JPH08226649A - Combustor - Google Patents

Abstract

PROBLEM TO BE SOLVED: To minimize emission of all polluting substances generated at combustion, regardless of the kinds of fuels used for operating a combustor by improving the combustor or the method of operating the combustor. SOLUTION: A first ocmbustor stage 1 is arranged with at least a burner 100 for forming a high temperature gas 4, a plurality of vortex generator 200 downstream of the burner, and a means for blowing in either or both of gaseous fuel and liquid fuel 9 into the stream of main fluid on the downstream side of a vortex generator. A second combustor stage 2 connected in the direction of the flow has a cross-sectional bursting expansion part showing the cross section of starting point flow, and the burner is operated with a portion of the compressed air 17, while the remaining compressed air 17 is blown in on the downstream side of the burner.

Description

Detailed Description of the Invention

[0001]

BACKGROUND OF THE INVENTION 1. Field of the Invention The invention consists essentially of a first combustor stage and a second combustor stage downstream of the first combustor stage when viewed in the flow direction. The present invention relates to a combustor of a type that is arranged on the downstream side of a fluid machine and the second combustor stage is arranged on the upstream side of another fluid machine, and a method of operating the combustor.

[0002]

In the case of combustors with a wide load range, the question of how to reduce the emission of harmful substances despite the high combustion efficiency still remains. In that case, although the problem of NOx emission is mostly pushed to the front, it was found that UHC (= unsaturated hydrocarbon) and CO emission should be reduced as soon as possible. Especially when liquid and / or gaseous fuel is used, the combustor is designed for a certain fuel type, for example, oil, and with the aim of minimizing the emission amount of harmful substances, for example NOx emission amount. However, it is empirically known that this design cannot be satisfactorily diverted with regard to different operating modes and different emission of harmful substances. In the case of multi-stage combustors, efforts are being made to operate the second combustor stage with leaner fuel. Nevertheless,
Operation with such a lean fuel is only possible if a constant temperature is always maintained at the inlet of the second combustor stage in order to obtain satisfactory complete combustion in the second combustor stage, even with small amounts of fuel. None, ie the air-fuel mixture must be kept sufficiently constant in the first combustor stage. However, this is not possible with known diffusion burners, for example. To the best of our knowledge, a combustor that makes this possible cannot be exemplified in the prior art.

[0003]

SUMMARY OF THE INVENTION The object of the present invention is to improve the combustor of the type mentioned at the beginning and the operating method of said combustor, irrespective of the fuel species used for its operation.
The goal is to minimize the emission of all harmful substances generated during combustion.

[0004]

According to the constitution means of the present invention for solving the above-mentioned problems, the first combustor stage is on the head side,
It has at least one burner for forming hot gas, a plurality of vortex generators are arranged downstream of the burner, and downstream of the vortex generators gaseous fuel and liquid are introduced into the flow of the main fluid. Means for injecting fuel or either are provided and the second combustor stage connected in the flow direction has a cross-section sudden extension that displays the origin flow cross-section of the second combustor stage. And the burner is operated with a portion of the compressor air, while the balance of the compressor air is injected downstream of the burner.

[0005]

The advantage of the combustor according to the invention is that here the two burner characteristics are focused on one combination, the ultimate purpose of which is especially NOx.
The goal is to make the emission as close to zero as possible. The first combustor stage or first combustor section based on premixed combustion only allows a portion of the combustion air to flow through,
Further, the hot gas is supplied to the second combustor stage or the second combustor portion connected afterwards. Moreover, the second combustor stage is passed through by the total mass flow. The aim is to have the lowest possible basic NOx with a low vppm
In order to achieve the level, the first combustor stage is operated in the "premix-mode" at the lowest possible temperature. In this low temperature operation, the temperature of the combustion air is 500 to 700 before the first combustor stage.
It is obtained by preheating to the temperature order of ° C. Said combustion air is heated relatively easily from the compressor final temperature to the desired temperature level, in particular it is used or incorporated as cooling air for the combustor itself immediately before it is introduced into the first combustor stage. It is possible to easily raise the temperature by guiding it along the heat exchanger element. The hot gas is then injected downstream of the first combustor stage by the wall cooling effect and also by injecting the remainder of the combustion air (compressor air) not used in the first combustor stage. The stage is heated to a temperature at which it self-ignites, and this second combustor stage is equipped with a vortex generator that induces a swirling flow.

Another advantage of the present invention is that the second combustor stage is operated as a single stage load combustor, unlike the first combustor stage which is operated as an idle combustor. The second combustor stage produces NO at gas temperatures up to about 1600 ° C. due to the significantly better mixing.
It operates to make x neutral and provides a very flat total NOx potential with stable NOx characteristics of 1-2 vppm.

Yet another advantage of the present invention is that the adaptation of the temperature at the inlet to the second combustor stage allows the ignition delay times for different fuels to be optimally adapted.

The advantageous constituent means for solving the problems of the present invention are as described in the second and subsequent claims.

[0009]

DETAILED DESCRIPTION OF THE PREFERRED EMBODIMENTS Next, embodiments of the present invention will be described in detail with reference to the drawings.

It should be noted that in the drawings, all component elements not directly necessary for an understanding of the present invention have been omitted.
The same constituent elements are denoted by the same reference numerals in many drawings. The flow direction of the fluid medium is indicated by an arrow.

According to FIG. 1, as can be seen from the combustor axis 16, the ring-type combustor is substantially in the form of an interconnecting annular or quasi-annular cylinder. Furthermore, such combustors can also consist of a predetermined number of individually completed combustion chambers arranged axially, quasi-axially or in a spiral. Also, the combustor can essentially consist of a single tube.
The ring-type combustor shown in FIG. 1 consists of a first combustor stage 1 and a second combustor stage 2 connected one behind the other, and the second combustor stage 2 is the original combustion zone 11
Is also included. When viewed in the flow direction, the first combustor stage 1 firstly consists of a certain number of burners 100 arranged in the circumferential direction, which burners will be explained in more detail later. The following description of the combustor shown in FIG. 1 relates exclusively to the cross-sectional plane shown. As a matter of course, all the constituent parts of the combustor are arranged in a considerable number in the circumferential direction. Burner 1
A compressor (not shown) operates on the upstream side of 00, and the sucked air is compressed in the compressor. The compressor air supplied from the compressor then has a pressure of 10-40 bar. Although 30 to 60% of the compressed air flows into the burner 100, the operation mode of the burner will be described in detail with reference to FIGS. Burner 100
Prior to the inflow into the inside, the air content 115 of the ratio is 500
Heat to a temperature of ~ 700 ° C. This heating is carried out prior to this by the air content 115 being used directly as cooling air for the combustor. It is also possible to preheat the air portion 115 by passing it through a heat exchanger (not shown). Due to the preheating and the reduced air content, the NOx emission rate in the first combustor stage is remarkably low, that is, 1 to 3 vppm. Therefore, at the terminal end of the first combustor stage 1, the high-heat gas 4 without sufficient NOx is taken out. After flowing out of the first combustor stage 1, the hot gas 4 flows into the inflow zone 5, where it is accelerated to approximately 80 to 120 m / s. The inflow zone 5 is equipped with vortex generating elements (hereinafter referred to as vortex generators 200) arranged on the inner wall surface of the passage wall 6 and in a row in the circumferential direction of the passage wall 6, and the vortex generator is I will explain in detail later. The hot gas 4 is brought to a temperature in the region of 800 to 1100 ° C. in this vortex generator region by the wall cooling effect and the injection of residual air 17, especially by "bleed-through cooling". The exudation injection in this case is advantageously performed via the vortex generator 200. The total air is then swirled by the vortex generator 200 in the premixing zone 7 following the inflow zone so that it no longer creates a recirculation zone in the wake of the vortex generator 200. Inside the premixing zone 7, which can be configured as a venturi passage, there are arranged a plurality of fuel lances 8 which undertake the supply of fuel 9 and supporting air 10. The supply of these media to the individual fuel lances 8 can take place, for example, via ring conduits (not shown), in which case the fuel supply takes place via the fuel lances 3 incorporated in the vortex generator 200. You can also The swirl flow induced by the vortex generator 200 serves to distribute the introduced fuel 9 as well as the mixed supporting air 10 into a large volume to form a fuel / air mixture 19. Furthermore, the swirling flow also serves to homogenize a mixture of combustion air and fuel.
Fuel 9 injected into the hot gas 4 by the fuel lance 8.
Causes autoignition as long as the hot gas 4 has a specific heat capable of initiating fuel-related autoignition.
When operating the ring type combustor with gaseous fuel,
In order to start self-ignition, the temperature of the hot gas 4 is 80
Must be above 0 ° C. In the case of such combustion, as already mentioned above, there is of course the risk of flashback. This problem is eliminated by configuring the premixing zone 7 as a Venturi passage (not shown in detail) while arranging the injection nozzle for the fuel 9 in the region of the maximum constriction of the premixing zone 7. By providing a constriction in the premixing zone 7, turbulence is reduced by increasing axial velocity and the risk of flashback is also minimized by reducing turbulent flame velocity. On the other hand, a large volume distribution of the fuel 9 is further guaranteed. This is because the circumferential component of the swirling flow caused by the vortex generator 200 is not impaired. A combustion zone 11 follows the relatively short premixing zone 7. The transition between the premixing zone 7 and the combustion zone 11 is formed by a radial cross-section radial bulge 12 which first represents the flow cross-section of the combustion zone 11. Expanded diameter section 1
A flame surface (ignition surface) 21 is generated in the area of 2. In order to avoid flame flashback into the interior of the premix zone 7, said flame surface 21 must be maintained stable. To this end, the vortex generator 200 is designed such that no recirculation takes place in the premixing zone 7. Only after a sudden expansion of the cross section does the swirl flow collapse.
The swirl flow assists the rapid reconstruction of the flow behind the sudden cross-section diametrical expansion 12, so that by utilizing the volume of the combustion zone 11 as completely as possible a high complete combustion with a short structural length can be obtained. It is possible. A flow edge zone is formed during operation inside the sudden expanded portion 12 of the cross section, and a separation vortex is generated in the flow edge zone due to the negative pressure prevailing there, and the separation vortex, that is, both corner vortices 20.
Then, the flame surface 21 is stabilized. Both corner vortices 20 also form an ignition zone inside the second combustor stage 2. The hot working gas 13 prepared in the combustion zone 11 then loads the turbine 14 working downstream. The exhaust gas from the turbine 14 is then used for the operation of the steam circulation circuit, which circulation circuit is then a combined plant.

In summary of the above matters, the start of after-combustion in the flow passage is excluded on the basis of the high flow velocity. When oil is burned, it is possible to prevent direct ignition by adding water. As already mentioned, the cross-section sudden expansion 12 serves to stabilize the afterburning.
Due to the long stay of the mixture, self-ignition of the mixture occurs in both corner vortices 20. The flame surface 21 propagates toward the center of the combustion zone 11. Both corner vortex 20
The complete combustion of CO has also been completed immediately downstream of the confluence of both flame surface portions in the above. Typical combustion temperatures are 1300 to 1600 ° C. The operation of injecting the fuel into the high-heat gas emits only a small amount of NOx (1-2 vp in the present invention).
p) It is predetermined so as not to generate.

The proposed method has very good behavior over a wide load range. Since the mixing in the first combustor stage 1 is always perfectly constant, UH
It is also possible to block C or CO emissions. Second
The constant temperature at the inlet to the combustor stage 2 ensures a reliable self-ignition of the mixture, irrespective of the fuel quantity to the second combustor stage 2. Furthermore, the inlet temperature is high enough to obtain sufficient combustion in the second combustor stage 2 even with a small amount of fuel. Power control with respect to the gas turbine load is effected substantially by adapting the fuel quantity in the second combustor stage 2.

The first combustor stage 1 is operated as an idling combustor and the second combustor stage 2 is operated as a one-stage load combustor.

In order to better understand the construction of the burner 100, in conjunction with the description of FIG.
It is advantageous to refer to the individual cross-sections shown in FIG. Furthermore, in order not to unnecessarily obscure FIG. 2, the guide plates 121a, 121b schematically illustrated in FIGS. 3 to 5 are only shown in FIG.

The burner 100 shown in FIG. 2 comprises two hollow truncated cone-shaped partial cones 101, 102,
Both partial cones are intertwined inward and outward with their central axes offset from each other. Both partial cones 101, 102
Each central axis or longitudinal symmetry axis 101b, 102b
Due to the mutual displacement, tangential air inlet slits 119 and 120 are released on both sides in a mirror-symmetrical manner (FIGS. 3 to 5), and the combustion air 115 is introduced into the burner 100 through the air inlet slits. That is, it flows into the conical hollow chamber 114. Illustrated partial cones 101, 102
The truncated cone shape has a predetermined fixed angle in the flow direction. Of course, depending on the purpose of use, both partial cones 101, 10
2 can have a gradually increasing conical gradient in a trumpet manner or a conical gradient in a tulip manner in the flow direction. This trumpet-like or tulip-like shape is not specifically illustrated because it can be sensed by those skilled in the art without making any effort. Both partial cones 101, 102 each have one cylindrical starting end portion 101.
a, 102a, the cylindrical leading end portions also extending offset from each other corresponding to the partial cones 101, 102, so that the tangential air inlet slits 119, 1
20 is present over the entire length of the burner 100.
A nozzle 103 is provided in the region of the cylindrical starting end portion, the injection orifice 104 of which is a conical hollow chamber 11 formed by both partial cones 101, 102.
It almost agrees with the narrowest cross section of No. 4. The injection capacity of the nozzle 103 and the type of the nozzle are determined with reference to predetermined parameters of each burner 100. Of course burner 1
00 may be constructed in a purely conical shape, that is, it may not have the cylindrical starting end portions 101a, 102a. Each of the partial cones 101, 102 also has a fuel conduit 108, 109 which is arranged along a tangential air inlet slit 119, 120 and which has a plurality of injection ports 117. Through the injection port, particularly preferably gaseous fuel 113,
It is injected into the combusting air 115 flowing therethrough, as schematically indicated by 6. The fuel conduits 108, 109 are arranged before the inlet of the conical hollow chamber 114, particularly preferably at the tangential inlet end, in order to obtain an optimum mixture of air and fuel. In the region of the inflow zone 5, the outlet port of the burner 100 transitions into the front wall 110, which is provided with a certain number of holes 110a. The holes function as required and are adapted to supply the lean or cooling air 110b to the front part of the inflow zone 5. The fuel introduced through the nozzle 103 is particularly preferably a liquid fuel 112, to which the return exhaust gas is added. The liquid fuel 112 is injected into the conical hollow chamber 114 at an acute angle. Therefore nozzle 1
A fuel cone 105 is formed from 03, which is surrounded by combustion air 115 which flows in tangentially and rotates. In the axial direction, the concentration of the liquid fuel 112 is continuously reduced through the incoming combustion air 115 to the optimum mixture. If the burner 100 is operated with gaseous fuel 113, this operation can also be carried out via the nozzle 103, but it is particularly advantageous if it is carried out via the injection port 117, in which case this fuel Formation of the air-fuel mixture takes place directly at the ends of the air inlet slits 119, 120. When injecting the liquid fuel 112 through the nozzle 103, an optimum homogeneous fuel concentration is obtained at the end of the burner 100 over the entire cross section. If the combustion air 115 is additionally preheated or enriched by the return exhaust gas, this continuously supports the vaporization of the liquid fuel 112. The same applies if liquid fuel is supplied via fuel conduits 108, 109 instead of gaseous fuel. When constructing the partial cones 101, 102, the cone apex angle and tangential air inlet slits 119, 120 are provided in order to be able to produce the desired flow field of the combustion air 115 at the outlet of the burner 100.
Narrow limits must be adhered to for the width of the. A critical swirl number occurs at the exit of burner 100. That is, there is also a backflow zone (vortex breakdown zone) with a flame stabilizing effect. Generally speaking, the minimization of the tangential air inlet slits 119, 120 is predetermined to form the backflow zone 106. Furthermore, the structure of the burner 100 is particularly suitable for changing the size of the tangential air inlet slits 119, 120, so that a relatively large operating band can be obtained without changing the structural length of the burner 100. It is possible. Of course, the partial cones 101, 102 can also be shifted relative to one another in another plane, so that it is even possible to control the overlap of both partial cones. Furthermore, by turning in the opposite direction, both partial cones 10
It is also possible to spirally entangle 1 and 102 with each other.

By the way, the geometrical shapes of the guide plates 121a and 121b are clear based on FIGS. 3 to 5. The guide plate has a flow introducing function, and further extends the ends of both partial cones 101, 102 in the flow direction with respect to the combustion air 115 depending on the length thereof. The passage of the combustion air 115 into the conical hollow chamber 114 is guided by the swirl fulcrum 12 located in the passage inlet area of the conical hollow chamber 114.
3 is optimized by opening and closing the guide plates 121a and 121b, and this is especially necessary because the original gap size of the air inlet slits 119 and 120 in the tangential direction is based on the above-mentioned motive (motive). This is the case when it has to be changed. Of course, the above-mentioned dynamic coping measures also make the essential guide plate a partial cone 1.
It may be provided statically by forming it as an integral fixed component with 01, 102. Similarly, the burner 100 may be operated without a guide plate, or it is possible to provide another auxiliary means instead of a guide plate.

The original inflow zone 5 is not shown in FIGS. 6, 7 and 8. On the other hand, the high temperature gas 4 is shown by a thick arrow, and the flow direction is defined by this. According to these drawings, the vortex generator 20
Reference numerals 0, 201 and 202 substantially consist of three triangular surfaces through which the fluid can flow freely, that is, one roof surface 210 and two side wall surfaces 211 and 213. The roof surface 210 and the side wall surfaces 211 and 213 extend in the flow direction at a predetermined angle when viewed in the longitudinal extension direction. The side walls of the vortex generators 200, 201, 202, which are particularly preferably right-angled triangles, are fixed on their long sides to the previously mentioned passage wall 6, particularly preferably airtightly. . Both side wall surfaces 211 and 213 are at the side of the height with respect to each other at the arrowhead angle α.
Are oriented to form a butt line. The butt line is constructed as a sharp joining edge 216 and stands perpendicular to the adjacent passage wall 6 of each side wall surface. Both side wall surfaces 211 and 213 forming the arrowhead angle α are symmetrical in shape, size and orientation in FIG. 4 and are arranged on both sides of the axis of symmetry 217. The direction of the symmetry axis 217 is equal to the passage axis direction.

The roof surface 210 has both lateral wall surfaces 211 and 211 with a very thin lateral edge 215 extending laterally at a right angle to the passage through which the fluid flows.
It is in contact with the same passage wall 6 as 13. Both longitudinal edges 212 and 214 of the roof surface 210 penetrate both side wall surfaces 211 and 213 so as to project toward the inside of the flow passage.
Coincides with the longitudinal edge of the. The roof surface 210 extends at an elevation angle θ with respect to the passage wall 6. Roof surface 210
Both longitudinal edges 212, 214 of the
6 and 6 together form a tip 218. Vortex generator 20
0, 201, 202 may of course also have a bottom surface which is fixed to the passage wall 6 in a suitable manner. However, such a bottom surface has nothing to do with the working mode of the vortex generator.

The mode of operation of the vortex generators 200, 201, 202 is as follows. That is: As it flows through both longitudinal edges 212, 214 of the roof surface 210, the main fluid is transformed into a pair of opposite vortices, as schematically shown in FIG.
The vortex axes of both vortices are located within the axis of the main fluid. The number of turns and the collapse point of the vortex (as long as vortex breakdown is desired) are determined by appropriate choice of elevation angle θ and arrowhead angle α. As the angle increases, the strength of the vortex flow, or the number of swirl increases, and the vortex breakdown point becomes the vortex generators 200, 20.
1,202 is shifted upstream into the action initiation area of itself. The elevation angle θ and the arrowhead angle α depending on the application
Are defined by design conditions as well as the mixing process itself. In this case, the vortex generator must also be adapted in length and height, as will be explained in more detail below with reference to FIG.

In FIG. 6, the joining edge 216 of both sidewall surfaces 211, 213 forms the downstream edge of the vortex generator 200. Therefore, the lateral edge 215 of the roof surface 210 that extends at right angles to the passage through which the fluid flows is the edge that initially receives the passage fluid load.

FIG. 7 shows a so-called "half (1/2) type vortex generator" based on the vortex generator shown in FIG. In the vortex generator 201 shown here, only one side wall surface 211 of both side wall surfaces has an arrowhead angle, that is, an arrowhead angle of α / 2. The other side wall surface is oriented so that the direction is straight to the flow direction. Unlike a symmetrical vortex generator, as schematically shown in the drawings, in this case vortices are generated only on the side having the arrowhead angle α / 2. Therefore, there is no vortex neutral zone on the downstream side of the vortex generator 201, and a vortex is given to the fluid flow.

FIG. 8 differs from the embodiment of FIG. 6 in that the sharp junction edge 216 of the vortex generator 202 is used.
However, it is the part that first receives the load of the passage flow. Therefore, the vortex generator 202 is rotated by 180 ° with respect to the vortex generator 200 shown in FIG. As can be seen from the drawing, both vortex flows opposite to each other change their swirling directions.

FIG. 9 shows the principle geometry of the vortex generator 200 incorporated in the passage 5. In principle, the height h of the joining edge 216 is such that the passage height H or the vortex generator is such that the generated vortex reaches such a size that it already occupies the entire passage height H immediately downstream of the vortex generator 200. It is in harmony with the height of the aisle to which he belongs. This results in an even velocity distribution within the fluid-loaded cross-sectional area. Another decisive factor which will have an effect on the selectable ratio of the height h of the joining edge 216 to the passage height H = h / H is the pressure created when flowing along the vortex generator. It is a descent. It is clear that the pressure loss rate increases as the ratio = h / H increases.

The vortex generators 200, 201, 202 are primarily used to mix the two fluids together. The main fluid 4 as the hot gas impinges on the lateral edge 215 or the joining edge 216 in the direction of the arrow. In any case, the secondary fluid in the form of gaseous fuel and / or liquid fuel, to which the supporting air component has been added (see FIG. 1), has a significantly smaller mass flow than the main fluid. As can be seen particularly well from FIG. 1, in this example the secondary fluid is introduced into the main fluid downstream of the vortex generator.

In the illustrated example of FIG. 1, four vortex generators 200 are distributed over the entire circumference of the passage 5 at intervals.
Of course, it is also possible to arrange a plurality of vortex generators so as to be in contact with each other in the circumferential direction so as not to leave a gap along the passage wall 6. When selecting the number and arrangement of vortex generators, the vortices to be generated are ultimately deterministic.

10 to 16 there are illustrated possible modes for introducing fuel into the hot gas 4. These embodiments can be combined with each other in a wide variety of ways and with a central fuel injector, for example as can be seen in FIG.

In FIG. 10, the fuel is injected not only through a plurality of passage wall holes 220 arranged downstream of the vortex generator, but also through a plurality of additional wall holes 221. It is injected. The additional wall hole 221 has side wall surfaces 211 and 213.
Is drilled in the same passage wall in which the vortex generator is arranged, in the vicinity of and in the direction of longitudinal extension of the side wall surface. Wall hole 2
The introduction of fuel through 21 imparts additional momentum to the vortex generator, which further extends the useful life of the vortex generator.

In FIGS. 11 and 12, fuel is injected through one slit 222 or a plurality of wall holes 223, in which case both injection means, namely the slit 222 and the wall hole 22.
3 is the same as the arrangement of the vortex generator immediately before the lateral edge 215 of the roof surface 210 extending in the lateral direction perpendicular to the passage through which the fluid flows and in the extending direction of the lateral edge. Is disposed inside the passage wall 6. The geometry of the wall holes 223 or the slits 222 allows the fuel to be injected into the flow of the main fluid 4 at a predetermined injection angle and to flow as a protective film along the vortex generator located immediately behind. It is chosen to shield the vortex generator from the hot main fluid 4.

In the embodiment described below, the secondary fluid is first introduced into the hollow interior of the vortex generator through the passage wall 6 via guide means not shown. This gives the possibility of internal cooling of the vortex generator without any further measures.

In FIG. 13, a plurality of holes perforated in the roof surface 210 immediately behind and along a lateral edge 215 extending transversely at right angles to the passage through which the main fluid 4 flows. Fuel is injected into the main fluid through the wall holes 224. Here, the cooling action of the vortex generator takes place more on the outside than on the inside. The secondary fluid ejected is the roof surface 210.
A protective film layer is formed which shields the roof surface against the main fluid 4 of high heat when flowing along.

In FIG. 14, fuel is injected through a plurality of wall holes 225 arranged stepwise in the area of the roof surface 210 along the axis of symmetry 217. If this variation is used, the fuel is first introduced in the outer peripheral region of the vortex, so that the passage wall 6
Is protected particularly well against the hot main fluid 4.

In FIG. 15, fuel is injected into the main fluid 4 through a plurality of wall holes 226 located in both longitudinal edges 212, 214 of the roof surface 210. This solution ensures good cooling of the vortex generator. This is because the fuel gushes at the extreme edges and therefore completely rinses the entire inner wall surface of the vortex generator. In this case, the secondary fluid is fed directly into the vortex that is generated, which gives rise to defined flow conditions.

In FIG. 16, both sidewall surfaces 211 and 21 are shown.
3 on the one hand both longitudinal edges 212 and 214
Fuel injection is carried out through a plurality of wall holes 227 which are drilled in the region of the, and on the other hand, in the region of the joining edge 216. This variation has the same effect as the case of the wall hole 221 of FIG. 10 and the case of the wall hole 226 of FIG.

[Brief description of drawings]

FIG. 1 is a schematic configuration diagram of a ring-type combustor having a first combustor stage and a second combustor stage.

FIG. 2 is a first partially cutaway ring-type combustor.
It is a perspective view of a combustor step.

3 is a cross-sectional view of the first combustor stage taken along the line III-III of FIG.

4 is a cross-sectional view of the first combustor stage taken along the line IV-IV in FIG.

5 is a cross-sectional view of the first combustor stage taken along section line VV of FIG.

FIG. 6 is a perspective view of a vortex generator.

FIG. 7 is a perspective view of a variation of an embodiment of the vortex generator.

8 is a perspective view of a variation of the arrangement of the vortex generator shown in FIG.

FIG. 9 is a schematic configuration diagram of a vortex generator arranged in a premix passage.

FIG. 10 is a first embodiment of a fuel supply system associated with a vortex generator.

FIG. 11 is a second embodiment of the fuel supply system associated with the vortex generator.

FIG. 12 is a third embodiment of the fuel supply system associated with the vortex generator.

FIG. 13 is a fourth embodiment of the fuel supply system associated with the vortex generator.

FIG. 14 is a fifth embodiment of the fuel supply system associated with the vortex generator.

FIG. 15 is a sixth embodiment of the fuel supply system associated with the vortex generator.

FIG. 16 is a seventh embodiment of the fuel supply system associated with the vortex generator.

[Explanation of symbols]

1 first combustor stage, 2 second combustor stage,
3 fuel lance, 4 high-temperature gas, 5 inflow zone, 6 passage wall, 7 premixing zone, 8
Fuel lance, 9 fuel, 10 support air,
11 Original combustion zone, 12 Cross section sudden expansion part, 13 High heat working gas, 14 Turbine, 16
Combustor axis, 17 residual air, 18 compressor, 19 fuel-air mixture, 20 corner vortex, 21 flame front, 100 burner, 1
01, 102 partial cones, 101a, 102a
Cylindrical starting portion, 101b, 102b longitudinal symmetry axis, 103 nozzle, 104 injection orifice, 106 backflow zone, 108, 109
Fuel conduit, 110 front wall, 110a hole,
110b diluted air or cooling air, 112 liquid fuel, 113 gaseous fuel, 114 conical hollow chamber, 115 air content or combustion air, 116 arrow showing inflow direction, 117 injection port, 11
9,120 Air inlet slit, 121a, 121
b guide plate, 123 turning fulcrum, 20
0,201,202 Vortex generator, 210 Roof surface, 211 Side wall surface, 212 Longitudinal edge, 213 Side wall surface, 214 Longitudinal edge, 215 Transverse edge, 216 Junction edge, 217 Symmetric axis, 218 Tip, 22
0 passage wall hole, 221 wall hole, 222 slit, 223, 224, 225, 226, 227
Wall hole, α arrowhead angle, L Vortex generator length, H
Passage height, h Junction edge height, θ elevation angle

Claims (15)

[Claims] 1. A first combustor stage (1), and a second combustor stage (2) downstream of the first combustor stage (1) when viewed in the flow direction. Arranging the combustor stage (1) downstream of the fluid machine (18),
In a combustor of the type in which the second combustor stage (2) is arranged upstream of another fluid machine (14), the first combustor stage (1) forms a hot gas (4) on the head side. It has at least one burner (100) and a plurality of vortex generators (20) downstream of the burner (100).
0, 201, 202) and the vortex generator (20
(0, 201, 202), a means for injecting a gaseous fuel and / or a liquid fuel (9) into the flow of the main fluid is provided on the downstream side, and is connected in the flow direction.
The combustor stage (2) has a cross-section sudden extension (12) displaying the origin flow cross-section of the second combustor stage, and the burner (100) is operated on a portion of the compressor air (17). On the other hand, the combustor, wherein the remainder of the compressed air (17) is injected downstream of the burner (100). 2. One vortex generator (200) has three surfaces extending in the flow direction and through which fluid can flow through, one of which serves as a roof surface (210) and the other. Of the two surfaces form side wall surfaces (211 and 213), and both side wall surfaces (211 and 213) together form a passage (5) through which a fluid flows.
Closer to the same passage wall segment of each other, the arrowhead angle (α)
And said roof surface (210) forms a lateral edge (215) extending laterally at right angles to the passage (5) through which the fluid flows, said side wall surfaces (211;
213) contacting the same passage wall segment and both longitudinal edges (21) of said roof surface (210).
2, 214) coincide with the longitudinal edges of the side wall surfaces (211, 213) extending into and penetrating into the passage (5) and an elevation angle with respect to the passage wall segment of the passage (5). The combustor according to claim 1, wherein the combustor extends along (θ). 3. The vortex generator (200) is provided on both side wall surfaces (211, 213) forming an arrowhead angle (α).
3. The combustor according to claim 2, which is arranged symmetrically with respect to the axis of symmetry (217) of (0). 4. Both side wall surfaces (211, 213) forming an arrowhead angle (α, α / 2) have joint edges (216) abutting each other, and the joint edges are roof surfaces (210).
Forming a point (218) in combination with the longitudinal edges (212, 214) of said, and said joining edge (216) being located within the radius of the circular passageway (5), The combustor according to claim 2. 5. Joining edge (216) and roof surface (21)
5. The combustor according to claim 4, wherein both longitudinal edges (22, 214) of (0) are configured as at least sharp edges. 6. The axis of symmetry (21) of the vortex generator (200).
7) extends parallel to the passage axis, and both side wall surfaces (21
1, 213) join edges (216) form a downstream edge of the vortex generator (200) and extend laterally at right angles to the passage (5) through which the fluid flows (5). 210) lateral edge (215) is the main fluid (4)
The combustor according to any one of claims 1 to 4, wherein the combustor is an edge that first receives the load. 7. The ratio of the height (h) of the vortex generator to the height (H) of the passage (5) is such that the height of the passage (5) is directly downstream of the vortex generator (200). 2. The combustor according to claim 1, which is selected to occupy the entire height (H) and the entire height (h) of the passage portion in which the vortex generator (200) is arranged. 8. A burner (100) consists of two hollow partial cones (101, 102) which are interlocked inwardly and outwardly with each other in the direction of flow, the longitudinal symmetry axis (101b, 101b, 101b) of each partial cone. 102b) extend offset from one another and both partial cones (101, 10)
2) the adjoining walls form in their longitudinal direction tangential passages (119, 120) for the combustion air flow (115) and by means of both partial cones (101, 102) 2. The combustor according to claim 1, wherein at least one fuel nozzle (103) is arranged in the conical hollow chamber (114) formed. 9. A plurality of further fuel nozzles (11) in the direction of their longitudinal extension in the area of the tangential passages (119, 120).
9. The combustor according to claim 8, wherein 7) is arranged. 10. The combustor according to claim 8, wherein both partial cones (101, 102) expand at a fixed angle in the flow direction or have a conical gradient that increases or decreases. 11. The combustor according to claim 8, wherein both partial cones (101, 102) are spirally connected to each other. 12. The combustor according to claim 1, wherein the combustor is a ring combustor. 13. Vortex generator (200, 201, 202)
2. The combustor according to claim 1, wherein a downstream section of the venturi is formed in a Venturi passage shape, and the fuel (9) is injected in the region of the maximum constriction of the Venturi passage section. 14. A substantially first combustor stage and a second combustor stage downstream of the first combustor stage when viewed in the flow direction, the first combustor stage being located downstream of the fluid machine. The method of operating a combustor according to claim 1, wherein the second combustor stage is operated and the second combustor stage is operated upstream of another fluid machine. One combustor stage (1) is caused to flow into the combustor stage (1) and the remainder of the compressor air (17)
Is charged on the downstream side of the first combustor stage (1) and on the upstream side of the injection portion of the fuel (9).
Combustor driving method. 15. Compressor air content of 30-60% (11
5) is preheated to 500 to 700 ° C. in advance and then charged into the first combustor stage (1) to leave a compressor air residue (17).
The method of operating a combustor according to claim 14, wherein an air-fuel mixture having a combustion temperature of 800 to 1050 ° C is prepared by mixing with.