WO2009019114A2

WO2009019114A2 - Burner for a combustion chamber of a turbine group

Info

Publication number: WO2009019114A2
Application number: PCT/EP2008/059350
Authority: WO
Inventors: Jaan Hellat; Adnan Eroglu; Jan Cerny; Douglas Anthony Pennell
Original assignee: Alstom Technology Ltd
Priority date: 2007-08-07
Filing date: 2008-07-17
Publication date: 2009-02-12
Also published as: WO2009019114A3

Abstract

The invention relates to a burner (1) for a combustion chamber of a turbine group, comprising a swirl generator (2), a mixer (3), and a lance (4) for introducing pilot fuel into a combustion chamber (10). In order to be able to better stabilize the combustion, the lance (4) comprises a plurality of concentrically disposed tubes (25, 26), a central inner tube (25) comprising a central channel (27) for liquid fuel and at least one axial outlet opening (28) on the end (15) of the lance, a hollow-wall outer tube (26) encompassing the inner tube (25) and forming an inner ring channel (30) and comprising at least one outer channel (36, 37) for gaseous fuel in the hollow wall (33) thereof, the inner ring channel (30) at the end (15) of the lance ending axially open and serving to guide air.

Description

Burner for a combustion chamber of a turbo group

Technical area

The present invention relates to a burner for a combustion chamber of a turbo group, in particular in a power plant.

State of the art

Such burners have a swirl generator, which encloses a burner interior on the input side and which has at least one air inlet tangential to a longitudinal central axis of the burner. Furthermore, such a burner comprises a mixer, which surrounds the burner interior on the output side and which has an outlet opening open to a combustion chamber of the combustion chamber. In addition, such a burner may be equipped with a lance for introducing pilot fuel into the combustion chamber. The lance is arranged coaxially to the longitudinal central axis of the burner and extends from a burner head, starting in the burner inside.

One problem with such burners is the risk of flashback from the combustion chamber into the burner interior. Such flashbacks are due to instabilities in the combustion process.

Presentation of the invention

This is where the present invention begins. The invention, as characterized in the claims, deals with the problem of providing a burner of the type mentioned in an improved embodiment, which is characterized in particular by an increased stability of the combustion process in the combustion chamber.

This problem is solved according to the invention by the subject matter of the independent claim. Advantageous embodiments are the subject of the dependent claims.

The invention is based on the general idea of constructing the lance from a plurality of tubes arranged concentrically with one another in order to be able to independently supply air, liquid fuel and gaseous fuel. By such a configuration of the lance, the respective

Pilot operation can be better adapted to current operating conditions of the combustion chamber, whereby the combustion reaction can be stabilized in the combustion chamber. For example, when starting or starting up the combustion chamber, a pilot operation with exclusively liquid pilot fuel can be carried out. In the transition to the nominal operating state, which usually no

Pilot fuel is supplied via the lance, gaseous pilot fuel can be increasingly supplied. At the same time, the supply of the liquid pilot fuel can be reduced successively. Finally, the supply of gaseous pilot fuel can be successively reduced. Likewise, it is conceivable to supply the supply of pilot fuel for a short-term increase in output of the combustion chamber, wherein here also, depending on various parameters, such as temperature and pressure, liquid or gaseous pilot fuel or any combination thereof can be introduced. Due to the increased variability of the supply of different pilot fuels, the stability of the combustion reaction in the combustion chamber can be improved.

The use of an inner annular channel to supply air is advantageous in several ways. On the one hand, the lance can be cooled with the air. On the other hand, the air prevents the penetration of the flames in the unused central channel and in the unused at least one outer channel, whereby a flushing of the respective channel is dispensable in the event that either only liquid pilot fuel or only gaseous pilot fuel is supplied.

According to an advantageous embodiment, the lance may be designed so that it extends at least in the pilot operation of the burner as far into the burner inside, that a flame front of a running in the combustion chamber combustion reaction at least partially into an enclosed by an outlet end portion of the mixer end portion of the burner interior extends into it. By moving a part of the flame front into the interior of the burner, the pilot operation is simplified due to the reduced distance between the free-standing lance end and the flame front. As a result, the stability of the flame front can be increased. Furthermore, the flame front, at least in the part running within the respective burner, is largely decoupled from interactions which, in the case of a combustion chamber equipped with a plurality of burners, are caused by the other burners via the common combustion chamber come. The reduction of such interactions stabilizes the flame front. Furthermore, this design makes it easier to transfer results from a single-burner test bench system to an industrial plant that is regularly equipped with multiple burners.

Other important features and advantages of the burner according to the invention will become apparent from the subclaims, from the drawings and from the associated description of the figures with reference to the drawings.

Brief description of the drawings

Preferred embodiments of the invention are illustrated in the drawings and will be described in more detail in the following description, wherein like reference numerals refer to the same or similar or functionally identical components. Show, in each case schematically,

1 is a greatly simplified longitudinal section through a burner,

2 is a view as in Fig. 1, but in another embodiment,

3 is a view as in FIGS. 1 and 2, but with the lance extended,

4 is a view as in FIGS. 1 and 2, but with a more detailed representation of the lance,

Fig. 5 is a view as in Fig. 4, but in another embodiment of the lance. Ways to carry out the invention

According to FIGS. 1 to 5, a burner 1 comprises a swirl generator 2, a mixer 3 and a lance 4. The burner 1 forms in the mounted state a component of a combustion chamber, not shown here, of a turbo group, which is arranged in particular in a power plant.

The swirl generator 2 encloses an input-side section of a burner interior 5 and has at least one air inlet 6, which extends tangentially with respect to a longitudinal central axis 7 of the burner 1. In the examples shown, the swirl generator 2 is configured conical. The respective air inlet 6 forms a longitudinal slot along the cone sheath. Preferably, a plurality of such air inlets 6 are arranged distributed in the circumferential direction. As a result, the air can penetrate tangentially into the burner interior 5, whereby it is acted upon by a twist. In the examples shown, the swirl generator 2 also has a fuel inlet 8, via which gaseous fuel can be introduced into the burner interior 5. For example, this fuel inlet 8 consists of several, along the generatrix of the conical swirl generator 2 extending rows of individual inlet openings through which the fuel gas can enter the burner interior 5. In this case, the fuel inlet 8 may be aligned tangentially to increase the swirl effect. Likewise, the fuel inlet 8 may generate some radial component to enhance mixing with the air.

The mixer 3 encloses an output-side section of the burner interior 5 and has an outlet opening 9, which leads to a combustion chamber 10 of FIG Combustion chamber is open. The mixer 3 comprises, for example, a tubular body 11, which is connected via a tubular transition piece 12 to the swirl generator 2 and which carries an outlet flange 13 with the outlet opening 9. About the outlet 13, the burner 1 can be connected to the combustion chamber. Suitably, the mixer 3 is cylindrically shaped.

The lance 4 is used for introducing pilot fuel into the combustion chamber 10. For this purpose, the lance 4 is arranged coaxially to the longitudinal central axis 7. Furthermore, at least in a pilot operation of the burner 1, the lance 4 extends into the burner interior 5 from a burner head 14, which essentially forms the tip of the conical swirl generator 2. The lance 4 thus starts from the burner head 14 and ends with a lance end 15 freestanding in the burner interior. 5

In the embodiment shown in FIG. 1, a part of a flame front 16 is also shown, which forms during operation of the combustion chamber by the combustion reaction taking place in the combustion chamber 10. As can be seen, part of this flame front 16 projects into the burner interior 5, into an end section of the burner interior 5, which is enclosed by an outlet-side end region of the mixer 3. In the example shown, the flame front 16 remains within the section of the burner interior 5 enclosed by the outlet flange 13. Such a course of the flame front 16, in which a part of the flame front 16 projects through the outlet opening 9 into the burner interior 5, is characterized by a particular embodiment and / or or arrangement of the lance 4 reached. In the pilot operation of the burner 1, the lance 4 extends with its free-standing end 15 comparatively far into the burner interior 5, namely to the extent that a part of the flame front 16 extends into the burner interior 5 inside. Thus the lance 4 so deep in the Burner interior 5 may protrude in the direction of the outlet opening 9, the lance 4 must be designed accordingly so that it has the required axial length. In the embodiments shown in FIGS. 1, 2, 4 and 5, the lance 4 is positioned in the burner 1 so that its free-standing end 15 is located in a portion of the burner interior 5 enclosed by the mixer 3. In other words, the lance 4 extends into the mixer 3. In this case, the lance 4 with its free-standing end 15 in the axial direction to about half of the mixer 3 or even beyond in the mixer 3 extend into it. For example, a distance 17 entered in FIG. 2, which the freestanding lance end 15 has from the outlet opening 9, is greater than 25% or less than 50% of a distance 18 that an outlet end 19 of the swirl generator 2 has from the outlet opening 9. The distance 17 between outlet opening 9 and lance end 15 is preferably in a range of 25% to 50% of the distance 18 prevailing between outlet opening 9 and outlet-side end 19.

According to FIG. 2, an inlet tube 20, which extends coaxially with the lance 4, can be arranged on the burner head 14. This inlet tube 20 projects in the axial direction into a portion of the burner interior 5 enclosed by the swirl generator 2. This inlet tube 20 may be an annular

Form inlet channel 21 for liquid fuel. The inlet channel 21 has at least one axially oriented outlet opening 22. By virtue of these at least one axial outlet opening 22, the liquid fuel can enter the burner interior 5 substantially in the axial direction, as indicated by arrows 48. The burner 1 can thus be operated with fuel gas and / or with liquid fuel. Preferably, a plurality of such axial outlet openings 22 are arranged at the end of the inlet tube 20 ending in the burner interior 5. According to a preferred embodiment, the lance 4 may be arranged in the axial direction adjustable on the burner head 14. Thus, the axial position of the free-standing lance end 15 within the burner interior 5 is adjustable. In particular, this allows the position of the part of the flame front 16 projecting into the burner interior 5 to be adjusted. With the help of the longitudinally adjustable lance 4, the burner 1 can be adapted to operating parameters of the combustion chamber, which allows stabilization of the combustion process. The lance 4 can thus be retracted more or less deep into the burner interior 5, depending on demand, or extend more or less far out of the burner interior 5. Fig. 3 shows a situation in which the lance 4 is largely extended from the burner interior 5. The lance end 15 expediently ends at the inside of the burner head 14 facing the burner interior 5. In FIG. 3, the lance 4 is fully extended for a simplified illustration. It can be retracted according to an arrow 23 back into the burner interior 5. In the configuration shown in FIG. 3, the flame front 16 is arranged completely outside the burner interior 5 and is located downstream of the outlet opening 9 with respect to the flow direction of the burner 1.

In Fig. 3 is a simplified velocity profile 24 is shown, the

Distribution of the flow velocity along the cross section of the burner 1 within the mixer 3 represents. Visible, the flow has a significant maximum in the absence of lance 4 in the center. By retracting the lance 4 into the described area within the mixer 3, the flow velocity in the center of the cross section of the mixer 3 is inevitably reduced. At the same time, the speed is correspondingly increased outside the lance 4, ie in the edge region of the cross section, in order to ensure a constant volume flow. The reduction of the central flow velocity allows the flame front 16 to hike upstream. With appropriate positioning and configuration of the lance 4, the flame front 16 projects partially into the burner interior 5, as shown in FIG.

In Figs. 4 and 5, the lance 4 is also shown cut. The following detailed description of the lance 4 applies in particular to the embodiments of FIGS. 1 to 3.

4 and 5, the lance 4 has a plurality of concentrically arranged tubes, namely a central inner tube 25 and an outer tube 26. The inner tube 25 includes a central channel 27 and has at least the free-standing lance end 15 axially oriented outlet opening 28. The central channel 27 serves to supply liquid fuel to the at least one outlet opening 28. In the example, the inner tube 25 is in the region of the outlet opening 28 with a nozzle-shaped

Cross-sectional constriction 29 equipped, which allows the formation of an intense liquid jet. This liquid fuel jet is indicated in FIGS. 4 and 5 by an arrow 32. The outer tube 26 is sized so that it surrounds the inner tube 25 to form an inner annular channel 30. This inner annular channel 30 is axially open at the end of the lance 15 and thus opens into the burner interior 5. The inner annular channel 30 serves to guide air, which can emerge from the inner annular channel 30 in the axial direction according to an arrow 31.

The outer tube 26 is configured hollow-walled, that is, the outer tube 26 has a hollow wall 33 with an inner wall 34 and a radially spaced outer wall 35. In the hollow wall 33, the outer tube 26 includes at least one outer channel 36 (Fig 37 (Figure 5). This at least one outer channel 36, 37 serves to supply gaseous fuel. The outer channel 36, 37 may be configured as an annular channel, which is simply formed between the two walls 34, 35 of the wall 33. According to FIG. 4, this outer annular channel 36 or 37 can have at least one axially oriented outlet opening 38 on the lance end 15, as a result of which an essentially axially oriented injection of fuel gas can be achieved in accordance with an arrow 39. Additionally or alternatively, in an in Fig. 5 marked with a brace lance end portion 40, which has the free-standing lance end 15, an array of a plurality of radial outlet openings 41 may be provided. These radial outlet openings 41 are preferably formed in the outer wall 35 of the hollow wall 33 of the outer tube 26. As a result, a substantially radially oriented injection of the fuel gas into the burner interior 5 can be realized. The thus radially injected gaseous fuel is thereby deflected according to arrows 42 due to the prevailing axial flow in the burner interior in the axial direction.

In order to be able to selectively realize the axial injection 39 and the radial injection 42 in the case of an outer annular channel 36 or 37, a corresponding control can be provided which, for example, operates with a sleeve-shaped control element which lies in a first position in front of the radial outlet openings 41. while it locks in a second position, the at least one axial outlet opening 38. Preferably, a plurality of circumferentially distributed axial outlet openings 38 are arranged at the axial end of the outer tube 26.

Alternatively, in the hollow wall 33 at least a first outer channel 36 may be formed, which leads at the lance end 15 to the at least one axial outlet opening 38. In addition, in the hollow wall 33 at least one second outer channel 37 may be formed which leads to at least one of the radial outlet openings 41 formed in the lance end section 40. For example, FIG. 4 shows a section through the first outer channels 36, while FIG. 5 shows a section through the second outer channels 37. The first and second outer channels 36, 37 may be connected on the input side to various, independently operable supply devices or control devices. This makes it possible to selectively introduce the introduction of the gaseous fuel only through the at least one axial outlet opening 38 or only through the at least one radial outlet opening 41 or both through the at least one axial outlet opening 38 and through the at least one radial outlet opening 41.

In the embodiments shown in FIGS. 4 and 5, the inner tube 25 projects axially beyond the outer tube 26. In this way, a certain separation of media during operation of the lance 4 for injecting the liquid fuel and for injecting the fuel gas can be achieved. This media separation can also be assisted by the injected air 31.

In the embodiments shown here, moreover, the inlet pipe 20 arranged at the burner head 14 is hollow-walled, so that it has a hollow wall 43 with an inner wall 44 and an outer wall 45. The hollow-walled inlet tube 20 is here also dimensioned so that it encloses the lance 4 and the outer tube 26 to form an axially open annular channel 46. Through this annular channel 46 47 air can be injected into the burner interior according to an arrow. In this way, an effective cooling of the lance in the region of the burner head 14 can be achieved. The inlet channel 21, which serves to introduce the liquid fuel according to arrows 48, is formed in the hollow wall 43 and may in particular also be designed annular. Figs. 4 and 5 show another feature. In these embodiments, a wall 49 of the mixer 3 is provided with a film cooling 50. Such a film cooling 50 is realized for example by means of a plurality of cooling holes 51 which pass through the corresponding wall 49 and can be flowed through by coolant, which applies to the side of the wall 49 facing the burner interior 5 and thereby generates a cooling film protecting the wall 49. As a coolant is usually air. The cooling holes 51 may be set in the main flow direction of the burner 1 as shown here to enhance the formation of a cooling film.

LIST OF REFERENCE NUMBERS

1 burner

2 swirl generators

3 mixers

4 lance

5 burner inside

6 air intake

7 longitudinal central axis

8 fuel gas inlet

9 outlet opening

10 combustion chamber

1 1 tubular body

12 transition piece

13 outlet flange

14 burner head

15 freestanding lance end

16 flame front

17 distance between 9 and 4

18 distance between 9 and 19

19 downstream end of 2

20 inlet pipe

21 inlet channel

22 inlet opening

23 retraction movement of 4 24 speed profile

25 inner tube

26 outer tube

27 central channel

28 outlet opening

29 nozzle

30 inner ring channel

31 air flow

32 liquid fuel flow

33 hollow wall

34 inner wall

35 outer wall

36 (first) outer channel

37 (second) outer channel

38 axial outlet opening

39 fuel gas flow

40 lance end section

41 radial outlet opening

42 fuel gas flow

43 hollow wall

44 inner wall

45 outer wall

46 ring channel

47 airflow

48 liquid fuel flow

49 wall of 3

50 film cooling

51 cooling hole

Claims

claims

1. Burner for a combustion chamber of a turbo group, - with a swirl generator (2) which surrounds a burner interior (5) on the input side and at least one with respect to a longitudinal central axis (7) of the burner (1) tangential air inlet (6), with a mixer (3), which surrounds the burner interior (5) on the output side and which has an outlet opening (9) open to a combustion chamber (10) of the combustion chamber, with a lance (4) for introducing pilot fuel into the combustion chamber (10), which is coaxial with Longitudinal axis (7) of the burner (1) is arranged and extends at least in a pilot operation of the burner (1) with a lance end (15) from a burner head (14) into the burner interior (5) into free standing, wherein the lance (4 ) has a plurality of concentrically arranged tubes (25, 26), wherein a central inner tube (25) has a central channel (27) for liquid

Contains fuel and at the lance end (15) at least one axial outlet opening (28), wherein a hollow outer tube (26) surrounds the inner tube (25) to form an inner annular channel (30) and in its hollow wall (33) at least one outer channel (36, 37) for gaseous fuel contains, - wherein the inner annular channel (30) at the end of the lance (15) ends axially open and serves to guide air.

2. Burner according to claim 1, characterized in that the outer channel (36, 37) in the hollow wall (33) of the outer tube (26) is designed as an annular channel which has at least one axial outlet opening (28) at the lance end (15) and / or in a lance end (40) having the lance end (15) has a plurality of radial outlet openings (41).

3. Burner according to claim 1, characterized in that in the hollow wall (33) of the outer tube (26) at least one (first) outer channel (36) is formed, which at the lance end (15) has at least one axial outlet opening (28) , and / or - that in the hollow wall (33) of the outer tube (26) at least one

(Second) outer channel (37) is formed, which has a plurality of radial outlet openings (41) in a lance end (15) having lance end portion (40).

4. Burner according to one of claims 1 to 3, characterized in that the inner tube (25) projects axially beyond the outer tube (26).

5. Burner according to one of claims 1 to 4, characterized in that the burner head (14) an inlet tube (20) is arranged coaxially with the lance (4) in the swirl generator (2) enclosed portion of the burner interior (5) protrudes and an annular inlet channel (21) for forms liquid fuel having at least one axial outlet opening (22).

6. Burner according to claim 5, characterized in that the inlet tube (20) is configured hollow-walled, that the inlet tube (20) surrounds the lance (4) to form an axially open annular channel (46) for air, that the inlet channel (21). is formed in the hollow wall (43) of the inlet pipe (20).

7. Burner according to one of claims 1 to 6, characterized in that a wall (49) of the mixer (3) is equipped with film cooling (50).

8. Burner according to one of claims 1 to 7, characterized in that the lance (4) is configured and / or arranged so that it at least in pilot operation of the burner (1) hineinerstreckt so far into the burner interior (5) that a flame front (16) of a combustion reaction taking place in the combustion chamber (10) extends at least partially into an end section of the burner interior (5) enclosed by an outlet-side end region of the mixer (3).

9. Burner according to one of claims 1 to 8, characterized in that the lance (4) arranged at least in the pilot operation of the burner (1) with its outlet end (15) in a mixer (3) enclosed portion of the burner interior (5) is, in particular a distance (17) of the Lanzenendes (15) from the outlet opening (9) may be greater than 25% or less than 50% of the distance (18), the one outlet end (19) of the swirl generator (2) from the outlet opening (9).

10. Burner according to one of claims 1 to 9, characterized in that the lance (4) is arranged longitudinally adjustable on the burner head (14) so that they more or less deep into the burner interior (5) depending on demand and from this more or less far is extendable.