EP2310741A2 - Élément d'injection de combustible - Google Patents

Élément d'injection de combustible

Info

Publication number
EP2310741A2
EP2310741A2 EP09779477A EP09779477A EP2310741A2 EP 2310741 A2 EP2310741 A2 EP 2310741A2 EP 09779477 A EP09779477 A EP 09779477A EP 09779477 A EP09779477 A EP 09779477A EP 2310741 A2 EP2310741 A2 EP 2310741A2
Authority
EP
European Patent Office
Prior art keywords
fuel
nozzle
receiving unit
nozzle insert
burner
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.)
Granted
Application number
EP09779477A
Other languages
German (de)
English (en)
Other versions
EP2310741B1 (fr
Inventor
Thomas Grieb
Bernd Prade
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 EP09779477.0A priority Critical patent/EP2310741B1/fr
Publication of EP2310741A2 publication Critical patent/EP2310741A2/fr
Application granted granted Critical
Publication of EP2310741B1 publication Critical patent/EP2310741B1/fr
Not-in-force legal-status Critical Current
Anticipated expiration legal-status Critical

Links

Classifications

    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F23—COMBUSTION APPARATUS; COMBUSTION PROCESSES
    • F23D—BURNERS
    • F23D11/00—Burners using a direct spraying action of liquid droplets or vaporised liquid into the combustion space
    • F23D11/36—Details, e.g. burner cooling means, noise reduction means
    • F23D11/38—Nozzles; Cleaning devices therefor
    • F23D11/383—Nozzles; Cleaning devices therefor with swirl means

Definitions

  • the present invention relates to a fuel nozzle for the twisting of a fuel / air-fuel mixture.
  • the invention further relates to a burner and a gas turbine.
  • Gas turbines are known to have the following components: a compressor for compressing air; a combustion chamber for generating hot gas by burning fuel in the presence of the compressed air supplied from the compressor; and a turbine in which the hot gas supplied from the combustion chamber is expanded.
  • Gas turbines are known to emit undesirable nitrogen oxides (NOx) and carbon monoxide (CO).
  • NOx nitrogen oxides
  • CO carbon monoxide
  • One known factor affecting NOx emissions is the combustion temperature. If the combustion temperature is lowered, the amount of NOx released decreases. However, high combustion temperatures are desirable to achieve high efficiency. It is known that leaner fuel / air mixtures burn cooler and therefore less NOx emissions arise.
  • One known technique for producing a leaner fuel mixture is to create turbulence to mix air and fuel as evenly as possible prior to combustion to avoid creating zones of rich mixture in which there are high temperature localities (so-called hot spots).
  • fuel is flowed in via a so-called Swirler.
  • compressed air is supplied through a channel of the combustion chamber.
  • Swirler are arranged, which are connected to a fuel line.
  • These swirlers twist the combustion air and at the same time introduce fuel into the combustion air through holes in the swirl blades.
  • This mixture then flows to the combustion chamber to be burned there.
  • This system becomes a as homogeneous as possible mixture of fuel to air, which contributes significantly to the NOx reduction.
  • a first object of the present invention to provide a fuel nozzle which overcomes the above-mentioned problems.
  • a second object of the present invention is the disclosure of an advantageous burner. It is a third object of the invention to provide an advantageous gas turbine.
  • the first object is achieved by a fuel nozzle according to claim 1.
  • the second object is achieved by a burner according to claim 13.
  • the object related to the gas turbine is achieved by a gas turbine according to claim 16.
  • a component namely the nozzle insert in another component, namely the receiving unit.
  • a flow path and a swirl chamber are formed.
  • fuel in particular liquid
  • the flow path can itself take on a kind of nozzle function in that it is formed differently geometrically, for example, when stream enters the swirl chamber tapers or widened. If the fuel is accelerated in the flow path, ie the highest speed is only when it enters the pickup unit itself, too high pressure losses and cavitations can be avoided.
  • the nozzle insert At the inlet beginning of the fuel and at the end, that is to say substantially in the swirl chamber itself, the nozzle insert is bent in a substantially circular manner, and thus essentially forms a broken circle. Flow thus occurs from a flow path and into a swirl chamber in such a way that the fuel performs a circular, in particular a spiral movement in the swirl chamber.
  • the nozzle insert according to the invention thus produces a
  • the depth of the receiving unit decreases at the beginning of entry of the nozzle insert in the flow direction.
  • This causes the flow rate of the fuel to be changed, namely increased.
  • This also causes an increase in the flow velocity.
  • the flow path, which is formed by the entry start of the nozzle insert and the receiving unit, also expand in the flow direction. This also causes a change in the flow velocity.
  • simultaneous reduction of the depth of the receiving unit at the inlet beginning in the flow direction can also be done so increasing the flow velocity.
  • the nozzle insert can be used as an integrated component in the receiving unit.
  • the swirl chamber is preferably designed circular.
  • the swirl chamber may further comprise an outlet, so that the fuel twisted can escape there.
  • the outlet thus serves as a spray nozzle and may, for example, also have a tapered shape.
  • the so twisted fuel then enters the combustion chamber.
  • the outlet is a bore, in particular a transverse bore. This is particularly easy to install later.
  • the fuel nozzle arrangement comprises four-eight fuel nozzles arranged symmetrically on a disk. This disc is accordingly integrated in a customized recording unit of the essay.
  • the essay also includes four-eight outlets.
  • Fuel nozzle assembly created which is integrated into an essay and thus includes all outlets (atomizer nozzles). Thus, therefore, the fuel is divided into individual streams on its circumference.
  • the number of nozzle inserts and receiving units arranged on the disk can vary, as can the arrangement of the nozzle inserts / receiving units on the disk.
  • the nozzle insert and / or the receiving unit preferably consists of metal or a metal alloy.
  • the nozzle insert and / or the receiving unit preferably consists of metal or a metal alloy.
  • Embodiment consist of the nozzle insert and / or the receiving unit of ceramic or ceramic material, since these materials are particularly abrasion resistant.
  • the nozzle insert and / or the receiving unit are fine mechanical or with print technology produced. This production is particularly inexpensive and quick to implement.
  • Fig. 4.5 shows schematically an article 13 with 4 burner inserts according to the invention in back and front view.
  • FIG. 1 shows by way of example a gas turbine 100 in a longitudinal partial section.
  • the gas turbine 100 has inside a rotatably mounted about a rotation axis 102 rotor 103 with a shaft, which is also referred to as a turbine runner.
  • the combustion chamber 110 communicates with an annular annular hot gas channel 111, for example.
  • annular annular hot gas channel 111 for example.
  • turbine stages 112 connected in series form the turbine 108.
  • Each turbine stage 112 is formed, for example, from two blade rings. In the flow direction of a working medium As can be seen in the hot gas duct 111 of a guide blade row 115, a row 125 formed of rotor blades 120 follows.
  • the guide vanes 130 are fastened to an inner housing 138 of a stator 143, whereas the moving blades 120 of a row 125 are attached to the rotor 103 by means of a turbine disk 133, for example.
  • Coupled to the rotor 103 is a generator or a work machine (not shown).
  • air 105 is sucked in and compressed by the compressor 105 through the intake housing 104.
  • the compressed air provided at the turbine-side end of the compressor 105 is guided to the burners 107 and mixed there with a fuel.
  • the mixture is then burned to form the working fluid 113 in the combustion chamber 110.
  • the working medium 113 flows along the hot gas channel 111 past the guide vanes 130 and the rotor blades 120.
  • the working medium 113 expands in a pulse-transmitting manner so that the rotor blades 120 drive the rotor 103 and drive the machine coupled to it.
  • FIG. 2 schematically shows a section through a burner 107 with a nozzle according to the prior art in a partially perspective view.
  • the burner 107 can be used on the one hand in conjunction with the annular combustion chamber 106.
  • the burner 107 is used in conjunction with a so-called tube combustion chamber.
  • the gas turbine 100 has, instead of the annular combustion chamber 106, a plurality of annularly arranged tube combustion chambers whose outflow-side openings open into the annular hot gas channel 111 on the inlet side of the turbine.
  • a plurality of, for example six or eight, burners 107 are preferably arranged on each of these tube combustion chambers at the opposite end of the downstream opening of the tube combustion chamber, usually annularly around a pilot burner.
  • the burner 107 comprises a cylindrical housing 12.
  • a lance with a fuel channel 16 is arranged along the central axis 27 of the burner 107.
  • the latter comprises a pointed attachment 13, which is arranged concentrically to the central axis 27.
  • the fuel nozzles 1 are arranged according to the prior art, which communicate with the fuel channel 16.
  • swirl vanes 17 are arranged around the lance.
  • the swirl blades 17 are arranged along the circumference of the lance in the housing 12.
  • a compressor air flow 15 is passed into the combustion chamber 110 leading to the part of the burner 107.
  • the air is displaced by the swirl blades 17 in a swirling motion.
  • Fuel for example oil, is injected through the fuel nozzles 1 into the resulting air stream.
  • the resulting fuel-air mixture is then passed on to the combustion chamber 110.
  • FIG. 3 schematically shows a section through a fuel nozzle according to the invention.
  • the nozzle inserts 1 are arranged on the outer circumference of the attachment 13 in corresponding receiving units 4.
  • a fuel nozzle arrangement comprises a plurality of, in the present embodiment, four nozzle inserts 1 according to the invention with corresponding receiving units 4 (FIG. 4, rear view and FIG. 5 front view).
  • the flow paths 5 are indicated here as four slots (FIG. 4, FIG. 5).
  • the central axis of the attachment 13 is indicated by the reference numeral 18.
  • the attachment 13 is conical to the combustion chamber 110, tapered designed.
  • the nozzle insert 1 is arranged on the outer circumference of the attachment 13 in the corresponding receiving units 4 and thus forms the swirl chambers 10.
  • the nozzle insert 1 according to the invention is made as an integrated component.
  • the nozzle according to the invention Insert 1 comprises at its fuel inlet 2, which is located in the swirl chamber 10 approximately a semicircular curved inlet beginning 7a and an end 7b.
  • the nozzle insert 1 has a nozzle insert neck 3.
  • the nozzle insert 1, in particular the nozzle insert neck 3 itself and the preferably circularly curved inlet beginning 7a, form with the receiving unit 4 a flow path 5, along which the fuel can flow.
  • the entry start 7a and the end 7b form with the receiving unit 4, the swirl chamber 10 from.
  • the flow path 5 which through the inlet beginning 7a of the nozzle insert 1 and the receiving unit
  • the flow rate is increased.
  • the increase can also take place in that the depth of the
  • the swirl chamber 10 is essentially circular.
  • the flow path 5 thus performs at the inlet beginning 7a in the swirl chamber 10 by this arrangement a circular movement, which directs the fuel towards the outlet 8.
  • the fuel thus performs a circular movement, that is, the fuel is thus circular, in particular spiral 12 swirled.
  • the so-swirled fuel passes through the outlet 8 for the purpose of atomization.
  • the outlet 8 is a transverse bore for the purpose of outflow.
  • the nozzle insert 1 according to the invention thus generates a flow of fuel, in particular a liquid fuel flow with a swirl component in the chambers downstream.
  • a fuel nozzle is thus created by a nozzle insert 1 which can be integrated in a receiving unit 4.
  • a disk with a fuel nozzle arrangement according to the invention is provided, which is inserted into an attachment 13 or another component and thus supplies all the outlets 8 (atomization openings) of the attachment 13.
  • the fuel nozzle or the fuel nozzle arrangement divides the Brennstoffström distributed in individual streams on the circumference.
  • the previously used nozzles are used for swirl generation in the flow of the fuel before it enters the combustion chamber.
  • the twist is now generated by means of the special geometry of the fuel nozzle according to the invention.
  • the fuel nozzle or the receiving unit and / or the nozzle insert can be made of metallic or ceramic materials fine mechanical or "print" -based.
  • an acceleration of the fuel take place, so as to obtain maximum speed only at the entrance to the swirl chamber 10, so that too high pressure losses and cavitation are avoided and one thus obtains an effective nozzle cross section, which is more independent of the throughput.
  • This can be achieved, for example, by bending the inlet beginning 7a to the outlet center 8 or bending it away from the outlet center 8 and / or by changing the depth of the receiving unit 4 at the entrance beginning 7a.

Landscapes

  • Engineering & Computer Science (AREA)
  • Chemical & Material Sciences (AREA)
  • Combustion & Propulsion (AREA)
  • Mechanical Engineering (AREA)
  • General Engineering & Computer Science (AREA)
  • Nozzles For Spraying Of Liquid Fuel (AREA)
  • Gas Burners (AREA)
  • Pre-Mixing And Non-Premixing Gas Burner (AREA)

Abstract

L'invention concerne un injecteur de combustible conférant un mouvement tourbillonnaire à un combustible ou mélange combustible-air et comprenant une unité réceptrice (4) et un élément d'injection (1), l'élément d'injection (1) et l'unité réceptrice (4) formant un chemin d'écoulement (5) puis une chambre de turbulence (10). L'élément d'injection (1) présente un début d'entrée (7a) et une fin (7b), le début d'entrée (7a) et la fin (7b) étant courbés pratiquement en cercle de manière à former un cercle interrompu de sorte qu'un mouvement circulaire (12) et en particulier hélicoïdal orienté radialement vers l'intérieur est imprimé à un combustible pénétrant dans la chambre de turbulence (10). L'invention concerne également un brûleur et une turbine à gaz.
EP09779477.0A 2008-08-11 2009-05-14 Insert d'une buse à combustible Not-in-force EP2310741B1 (fr)

Priority Applications (1)

Application Number Priority Date Filing Date Title
EP09779477.0A EP2310741B1 (fr) 2008-08-11 2009-05-14 Insert d'une buse à combustible

Applications Claiming Priority (3)

Application Number Priority Date Filing Date Title
EP08014308A EP2154428A1 (fr) 2008-08-11 2008-08-11 Insert d'une buse à combustible
EP09779477.0A EP2310741B1 (fr) 2008-08-11 2009-05-14 Insert d'une buse à combustible
PCT/EP2009/055827 WO2010018013A2 (fr) 2008-08-11 2009-05-14 Élément d'injection de combustible

Publications (2)

Publication Number Publication Date
EP2310741A2 true EP2310741A2 (fr) 2011-04-20
EP2310741B1 EP2310741B1 (fr) 2015-02-25

Family

ID=40352136

Family Applications (2)

Application Number Title Priority Date Filing Date
EP08014308A Withdrawn EP2154428A1 (fr) 2008-08-11 2008-08-11 Insert d'une buse à combustible
EP09779477.0A Not-in-force EP2310741B1 (fr) 2008-08-11 2009-05-14 Insert d'une buse à combustible

Family Applications Before (1)

Application Number Title Priority Date Filing Date
EP08014308A Withdrawn EP2154428A1 (fr) 2008-08-11 2008-08-11 Insert d'une buse à combustible

Country Status (3)

Country Link
US (1) US20110136067A1 (fr)
EP (2) EP2154428A1 (fr)
WO (1) WO2010018013A2 (fr)

Families Citing this family (1)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
EP3023696B1 (fr) * 2014-11-20 2019-08-28 Ansaldo Energia Switzerland AG Lance à lobes pour chambre de combustion d'une turbine à gaz

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Also Published As

Publication number Publication date
EP2154428A1 (fr) 2010-02-17
US20110136067A1 (en) 2011-06-09
WO2010018013A2 (fr) 2010-02-18
EP2310741B1 (fr) 2015-02-25
WO2010018013A3 (fr) 2010-08-05

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