WO2011072665A1

WO2011072665A1 - Burner for a turbine

Info

Publication number: WO2011072665A1
Application number: PCT/DE2010/050074
Authority: WO
Inventors: Frank Reiss; Ulrich Orth; Holger Huitenga
Original assignee: Man Diesel & Turbo Se
Priority date: 2009-12-15
Filing date: 2010-09-28
Publication date: 2011-06-23
Also published as: CA2782196A1; JP2013517440A; CA2782196C; US20120227407A1; EP2513562A1; DE102009054669A1; EP2513562B1

Abstract

The invention relates to a burner for a turbine, comprising: a flame tube, in which a combustion chamber is formed, a jacket, which encloses the flame tube radially from the outside at a predetermined distance so that an oxidant collection chamber is formed between the flame tube and the jacket, a burner bottom, which bounds the oxidant collection chamber and the combustion chamber at an axial end of the burner, and a swirl generator, which is arranged axially between the flame tube and the burner bottom and axially adjacent to the burner bottom and radially adjacent to the oxidant collection chamber, for feeding a fuel-oxidant mixture into the combustion chamber, wherein the swirl generator has a plurality of guide blades arranged in a circumferential direction of the burner at a circumferential distance from each other so that the distances between the guide blades form a plurality of radial inlet passages to the combustion chamber that each have a tangential component in the course thereof, wherein a fuel supply tube is provided in the inlet flow area of at least some of the inlet passages, which fuel supply tube extends through the respective inlet passage in an axial direction of the burner and transversely to an oxidant flow direction, and wherein each fuel supply tube has at least one fuel outlet opening in the wall thereof, by means of which fuel outlet opening fuel can be mixed into the respective inlet passage with a directional component extending transversely to the oxidant flow direction.

Description

Burner for a turbine

The invention relates to a burner for a turbine, and more particularly to a device for premixing oxidant and fuel

provided burner for a turbine.

In order to achieve low emission levels, turbines such as e.g.

Gas turbines called "premix burner" or "Premix Burner" used. By using premix technology, the mixing process of

Fuel and oxidants, such as air, are decoupled from the actual combustion process, i. preceded by this. This allows the peak combustion temperatures to be lowered. At the same time, the residence time of the fuel-oxidant mixture (e.g., fuel-air mixture) in the reaction zone may be shortened. In particular, this reduces the formation of NOx (especially thermal NOx). There are different "premix burners" in atmospheric combustion and combustion under pressure in use, and also in the field of gas turbines different burners are used with an optimal burner, the combustion in a wide operating range stable, controlled, low in emissions and possible The focus is always on the quality of the mixture of fuel and oxidant, which determines the local combustion temperature and therefore the reaction products, ie the emissions, which is why the location and aerodynamics of the

Fuel injection should be carefully selected.

DE 10 2008 019 1 17 A1 describes a burner for a turbine provided with a device for premixing air and fuel. According to this document, the burner has a cylindrical combustion chamber for gaseous or liquid fuel and a Haupindindüsung. The combustion chamber is in an Axialnchtung of the burner bounded on one side by a burner bottom and radially by a flame tube. The main injection is used to inject a premixed fuel-air mixture. The injection takes place radially to a burner longitudinal axis via main nozzles, which open into a radial swirl generator. The radial swirler is disposed between the burner bottom and the flame tube and causes the fuel-air mixture to be impinged with a swirl pulse and swirl into the combustion chamber.

Further with a means for premixing oxidant and

Fuel burners are described in DE 198 59 210 A1 and in DE 38 19 898 A1.

The invention has for its object to provide a burner for a turbine, in a simple and cost-effective manner an extremely homogeneous premix of a in a combustion chamber of the burner

fuel-oxidizer mixture to be incorporated, e.g. one

Fuel-air mixture is achieved.

This is achieved with a burner according to claim 1. Further developments of the invention are defined in the dependent claims.

According to the invention, a burner for a turbine comprises: a flame tube, in which a combustion chamber is formed, a jacket, which surrounds the flame tube from radially outside with a predetermined distance thereof, so that an oxidant collecting space is formed between flame tube and jacket, a combustor bottom defining the oxidizer plenum and combustion chamber at an axial end of the combustor, and a swirler axially disposed between the combustor tube and the burner floor axially adjacent the combustor bottom and radially adjacent to the oxidant plenum for supplying a fuel oxidant; Mixture in the combustion chamber, the

Swirl generator one along a circumferential direction of the burner with each Having circumferentially spaced plurality of vanes, so that the respective distances between the vanes form a plurality of in their course each having a tangential component having radial inlet passages to the combustion chamber, wherein in each Inlasströmungsbereich at least some of the plurality of inlet passages each have a Brennstoffzuführrohr is provided which extends with respect to its length in an axial direction of the burner and transversely to an oxidant flow direction through the respective inlet passage, and wherein each fuel feed tube has in its wall at least one with respect to the Brennstoffzuführrohrs radial fuel discharge opening, via the fuel with a transverse to the Oxidationsmittel- Flow direction extending direction component in the respective inlet passage is einmischbar.

Preferably, air is provided as the oxidizing agent, which is fed at atmospheric or elevated pressure into the oxidant collecting space.

Due to the fact that in the burner according to the invention the fuel injection takes place within the inlet passages or air passages of the swirl generator through individual fuel supply pipes with a directional component running transversely to the oxidant flow direction, an extremely homogeneous premix of the fuel combustion chamber to be introduced into the combustion chamber of the burner is easily and inexpensively achieved. Oxidizing agent mixture, such as of a fuel-air mixture achieved.

Due to the free design possibility of the fuel dispensing opening (s), which is preferably designed as a bore or are, and the freely selectable

Positioning of the fuel supply pipes and the fuel discharge opening (s) within the respective Einlassströmungsbereiche or to the respective

Fuel supply pipes, an optimal premix of fuel (eg fuel gas) and oxidizing agents (eg air) can be achieved. If the As fuel composition changes, the fuel delivery ports may be adjusted in size and shape.

According to one embodiment of the invention, all inlet passages are each provided with a fuel feed pipe.

This advantageously promotes particularly homogeneous mixing of fuel and oxidant prior to introduction into the combustion chamber.

According to another embodiment of the invention, at least one of the fuel supply pipes is arranged in the respective intake passage.

This embodiment of the invention provides an advantageous variant for the

Arrangement of one or more or all fuel supply pipes, wherein the respective position in the inlet passage freely selectable and thus the

Mixing length of fuel and oxidant are freely changeable.

According to yet another embodiment of the invention, at least one of the fuel supply tubes is in the oxidant flow direction directly in front of the respective inlet passage, i. at the beginning of Einlasströmungsbereichs arranged.

This embodiment of the invention represents a further advantageous variant for the arrangement of one or more or all Brennstoffzuführrohre, wherein the mixing length or mixing distance of fuel and oxidant is maximally extended. According to yet another embodiment of the invention, at least one of the fuel supply pipes is relative to a longitudinal center axis of the respective one

Inlet passage arranged off-center in the respective intake passage.

This embodiment of the invention represents yet another advantageous variant for the arrangement of one or more or all fuel supply pipes, wherein the respective off-center position in the inlet passage transversely to their

Longitudinal center axis freely selectable and thus the turbulence of the fuel is freely changeable. According to an embodiment of the invention, at least one of the fuel supply pipes or a plurality or all of the fuel supply pipes is arranged centrally in the respective intake passage with respect to the longitudinal central axis of the respective intake passage.

According to another embodiment of the invention, at least one of the fuel supply pipes has a plurality of fuel discharge openings spaced along the length of the fuel supply pipe.

With this embodiment of the invention, the homogeneous mixing of fuel and oxidant can be further improved. Preferably, therefore, several or all of the fuel supply pipes each having a plurality of along the length of the Brennstoffzuführrohre each with a distance from each other

arranged fuel delivery openings provided.

According to yet another embodiment of the invention, at least one of the Brennstoffzuführrohre two fuel discharge openings, which are arranged with respect to the length of the Brennstoffzuführrohrs at the same position, so that these two fuel discharge openings fuel with two opposite direction components of the

Fuel supply tube can be dispensed. According to this embodiment of the invention, by oppositely outputting the fuel into the intake passage, the oxidant flow on both sides of the fuel supply pipe is utilized for fluidizing the fuel, thereby further improving homogeneous mixing of fuel and oxidant.

Preferably, several or all fuel supply pipes each have two

Fuel discharge openings on the length of the

Fuel supply tube are arranged at the same position, so that these two fuel discharge openings fuel with two each other

opposite direction components can be output from the Brennstoffzuführrohr.

More preferably, each fuel dispensing opening of a respective

Fuel supply such a with respect to the length of the Brennstoffzuführrohrs at the same position arranged their fuel with an opposite direction component issuing fuel dispensing opening.

In addition to optimal "standard positions" can of course also individual

Optimizations regarding emissions and reignition behavior - depending on fuel consequences.

According to further embodiments of the invention, as seen in cross section of the respective fuel supply pipe, the two fuel discharge openings are diametrically opposed to each other or include respective longitudinal center axes of the two fuel discharge openings at an obtuse angle.

Also with this embodiment of the invention can in a simple and efficient way, the strength of the turbulence and the entrainment of the fuel in the Oxidized and thus optimized for the particular application.

According to further embodiments of the invention, the

Fuel supply pipes each have a cylindrical cross section or a wing-shaped cross-section or other suitable for optimum turbulence cross-sections. According to the invention, all

Fuel supply tubes have the same cross-sectional shape.

Embodiments in which groups of fuel supply pipes are formed, wherein within a group all the fuel supply pipes are the same

Have cross-sectional shape, but the groups different

Have cross-sectional shapes are also possible.

For example, the airfoil shape may prove advantageous for reducing direct mixing in the pipe wake, which may be particularly necessary with reactive fuels (such as hydrogen).

In accordance with yet another embodiment of the invention, the fuel supply tubes are each detachably mounted so that each is arranged in a predetermined manner

If necessary, the fuel feed configuration formed fuel supply tube is individually replaceable with a fuel supply tube according to another predetermined fuel mixing configuration.

Due to the simple interchangeability of the fuel supply pipes, a simple and rapid adaptation of the burner during a fuel change can be carried out. Typically, the burner according to the invention is suitable for the use of fuel gas as fuel. However, the burner according to the invention can also be operated with liquid fuel, wherein, if necessary, special nozzles should be inserted into the fuel discharge openings. Through the use of the central fuel supply pipes in the intake passages of the swirl generator (Swirlers) optimal mixtures of fuel (eg

Fuel gas) and oxidizing agent (e.g., air). This can be low

Emission values can be achieved. At the same time can by the individual

Design of the fuel delivery openings and / or positioning of

Fuel supply tubes to locally different oxidant distributions, such. locally different air distributions, be reacted. Due to the central replaceable fuel supply pipes solution of the invention is very inexpensive.

In the following the invention will be described in more detail by means of preferred embodiments and with reference to the attached figures.

1 shows a schematic longitudinal sectional view of the structure of a

Burner of a gas turbine according to an embodiment of the invention.

FIG. 2 shows a schematic cross-sectional view of a part of the burner of FIG. 1, seen along a line A-A in FIG.

3 shows in enlarged partial views of an inlet passage of the burner of Figure 2 three possible configuration variants of a

Brennstoffzuführrohrs.

4 shows two possible configuration variants of a fuel feed tube in an inlet passage of the burner according to the invention, as seen along a line B-B in FIG.

1 shows the structure of a burner 1 of a gas turbine (not completely shown) according to an embodiment of the invention.

The burner 1 has a flame tube 10, in which a combustion chamber 1 1 is formed, and a tubular shell 20, the flame tube 10 from radially outward encloses it with a predetermined distance, so that between

Flame tube 10 and shell 20 an oxidant-collecting space 21 is formed.

As fuel for the burner 1 fuel gas is provided, and as

Oxidizing agent for the fuel gas is provided atmospheric air, which is compressed by a compressor (not shown) and then the

Oxidant collecting space 21 is supplied.

The burner 1 further has a burner bottom 30 defining the Oxidationsmittel- collecting space 21 and the combustion chamber 1 1 at an axial end of the burner 1, and a swirl generator 40, the axially adjacent to the burner bottom 30 and radially to the oxidant collecting space 21 axially between the flame tube 10 and the burner bottom 30 is arranged, for supplying a

Fuel-oxidizer mixture BOG in the combustion chamber 1 1.

Referring additionally to FIG. 2, which shows a sectional view of a part of the burner of FIG. 1 as seen along a line A - A in FIG. 1, the swirl generator 40 has a plurality of circumferentially spaced apart UR of the burner 1 (FIG. here eight) of vanes 41.

The guide vanes 41 are each shaped and arranged such that the respective distances between the guide vanes 41 form a plurality (in this case eight) of radial inlet passages 42 each having a tangential component in their course toward the combustion chamber 11.

In a respective intake flow area of at least some of the plurality of intake passages 42, there is provided a fuel supply pipe 43a, 43b, 43c, 43d each having a length in an axial direction AR (see FIG 1) of the burner 1 and extends transversely to an oxidant flow direction OR through the respective inlet passage 42 therethrough.

Although only one of four intake passages 42 in each of FIG

Fuel supply pipe 43a, 43b, 43c, 43d, according to not shown embodiments of the invention may also be provided in more or less or in all inlet passages 42 respective fuel supply pipes 43a, 43b, 43c, 43d.

As shown in Figs. 3 and 4, each fuel supply pipe 43a, 43b, 43c, 43d has in its wall at least one fuel discharge port 44, 45 radial with respect to the fuel supply pipe 43a, 43b, 43c, 43d, over which

Fuel BS with a direction transverse to the oxidant flow direction OS direction component into the respective inlet passage 42nd

is mixable. Preferably, each fuel dispensing opening 44, 45 is formed as a bore or as a nozzle insert.

As can be seen from Figure 2, one or more, or all

Fuel supply pipes 43 a, 43 b, 43 d directly into the respective

Inlet passages 42 may be arranged. As also seen from FIG. 2, the fuel supply pipes 43a, 43b, 43d may be disposed within the respective intake passages 42 at different positions along the length of the respective ones

Inlet passages 42 may be arranged.

On the other hand, one, several or all of the fuel supply pipes 43c in the oxidant flow direction OS can be directly in front of the respective ones

Inlet passages 42 (ie at the entrance of the respective inlet passages 42 partially or completely in the oxidant collecting space 21) may be arranged. As also shown in FIG. 2, one, several or all fuel supply pipes 43 a, 43 b, 43 c may be arranged centrally in the respective intake passages 42 with respect to longitudinal center axes L of the respective intake passages 42. On the other hand, one, several or all of the fuel supply pipes 43d may be off-center with respect to the longitudinal center axes L of the respective ones

Inlet passages 42 may be arranged in these.

As can be seen in FIG. 4, one or more, or all, can

Fuel supply pipes 43 a, 43 b, 43 c, 43 d a plurality of

Fuel discharge openings 44, 45, which along the respective length of the fuel supply pipes 43 a, 43 b, 43 c, 43 d spaced from each other

are arranged [variant a) in Figure 4]. On the other hand, one, several or all fuel supply pipes 43a, 43b, 43c, 43d may have only a single fuel discharge opening 44, 45 with respect to the respective length of the fuel supply pipes 43a, 43b, 43c, 43d [variant b) in Fig. 4].

As can be seen from FIG. 3, one, several or all of the central fuel supply pipes 43a, 43b, 43c (designated by 43a-c in FIG. 3) and also one, several or all off-center fuel supply pipes 43d (not in FIG shown) have two fuel discharge openings 44, 45, which are arranged at the same position with respect to the length of the Brennstoffzuführrohrs, so that these two fuel discharge openings 44, 45 fuel BS with two opposite direction components (as shown by the

oppositely directed exit arrows for the fuel BS indicated) from the respective Brennstoffzuführrohr 43a, 43b, 43c, 43d can be dispensed.

As can be seen from Figure 3, the two can

Fuel discharge openings 44, 45 in cross section of the respective

Fuel supply pipe 43 a, 43 b, 43 c, 43 d seen diametrically

opposite [variant a) in Figure 3] or can respective longitudinal center axes L1, L2 of the two fuel discharge openings 44, 45 an obtuse angle α (45 ° <α <180 °) with each other include [variants b) and c) in Figure 3].

Of course, it would also be possible within the scope of the invention, which are each opposite diametrically or with the obtuse angle α

Fuel discharge openings 44, 45 to let the length of the Brennstoffzuführrohrs 43a, 43b, 43c, 43d to alternate, so that at each length position of the fuel supply pipe 43a, 43b, 43c, 43d only a single

Fuel discharge openings 44, 45 is arranged.

As can be seen in FIGS. 2-4, the fuel supply pipes 43a, 43b, 43c, 43d each have a cylindrical cross section. However, according to non-illustrated embodiments of the invention, the fuel supply pipes 43a, 43b, 43c, 43d may also have a wing-shaped cross-section or other suitable for homogeneous mixing of oxidant and fuel

Have cross-sectional shapes. A hydrofoil shape is for example in

DE 38 19 898 A1 shown in Figure 2 with reference to vanes.

Although not shown in detail in FIGS

Each of fuel supply pipes 43a, 43b, 43c, 43d is detachably mounted in the burner 1 such that each of fuel supply pipes 43a, 43b, 43c formed according to a predetermined fuel mixing configuration (position of the fuel supply pipe in the intake passage, number and arrangement of the fuel discharge ports, cross sectional shape of the fuel supply pipe); 43d is individually replaceable with a fuel supply pipe 43a, 43b, 43c, 43d, if necessary, according to another predetermined fuel mixing configuration.

For this purpose, the fuel supply pipes 43a, 43b, 43c, 43d (designated 43a-d in Fig. 4) are detachably inserted into corresponding openings in the burner bottom 30, as shown in Fig. 4, with each fuel supply pipe 43a, 43b, 43c, 43d a longitudinal end of a flange or head portion 46, 47th which, on the side facing away from the swirl generator 40 of the

Burner bottom 30 abuts this and e.g. by means of screws (not shown) screwed to the burner bottom 30.

Finally, it should be noted that each fuel delivery tube 43a, 43b, 43c, 43d is naturally connected via respective conduits and control valves (both not shown) to a fuel source (not shown), such as a fuel source. one

Fuel gas tank, fluid-connected.

LIST OF REFERENCE NUMBERS

1 burner

10 flame tube

1 1 combustion chamber

20 coat

21 Oxidant collecting chamber 21 30 Burner bottom

40 swirl generators

41 vane

42 inlet passage

43a fuel supply pipe

43b fuel supply pipe

43c fuel supply pipe

43d fuel supply pipe

44 fuel dispensing opening

45 fuel dispensing opening

46 head section

47 head section

L longitudinal central axis

L1 longitudinal central axis

L2 longitudinal central axis

α obtuse angle

UR circumferential direction

AR axial direction

OR oxidant flow direction

BS fuel

BOG fuel-oxidizer mixture

Claims

claims

1 . Burner (1) for a turbine, comprising:

a Flannnnrohr (10), in which a combustion chamber (1 1) is formed,

a jacket (20) which surrounds the flame tube (10) from radially outside at a predetermined distance therefrom, so that an oxidant collecting chamber (21) is formed between the flame tube (10) and the jacket (20),

a burner bottom (30) defining the oxidizer plenum (21) and the combustion chamber (11) at an axial end of the burner (1), and

a swirl generator (40) disposed axially adjacent the burner bottom (30) and radially adjacent to the oxidizer plenum (21), axially between the flame tube (10) and the burner bottom (30), for supplying a fuel-oxidizer mixture (BOG) into the combustion chamber (1 1),

wherein the swirl generator (40) has a plurality of vanes (41) circumferentially spaced apart along a circumferential direction (UR) of the burner (1) such that the respective distances between the vanes (41) are a plurality of in their course, respectively a tangential component having radial inlet passages (42) for

Form combustion chamber (1 1),

wherein in a respective Einlassströmungsbereich at least some of

A plurality of inlet passages (42) each have a fuel supply pipe (43a, 43b, 43c, 43d) is provided, which in terms of its length in a

Axialrichtung (AR) of the burner (1) and transverse to an oxidant flow direction (OR) through the respective inlet passage (42) extends therethrough, and

wherein each fuel supply pipe (43a, 43b, 43c, 43d) has in its wall at least one fuel delivery opening (44, 45) radial with respect to the fuel supply pipe (43a, 43b, 43c, 43d), via which fuel (BS) is traversed across the oxidant Flow direction (OR) extending

Direction component in the respective inlet passage (42) is einmischbar.

2. Burner (1) according to claim 1, wherein at least one of

Fuel supply pipes (43a, 43b, 43d) in the respective inlet passage (42) is arranged.

3. burner (1) according to claim 1 or 2, wherein at least one of

Fuel supply tubes (43c) in the oxidant flow direction (OR) is arranged directly in front of the respective inlet passage (42).

The burner (1) according to any one of claims 1 to 3, wherein at least one of the fuel supply pipes (43a, 43b, 43c) is disposed centrally in the respective intake passage (42) with respect to a longitudinal center axis (L) of the respective intake passage (42).

5. Burner (1) according to one of claims 1 to 4, wherein at least one of the fuel supply pipes (43 d) with respect to the longitudinal central axis (L) of the respective

Inlet passage (42) is arranged off-center in the respective inlet passage (42).

A burner (1) according to any one of claims 1 to 5, wherein at least one of the fuel supply pipes (43a, 43b, 43c, 43d) has a plurality of

Fuel discharge openings (44, 45) along the length of the

Fuel supply pipe (43a, 43b, 43c, 43d) are arranged at a distance from each other.

7. Burner (1) according to one of claims 1 to 6, wherein at least one of the Brennstoffzuführrohre (43a, 43b, 43c, 43d) has two fuel discharge openings (44, 45) with respect to the length of the Brennstoffzuführrohrs (43a, 43b, 43c, 43d) are arranged at the same position, so that over these two

Fuel output openings (44, 45) fuel (BS) with two opposite direction components from the fuel supply pipe (43a, 43b, 43c, 43d) can be output.

8. burner (1) according to claim 7, wherein seen in cross section of the respective Brennstoffzuführrohrs (43 a, 43 b, 43 c, 43 d) the two

Fuel discharge openings (44, 45) diametrically opposite each other or include respective longitudinal center axes (L1, L2) of the two fuel discharge openings (44, 45) an obtuse angle (a) with each other.

9. Burner (1) according to one of claims 1 to 8, wherein the

Fuel supply pipes (43 a, 43 b, 43 c, 43 d) each have a cylindrical cross-section or a wing-shaped cross-section.

10. Burner (1) according to one of claims 1 to 9, wherein the

Fuel supply pipes (43 a, 43 b, 43 c, 43 d) are each detachably mounted, so that each formed according to a predetermined Brennstoffeinmisch configuration Brennstoffzuführrohr (43 a, 43 b, 43 c, 43 d), if necessary, individually against a

Fuel supply pipe (43a, 43b, 43c, 43d) is interchangeable according to another predetermined Brennstoffeinmisch configuration.