EP1526332A2 - Injecteur de combustible - Google Patents

Injecteur de combustible Download PDF

Info

Publication number
EP1526332A2
EP1526332A2 EP20040023823 EP04023823A EP1526332A2 EP 1526332 A2 EP1526332 A2 EP 1526332A2 EP 20040023823 EP20040023823 EP 20040023823 EP 04023823 A EP04023823 A EP 04023823A EP 1526332 A2 EP1526332 A2 EP 1526332A2
Authority
EP
European Patent Office
Prior art keywords
fuel
injection nozzle
fuel injection
air
nozzle according
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Withdrawn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
EP20040023823
Other languages
German (de)
English (en)
Other versions
EP1526332A3 (fr
Inventor
Leif Rackwitz
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.)
Rolls Royce Deutschland Ltd and Co KG
Original Assignee
Rolls Royce Deutschland Ltd and Co KG
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 Rolls Royce Deutschland Ltd and Co KG filed Critical Rolls Royce Deutschland Ltd and Co KG
Publication of EP1526332A2 publication Critical patent/EP1526332A2/fr
Publication of EP1526332A3 publication Critical patent/EP1526332A3/fr
Withdrawn legal-status Critical Current

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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
    • F23D11/10—Burners using a direct spraying action of liquid droplets or vaporised liquid into the combustion space the spraying being induced by a gaseous medium, e.g. water vapour
    • F23D11/106—Burners using a direct spraying action of liquid droplets or vaporised liquid into the combustion space the spraying being induced by a gaseous medium, e.g. water vapour medium and fuel meeting at the burner outlet
    • 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
    • F23D11/10—Burners using a direct spraying action of liquid droplets or vaporised liquid into the combustion space the spraying being induced by a gaseous medium, e.g. water vapour
    • F23D11/106—Burners using a direct spraying action of liquid droplets or vaporised liquid into the combustion space the spraying being induced by a gaseous medium, e.g. water vapour medium and fuel meeting at the burner outlet
    • F23D11/107—Burners using a direct spraying action of liquid droplets or vaporised liquid into the combustion space the spraying being induced by a gaseous medium, e.g. water vapour medium and fuel meeting at the burner outlet at least one of both being subjected to a swirling motion
    • 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
    • F23D—BURNERS
    • F23D2900/00—Special features of, or arrangements for burners using fluid fuels or solid fuels suspended in a carrier gas
    • F23D2900/11101—Pulverising gas flow impinging on fuel from pre-filming surface, e.g. lip atomizers

Definitions

  • the invention relates to a fuel injector according to the features of the preamble of the main claim.
  • the invention relates to a fuel injector for a gas turbine combustor with a film former, on which a plurality of fuel openings formed are.
  • Fig. 1 shows a schematic side sectional view of a Combustion chamber 10 with associated fuel injection.
  • a schematic view of the supply of air to a inner swirler 14 and an outer swirler 15 are shown.
  • the fuel-air mixture 13 flows in a known manner in the combustion chamber 10 a.
  • the stabilization of the combustion takes place almost exclusively with air swirl, which is a recirculation of partially combusted gases allows.
  • the fuel is often centrally through a nozzle introduced, which mounted on the center axis of the atomizer is.
  • the fuel is often with considerable Overpressure injected into the air flow enough to Penetration to achieve and as much air with fuel to be able to premix.
  • These pressure atomizers have to one the function to directly atomize fuel.
  • the fuel gets through the air on a nebulizer lip accelerated and at the downstream end of this lip Torn into small drops and mixed with the air.
  • a another way of putting the fuel on this nebulizer lip to raise, consists with a so-called film depositor, wherein Fuel is distributed as uniformly as possible in a film.
  • FIG. 2 Another way of keeping the fuel as intense as possible to mix with a large part of the air, consists in one decentralized injection (Fig. 2) from the outer boundary a flow channel formed by a film feeder 1, which the majority of the air leads. This can be from a nebulizer lip or else from the outer nozzle contour.
  • This injection is characterized in that, different as with a film-maker, the fuel is one defined Penetration into the main air flow should learn.
  • the fuel nozzles are often through one in the radial direction very uneven velocity and mass flow distribution characterized. Due to the swirl of the air, which needed to stabilize the subsequent combustion is, the local air mass flow in the area of the radial outer boundary wall largest. Is the fuel out a few openings introduced into the flow, on the one hand the homogeneity of the fuel in the air in the circumferential direction impaired, on the other hand, the fuel can be very penetrate deeply into the flow and thus unintentionally in Regions mix and vaporize where not sufficient Air is available. This can also be done with a decentralized Injection occur.
  • the invention is based on the object, a fuel injector to create the type mentioned, which at simple construction and reliable operation a uniform Mixing of fuel and air ensured.
  • This essentially Parallel arrangement can also be up to a range of the absolute Diverge in parallelism through an acute angle is marked. Purely for structural reasons, it is not always possible, the fuel injection completely parallel perform. According to the invention, it is important that the fuel injection has a high axial component and the fuel thus not injected radially.
  • the fuel openings may be on a radially inner wall
  • the filmmaker can be created, but you can also at a Leave the rear edge of the same.
  • the film-maker or the area of injection of the fuel is preferably arranged between two swirlers.
  • the fuel openings in addition are inclined in the twisting direction of the air, i. an additional Have circumferential component. This can be in the same direction or be formed in the counter-twist. Furthermore, it is according to the invention possible, the fuel ports single row, multi-row, to arrange flush with each other or staggered to each other.
  • the film-maker can also be designed like a lamella be to even better mixing of the air-fuel mixture to reach.
  • Fig. 3 shows a simplified representation of a section by the film applicator 1 according to the invention, wherein fuel openings 2, in particular fuel bores 3, shown are whose center axes 5 by an angle ⁇ to the main flow direction 6 (wall-near flow direction in the inner swirl duct) are inclined.
  • the reference numeral 16 shows a hired wall element of Filmlegers 1
  • the reference numeral 17 shows an aerodynamic adapted film layer surface.
  • the reference numeral 21 is a fuel line shown.
  • the invention avoids the unwanted intrusion of the liquid Fuel in areas with low flow rates and the associated uneven fuel-air mixture.
  • a proposed embodiment is shown in FIG. 3 shown.
  • the fuel is here at a film layer not radially inward, i. with a high radial component the exit velocity of the fuel into an inner Injected swirl channel. Rather, in the proposed concept a high axial component of the exit velocity the fuel is present and the fuel is approaching parallel to the main flow direction of the inner swirl duct brought in.
  • Fig. 3 are schematically the fuel ports as well as the Ausdüsung of the fuel shown.
  • the fuel is initially through the openings shown over a hired against the air flow direction Angle ⁇ injected, which is formed as an acute angle.
  • Angle ⁇ injected which is formed as an acute angle.
  • the fuel openings in the circumferential direction arranged in the same or counter-rotation to the air flow be.
  • the shape of the openings can also be different be executed, i. round, elliptical, etc.
  • Construction will be the development of a fuel film in a radially very limited flow layer guaranteed. At the trailing edge of the filmmaker rips the Fuel film decreases and is accelerated by the presence of and twisted air from the outer and inner Flow channel homogeneously mixed.
  • FIG. 4 Another embodiment of the invention provides the injection of the fuel at the trailing edge of a flow divider between two swirlers before (Fig. 4).
  • the speed maxima the accelerated and twisted in the swirl generator Air is near the wall of the formed flow divider, i.e. in the outer flow of the boundary layer both sides of the flow divider.
  • Figs. 7 and 8 show the axial acceleration of the flow in the wake of the trailing edge of the flow divider, where x is the axial distance from the trailing edge of the flow divider is.
  • FIG. 15 is to schematically illustrated a variant of the filmmaker.
  • a Aero engine is aimed at different mass air flows To bring together loss as possible to a total flow.
  • the mixture should be in the proposed burner concept however, to an improved mixture formation by a three-dimensional mixing of a twisted air stream with a partially premixed with air fuel flow to lead.
  • the twisted air from the outer channel periodically penetrates into the inner channel through the shaping one. With an injection of the fuel in the inner or outer Spinal canal develops as the residence time increases downstream of the coater a fuel-air mixture. This Mixture may also be due to the shaping in the inner Penetrate swirl channel.
  • the film layer can thus produce a flow layer be in a very intense mixture of the fuel-air mixture from the inner canal and pure air mixing can be done from the outer swirl duct or vice versa.
  • the uniform temperature field with low absolute temperatures and low nitrogen oxide levels.
  • Another feature the embodiment shown in Fig. 15 can also be a Flange-adapted spiral geometry of the lamellar film layer be in which the lamellar geometry correspondingly effective adapted to the air swirl near the wall of the filmmaker.
  • the advantage of the invention is thus a practice-relevant solution the problem of premixing fuel homogeneously with air and this with as few, relatively large fuel ports a defined and not too large penetration depth of the Fuel into the air flow to achieve.
  • Overall goal is the reduction of nitrogen oxide ejection of the gas turbine combustor with a robust and technically feasible fuel injection configuration.

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)
  • Spray-Type Burners (AREA)
EP20040023823 2003-10-20 2004-10-06 Injecteur de combustible Withdrawn EP1526332A3 (fr)

Applications Claiming Priority (2)

Application Number Priority Date Filing Date Title
DE2003148604 DE10348604A1 (de) 2003-10-20 2003-10-20 Kraftstoffeinspritzdüse mit filmartiger Kraftstoffplatzierung
DE10348604 2003-10-20

Publications (2)

Publication Number Publication Date
EP1526332A2 true EP1526332A2 (fr) 2005-04-27
EP1526332A3 EP1526332A3 (fr) 2012-02-15

Family

ID=34384376

Family Applications (1)

Application Number Title Priority Date Filing Date
EP20040023823 Withdrawn EP1526332A3 (fr) 2003-10-20 2004-10-06 Injecteur de combustible

Country Status (3)

Country Link
US (1) US9033263B2 (fr)
EP (1) EP1526332A3 (fr)
DE (1) DE10348604A1 (fr)

Cited By (4)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
RU2523519C2 (ru) * 2009-03-17 2014-07-20 Сименс Акциенгезелльшафт Способ эксплуатации горелки, горелка, в частности для газовой турбины и газовая турбина
EP3076082A1 (fr) * 2015-03-31 2016-10-05 Delavan Inc Buses de combustible
US10309651B2 (en) 2011-11-03 2019-06-04 Delavan Inc Injectors for multipoint injection
US10385809B2 (en) 2015-03-31 2019-08-20 Delavan Inc. Fuel nozzles

Families Citing this family (10)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US20060283181A1 (en) * 2005-06-15 2006-12-21 Arvin Technologies, Inc. Swirl-stabilized burner for thermal management of exhaust system and associated method
US8453454B2 (en) * 2010-04-14 2013-06-04 General Electric Company Coannular oil injection nozzle
EP3087323B1 (fr) * 2014-04-03 2019-08-21 Siemens Aktiengesellschaft Injecteur de combustible, brûleur avec un tel injecteur de combustible, et turbine à gaz munie dudit brûleur
EP3143334B1 (fr) 2014-05-12 2020-08-12 General Electric Company Cartouche de combustible liquide pour la formation de film
US10132500B2 (en) 2015-10-16 2018-11-20 Delavan Inc. Airblast injectors
US20180058696A1 (en) * 2016-08-23 2018-03-01 General Electric Company Fuel-air mixer assembly for use in a combustor of a turbine engine
US10876477B2 (en) 2016-09-16 2020-12-29 Delavan Inc Nozzles with internal manifolding
US10344981B2 (en) 2016-12-16 2019-07-09 Delavan Inc. Staged dual fuel radial nozzle with radial liquid fuel distributor
US20180335214A1 (en) * 2017-05-18 2018-11-22 United Technologies Corporation Fuel air mixer assembly for a gas turbine engine combustor
US11149948B2 (en) 2017-08-21 2021-10-19 General Electric Company Fuel nozzle with angled main injection ports and radial main injection ports

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US3866413A (en) * 1973-01-22 1975-02-18 Parker Hannifin Corp Air blast fuel atomizer
DE3819898A1 (de) 1988-06-11 1989-12-14 Daimler Benz Ag Brennkammer fuer eine thermische stroemungsmaschine
FR2673705A1 (fr) * 1991-03-06 1992-09-11 Snecma Chambre de combustion de turbomachine munie d'un dispositif anti-cokefaction du fond de ladite chambre.
DE19532264A1 (de) 1995-09-01 1997-03-06 Mtu Muenchen Gmbh Einrichtung zur Aufbereitung eines Gemisches aus Brennstoff und Luft an Brennkammern für Gasturbinentriebwerke
EP1087178A1 (fr) * 1999-09-23 2001-03-28 Nuovo Pignone Holding S.P.A. Chambre de prémélange pour turbines à gaz
EP1331441A1 (fr) 2002-01-21 2003-07-30 National Aerospace Laboratory of Japan Buse d'atomisation de liquide

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EP1499800B1 (fr) * 2002-04-26 2011-06-29 Rolls-Royce Corporation Module de premelange de combustible pour chambre de combustion de turbine a gaz
DE10219354A1 (de) * 2002-04-30 2003-11-13 Rolls Royce Deutschland Gasturbinenbrennkammer mit gezielter Kraftstoffeinbringung zur Verbesserung der Homogenität des Kraftstoff-Luft-Gemisches
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Publication number Priority date Publication date Assignee Title
US3866413A (en) * 1973-01-22 1975-02-18 Parker Hannifin Corp Air blast fuel atomizer
DE3819898A1 (de) 1988-06-11 1989-12-14 Daimler Benz Ag Brennkammer fuer eine thermische stroemungsmaschine
FR2673705A1 (fr) * 1991-03-06 1992-09-11 Snecma Chambre de combustion de turbomachine munie d'un dispositif anti-cokefaction du fond de ladite chambre.
DE19532264A1 (de) 1995-09-01 1997-03-06 Mtu Muenchen Gmbh Einrichtung zur Aufbereitung eines Gemisches aus Brennstoff und Luft an Brennkammern für Gasturbinentriebwerke
EP1087178A1 (fr) * 1999-09-23 2001-03-28 Nuovo Pignone Holding S.P.A. Chambre de prémélange pour turbines à gaz
EP1331441A1 (fr) 2002-01-21 2003-07-30 National Aerospace Laboratory of Japan Buse d'atomisation de liquide

Cited By (7)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
RU2523519C2 (ru) * 2009-03-17 2014-07-20 Сименс Акциенгезелльшафт Способ эксплуатации горелки, горелка, в частности для газовой турбины и газовая турбина
US9032736B2 (en) 2009-03-17 2015-05-19 Siemens Aktiengesellschaft Method for operating a burner and burner, in particular for a gas turbine
US10309651B2 (en) 2011-11-03 2019-06-04 Delavan Inc Injectors for multipoint injection
EP3076082A1 (fr) * 2015-03-31 2016-10-05 Delavan Inc Buses de combustible
US9897321B2 (en) 2015-03-31 2018-02-20 Delavan Inc. Fuel nozzles
US10385809B2 (en) 2015-03-31 2019-08-20 Delavan Inc. Fuel nozzles
US11111888B2 (en) 2015-03-31 2021-09-07 Delavan Inc. Fuel nozzles

Also Published As

Publication number Publication date
EP1526332A3 (fr) 2012-02-15
US9033263B2 (en) 2015-05-19
DE10348604A1 (de) 2005-07-28
US20050133642A1 (en) 2005-06-23

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