EP2588805B1 - Burner - Google Patents

Description

The present invention relates to a burner assembly for a gas turbine having at least one combustion chamber, the burner assembly comprising a centrally located pilot burner and a plurality of main burners surrounding the pilot burners, each of the main burners comprising a cylindrical housing having a lance centrally disposed therein and having a liquid fuel fuel channel wherein the lance is supported by swirl vanes on the housing and in the direction of the combustion chamber, an attachment is arranged on the lance, wherein at least one liquid fuel nozzle is preferably arranged in the attachment downstream of the swirl blades and connected to the fuel channel.

During operation of the gas turbine, the combustion chamber is supplied with compressed air from the compressor. The compressed air is mixed with a fuel, such as oil or gas, and the mixture burned in the combustion chamber. The hot combustion exhaust gases are finally supplied as a working medium via a combustion chamber outlet of the turbine, where they transmit momentum to the blades under relaxation and cooling and thus do work. The vanes serve to optimize the momentum transfer.

In combustion engines, in particular those which are operated with two different fuels, for example, an injection of the fuel oil via swirl generator, in which the oil is mixed with air. For better mixing of oil and air, the oil within the nozzles used for the injection into a swirling motion is added. This oil nozzle is also referred to as a pressure-swirl nozzle.

Especially with machines with two different fuels, the oil nozzles can not be arranged so that the Mixing of the fuel with the air leads to an optimal result in terms of pressure pulsations.

From the documents US 3 904 119 A . US 6 141 967 A . WO 99/19670 A2 . EP 0 870 989 A2 Gas turbines are already known which show various features of the invention. A generic arrangement is in each case from the JP 2002 276943 A . US 2004/060297 A1 . JP H09 303776 A known.

The object of the present invention is therefore to provide a burner assembly of the type mentioned, which solves the above problem.

The object is achieved by a burner assembly according to claim 1.

The further subclaims contain advantageous embodiments of the invention.

Through the use of full jet nozzles, the setting of the fuel profile, in particular the radial fuel distribution can be changed very effectively. Full jet nozzles produce a full jet without disturbing turbulence. Compared to the pressure swirl nozzle, the full jet nozzle has the advantage that a higher fuel pressure is converted into a greater penetration depth. In pressure-swirl nozzles smaller drops are formed by a higher pre-pressure, which in turn penetrate less effectively. It follows that a much higher pressure is required for an increased penetration depth for pressure-swirl nozzles than for full-jet nozzles. This makes it possible with the full jet nozzle, for example, expensive pumps, which can provide more fuel supply pressure, or avoid piping systems with high pressure levels.

The jet nozzle may be configured as a bore extending in the attachment.

The liquid fuel nozzles designed as full jet nozzles according to the invention have a length to diameter ratio of at least 1.5. In accordance with the invention, this provides a liquid fuel jet emerging from the nozzle which optimally mixes with the air twisted by the swirl vanes. The length to diameter ratio of at least 1.5 ensures that, for example, vapor bubble formation in the liquid fuel jet is reliably avoided and a sufficiently low level of turbulence in the jet is maintained. This also ensures a sufficient penetration depth of the fuel jet and a good mixing behavior of the jet with the passing air. Advantageously, the length to diameter ratio is selected in a range of 6 to 14. A liquid fuel jet produced by a full jet nozzle with this length to diameter ratio behaves particularly optimally with regard to penetration depth and mixing properties.

In each case at least one such full jet nozzle can be arranged in the attachment both in the main burners (which can also be called main swirl generators) and in the pilot burner. The attachment arranged on the lance is a component which is different from the lance.

For the invention, it is important to consider the overall concept of the combustion system consisting of a central pilot burner with pilot cone and the main burners arranged around the pilot burner. In principle, the penetration depth of the fuel can be selectively varied by adjusting the nozzle diameter in order to achieve an advantageous radial fuel profile. The interaction with the central pilot burner requires In addition, the optimization of the fuel and droplet size distribution, especially as a function of the relative orientation of the injection position to the pilot cone, so as to set the ignition of the fuel / air mixture with an advantageous time delay. This time delay between Eindüsposition and the combustion of the fuel is largely responsible for the formation of thermoacoustic feedback, from which combustion chamber pulsations may arise.

In addition to the radial fuel profile, the local droplet size distributions and air / fuel ratios as well as the axial injection position are the main influencing parameters to be adapted as a function of the local flow conditions of the combustion air. It is achieved according to the invention by means of suitably designed full jet nozzles thus optimizing the fuel and droplet size distribution in the circumferential direction to achieve the ignition of the fuel / air mixture at an advantageous time delay.

An advantageous embodiment of the invention may provide that the attachment an center attachment axis, and the at least one solid jet nozzle comprises a central axis and the at least one solid jet nozzle is arranged in the attachment so that the central axis of the at least one full jet nozzle at an angle of 90 ° to the center attachment axis of the essay.

The central axis of the full jet nozzle runs in the longitudinal direction of the full jet nozzle. According to this advantageous embodiment of the invention, the fuel is injected substantially transversely to the flow direction of the air, whereby a particularly high penetration depth is achieved. This allows a favorable mixing with the passing air.

It can also be advantageously provided that the attachment comprises an attachment center axis, which comprises at least one full jet nozzle a central axis and the at least a full jet nozzle is arranged in the attachment so that the central axis of the at least one full jet nozzle has an angle between 90 ° +/- 30 ° degrees to the center attachment axis of the attachment.

The angle refers to the inclination of the central axis in the direction of the center essay axis. The angular range is selected such that by varying the central axis of the at least one solid jet nozzle, a variation of the penetration depth can be set with essentially the same droplet size distribution and injection quantity of the fuel. This allows the tuning of the radial fuel profile with respect to the entire burner assembly, particularly the radial fuel profile of a main burner with respect to the pilot burner.

It can also be considered advantageous for the attachment to have an attachment surface and the at least one solid jet nozzle to comprise a center axis, and the at least one solid jet nozzle to be arranged in the attachment such that the central axis of the at least one full jet nozzle is perpendicular to this attachment surface.

The advantageous embodiment of the invention makes it possible for a region of the attachment tapering towards an attachment tip to inject the liquid fuel jet transversely to the flow direction, thereby enabling the greatest possible penetration depth of the fuel for jet nozzles arranged in this region of the attachment.

It may also be considered advantageous for the attachment to have an attachment surface and the at least one solid jet nozzle to be centered and the at least one solid jet nozzle to be located in the attachment so that the center axis of the at least one full jet nozzle is at an angle to the surface normal of the attachment surface -10 degrees to + 10 degrees. The surface normal runs perpendicular to the surface of the surface and is to be considered in each case in the area of the intersection of the central axis and the surface of the surface. Starting from the surface normal, the central axis can for this purpose be inclined both in the direction of the center attachment axis and in the circumferential direction (azimuthal angle). The specified angle range of -10 degrees to + 10 degrees for the inclination of the central axis ensures a high penetration depth of the fuel jet without the droplet size distribution or the injected amount of fuel to change. This allows adjustment of the fuel profile to be generated around the lance in both the radial and circumferential directions of the lance. As a result, the fuel profiles of the individual main burners can be matched with respect to the entire burner arrangement.

Furthermore, it can be advantageously provided that eight to twelve full jet nozzles with a diameter are provided for each of the main burners, the diameter being between 0.55 mm and 0.8 mm.

The number of eight to twelve jet nozzles is preferred. Also, a number of 6 to 16 full jet nozzles per main burner can be considered advantageous. Also, a number of 8 to 20 jet nozzles may be considered advantageous.

It can also be considered advantageous that full jet nozzles are provided with a diameter between 0.6mm-0., 7mm.

Advantageously, it can further be provided that full jet nozzles are provided with a diameter between 0.55 mm-0.65 mm.

A further advantageous embodiment of the invention can provide that full jet nozzles are provided with a diameter between 0.7mm-0.8mm.

According to the invention it is provided that in at least one of the main burners full jet nozzles are arranged along at least one peripheral line extending around the attachment.

The perimeter does not require any material realization, but merely serves to describe the arrangement of the full jet nozzles. The at least one circumferential line can, for example, run flat and closed around the lance. For example, the circumferential line may extend in a ring shape and perpendicular to the center attachment axis. By varying the nozzle arrangement and the nozzle diameter in the circumferential direction, suitable fuel profiles can be produced for suppressing pressure pulsations.

For the invention, it is important to consider the overall concept of the combustion system consisting of a central pilot burner with pilot cone and the main burners arranged around the pilot burner. The interaction with the central pilot burner requires optimization of the fuel and droplet size distribution, especially as a function of the relative orientation of the injection position to the pilot cone, in order thus to set the ignition of the fuel / air mixture with an advantageous time delay.

It can also be regarded as advantageous that in the case of at least one of the main burners more full jet nozzles are arranged on the side of the attachment facing the pilot burner than on the side of the attachment facing away from the pilot burner.

In particular, it is for the two special cases - Eindüsposition in the direction of the pilot flow (which can also be referred to as pilot cone flow) and in the opposite direction to the combustion chamber outer wall out - set optimal conditions. Since in the first case, the mixture formation and the sputtering mechanism caused due to strong flow of the stomata is different than in the second case, this should be taken into account when adjusting the fuel profile.

By increasing the number of full jet nozzles in the direction of the pilot burner, it is possible to produce a higher fuel concentration in the direction of the pilot burner with the same radial fuel profile and thus identical penetration depth. This allows you to adjust the flame position. The embodiment according to the invention can be implemented in one or more of the main burners. For example, every other one of the main burners arranged around the pilot burner.

A further advantageous development of the invention can provide that along at least one circumferential line the number density of the full-jet nozzles varies in the circumferential direction.

According to an embodiment of the advantageous development of the invention, the circumferential line may extend in an annular manner and perpendicular to the center attachment axis, wherein the full jet nozzles arranged along the circumferential line all have the same diameter. According to this exemplary embodiment of the development, the number density of the full-jet nozzles increases along the circumferential line in the direction of the pilot burner. As a result, with the same radial fuel profile, a higher fuel concentration can be generated in the direction of the pilot burner.

It can also be considered advantageous if along at least one circumferential line full-jet nozzles are arranged such that an inclination of the center axes of the full-jet nozzles varies in the direction of the central attachment axis in the circumferential direction.

This allows a circumferential variation of the penetration depth. The angle of inclination in the direction of the center attachment axis can be selected, for example, between 90 + -20 degrees, wherein the angle indication on the Angle between the center axis inclined in the direction of the center attachment axis and the center attachment axis refers. There are thus also blunt angle of attack possible. In the stated angular range, a circumferential variation of the penetration depth can be achieved independently of the droplet size distribution and the injection quantity.

It can be advantageously provided that the center axes of the full-jet nozzles arranged along the circumferential line are aligned alternately, wherein the center axes are alternately perpendicular to the central attachment axis and deviating therefrom inclined by at most 20 degrees in the direction of the center attachment axis.

In other words, the central axis of each second full-jet nozzle extends on the circumferential line perpendicular to the center line and the center axis of the full-jet nozzle arranged therebetween is inclined in each case in the direction of the central attachment axis. For example, from the surface normal by 10 degrees in the direction of center attachment axis in the flow direction.

The circumferential line can, for example, extend in an annular manner around the lance perpendicular to the middle attachment axis.

Furthermore, it can be advantageously provided that full-jet nozzles are arranged along at least one circumferential line in such a way that the center axis of at least one full-jet nozzle has an inclination in the circumferential direction starting from a position perpendicular to the center attachment axis.

This embodiment of the invention allows alternatively or in addition to the inclination of the central axis in the direction of the center attachment axis, an inclination in the circumferential direction (azimuth angle). This makes it possible to adjust the interaction of the fuel jet with the swirl flow in terms of atomization. Over a limited range, an isolated adaptation of the Drop size distribution can be achieved without causing a significant change in the radial penetration depth. This azimuthal adjustment of the central axis of the at least one full-jet nozzle can be selected to be the same for all full-jet nozzles arranged along the circumferential line, for example. The azimuthal angle of inclination of the central axes could, however, also be chosen, for example, as a function of the circumference. According to an embodiment of the advantageous development of the invention, the circumferential line runs perpendicular to the central attachment axis annularly around the lance, wherein the full-jet nozzles along the circumferential line have a same diameter. The center axes of the full-jet nozzles run alternately, wherein the center axis of each second full-jet nozzle is perpendicular to the attachment surface and the center axis of the full-jet nozzle arranged therebetween has an azimuth angle of 20 degrees to the surface normal.

It can also be considered advantageous that the full-jet nozzles have different diameters along at least one circumferential line.

The different diameters result in different penetration depths of the fuel in the circumferential direction. This allows adaptation of the radial fuel profile of a main burner with respect to the entire burner assembly.

Advantageously, it can further be provided that the full-jet nozzles have a same diameter along at least one circumferential line.

According to the invention, it is provided that the full-jet nozzles are arranged at least along two circumferential lines.

An at least two-row arrangement of the full-jet nozzles allows a much greater variation of the fuel profiles than with a single-row arrangement.

According to the invention, the at least two circumferential lines extend at different axial positions annularly and perpendicular to the center post axis around the lance around.

Along the two circumferential line can be arranged an equal or different number of full jet nozzles. For example, 4 to 10 nozzles per perimeter can be arranged. Due to the at least double arrangement or circumferential lines, an improved atomization of the fuel can be achieved. In addition, the arrangement of the jet nozzles in two axial planes offers the possibility of distributing fuel radially more uniformly at the same circumferential position by injecting at two axial positions at different depths into the same flow line of the passing air.

According to the invention, the full jet nozzles arranged along an upstream circumferential line have a larger diameter than the full jet nozzles arranged along a downstream circumferential line.

This embodiment of the invention is advantageous if a uniform radial distribution is to be achieved.

Advantageously, it can further be provided that full jet nozzles arranged along the downstream circumferential line and full jet nozzles arranged along the upstream circumferential line are arranged on common streamlines, with these being able to be twisted along the streamlines as the swirl vanes flow through them.

This embodiment of the invention is advantageous in order to achieve a uniform radial fuel distribution, in particular when the fuel injected by the downstream jet nozzles is smaller or significantly larger Penetration depth has injected as the injected from the upstream Völlstrahldüsen fuel. In particular, a smaller penetration depth is considered advantageous.

However, the design also makes it possible to achieve a narrow radial fuel distribution, wherein the jet injected from downstream full jet nozzles fuel is injected to the same radial position as the injected from upstream full jet nozzles fuel. The radial position is chosen so that the flame is stabilized at a point whose associated time delay can not be excited in the combustion system.

Advantageously, it can further be provided that full jet nozzles arranged along the downstream circumferential line and full jet nozzles arranged along the upstream circumferential line are arranged offset from one another in such a way that they can be twisted along the streamline as the swirl blades flow through them, on which only one of the full jet nozzles is arranged.

This embodiment of the invention is particularly advantageous in order to achieve a uniform circumferential distribution of the fuel profile. It can for example be combined with a narrow or a uniform radial and axial distribution. Particularly advantageous is considered a uniform radial and uniform axial distribution.

Furthermore, it can be advantageously provided that along the downstream circumferential line arranged full-jet nozzles inject fuel to the same radial position as along the upstream circumferential line arranged full-jet nozzles.

The radial position is chosen so that the flame is stabilized at a point whose associated time delay can not be excited in the combustion system. It can be advantageously provided that the full-jet nozzles are arranged along at least one helical circumferential line.

In addition to the illustrated circumferential and axial variations of the injection guidance by the full jet nozzles, which allows an optimization of the fuel and droplet size distribution in the circumferential axial and radial direction, an additional broadening of the time delay spectrum can be achieved by the additional helical arrangement of the full jet nozzles ,

If the injection of the fuel takes place, for example, along a single helical circumferential line and this circumferential line extends along a flow line of the twisted air flow, a uniform radial fuel profile can be achieved for the same diameter of the full jet nozzles.

This embodiment may be advantageous if an alternating circumferential fuel distribution is needed with the greatest possible smearing of the time delay spectrum. The arrangement of different full-jet nozzle diameters allows the setting of different radial fuel profiles, with uniform radial profiles are considered advantageous.

It can advantageously be provided that the diameters of the solid-jet nozzles arranged along the at least one helical circumferential line are designed such that the diameters increase in the direction of flow.

This embodiment of the invention is advantageous if a homogenization of the radial profile by enrichment of the near-axis region is to take place.

It may also be considered advantageous that the diameters along the at least one helical

Circumferentially arranged full-jet nozzles are formed such that the diameters rise opposite to the flow direction.

This embodiment of the invention is advantageous when a narrow radial fuel distribution is preferred.

The helical circumferential line can not run along a streamline according to another embodiment of the invention. This embodiment allows a uniform circumferential fuel distribution, wherein the diameter of the full jet nozzles arranged along the circumferential line can increase or decrease in the flow direction, depending on the desired radial fuel profile. Also, the inclination angle of the center axis of the full jet nozzles in the flow direction toward the center attachment axis and / or circumferentially along the helical peripheral line can be varied to adjust the interaction of the swirling flow of the air with the full jet of fuel with respect to atomization depending on the nozzle position.

Furthermore, it can be considered advantageous that the full-jet nozzles are arranged along two helical peripheral lines.

This is particularly advantageous for short essays, if the largest possible axial distribution of the nozzle assembly to be achieved. The double helix can also run antiparallel in addition to a parallel arrangement, whereby more uniform circumferential distributions can be achieved.

According to a further advantageous embodiment of the invention, it is provided for the circumferential enrichment of the fuel concentration that the full-jet nozzles are arranged along a helical circumferential line, the helical circumferential line partially overlapping. The diameters of the full-jet nozzles can all be the same size. The enrichment of Fuel concentration may serve to enrich the shear flow between the pilot burner and a main burner.

An advantageous development of the invention can provide that the full jet nozzles arranged along a circumferential line have distances from each other and diameter, wherein their sequence is repeated along the circumferential line.

The full jet nozzles arranged along the circumferential line can have regular distances from each other and all have the same diameter. The distances and / or the diameters may also vary in a regular sequence. This allows additional adjustment of the radial fuel profile. Radial fuel distribution is critical to thermoacoustic stability because it sets the delay time between injection and combustion. The delay time in turn determines which combustion chamber frequencies can be excited. According to an embodiment of the advantageous embodiment of the invention, an independent variation of the penetration depth and the distribution of the fuel can be achieved by a sequence of mixed diameter of the full jet nozzles along the circumferential line. For example, two different diameters may be mixed in a regular sequence or more. By selecting the size ratios of the full-jet nozzle diameter, the radial range can be set, in which the fuel distribution of the different nozzle diameters is superimposed. The degree of overlap can additionally be adjusted by selecting the circumferential position of the full-jet nozzles, in particular the mutual distances.

According to an advantageous embodiment of the invention is for generating a fuel profile with an annular zone of a first fuel distribution and an annular zone of a second fuel distribution along the circumferential line arranged between each two full-jet nozzles of the same diameter a full-jet nozzle with a smaller diameter.

It can be provided on the lance, for example, according to an embodiment of the advantageous embodiment 8 to 16 full jet nozzles. For the smaller jet nozzles a diameter between 0.5mm-0.7mm and for the larger jet nozzles a diameter between 0.6mm-0.8mm can be chosen.

According to an advantageous embodiment of the invention, the two zones may overlap, for example, by the solid jet nozzle is arranged with the smaller diameter closer to one of the two full jet nozzles with a larger diameter.

It can also be considered advantageous that the solid jet nozzles arranged along at least one circumferential line are configured such that a fuel injected by means of the nozzles has a radial fuel distribution around the center overhead axis, wherein the fuel distribution comprises an annular zone of a first fuel distribution and an annular zone of a second Fuel distribution includes.

The advantageous fuel distribution can be generated by varying the distances, the diameter, the inclination angle and / or the course of the circumferential line. As already stated above, such a fuel prefilf can be produced by means of an annular circumferential line running perpendicularly to the central attachment axis, along which full-jet nozzles of equal spacing are arranged, the diameters of which have alternately two different sizes.

It can also be considered advantageous that the annular zone of a first fuel distribution and the annular zone of a second fuel distribution overlap each other.

It may also be considered advantageous that the annular zone of a first fuel distribution and the annular zone of a second fuel distribution have a distance from each other.

Fig. 1

zeigt schematisch einen Schnitt durch einen Hauptbrenner- der Brenneranordnung gemäß einem ersten Beispiel,

Fig. 2

zeigt schematisch einen Schnitt durch den Aufsatz 13 des in Figur 1 dargestellten Beispiels in perspektivischer Ansicht,

Fig.3

zeigt schematisch einen Schnitt durch einen Hauptbrenner der Brenneranordnung gemäß einem zweiten Beispiel,

Fig.4

zeigt schematisch einen Schnitt durch einen Hauptbrenner der Brenneranordnung gemäß einem dritten Beispiel,

Fig.5

zeigt ein Diagramm zur Verdeutlichung des in Figur 4 dargestellten Beispiel,

Fig.6

zeigt schematisch einen Schnitt durch einen Hauptbrenner der Brenneranordnung gemäß einem vierten Beispiel,

Fig. 7

zeigt einen Querschnitt des in Fig.6 dargestellten Aufsatzes,

Fig.8

zeigt ein Diagramm zur Verdeutlichung des in Fig.6 dargestellten Beispiels,

Fig.9

zeigt schematisch einen Schnitt durch einen Hauptbrenner der Brenneranordnung gemäß einem fünften Beispiel,

Fig.10

zeigt schematisch einen Schnitt durch einen Hauptbrenner der Brenneranordnung gemäß einem sechsten Beispiel,

Fig.11

zeigt schematisch einen Querschnitt durch ein radiales Brennstoffprofil, welches mittels des in Figur 10 dargestellten Hauptbrenners erzeugbar ist, und

Fig.12

zeigt schematisch eine erfindungsgemäße Brenneranordnung in perspektivischer Ansicht.

Further advantages, features and characteristics of the present invention will be described in more detail below on the basis of exemplary embodiments with reference to the attached figures. The features of the embodiments may hereby individually or in combination serin advantageous.

Fig. 1

shows schematically a section through a main burner of the burner assembly according to a first example,

Fig. 2

schematically shows a section through the attachment 13 of the in FIG. 1 illustrated example in perspective view,

Figure 3

shows schematically a section through a main burner of the burner assembly according to a second example,

Figure 4

shows schematically a section through a main burner of the burner assembly according to a third example,

Figure 5

shows a diagram to illustrate the in FIG. 4 example shown,

Figure 6

shows schematically a section through a main burner of the burner assembly according to a fourth example,

Fig. 7

shows a cross section of in Figure 6 presented essay,

Figure 8

shows a diagram to illustrate the in Figure 6 illustrated example,

Figure 9

shows schematically a section through a main burner of the burner assembly according to a fifth example,

Figure 10

shows schematically a section through a main burner of the burner assembly according to a sixth example,

Figure 11

schematically shows a cross section through a radial fuel profile, which by means of in FIG. 10 shown main burner can be generated, and

Figure 12

schematically shows a burner assembly according to the invention in a perspective view.

The examples shown in the figures are not part of the invention.

Fig. 1 shows a detail of a burner arrangement in the region of a main burner 1.07. In the housing 12 of the main burner 107, swirl vanes 17 are arranged around the lance. The swirl blades 17 are arranged along the circumference of the lance in the housing 12. Through the swirl vanes 17, a compressor air flow 15 is passed into the leading to a combustion chamber part of the burner 107. The air is displaced by the swirl blades 17 in a swirling motion. The lance also comprises a fuel channel 16. The burner 107 further comprises an attachment 13 on the side leading to a combustion chamber. The attachment 13 can be welded or screwed to the lance, for example. The fuel nozzles are arranged in the attachment 13 preferably downstream of the swirl vanes 17 and are fluidically connected to the fuel channel 16, here represented as an oil channel. Preferably comprises the burner assembly according to the invention eight such main burner 107 arranged circular (see FIG. 12 ). The main burners 107 will be one (see FIG. 12 ) Pilot burner with pilot cone arranged.

Previous pressure-swirl nozzles used in the prior art have high pressure pulsations. Especially in base load operation, however, there are major problems here. This is avoided by means of the invention now.

Therefore, the plurality of fuel nozzles according to the invention are designed as full jet nozzles 1. The design of the nozzle as full jet nozzles 1, the full jet nozzle size and also arrangement make it possible to adjust the penetration depth of the fuel so that an advantageous fuel profile is formed. The parameters are the diameter of the full jet nozzles 1 and the number of full jet nozzles 1 available. In conjunction with the central pilot burner, the fuel distribution is adjusted so that the ignition of the fuel-air mixture is done with a beneficial time delay. The time delay between the injection and the combustion of the fuel is decisive for the formation of thermoacoustic feedback loops, from which combustion chamber pulsations can arise. The full jet nozzles 1 have a length, wherein the length to diameter ratio is at least 1.5, in order to achieve a good mixing. Thus, the divergence of the Volistrahles is small enough so that it does not come to an unwanted ejection of drops.

By using full-jet nozzles 1, the adjustment of the fuel profile, in particular the radial fuel distribution, can thus be changed very effectively. Compared with a pressure-swirl nozzle, the full jet nozzle 1 has the advantage that a higher fuel admission pressure is converted, above all, in a greater penetration depth. The pressure swirl nozzles of the prior art are replaced by a higher Form smaller drops formed, which in turn penetrate less effectively. It follows that a much higher pressure is required for an increased penetration depth for pressure-swirl nozzles than for full-jet nozzles. This can be with the full jet nozzle 1, for example, expensive pumps that can provide more fuel supply pressure, or avoid piping systems with high pressure levels.

The Fig. 2 schematically shows a section through the attachment 13 in a perspective view. The center attachment axis of the attachment 13 is identified by the reference numeral 18. The attachment 13 is spherical towards the combustion chamber, tapered designed. It comprises several, in the present embodiment four, full jet nozzles 1. The full jet nozzles 1 are arranged on the outer circumference of the attachment 13. The center axes of the full-jet nozzles 1 are identified by the reference numeral 19. The central axes 19 of the full-jet nozzles 1 have an angle 20 with respect to the middle attachment axis 18 of the attachment 13. The fuel enters the attachment 13 along the direction of flow indicated by the reference numeral 26 through the fuel channel 16. The fuel is then injected through the full jet nozzles 1 in the direction 25 in the coming of the swirl blades 17 air flow. The central axis 19 of the full-jet nozzles 1 is arranged substantially perpendicularly (90 degrees) to the middle attachment axis 18 of the full-jet nozzles 1. Also, the central axis 19 of the nozzle 1 can be perpendicular to the Aüfsatzoberfläche. Thus, the steel is introduced vertically into the air stream; a very good mix is the result. However, an arrangement of 90 ° +/- 30 ° degrees, in particular 90 ° +/- 10 ° degree, from the central axis 19 of the full-jet nozzles 1 to the axis 18 or the top surface results in a very advantageous arrangement.

The attachment 13 comprises a cylindrical 130 and a tapered to a combustion chamber portion 140. Here, the conical portion 140 may have a cone angle of 10-20 ° degrees. By this configuration takes place at the Top tip no demolition of the flow. In this case, the full-jet nozzles 1 can be arranged on the conical tapering part 140 of the attachment 13. The position of the full jet nozzles 1 may vary depending on the autoignition time of the mixture. In order to achieve a good fuel distribution, eight to twelve full-jet nozzles per attachment 13 are preferably used (not shown). Also advantageous are six to sixteen full jet nozzles 1 (not shown). These are evenly distributed on the circumference of the article 13. Good fuel distribution is necessary to meet emission limits and avoid soot formation. The solid jet nozzles 1 can be formed as bores in the attachment 13. Advantageously with regard to the mixing, in particular a length to diameter ratio of six to fourteen. The length of the full jet nozzle is designated by the reference numeral 32. The diameter of the full-jet nozzle with reference 33. Preferred diameter of the full-jet nozzles 1 are 0.55-0.8 mm, also advantageous are 0.5 -1 mm (not shown).

In particular, also not shown, are also the combinations of eight nozzles with a diameter of 0.7-0.8 mm, or of ten nozzles with 0, 6-0.7 mm diameter and twelve nozzles with 0.55-0 , 65 mm diameter advantageous.

In addition, the solid jet nozzles 1 can easily be adapted to other thermodynamic conditions, which are e.g. in an altered air cross-flow speed, air density or fuel mass flow result perform by the diameter 33 of the jet nozzles 1 is adjusted accordingly.

In addition, it is also possible to provide an optimized design for water content by adjusting the diameter 33 of the full-jet nozzles 1. This may be interesting, for example, if the emission limits, in particular for NOx, are increased. This happens, for example, in arid regions where Gas turbines 1 are also used for fresh water treatment.

The FIG. 3 shows a detail of the burner assembly in the region of a main burner 107. The main burner 107 comprises a cylindrical housing 12, in which a central lance 14 is arranged, which is surrounded by a main whirlwind 10. The main vortex generator 10 shown schematically has swirl vanes 17 (not shown), which support the lance 14 on the housing 12. Through the main swirl 10, a compressor air flow 15 flows in the direction of the combustion chamber (not shown). The lance 14 extends along an center attachment axis 18, on which in the direction of the combustion chamber (not shown) an attachment 13 is arranged. The attachment 13 has a cylindrical part 130 and merges in the direction of the combustion chamber into a tapered part 140. In the tapered portion 140 of the attachment 13 are indicated by circles solid jet nozzles 1, which are arranged along a perpendicular to the center attachment axis 18 and annularly around the center attachment axis 18 around circumferential line 11. In other words, the outputs of the full-jet nozzle 1 which open towards the attachment surface are arranged along a peripheral line 11 extending on the attachment surface, the circumferential line 11 extending in the circumferential direction 22 around the attachment 13. From the circumferential line 11, one half can be seen in the sectional view. The circumferential direction 22 is not necessarily perpendicular to the center attachment axis 18. Important here is only that in the circumferential direction 22 extending on the Aüfsatzöberfläche circumferential line 11 surrounds the central attachment axis 18. The in the FIG. 3 shown circumferential line 11 does not have to have a real equivalent, but only serves to describe the full jet nozzle assembly. According to the illustrated second embodiment of the burner assembly according to the invention, the number density of the full jet nozzles 1 varies in Umtangsrichtung 22, since the number density of the full jet nozzles 1 above the Center attachment axis 18 is greater than below the Mittelaufsatzächse 18. To increase the fuel concentration between the pilot burner (not shown) and main burner 107, the side of the attachment 13 shown above the center attachment axis 18 of the pilot burner (not shown) faces. The central axes 19 of the full jet nozzles 1 run according to the illustrated embodiment perpendicular to the attachment surface. That is to say, each of the central axes 19 extends in the direction of a surface normal 23. To clarify the term "surface normal," surface normals 23a, 23b, 23c are arbitrarily picked out in FIG FIG. 3 represented, wherein the Oberflächennörmale 23 b is located in the output region of a jet nozzle 1.

FIG. 4 shows a schematic sectional view of a detail of a burner assembly in the region of a main burner 107 according to a third embodiment. The structure of the main burner corresponds to the in FIG. 3 Except for the arrangement of the full jet nozzles 1. According to the third Ausführüngsbeispiel these are arranged along an annular and perpendicular to the main attachment line 18 circumferential line 11. The inclination of the center axes 19 of the full-jet nozzles extends in this case alternately along the circumferential line 11. The central axis 19 and thus also the direction 25 of the fuel jet, in which he leaves the solid jet nozzles, at a first full-jet nozzle perpendicular to the attachment surface and thus in the direction of a surface normal 23rd The central axis 19 of the solid jet nozzle 1 following the circumferential line 11 is deviating therefrom by 10 degrees in the direction of the middle attachment axis 18 in the flow direction of the compressor fan flow 15. In this sense, the inclination of the central axes 19 of the full-jet nozzles 1 varies in the circumferential direction 22 along the circumferential line 11. The drawn angle φ denotes the angle between the central axis 19 and top surface.

The FIG. 5 shows a diagram to illustrate the in FIG. 4 illustrated embodiment. The angle φ between central axis 19 and attachment surface of some full-jet nozzles 1 as an example of the circumferential position along circumferential line 11 is shown as an example. Angle φ is denoted by the angle of attack.

The FIG. 6 shows a schematic sectional view of a main burner 107 according to a fourth embodiment. The structure of the main burner 07 corresponds to the in FIG. 3 except for the arrangement of the full jet nozzles 1. According to the fourth embodiment, the full jet nozzles 1 along an annular and perpendicular to the main attachment line 18 extending circumferential line 11 are arranged. The inclination of the central axes 19 of the full-jet nozzles extends in this case alternately along the circumferential line 11. The central axis 19 and thus also the direction 25 of the fuel jet, in which he leaves the jet nozzle 1, runs at a first full-jet nozzle 1 perpendicular to the attachment surface and thus in the direction of a surface normal 23. The central axis 19 of the following on the circumferential line 11 full jet nozzle 1 is deviating from this by 20 degrees in the circumferential direction 22 inclined. The inclination angle in the circumferential direction 22 can also be referred to as the azimuth angle.

FIG. 7 shows for clarification of in FIG. 6 illustrated fourth embodiment, a cross section of the attachment 13 at the axial height of the circumferential line 11. The arranged along the circumferential line 11 full jet nozzles 1 are illustrated by circles. In other words, the openings of the full-jet nozzles, along the circumferential line 11 are arranged. The central axes 19 of the full-jet nozzles and thus also the direction 25 of the solid jet nozzle leaving fuel jet run alternately perpendicular to the attachment surface and thus in the direction of a surface normal 23 or thereof 20 degrees in the circumferential direction 22. The angle between Surface normal 23 and central axes 19 is denoted by ψ.

FIG. 8 shows a diagram to illustrate the in FIG. 6 illustrated fourth embodiment. The angle between center axis 19 and surface normal 23 in the circumferential direction (azimuth angle ψ) of some solid jet nozzles 1 as a function of the circumferential position along the circumferential line 11 is shown by way of example.

FIG. 9 shows a schematic sectional view of a main burner 107 according to a fifth embodiment. The structure of the main burner 107 corresponds to the in FIG. 3 Except for the arrangement of the full jet nozzles 1. These are arranged along a helical circumferential line 11, wherein the diameter of the full jet nozzles 1 opposite to the flow direction of the compressor air flow 15 increases. The air twisted when flowing through the main whirlwind 10 flows along flow lines 27 along the attachment 13 in the direction of the combustion chamber (not shown). The helical circumferential line 11 in this case runs in such a way that the solid jet nozzles 1 are arranged on a common streamline 27.

FIG. 10 shows a schematic sectional view of a main burner 107 according to a sixth embodiment. The structure of the main burner 107 corresponds to the in FIG. 3 Except for the arrangement of the full jet nozzles 1. These are along an annular and perpendicular to the center attachment axis extending circumferential line 11, wherein the full jet nozzles 1 along the circumferential line 11 distances from each other and have diameters, wherein the sequence along the circumferential line 11 is repeated. According to the illustrated Ausführüngsbeispiel the Völlstrahldüsen 1 are equally spaced from each other, wherein between each two full-jet nozzles 1 with the same diameter a Full jet nozzle 1 is arranged with a smaller diameter. The central axes (not shown) of the full-jet nozzles 1 are perpendicular to the middle attachment axis 18 in the radial direction.

FIG. 11 shows a means of in FIG. 10 shown full jet nozzles 1 producible fuel profile. The injected fuel in this case generates a radial fuel distribution around the center attachment axis 18, the fuel channel 16 and the attachment 13, the fuel distribution having an annular zone of a first fuel distribution 28 from the full-jet nozzles with large diameter and an annular zone of a second fuel distribution 29 from the jet nozzles includes small diameter. The fuel distribution from a single full-jet nozzle with large diameter is designated by the reference numeral 30. The fuel distribution from a single full-diameter, small-diameter nozzle is designated by reference numeral 31. Due to the selected distances between the full jet nozzles 1 and the size ratios of the diameters, the annular zone of a first fuel distribution 28 and the annular zone of a second fuel distribution 29 overlap one another.

FIG. 12 1 shows a burner arrangement 108 according to the invention with a pilot burner 106 with pilot cone 109 and a multiplicity of main burners 107 arranged around the pilot burner 106. Each of the main burners 107 comprises a substantially cylindrical housing 12 in which a lance is centrally arranged, in the direction of a combustion chamber (FIG. not shown) an attachment 13 is arranged on the lance.

Claims (26)

1. Burner assembly (108) for a gas turbine, having at least one combustor, with

   - a centrally arranged pilot burner (106) with a pilot cone and

   - a number of main burners (107) surrounding the pilot burner,

   - wherein each of the main burners (107) comprises a cylindrical housing (12) having a lance (14) which is centrally arranged therein and has a fuel channel (16) for liquid fuel, wherein the lance (14) is supported on the housing (12) by means of swirl blades (17) and an attachment (13) is arranged on the lance (14) in the direction of the combustor,

   - wherein at least one liquid fuel nozzle is arranged in the attachment (13) preferably downstream of the swirl blades (17) and connected to the fuel channel (16),
   wherein

   - the at least one liquid fuel nozzle is embodied as a full jet nozzle (1) and the at least one full jet nozzle (1) has a length (32) and a diameter (33), the ratio of the length (32) to the diameter (33) being at least 1.5,

   - wherein in at least one of the main burners (107) full jet nozzles (1) are arranged along at least two peripheral lines (11) running around the attachment (13),

   - the at least two peripheral lines (11) run in a ring shape and perpendicular to the central attachment axis (18) at different axial positions,

   - wherein the full jet nozzles (1) arranged along an upstream peripheral line (11) have a larger diameter (33) than the full jet nozzles (1) arranged along a downstream peripheral line (11).
2. Burner assembly (108) according to claim 1,
   characterised in that the attachment (13) has a cylindrical part (130) and a part (140) tapering conically in the direction of the combustor.
3. Burner assembly (108) according to claim 2,
   characterised in that the conical part (140) has a cone angle of 10 to 20 degrees.
4. Burner assembly (108) according to one of the preceding claims,
   characterised in that the attachment (13) comprises a central attachment axis (18) and the at least one full jet nozzle (1) comprises a central axis (19) and the at least one full jet nozzle (1) is arranged in the attachment (13) in such a manner that the central axis (19) of the at least one full jet nozzle (1) is at an angle (20) of 90 degrees to the central attachment axis (18) of the attachment (13).
5. Burner assembly (108) according to one of the preceding claims 1 to 3,
   characterised in that the attachment (13) comprises a central attachment axis (18), the at least one full jet nozzle (1) has a central axis (19) and the at least one full jet nozzle (1) is arranged in the attachment (13) in such a manner that the central axis (19) of the at least one full jet nozzle (1) is at an angle (20) of between 90 +/- 30 degrees to the central attachment axis (18) of the attachment (13).
6. Burner assembly (108) according to one of the preceding claims 1 to 3,
   characterised in that the attachment (13) has an attachment surface and the at least one full jet nozzle (1) comprises a central axis (19) and the at least one full jet nozzle (1) is arranged in the attachment (13) in such a manner that the central axis (19) of the at least one full jet nozzle (1) is perpendicular to said attachment surface.
7. Burner assembly according to one of the preceding claims 1 to 3 or 5,
   characterised in that the attachment (13) has an attachment surface and the at least one full jet nozzle (1) comprises a central axis (19) and the at least one full jet nozzle (1) is arranged in the attachment (13) in such a manner that the central axis (19) of the at least one full jet nozzle (1) forms an angle of -10 degrees to +10 degrees with the surface normal (23) of the attachment surface.
8. Burner assembly (108) according to one of the preceding claims,
   characterised in that eight to twelve full jet nozzles (1) are provided with a diameter (33) for each of the main burners (107), the diameter (33) being between 0.55 mm and 0.8 mm.
9. Burner assembly (108) according to claim 8,
   characterised in that ten full jet nozzles (1) with a diameter (33) between 0.6 mm and 0.7 mm are provided.
10. Burner assembly (108) according to claim 8,
    characterised in that twelve full jet nozzles (1) with a diameter (33) between 0.55 mm and 0.65 mm are provided.
11. Burner assembly (108) according to claim 8,
    characterised in that eight full jet nozzles (1) with a diameter (33) between 0.7 mm and 0.8 mm are provided.
12. Burner assembly (108) according to claim 1,
    characterised in that in at least one of the main burners (107) more full jet nozzles (1) are arranged on the side of the attachment (13) facing the pilot burner (106) than on the side of the attachment (13) facing away from the pilot burner (106).
13. Burner assembly (108) according to claim 12,
    characterised in that the number density of the full jet nozzles (1) varies in the peripheral direction (22) along at least one peripheral line (11).
14. Burner assembly (108) according to at least one of claims 12 to 13,
    characterised in that full jet nozzles (1) are arranged along at least one peripheral line (11) in such a manner that an inclination of the central axes (19) of the full jet nozzles (1) in the direction of the central attachment axis (18) varies in the peripheral direction (22).
15. Burner assembly (108) according to claim 14,
    characterised in that the central axes (19) of the full jet nozzles (1) arranged along the peripheral line (11) are aligned in an alternating manner, with the central axes (19) alternately running perpendicular to the central attachment axis (19) and being angled maximum 20 degrees from this in the direction of the central attachment axis (18).
16. Burner assembly (108) according to at least one of claims 1, 12 to 15,
    characterised in that full jet nozzles (1) are arranged along at least one peripheral line (11) in such a manner that the central axis (19) of at least one full jet nozzle (1) has an inclination in the peripheral direction (22) from a position perpendicular to the central attachment axis (18).
17. Burner assembly (108) according to at least one of claims 1, 12 to 16,
    characterised in that the full jet nozzles (1) have different diameters (33) along at least one peripheral line (11).
18. Burner assembly (108) according to at least one of claims 1, 12 to 16,
    characterised in that the full jet nozzles (1) have the same diameter (33) along at least one peripheral line (11).
19. Burner assembly (108) according to at least one of claims 1, 12 to 17,
    characterised in that full jet nozzles (1) arranged along the downstream peripheral line (11) and full jet nozzles (1) arranged along the upstream peripheral line (11) are arranged so that they are offset from one another in such a manner that when air flows through the swirl blades (17), said air can be swirled along flow lines (27) on which only one of the full jet nozzles (1) is arranged in each instance.
20. Burner assembly (108) according to at least one of claims 1, 12 to 19,
    characterised in that full jet nozzles (1) arranged along the downstream peripheral line (11) inject fuel to the same radial position as full jet nozzles (1) arranged along the upstream peripheral line (11).
21. Burner assembly (108) according to at least one of claims 1 to 20,
    characterised in that the full jet nozzles (1) arranged along a peripheral line (11) are at distances from one another and have diameters (33), such that their sequence is repeated along the peripheral line (11).
22. Burner assembly (108) according to claim 21,
    characterised in that a full jet nozzle (1) with a smaller diameter (33) is arranged along the peripheral line (11) between two full jet nozzles (1) of the same diameter (33).
23. Burner assembly (108) according to claim 22,
    characterised in that the full jet nozzle (1) with the smaller diameter (33) is arranged closer to one of the two full jet nozzles (1) with a larger diameter (33).
24. Burner assembly (108) according to at least one of claims 21 to 23,
    characterised in that the full jet nozzles (1) arranged along at least one peripheral line (11) are configured in such a manner that a fuel injected by means of the full jet nozzles (1) has a radial distribution about the central attachment axis (18), the fuel distribution comprising a ring-shaped zone of a first fuel distribution (28) and a ring-shaped zone of a second fuel distribution (29).
25. Burner assembly (108) according to claim 24,
    characterised in that the ring-shaped zone of a first fuel distribution (28) and the ring-shaped zone of a second fuel distribution (29) overlap.
26. Burner assembly (108) according to claim 25,
    characterised in that the ring-shaped zone of a first fuel distribution (28) and the ring-shaped zone of a second fuel distribution (29) are at a distance from one another.

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