EP0125572B1 - Brûleur polycombustible - Google Patents

Brûleur polycombustible Download PDF

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Publication number
EP0125572B1
EP0125572B1 EP84105008A EP84105008A EP0125572B1 EP 0125572 B1 EP0125572 B1 EP 0125572B1 EP 84105008 A EP84105008 A EP 84105008A EP 84105008 A EP84105008 A EP 84105008A EP 0125572 B1 EP0125572 B1 EP 0125572B1
Authority
EP
European Patent Office
Prior art keywords
outlet
burner
pipes
fuel
fuel supply
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
EP84105008A
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German (de)
English (en)
Other versions
EP0125572A1 (fr
Inventor
Hans Dipl.-Ing. Hoffeins
Richard Ing. Grad. Kalbfuss
Bora Dipl.-Ing. Ipek
Current Assignee (The listed assignees may be inaccurate. Google has not performed a legal analysis and makes no representation or warranty as to the accuracy of the list.)
BBC Brown Boveri AG Switzerland
Original Assignee
BBC Brown Boveri AG Switzerland
Priority date (The priority date 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 date listed.)
Filing date
Publication date
Application filed by BBC Brown Boveri AG Switzerland filed Critical BBC Brown Boveri AG Switzerland
Publication of EP0125572A1 publication Critical patent/EP0125572A1/fr
Application granted granted Critical
Publication of EP0125572B1 publication Critical patent/EP0125572B1/fr
Expired legal-status Critical Current

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Classifications

    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F23—COMBUSTION APPARATUS; COMBUSTION PROCESSES
    • F23D—BURNERS
    • F23D17/00—Burners for combustion conjointly or alternatively of gaseous or liquid or pulverulent fuel
    • F23D17/002—Burners for combustion conjointly or alternatively of gaseous or liquid or pulverulent fuel gaseous or liquid fuel

Definitions

  • the invention relates to a multi-fuel burner, in particular for the combustion chamber of a gas turbine, with outlet points for a plurality of fuels, which are connected by pipelines to associated fuel supply spaces arranged on the burner head, an expansion compensator being inserted into the connection between at least one outlet point and the associated fuel supply space, and wherein at least one outlet point comprises a plurality of outlet nozzles, which are arranged in a ring on a nozzle head.
  • a known multi-fuel burner of this type has a complex structure, in particular with regard to the design of the expansion compensators (WO-A-8 000 593).
  • the multi-fuel burner is intended for the combustion of fuel gas during commissioning, whereas the actual operation takes place with the combustion of liquid fuel, so that the nominal burner output required for the nominal operation of the burner is not required when burning fuel gases.
  • a burner for a liquid and a gaseous fuel has become known, in which a swirling of the fuel is to be achieved through different exit velocities of air and fuel (FR-A-1 249 283).
  • the fuel supply and the fuel outlet take place through straight, annular channels or through tubular channels which are arranged in a circular ring, the ends of the tubular channels not being connected to one another and therefore being able to expand freely.
  • This burner is not intended for the combustion of several combustion gases, each of which can achieve the full rated burner output.
  • a toroid burner has become known, which is provided for melting or heating material in furnaces (DE-A-2106 448).
  • This toroidal burner has an annular combustion chamber into which a fuel-air mixture enters in the direction of the longitudinal axis of the combustion chamber. Since the bottom of the annular combustion chamber is inclined to the longitudinal axis of the overall arrangement, the impression is given that the fuel or the fuel-air mixture would enter the combustion chamber at an angle to the axis of the combustion chamber.
  • our object of the invention is to provide a multi-fuel burner which, with a simple, inexpensive construction, enables problem-free simultaneous or alternate combustion of different combustion gases with a rated burner output and good efficiency.
  • the multi-fuel burner should be fully washed against the thermal loads that occur.
  • the outlet nozzles Due to the circular arrangement of the outlet nozzles, the openings of which are inclined outwards to the longitudinal axis of the multi-fuel burner, good mixing with the inflowing combustion air is achieved both when burning a single fuel and when burning several fuels, so that there is good combustion efficiency.
  • the dimensioning of the outlet points or nozzles for a full burner nominal output gives the possibility that the multi-fuel burner can be adapted to existing types of fuel gas.
  • outlet nozzles are part of the nozzle head, their mutual position remains itself thermally triggered movements of the burner head unchanged. The movements of the burner head therefore have no influence on the good mixing ratio between fuel and combustion air.
  • the outlet points are connected to the associated fuel supply spaces of the burner head by a large number of thin pipes. Since the pipes of one outlet point surround the pipes of the other outlet point in a ring shape, this results in a compact design.
  • the bends provided in the thin pipes provide expansion compensators in a particularly simple manner, which can also accommodate larger expansion differences without the risk of leaks.
  • the multi-fuel burner according to the invention therefore meets the combustion requirements placed on it with a simple, inexpensive construction.
  • more than two outlet points for fuel gases can be arranged in a simple manner on the stated solution. This ensures that the burner can be used in a wide variety of operating conditions.
  • the outlet nozzles consist of cylindrical channels.
  • the outlet nozzles of at least one outlet point can be connected individually and directly through the pipelines to the associated fuel supply spaces.
  • the outlet nozzles are connected to the associated fuel feed chambers by at least one outlet point with the interposition of a collecting space through the pipelines.
  • an outlet point for liquid fuels in the form of an atomizer nozzle is arranged in the central opening of the nozzle head. This measure significantly increases the usability of the multi-fuel burner according to the invention.
  • the multi-fuel burner shown in FIG. 1 has a nozzle head 10 in the form of an annular cylinder 11, in which the first outlet point 12 and the second outlet point 14 are each arranged for a fuel gas.
  • Both outlet points 12, 14 each consist of a multiplicity of outlet nozzles 16 and 18, respectively.
  • the outlet nozzles of each outlet point 12, 14 are arranged in an annular and evenly distributed manner in the nozzle head 10, the outlet nozzles 16 being the first outlet point concentrically surrounded by the outlet nozzles 18 of the second outlet point and, viewed in the radial direction, are arranged offset with respect to the outlet nozzles 18. It is particularly important that the radial distance d between the outlet nozzles 16 and 18 is as small as possible for a compact structure.
  • the outlets of the outlet nozzles 16, 18 are directed outwards at an angle a of 20 ° to 80 ° with respect to the longitudinal axis 20 of the multi-fuel burner.
  • the front outer edge of the ring-cylindrical nozzle head 10 is provided with a chamfer 22 or a circumferential surface inclined to the longitudinal axis 20, which is oriented such that the axes of the openings penetrate this chamfer 22 perpendicularly.
  • the axial length of the mouth area is short compared to the total length of the nozzle head 10 (ratio 1: 4 to 1: 6) as can be clearly seen from FIG. 1.
  • the outlet nozzles 16, 18 are incorporated in the nozzle head 10 as cylindrical bores.
  • a straight pipe 24 is connected at the upper end of the nozzle head, each parallel to the longitudinal Axis 20 of the multi-fuel burner extends and its other end opens into the essentially ring-cylindrical burner head 26 which is coaxial with the nozzle head.
  • cylindrical bores 28 extending in the direction of the longitudinal axis 20 are provided in the burner head 26 and open into an annular and concentric first fuel feed chamber 30 arranged at the upper end of the burner head.
  • This is provided with a first connection piece 32 pointing to the left in the sectional plane of FIG. 1 and running radially.
  • the connecting piece 32 can also run perpendicular to the plane of the drawing, that is, point to the viewer. If necessary, several connecting pieces can be provided.
  • outlet nozzles 18 of the second outlet point 14 are connected to a coaxial second fuel feed chamber 36 by further pipelines 34.
  • This is also annular and is incorporated in the burner head 26 below the first fuel supply chamber 30.
  • Connected to the second fuel supply space 36 is a radially extending second connecting piece 38 pointing to the right in the sectional plane of FIG. 1.
  • the further pipelines 34 surround the pipelines 24.
  • the further pipes 34 which are connected to the second outlet point 14, are each provided with an expansion compensator 40.
  • Figure 3 which shows a development of some of the annularly arranged tubes 24, 34 in the plane of the drawing, the design of these expansion compensators 40 can be clearly seen.
  • the other tubes 34 are provided with two changes of direction such that these tubes - starting from the nozzle head 10 - initially run straight and parallel to the longitudinal axis 20, then angled and at an angle a of 30 ° to 60 ° to the longitudinal axis 20 or to the respective tube longitudinal axis are aligned and are finally brought back in the direction of the longitudinal axis 20 by a further bend.
  • the bending is preferably carried out with the largest possible angle to the respective longitudinal axis of the pipeline in order to increase the effectiveness of the expansion compensator thus formed.
  • all pipelines are angled at the same angle and, when installed on a cylindrical surface, there is no overlap between these pipelines, but that they run side by side. This can be seen very clearly from FIG. 3, to which express reference is made.
  • the expansion compensators are preferably arranged approximately in the middle of the distance between the burner head 26 and the nozzle head 10. 6 and 7 and the associated description, further details can be found.
  • a coaxial cylindrical nozzle nozzle 42 which extends into the interior of the nozzle head 10, the lower end of which forms an outlet 44 for liquid fuels, for example fuel oil an atomizing nozzle 46 forms.
  • the upper end of the nozzle assembly 42 can open into a supply space for liquid fuels, which is not shown in the drawing.
  • a plurality of radially extending air guide or swirl plates 48 are provided in the region of the atomizer nozzle.
  • the air baffles 48 have the shape of circular ring segments.
  • An outer flange 50 with fastening bores 52 is also arranged at the lower end of the burner head 26 for fixing the multi-fuel burner to the combustion chamber, for example.
  • the supply and / or guide devices for the combustion air belonging to a multi-fuel burner or forming part of the multi-fuel burner are shown in FIG. 8.
  • FIG. 4 shows the detail IV of Figure 1 in a larger representation as a variant. While each of the outlet nozzles 16, 18 in the exemplary embodiment according to FIGS. 1 to 3 is directly connected to the associated fuel supply chamber 30, 36 by a pipe 24, 34, in the exemplary embodiment according to FIGS. 4 and 5 collectors 54, 56 are switched on between the outlet nozzles 18, 16 and the pipes 34, 24.
  • the outlet nozzles 16, 18 of each individual outlet point 12, 14 each open into a collector 56 and 54, respectively.
  • the pipes 34, 24, which lead to the fuel supply spaces, are connected to the collectors 54, 56.
  • the number of these pipelines 24, 34 can be less than the number of outlet nozzles 16, 18, if the remaining pipelines are advantageously evenly distributed and connected to the collectors 54, 56 and have a cross section sufficient for the transport of fuel gas or for sufficient transport of the fuel gas are dimensioned.
  • the collectors 54, 56 in the nozzle head 10 are designed as annular cavities with a rectangular cross section. This can easily be achieved with nozzle heads which are produced with the aid of a casting process.
  • the following guide values apply to the dimensioning of the multi-fuel burner according to the invention.
  • the diameter of the nozzle head and its thickness in the radial direction must be selected so that the number of outlet nozzles that are required to achieve the intended burner rating can be accommodated.
  • the placement of a central outlet for liquid fuels and / or the central supply of combustion air and the arrangement of baffles must be taken into account.
  • the nozzle head is to be dimensioned in the axial direction only with consideration of the design of the outlet nozzles and, if necessary, with regard to the arrangement of the collectors.
  • FIG. 6 shows a further pipeline 34 as a detail and in a view.
  • the expansion compensator 40 can be seen in the form of the bend in the further pipeline 34.
  • the direction of the bend with an angle a of 20 ° to 80 °, preferably 30 ° to 70 ° to the longitudinal axis 20, can be clearly seen.
  • the bend resiliently absorbs changes in length of the pipeline, it should be noted that the bend has such a sufficient length transversely to the longitudinal axis 20 that the bend can be resilient.
  • FIG. 7 shows a view of the further pipeline 34 from the direction VII of FIG. 6 in the ready-to-install state.
  • each further pipeline 34 in particular the area of the bend (expansion compensator 40), is designed in the form of a circular arc. This is necessary in order to be able to connect the outlet nozzles 14 arranged in a ring with the bores in the burner head 26 which are likewise arranged in a ring.
  • FIG. 8 shows a section of a gas turbine plant in vertical section with a multi-fuel burner according to the invention.
  • a plurality of rows of rotor blades 62 are fastened on the turbine shaft 60 and can rotate between associated rows of guide vanes 64.
  • an overflow housing 66 opens and forms a propellant gas inlet 68.
  • This is annular, so that the entire row of guide vanes and rotor blades can be acted upon by propellant gases.
  • the overflow housing 66 is formed approximately in the form of a torus in the region which is adjacent to the rotor blades and has an annular opening which forms the propellant gas inlet 68.
  • a radial cylindrical combustion chamber 74 adjoins the toroidal region of the overflow housing 66.
  • the combustion chamber 74 is bell-shaped and connected to the overflow housing 66 at its lower end.
  • the multi-fuel burner is arranged centrally in the upper closed end region of the combustion chamber 74.
  • the combustion chamber 74 and the overflow housing 66 are surrounded by a jacket 78 to form an intermediate space 76.
  • the combustion air is introduced into this intermediate space 76.
  • the combustion air is compressed in an axial compressor 80 integrated in the gas turbine system with guide vanes 81 and rotor blades 83, which has the common shaft 60 with the turbine, and is fed to the intermediate space 76 via a diffuser 82.
  • the nozzle head 10 of the multi-fuel burner projects into the combustion chamber 74 and is surrounded by radially extending and evenly distributed guide vanes 84 made of sheet metal for the combustion air.
  • the guide vanes 84 are each designed in the manner of proppellers and are arranged at such a mutual spacing that combustion air can enter the combustion chamber 74 from the intermediate space 76 between the guide vanes 84.
  • the outline of the guide vanes can be clearly seen from FIG. 8.
  • the number of guide vanes is between 8 and 16 pieces. Further combustion air can enter through the radial openings 88 of the combustion chamber wall. The flow of the combustion air is indicated by arrows.
  • the multi-fuel burner penetrates the space 76 in a vertical direction as far as the outer space 86, and the flange 50 of the burner head 26 is fastened on the outside of the upper horizontal region of the jacket 78.
  • the first connecting piece 32 is provided with a pipe 90 through which a fuel gas, for. B. a fuel gas with a low calorific value can be supplied.
  • a pipe 92 is attached closed, through which another fuel gas, e.g. B. a fuel gas with a higher calorific value can be supplied.
  • the upper end of the burning head 26 is closed by a cover 94, which is penetrated by the nozzle assembly 42.
  • the upper end of the nozzle assembly 42 is also closed with a lid 96 and provided with a pipeline 98 through which a liquid fuel, e.g. B. fuel oil can be supplied.
  • a liquid fuel e.g. B. fuel oil
  • the upper end of the nozzle assembly 42 forms the fuel supply space for liquid fuel.
  • combustion air flows through the annular space 100, which is present between the nozzle assembly 42 and the pipes 24, into the combustion chamber 74, which has a circular cross section (cf. FIG. 1).
  • the combustion air flows from the intermediate space 76 through the gaps formed between the pipes 24 and 34 into the annular space 100 and from here through the swirl plates 48 into the combustion chamber.
  • This air is used primarily for the combustion of the liquid fuel, which enters the combustion chamber under pressure through the atomizing nozzle 46.
  • the vortex plates 48 run in the radial direction and are in large numbers, for. B. 8 to 12 pieces, evenly arranged around the atomizer nozzle 48.
  • the shape of the swirl plates 48 is clearly shown in FIG. 1.
  • the fuels are burned individually or in any combination by the multi-fuel burner in the combustion chamber 74, and the hot propellant gases produced flow to the propellant gas inlet 68. From here, the propellant gases flow to the left to the guide and rotor blades 64, 62 of the gas turbine, see above that the turbine shaft 60 is driven.
  • the burner rating can already be achieved by operating a single outlet point 12, 14, 44.
  • the rated burner output is the output for which the burner is intended and built.

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  • Engineering & Computer Science (AREA)
  • Chemical & Material Sciences (AREA)
  • Combustion & Propulsion (AREA)
  • Mechanical Engineering (AREA)
  • General Engineering & Computer Science (AREA)
  • Pre-Mixing And Non-Premixing Gas Burner (AREA)
  • Pressure-Spray And Ultrasonic-Wave- Spray Burners (AREA)
  • Gas Burners (AREA)

Claims (6)

1. Brûleur polycombustible, notamment pour la chambre de combustion d'une turbine à gaz, comportant des sorties (12, 14) pour plusieurs combustibles, lesquelles communiquent par des conduites (24, 34) avec des volumes d'amenée de combustible (30, 36) qui leur sont affectés et sont agencés sur la tête (26) du brûleur, un compensateur de dilatation (40) étant inséré dans la communication entre au moins une sortie (14) et le volume d'amenée de combustible (36) qui lui est affecté, au moins une sortie (12, 14) comportant une pluralité de gicleurs de sortie (16, 18) agencés en couronne circulaire sur une tête porte-gicleurs (10), caractérisé par les caractéristiques suivantes :
des sorties (12,14) sont prévues pour au moins deux combustibles gazeux, chacune comportant une multitude de gicleurs de sortie (16, 18) qui sont agencés en couronne circulaire :
les débouchés des gicleurs de sortie (16, 18) sont dirigés vers l'extérieur en étant inclinés d'un angle de 20° à 80°, de préférence de 50° à 70°, par rapport à l'axe longitudinal (20) du brûleur, et sont disposés sur un chanfrein (22) du bord extérieur de la tête porte-gicleurs (10), avec un intervalle mutuel (d) aussi réduit que possible ;
chacune des sorties (12,14) pour gaz combustible est dimensionnée, pour ce qui est du nombre et/ou de la section droite des gicleurs de sortie y afférents (16, 18), de manière à autoriser le passage d'un courant de gaz combustible permettant d'atteindre la puissance nominale du brûleur ;
chacune des sorties (12, 14) pour gaz combustible est reliée au volume d'amenée de combustible (30, 36) y afférent par une pluralité de conduites tubulaires (24, 34) qui sont minces par rapport à l'épaisseur de la tête porte-gicleurs (10) ;
les conduites tubulaires (34) de l'une des sorties (14) entourent en forme de couronne circulaire les conduites tubulaires (24) de l'autre sortie (12), également disposées en forme de couronne circulaire ;
le compensateur de dilatation (40) prévu dans la communication est formé par deux coudes des conduites tubulaires (34), lesquelles suivent un tracé qui, en partant de la tête porte-gicleurs (10), est d'abord rectiligne et parallèle à l'axe longitudinal (20) du brûleur, puis comporte un coude de 30° à 60° par rapport à l'axe longitudinal de la conduite, et présente ensuite un deuxième coude rétablissant le parallélisme avec l'axe longitudinal (20), et va à la tête (26) du brûleur qui est alignée sur la tête porte-gicleurs (10).
2. Brûleur selon revendication 1, caractérisé en ce que les gicleurs de sortie (16, 18) sont constitués par des canaux cylindriques.
3. Brûleur selon revendication 1 ou 2, caractérisé en ce que les gicleurs de sortie (16, 18) d'au moins une sortie (12, 14) communiquent, individuellement et directement, par les conduites tubulaires (24, 34), avec les volumes d'amenée de combustible (30, 36) correspondants.
4. Brûleur selon revendication 1 ou 2, caractérisé en ce que les gicleurs de sortie (16, 18) d'au moins une sortie (12, 14) communiquent avec les volumes d'amenée de combustible correspondants par les conduites tubulaires (34, 24), à chaque fois avec interposition d'un volume collecteur (54, 56).
5. Brûleur selon l'une quelconque des revendications 1 à 4, caractérisé en ce que, considérés dans la direction de l'axe longitudinal (20), les volumes d'amenée de combustible (30, 36) sont agencés l'un derrière l'autre.
6. Brûleur selon l'une quelconque des revendications 1 à 5, caractérisé en ce qu'une sortie (44) pour combustibles liquides est aménagée, sous la forme d'un gicleur de pulvérisation (46), dans l'ouverture centrale de la tête porte-gicleurs (10).
EP84105008A 1983-05-10 1984-05-03 Brûleur polycombustible Expired EP0125572B1 (fr)

Applications Claiming Priority (2)

Application Number Priority Date Filing Date Title
DE19833317035 DE3317035A1 (de) 1983-05-10 1983-05-10 Mehrstoffbrenner
DE3317035 1983-05-10

Publications (2)

Publication Number Publication Date
EP0125572A1 EP0125572A1 (fr) 1984-11-21
EP0125572B1 true EP0125572B1 (fr) 1987-09-09

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EP84105008A Expired EP0125572B1 (fr) 1983-05-10 1984-05-03 Brûleur polycombustible

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US (1) US4566268A (fr)
EP (1) EP0125572B1 (fr)
JP (1) JPS59208312A (fr)
DE (2) DE3317035A1 (fr)

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Publication number Priority date Publication date Assignee Title
DE4304213A1 (de) * 1993-02-12 1994-08-18 Abb Research Ltd Brenner zum Betrieb einer Brennkraftmaschine, einer Brennkammer einer Gasturbogruppe oder Feuerungsanlage

Also Published As

Publication number Publication date
DE3466057D1 (en) 1987-10-15
JPH0429930B2 (fr) 1992-05-20
DE3317035A1 (de) 1984-11-15
JPS59208312A (ja) 1984-11-26
EP0125572A1 (fr) 1984-11-21
US4566268A (en) 1986-01-28

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