WO2015043749A1 - Burner head of a burner and gas turbine having a burner of said type - Google Patents

Abstract

The invention relates to a burner head (36) for a burner (35) and to a gas turbine (30) having a burner (35) comprising a burner head (36) of said type. The burner head (36) extends along a burner longitudinal axis (1) and comprises at least one oxidant duct (3), which is arranged with a radial spacing to the burner longitudinal axis (1) in a main body (2) and has a duct longitudinal axis (20), and at least one fuel nozzle (4), which issues into the at least one oxidant duct (3). In the main body (2) there is formed at least one supply duct (13, 14) for the supply of fuel to the at least one fuel nozzle (4) and/or at least one fuel duct (5) for forming the fuel nozzle (4). In the case of the gas turbine (30), the burner head (36) has a central pilot stage (11) and a main stage (12) arranged concentrically around the pilot stage (11), wherein the main stage (12) is formed by the at least two different burner stages (7, 8). For each burner stage (7, 8), there is provided in the main body (2) a respective independent supply duct (13, 14) in the form of an at least partially encircling and closed annular groove (15, 16) for forming separate and mutually independent fuel feeds (9, 10) for the burner stages (7, 8), wherein the gas turbine (30) is at least partially driven by means of an exhaust-gas flow (38) of the burner (35).

Description

 Burner head of a burner and gas turbine with such a burner

The invention relates to a burner head of a burner of the type specified in the preamble of claim 1 and a gas turbine with a burner having such a burner head.

For the decentralized supply, for example, of companies with electrical, thermal and / or mechanical energy increasingly combined heat and power systems are used, which are operated with an internal combustion engine, in particular in the form of a micro gas turbine. Such micro gas turbines are gas turbines of the lower power class, ie up to about 500 kW nominal power. Combined heat and power systems of this type include in a known design in addition to the internal combustion engine itself nor a drivable by the internal combustion engine power converter, in particular in the form of an electric generator and a waste heat for the use of waste heat contained in the exhaust gas of the internal combustion engine.

The gas turbines mentioned have a burner between the compressor and the turbine, in which fuel is oxidized or burned with an oxidizing agent, as a rule with air. The required mixing of fuel and oxidant takes place in a burner head, which is typically designed as a burner flange, and a combustion chamber is connected downstream. The burner head extends along a burner longitudinal axis and usually comprises a plurality of arranged at a radial distance from the burner longitudinal axis in a body oxidant channels. In the

Oxidant channels each open a fuel nozzle, which is formed according to the prior art as a nozzle lance. Depending on a nozzle lance is preferably coaxial in each case an oxidant channel. The nozzle lances are usually kept at Burner flange, where they are aligned and stored by a constructive paragraph in the axial direction. The fixation of the burner nozzles is usually done by means of plates, which are bolted to the burner flange. Here, the nozzle lances are placed on the individual located in the burner flange, designed as through holes oxidant channels in the combustion chamber. The fuel is supplied via individual hoses, which are fed via an upstream external distributor ring. In the systems realized so far, the fuel nozzles are made of solid material.

This results in a high production, assembly and disassembly effort and because of the high number of individual components an increased cost. In particular, the production of the nozzle lances is expensive because thin holes (1 to 4 mm in diameter) over a length of several centimeters are required for the passage of the fuel. As further disadvantages, a high risk of leakage through single seals with often small space due to installation small sealing surfaces, a Fehleranfalligkeit by the installation complexity, the requirement of an external Brennstoffverteilerrings and individual hose and / or pipe connections from the fuel distributor ring to the fuel nozzles identified.

The invention has the object of developing a generic burner head such that with a simplified structure increased reliability is achieved.

This object is achieved by a burner head with the features of claim 1.

The invention is further based on the object of specifying a turbine, in particular a gas turbine or a micro gas turbine with an improved burner.

This object is achieved by a turbine having the features of claim 14. According to the invention, it is provided that at least one supply channel for fuel supply of the at least one fuel nozzle is formed in the main body of the burner head. In particular, a plurality of arranged around the burner longitudinal axis in the main body oxidant channels is provided with at least one each opening into an oxidant fuel nozzle, the fuel nozzles are at least partially and in particular all connected to the at least one supply channel for supplying fuel. By integrating the supply channel into the main body of the burner head can be dispensed with the usual and required according to the prior art complicated arrangement of hoses, pipes or the like. The design of the supply channel in the body of the burner head is structurally simple in construction, can be produced inexpensively, and is also reliable in the function.

In addition or as an alternative to the at least one supply channel, the at least one fuel nozzle is at least partially formed by a fuel channel opening into the associated oxidant channel in the base body, wherein a nozzle axis of the fuel channel has a radial direction component relative to the channel longitudinal axis of the oxidant channel and / or to the burner longitudinal axis of the burner head. Such a fuel channel can be formed easily and with little effort, for example, through a hole, a groove or any other recess in the main body of the burner head. On the customary in the prior art nozzle lances can be completely dispensed with, so that also eliminates the associated high assembly, sealing and manufacturing costs. The aligned with radial direction component fuel channels lead the fuel with just this radial direction component in the oxidant or combustion air stream, resulting in a good mixing and thus a stable oxidation or combustion takes place. The aforementioned good mixing can be further improved by different spatial angles of the nozzle axes, for example in the form of a helix angle.

In an expedient alternative, a fuel channel body is guided into the oxidant channel, wherein the at least one fuel nozzle is formed on the fuel channel body and in particular is arranged at least approximately on the channel longitudinal axis. Again, a simple design waiving the usual prior art nozzle lances given. The named design leads to a positioning of the fuel nozzle on the channel longitudinal axis or at least sufficiently close thereto. In any case, an at least substantially central fuel injection can be achieved, which can promote a clean mixture formation.

In a preferred development, the oxidant channels and the associated fuel nozzles, in particular fuel channels, are divided at least into a first burner stage and into a second burner stage, wherein separate and independent fuel supplies, in particular fuel supply channels, are provided for the various burner stages. In particular, the burner head in this case has a central pilot stage and a, preferably concentrically arranged around the pilot stage main stage, wherein the main stage by the at least two different

Burner stages is formed. As a result, an optimal adaptation to different load conditions can be achieved. The central pilot stage stabilizes combustion and ensures safe operation in transient control processes. In the pilot stage but only a small part of the total fuel flow is implemented. By far the largest share of fuel and power is provided by the two-stage main stage. The two-stage or multi-stage design allows for adaptation to changes in power requirements such that one or more stages of the main stage are shut down while one or more remaining stages of the main stage are operating at their optimum operating point. The invention described above in more detail and in more detail below finds its preferred use in a gas turbine, which in turn is preferably part of a combined heat and power system. Here are the advantages mentioned in full width to fruition. However, the burner head according to the invention can also be used equally advantageously in other burners, for example for heating systems, boilers, exhaust air purification systems, furnaces or the like.

In particular, in cleaning systems for the thermal or regenerative thermal oxidation of polluted with flammable pollutants exhaust gases, exhaust and / or wastewater by the use of the burner head according to the invention a cleaning performance even with rapidly and / or greatly varying calorific values of the exhaust gases, exhaust and / or wastewater and / or with you quickly and / or strongly

fluctuating mass flows are advantageously stabilized.

Exemplary embodiments of the invention are described below with reference to the drawing. Show it:

1 is a schematic block diagram of a gas turbine with a burner according to the invention,

2 shows a longitudinal section of the burner according to the invention according to FIG. 1 with a burner head and a downstream combustion chamber for illustrating the gas flow, FIG.

3 is a longitudinal sectional view of a burner head in the form of a burner flange according to the prior art for a burner according to FIG. 2 with fuel nozzles designed as nozzle lances, FIG.

Fig. 4 is a longitudinal sectional view of a first embodiment of a

burner head according to the invention with a formed in the body, annular supply channel for fuel in the form of a sealed, formed in the peripheral surface annular groove, and channels leading from the supply channel to the respective oxidant channel, the fuel nozzles forming fuel,

Fig. 5 shows a variant of the arrangement according to Fig. 4, in which the annular

 Supply channel is formed in an end face of the burner head,

Fig. 6 shows a further variant of the burner head according to Fig. 4 or 5 with two

 separate supply channels in the peripheral surface for the fuel supply of two independent burner stages of a main stage of the burner,

Fig. 7 shows a modification of the burner head of Fig. 6, in which the two separate

 Supply channels are formed in the end face of the burner head,

8 is a schematic detail of a single oxidant channel according to FIGS. 4 to 7 with an optional annular channel running around the oxidant channel,

9 shows in a perspective longitudinal sectional view of the burner head according to FIG. 4 for illustrating different angles of the nozzle axes to the burner longitudinal axis or to the respective channel longitudinal axis and the consequent flow pattern,

10 is a schematic cross-sectional view of the burner head of Figure 4 illustrating an optional spin angle of the respective nozzle axes.

Fig. 11 shows a variant of the arrangement of FIG. 4 with two differently executed

Fuel channel bodies, which in the respective oxidant channel into it wherein the respective fuel nozzle is formed on the fuel channel body and at least approximately disposed on the channel longitudinal axis, wherein in one embodiment, the fuel nozzle is connected to a transversely extending to the channel longitudinal axis, continuous fuel channel portion, and wherein in the other embodiment, the fuel nozzle from an angled fuel channel section is fed

FIG. 12 shows the arrangement according to FIG. 11 with alternatively configured fuel channel bodies, wherein in one embodiment the fuel nozzle is fed by an inclined fuel channel section, and in the other embodiment two near-axis fuel nozzles are connected to a fuel channel section extending transversely to the channel longitudinal axis.

1 shows a schematic block diagram of a gas turbine 30, which is preferably used in a cogeneration system. The gas turbine 30 includes a compressor 32, a turbine 33 and a burner 35, the compressor 32 being driven by the turbine 33 by means of a shaft 34. The shaft 34 also drives a schematically indicated generator 31 or other engine. By means of the compressor 32, air or another oxidizing agent is sucked in, compressed, and supplied to the burner 35, which is also indicated only schematically, as the oxidant stream or combustion air stream 37. By means of an adjustable and possibly also switchable Durchfiussbegrenzungselementes 22 the burner 35 is also supplied fuel, which is oxidized or burned in the burner 35 together with the oxidant stream 37. This results in a high-energy exhaust stream 38, which is derived by the turbine 33 and thereby relaxed, as a result, the turbine 33 and from this, the compressor 32 and the generator 31 is driven.

Depending on the embodiment of the schematically indicated in Fig. 1 power-heat coupling system but also additional or alternative forms of Use of useful energy will be used. For example, the waste heat of the exhaust stream 38 can be used directly for heating purposes.

Fig. 2 shows in a longitudinal sectional view of an embodiment of the invention burner 35 of the gas turbine 30 of FIG. 1. The burner 35 and its burner head 36 can also be used for other purposes, for example in heating systems, boilers, kilns, in an exhaust air purification or the like come. In the exemplary embodiment shown, the burner 35 comprises at least one combustion chamber 39, at the one end of which a burner head 36 is arranged. The burner head 36 extends along a burner longitudinal axis 1 or concentrically around it, with the burner longitudinal axis extending through the combustion chamber 39 or concentrically therethrough. Several combustion chambers 39 may also be advantageous.

The burner head 36 comprises a basic body 2 which is preferably designed in one piece and in which at least one oxidant channel 3 arranged at a radial distance from the burner longitudinal axis 1 is formed. In the illustrated preferred embodiment of FIG. 4, a plurality of concentrically arranged around the burner longitudinal axis 1 in the base body 2 oxidant channels is provided. The oxidizing agent channels 3 of the preferred example of FIG. 4 are in uniform

Angular distances distributed over a circumferential line around the burner longitudinal axis 1 arranged. In the example of FIG. 4 it is further provided that the oxidant channels 3 have a uniform radial distance to the burner longitudinal axis 1. Furthermore, the oxidant channels 3 in the example according to FIG. 4 have a uniform, circular cross-sectional contour with almost identical channel diameters, as best seen in FIG. 10. However, it may also be advantageous if neighboring ones

Oxidizing agent channels 3 varying angular distances on the circumferential line around the burner longitudinal axis 1 and / or varying radial distances from the burner longitudinal axis 1 and / or divergent channel cross-sections, in particular cross-sectional contours and / or diameter. For example, a preferred embodiment may also include two, three or more groups of oxidant channels 3 include, which differ in groups in terms of their angular distance and / or their radial distance and / or their channel cross-section.

In addition, the base body 2 according to FIG. 4 still bears centrally on the longitudinal axis of the burner 1 a pilot fuel nozzle 19 whose function will be described in more detail below.

 In the preferred exemplary embodiment shown, the combustion chamber 39 or its outer wall is enclosed by a jacket 40, whereby an annular space is formed. At an end of the end face of this annular space facing away from the burner head 36, the oxidant stream or the combustion air stream 37 is introduced and guided to the opposite side of the burner head 36. There, an oxidizing agent or combustion air plenum 23 which surrounds the burner longitudinal axis 1 is formed, in which the oxidizing agent collects, deflected in accordance with an arrow 41 and fed into the at least one or into the plurality of oxidant channels 3 on the side opposite the combustion chamber 39 becomes. Upstream of the oxidant channels 3, a flow restrictor element 24 for the oxidant stream 37, which is only schematically indicated, not shown in detail, can be optionally arranged, with which the flow rate of the oxidizer can be adjusted, controlled or regulated if required.

In the region of the oxidant channels 3, fuel is supplied to the oxidant stream 37, which is not shown here in detail, but will be described in more detail below in connection with FIGS. 4 to 10. The result is a combustible mixture which is oxidized or burned in the at least one combustion chamber 39.

The illustrated construction of the burner 35 is only a preferred embodiment. The burner head 36 according to the invention, which is described in more detail below, can also be advantageously used in other types of burners 35. 3 shows a longitudinal section of a burner head 36 'in the form of a burner flange according to the prior art. In the flange-shaped base body 2 ', a number of concentric to the burner longitudinal axis 1' arranged around oxidant channels 3 'are formed, each extending along channel longitudinal axes 20'. The main body 2 'also carries in the center a pilot fuel nozzle 19' for forming a pilot stage 11 '. In the oxidant channels 3 'each protrude a fuel nozzle 4', which are formed according to the prior art as a nozzle lance, and which are concentric with the respective channel longitudinal axes 20 '. Trained as a nozzle lance fuel nozzles 4 'are not shown in detail, but above described manner attached to the flange body 2, sealed against this and fed via separate fuel distributor with hoses or pipes or the like with fuel.

By means of the fuel nozzles 4 'designed as nozzle lances, fuel is introduced into the oxidant flow through the oxidant channels 3' in the same direction and coaxially, thereby producing an oxidation or combustible mixture. The oxidation channels 3 'together with the associated fuel nozzles 4' form a main stage 12 '.

4 shows a longitudinal section of a first exemplary embodiment of a burner head 36 according to the invention, which in its configuration resembles the burner head 36 according to FIG. Identical features are provided here with the same reference numerals, wherein individual features have already been described above in connection with FIG. In the base body 2, at least one supply channel 13 is formed, which here according to a preferred embodiment at least partially and in particular completely in the main body 2 rotates about the burner longitudinal axis 1. The supply channel 13 is supplied with fuel in particular by a single fuel supply 9, wherein the fuel supply 9 may have a flow-limiting element 22, not shown here but shown in FIGS. 1 and 9. The supply channel 13 is designed as an at least partially circumferential annular groove 15 in the base body 2, wherein the annular groove 15 is sealed on its open side. The rotating body around the burner longitudinal axis 1 rotating body 2 has a radially outer peripheral surface 17, in which the annular groove 15 is incorporated from the outside and radially outwardly closed.

Furthermore, the burner head 36 has at least one, in this case exactly one fuel nozzle 4, for each oxidant channel 3. From the additional illustration according to FIG. 10, it is apparent that eight oxidant channels 3 each having a fuel nozzle 4 are provided here by way of example. But it can also be a different number appropriate. The fuel nozzles 4 are at least partially, here all formed by incorporated into the body 2 fuel channels 5, wherein the fuel channels 5 are connected on its input side to the supply channel 13 and open on its output side in the respective oxidant channel 3. Thus, the fuel nozzles 4 and the fuel channels 5 are at least partially and here all connected to the supply channel 13 for the supply of fuel.

The fuel channels 5 have nozzle axes 6, which have a radial direction component to the channel longitudinal axis 20 of the oxidant channel 3 and / or to the burner longitudinal axis 1 of the burner head 36. In the embodiment shown, the channel longitudinal axes 20 are parallel to the axis of the burner longitudinal axis 1, so that said radial direction components apply equally relative to the channel longitudinal axis 20 and the burner longitudinal axis 1. However, said axis parallelism does not have to be given so that the radial directional component applies at least with respect to one of the two axes. The longitudinal section shown leads to a sectional plane which is spanned by the burner longitudinal axis 1 and a radial direction 26 thereto. In a same, but possibly also different cutting plane, a further cutting plane is spanned by the channel longitudinal axis 20 and a radial direction 27 for this purpose. In the mentioned sectional planes, the nozzle axis 6 lies in a first

Inclination angle α relative to the channel longitudinal axis 20 and at a second inclination angle ß relative to the burner longitudinal axis 1. The said first and second Tilt angles α, β are advantageously in a range of> 0 ° to 90 ° inclusive, and preferably in a range of 60 ° to 90 ° inclusive. In the exemplary embodiment shown, both inclination angles α, β are at least approximately 90 °. Further details of the burner head 36 according to FIGS. 2 and 4 and in particular further details of the angular position of the nozzle axes 6 are still shown in FIGS. 9, 10 and described in more detail below in their context.

FIG. 5 shows a variant of the arrangement according to FIG. 4, wherein the supply channel 13 designed as an annular groove 15 is not formed in the peripheral surface 17 (FIG. 4) but in an end face 18 perpendicular to the longitudinal axis of the burner 1. The supply channel 13 can, as in the embodiment of FIG. 4, orbit on the outside around the multiplicity of oxidant channels 3, but in the exemplary embodiment according to FIG. 5 lies radially on the inside of the oxidant channels 3. Accordingly, the fuel channels 5 do not lead from the outside to the inside with a radial direction component, but instead vice versa with radial direction component from the inside to the outside of the supply channel 13 in the oxidant channels 3. In the other features and reference numerals, the embodiment of FIG. 5 is consistent with that of FIG.

FIG. 6 shows a longitudinal section of a further variant of the burner head 36 according to FIG. 4 or 5. Here, the oxidant channels 3 and the associated fuel nozzles 4 or fuel channels 5 are at least exactly here in a first

Burner stage 7 and divided into a second burner stage 8. The at least two, here exactly two burner stages 7, 8 together form the main stage 12. In addition, the burner head 36 has a central pilot stage 11 with the associated pilot fuel nozzle 19. The divided into the two burner stages 7, 8 main stage 12 and their

Oxidant channels 3 and fuel channels 5 are arranged concentrically around the pilot stage 11. For the various burner stages 7, 8 separate and independent fuel supplies 9, 10 are provided, as shown in the illustration Fig. 1 and 9 may be provided with independent Durchfiussbegrenzungselementen 22.

The two fuel feeds 9, 10 lead into two separate

Supply channels 13, 14, which are both formed in the peripheral surface 17 of the base body 2 as an annular groove 15, 16 with mutual axial displacement. Both annular grooves 15, 16 with the associated fuel channels 5 are executed according to the annular groove 15 of FIG. 4. The fuel channels 5 of the upper supply channel 13 open into at least one, preferably in a first group of several Oxidationsmittel- channels 3, while the fuel channels 5 in at least one other, preferably in a second group of multiple oxidant channels 3 open. In this way, if required, individual oxidant channels 3 or individual groups thereof can be switched off or operated with different operating parameters than a respective different oxidant channel 3 or another group thereof. In other words, the two burner stages 7, 8 of the main stage 12 can be operated independently of each other and, if necessary, switched off individually.

FIG. 7 shows a modification of the burner head 36 according to FIG. 6, in which the two separate supply channels 13, 14 are formed in the end face of the burner head 36 or its basic body 2. This is comparable to the embodiment of FIG. 5 to two in the end face 18 of the body 2 incorporated annular grooves 15, 16, which are arranged in the preferred embodiment shown in the axial direction one above the other and separated by a separating plate. The first fuel supply 9 opens directly into the upper annular groove 15, while the second fuel supply 10 is passed from above through the upper annular groove 15 and below it opens into the annular groove 16. Alternatively, the two can

Supply channels 13, 14 and the two annular grooves 15, 16 may be radially offset from one another, wherein, for example, a supply channel 13 radially on the inside of the Oxidationsmittelkanäle 3 and the other supply channel 14 may be positioned radially outside thereof. Regarding the further embodiment, the vote Supply channels 13, 14 and the associated annular grooves 15, 16 with the

Supply channel 13 and the annular groove 15 of the exemplary embodiment of FIG. 5 match.

8 shows, in a schematic detail illustration, a single oxidant channel 3 according to FIGS. 4 to 7 with an optional annular channel 21 which surrounds the oxidant channel 3 in an annular manner. The annular channel 21 is in a manner not shown with one of the two supply channels described above 13, 14 connected and is supplied in this way with fuel. The annular channel 21 runs at least partially, in this case completely closed around the oxidant channel 3. In the illustrated embodiment, it is designed as an annular groove which is closed at the top by a cover 25 and by a cover plate. From the annular channel 21, at least one fuel channel 5, in this case a plurality of fuel channels 5 with associated nozzle axes 6, leads into the oxidant channel 3.

Unless expressly stated otherwise or shown in the drawing, the exemplary embodiments according to FIGS. 2 and 4 to 8 coincide with each other in their other features, reference numerals and optional design possibilities, whereby a combination of such features as, for example, the combination of an end-side supply channel 13 with a peripheral side Supply channel 14 comes into consideration.

FIG. 9 shows, in a perspective longitudinal section illustration, the burner head 36 according to FIGS. 2 and 4 for illustrating different angles of the nozzle axis 6.

Notwithstanding the representation according to FIG. 4, the nozzle axes 6 have first and second angles of inclination α, β which are smaller than 90 °. The two angles of inclination a, ß are determined such that at an amount of <90 °, the respective nozzle axis 6 is inclined starting from the supply channel 13 to the oxidant channel 3 in the flow direction or to the output of the oxidant channel 3. For the Possible amounts of the two angles of inclination α, β apply in connection with FIG. 4.

Fig. 10 shows a schematic cross-sectional view of the burner head according to FIGS. 2, 4 and 9 for illustrating further optional angular positions of the nozzle axes 6. The cross-sectional plane shown here is perpendicular both to the burner longitudinal axis 1 and to the respective channel longitudinal axis 20. If the channel longitudinal axes 20th deviate from the illustration of FIG. 10 is not parallel to the axis of the burner longitudinal axis 1, then the two mentioned cross-sectional planes are not congruent. For a better overview, three different fuel channels 5, 5 ', 5 "with associated nozzle axes 6, 6', 6" are shown in FIG. In practice, however, preferably only one design of the fuel channels 5, 5 ', 5 "described in more detail below with nozzle axes 6, 6', 6" in a single burner head 36 is used. Of course, a combination of it is possible.

In a first optional embodiment, the nozzle axis 6 of the fuel channel 5 lies in the perpendicular to the burner longitudinal axis 1 cross-sectional plane exactly radially to the burner longitudinal axis 1, ie in the radial direction 26. Thus, the nozzle axis 6 passes through the burner longitudinal axis 1. In addition, the nozzle axis 6 of the combustion Material channel 5 in the plane perpendicular to the channel longitudinal axis 20 cross-sectional plane exactly radially to the channel longitudinal axis 20, so runs exactly on the channel longitudinal axis 20.

In a further optional embodiment, the nozzle axis 6 'of the fuel nozzle 5' in the cross-sectional plane perpendicular to the burner longitudinal axis 1 is measured at a side angle γ to the burner longitudinal axis 1, so that the nozzle axis 6 'does not pass through the burner longitudinal axis 1. But well, the nozzle axis 6 'passes through the associated channel longitudinal axis 20'. From the burner longitudinal axis 1 extends through the associated channel longitudinal axis 20 ', a radial direction 26', wherein the side angle γ between the radial direction 26 'and the nozzle axis 6' is measured. Finally, another optional embodiment of a fuel channel 5 "with a nozzle axis 6" is shown. Here, the nozzle axis 6 "of the fuel channel 5" in the plane perpendicular to the channel longitudinal axis 20 "cross-sectional plane measured in a helix angle δ to the channel longitudinal axis 20". From the channel longitudinal axis 20 "extends to the mouth of the fuel channel 5" a radial direction 27 ", wherein the helix angle δ between the radial direction 27" and the nozzle axis 6 "is measured.

In addition to the helix angle δ, the nozzle axis 6 "has a side angle γ not shown here but shown at the nozzle axis 6 '. Of course, a position of the nozzle axis 6" is possible with a helix angle δ but without a side angle γ. Conversely, the nozzle axis 6 'only the side angle γ, while there is not drawn twist angle δ = 0. The nozzle axis 6 of the fuel channel 5 has neither a side angle γ, nor a helix angle δ. In other words, the amounts of the side angle γ and the helix angle δ equal 0. At least by the arrangement of the nozzle axis 6 "in a helix angle δ, alternatively or in combination with a side angle γ and inclination angles α, ß can be a swirled fuel entry in the respective oxidant channel 20 corresponding to a spiral line 28 of FIG. 9 for a good mixing of the fuel with the oxidizing agent.

FIGS. 11 and 12 show variants of the exemplary embodiment according to FIG. 4, wherein instead of a fuel channel 5 (FIG. 4) formed in the base body 2 and forming the respective fuel nozzle 4, a fuel channel body 42 is provided which led into the associated oxidant channel 3 is. The fuel channel body 42 is shown in Figures 11 and 12 in a total of four different exemplary embodiments, wherein in practice preferably a plurality of fuel channel body 42 of the same design are used. Of course, it is also possible to provide mixed designs within a burner head 36. Common features of the various fuel channel bodies 42 are the formation of at least one fuel nozzle 4 on each of a fuel channel body 42 and the optional, preferred positioning of the fuel nozzle 4 at least approximately on the channel longitudinal axis 20. In all cases, is located within the fuel channel body 42, a fuel channel section 43 for the supply of Fuel to the respective fuel nozzle 4. Preferably, but not necessarily, the fuel channel portion 43 is fed from an associated supply channel 13, 14, as described above in connection with Figures 4 to 7, 9 and 10.

It may be sufficient for the respective fuel channel body 42 to protrude beyond the associated oxidant channel 3 on only one side in a cantilever manner. In the preferred exemplary embodiments shown, it is guided into the respective oxidant channel 3 in such a way that it passes completely through it transversely to its channel longitudinal axis 20 and is supported on both sides on the opposite walls of the respective oxidant channel 3. In the preferred exemplary embodiments shown, the fuel channel bodies 42 have a circular cross-section, wherein they are here overall cylindrical. But there are also deviating cross-sectional shapes, in particular for reducing the flow resistance into consideration, such as elliptical, teardrop-shaped or otherwise streamlined cross-sectional shapes.

In the exemplary embodiment according to the left-hand half of FIG. 11, the fuel channel section 43 is formed as a through-hole, which completely passes through the fuel channel section 43 in its longitudinal direction, that is to say perpendicular to the channel longitudinal axis 20. Alternatively, a shortened, designed as a blind bore fuel channel section 43 may be provided which extends only to the fuel nozzle 4 according to the right half of FIG. In both cases, at right angles thereto and coaxially to the channel longitudinal axis 20, a channel section branches off, which forms the fuel nozzle 4, the associated nozzle axis 6 being congruent with the channel longitudinal axis 20. It but can also be an axis parallelism with a distance between the nozzle axis 6 and the channel longitudinal axis 20 may be appropriate.

A further variant is shown in the right-hand half of FIG. 12, wherein instead of a single fuel nozzle 4, a plurality of fuel nozzles 4, for example two fuel nozzles 4, are formed at a distance from the channel walls of the associated oxidant channel 5 and in particular in the vicinity lie to the associated channel longitudinal axis 20. The plurality of fuel nozzles 4 are advantageously fed from a common fuel channel section 43. Instead of the continuous fuel channel section 43 shown here, however, a shortened fuel channel section 43 analogous to the right-hand half of FIG. 11 may also be expedient. In any case, in all three embodiments described above, the fuel nozzles 4 are aligned in the flow direction of the oxidant channel 3, wherein an at least approximately central injection of the fuel into the respective oxidant channel 3 takes place.

Finally, the left-hand half of FIG. 12 shows yet another variant with a fuel channel section 43 guided obliquely through the fuel channel body 42. Here, the fuel channel section 43 directly forms the fuel nozzle 4 whose nozzle axis 6 is equal to the fuel channel axis directly at its output end. The nozzle axis 6 thus has both an axial and a radial direction component with respect to the plane of the burner longitudinal section shown here. In other words, the nozzle axis 6 is based on the direction of the burner longitudinal axis 1 or the channel longitudinal axis 20, as well as with respect to the direction of the respective associated radial direction 26, 27 in an angle deviating from 0 ° and 90 °. In particular, with such an oblique orientation of the nozzle axis 6, it may be expedient to arrange the fuel nozzle 4 at a distance from the channel walls of the associated oxidant channel 5, but also to maintain a distance from the channel longitudinal axis 20 of the oxidant channel 3. Taking advantage of the radial directional component of the exiting fuel can on this way one equivalent to the central and coaxial fuel feed according to the other embodiments of Figures 11 and 12 can be achieved.

Unless otherwise expressly described, the various embodiments of the fuel channel body 42 agree in their other features and reference numerals, which also applies to the comparison of the burner heads 36 according to Figures 11 and 12 with the burner head 36 of FIG. In addition, the fuel channel body 42 according to the invention can also be described in any other burner heads, in particular in burner heads 36 according to the further described here in total

Use exemplary embodiments.

Claims

claims A burner head (36) for a burner (35) which extends along a burner longitudinal axis (1), comprising at least one oxidant channel which is arranged at a radial distance from the burner longitudinal axis (1) in a base body (2) and has a channel longitudinal axis (20) (3) and at least one fuel nozzle (4) opening into the at least one oxidant channel (3), characterized in that at least one supply channel (13, 14) for supplying fuel to the at least one fuel nozzle (4) is formed in the base body (2). 2. Burner head according to claim 2,  characterized in that a plurality of about the burner longitudinal axis (1) around in the base body (2) arranged oxidant channels (3) is provided with at least one each in an oxidant (3) fuel nozzle (4), wherein the fuel nozzles (4) at least partially and in particular all connected to the at least one supply channel (13, 14) for supplying fuel. 3. Burner head according to claim 1 or 2, but at least according to the preamble of claim 1,  characterized in that the at least one fuel nozzle (4) is at least partially formed by an opening in the associated oxidant channel (3) fuel channel (5) in the base body (2), wherein a nozzle axis (6) of the fuel channel (5) relative to a radial direction component to the channel longitudinal axis (20) of the oxidant channel (3) and / or to Has burner longitudinal axis (1) of the burner head (36) and in particular radially to the channel longitudinal axis (20) and / or radially to the burner longitudinal axis (1). 4. Burner head according to claim 3,  characterized in that the nozzle axis (6) has a first inclination angle (a) to the channel longitudinal axis (20), wherein the first inclination angle (a) in a range of greater than 0 ° to and including 90 °, and preferably in a range of from 60 ° to including 90 °, and in particular at least approximately 90 °. 5. Burner head according to claim 3 or 4,  characterized in that the nozzle axis (6) has a second inclination angle (ß) to the burner longitudinal axis (1), wherein the second inclination angle (ß) in a range of greater than 0 ° to and including 90 ° and preferably in a range of up to and including 60 ° including 90 °, and in particular at least approximately 90 °. 6. Burner head according to one of claims 3 to 5,  characterized in that the nozzle axis (6 ') of the fuel nozzle (4, 5') in a direction perpendicular to the burner longitudinal axis (1) cross-sectional plane measured in a side angle (γ) to the burner longitudinal axis (1). 7. Burner head according to one of claims 3 to 6,  characterized in that the nozzle axis (6 ") of the fuel nozzle (4, 5") in a perpendicular to the channel longitudinal axis (20) lying cross-sectional plane measured in a helix angle (δ) to the channel longitudinal axis (20). 8. Burner head according to claim 1 or 2, but at least according to the preamble of claim 1, characterized in that a Brömstoffkanalkörper (42) is guided into the Oxidationsmittelkanal (3) inside, wherein at least one fuel nozzle (4) formed on the Bremstoffkanalkörper (42) and in particular at least approximately on the channel longitudinal axis (20). 9. burner head according to one of claims 1 to 8,  characterized in that the oxidant channels (3) and the associated fuel nozzles (4), in particular fuel channels (5), at least in a first burner stage (7) and in a second burner stage (8) are divided, wherein the burner head (36) is preferably a central pilot stage (11) and a main stage (12) preferably arranged concentrically around the pilot calls (11), wherein the main stage (12) is formed by the at least two different burner stages (7, 8), and wherein for the various burner stages (7 , 8) separate and mutually independent fuel supply (9, 10) are provided and in particular in the base body (2) are formed. 10. Burner head according to one of claims 1 to 9,  characterized in that the at least one supply channel (13, 14) as at least partially around the burner longitudinal axis (1) of the burner head (36) encircling annular groove (15, 16) in the base body (2) is executed, wherein the annular groove (15, 16) is sealed on its open side, and wherein advantageously an annular groove (15, 16) in a peripheral surface (17) and / or in an end face (18) of the base body (2) is incorporated. 11. Burner head according to one of claims 1 to 10,  characterized in that in the base body (2) in each case around the oxidant channels (3) around an annular channel (21) is provided which with the Supply channel (13, 14) is connected, and from which the fuel channels (5) in the oxidant channels (3) lead. 12. Burner head according to one of claims 1 to 11,  characterized in that between the supply channel (13, 14) and through the supply channel (13, 14) fuel-supplied fuel nozzles (4, 5) is provided a controllable flow-limiting element (22) via which the supply of the fuel nozzles (4, 5) is selectable with fuel selectable. 13. Burner head according to one of claims 1 to 12,  characterized in that in addition to the supply of fuel to the fuel nozzles (4, 5) provided supply channel (13, 14) a channel-like Oxidungsmittelplenum (23) in or on the base body (2) is provided, via which the or the oxidant channels (3) with oxidizing agent can be acted upon, between the Oxidationsmittelplenum (23) and the Oxidationsmittelplenum (23) supplied with Oxidationsmittel Oxiden dationsmittelkanälen (3) is preferably a controllable flow restrictor (24) via which the supply of the oxidant channels (3) selectable with oxidizing agent is. 14. A gas turbine (30) with a burner (35) comprising a burner head (36) according to one of claims 1 to 13, wherein the burner head (36) has a central pilot stage (11) and a main stage concentrically arranged around the pilot stage (11). 12), wherein the main stage (12) by the at least two different burner stages (7, 8) is formed, wherein for each burner stage (7, 8) in the base body (2) depending on an independent supply channel (13, 14) in the form of a at least partially encircling and sealed annular groove (15, 16) for forming separate and independent fuel supply (9, 10) for the burner stages (7, 8) is formed, wherein the gas turbine (30) at least partially via an exhaust gas stream (38) of the burner (35) is driven.