WO2012000712A1

WO2012000712A1 - Burner module

Info

Publication number: WO2012000712A1
Application number: PCT/EP2011/057820
Authority: WO
Inventors: Matthias Hase; Nicolas Savilius; Oliver Schneider
Original assignee: Siemens Aktiengesellschaft
Priority date: 2010-07-02
Filing date: 2011-05-16
Publication date: 2012-01-05
Also published as: EP2402655A1; EP2588806A1; EP2588806B1

Abstract

The invention relates to a burner module, comprising a plate (90) consisting of an upper face (92) and a lower face (91), wherein at least two cavities containing fuel (110) are provided in the lower face (91), and wherein a through-passage (98) extending from the lower face (91) to the upper face (92) of the plate (90) is present for guiding air (100). The air (100) flowing through the through-passage (98) forms an air flow direction (L), wherein a combustion chamber is provided downstream in the air flow direction (L). Inside the plate (90) at least two fuel connections (105) are provided, which lead from the at least two cavities to at least two opposite openings (101) in the through-passage (98), so that an injection of fuel (110) present in the cavities through the fuel connections (105) into the air (100) of the through-passage (98) is provided.

Description

description

Burner module The invention relates to a burner module according to the preamble of claim 1.

In the prior art, a small number of burners (up to about 24) with long flames (up to about 0.5 m) are used in gas turbines for large industrial applications. Here, in order ei ^¬ NEN sufficient burnout prior to entering the turbine to ge ^¬ währleisten, a sufficient residence time of the fluid in the combustion chamber is needed. This necessarily results in a large or longer combustion chamber.

Another approach to gas turbine combustion is the use of micro flame burners. The number of flames is significantly increased compared to the design in the prior art (number depending on the power (> 1000)). Depending on the design, the size of the flames is only a few millimeters to a few centimeters. Through the shorter dwell time ^¬ at high temperatures, the formation of thermal NOx is drastically reduced. Due to the good burnout, the formation of CO is minimized.

DE 2023 060 shows a burner for gaseous fuels having a perforated porous outlet plate which adjoins a combustion ^zone on one side and a base plate on the other. The base plate is connected to the exit plate so that the perforations or holes in the exit plate are congruent with the perforations or holes in the base plate. So air can flow through them. The exit points have of the Grund ^¬ plate such a distance between the holes, that

Fuel passageways are formed. These provide the Strö ^¬ tion of the fuel gas, a resistance which is low compared to the flow resistance through the outlet plate. The burner as a whole is designed so that during the Use of the burner gaseous fuel through the

Fuel passages and from there through the porous exit ^¬ plate flows into the combustion zone, where it burns with the sucked through the perforations or holes air.

EP 1 001 216 A1 shows a disk with openings passing through the disk. Channels are arranged transversely to the openings through which fuel is passed. Through these channels fuel can be supplied to the openings.

However, in the prior art microflame burners, a major drawback is that the large number of microflame burners adds enormously to the cost of manufacturing the entire gas turbine unless an efficient manufacturing process with a correspondingly simple design is used. At the same time, however, every single Bren ^¬ ner must ensure adequate mixing of air and fuel / fuel gas. In addition, a certain control range for the power control of the gas turbine is desirable, which must be achieved differently for small flames than for large ones.

The object of the present invention is therefore to specify a burner module which avoids the above disadvantages while maintaining the above-mentioned conditions.

The related to the burner module object is achieved by the administration of a burner on ^¬ module according to Claim. 1 More part-like before ^¬ embodiments result from the dependent claims.

By the burner module according to the invention thus individual parts of the combustion chamber or the entire combustion chamber can be replaced by such burner modules. The design and manufacture of the individual modules is very cost-efficient and can also be used in small-scale applications and also reduce costs. The simple design allows this a fast and intensive mixing of fuel and air (or an air-fuel mixture), just feeding the fuel with not parallel to the air flow arranged fuel compounds leads to very good mixing conditions.

The burner module according to the invention reduces the required residence time in the combustion chamber. As a result, the combustion chamber, compared to the combustion chambers in the prior art can be significantly reduced. Thus, the costs and the effort can be reduced here as well. The reduction of the combustion chamber simultaneously allows a shortening of the rotor or the entire gas turbine. Here, material costs are saved to a great extent and the dynamic behavior of the machine with respect to vibrations and mass inertia is improved. By reducing the size of the combustion chamber, the surface of the combustion chamber to be cooled also decreases. Cooling air can be saved here, which improves the efficiency of the overall process.

Further features, properties and advantages of the present invention will become apparent from the following description of embodiments with reference to the accompanying figures.

1 shows a section along an axis I-I of a first embodiment of a burner module according to the invention,

2 shows the section of the first embodiment along an axis II-II,

Fig. 3 shows a section along a line II of a second embodiment of a burner according to the invention ^¬ SEN module, 4 shows the section of the second embodiment along an axis II-II,

Fig. 5 shows the section of a third Ausführungsbei ^¬ game along an axis II-II.

Fig. 1 shows a section along an axis II of he ^¬ inventive burner module according to a first embodiment ^¬ example. 2 shows the section of the first exemplary embodiment along the axis II-II extending perpendicular to II. The burner module consists of a plate 90 with a bottom 91. On this bottom 91, a top 92 is fixed by soldering or welding, the centering is accomplished with index holes and pinnacles. In the bottom 91 at least two, however, usually more cavities are introduced. The cavities can be a Laserschnei ^¬ dung or erosion or stamping or pressing, but are not limited to this production method is ^¬ limits. The cavities are supplied with fuel 110 (not shown). These cavities are in the first exporting approximately ^¬ for grooves 95 (Figure 2). Also suitable for the production of grooves 95 laser cutting, milling, EDM or embossing / pressing. Are - as shown in Fig. 2 - several such grooves 95 on a burner module, so are DIE se preferably parallel to each other, that is, in rows being arranged ^¬. In the grooves 95 also fuel 110 is vorgese ^¬ hen. The grooves 95 terminate in a collection channel (not shown) at the end of the burner module and then via a suitable flange construction to a fuel supply system

(not shown) connected.

In the plate 90, a passageway 98 is now attached, which extends from the bottom 91 to the top 92. As also shown in FIG. 1, the through-channel 98 in the upper side 92 has a through-passage end 111. For the following description it is assumed that the Plat ^¬ te 90 consists of several passage ducts 98 and a plurality of cavities. The passageways 98 serve to guide air 100 through the plate 90. In this case, the air 100 may also be an air-fuel mixture. In this case, an air flow direction L is formed by the air 100 flowing through the passageways 98. In the air flow direction L of the plate 90 nachge ^¬ switched is a combustion chamber (not shown). The air 100 is transported through the inside through channels 98 in the Brennkam ^¬ mer. The through-passages 98, like the cavities, are introduced into the plate 90, for example by punching, drilling or laser drilling. However, the passageway 98 is also not be ^¬ limited to this type of production, but these represent a particularly simple Her ^¬ position wise.

The passageway 98 has at least two ^mutually opposite channel openings 101 (FIG. 2); that is, they are arranged at the same height in the passageway 98. This allows a better turbulence of the fuel with the air 100 take place. As shown in FIG. 2, the plate 90 also has two fuel connections 105 leading from the grooves 95 to the channel openings 101. The fuel connections 105 are with the channel openings 101 at the same height. The fuel connections 105 are introduced, for example, by punching, erosion or laser drilling. The fuel 110 can thus be injected from the grooves 95 via the fuel connections 105 into the flow of the air 100 of the through-passage 98 and thus mix. In this case, the fuel connections 105 can be arranged in such a way to the through-channel 98, which here essentially sets a 90 ° angle. This results in a particularly good mixing ratio of

Fuel with the air 100.

From the bottom 92, therefore, compressed air 100 flows through the passageways 98 into the combustion chamber. Fuel 110 enters the air 100 from the grooves 95 through the fuel connections 105. After appropriate mixing then burns a flame essentially as a premix flame or partially pre-mixed flame behind the flame bottom.

If the channel openings 101 are placed directly under the top side 92 (FIG. 1), the combustion results in a premixed or partially premixed flame. The upper side 92 then contains exclusively the passage end 111 (FIG. 1) seen in the air flow direction L. That's it

Through-passage end 111 is formed as a diffuser for mixing air 100 with fuel 110. This results in a change in the flow rate of the flow present in the passageway 98, resulting in improved mixing and inflow into the combustion chamber. Fig. 3 shows a second embodiment of a burner OF INVENTION ^¬ to the invention the module. Again, the plate 90 consists of a bottom 91 and a top 92. In the Un ^¬ terseite 91 as cavities hollow areas 120 are introduced. Here, too, it is assumed that the plate 90 has a plurality of hollow regions 120 and through-channels 98. Hollow regions 120 also include fuel (not shown). In this case, the hollow regions 120 are distributed in the plate 90 as a honeycomb-shaped (FIG. 5) or square (FIG. 4) pattern. In this case, the pattern can be made by milling grooves over cross or embossing. The hollow regions 120 may be triangular with a side surface b and arranged at a distance a from each other (Fig. 5). Optionally, the hollow portions 120 may also be performed square with a side surface b from ^¬ and arranged at a distance a from each other

(Fig.4). However, the geometric arrangement of the hollow regions 120 in the plate is not limited to these geometric ^shapes . Likewise, the hollow regions 120 may have any other shape. Into the plate 90 of Fig. 3 are also passageways

98 with channel openings 101 attached. In the case of honeycomb-shaped (FIG. 5) or square (FIG. 4) distribution of the hollow regions 120, the through-channels 98 preferably have three channels. Nalöffnungen 101 and four channel openings 101 on. In this case, the three or four channel openings 101 each relate to a passage channel 98. In this case, the channel openings 101 may be arranged in the upper side 92, so that the fuel either first in the combustion chamber with the air 100 mixes (that is, the channel openings are on the surface 92 to ^¬ ordered) or in the passageway 98, just before the air enters the combustion chamber 100. In FIGS. 3 to 5, the fuel connections 105 are directed obliquely radially inward toward the through-passage 98, possibly tangentially to the through-passage 98. In addition, the two fuel connections 105 to the through-passage 98 can have an angle between> 0 and 90 °. As a result, an increase of the mixture takes place. Fuel, which is guided in the hollow region 120, thus escapes into the flow of the air 100 of the passage channel 98 via the obliquely radially inwardly directed, possibly tangentially engaged fuel connections 105. The flame then burns after appropriate mixing essentially as a diffusion flame behind the flame bottom.

Additionally or alternatively, there is the possibility of the

To inject fuel 100 from the cavities 120 into the combustion chamber through an annular gap (not necessarily continuous) disposed about the passageway 98 (not necessarily continuous).

Advantageously, a plurality of burner modules

Combustion chamber formed. Thereby, the combustion chamber can be significantly reduced in size, as a conventional combustion chamber with e.g. Pilot burner.

The described design and manufacturing methodology enables the advantages of micro flame burners to be used cost-effectively also in gas turbines for large scale industrial applications. The concept of construction and production described here can also find use in small applications and also reduce costs here. The design allows for a fast and intensive mixing of fuel and air 100, with just the supply of fuel, with tangen ^¬ tial or at 90 ° angle, arranged for air flow fuel compounds leads to excellent mixing ratios. Through the concept, the required residence time in the

Reduced combustion chamber or the combustion chamber can be downsized. Thus, the costs and the effort can be reduced here as well. The reduction of the combustion chamber at the same time allows a shortening of the rotor or ge ^¬ entire gas turbine, here are largely saved material costs, the dynamic behavior of the machine with respect to vibrations and inertia improved. By Ver ^¬ kleinerung the combustion chamber and the surface to be cooled of the combustion chamber decreases. Cooling air can be saved here, which improves the efficiency of the overall process.

Claims

claims

1. burner module comprising a plate (90) consisting of egg ^¬ ner top (92) and an underside (91), wherein at least two cavities with fuel (110) are provided in the underside (91), and wherein a passageway (98) is present for guiding air (100) extending from the bottom (91) to the top (92) of the plate (90) it passes ^¬ stretched, wherein reciprocated by passing through the through-channel (98) by flowing air (100) air flow direction (L) is formed from ^¬, wherein in the air flow direction (L) nachgeschal ^¬ tet a combustion chamber is provided, characterized in that within the plate (90) has two fuel connections (105) are provided at ^¬ least WEL surface of the at least two Cavities to at least two at the same height arranged openings (101) in the passageway (98) leads, so that an injection of existing in the Hohlräu ^¬ men fuel (110) through the fuel compounds (105) into the air (100) d passageway (98).

2. Burner module according to claim 1,

characterized in that the at least two fuel ^¬ compounds (105) is substantially formed with the transit channel (98) a 90 ° angle.

3. burner module according to claim 1,

characterized in that the at least two fuel ^¬ compounds (105) to the through channel (98) have an angle between> 0 and 90 °.

4. burner module according to claim 3,

The openings (101) of the passageway (92) are in the area of the top of the plate (90).

Burner module according to one of the preceding claims, characterized in that the Through passage (98) is a punched or drilled hole, in particular a laser bore.

6. Burner module according to one of the preceding claims, characterized in that the ^¬ least two cavities are a laser cutting or Erodie ^¬ tion or an embossing or pressing.

7. Burner module according to one of the preceding claims, characterized in that the ^¬ least two cavities are formed by grooves (95) in the plate (90).

8. burner module according to claim 7,

characterized in that the Nu ^¬ th (95) open into a collecting channel, which is connected to a fuel ^¬ supply system.

9. burner module according to any one of the preceding claims, characterized in that the at least two cavities ^¬ designed as hollow regions (120) and honeycomb-shaped in the plate (90) are arranged.

10. Burner module according to one of the preceding claims 1-8, characterized in that the ^¬ least two cavities as hollow areas (120) and square in the plate (90) are arranged.

11. Burner with a plurality of burner modules according to one of the preceding claims.

12. Gas turbine with a compressor, a turbine and a burner according to claim 11.