EP1722164A1 - Kraftstoffeinspritzeinrichtung - Google Patents

Kraftstoffeinspritzeinrichtung Download PDF

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Publication number
EP1722164A1
EP1722164A1 EP06009563A EP06009563A EP1722164A1 EP 1722164 A1 EP1722164 A1 EP 1722164A1 EP 06009563 A EP06009563 A EP 06009563A EP 06009563 A EP06009563 A EP 06009563A EP 1722164 A1 EP1722164 A1 EP 1722164A1
Authority
EP
European Patent Office
Prior art keywords
flow
fuel
fuel injection
swirl
annular member
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Withdrawn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
EP06009563A
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English (en)
French (fr)
Inventor
Nikolaos Prof. Dr. Zarzalis
Paris Fokaides
Klaus Merkle
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.)
Karlsruher Institut fuer Technologie KIT
Original Assignee
Universitaet Karlsruhe
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 Universitaet Karlsruhe filed Critical Universitaet Karlsruhe
Publication of EP1722164A1 publication Critical patent/EP1722164A1/de
Withdrawn legal-status Critical Current

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Classifications

    • 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 
    • F23C7/00—Combustion apparatus characterised by arrangements for air supply
    • F23C7/002—Combustion apparatus characterised by arrangements for air supply the air being submitted to a rotary or spinning motion
    • F23C7/004—Combustion apparatus characterised by arrangements for air supply the air being submitted to a rotary or spinning motion using vanes
    • 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
    • F23R3/02—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
    • 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 present invention relates to a fuel injection apparatus, in particular for aircraft gas turbine engines, comprising a central channel which extends at least between a fuel injection means and an injection opening to a combustion chamber and forms a diffuser at said injection opening, wherein said fuel injection means is adapted to spray liquid fuel across a primary flow of gaseous oxidation medium onto the radially inner surface of a generally annular member downstream of said fuel injection means to form a fuel film flow in a generally downstream direction over said surface, a downstream end of said annular member terminating in an annular lip.
  • the fuel injection apparatus further comprises swirl generation means applying a swirl to the primary flow of gaseous oxidation medium and means for directing a secondary flow of gaseous oxidation medium, a mass flow of which is equal or higher than a mass flow of the primary flow, over the radially outer surface of said annular member to cooperate with said primary flow to provide atomization of said fuel film downstream of said annular lip.
  • a gas turbine engine includes a compressor that provides pressurized air to a combustor wherein the air is mixed with fuel and ignited for generating hot combustion gases. This gases flow downstream to one ore more turbines said extract energy therefrom to power the compressor and provide useful work such as powering an aircraft in flight.
  • the air is supplied through surrounding assemblies, known as swirl generators, which impart a swirling motion to the air so as to cause the air and fuel to be thoroughly mixed.
  • a main object of the continuing development of fuel injection systems for gas turbines is the improvement of the efficiency which requires an increased pressure and temperature level within the combustion chamber. These increased levels, however, also result in an increased emission of undesired oxides of nitrogen. Such oxides are considered as harmful emissions which should be reduced.
  • One known way to reduce the emission of oxides of nitrogen is the optimization of the mixing of the liquid fuel with the air which is fed into the combustion chamber for combustion purposes. If the fuel is poorly atomized and evaporated so said liquid fuel droplets remain or if local areas of high fuel concentration occur, the combustion temperature increases locally. This in turn results in a correspondingly increased rate in the production of the oxides of nitrogen.
  • the proposed fuel injection apparatus comprises a central channel extending at least between a fuel injection means and an injection opening to a combustion chamber, said central channel forming a diffuser at said injection opening.
  • the fuel injection means is adapted to spray liquid fuel across a primary flow of gaseous oxidation medium, in particular air, onto the radially inner surface of a generally annular member downstream of the fuel injection means to form a fuel film flow in a generally downstream direction over said surface.
  • the downstream end of said annular member terminates in an annular lip, also called atomizer lip.
  • the apparatus further comprises a swirl generation means which applies a swirl to the primary flow of gaseous oxidation medium, and means for directing a secondary flow of gaseous oxidation medium, a mass flow of which is equal or higher than a mass flow of the primary flow, over the radially outer surface of the annular member to cooperate with said primary flow to provide atomization of said fuel film downstream of said annular lip.
  • the annular lip preferably is arranged at a position of the central channel at which a smallest flow cross section of the primary and secondary flow of gaseous oxidation medium is achieved within the apparatus.
  • the proposed fuel injection apparatus is characterized in that said diffuser formed of said central channel has a diffuser angle of s 15° and that said means for directing the secondary flow of gaseous oxidation medium to the radially outer surface of the annular member is designed to apply a swirl with a swirl number of lower than 0.2 to the secondary flow or to apply no swirl to the secondary flow.
  • the present invention is based on the finding that with the generation of a lifted flame within the combustion chamber a better mixing between the liquid fuel and the oxidation medium is achieved.
  • the lifted flame allows the mixing process to completely or partly take place within the combustion chamber prior to combustion.
  • the two measures of the characterizing portion of claim 1 have to be taken.
  • a further improvement in the generation of a lifted flame having a sufficiently high distance from the injection opening is achieved when the edges of the injection opening are designed as sharp edges.
  • the further components of the fuel injection apparatus can be designed in the manner known in the art, for example as known from DE 196 27 760 A1 , which is included in the present patent application by reference.
  • the primary flow of gaseous oxidation medium is supplied to the central channel preferably via a primary flow duct through a first discharge opening downstream of the fuel injection means, for example one or several spray nozzles.
  • the discharge opening surrounds the central channel at this position.
  • the secondary flow is preferably supplied via a secondary flow duct through a second discharge opening downstream of the first discharge opening, said second discharge opening also surrounding the central channel.
  • the two discharge openings are separated by the annular member forming the annular lip.
  • the swirl generation means for applying a swirl to the primary flow and, if applicable, to the secondary flow are arranged within the primary and the secondary flow duct.
  • the diffuser is formed at the downstream end of the central channel by increasing the cross section of the central channel towards the combustion chamber. This can be a linear as well as a nonlinear increase resulting in a straight-line or, for example, a convex inner shape of the diffuser section. In case of a convex shape it is the tangent to this shape at the downstream end of the diffuser which must have an angle against the central axis of equal or less than 15° in order to fulfill the requirement of the present fuel injection apparatus.
  • the central member terminating in the annular lip extends to a length in a flow direction of said primary flow, i.e. in a downstream direction of the central channel, which length is higher than the inner diameter of the opening formed by the angular lips.
  • a length of the annular member in the downstream direction preferably is ⁇ 1.5 times of the inner diameter of the opening formed by the angular lip.
  • a further improvement of the mixing of the liquid fuel and the oxidation medium is achieved with an elongation of the distance between the annular lip and the injection opening to the combustion chamber.
  • a longer distance allows a longer time for mixing between the atomized liquid fuel and the oxidation medium which also results in a more homogeneous distribution of the fuel at the combustion region. If the distance is too large, the inner wall is wetted with liquid fuel, which again deteriorates the fuel distribution at the combustion region.
  • the distance is selected as large as possible without wetting the inner wall of the central channel at the injection opening with liquid fuel.
  • one or several fuel supply channels for liquid fuel are arranged, preferably symmetrically around the central channel, within the annular member.
  • These additional fuel supply channels have discharge openings at the radially inner surface of this annular member upstream of the annular lip.
  • the liquid fuel can be supplied through this additional fuel supply channels to the radially inner surface of the annular member in addition to the supply of fuel via the central fuel injection means or alternatively to this central injection.
  • the liquid fuel is supplied through the central injection means during low load conditions of the gas turbine, whereas the liquid fuel is supplied through the additional fuel supply channel(s) during high load conditions of the turbine engine. This also leads to an improvement in the homogeneity of the fuel distribution in the combustion region.
  • the following exemplary embodiment shows an example of the proposed fuel injection apparatus with reference to the accompanying figure without limiting the scope of the invention as defined in the claims.
  • the figure shows an example of the fuel injection apparatus in a schematic view.
  • the fuel injection apparatus shown in figure 1 can be used in a gas turbine engine, a section of which is shown for example in figure 1 of DE 196 27 760 A1 .
  • the exemplary fuel injection apparatus comprises a central channel 13 which extends between a fuel spray nozzle 10 and an injection opening 14 to the combustion chamber 15 not explicitly shown in this figure.
  • the fuel injection apparatus further comprises a primary flow duct 6 and a secondary flow duct 1 downstream of said primary flow duct 6.
  • the two flow ducts 6, 1 are separated by a generally annular member 16 terminating in an annular lip 8 in the downstream direction.
  • the flow ducts 1, 6 are formed concentrically to the central axis A of the central channel 13, which is the central axis of the radially symmetric fuel injection apparatus of the present example.
  • a diffuser 5 is formed at the injection opening 14.
  • the diffuser 5 is formed with a linear increasing cross section of the central channel 13.
  • a intermediate section 12 having a constant diameter is provided between the diffuser 5 and the annular lip 8 .
  • the length of this intermediate section 12 together with the length of the diffuser 5 in the flow direction is selected such that it is as long as possible without wetting of the inner wall of the diffuser 5 with liquid fuel droplets. This maximum length improves the mixing between the liquid fuel atomized at the annular lip 8 and the air flow due to a longer flight time of the fuel prior to combustion.
  • Annular member 16 also comprises additional fuel channels 11 for supplying liquid fuel to the radially inner surface of the annular member 16.
  • these fuel channels 11 are shown in the figure to be arranged vertically with respect to the central axis A, this is only exemplary. They can also be arranged at another angle with respect to the central axis A or can follow a curved line, preferably in order to enter the central channel 13 in flow direction nearly tangentially to the radially inner surface 7 of the annular member 16.
  • swirl generators are arranged to apply a swirl to the primary flow 3 of air and to the secondary flow 2 of air which is supplied from the compressor stage of the gas turbine.
  • the swirl generator in the secondary flow duct 1 is designed such that the swirl of the secondary flow 2 has a swirl rate of less than 0.2.
  • the swirl directions of the primary flow 3 and secondary flow 2 can be co-rotating or counter-rotating. It is also possible to provide the secondary flow duct 1 without any swirl generator. In this case the secondary flow 2 is without any swirl.
  • the cross sections of the primary duct 6 and the secondary duct 1 are such that the mass flow of the air through the secondary duct 1 is equal or greater than the mass flow of the air through the primary duct 6.
  • liquid fuel 17 is sprayed by the fuel spray nozzle 10 to the radially inner surface 7 of the annular member 16 as indicated in the figure.
  • the primary air flow 3 and secondary air flow 2 are supplied through the primary 6 and secondary duct 1 to the central channel 13. This is indicated by corresponding arrows in the figure.
  • the liquid fuel 17 sprayed onto the inner surface 7 of the annular member 16 forms a thin film of liquid fuel on the surface 7 which moves downstream towards annular lip 8. Due to the shearing stream of the secondary flow 2 and the primary flow 3 at the edge of this annular lip 8 the fuel film tears off and at the same time is atomized and/or evaporated due to the shearing forces of the air flows.
  • Annular lip 8 is arranged at the narrowest flow cross section or immediately before this narrowest flow cross section of the primary and secondary flow, i.e. at the position of highest flow velocities. This results in a maximum atomizing effect and leads to an optimum atomizing of the liquid fuel.
  • the combustion flame forms not immediately at the injection opening 14 in the combustion chamber 15, but at a downstream distance from this injection opening.
  • a flame which is not attached to the injection opening is called a lifted flame.
  • the sharp edges 4 of the injection opening furthermore improve the formation of such a lifted flame.
  • the distance between the lifted flame and the injection opening 14 is large enough to enable a significant further mixing of the atomized fuel with the air prior to combustion, which results in a more homogeneous distribution of the fuel at the combustion region.
  • the liquid fuel 17 is sprayed by the fuel spray nozzle 10 onto the radially inner surface 7 of the annular member 16 during low load operation of the gas turbine.
  • the fuel is not supplied via the central fuel spray nozzle 10 but through the additional fuel supply channels 11 in order to achieve a more reliable wetting of the inner surface 7 of the annular member 16 at this load.
  • the preferably concentrically arranged fuel supply channels 11 can nevertheless also be operated at the same time as the fuel spray nozzle 10 and vice versa.
  • the length L of the annular member 16 in flow direction is larger than the diameter D of annular lip 8 at the downstream end of the annular member 16. This results in a longer distance available for the evaporation of the liquid fuel sprayed onto the inner surface 7 of the annular member 16. Therefore, the mixing of air and liquid fuel is further improved by this measure.

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  • 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)
EP06009563A 2005-05-12 2006-05-09 Kraftstoffeinspritzeinrichtung Withdrawn EP1722164A1 (de)

Applications Claiming Priority (1)

Application Number Priority Date Filing Date Title
DE200510022772 DE102005022772A1 (de) 2005-05-12 2005-05-12 Brenner mit Teilvormischung und -vorverdampfung des flüssigen Brennstoffs

Publications (1)

Publication Number Publication Date
EP1722164A1 true EP1722164A1 (de) 2006-11-15

Family

ID=36616795

Family Applications (1)

Application Number Title Priority Date Filing Date
EP06009563A Withdrawn EP1722164A1 (de) 2005-05-12 2006-05-09 Kraftstoffeinspritzeinrichtung

Country Status (2)

Country Link
EP (1) EP1722164A1 (de)
DE (1) DE102005022772A1 (de)

Cited By (3)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
EP2223017A2 (de) * 2007-11-21 2010-09-01 Woodward Governor Company Vorfilmbildungskraftstoffdüse mit geteilter strömung
JP2014137193A (ja) * 2013-01-17 2014-07-28 Hino Motors Ltd バーナー
FR3057648A1 (fr) * 2016-10-18 2018-04-20 Safran Helicopter Engines Systeme d'injection pauvre de chambre de combustion de turbomachine

Families Citing this family (4)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
DE102007050276A1 (de) * 2007-10-18 2009-04-23 Rolls-Royce Deutschland Ltd & Co Kg Magervormischbrenner für ein Gasturbinentriebwerk
US8919132B2 (en) 2011-05-18 2014-12-30 Solar Turbines Inc. Method of operating a gas turbine engine
US8893500B2 (en) 2011-05-18 2014-11-25 Solar Turbines Inc. Lean direct fuel injector
US9182124B2 (en) 2011-12-15 2015-11-10 Solar Turbines Incorporated Gas turbine and fuel injector for the same

Citations (8)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US4842197A (en) * 1986-12-10 1989-06-27 Mtu Motoren-Und Turbinen-Union Gmbh Fuel injection apparatus and associated method
US5373693A (en) * 1992-08-29 1994-12-20 Mtu Motoren- Und Turbinen-Union Munchen Gmbh Burner for gas turbine engines with axially adjustable swirler
US5417070A (en) * 1992-11-24 1995-05-23 Rolls-Royce Plc Fuel injection apparatus
US5490378A (en) * 1991-03-30 1996-02-13 Mtu Motoren- Und Turbinen-Union Muenchen Gmbh Gas turbine combustor
DE19627760A1 (de) * 1996-07-10 1998-01-15 Mtu Muenchen Gmbh Brenner mit Zerstäuberdüse
US5966937A (en) * 1997-10-09 1999-10-19 United Technologies Corporation Radial inlet swirler with twisted vanes for fuel injector
US6543235B1 (en) * 2001-08-08 2003-04-08 Cfd Research Corporation Single-circuit fuel injector for gas turbine combustors
US20040219466A1 (en) * 2003-05-02 2004-11-04 Marino John A. Aggregate dryer burner with compressed air oil atomizer

Family Cites Families (5)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
GB1421399A (en) * 1972-11-13 1976-01-14 Snecma Fuel injectors
DE3608698A1 (de) * 1986-01-18 1987-07-23 Deutsche Forsch Luft Raumfahrt Brenner-heizkessel-einheit
DE4444961A1 (de) * 1994-12-16 1996-06-20 Mtu Muenchen Gmbh Einrichtung zur Kühlung insbesondere der Rückwand des Flammrohrs einer Brennkammer für Gasturbinentriebwerke
FR2753779B1 (fr) * 1996-09-26 1998-10-16 Systeme d'injection aerodynamique d'un melange air carburant
US6427435B1 (en) * 2000-05-20 2002-08-06 General Electric Company Retainer segment for swirler assembly

Patent Citations (8)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US4842197A (en) * 1986-12-10 1989-06-27 Mtu Motoren-Und Turbinen-Union Gmbh Fuel injection apparatus and associated method
US5490378A (en) * 1991-03-30 1996-02-13 Mtu Motoren- Und Turbinen-Union Muenchen Gmbh Gas turbine combustor
US5373693A (en) * 1992-08-29 1994-12-20 Mtu Motoren- Und Turbinen-Union Munchen Gmbh Burner for gas turbine engines with axially adjustable swirler
US5417070A (en) * 1992-11-24 1995-05-23 Rolls-Royce Plc Fuel injection apparatus
DE19627760A1 (de) * 1996-07-10 1998-01-15 Mtu Muenchen Gmbh Brenner mit Zerstäuberdüse
US5966937A (en) * 1997-10-09 1999-10-19 United Technologies Corporation Radial inlet swirler with twisted vanes for fuel injector
US6543235B1 (en) * 2001-08-08 2003-04-08 Cfd Research Corporation Single-circuit fuel injector for gas turbine combustors
US20040219466A1 (en) * 2003-05-02 2004-11-04 Marino John A. Aggregate dryer burner with compressed air oil atomizer

Cited By (4)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
EP2223017A2 (de) * 2007-11-21 2010-09-01 Woodward Governor Company Vorfilmbildungskraftstoffdüse mit geteilter strömung
EP2223017A4 (de) * 2007-11-21 2014-01-22 Woodward Inc Vorfilmbildungskraftstoffdüse mit geteilter strömung
JP2014137193A (ja) * 2013-01-17 2014-07-28 Hino Motors Ltd バーナー
FR3057648A1 (fr) * 2016-10-18 2018-04-20 Safran Helicopter Engines Systeme d'injection pauvre de chambre de combustion de turbomachine

Also Published As

Publication number Publication date
DE102005022772A1 (de) 2007-01-11

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