DE2355127C2 - Burner for a gas turbine - Google Patents

Description

35

The invention relates to a burner for a Gas turbine for liquid fuel according to the preamble of claim 1.

Such a burner is from FR-OS 21 17 965 known.

In this case, the staggered air supply ensures that fuel and air are mixed well in a wide load range and a combustion with low soot formation achieved.

With the increasing interest in the cleanliness of the environment, however, is the reduction in soot development as well as the avoidance of harmful nitrogen-oxygen compounds when burning the Fuel in a gas turbine has become a priority.

The invention is based on the object of providing a burner for a gas turbine of the type mentioned at the beginning To create a way that further reduces the generation of pollutants during combustion can be.

This object is achieved according to the invention by what is specified in the characterizing part of claim 1 Characteristics.

A preferred further development results from the dependent claim.

The invention is explained below with reference to an embodiment shown in the drawings will. It shows

Fig. I a longitudinal section through a burner designed according to the invention,

F i g. 2 is a view along the line II-II in FIG. 1 and

F i g. 3 shows a section along the line III-III in FIG F i g. 2.

The burner 10 for a (not shown) gas turbine has a combustion chamber 12 and a supply line 14 to Supply of compressed air ven a compressor 13 as an atomizing means for the fuel.

Via a fuel line 16, fuel arrives at a nozzle 18 with at least one tiny opening 19, from which the fuel is sprayed into the combustion chamber 12. An outer air chamber 20 surrounds the burner core in an annular manner and is in communication with a source of air via a multiplicity of openings 22 which are arranged in the cylindrical outer wall 24 of the air chamber 20. A plurality of inclined swirl vanes 26 (guide vanes) are attached to the cylindrical inner wall 28 of the air chamber 20, from which they extend radially outward. Owing to the inclined guide vanes 26, the air flowing through the chamber 20 can be given a swirled course when it enters the combustion chamber, specifically at an angle of 30 to 35 ° to the axis of the combustion chamber. A frustoconical guide body 30 is attached to the small diameter end of the inner wall 28 of the air chamber 20 and has a plurality of annularly arranged nozzle-like openings 32 which are at an angle of 30 to 35 ° to the axis of the combustion chamber 12. The guide vanes 26 and the openings 32 direct their respective air flows parallel to one another. Any air flow contributes to and combines with the swirling motion of the fuel atomizer.

An inner air chamber 34 is provided near the fuel nozzle 18, which the atomizing agent via the Feed line 14 is fed, which then flows through an opening 36 near the head of the nozzle 18, and although at an angle towards the fuel, like this that it meets the fuel flowing into the combustion chamber.

A central air chamber 38 is formed between the inner and outer air chambers 34 and 20, respectively. while a plurality of passages 40 are provided in the inner wall 28 of the outer air chamber 20. The middle Air chamber 38 is angled on the fluid side with combustion chamber 12 over a plurality of arranged nozzle-like openings 42 in connection, which to the axis of the combustion chamber under a Angles of 30 to 35 °. The air passing through here flows parallel to that through the guide vanes 26 and the outer row of openings 32 created vortex airflow.

The vane 26 and the rows of angled openings 42 and 32 are shown in FIG. 2 shown.

The angular position of the guide vanes and the outer openings 32 is shown in FIG. 3 shown.

The burner is in the initial burn zone Vortex air is supplied in three stages, which widens the angle of the fuel injection cone Fuel particles are made smaller in size, which improves the ignitability of the fuel and finally the length of the flame is shortened. The atomization of the fuel is achieved by the Use of a vortex flow with a vortex direction identical to that of the fuel injection cone increased. In addition, the injected air penetrates the fuel injection cone, causing internal turbulence and mix leads. Since the combustion pressure increases during the combustion process, can a pressure equalizing piston 44 additional air from the

Combustion air source c. those in Fig. 1 as a compressor as shown, the air flowing through a disordered annular space 46 around the fuel supply line flows to interact with the air in the central air chamber 38 prior to being blown into the combustion chamber 12 to mix. The mixture of fresh air with the circulating, combustible fuel gas flow can be quick achieved and the combustion load factor can be quickly increased to a level in which a stable Combustion can be sustained. The mixture of fuel and air is thus sufficiently promoted and the carbon emissions due to incomplete combustion are reduced.

1 sheet of drawings

Claims (2)

Patent claims: 1. Burner for a gas turbine for liquid fuel, pressurized by one Combustion air and pressurized atomizing agent for the compressor supplied Fuel, with a fuel nozzle with at least one opening, with an atomizer chamber having at least one opening directed towards the spray cone of the fuel and a series of first arranged in a ring around the outflow end of the fuel nozzle in the circumferential direction inclined openings for combustion air, with a number of second, radially outward from the latter, arranged around the fuel nozzle th openings for combustion air and with an outer ring chamber for combustion air radially arranged swirl blades, thereby characterized in that the second openings (32) are also inclined in the circumferential direction and that the first and second openings (42,32) and the DraHschaufcln (26) with respect to the axis of the the burner downstream combustion chamber each have approximately the same angle, which for the first openings (42) 30 to 45 ° and for the second openings (32) and the swirl blades (26) 30 to 35 ° amounts to. 2. Burner according to claim 1, characterized in that the second openings (32) approximately are aligned perpendicular to the fuel spray cone.