used as motive fluid

Combustion products generator

60746, 60737, F23R 328, F23R 336

Patent

active

060388633

ABSTRACT:
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).

REFERENCES:
patent: 3691765 (1972-09-01), Carlisle
patent: 3763650 (1973-10-01), Hussey et al.
patent: 5062792 (1991-11-01), Maghon
patent: 5337961 (1994-08-01), Brambani et al.
patent: 5615555 (1997-04-01), Mina
patent: 5664943 (1997-09-01), Joos et al.
patent: 5765366 (1998-06-01), Beeck et al.
patent: 5782626 (1998-07-01), Joos et al.
patent: 5884471 (1999-03-01), Anderson et al.

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