EP0029619B1 - Chambre de combustion pour turbine à gaz avec éléments de prévaporisation/prémélange - Google Patents

Chambre de combustion pour turbine à gaz avec éléments de prévaporisation/prémélange Download PDF

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Publication number
EP0029619B1
EP0029619B1 EP80200979A EP80200979A EP0029619B1 EP 0029619 B1 EP0029619 B1 EP 0029619B1 EP 80200979 A EP80200979 A EP 80200979A EP 80200979 A EP80200979 A EP 80200979A EP 0029619 B1 EP0029619 B1 EP 0029619B1
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EP
European Patent Office
Prior art keywords
combustion chamber
orifices
elements
flame retention
flame
Prior art date
Legal status (The legal status is an assumption and is not a legal conclusion. Google has not performed a legal analysis and makes no representation as to the accuracy of the status listed.)
Expired
Application number
EP80200979A
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German (de)
English (en)
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EP0029619A1 (fr
Inventor
Eduard Brühwiler
Hans Koch
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BBC Brown Boveri AG Switzerland
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BBC Brown Boveri AG Switzerland
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Classifications

    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F23—COMBUSTION APPARATUS; COMBUSTION PROCESSES
    • F23R—GENERATING COMBUSTION PRODUCTS OF HIGH PRESSURE OR HIGH VELOCITY, e.g. GAS-TURBINE COMBUSTION CHAMBERS
    • F23R3/00—Continuous combustion chambers using liquid or gaseous fuel
    • F23R3/28—Continuous combustion chambers using liquid or gaseous fuel characterised by the fuel supply
    • F23R3/286—Continuous combustion chambers using liquid or gaseous fuel characterised by the fuel supply having fuel-air premixing devices
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F23—COMBUSTION APPARATUS; COMBUSTION PROCESSES
    • F23R—GENERATING COMBUSTION PRODUCTS OF HIGH PRESSURE OR HIGH VELOCITY, e.g. GAS-TURBINE COMBUSTION CHAMBERS
    • F23R3/00—Continuous combustion chambers using liquid or gaseous fuel
    • F23R3/02—Continuous combustion chambers using liquid or gaseous fuel characterised by the air-flow or gas-flow configuration
    • F23R3/04—Air inlet arrangements
    • F23R3/10—Air inlet arrangements for primary air
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F23—COMBUSTION APPARATUS; COMBUSTION PROCESSES
    • F23R—GENERATING COMBUSTION PRODUCTS OF HIGH PRESSURE OR HIGH VELOCITY, e.g. GAS-TURBINE COMBUSTION CHAMBERS
    • F23R3/00—Continuous combustion chambers using liquid or gaseous fuel
    • F23R3/28—Continuous combustion chambers using liquid or gaseous fuel characterised by the fuel supply
    • F23R3/30—Continuous combustion chambers using liquid or gaseous fuel characterised by the fuel supply comprising fuel prevapourising devices
    • F23R3/32—Continuous combustion chambers using liquid or gaseous fuel characterised by the fuel supply comprising fuel prevapourising devices being tubular
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F23—COMBUSTION APPARATUS; COMBUSTION PROCESSES
    • F23D—BURNERS
    • F23D2209/00—Safety arrangements
    • F23D2209/10—Flame flashback

Definitions

  • the invention relates to the combustion chamber of a gas turbine according to the preamble of claim 1.
  • Gas turbines are increasingly subject to the stringent environmental regulations in many countries regarding exhaust gas composition. Above all, compliance with the regulations on the maximum permitted NO x emissions is extremely difficult when operating a gas turbine.
  • a combustion chamber of the type mentioned at the outset for the purpose of reducing the pollutants liberated during combustion is known from US-A-4 100 733. It is aimed there that the emission values of pollutants without the injection of aids such as water or steam into the combustion chamber under the allowable values fall from the emission regulations. This is achieved by adding a pre-mixing / pre-evaporation phase to the actual combustion process. For this purpose, the pre-mixing / pre-evaporation is carried out in several tubular elements, the fuel being mixed with air from the compressor with a large excess of air.
  • This known combustion chamber is designed in two stages and is operated in such a way that the first stage is operated at low load, i. H. that about half of the tubular elements are used in terms of fuel. The second stage is only operated at higher loads. The aim here is that the mixture in the first stage is always rich enough to ensure stable combustion. This can be achieved either by changing the resistance at the air inlets on the distribution chamber side or by using fuel injectors of different sizes.
  • the present invention is based on the object of improving a combustion chamber of the type mentioned in such a way that first of all a reliable ignition of all elements is ensured and that then a re-ignition of the Flame from the combustion chamber into the interior of the tubular elements is prevented.
  • pilot elements are used in the present invention, it is expedient to distribute them geometrically evenly among the tubular elements used. If these are still put into operation by initial ignition, then one does not apply to the elements which are put into operation later: the flame jumps from the pilot elements to the surrounding ones, favored by the fact that the flame holders of these pilot elements are provided either with swirl bodies or with oblique holes, so that divergent tongues of flame are generated, which additionally promote good caloric and air-jet mixing, which is reflected in a more uniform temperature and speed distribution after the combustion chamber.
  • both the oblique openings and the openings in the flame holder parallel to the axis of the flame holder have a length of at least 1.5 opening diameters. Through this opening, the air-fuel oil vapor mixture or the air-fuel gas mixture flows to the combustion chamber at an increased speed, as a result of which flame back ignition is avoided.
  • a further embodiment in order to avoid a flashback, is to design the openings in the flame holder as injectors, so that air is introduced into the boundary layer of the openings.
  • Another configuration of the openings in the flame holder is to design them as diffusers. With this solution, a higher speed is possible with the same pressure loss. The higher speed offers more security against the flame reigniting from the combustion chamber. To ensure the safe operation of the diffuser, it is necessary to add a cylindrical section with a minimum length of 1.5 diameter.
  • FIG. 1 shows schematically the concept of such a combustion chamber.
  • a larger number of tubular elements 2 are arranged in the upper area of the combustion chamber casing 1, which optimally fill the available space.
  • FIG. 2 An example of such an arrangement is shown in FIG. 2, in which thirty-seven tubular elements 2 are arranged. However, this number is not mandatory, because it depends on the size of the combustion chamber, which in turn is dependent on the desired combustion output.
  • a support bridge 27, on which the tubular elements 2 are connected by means of end nuts 5, is anchored to a support rib 23. In order to connect the tubular elements 2 to the support bridge 27, other types of connection can of course also be used.
  • the tubular elements 2 are guided laterally in the lower region by means of a guide plate 6.
  • the tubular elements 2 can also be guided individually, as can be seen in FIG. 16, in which case no guide plate is then used, but individual guide rings 25 take on this task.
  • the guide rings 25 are also carried here by support elements 22 which are firmly connected to the support bridge 27.
  • the tubular elements 2 can also be anchored differently than with the support bridge 27 shown, but in such cases it will always be necessary to ensure that the chosen anchoring is placed as far away from the combustion chamber 7 as possible so that the thermal expansions cannot have a disruptive effect.
  • the greater part of the compressed air which is provided in the compressor (not shown), flows through the openings 9 into a distribution chamber 19 provided in the combustion chamber casing I, which distributes downwards through the support bridge 27 and upwards through the cover 35 flanged on the flange rib 38 is narrowed down. From this distribution chamber 19, the compressed air then flows through the air funnels 14 into the individual tubular elements 2.
  • the fuel supply is provided for each tubular element 2 by means of a fuel line 4, a fuel nozzle 15, which projects into the tubular element 2 and has one or more fuel openings (not shown), atomizing the fuel against the air inflow direction. The fuel does not necessarily have to be injected against the air flow.
  • fuel gas natural gas
  • the gas is blown in in the direction of air inflow. It is also possible to input and burn oil and gas at the same time.
  • fuel oil to achieve finer atomization, the smallest possible amount of compressed air can be added through the nozzle 15, which has an overpressure compared to the process pressure.
  • the fuel therefore mixes with the incoming compressed air in such a way that a pre-mixing nor evaporation process takes place in the tubular element 2.
  • This process can be intensified due to the turbulence which arises by inserting a flange 34 at the air inlet of the tubular element 2, as can be seen in FIG. 16.
  • the fuel injection or fuel injection through the fuel nozzle 15 must be carried out at an optimal distance from the mouth 34, but still in the region of the turbulence that has arisen.
  • the fuel evaporates and mixes with the air.
  • the degree of evaporation is stronger, the greater the temperature and the residence time and the smaller the drop size of the atomized fuel.
  • the critical time until the mixture self-ignites decreases, so that the length of the tubular elements 2 is coordinated in such a way that the best possible evaporation results for the shortest possible time.
  • gas there is no evaporation; the gas only needs to be distributed evenly with the air.
  • a remaining amount of compressed air does not flow into the distribution chamber 19, but into the combustion chamber casing I through the openings 26, is distributed between the tubular elements 2 and flows through the openings 18 recessed in the flame holder edge 13 (FIG. 2) to the combustion chamber, as a result of which the outer part of the flame holder 3 is cooled in such a way that the risk of burning, which is latent especially when producing divergent flame tongues, is counteracted.
  • the combustion of the mixture is aimed at with the largest possible excess of air, which is given by the fact that the flame is still burning and further by the fact that not too much CO is produced.
  • a good optimization can be present, for example, if the air content of the mixture is kept at 1.8 times the stoichiometric value.
  • the lower terminating rib 24 prevents free convection of the hot air from the combustion chamber 7, the terminating rib 24 also being cooled with the same residual air flowing in through the openings 26, which then flows out through the openings 18 of the adjacent flame shader edges 13 to the combustion chamber 7.
  • the flame holder 3 which forms the end of the downstream part of the tubular element 2, has the task of preventing the flame from reigniting from the combustion chamber 7 into the interior of the tubular element 2.
  • the inner wall of the combustion chamber casing 1 is provided with a cooling system (not shown) in the area of the combustion chamber 7, that is to say from the flame heater 3.
  • the flame holder 3 shown has a number of cylindrical holes 21 which run parallel to the axis of the tubular element 2. If additional divergent flame tongues are to be produced, as can be seen in FIGS. 4 and 5, the holes 30 in the flame holder 3, with the exception of the central hole, can be made obliquely in radial planes of the flame holder 3, the angle 38 from the center to the periphery of the flame holder 3 steadily increases or remains the same.
  • the length of both the parallel holes 21 and the oblique holes 30, 31 must be at least 1.5 hole diameter.
  • the resulting increased mixture speed in the holes 21, 30, 31 and the length of the holes counteract flame reignition from the combustion chamber 7.
  • the number of holes 21, 30, 31 must be adapted to the given conditions. In the example shown in FIG. 7, there are for example twenty-one holes 31.
  • the flame holder 3 consists of an upper plate 3a and a lower plate 3b, between which a channel 10 connected to the openings 8 runs.
  • the openings 8 provided in the flame holder 3 are each lined with two slightly conical bushes 11, 12, these overlapping in the region of the channel 10 telescopically and with play 16. Burning back of the flame from the combustion chamber 7, in particular in the boundary layer along the wall of the sleeve 12, is counteracted by introducing compressed air through the channel 10, which flows through the play 16 along the endangered wall of the sleeve 12 with the mixture . Flow separations, which would favor reignition, are prevented by the conical shape of the openings 8.
  • the flame holder 3 shown in FIG. 11 has sixteen openings 8, which are fed symmetrically from two channels 10 with compressed air.
  • the supply of the openings 8 made in the flame holder 3 with compressed air can be fulfilled by other channel configurations.
  • the openings 8 in the flame holder 3 are designed as diffusers 39.
  • an initial cylindrical bore 32 is followed by a section formed as a diffuser 40, which is followed by a cylindrical bore 33 of larger diameter than the inlet bore 32, which has a length of at least 1.5 bore diameter.
  • a higher speed at the narrowest point is possible with the same pressure loss, which is reflected in greater safety against flame reignition from the combustion chamber 7.
  • the beginning of the flame in the combustion chamber 7 is brought into a corresponding distance from the diffuser 40 through the cylindrical bore 33.
  • the flow in the subsequent cylindrical part 33 will again rest against the wall.
  • the flame holder 3 can, as shown in FIG. 9 10 and 10, can be provided with a swirl body 28, the mixture being directed to the combustion chamber 7 in a swirling manner through its openings 41, for example fourteen in number.
  • the swirl body 28 promotes good air-jet mixing of the fuel / air mixture and good heat distribution, which results in a homogeneous temperature and speed distribution after the combustion chamber 7, with the effect that the turbine, not shown, is acted upon uniformly.
  • tubular elements 2 and the individual flame holder 3 itself in combination according to Figures 3, 4/5, 6/7/8, 9/10, 11/15 or 14 can be formed.
  • the combustion chamber casing 1 is optimally filled with a larger number of tubular elements 2. As shown in FIG. 2, among the thirty-seven tubular elements 2 used, thirteen pilot elements 17 are geometrically evenly distributed. When the combustion chamber is started, pilot elements 17 are initially put into operation by an initial ignition unit (not shown). When the load increases, the flame jumps from the pilot elements 17 to the surrounding ones, which have just been put into operation.
  • the openings 8 in the flame holder 3 of the pilot elements 17 can optionally be formed after the holes 30 and / or after the holes 31.
  • the use of swirl bodies 28 can also be provided for the pilot elements 17, which, like the holes 30, 31, also produce divergent flame tongues and thus favor the ignition of the surrounding tubular elements 2.
  • the flame holder 3 is hexagonal 20 in the circumferential direction. From these figures it can also be seen that the openings 18 made in the flame holder base 13 are evenly distributed between the hexagonal shape 20 and the tubular element. A polygon game 29 absorbs the thermal expansion in this area.
  • an orifice 34 is used, which in this area, that is to say directly around the fuel nozzle 15, generates turbulence which is suitable for this purpose; to intensify the premixing, atomization and pre-evaporation process in addition to the measures described above, that is to say in particular by the fine injection of the fuel against the direction of air inflow.
  • turbulence amplifiers can also be used instead of the on-board mouth 34.

Claims (12)

1. Chambre de combustion d'une turbine à gaz, dans laquelle, à l'intérieur de son enveloppe (1), la chambre de distribution d'air (19) et l'espace de combustion (7) sont séparés localement l'un de l'autre et dans laquelle, entre la chambre de distribution (19) et l'espace de combustion (7) sont installés plusieurs éléments tubulaires (2) dans lesquels s'effectuent le prémélange et la prévaporisation de l'huile combustible amenée par des ajustages (15) à l'extrémité située du côté de la chambre de distribution et/ou le prémélange du gaz de combustion amené à l'extrémité située du côté de la chambre de distribution par des ajutages (15) avec l'air du compresseur dans des proportions déterminant un excès d'air important, caractérisée en ce qu'entre les éléments tubulaires (2) se trouvent un ou plusieurs éléments pilotes (17) et chaque élément tubulaire (2) ainsi que le ou les éléments pilotes (17) sont fermés à leur extrémité située du côté de l'espace de combustion par un élément accrocheur de flamme (3) pourvu d'une ou de plusieurs ouvertures (8).
2. Chambre de combustion suivant la revendication 1, caractérisée en ce que dans le cas de plusieurs éléments pilotes (17), ces éléments sont répartis géométriquement de manière uniforme parmi les éléments tubulaires (2) de telle façon que, lors d'une mise en service, échelonnée en fonction de la charge de la machine, des éléments tubulaires individuels (2), la flamme saute chaque fois aux éléments environnants.
3. Chambre de combustion suivant la revendication 1, caractérisée en ce que l'injection du combustible amené par les ajustages (15) s'effectue dans un sens opposé à celui de l'air entrant.
4. Chambre de combustion suivant la revendication 1, caractérisée en ce que les ouvertures (8) dans l'élément accrocheur de flamme (3) sont des trous cylindriques parallèles à l'axe de l'élément tubulaire (2) dont la longueur est s= à 1,5 fois leur diamètre.
5. Chambre de combustion suivant la revendication 1, caractérisée en ce que les ouvertures (8) dans l'élément accrocheur de flamme (3) sont des trous (30) qui s'étendent obliquement dans des plans radiaux de l'élément accrocheur de flamme (3), l'angle (36) du centre vers la périphérie de l'élément accrocheur de flamme (3) augmentant de manière continue ou restant constant et la longueur des trous (30) étant , à 1,5 fois leur diamètre.
6. Chambre de combustion suivant la revendication 1, caractérisée en ce que les ouvertures (8) dans l'élément accrocheur de flamme (3) sont des trous (31) qui s'étendent obliquement dans des plans tangentiels de l'élément accrocheur de flamme (3), l'angle (37) du centre vers la périphérie de l'élément accrocheur de flamme (3) allant en augmentant de manière continue ou restant constant et la longueur des trous (31) étant -- à 1,5 fois leur diamètre.
7. Chambre de combustion suivant la revendication 1, caractérisée en ce que les ouvertures (8) dans l'élément accrocheur de flamme (3) sont pourvues de corps hélicoïdaux (28).
8. Chambre de combustion suivant la revendication 1, caractérisée en ce que l'élément accrocheur de flamme (3) est formé d'une plaque supérieure (3a) et d'une plaque inférieure (3b) entre lesquelles s'étend un canal (10) en communication avec les ouvertures (8) et les ouvertures (8) sont garnies chacune de deux douilles coniques (11, 12) qui, dans la zone du canal (10), se chevauchent de manière télescopique et avec un certain jeu (16) grâce à quoi l'agent qui arrive par le canal (10) sort avec le mélange de l'élément tubulaire (2).
9. Chambre de combustion suivant la revendication 1, caractérisée en ce que les ouvertures (8) dans l'élément accrocheur de flamme (3) ont la forme de diffuseurs (40) prolongés par des ouvertures cylindriques (33), leur longueur étant au moins égale à 1,5 fois leur diamètre.
10. Chambre de combustion suivant la revendication 1, caractérisée en ce que plusieurs ouvertures (18) sont ménagées dans le bord de l'élément accrocheur de flamme (13), autour de la paroi extérieure de l'élément tubulaire (2).
11. Chambre de combustion suivant la revendication 1, caractérisée en ce que la périphérie extérieure de l'élément accrocheur de flamme (3) a la forme d'un polygone (20).
12. Chambre de combustion suivant la revendication 1, caractérisée en ce que chaque élément tubulaire (2) est pouvu, à son extrémité située du côté de la chambre de distribution, d'un entonnoir d'admission d'air (14) suivi d'une embouchure à épaulement (34).
EP80200979A 1979-11-23 1980-10-16 Chambre de combustion pour turbine à gaz avec éléments de prévaporisation/prémélange Expired EP0029619B1 (fr)

Applications Claiming Priority (2)

Application Number Priority Date Filing Date Title
CH1044479 1979-11-23
CH10444/79 1979-11-23

Publications (2)

Publication Number Publication Date
EP0029619A1 EP0029619A1 (fr) 1981-06-03
EP0029619B1 true EP0029619B1 (fr) 1983-06-01

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US (1) US4408461A (fr)
EP (1) EP0029619B1 (fr)
JP (1) JPS5691132A (fr)
CA (1) CA1157280A (fr)
DE (2) DE2950535A1 (fr)

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US4539811A (en) * 1982-01-27 1985-09-10 The United States Of America As Represented By The Secretary Of The Navy Multi-port dump combustor
EP0526152A1 (fr) * 1991-08-01 1993-02-03 General Electric Company Chambre de combustion étagée à prémélange résistant au retour de flammes
FR2695460A1 (fr) * 1992-09-09 1994-03-11 Snecma Chambre de combustion de turbomachine à plusieurs injecteurs.
US5412938A (en) * 1992-06-29 1995-05-09 Abb Research Ltd. Combustion chamber of a gas turbine having premixing and catalytic burners
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JPS5691132A (en) 1981-07-23
CA1157280A (fr) 1983-11-22
DE3063624D1 (en) 1983-07-07
JPH0130055B2 (fr) 1989-06-15
EP0029619A1 (fr) 1981-06-03
DE2950535A1 (de) 1981-06-11
US4408461A (en) 1983-10-11

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