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EP2558781B1 - Générateur de turbulence pour un brûleur - Google Patents

Générateur de turbulence pour un brûleur Download PDF

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Publication number
EP2558781B1
EP2558781B1 EP11711807.5A EP11711807A EP2558781B1 EP 2558781 B1 EP2558781 B1 EP 2558781B1 EP 11711807 A EP11711807 A EP 11711807A EP 2558781 B1 EP2558781 B1 EP 2558781B1
Authority
EP
European Patent Office
Prior art keywords
swirl
swirl generator
hub
burner
fuel
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.)
Not-in-force
Application number
EP11711807.5A
Other languages
German (de)
English (en)
Other versions
EP2558781A1 (fr
Inventor
Karsten Jordan
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.)
Siemens AG
Original Assignee
Siemens AG
Siemens Corp
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 Siemens AG, Siemens Corp filed Critical Siemens AG
Publication of EP2558781A1 publication Critical patent/EP2558781A1/fr
Application granted granted Critical
Publication of EP2558781B1 publication Critical patent/EP2558781B1/fr
Not-in-force legal-status Critical Current
Anticipated expiration legal-status Critical

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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
    • F23R3/02—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
    • F23R3/12—Air inlet arrangements for primary air inducing a vortex
    • F23R3/14—Air inlet arrangements for primary air inducing a vortex by using swirl vanes

Definitions

  • the invention relates to a swirl generator, in particular for a burner in a gas turbine.
  • the invention further relates to a burner and a gas turbine.
  • a generic swirl generator is out EP 1 614 967 A1 known.
  • the in EP 0 276 696 B1 described burner is a hybrid burner for Vormisch plante with gas and / or oil, as it is used in particular for gas turbine plants.
  • the burner comprises a central fuel supply assembly, in which a pilot burner system is integrated, which is operable with gas and / or oil as a so-called diffusion burner or as a separate premix burner.
  • a pilot burner system is integrated, which is operable with gas and / or oil as a so-called diffusion burner or as a separate premix burner.
  • the central fuel supply assembly is surrounded by a main burner system having an air supply annular channel system with therein a swirl blading with a plurality of blades and nozzle pipes for pre-mixing with gas arranged upstream of the blades.
  • inlet nozzles for oil in the area of the swirl blading which allow premixing of the main air flow with oil.
  • the fuel gas can also be injected into the air duct through nozzle openings arranged in the swirl vanes itself, as described, for example, in US Pat EP 0 580 683 B1 is described.
  • the object of the invention is to provide a swirl generator with improved storage for swirl blades.
  • the movable bearing is arranged in the outer boundary wall. If the blades are connected to the hub via a fixed bearing, fuel can be supplied to the supply channels in the blades centrally via distribution channels in the hub in order to inject fuel into the airflow via outlet nozzles in the supply channels.
  • an inner part of the floating bearing on the spherical bearing surface and an outer part of the movable bearing a cylindrical bearing surface.
  • the radius of the spherical bearing surface is interpreted according to the pivot point of the tilt, it may be advantageous if the spherical bearing surface is spherical.
  • the radius can also vary as long as jamming in the floating bearing is excluded, expediently, the radius of the spherical bearing surface is equal to or greater than half a diameter of the outer part of the floating bearing.
  • the inner part is formed by the surface of a blade nut, which is screwed to the swirl blade.
  • the swirl vane comprises a first and a second fuel channel, which can better control the emissions compared to a single fuel channel and further increase the combustion stability.
  • the swirl blade by means of molded as cylindrical hollow elements sliding seats within which the fuel channels extend, is connected to the hub, so that the fuel channels are in fluid communication with gas distribution channels of the hub.
  • such a swirl generator is provided in a burner.
  • the burner is further provided in a gas turbine.
  • FIG. 1 shows schematically and by way of example the burner 2 according to the invention in a highly schematic diagram, on the basis of which the burner 2 underlying concept is described.
  • the burner 2 according to the invention which can optionally be used in conjunction with a plurality of identical burners, for example in the combustion chamber of a gas turbine plant, comprises an inner pilot burner system and a main burner system concentrically surrounding the pilot burner system. Both the pilot burner system and the main burner system may optionally be operated with gaseous and / or liquid fuels, such as natural gas or fuel oil.
  • the pilot burner system includes an inner oil supply passage 14 concentrically surrounded by an inner annular gas supply passage 15. This is in turn surrounded by an inner air supply channel or Inertstoffzubuchkanal 16 concentrically.
  • a suitable ignition system may be arranged in or on this air supply channel 16 (not shown in the figure).
  • the pilot burner system has a combustion chamber 17 facing the outlet opening 18, in whose area a swirl blading 19 is arranged in the air supply channel. Gas can be injected from the inner gas supply channel 15 in the area of the swirl blading or upstream of the swirl blading into the air supply channel 16 by means of nozzle openings 20. Oil from the oil supply channel can be injected by means of oil nozzles 21 downstream of the swirl blading in the supplied air or the supplied inert material.
  • the task of the pilot burner system is to maintain the burners in a stable combustion mode, since this is usually operated with a tendency to instabilities lean mixture.
  • the pilot burner system can be operated in a conventional manner with oil and / or gas as a diffusion burner, in which the fuel is injected directly into the flame.
  • the main burner system surrounding the pilot burner system includes a radial outer air supply passage 22, also annular air passage called, through which a plurality of swirl blades 5 extend a swirl blading.
  • These swirl vanes 5 have first gas nozzles 23 and second gas nozzles 24, through which fuel gas can be injected into the air flowing in through the radial air supply duct 22.
  • air can be injected into the air flowing through the air supply channel 22 by means of oil nozzles 25.
  • the first gas nozzles 23 and second gas nozzles 24 located in the swirl blades 5 and the oil nozzles 25 are supplied with fuel via a radially inner fuel supply arrangement, the so-called hub 3.
  • first and second annular gas distribution channels 26 and 27 are arranged, which supply the gas nozzles 23 and 24 with gas.
  • annular oil distribution channel 28 is arranged, which supplies the oil nozzles 25 with oil.
  • the gas distribution channels 26, 27 and the oil distribution channel 28 are supplied via gas supply channels 29, 30 and via an oil supply channel 31 with the appropriate fuel.
  • For the oil supply channel 31 is a separate oil supply pipe 32 before.
  • FIG. 2 shows a side view of a known gas turbine premix burner 2 and in particular the swirl generator 1.
  • Swirl vanes 5 are welded on the hub side 3 of the swirl generator 1 (fixed bearing 6) and on the outside of the swirl generator 1 on the outer boundary wall 4 in movable bearings (floating bearing 7) safe guided.
  • FIG. 3 shows a plan view of the gas turbine premix burner 2 of FIG. 2 .
  • FIG. 4 shows an enlarged partial cross-sectional view through a known burner hub 3 of a gas turbine premix burner 2 with swirl blade 5 and arranged in the swirl vane 5 the fuel passage 11 with the outlet nozzles 23.
  • the swirl blade 5 is mounted on the hub side with a sliding fit in the hub 3, that the fuel channel 11 of the swirl blade 5 is connected to an annular channel 26 in the hub 3, which via a separate pipe connection 29 (not in FIG. 4 shown).
  • the arrangement is circular, so that one has to imagine the annular channel 26 as a circle.
  • the swirl vane 5 On the side of the outer boundary wall 4, the swirl vane 5 has a fit in the form of a vane nut 10 which is screwed onto the radially outer end of the swirl vane 5 (and secured against loosening by swirl points after alignment of the swirl vane 5) and with its surface cylindrical inner bearing surface 9 of a movable bearing 7 according to the prior art forms.
  • FIG. 4 shows the axial movement 33 of the swirl blade 5 in the floating bearing 7 due to thermal expansion.
  • FIG. 5 shows a schematic diagram of a swirl blade 5 with two integrated, independently controllable fuel channels 11, 12.
  • the first fuel channel 11 with the outlet nozzles 23, for example, for injecting a first medium and the second fuel channel 12 via the outlet nozzles 24 can be used for injecting a second medium .
  • both media to be injected through the fuel channels 11, 12 of the swirl vanes 5 will be gaseous, for example the one natural gas and the other coal gas.
  • an inert material such as water vapor can be injected via these outlet nozzles 23, 24 if necessary.
  • Asymmetrically arranged fuel channels 11, 12 can now also radial thermal movements 34 result in addition to the axial heat movements.
  • a thus caused clamping in floating bearing 7 with cylindrical bearing surface 9 can now by the inventive solution of the problem, in which the movable bearing 7 has a spherical bearing surface 8, can be avoided.

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  • Engineering & Computer Science (AREA)
  • Chemical & Material Sciences (AREA)
  • Combustion & Propulsion (AREA)
  • Mechanical Engineering (AREA)
  • General Engineering & Computer Science (AREA)

Claims (10)

  1. Générateur (1) de turbulence pour un brûleur (2), comprenant un moyeu (3), une paroi (4) de démarcation extérieure entourant le moyen (3) et plusieurs pales (5) de turbulence, qui sont montées entre le moyeu (3) et la paroi (4) de démarcation extérieure et qui sont reliées au moyeu (3) ou à la paroi (4) de démarcation extérieure par respectivement un palier (6) fixe et un palier (7) libre; caractérisé en ce que le palier (7) libre a une surface (8) de palier bombée.
  2. Générateur (1) de turbulence suivant la revendication 1, dans lequel le palier (7) libre est disposé dans la paroi (4) de démarcation extérieure.
  3. Générateur (1) de turbulence suivant l'une des revendications 1 ou 2, dans lequel une partie intérieure du palier (7) libre a une surface (8) de palier bombée et une partie extérieure du palier (7) libre a une surface de palier cylindrique.
  4. Générateur (1) de turbulence suivant l'une des revendications 1 à 3, dans lequel la surface (8) de palier bombée est sphérique.
  5. Générateur (1) de turbulence suivant l'une des revendications 1 à 3, dans lequel un rayon de la surface (8) de palier bombée est supérieur ou égal à un demi-diamètre de la partie extérieure du palier (7) libre.
  6. Générateur (1) de turbulence suivant l'une des revendications 3 à 5, dans lequel la partie intérieure est formée par la surface d'un écrou (10) de pale, qui peut se visser à la pale (5) de turbulence.
  7. Générateur (1) de turbulence suivant l'une des revendications précédentes, dans lequel la pale (5) de turbulence entoure un premier canal (11) et un deuxième canal (12) pour du combustible.
  8. Générateur (1) de turbulence suivant la revendication 7, dans lequel la pale (5) de turbulence est reliée au moyeu (3) à l'aide de sièges coulissants sous la forme d'éléments creux cylindriques, à l'intérieur desquels s'étendent les canaux (11, 12) pour du combustible, de sorte que les canaux (11, 12) pour du combustible sont en liaison d'écoulement avec des canaux (26, 27) du moyeu (3) formant répartiteur de gaz.
  9. Brûleur (2) ayant un générateur (1) de turbulence suivant l'une des revendications précédentes.
  10. Turbine à gaz ayant au moins un brûleur (2) suivant la revendication 9.
EP11711807.5A 2010-04-15 2011-03-21 Générateur de turbulence pour un brûleur Not-in-force EP2558781B1 (fr)

Applications Claiming Priority (2)

Application Number Priority Date Filing Date Title
DE102010027808A DE102010027808A1 (de) 2010-04-15 2010-04-15 Drallerzeuger für einen Brenner
PCT/EP2011/054237 WO2011128179A1 (fr) 2010-04-15 2011-03-21 Générateur de turbulence pour un brûleur

Publications (2)

Publication Number Publication Date
EP2558781A1 EP2558781A1 (fr) 2013-02-20
EP2558781B1 true EP2558781B1 (fr) 2015-07-15

Family

ID=43881219

Family Applications (1)

Application Number Title Priority Date Filing Date
EP11711807.5A Not-in-force EP2558781B1 (fr) 2010-04-15 2011-03-21 Générateur de turbulence pour un brûleur

Country Status (4)

Country Link
EP (1) EP2558781B1 (fr)
CN (1) CN102859282B (fr)
DE (1) DE102010027808A1 (fr)
WO (1) WO2011128179A1 (fr)

Families Citing this family (4)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
DE102014201386A1 (de) * 2014-01-27 2015-07-30 Siemens Aktiengesellschaft Pilotbrenner als Bestandteil einer Brenneranordnung für die Druckvergasung fester und flüssiger Brennstoffe
EP2927598B1 (fr) * 2014-03-31 2018-12-19 Siemens Aktiengesellschaft Procédé destiné à remplacer une coupelle à aubes rotatives
DE102014206139A1 (de) * 2014-04-01 2015-10-01 Siemens Aktiengesellschaft Brennerkopf
DE102015204594A1 (de) * 2015-03-13 2016-09-15 Siemens Aktiengesellschaft Monolithische Brennerdüse

Family Cites Families (6)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
EP0276696B1 (fr) 1987-01-26 1990-09-12 Siemens Aktiengesellschaft Brûleur hybride pour fonctionnement en prémélange au gaz et/ou au mazout, notamment pour turbines à gaz
CH676735A5 (fr) * 1988-08-03 1991-02-28 Asea Brown Boveri
DE59204270D1 (de) * 1991-04-25 1995-12-14 Siemens Ag Brenneranordnung, insbesondere für gasturbinen, zur schadstoffarmen verbrennung von kohlegas und anderen brennstoffen.
EP1507119A1 (fr) * 2003-08-13 2005-02-16 Siemens Aktiengesellschaft Brûleur et méthode de fonctionnement d'une turbine à gaz
EP1614967B1 (fr) * 2004-07-09 2016-03-16 Siemens Aktiengesellschaft Procédé et système de combustion à prémélange
EP2161502A1 (fr) * 2008-09-05 2010-03-10 Siemens Aktiengesellschaft Brûleur à prémélange pour un combustible pauvre et riche

Also Published As

Publication number Publication date
CN102859282B (zh) 2015-01-07
WO2011128179A1 (fr) 2011-10-20
EP2558781A1 (fr) 2013-02-20
CN102859282A (zh) 2013-01-02
DE102010027808A1 (de) 2011-10-20

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