EP2597374A1 - Agencement de brûleur pour une turbine à gaz - Google Patents

Agencement de brûleur pour une turbine à gaz Download PDF

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Publication number
EP2597374A1
EP2597374A1 EP11190962.8A EP11190962A EP2597374A1 EP 2597374 A1 EP2597374 A1 EP 2597374A1 EP 11190962 A EP11190962 A EP 11190962A EP 2597374 A1 EP2597374 A1 EP 2597374A1
Authority
EP
European Patent Office
Prior art keywords
burner
nozzles
carrier
fuel
openings
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.)
Withdrawn
Application number
EP11190962.8A
Other languages
German (de)
English (en)
Inventor
Christian Beck
Stefan Braun
Jan Martin Breitenbücher
Stefan Dederichs
Olga Deiss
Thomas Grieb
Arsène Brice Kadji
Oliver Schneider
Daniel Vogtmann
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
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 filed Critical Siemens AG
Priority to EP11190962.8A priority Critical patent/EP2597374A1/fr
Publication of EP2597374A1 publication Critical patent/EP2597374A1/fr
Withdrawn legal-status Critical Current

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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
    • 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
    • F23R3/34—Feeding into different combustion zones
    • F23R3/346—Feeding into different combustion zones for staged combustion
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F23—COMBUSTION APPARATUS; COMBUSTION PROCESSES
    • F23C—METHODS OR APPARATUS FOR COMBUSTION USING FLUID FUEL OR SOLID FUEL SUSPENDED IN  A CARRIER GAS OR AIR 
    • F23C2201/00—Staged combustion
    • F23C2201/20—Burner staging

Definitions

  • the invention relates to a burner arrangement for a gas turbine and a gas turbine, in particular a burner.
  • a burner may consist of a nozzle carrier with a number of nozzles, for example a total of sixteen nozzles, which can currently be switched in one or more stages. Each of these nozzles is controlled via its own valve in conjunction with a central distributor.
  • the nozzles usually consist of a piece of pipe with a welded tip.
  • the nozzles are passed through an opening in a burner support flange and secured to the flange by means of a compression fitting and sealed to the outside.
  • the nozzle is connected via a hose to the central distributor or a valve. This connection can also be realized by means of a cutting ring connection.
  • a burner arrangement for a gas turbine for introducing fuel comprises two fuel distribution channels, which are each connected to a supply line for fuels, and two groups of nozzles, which are arranged parallel to a flow direction and each of which has a group Fuel distribution channel is connected.
  • the flow direction may be the injection direction of the fuel or the flow direction be the gas turbine.
  • the proposed two-stage burner assembly is characterized by a simple and inexpensive distribution system, in which the number of components is significantly reduced. According to the invention, only a few supply lines are needed, which ensures better clarity and accessibility and minimizes the risk of incorrectly connected hoses.
  • a first group and a second group of nozzles may be supplied with identical or different fuel and may be activated simultaneously or individually.
  • Each group can have the same number of nozzles, here for example eight nozzles. This arrangement ensures a uniform injection of the fuel and thus the combustion. Other, unbalanced configurations can also be realized.
  • the burner assembly may include a burner carrier, wherein a first fuel rail is disposed at a downstream end side of the burner carrier and a second fuel rail is disposed at an upstream opposite end of the burner carrier, a first group of nozzles at the first fuel rail in communication therewith and wherein a second group of nozzles is arranged in openings of the burner carrier such that the nozzles are in communication upstream with the second fuel distributor channel and lie downstream on the side of the downstream end side.
  • the terms downstream and upstream refer to the flow direction. According to this structure, all the nozzles are oriented in the flow direction, with the first group of nozzles being arranged directly on the first fuel distributor channel and being supplied with fuel.
  • the second group of nozzles is arranged in openings of the burner carrier and extends through the burner carrier and optionally through the first fuel distributor channel.
  • the second fuel distribution channel is in communication with the upstream ends of the nozzles to fuel them.
  • the burner assembly may include a burner carrier having a downstream end face and an upstream opposing face, wherein both groups of nozzles are arranged in openings arranged on a circle in the downstream end face, the fuel distributor channels being at the upstream end side are arranged so that a part of the openings in the region of the one fuel distributor channel and the rest of the openings is in the region of the other fuel distributor channel.
  • the burner carrier may have a circular shape, wherein the circle of the openings may be concentric with the circumference of the burner carrier.
  • the fuel distribution channels may be formed in a hollow or interior of the burner carrier.
  • the burner assembly may comprise a burner carrier comprising a nozzle carrier having openings arranged on a circle in which the two groups of nozzles are arranged, and a distributor carrier arranged upstream of the nozzle carrier, wherein in the distributor carrier the two fuel distributor channels concentric annular grooves are formed with recesses, wherein the recesses are in communication with the openings.
  • the nozzle carrier may be a burner carrier flange
  • the distributor carrier may be, for example, a fuel distributor cap. Both elements can also be arranged as separate parts on a Brennerthereflansch. This variant can be easily manufactured.
  • the distributor carrier has only grooves or annular distribution channels, which in each one clamping for drilling and milling are made.
  • the openings for the nozzles and / or the fuel distributor channels may be arranged such that the nozzles of the first group and the second group are assigned alternately. This arrangement ensures a uniform injection of the fuel and thus the combustion. Other, unbalanced configurations can also be realized.
  • the burner carrier may be formed as a flange, cover or ring cover. Depending on the design or design of the burner support can be realized in different versions.
  • a lid or ring cover allows the use of a standardized flange with the ability to adapt the gas turbine with another cover to new operating modes.
  • a pilot burner or other burner or a fuel or air supply can be performed through the ring opening.
  • the nozzles and / or the supply lines for fuels may be fastened by means of a welded connection.
  • the fuel distributor channels can be arranged in an undulating manner in order to enable, in a simple manner, a preferably alternating assignment of nozzles or openings for the nozzles to the two groups or distribution channels.
  • the invention is directed to a gas turbine with a combustion chamber and with a flow direction, comprising a burner arrangement as described above.
  • a gas turbine with a combustion chamber and with a flow direction, comprising a burner arrangement as described above.
  • FIGS. 1 and 2 show a first example of a burner assembly or a gas turbine according to the invention.
  • FIGS. 3 and 4 show a second example of a burner assembly or a gas turbine according to the invention.
  • FIGS. 5 to 8 shows a third example of a burner assembly or a gas turbine according to the invention.
  • FIG. 1 is a plan view shown in the axial direction, while in FIG. 2 a sectional view according to the section line II-II of the plan view is shown. In the upper part of the sectional view of the upper vertical section of the section is shown, while in the lower part of the sectional view of the lower, oblique section of the section is shown.
  • the burner assembly 2 comprises a burner carrier 4, which is designed here annular and is connected to a housing 5 of the gas turbine 1, for example, screwed.
  • the burner carrier 4 is oriented perpendicular to a flow direction S of the fuel or the gas turbine 1.
  • An axis of rotation of the burner carrier 4 coincides with the flow direction S.
  • the burner carrier 4 can also be designed as a burner support flange or as here as a ring cover or cover.
  • the burner carrier 4 has a downstream or aligned end face 6 and an opposite upstream or oriented end face 7.
  • a first fuel distribution channel 8 is arranged, for example gas-tight welded.
  • the first fuel distribution channel 8 is in the form of a hollow annulus, which may be open on an end face facing the burner support 4.
  • openings for nozzles or fuel injector lances 9 are provided.
  • the nozzles 9 are gas-tight in the opening, for example, welded.
  • the nozzles 9 are aligned parallel to the flow direction, with a nozzle end being arranged in or on the first fuel distributor channel 8. At the other end of the nozzle is the nozzle tip, from which the fuel exits into the combustion chamber 3 or in the direction of the combustion chamber 3.
  • the first fuel distributor channel 8 is connected to a fuel supply line 10, via which a fuel is conducted into the first fuel distributor channel 8 and then through the nozzles 9.
  • the supply line 10 is designed as a tube which is gas-tight manner connected to the distribution channel 8, for example with a welded connection.
  • the supply line is brought in the radial direction at the first fuel distributor channel 8. Accordingly, the fuel distribution channel 8 has an opening in the outer peripheral surface.
  • a second fuel distribution channel 11 is arranged, for example welded gas-tight.
  • the second fuel distribution channel 8 also has the shape of a hollow circular ring, which may be open at an end face facing the burner carrier 4.
  • Both fuel distributor channels 8, 11 are arranged concentrically to the burner carrier 4 or the flow direction S and have at least approximately the same dimensions.
  • a plurality of openings 12 are provided, which extend in the axial direction, from the upstream end face 7 to the downstream end face 6.
  • the openings 12 are arranged circularly and concentrically to the flow direction S and are located in the region of the fuel distributor channels 8 and 11th
  • nozzles 9 are provided, which are aligned parallel to the nozzles 9, which are arranged on the first fuel distributor channel 8.
  • the nozzles 9 are gas-tightly secured in the openings 12, for example with a welded connection, and are in communication or in communication with the second fuel distributor channel 11.
  • These nozzles 9 extend through the interior of the first fuel distributor channel 8 and then further through an opening in the downstream
  • the lengths of the nozzles 9 are dimensioned such that all nozzle tips are at least approximately equidistant from the burner support 4 and protrude into the combustion chamber 3.
  • the second fuel distribution channel 11 is connected to a supply line 13 for fuels, via which a fuel in the second fuel distribution channel 11 and then passed through the nozzles 9.
  • the supply line 13 is designed as a tube which is gas-tightly connected to the distribution channel 11, for example with a welded connection.
  • the supply line 13 is brought in the axial direction on the second fuel distribution channel 11. Accordingly, the fuel distribution channel 11 has an opening in the upstream end face.
  • the nozzles 9 are divided into two stages or groups A and B. The division into two stages is based on in the FIG. 1 illustrated top view.
  • the nozzles 9 of the stage A and 14 are those nozzles 9, which are associated with the second fuel distributor channel 11, that is with him in connection, or are arranged in the openings 12.
  • the nozzles 9 of the stage B or 15 are those nozzles 9, which are associated with the second fuel distributor channel 11, that is, with him in connection, or are attached to it.
  • Each stage A, B comprises six nozzles 9, other values are possible, for example eight nozzles per stage.
  • the nozzles 9 of both stages A, B are arranged alternately on a circle, that is, a nozzle 9 of stage A is followed by a nozzle 9 of stage B.
  • This symmetrical arrangement allows a balanced fuel supply and combustion. For special configurations, this arrangement may be deviated. Then, both the arrangement of the individual nozzles 9 and the assignment to the stages can be changed.
  • fuel is passed through the supply lines 10, 13 in the fuel distribution channels 8 and 11 and injected from there by means of the nozzles 9 in the combustion chamber 3 or an anteroom.
  • both stages A, B or only one of the two stages can be active.
  • the fuel supply is controlled via two valves (not shown) in the supply lines 10, 13.
  • the in the FIGS. 3 and 4 illustrated burner carrier 4 has as in the Figures 1 and 2 a downstream end face 6 and an upstream end face 7.
  • the burner carrier 4 has a closed ring shape without a central passage opening. If necessary, a central passage opening can also be provided.
  • the two fuel distribution channels 8 and 11 are both arranged at the upstream end face 7.
  • the term "on" encompasses the positions on, below and in the region of the upstream end side 7.
  • the two fuel distribution channels 8 and 11 are arranged in the burner carrier 4 in one Interior under a lid 16.
  • the lid 16 and the surrounding edge or on the other hand the bottom of the interior can be referred to.
  • FIGS. 3 and 4 illustrated burner carrier 4 may as well as in FIG. 2 shown attached to a housing 5 or a flange of the gas turbine 1. It is also possible to fit the inner part with the cover 16 in a flange. In this case, the edge surrounding the cover 16 could represent the flange.
  • FIGS. 3 and 4 are all the nozzles 9 of the two stages A and B arranged in openings or holes 12 of the downstream end face 6 and fixed in a gas-tight manner, for example, welded.
  • the openings 12 are arranged circular and concentric with the circumference of the burner carrier 4.
  • the openings 12 or the nozzles 9 open into an interior space or cavity 17 of the burner carrier 4.
  • This interior space 17 is bounded on its outer peripheral surface by an edge and is on the upstream side with a detachable lid 16 locked.
  • the lid 16 is gas-tight and can be welded after assembly of the burner carrier 4.
  • the ring-shaped inner space 17 is subdivided into the two fuel distributor channels 8 and 11 by means of a wave-shaped dividing wall 18.
  • the first fuel distributor channel 8 is located radially inward and the second fuel distributor channel 11 is located radially outward.
  • the partition 18 is fixed in such a way or dimensioned in the height that with the lid 16 closed, the two fuel distribution channels 8, 11 preferably gas-tight are separated.
  • both channels 8, 11 can be milled into the body of the burner carrier 4, so that the partition wall 18 stops.
  • the partition wall 18 is designed wave-shaped or contoured such that a part of the openings 12 is in the region of one fuel distributor channel 8 and the rest of the openings 12 is in the region of the other fuel distributor channel 11. This assigns the holes 12 and thus the nozzles 9 to the two stages or groups A and B. About the shape of the channels 8, 11 and the partition 18, the number and assignment of the nozzles 9 to the stages A, B can be realized. Here, an alternating or alternating assignment is shown, alternatively, successive nozzles 9 can be assigned to one stage.
  • the cover 16 has two holes for the supply lines for the fuel 10 and 13.
  • the holes are arranged in the lid such that each feed communicates with only one channel.
  • the leads 10, 13 are gas-tight attached to the lid 16, for example by means of a welding process.
  • FIGS. 5 to 8 a further burner assembly 2 or part of a gas turbine 1 is shown.
  • the burner carrier 4 comprises a nozzle carrier 19 with openings 12 which are arranged on a circle in which the two groups of nozzles 9 are arranged.
  • the circle is concentric with the flow direction S.
  • the nozzle carrier 19 is fastened to the housing 5 of the gas turbine or may itself be a part of the burner carrier flange.
  • the nozzles 9 are gas-tight fastened in the openings 12, for example welded.
  • the burner carrier 4 comprises a distributor carrier 20, which is arranged upstream of the nozzle carrier 19.
  • the distributor carrier or cover 20 is annular and concentric to the flow direction S.
  • the distributor carrier 20 is gas-tightly attached to the burner carrier 4, here by means of screw connections.
  • the two fuel distributor channels 8, 11 are formed as concentric annular grooves.
  • the annular grooves are open on their downstream side.
  • recesses 21 are formed, which are part of the annular groove or communicate with this.
  • the recesses 21 of the outer groove 11 are directed inwardly and the recesses 21 of the inner groove are directed outwards.
  • at least partial regions of the recesses 21 lie on a circle whose radius corresponds to the circle of the openings 12, so that the recesses 21 are in communication with the openings 12. This ensures that the nozzles 9 are assigned to the two stages A and B via the fuel distributor channels 8, 11.
  • the leads 10, 13 may be welded.
  • the distributor carrier 20 can be easily manufactured, the fuel distributor channels 8, 11 and the openings can be milled and drilled in one clamping.

Landscapes

  • Engineering & Computer Science (AREA)
  • Chemical & Material Sciences (AREA)
  • Combustion & Propulsion (AREA)
  • Mechanical Engineering (AREA)
  • General Engineering & Computer Science (AREA)
  • Gas Burners (AREA)
EP11190962.8A 2011-11-28 2011-11-28 Agencement de brûleur pour une turbine à gaz Withdrawn EP2597374A1 (fr)

Priority Applications (1)

Application Number Priority Date Filing Date Title
EP11190962.8A EP2597374A1 (fr) 2011-11-28 2011-11-28 Agencement de brûleur pour une turbine à gaz

Applications Claiming Priority (1)

Application Number Priority Date Filing Date Title
EP11190962.8A EP2597374A1 (fr) 2011-11-28 2011-11-28 Agencement de brûleur pour une turbine à gaz

Publications (1)

Publication Number Publication Date
EP2597374A1 true EP2597374A1 (fr) 2013-05-29

Family

ID=45065797

Family Applications (1)

Application Number Title Priority Date Filing Date
EP11190962.8A Withdrawn EP2597374A1 (fr) 2011-11-28 2011-11-28 Agencement de brûleur pour une turbine à gaz

Country Status (1)

Country Link
EP (1) EP2597374A1 (fr)

Cited By (4)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
DE102013016202A1 (de) * 2013-09-28 2015-04-02 Dürr Systems GmbH "Brennerkopf eines Brenners und Gasturbine mit einem solchen Brenner"
DE102013016201A1 (de) * 2013-09-28 2015-04-02 Dürr Systems GmbH "Brennerkopf eines Brenners und Gasturbine mit einem solchen Brenner"
WO2016045779A1 (fr) * 2014-09-25 2016-03-31 Dürr Systems GmbH Tête de brûleur et turbine à gaz pourvue d'un tel brûleur
EP3184782A4 (fr) * 2014-08-18 2018-04-11 Kawasaki Jukogyo Kabushiki Kaisha Dispositif d'injection de carburant

Citations (4)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US4344280A (en) * 1980-01-24 1982-08-17 Hitachi, Ltd. Combustor of gas turbine
US20040000146A1 (en) * 2001-08-29 2004-01-01 Hiroshi Inoue Gas turbine combustor and operating method thereof
US20040237531A1 (en) * 2002-04-15 2004-12-02 Takeo Hirasaki Combustor of gas turbine
US20110239619A1 (en) * 2010-03-30 2011-10-06 Mitsubishi Heavy Industries, Ltd. Combustor and gas turbine

Patent Citations (4)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US4344280A (en) * 1980-01-24 1982-08-17 Hitachi, Ltd. Combustor of gas turbine
US20040000146A1 (en) * 2001-08-29 2004-01-01 Hiroshi Inoue Gas turbine combustor and operating method thereof
US20040237531A1 (en) * 2002-04-15 2004-12-02 Takeo Hirasaki Combustor of gas turbine
US20110239619A1 (en) * 2010-03-30 2011-10-06 Mitsubishi Heavy Industries, Ltd. Combustor and gas turbine

Cited By (5)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
DE102013016202A1 (de) * 2013-09-28 2015-04-02 Dürr Systems GmbH "Brennerkopf eines Brenners und Gasturbine mit einem solchen Brenner"
DE102013016201A1 (de) * 2013-09-28 2015-04-02 Dürr Systems GmbH "Brennerkopf eines Brenners und Gasturbine mit einem solchen Brenner"
EP3184782A4 (fr) * 2014-08-18 2018-04-11 Kawasaki Jukogyo Kabushiki Kaisha Dispositif d'injection de carburant
WO2016045779A1 (fr) * 2014-09-25 2016-03-31 Dürr Systems GmbH Tête de brûleur et turbine à gaz pourvue d'un tel brûleur
US10712009B2 (en) 2014-09-25 2020-07-14 Duerr Systems Ag Burner head of a burner and gas turbine having a burner of this type

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