EP1073864B1 - Combustion chamber assembly - Google Patents

Abstract

The invention relates to a combustion chamber assembly (1), especially an annular combustion chamber assembly for a gas turbine. One or more burners (3) comprise(s) a deflection means (17) on the opening (13) thereof. A combustion gas stream (14) flowing into the combustion chamber assembly (1) is deflected by said deflection means. As a result, an acoustic detuning is achieved, whereby the formation of combustion oscillation is suppressed.

Description

The invention relates to a combustion chamber arrangement with a Combustion chamber in which a burner is arranged. The combustion chamber is in particular an annular combustion chamber of a gas turbine.

DE 195 41 303 A1 describes a combustion chamber arrangement Gas turbine, into which a number of burners open. The gas turbine has a turbine shaft with a main axis on. Each burner is directed along a major axis. To achieve a particularly high degree of efficiency, the Major axis of each burner to produce a swirl Work equipment opposite the main axis of the turbine shaft tilted. By tilting the burner in this way a swirl-generating structural part can be disregarded.

DE 43 39 094 A1 describes a method for damping thermoacoustic vibrations in the combustion chamber of a gas turbine described. When burning fuels in the combustion chamber of a stationary gas turbine, an aircraft engine or the like may be due to the combustion processes instabilities or pressure fluctuations occur, the thermoacoustic under unfavorable conditions Excite vibrations, also called combustion vibrations become. These are not just undesirable Sound source, but can lead to impossibly high mechanical Load the combustion chamber. Such a thermoacoustic Vibration is actively damped by the fact that Injecting a fluid is the location of the combustion associated with it Heat release fluctuation is controlled.

US-A 4,967,562 discloses a turbine engine in which a particularly good fuel distribution in the combustion air is achieved. This is achieved in that Fuel sprayed from a nozzle onto a baffle becomes. The fuel is atomized and distributed well in the combustion air that flows past the baffle.

DE 196 15 910 A1 describes a burner arrangement in particular disclosed for a gas turbine. There are at least two Burner groups, each consisting of at least one burner same size and geometry for loading a combustion chamber intended. At least one burner group provides the Main burner. The other burner group is a fault burner group trained, with each of the interference burners opposite a main burner is inclined so that one of the main burner formed flame disc in its homogeneity and symmetry is disturbed. This can avoid pressure pulsations become.

The object of the invention is to provide a burner chamber arrangement, which in particular with regard to avoiding thermoacoustic Vibrations have a favorable behavior.

According to the invention, this object is achieved by a combustion chamber arrangement according to claim 1.

In such a combustion chamber arrangement, the location of the combustion of the fuel gas flowing out of the burner the deflection of the fuel gas flow with the aid of the deflecting means relocated. Such a shift has the consequence that the distances from the place of combustion to the combustion chamber wall change. This will make the acoustic system through Burner and combustion chamber is formed, acoustically out of tune. By a suitable orientation of the deflecting means, i.e. through a suitable selection of the direction of deflection, is thus the formation of a thermoacoustic oscillation can be suppressed.

The combustion chamber is preferably rotationally symmetrical about the Combustion chamber axis.

The orthogonal component preferably has one of zero different length on. A non-zero orthogonal component the inflow direction means the direction of the inflowing fuel gas flow not in the connection plane lies, i.e. the inflow direction is opposite to that Combustion chamber axis twisted. Through such an oblique inflow is particularly efficient at relocating the location of the Combustion possible, so that formation of a thermoacoustic Vibration is suppressed.

a) eine weitere Achsenkomponente , die zur Brennkammerachse parallel ist ,

b) eine weitere Ebenenkomponente, die senkrecht zur Brennkammerachse ist und in einer weiteren Verbindungsebene liegt, die durch den weiteren Aufpunkt und die Brennkammerachse aufgespannt ist,

c) eine weitere Orthogonalkomponente, die senkrecht zur Brennkammerachse und zur weiteren Ebenenkomponente ist.

A further burner is preferably provided, which has an opening for an inflow of a fuel gas flow along a further inflow direction into the combustion chamber, which defines the further inflow direction as a unit vector with a further point at the cross-sectional center of the opening of the further burner and with the unit length by three further component vectors is:

a) a further axis component which is parallel to the combustion chamber axis,

b) a further plane component which is perpendicular to the combustion chamber axis and lies in a further connection plane which is spanned by the further point of incidence and the combustion chamber axis,

c) a further orthogonal component which is perpendicular to the combustion chamber axis and to the further plane component.

Preferably, the axis component has one of the others Axis component of different lengths. The different Have lengths of the axis components of the two burners as a result that the respective inflow directions of the two Burner inclined or tilted differently to the combustion chamber axis are. Due to such a different inclination of the Inflow direction are the locations of the respective combustion to each other so adjustable that combustion vibrations emanating from these locations interfere with each other or even extinguish each other. In particular, such an arrangement for a Combustion chamber can be used with a variety of burners. Only two or more burners can be different be tilted relative to the combustion chamber axis. ever after the geometric design of the combustion chamber it is also advantageous, most or all of the burners different to tilt towards the combustion chamber axis.

A tilt of one burner or several burners compared the combustion chamber axis, which is in a different The length of the axis components of the burner can be expressed can also be combined with a twist. Such a twist corresponds to a non-zero orthogonal component, as mentioned above. The possibility a simultaneous twisting and tilting results in one wide choice for relocating the location of the Combustion. This results in a large number of configurations, from which one can be selected, the an acoustic detuning of the acoustic system Combustion chamber and burner guaranteed, i.e. with the one special great suppression of thermoacoustic vibrations is achieved. Such a selection can e.g. done by that tried different configurations and those with the best thermoacoustic behavior.

The further burner is preferably in the area of the mouth another deflecting means for deflecting one from the other Burner escaping fuel gas flow in the further inflow direction intended.

A combustion of the fuel gas stream from the is preferred Burner in an energy column and combustion of the fuel gas stream from the further burner in another energy column can be generated, which energy pillars each an extension represent the fuel gas flow, the orthogonal component and the other orthogonal component so big and are oriented so that the energy column is out of the burner and the energy column from the other burner overlap. An energy pillar is created by the burning of a pillar representing fuel gas stream emerging from the burner educated. Such an arrangement is mutually influencing Burns from two burners leads to one particularly efficient suppression of thermoacoustic vibrations. Overlay through the overlapping pillars of energy resulting from these pillars of pressure and Power fluctuations, the cause of a combustion vibration could be. Through this overlay, a Reduction or suppression of a combustion vibration reached.

The deflecting means is preferably a wall which projects into the combustion chamber and surrounds the mouth. The deflection means further preferably has a tear-off edge for eddies which can be caused by the fuel gas flow. Such a tear-off edge for vortices creates vortices in the fuel gas flow at the deflecting means. These vortices cause a return flow region for the fuel gas flow to form on the deflection means, in which a location for combustion is stabilized. Such stabilization makes it easier to control acoustic detuning of the system. In addition, fuel and combustion air are mixed still further by the swirling, which advantageously has the additional advantage that NO _x emission is reduced.

The deflecting means is preferably a hollow cylinder or a Hollow truncated cone with sloping top surfaces. These cover surfaces are imaginary surfaces, so they are not massive Surfaces made of one material. You will be through the edge of the shell of the hollow cylinder or hollow cone educated. A cover surface is therefore the imaginary connection surface of the rim facing the mouth and the other Cover area the imaginary connection area of the in the combustion chamber protruding edge. This is a particularly simple and effective execution of the deflecting means.

The combustion chamber is preferably an annular combustion chamber, in particular for a gas turbine. The annular combustion chamber has a complex one Geometry on. In such a system is the occurrence thermoacoustic vibrations unpredictable and special difficult to control. By means of deflection such a system in a structurally simple manner and Acoustically so detuned that there is a suppression results in thermoacoustic vibrations. Preferably, the Annular combustion chamber on a variety of burners, being for the predominant part of these burners, especially for all Burner, each a deflecting means in the area of a respective one Mouth is arranged.

Figur 1

einen Längsschnitt durch einen in einer Brennkammer angeordneten Brenner mit einem Umlenkmittel,

Figur 2

den Brenner aus Figur 1 mit einem anders ausgeführten Umlenkmittel,

Figur 3

eine Ringbrennkammer einer Gasturbine,

Figur 4

eine Darstellung einer Komponentenaufteilung für eine Einströmrichtung,

Figur 5

eine der Figur 4 entsprechende Darstellung aus einer anderen Blickrichtung,

Figur 6

einen Längsschnitt durch eine Ringbrennkammer einer Gasturbine und

Figur 7

einen Querschnitt durch eine Ringbrennkammer einer Gasturbine.

The invention is illustrated by way of example and partly schematically with reference to the drawing. Show it:

Figure 1

2 shows a longitudinal section through a burner arranged in a combustion chamber with a deflection means,

Figure 2

1 with a differently designed deflection means,

Figure 3

an annular combustion chamber of a gas turbine,

Figure 4

a representation of a component division for an inflow direction,

Figure 5

4 shows a representation corresponding to FIG. 4 from a different viewing direction,

Figure 6

a longitudinal section through an annular combustion chamber of a gas turbine and

Figure 7

a cross section through an annular combustion chamber of a gas turbine.

The same reference numerals have in the different figures same meaning.

Figure 1 shows a longitudinal section through a burner 3. Der Burner 3 is designed as a hydride burner, i.e. he points as Premix stage a ring channel 5, which concentrically one Pilot burner 7 surrounds. The burner is on a combustion chamber wall 9 a combustion chamber 11 arranged. In the ring channel 5 a fuel-air mixture 14A is conducted. This unites with a fuel-air mixture 14B from the pilot burner 7 to a fuel gas stream 14. The fuel gas stream 14 emerges a mouth 13 along a mouth direction 15 from the Burner off. The mouth 13 is of a hollow cylindrical shape Deflection means 17, 17A surrounded. The deflecting means 17, 17A has imaginary top surfaces 16A inclined to one another, 16B. The deflecting means is therefore not rotationally symmetrical around the mouth direction 15. The deflecting means 17, 17A could also have a preferred direction in cross section, ie not a circular cross-section as in the example shown here but e.g. have an elliptical cross section. It could also be a wall that the mouth 13 does not completely but only partially surrounds. By the deflecting means 17 becomes the fuel gas stream 14 from the mouth direction 15 deflected in an inflow direction 19. The deflecting agent 17, 17A has a tear-off edge 18. At this tear-off edge 18 14 vortices 20 are formed in the fuel gas stream this vortex 20 becomes a return flow area for the fuel gas flow 14 generated. This has the consequence that in these vertebrae 20 a combustion site is stabilized. By the deflecting means 17, 17A becomes the location of the combustion of the fuel gas stream 14 displaced relative to the combustion chamber wall 9, opposite an inflow along the direction of the mouth 15. A such a shift means that the acoustic system, which is formed from the burner and combustion chamber, acoustically is out of tune. Such an acoustic detuning results there is a suppression of thermoacoustic vibrations. The creation of a stable combustion site with the help of Vortex 20 simplifies the controllability of such acoustic detuning.

FIG. 2 shows the burner from FIG. 1 with a different design Deflection means 17, 17B. This deflection means 17, 17B is designed as a truncated cone. It also points to each other inclined, imaginary top surfaces 16A, 16B. The Advantages of this arrangement correspond to the advantages of the arrangement from Figure 1.

Figure 3 shows in perspective a combustion chamber arrangement 1, consisting from a combustion chamber designed as an annular combustion chamber 11 of a gas turbine and therein along a circumferential direction arranged burners 3. The combustion chamber 11 is rotationally symmetrical about a combustion chamber axis 25 and has an outer Wall 21 and an inner wall 23. The outer wall 21 and the inner wall 23 enclose an annular burner chamber 24. The inner surface of the outer wall 21 and the outer surface the inner wall 23 are with a refractory inner lining 27 provided.

1. Eine Achsenkomponente 35, 36, mit einer Länge AL, BL welche parallel zur Brennkammerachse 25 ist.

2. Eine Ebenenkomponente 33, 34, welche senkrecht auf der Achsenkomponente 35, 36 steht und in einer Verbindungsebene 31 liegt, die durch den Aufpunkt A und die Brennkammerachse 25 aufgespannt ist.

3. Eine Orthogonalkomponente 37, 38, welche senkrecht sowohl auf der Achsenkomponente 35, 36 als auch auf der Ebenenkomponente 33, 34 steht.

FIG. 4 shows how the inflow direction 19, 41 can be represented as a unit vector with the unit length L by three components. A burner 3, 39 has an opening direction 15, 43. A deflection means 17, 45 deflects a fuel gas stream emerging from the burner 3, 39 in an inflow direction 19, 41. This inflow direction 19, 41 is defined by a unit vector placed at an apex A. The point A lies in the centroid of the outer cover surface 16A located in the combustion chamber. The unit vector has the following three component vectors:

1. An axis component 35, 36 with a length AL, BL which is parallel to the combustion chamber axis 25.

2. A plane component 33, 34 which is perpendicular to the axis component 35, 36 and lies in a connecting plane 31 which is spanned by the point A and the combustion chamber axis 25.

3. An orthogonal component 37, 38, which is perpendicular to both the axis component 35, 36 and the plane component 33, 34.

This orthogonal component 37, 38 is a circle with a cross shown to illustrate that the orthogonal component 37, 38 points into the plane of the drawing.

Figure 5 shows the burner arrangement of Figure 4 from a Viewing direction along the combustion chamber axis 25. In this illustration is the orthogonal component 37, 38 in length OL visible. The axis component 35, 36 points from the plane of the drawing out.

In Figure 6 is a longitudinal section through an annular combustion chamber executed combustion chamber 11 of a not shown Gas turbine shown. In the upper half of the longitudinal section mouths a burner 3 along a mouth direction 15 in the combustion chamber 11 is turned off by a deflecting means 17 the fuel gas stream exiting the burner 3 in an inflow direction 19 redirected. In the case shown here, the orthogonal component 37 the inflow direction 19 zero, so that the inflow direction 19 intersects the combustion chamber axis 25 and forms an angle 46 with the combustion chamber axis 25. In the Another burner opens into the lower half of the longitudinal section 39 along a further opening 49 into the combustion chamber 11. Another deflection means 45 turns one off the further burner 39 escaping fuel gas flow into a deflected further inflow direction 41. In the example shown here also intersects the further inflow direction 41 Combustion chamber axis 25, namely at an angle 48. The angle 46 of the inflow direction 19 with the combustion chamber axis 25 is different from the angle 48 of the further inflow direction 41 with the combustion chamber axis 25. This is equivalent to the fact that the axis component 35 of the inflow direction 19th a different length AL than the further axis component 36 of the has another inflow direction 41. The burner 3 and the further burners 39 thus point differently against the Combustion chamber axis 25 has tilted inflow directions 19, 41. This different tilting ensures that Burning vibrations from the respective places of the Combustion of fuel gas from burner 3 or of fuel gas originate from the further burner 39, overlap so that thermoacoustic vibrations are suppressed. The case shown here that the orthogonal component or other orthogonal components are zero, only serves a simplified one Presentation. The orthogonal component and / or the further orthogonal components can also differ from zero be what an additional rotation of the inflow direction 19 or the further inflow direction 41 with respect to the combustion chamber axis 25 corresponds.

Figure 7 shows a cross section through an annular combustion chamber executed combustion chamber 11 of a gas turbine. Along one A plurality of burners 3, 39 are arranged in a circle. Each of these burners 3, 39 points in the region of its mouth a deflecting means 17, 45. For two neighboring ones Burner 3, 39, the deflection means 17, 45 are aligned so that each is characterized by a columnar combustion forming fuel gas emerging from the burner 3, 39 Superimpose energy columns 47, 49 in pairs. In order to The pressure fluctuations that are in the energy columns also overlap 47, 49 arise and the one cause for the emergence can be a combustion vibration. By a such superimposition becomes the formation of combustion vibrations suppressed.

Claims (11)

1. Combustion chamber arrangement (1)

   with a combustion chamber (11) which has a combustion chamber axis (25) and in which

   there is arranged a burner (3) which

   has an opening (13) for a combustion gas stream (14) to flow into the combustion chamber along an opening direction (15),

   a deflecting means (17) being arranged in the region of the opening (13) for deflecting the combustion gas stream (14) into an inflow direction (19) which differs from the opening direction (15) and the deflecting means (17) being a wall protruding into the combustion chamber and surrounding the opening (13),

   the inflow direction (19) being defined as a unit vector, with a reference point (A) at the cross-sectional centre point of the opening (13) and a unit length (L), by three component vectors (33, 35, 37):

   a) an axial component (35), which is parallel to the combustion chamber axis (25),

   b) a planar component (33), which is perpendicular to the axis of symmetry (25) and lies in a connecting plane (31) which is defined by the reference point (A) and the combustion chamber axis (25),

   c) an orthogonal component (37), which is perpendicular to the combustion chamber axis (25) and to the planar component (33).
2. Combustion chamber arrangement (1) Claim 1,

   in which the combustion chamber (11) is rotationally symmetrical about the burner axis (25).
3. Combustion chamber arrangement (1) as claimed in Claim 1 or 2, the orthogonal component (37) having a length (0L) different from zero.
4. Combustion chamber arrangement (1) as claimed in Claim 1, 2 or 3,

   in which a further burner (39) is provided, which further burner has an opening (40) for a combustion gas stream to flow into the combustion chamber (11) along a further inflow direction (41), which further inflow direction (41) is defined as a unit vector, with a further reference point (B) at the cross-sectional centre point of the opening of the further burner (39) and with the unit length (L), by three further component vectors:

   a) a further axial component (36), which is parallel to the combustion chamber axis (25),

   b) a further planar component (34), which is perpendicular to the combustion chamber axis (25) and lies in a further connecting plane (31A), which is defined by the further reference point (B) and the combustion chamber axis (25),

   c) a further orthogonal component (38), which is perpendicular to the combustion chamber axis (25) and to the further planar component (34).
5. Combustion chamber arrangement (1) as claimed in Claim 4, in which the axial component (35) has a length (AL) which is different from a length (BL) of the further axial component (36).
6. Combustion chamber arrangement (1) as claimed in Claim 4 or 5, in which a further deflecting means (45), for deflecting a combustion gas stream emerging from the further burner (39) into the further inflow direction (41), is provided in the region of the opening (40) of the further burner (39).
7. Combustion chamber arrangement (1) as claimed in Claim 4, 5 or 6, in which a combustion of the combustion gas stream (14) from the burner (3) in an energy column (47) and a combustion of the combustion gas stream (14) from the further burner (39) in a further energy column (49) can be produced, which energy columns (47, 49) respectively represent an extension of the combustion gas stream (14), with the orthogonal component (37) and the further orthogonal component (38) being of such a magnitude and such an orientation that the energy column (47) from the burner (3) and the energy column (49) from the further burner (39) overlap.
8. Combustion chamber arrangement (1) as claimed in Claim 1, in which the deflecting means (17) is a hollow cylinder (17A) or a hollow truncated cone (17B) with covering surfaces (16A, 16B) sloping with respect to each other.
9. Combustion chamber arrangement (1) as claimed in one of the preceding claims, in which the deflecting means (17) has a breakaway edge for swirls (20), which can be induced by the combustion gas stream (14).
10. Combustion chamber arrangement (1) as claimed in one of the preceding claims, in which the combustion chamber (11) is an annular combustion chamber, especially for a gas turbine.
11. Combustion chamber arrangement (1) as claimed in Claim 10, with a multiplicity of burners (3, 39), a deflecting means (17, 45) being arranged in each case in the region of a respective opening (13, 40) for the majority of these burners (3, 39), in particular for all the burners (3, 39).

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