Abstract:
The invention relates to a premix burner with high flame stability for use in a heat producer, preferably in the combustion chamber of a gas turbine. Modern lean operated premix burners make possible very low pollutant emissions, but sometimes operate very close to the extinction limit. To increase the stability of the lean premix combustion by increasing the distance between the flame temperature and the extinction limit temperature, it is proposed according to the invention to arrange a downstream combustion gas mixing section ( 300 ) for the burner, which mixing section ( 300 ) projects at least partially into the combustion chamber ( 50 ) and enables combustion gases from the combustion chamber ( 50 ) access to the fuel/air mixture ( 144 ) by means of combustion gas inlet openings ( 311 ). The added combustion gases ( 145 ) are mixed with the fuel/air mixture ( 144 ), and in this manner increase its temperature. This increase in temperature results in a significant increase in the flame speed, as a consequence of which the extent of the flame front ( 123 ) and the extinction limit temperature of the burner decrease.

Description:
FIELD OF THE INVENTION  
         [0001]    The invention describes a burner for a heat producer.  
         BACKGROUND OF THE INVENTION  
         [0002]    Premix burners are known from EP 0 321 809, EP 0 780 629, WO 9317279, as well as EP 0 945 677; in them, a combustion air stream is introduced tangentially into the interior of a burner by means of a swirl producer, and is mixed with fuel. At the burner outlet, the vortex flow which arises bursts open at a sudden change of cross section, with the initiation of a back-flow zone which serves to stabilize a flame in the operation of the burner.  
           [0003]    Although such burners make possible an operation with very low pollutant emissions, they often operate dangerously near to the extinction limit of the flame. Flame temperatures usually obtained with the lean premix flames of such burners are about 1,700-1,750 K. The extinction limit of the flame is given as about 1,650 K. This value is comparatively high. This is based on the low fuel ratio in the fuel-air mixture. This reduces the flame speed, which in turn results in a flame front which is widely expanded spatially and is hence unstable.  
           [0004]    A stronger enrichment of the mixture would, however, drive the pollutant emissions higher and would negate the value of the use of lean premix burners.  
         SUMMARY OF THE INVENTION  
         [0005]    The present invention has as its object to improve the stability of the lean premix combustion of modern burners of the kind mentioned at the beginning, as particularly used in the combustors of gas turbines, in that the distance between the flame temperature and the extinction limit temperature is enlarged. Here an essential raising of the combustion temperature is to be avoided in order to furthermore ensure a low-pollutant operation.  
           [0006]    This is attained according to the invention in that the burner has a combustion gas mixing section at a downstream end, the said combustion gas mixing section partially projecting into a combustion space, and having combustion gas inlet apertures into the combustion space upstream of its mouth, through which combustion gas inlet apertures an amount of combustion gas flows from the combustion space into the combustion gas mixing section.  
           [0007]    The invention makes use of the knowledge that an increase of the temperature of the fresh gas—and thus of the fuel-air mixture—results in an increase of the flame speed. In the relevant region, an increase of the fresh gas temperature by 300 K leads to about a doubling of the flame speed. As a result, the extent of the flame front is reduced, and the extinction temperature of the burner falls.  
           [0008]    The core of the invention is thus an increase of the temperature of the fuel-air mixture in the process of combustion. A preheating of the combustion air is actually no longer realizable, precisely in gas turbine applications. Therefore, according to the invention, a combustion gas mixing section projecting into the combustion zone is used, in which on the one hand the premixed fuel/air mixture flows in as fresh gas, but in which on the other hand hot combustion gases flow in from the combustion space into the combustion gas mixing section in an upstream region of the mixing section, mix with the fresh gas in the mixing section, and thus raise the temperature of the combustion zone forming downstream of the combustion gas mixing section.  
           [0009]    As described above, the extinction limit temperature of the flame is thereby lowered, and thus the flame stability is improved at the same combustion temperature.  
           [0010]    It is indeed in the foreground that raising the mixture temperature increases the combustion temperature and thus the formation of nitrogen oxides; however, it should not remain unconsidered that the fuel/air mixture is mixed with inert combustion gas. Hence the middle flame temperature is raised, but the power density and the temperature rise decrease, which compensates for the effect on the pollutant formation and particularly the formation of nitrogen oxides. The effects combine favorably when the mass flow of the admixed combustion gases is between 5% and 60% of the air mass flow supplied.  
           [0011]    The admixture of combustion gases can be supported by suitable constructional measures. In particular, the axial flow cross section of the mixing section can be shaped so that at the place at which the combustion gas inlet apertures are located, a reduced pressure predominates relative to the combustion space. This can be attained, for example, in that the axial flow cross section has a sudden cross section widening, at which an eddy with a reduced pressure forms. The combustion gas inlet apertures are in this case arranged immediately downstream of the sudden change in cross section. In operation, the combustion gases are sucked into the eddy. Care has to be taken here that the cross section ratio of the flow sections upstream and downstream of the change in cross section is not too large, so that the swirl flow produced in the burner is maintained as far as the mouth of the mixing section in the combustion space, which is essential for the function of the burner mentioned in the preamble of the claims. A cross sectional surface ratio in the region of 1.05-2.5 ensures good operating performance.  
           [0012]    A further possibility of affecting the pressure ratios toward a strengthened mixing-in of combustion gases, by means of the pressure ratios in the combustion gas mixing section, is represented by a diffusor-like formation of the mixing section downstream of the combustion gas inlet apertures; also, a convergent-divergent course of the mixing section, in which the combustion gas inlet apertures are situated in the region of the narrowest flow cross section, is possible. The diffusor half-angle of the divergent portion of the combustion gas mixing section is in these cases to be in the region of 3° to 10°, preferably 5°.  
           [0013]    The invention is based on premix burners which are well known and familiar to the person skilled in the art from the prior art cited at the beginning. The invention can be directly combined with all the familiar kinds of swirl producers and burners disclosed in the documents cited there and developed from these documents and known per se to the person skilled in the art, and as only incompletely reflected in the preferred variants given in the dependent claims, among the multiplicity of possible embodiments.  
           [0014]    The wall of the combustion gas mixing section is situated in operation in a strong hot gas exposure. In particular, when using conventional materials, it is advantageously embodied as cooled. A film cooling is preferred for reasons of cooling efficiency.  
           [0015]    On the other hand, it is possible to mechanically decouple the combustion gas mixing section from the rest of the burner components, that is, from the swirl producer and/or a mixing tube which may possibly follow the swirl producer. This advantageously facilitates the use of materials whose expansion coefficients and thermal resistance are greatly different from those of the burner. Since the combustion gas mixing section furthermore has no appreciable mechanical loads to carry, it can advantageously be completely embodied in ceramic. In this case, cooling can be omitted in spite of the hot gas exposure of the mixing section, or the cooling can be a closed embodiment. Abstaining in this manner from blowing cooling medium into the region of the flame immediately confers advantages which are recognized by a person skilled in the art.  
       
    
    
     BRIEF DESCRIPTION OF THE DRAWINGS  
       [0016]    Further features, advantages and details of the invention will be explained hereinbelow with reference to the accompanying drawings. Only elements of importance for the invention are shown. The same or corresponding elements are given the same reference numerals.  
         [0017]    [0017]FIG. 1 is a cross sectional view of the burner according to a preferred embodiment of the present invention.  
         [0018]    [0018]FIG. 2 is a cross sectional view of the burner according to an alternative embodiment of the present invention.  
         [0019]    [0019]FIG. 3 is a perspective view, with portions taken away, of a prior art burner.  
         [0020]    [0020]FIG. 4 is a cross sectional view of the burner according to the preferred embodiment of the present invention.  
         [0021]    [0021]FIG. 5 is a cross sectional view of the burner of the present invention.  
         [0022]    [0022]FIG. 6 is a cross sectional view of the burner of the present invention.  
         [0023]    [0023]FIG. 7 is a cross sectional view of a two-shell swirl producer.  
         [0024]    [0024]FIG. 8 is a cross sectional view of a four-shell swirl producer.  
         [0025]    [0025]FIG. 9 is a cross sectional view of a swirl producer with a hollow cylindrical monolith.  
         [0026]    [0026]FIG. 10 is a perspective view of the burner according to the present invention.  
         [0027]    [0027]FIG. 11 is a schematic of the burner showing a first mode of operation.  
         [0028]    [0028]FIG. 12 is a schematic of the burner showing a second mode of operation in a gas turbine plant.  
         [0029]    [0029]FIG. 13 is a schematic of the burner showing another mode of operation in a gas turbine plant.  
     
    
     DETAILED DESCRIPTION OF THE INVENTION  
       [0030]    [0030]FIGS. 1 and 2 reproduce, very schematically, the essence of the invention. Initially the swirl producer  100  is effective; its possibilities of embodiment are discussed in further detail in the following FIGS.  3 - 5 . As is shown there, a premix burner, known per se, can be concerned for this swirl producer  100 , as is described, among other things, in the publications cited in this explanation. These burners, cited by way of example, are all based on a common principle. They have an axially extending, at least approximately rotationally symmetrical cavity  122 , into which combustion air flows through inlet slots  121  running preferably parallel to the longitudinal axis. The combustion air receives a strong tangential speed component from the tangential alignment of these more or less slot-shaped inlet apertures  121 , resulting in a swirl flow through the said internal space ( 122 ) from the reciprocal action of the said tangential component with the axial components directed toward the burner mouth. The enrichment of the combustion air with fuel takes place alternatively or complementarily through means ( 1111 ) on the housing jacket close to the combustion air inlet slots ( 121 ) and/or by means of central supply means ( 113 ) in the burner axis ( 100   a ).  
         [0031]    It is furthermore common to these burners that the flow cross section constantly widens in the direction to the burner outlet, in order to maintain approximately constant flow conditions with the increasing mass flow.  
         [0032]    Although burners referred to in the present document are based on the stated uniform principle, the invention is not to be restricted to this particular category of swirl burners, but is to include any kind of premix burners whose flame stability is to be increased at constant low pollutant emissions.  
         [0033]    According to the invention a mixing section ( 300 ) projecting into the combustion chamber ( 50 ) in extension of the burner axis adjoins the burner mouth. This can take place in any suitable manner. Depending on the specific conditions of the case of application, a range of possibilities will be accessible to the person skilled in the art. Thus the mixing section ( 300 ) can be directly connected to the swirl producer ( 100 ), for example by means of a flange connection. Alternatively, the swirl producer ( 100 ) and mixing section ( 300 ) can be indirectly connected, with the interposition of the combustion chamber wall. Hot combustion gases from the combustion chamber ( 50 ) are admixed to the premixed fuel/air mixture in this mixing section ( 300 ). For this purpose, the mixing section ( 300 ) forms a region of relatively reduced pressure at its upstream end, equipped with a number of passage channels ( 311 ) for the combustion gases from the combustion chamber ( 50 ). The relative reduced pressure is produced by a corresponding shape of the mixing section ( 300 ).  
         [0034]    According to a preferred embodiment, shown in FIG. 1, the mixing region ( 300 ) has a sudden widening of cross section with respect to the swirl zone ( 100 ). A boundary layer detachment of the outer flow takes place on flowing through this region, with the formation of a region of greatly decelerated flow, the eddy, on the back side of the outer flow. It has been found to be advantageous for the ratio of cross-sectional surfaces to be 1.05-2.5.  
         [0035]    According to an alternative embodiment, shown in FIG. 2, the internal contour of the mixing section ( 300 ) takes a convergent-divergent course, the combustion gas inlet apertures ( 311 ) being arranged distributed over the periphery in its narrowest cross section. In order to ensure an undisturbed flow path, the diffusor half angle takes a value of 5°. The combustion gases mix very homogeneously with the fuel/air mixture within the mixing section ( 300 ), which inevitably leads to a significant rise of the mixture temperature. Precise-ly this temperature rise increases the flame front speed and thus reduces the extinction limit temperature, clearly improving the flame stability at the same, or only slightly higher, combustion temperature.  
         [0036]    The combustion gas passage channels ( 311 ) pass through the jacket housing ( 301 ) of the mixing section ( 300 ) either radially or with a component in the flow direction. This means that the longitudinal axes of these apertures ( 311 ) run perpendicularly or at an acute angle to the burner axis  100   a . The range of variation of their cross sectional shapes is many and diverse, and ranges from being circular to being an annular gap. They can have a parallel or conically widening internal contour.  
         [0037]    The burner as characterized in the preamble of the claims is familiar to the person skilled in the art in different constitutions which can differ in specific embodiment from the burner shown in FIG. 3, which substantially consists of a conical swirl producer. Nevertheless, all these burners are constructed according to a common principle: they have a swirl producer in the form of a hollow body, with a longitudinal extent which includes a swirl producer interior. The swirl producer furthermore has inlet slots extending in the direction of the swirl producer longitudinal axis, or inlet apertures arranged in the direction of the longitudinal axis, their throughflow cross section substantially predetermining a tangential flow direction. Combustion air flows through these inlet apertures into the swirl producer interior with a strong tangential speed component, and forms there a swirl flow with a certain axial component directed toward the burner mouth in the combustion space. The axial flow cross section of the swirl producer interior is advantageously widened out here toward the burner mouth, at least in the region of the air inlet apertures. This constitution is favorable in order to attain a constant swirl number of the swirl flow with a combustion air mass flow which increases in the direction of the swirl producer axis. These burners furthermore have means to introduce fuel into the combustion air flow, to mix as homogeneously as possible with the swirled combustion air in a mixing zone, for example a mixing tube, to be optionally arranged downstream of the swirl producer. A sudden cross section change of the axial flow cross section is present at the outlet from the burner into the combustion space. A bursting open of the swirl flow occurs here, with the formation of a central backflow zone which, as described in detail herein-above, is usable for the stabilization of a lean premix flame.  
         [0038]    [0038]FIG. 3 shows a preferred embodiment of a premix burner characterized in the preamble of the claims, and as known per se from EP 0 321 809. The burner substantially consists of a swirl producer  100  for a combustion air flow, formed from two conical partial members  101 ,  102 . It can be seen from the cross section shown in FIG. 7 that the partial members  101  and  102  are arranged with their axes  101   a  and  102   a  offset with respect to the burner axis  100   a  and also opposedly laterally. Because of this lateral offset of the partial members, tangential inlet slots  121  are constituted between the partial members. A combustion air flow  141  flows substantially tangentially into the interior  122  of the swirl producer  100  through the tangential inlet slots  121 . Of course it is also possible to embody such a swirl producer  100  with another number of partial members; a completely analogous construction with, for example, four swirl producer partial members  101 ,  102 ,  103 , and  104  is shown in FIG. 8, with the mutually offset axes  101   a ,  102   a ,  103   a ,  104   a  of the partial members. Referring again to FIG. 3, a swirl flow  144  is consequently formed within the swirl producer, with its axial flow component facing toward the downstream mouth of the swirl producer  100 . The partial members  101 ,  102  border on the downstream end of the swirl producer  100  at a front plate  108 . The front plate  108  usually forms the end wall of a combustion space  50 , and is normally cooled. In the embodiment example, cooling air  148  flows through cooling bores  1081 . The interior  122  of the swirl producer  100  has a substantially frustroconical shape, widening from an upstream to a downstream end of the swirl producer ( 100 ) or burner. The axial flow cross section thus formed has at its downstream end, at the opening into the combustion space  50 , a sudden widening of the cross section. Due to the sudden change in cross section, a bursting open of the vortex flow  144  and the formation of a backflow zone  123  occur in the region of the burner mouth. An amount of fuel is supplied in a suitable manner to the combustion air flow in the swirl producer  100 . In the embodiment example, fuel ducts  111  are arranged along the partial members  101 ,  102  in the axial direction of the swirl producer  100  in the region of the tangential inlet slots  121 . Rows of fuel outlet bores  1111  can be seen in the embodiment example. An amount of fuel  142  is fed in by means of the fuel ducts  111  and flows through the fuel outlet openings  1111  into the interior  122  of the swirl producer  100 . This kind of fuel admixture frequently and preferably finds application with gaseous fuels. Furthermore, a fuel  146  can be introduced additionally, or as an alternative to the amount of fuel  142 , into the swirl producer interior  122  by means of a central fuel nozzle  113 ; in the example in FIG. 3, this is a liquid fuel, which forms a spray cone  147  in the swirl producer interior. Intensive mixing of the amount of fuel  142  with the combustion air  141  flowing in tangentially occurs in the interior of the swirl producer  100 . A very homogeneous mixture of air and fuel is present in the swirl flow  144  at the outlet from the burner into the combustion space  50 . A flame from the premixed fuel/air mixture can be stabilized in the region of the backflow zone  123 . Because of the good premixing of air and fuel, this flame can be operated with a quite high air excess—as a rule, air numbers of two and more are found at the burner itself—while avoiding stoichiometric zones with the formation of hot spots. Because of these comparatively cool combustion temperatures, very low nitrogen oxide emissions can be attained with such burners without expensive exhaust gas treatment. Because of the good premixing of the fuel with the combustion air and good flame stabilization by means of the backflow zone, a good burnup is furthermore attained, in spite of the low combustion temperatures, and thereby also low emissions of partially combusted and uncombusted materials, thus particularly carbon monoxide and uncombusted hydrocarbons, but also other undesired organic compounds, are attained. Furthermore, the purely aerodynamic flame stabilization by the bursting open of the swirl flow  144  (“vortex breakdown”) is found to be advantageous. By dispensing with mechanical flame holders, no components which are mechanical per se come into contact with the flame. The feared failure of mechanical flame holders due to overheating, with the possible result of severe damage to machine sets, is thus excluded. Further the flame loses no heat to cold walls, other than by radiation. This additionally contributes to comparative moderation of the flame temperature and thus lower nitrogen oxide emissions and good combustion stability.  
         [0039]    According to the invention, combustion gases are admixed with the premixed fuel/air mixture in the swirl flow  144 . As depicted in FIG. 4 in more detail than in FIG. 1, a combustion gas mixing section  300  is arranged down-stream of the swirl producer  100  and projects into the combustion chamber  50 . At the transition from the swirl producer ( 100 ) to the combustion gas mixing section ( 300 ), the configuration has a small, sudden cross section widening. This is sufficient to permit an eddy to arise. On the other hand, the cross section widening is also small enough for the swirl flow  144  to continue to exist, largely undisturbed and to be extended further, transversely through the interior  310  of the combustion gas mixing section  300 . Combustion gas passage channels  311  are arranged in the wall  301  of the mixing section  300 . These are advantageously arranged in a region in which the eddy  320  is effective, with the resulting reduced pressure. A combustion gas amount  145  is hereby sucked into the mixing section  300 . These combustion gases  145  can mix very homogeneously with the swirled fuel/air mixture within the combustion gas mixing section  300 . The temperature of the swirl flow  144  is significantly raised by the mixing with the hot combustion gases  145 . As already explained at another place, this rise in temperature raises the flame front speed and thus lowers the extinction limit temperature. At equal or only marginally higher combustion temperature, the flame stability is thus clearly improved.  
         [0040]    Burners according to the preamble of the claims are likewise known from WO 93/17279 and EP 0 945 677, and have cylindrical swirl producers with tangential combustion air inlets. In this connection it is also known to arrange a compression member ( 105 ), tapering toward the burner mouth, within a cylindrical swirl producer. The favorable criteria given above for the axial throughflow cross section of the swirl producer, namely that the axial throughfiow cross section increases in the axial throughflow direction, can furthermore be fulfilled by such a swirl producer interior member ( 105 ).  
         [0041]    An embodiment of the invention with such a swirl producer is shown in FIG. 5. The manner of functioning of the swirl producer  100  is sufficiently well known and is explained in principle in connection with FIG. 3. Deviating from the embodiment of a premix burner shown in FIGS. 3 and 4, the embodiment of a swirl producer  100  shown in FIG. 5 certainly has a conical compression member  105  with a cylindrical or slightly conical housing jacket  102 , tapering toward the burner mouth in the combustion chamber  50 . Combustion air flows with a strong tangential speed component into the swirl producer interior  122  through tangential inlet slots  121  which extend parallel to the longitudinal axis. Fuel, which mixes as homogeneously as possible with the combustion air in the interior ( 122 ) of the swirl producer, is metered into the combustion air through inlet apertures  142 . The injection device ( 112 ) for the axial central flow ( 147 ) is appropriately arranged in the region of the down-stream end of this compression body. The downstream end ofthe swirl producer ( 100 ) borders on a front plate ( 108 ), which preferably forms the end wall of the combustion chamber ( 50 ). The interior ( 122 ) has the cross section widening in the flow direction which is characteristic of this category of burner. The swirl flow ( 144 ) which forms as a result of the tangential inflow of the combustion air has an axial component of motion toward the mouth of the swirl producer in the combustion chamber ( 50 ). The combustion gas mixing section ( 300 ) projecting into the combustion chamber ( 50 ) adjoins the swirl producer ( 100 ) downstream, with the formation of a sudden cross section widening, [from the] interior ( 122 ) of the swirl producer ( 100 ) to the interior ( 322 ) of the mixing section ( 300 ). Analogously to the mechanisms of action explained in connection with FIG. 1 and FIG. 6, combustion gases ( 145 ) are sucked out of the combustion chamber ( 50 ) through the combustion gas passage channels ( 311 ) and are homogeneously distributed in the swirled fuel/air mixture ( 144 ) with the formation of a mixture temperature. To avoid repetition, reference is made to the statements there.  
         [0042]    It is known from EP 0 780 629, which document is incorporated herein by reference, to arrange a fresh gas mixing tube  230  downstream of the swirl producer of a burner characterized in the preamble, to intensify the mixing of fuel and combustion air. The implementation of the invention with such a burner is shown in FIG. 6 by way of example. Downstream of a conical swirl producer  100 , whose construction and function are not further discussed in detail at this point, a first mixing section  200  is arranged, serving as a fresh gas mixing section. The swirl producer ( 100 ) is secured to a holder ring  210 . A transition element  220  is furthermore arranged in the holder ring  210 , and is provided with a number of transition channels  221  which transfer the swirl flow  144  generated from the inflowing combustion air in the swirl producer  100  into the first mixing section, without sudden changes of cross section. The fresh gas mixing tube proper  230  is arranged downstream of the transition element  220 . If necessary, a further homogenization of the mixture of combustion air and fuel takes place in this first mixing tube  230 . A front segment  108  forming a combustion space wall is in this example impact cooled by impact cooling air  149  and cooling baffles  109 . Downstream of the fresh gas mixing section  200 , a flue gas mixing section  300  is arranged according to the invention. The throughflow cross section of the interior of the mixing section  200  takes a constant convergent-divergent course, in that the throughflow cross section first narrows to a minimum value and then continuously increases again to the mouth of the mixing section  300 . A number of throughflow channels  311 , preferably of circular shape, are arranged distributed over the periphery of the wall  301  in the region of the narrowest flow cross section. In operation, the accelerating swirl flow  144 , because of the injector-like configuration of the flow cross section, sucks flue gas  145  out of the combustion chamber  50  into the mixing section interior  310 . In the further course of the mixing section  300 , the entering combustion gases and the fuel/air mixture are mixed to a homogeneous mixture. As already mentioned, the temperature of the mixture is significantly raised, and as a result the flame stability is clearly improved. The mixing section  300  is subjected to a high thermal stress because of its exposed position in the combustion chamber  50 . Cooling of the housing jacket is therefore to be provided for when conventional materials are used. The housing is provided for this purpose with coolant channels  312  through which cooling air flows. In the interest of efficient cooling, the cooling air can be let out into the combustion chamber  50  via film cooling bores after passing through the coolant channels  312 .  
         [0043]    The burner can also be provided with a cylindrical or conically slightly tapering swirl producer ( 100 ) with a mixing section ( 200 ) following downstream of the swirl producer ( 100 ), without departing from the scope of the invention.  
         [0044]    Swirl producers with tangential combustion air inlets can be constructed in different ways. Besides the construction shown in cross section in FIGS. 7 and 8 with several partial members ( 101 ,  102 , 103 ,  104 ), monolithic modes of construction with inlet apertures are possible. Such an embodiment is shown in cross section in FIG. 9. The swirl producer ( 100 ) is constructed of a hollow cylindrical monolith. Machined in to this are inlet apertures ( 121 ) in the form of slots running axially and tangentially, through which a combustion air flow  141  flows in tangentially into the interior  122  of the swirl producer ( 100 ). Furthermore, fuel feeds  111  in the form of bores running axially arranged in the region of the inlet apertures can be seen, and have outlet bores  1111  through which an amount of fuel  142  can flow out into the combustion air flow  141 . A conical swirl producer  100  of a monolithic hollow body is shown in FIG. 10. This could of course also be cylindrical. Tangential openings, for example, bores, are machined into the monolithic swirl producer and likewise serve as tangential inlet apertures  121  for a combustion air flow  141 .  
         [0045]    The embodiment examples shown above are in no case to be understood in a limitative sense for the invention. On the contrary, they are to be understood as instructive and as an outline of the multiplicity of the possible embodiments within the scope of the invention characterized in the claims.  
         [0046]    Preferred processes for the operation of a burner according to the invention will be apparent to the person skilled in the art from the specific application.  
         [0047]    A first mode of operation, which is simple to manipulate, is shown in FIG. 11. The burner  1  is operated with an amount of fuel  142 . The mass flow of this fuel is determined at a measurement point  2 . The resulting mass flow signal X m  is processed in a control unit  3 , and is converted into a control signal Y for the adjusting mechanism of the axial central air injection of the burner  1 .  
         [0048]    A second embodiment, shown in FIG. 12, concerns the use of the burner according to the invention in gas turbine plants, for which the burner according to the invention is particularly suitable. In the example of FIG. 13, a compressor  10 , a turbine  30 , and a generator  40  are arranged on a common shaft. The compressor  10  is equipped with an adjustable forward guide row  11 . A combustion chamber  20  is arranged between the compressor  10  and the turbine  30 , in the flow path of a working medium. The combustion chamber  20  is operated with at least one burner  1  according to the invention. A control signal Y is conducted from a control unit  3  to the adjustable device for injecting the axial central flow. In the example shown, the control unit  3  receives a power signal X p , signals X AMB  from sensors (not shown) which determine environ-mental conditions such as temperature, humidity and pressure of the ambient air, and also a signal X VLE , which reports the setting of the forward guide row  11 . A whole series of data relative to machine operation can of course be supplied to the control unit  3 ; in particular, the generator power signal could be replaced by fuel mass flow signals. The control unit  3  is able to form from these magnitudes a combustion air specific burner loading, and to determine from this the control signal Y for the adjusting mechanism of the burner  1 .  
         [0049]    A gas turbine set with a compressor  10 , a turbine  30 , and a generator  40  arranged on a common shaft is again shown in FIG. 13. The combustion chamber  20  is shown as an annular combustion chamber, in longitudinal section, and is operated with at least one burner  1  according to the invention. The burner  1  is provided with a temperature measurement point for the determination of the material temperature, and produces a temperature signal X T . The combustion chamber  20  is provided with a pulsation measurement device for the determination of combustion pressure fluctuations, and producing a pulsation signal X Puls . The signals X T  and X Puls  are conducted to a control unit  3 , which generates a control signal Y for control of the intensity of the axial central flow. If the material temperature exceeds a given threshold value, the centrally injected mass flow is increased, so as to drive the flame a little away from the burner mouth, reducing the heat loading of the burner. On the other hand, an undesired reduction of the flame stability can result from this. This is determined by the pulsation measurement point. When the pulsation signal X Puls  increases, the centrally injected mass flow can be decreased, in order to increase the combustion stability and to counteract the increase in combustion pressure fluctuations. The central injection can be regulated in this manner, depending on the measured relevant data.  
         [0050]    It goes without saying that the operating process described can also form a portion of substantially more complex, superordinated control designs, and can be integrated into these.  
         [0051]    The foregoing explanations serve the person skilled in the art as illustrative examples for the many possible embodiments of the burner according to the invention and characterized in the claims, and for their advantageous modes of operation. They are not to be understood as limitative.