EP0224397B1 - In Sektoren aufgeteilter Einspritzkopf für Kraftstoff - Google Patents

In Sektoren aufgeteilter Einspritzkopf für Kraftstoff Download PDF

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Publication number
EP0224397B1
EP0224397B1 EP86402290A EP86402290A EP0224397B1 EP 0224397 B1 EP0224397 B1 EP 0224397B1 EP 86402290 A EP86402290 A EP 86402290A EP 86402290 A EP86402290 A EP 86402290A EP 0224397 B1 EP0224397 B1 EP 0224397B1
Authority
EP
European Patent Office
Prior art keywords
sectors
bowl
air
combustion chamber
holes
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.)
Expired
Application number
EP86402290A
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English (en)
French (fr)
Other versions
EP0224397A1 (de
Inventor
Gérard Yves Georges Barbier
Gérard Joseph Pascal Bayle-Laboure
Michel André Albert Desaulty
Rodolphe Martinez
Jérome Perigne
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.)
Safran Aircraft Engines SAS
Original Assignee
Societe Nationale dEtude et de Construction de Moteurs dAviation SNECMA
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 Societe Nationale dEtude et de Construction de Moteurs dAviation SNECMA filed Critical Societe Nationale dEtude et de Construction de Moteurs dAviation SNECMA
Publication of EP0224397A1 publication Critical patent/EP0224397A1/de
Application granted granted Critical
Publication of EP0224397B1 publication Critical patent/EP0224397B1/de
Expired 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
    • F23R3/02—Continuous combustion chambers using liquid or gaseous fuel characterised by the air-flow or gas-flow configuration
    • F23R3/26—Controlling the air flow
    • 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
    • F23C7/008—Flow control devices
    • 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

Definitions

  • the invention relates to the supply of fuel and primary air to a combustion chamber, in particular for a turbomachine.
  • Traditional combustion chambers generally have a high-rich primary zone and a dilution zone.
  • part of the primary air flow is injected, on the one hand by means of internal and external turbulence tendrils intended to create a cone for spraying the fuel leaving the injector, on the other hand by means orifices of the chamber bottom and the internal and external walls of the combustion chamber.
  • the choice of the fraction of air to be injected into the primary zone results from a compromise between the performance of the combustion chamber at full gas: emission of smoke, thermal resistance of the walls, distribution of temperatures and performance in idle mode : yield, stability.
  • aerodynamic bowl injectors have been developed such as those described in the applicant's prior patents FR 2 357 738 and FR 2 391 359. These injectors are mounted on the chamber bottom with the interposition of an intermediate piece called a bowl comprising a frustoconical part flared downstream and pierced with a multiplicity of small diameter holes through which air at high pressure enters the cone of sprayed fuel. By the turbulence it creates and the intimate mixing it produces, this bowl completes the role of the injector, acts on the mixing composition and allows the creation of a mini primary zone in slow motion.
  • the present invention aims to improve said type of aerodynamic injector with intermediate bowl by shaping it so that it contributes, on the one hand, to improving the cooling of the walls of the combustion chamber and, on the other hand on the other hand, to improve the idling efficiency, in particular when it is mounted in annular combustion chambers on the bottom of which they are regularly distributed, this by making the best use of the localized recirculation zones existing between the adjacent injectors
  • the subject of the invention is a device for injecting air and fuel into a combustion chamber, in particular of a turbomachine, comprising at least one fuel injector, an external swirl spin for the passage of atomizing air.
  • fuel equipped with a diaphragm for modulating the air inlet flow rate, a bowl-shaped body comprising a downstream web flared in the direction of flow and provided with a row of bowl holes for the injection of air into the sprayed fuel cone and an impact cooling chamber formed by the downstream web, an intermediate ring and an outer skirt having air inlet orifices.
  • the chamber is divided into four equal sectors, diametrically opposite two by two and separated by radial partitions, first two sectors comprising on the parts of the downstream web which are associated with them small diameter bowl holes suitable for a optimized operation of the combustion chamber at idle and two second sectors comprising on the corresponding parts of the downstream web large diameter bowl holes adapted to an optimized efficiency at full gas speed.
  • the injection device comprises a diaphragm for modulating the air flow rate of the large diameter bowl holes of the second sectors.
  • the bowls are oriented so that the first sectors of each bowl are arranged side by side while the second sectors of the bowls have holes large diameter are oriented towards the internal and external walls of the combustion chamber to improve cooling at full gas speed.
  • Figure 1 is shown in longitudinal half-section an annular combustion chamber 1 for a turbomachine comprising the injection system according to the invention.
  • Chamber 1 is between an external casing 2 and an internal ferrule 3 which delimit the stream of compressed gases.
  • a fraction F1 of the upstream air coming from the compressor (not shown) is guided through the injection system 4 for the formation of the fuel mixture. This passes into the primary zone 5 where the combustion reactions take place, then the gases produced are diluted in the dilution zone 6 and cooled in the downstream secondary zone 7 and are distributed to the turbine, not shown, which they train.
  • the injector of which only the body 8 is shown in dotted lines in FIG. 1 is connected to the bottom 9 of the combustion chamber by an intermediate bowl 10 whose particular structure is the subject of the invention.
  • the injection system comprises, in known manner, an internal turbulence spin (not shown) which can be either of the radial type, or of the centripetal axial type intended to project the fuel coming from the injector by forming a frustoconical jet flared downstream. .
  • the injector 8 provided with its swirl of internal turbulence is surrounded by a cap 11 forming the upstream wall of the intermediate bowl 10.
  • the cap 11 comprises downstream a part 1 the frustoconical extended upstream by a cylindrical bearing 11b and finally by a radial wall 11c c delimiting with the radial wall 12c of an intermediate ring 12 a radial channel provided with inclined blades 13 forming an external swirling swirl for the injection system.
  • the intermediate ring 12 has a cylindrical portion 12b and is extended by tightening downstream by a frustoconical bearing 12a, the cap 11 and the ring 12 forming an axial-centripetal annular channel for the air coming from the swirl of external turbulence 13.
  • the external turbulence spin 13 can be diaphragmed by a cylindrical ring 22 movable in rotation and having air intake orifices in a number equal to that of the passages of the spin 13.
  • the rotation of the diaphragm 22 takes place by means of an operating lever 23 (shown diagrammatically in FIG. 1) connected to a control system external to the casing 2 and not shown.
  • the external spin 13 can be closed at idle speed and opened continuously until full opening at full gas in order to optimize the air-fuel mixture conditions (air-fuel percentages, volume distribution, spraying) at all operating speeds, which is allowed because the external spin has an important axial component at full throttle conditions and low at idle, this being due to the fact that the spin is diaphragmed upstream and that, the section at the neck of the bowl being constant, the speed of delivery, axial at this level, is directly proportional to the air flow and is therefore increasing from idle to full gas.
  • air-fuel mixture conditions air-fuel percentages, volume distribution, spraying
  • the ring 12 is extended downstream by a frustoconical downstream web 14 flared downstream and forming the bowl proper.
  • the latter is connected to the combustion chamber by an external cylindrical skirt 15 attached to its downstream edge and comprising a thread allowing a nut, not shown, to come to grip in a known manner a cup cut out in the bottom 9 of the combustion chamber.
  • the ring 12, the downstream web 14 and the outer skirt 15 form an annular cooling chamber 16 by impact of the web 14.
  • the skirt 15 has radial openings 17 regularly distributed around its periphery, allowing the supply of chamber 16 in upstream air.
  • the chamber 16 is divided into four equal, diametrically opposite sectors 16a, 16b, separated by radial partitions 21.
  • the downstream web 14 regularly has bowl holes distributed over its periphery allowing the upstream air introduced into the sectors 16a, 16b of the chamber 16 escape from said chamber by fulfilling a spraying function of the conical sheet 18 of fuel formed between the air jets from the two tendrils of external and internal turbulence.
  • the first two sectors 16a of the chamber 16 comprise on the parts of the downstream web 14 which are associated with them small diameter bowl holes 19 while the second sectors 16b comprise on the corresponding parts of the downstream web of bowl 20 of large diameter.
  • the first sectors 16a and the second sectors 16b are supplied with air separately upstream through the radial openings 17, the partitions 21 completely isolating them from each other.
  • the openings 17, supplying the second sectors with large-diameter bowl holes can be diaphragmed by two perforated cylindrical extensions 22a of the ring 22 forming the diaphragm of the external swirl girder 13, in order to modulate the flow bowl hole outlet 20.
  • the diaphragms 22 and 22a thus secured are operated simultaneously towards opening or closing and it is immediately seen that, at idle, the large-diameter bowl holes 20 of the second sectors are not supplied and that they can be supplied up to full flow by the gradual opening of the diaphragm 22a until it is fully open to full gas, while the bowl holes 19 of the first two sectors remain supplied with upstream air during the entire operating time of the turbomachine.
  • Figure 5 shows the arrangement and orientation of the bowls according to the invention applied to an annular combustion chamber. In this figure, without showing the totality of each bowl, there are adjacent bowls 10 seen in a section similar to that of FIG. 4.
  • the combustion chamber 1 comprises a number of injectors connected to the chamber bottom by as many intermediate bowls regularly distributed in a ring.
  • the adjacent bowls are oriented so that their first sectors permanently supplied with upstream air are face to face while the second diaphragmed sectors at idle and delivering at full throttle are oriented facing the internal 3 and external walls. 2 of the combustion chamber to ensure maximum cooling at full gas.
  • This arrangement is chosen, in addition to the cooling needs of the walls at full throttle speed, because we realized by tests of hydraulic analogy then by measurements of cold laser velocimetry that there was a zone of localized recirculation between the adjacent injectors where the flame is localized just before extinction and that it was important to keep a constant supply of carbureted air from this zone at idle in order to improve the flame stability in this operating configuration.
  • the diameter of the bowl holes 20 of the sectors 16b is calculated in order to make the operation of the injection device at full gas speed optimal, with the diaphragms open.
  • the optimal efficiency at idle and in full throttle was obtained with ten holes of two millimeters in diameter for each first sector, of five holes of four millimeters in diameter for each second sector.
  • Another calculation element taken into account in determining the number and dimensions of the holes in each sector consists in the percentage of air admitted into the combustion chamber, respectively by the internal and external swirl tendrils, by the bowl and by the other air intake orifices of the chamber (primary orifices 24 and dilution orifices 25, devices for cooling the walls by impact, by convection or by parietal film).
  • This arrangement combined with the orientation of the adjacent bowls with respect to each other and the variation in swirl angle of the external spin obtained by the upstream arrangement of the diaphragm 22, makes it possible to vary between idle and full throttle the volumetric distribution of the air-fuel mixture in the reaction zone and thereby improving the flame stability at idle and the combustion efficiency at full gas and achieving continuous modulation of these parameters throughout the operating range of the combustion chamber.

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  • Engineering & Computer Science (AREA)
  • Chemical & Material Sciences (AREA)
  • Combustion & Propulsion (AREA)
  • Mechanical Engineering (AREA)
  • General Engineering & Computer Science (AREA)
  • Fuel-Injection Apparatus (AREA)
  • Spray-Type Burners (AREA)

Claims (5)

1. Vorrichtung zur Luft- und Kraftstoffeinspritzung in eine Brennkammer, insbesondere in eine Turbomaschinen-Brennkammer,
mit wenigstens einer Kraftstoffeinspritzdüse,
mit einem externen Verwirbler (13) für den Luftdurchtritt zur Zerstäubung des Kraftstoffs, der mit einem Diaphragma (22) zum Modulieren des Durchsatzes der eintretenden Luft ausgestattet ist,
mit einem Mantelkörper mit einer in Strömungsrichtung ausgeweiteten stromabwärtsseitigen Abdeckung (14) mit einer Reihe von Löchern zum Einspritzen von Luft in den Kegel zerstäubten Kraftstoffs
sowie mit einer Aufprallkühlkammer (16), die von der stromabwärtigen Abdeckung, einem Zwischenring (12) und einer äußeren Schürze (15) mit Lufteintrittsöffnungen gebildet ist, dadurch gekennzeichnet,
daß die Kammer (16) in vier gleiche Sektoren (16a, 16b) unterteilt ist, die jeweils zu zweien diametral einander gegenüberliegen und durch radiale Wandungen (21) voneinander getrennt sind,
und daß die beiden ersten Sektoren (16a) auf den ihnen zugeordneten Teilen der stromabwärtigen Abdeckung (14) Mantellöcher (19) mit kleinem Durchmesser aufweisen, die an einen optimierten Betrieb der Brennkammer bei Langsamlauf angepaßt sind, während die beiden zweiten Sektoren (16b) auf den zugeordneten Teilen der stromabwärtigen Abdeckung (14) Mantellöcher (20) mit großen Durchmesser aufweisen, die an einen optimierten Wirkungsgrad im Vollgasbetrieb angepaßt sind.
2. Einspritzvorrichtung nach Anspruch 1, dadurch gekennzeichnet, daß ein Diaphragma (22a) zum Modulieren des Luftdurchsatzes der Mantellöcher (20) mit großem Durchmesser der zweiten Sektoren (16b) vorgesehen ist.
3. Einspritzvorrichtung nach Anspruch 2, dadurch gekennzeichnet, daß das Diaphragma (22) des externen Verwirblers und das Diaphragma (22a) der Mantellöcher der zweiten Sektoren (16b) fest miteinander verbunden und gleichzeitig in die der Öffnung bei Vollgasbetrieb entsprechende Richtung oder dem Schließen bei Langsamlauf entsprechende Richtung bewegbar sind.
4. Einspritzvorrichtung nach einem der Ansprüche 1 bis 3 für eine ringförmige Brennkammer mit mehreren einander benachbarten Einspritzdüsen, die kranzförmig an dem Boden der Brennkammer verteilt sind, dadurch gekennzeichnet, daß die ersten Sektoren (16a) der benachbarten Mantelkammern (16) einander gegenüberliegen, und daß die zweiten Sektoren (16b) der Mantelkammern, die die Löcher (20) mit großem Durchmesser haben, gegen die Wandungen (2, 3) der Brennkammer ausgerichtet sind, um die Kühlung im Vollgasbetrieb zu gewährleisten.
5. Einspritzvorrichtung nach Anspruch 4, dadurch gekennzeichnet, daß die Abmessungen und die Anzahl der Mantellöcher (20) der zweiten Sektoren (16b) so beschaffen sind, daß ihr Durchsatz für den Lufteinlaß in die Kammer, bezogen auf den Gesamtdurchsatz des Lufteinlasses in die Brennkammer, zwischen 0 % bei Langsamlauf und 4 % bei Vollgasbetrieb variiert, und daß der Durchsatz der Mantellöcher (19) der ersten Sektoren (16a) konstant 2 % beträgt und der Durchsatz des externen Verwirblers (13) zwischen 1 % bei Langsamlauf und 13 % bei Vollgasbetrieb variiert.
EP86402290A 1985-10-18 1986-10-15 In Sektoren aufgeteilter Einspritzkopf für Kraftstoff Expired EP0224397B1 (de)

Applications Claiming Priority (2)

Application Number Priority Date Filing Date Title
FR8515925A FR2588919B1 (fr) 1985-10-18 1985-10-18 Dispositif d'injection a bol sectorise
FR8515925 1985-10-18

Publications (2)

Publication Number Publication Date
EP0224397A1 EP0224397A1 (de) 1987-06-03
EP0224397B1 true EP0224397B1 (de) 1988-12-14

Family

ID=9324228

Family Applications (1)

Application Number Title Priority Date Filing Date
EP86402290A Expired EP0224397B1 (de) 1985-10-18 1986-10-15 In Sektoren aufgeteilter Einspritzkopf für Kraftstoff

Country Status (5)

Country Link
US (1) US4696157A (de)
EP (1) EP0224397B1 (de)
JP (1) JPH0637977B2 (de)
DE (1) DE3661440D1 (de)
FR (1) FR2588919B1 (de)

Families Citing this family (16)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
FR2601115B1 (fr) * 1986-07-03 1988-09-02 Snecma Chambre de combustion annulaire comportant un moyen de commande unique des diaphragmes d'injecteurs
US5297385A (en) * 1988-05-31 1994-03-29 United Technologies Corporation Combustor
US5481867A (en) * 1988-05-31 1996-01-09 United Technologies Corporation Combustor
FR2639095B1 (fr) * 1988-11-17 1990-12-21 Snecma Chambre de combustion de turbomachine a bols de prevaporisation montes flottants
FR2652858B1 (fr) * 1989-10-11 1993-05-07 Snecma Stator de turbomachine associe a des moyens de deformation.
FR2678715B1 (fr) * 1991-07-03 1995-01-13 Snecma Bol de chambre de combustion pour injection aerodynamique.
FR2698157B1 (fr) * 1992-11-18 1994-12-16 Snecma Système d'injection aérodynamique de chambre de combustion.
GB2299399A (en) * 1995-03-25 1996-10-02 Rolls Royce Plc Variable geometry air-fuel injector
US6898938B2 (en) * 2003-04-24 2005-05-31 General Electric Company Differential pressure induced purging fuel injector with asymmetric cyclone
ITMO20030154A1 (it) * 2003-05-23 2004-11-24 Worgas Bruciatori Srl Bruciatore modulabile
US7836699B2 (en) * 2005-12-20 2010-11-23 United Technologies Corporation Combustor nozzle
FR2901349B1 (fr) * 2006-05-19 2008-09-05 Snecma Sa Chambre de combustion d'une turbomachine
US8146365B2 (en) * 2007-06-14 2012-04-03 Pratt & Whitney Canada Corp. Fuel nozzle providing shaped fuel spray
FR2950415B1 (fr) * 2009-09-21 2011-10-14 Snecma Chambre de combustion de turbomachine aeronautique avec trous de combustion decales ou de debits differents
FR2980554B1 (fr) 2011-09-27 2013-09-27 Snecma Chambre annulaire de combustion d'une turbomachine
FR3141755A1 (fr) * 2022-11-08 2024-05-10 Safran Aircraft Engines Chambre de combustion d’une turbomachine

Family Cites Families (15)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
DE386159C (de) * 1923-12-04 Stettin Act Ges Luftzufuehrung bei OElfeuerungen
FR950363A (fr) * 1946-07-30 1949-09-26 Westinghouse Electric Corp Dispositif de combustion pour turbines à gaz
US2655787A (en) * 1949-11-21 1953-10-20 United Aircraft Corp Gas turbine combustion chamber with variable area primary air inlet
US3490230A (en) * 1968-03-22 1970-01-20 Us Navy Combustion air control shutter
US3831854A (en) * 1973-02-23 1974-08-27 Hitachi Ltd Pressure spray type fuel injection nozzle having air discharge openings
US3834159A (en) * 1973-08-03 1974-09-10 Gen Electric Combustion apparatus
US3901446A (en) * 1974-05-09 1975-08-26 Us Air Force Induced vortex swirler
US3982392A (en) * 1974-09-03 1976-09-28 General Motors Corporation Combustion apparatus
JPS5296420A (en) * 1976-02-10 1977-08-13 Mitsubishi Heavy Ind Ltd Burner
FR2357738A1 (fr) * 1976-07-07 1978-02-03 Snecma Chambre de combustion pour turbomachines
FR2391359A2 (fr) * 1977-05-18 1978-12-15 Snecma Chambre de combustion pour turbomachines
GB1539136A (en) * 1976-07-07 1979-01-24 Snecma Gas turbine combustion chambers
US4050240A (en) * 1976-08-26 1977-09-27 General Motors Corporation Variable air admission device for a combustor assembly
GB2085146B (en) * 1980-10-01 1985-06-12 Gen Electric Flow modifying device
GB2085147A (en) * 1980-10-01 1982-04-21 Gen Electric Flow modifying device

Also Published As

Publication number Publication date
FR2588919A1 (fr) 1987-04-24
US4696157A (en) 1987-09-29
JPH0637977B2 (ja) 1994-05-18
DE3661440D1 (en) 1989-01-19
EP0224397A1 (de) 1987-06-03
JPS62106223A (ja) 1987-05-16
FR2588919B1 (fr) 1987-12-04

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