EP1731839B1 - Vorrichtung zum Anbringen einer Einspritzungvorrichtung am Boden einer Turbinenbrennkammer und Verfahren zum Anbringen - Google Patents

Vorrichtung zum Anbringen einer Einspritzungvorrichtung am Boden einer Turbinenbrennkammer und Verfahren zum Anbringen Download PDF

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Publication number
EP1731839B1
EP1731839B1 EP06115000.9A EP06115000A EP1731839B1 EP 1731839 B1 EP1731839 B1 EP 1731839B1 EP 06115000 A EP06115000 A EP 06115000A EP 1731839 B1 EP1731839 B1 EP 1731839B1
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EP
European Patent Office
Prior art keywords
deflector
injection system
turbojet
retaining
shoulder
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.)
Active
Application number
EP06115000.9A
Other languages
English (en)
French (fr)
Other versions
EP1731839A3 (de
EP1731839A2 (de
Inventor
Didier Hippolyte Hernandez
Romain Nicolas Lunel
Christophe Pieussergues
David Pinchon
Guillaume Sevi
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
SNECMA SAS
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
Priority claimed from FR0551518A external-priority patent/FR2886714B1/fr
Application filed by SNECMA SAS filed Critical SNECMA SAS
Publication of EP1731839A2 publication Critical patent/EP1731839A2/de
Publication of EP1731839A3 publication Critical patent/EP1731839A3/de
Application granted granted Critical
Publication of EP1731839B1 publication Critical patent/EP1731839B1/de
Active 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
    • F23R3/04—Air inlet arrangements
    • F23R3/10—Air inlet arrangements for primary air
    • 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
    • F23R3/283—Attaching or cooling of fuel injecting means including supports for fuel injectors, stems, or lances
    • 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
    • F23R3/42—Continuous combustion chambers using liquid or gaseous fuel characterised by the arrangement or form of the flame tubes or combustion chambers
    • F23R3/60—Support structures; Attaching or mounting means

Definitions

  • the invention relates to a system for fixing an injection system on a turbojet engine combustion chamber bottom.
  • the combustion chambers of the turbojet engines comprise an inner wall and an outer wall connected at their upstream end by an annular bottom to define a combustion chamber bottom.
  • Regularly distributed injection systems on the periphery of the bottom of the combustion chamber deliver a mixture of air and fuel which is ignited to provide combustion gases.
  • Each injection system includes a venturi in which air and fuel mix.
  • a bowl located downstream of the venturi, has the function of bursting the jet of air / fuel mixture leaving the venturi.
  • a deflector protects the chamber bottom of the flames of the combustion chamber.
  • the injection system is mounted downstream that is to say from the rear of the turbojet engine.
  • the injection system is brazed to the chamber bottom directly or through an intermediate piece; the deflector and the bowl are brazed on the injection system. If the solder between the injection system and the bowl gives way, the latter comes crashing the combustion chamber and the downstream part of the engine, including the HP turbine, which can lead to an explosion of the engine.
  • the present invention relates to an injection system and a fixing method that overcomes these disadvantages.
  • the deflector comprises an annular portion having a shoulder forming a retaining shoulder directed towards the front of the turbojet and the fact that the injection system comprises a collar on which is formed a retaining shoulder. directed towards the rear of the turbojet and bearing against the retaining shoulder of the deflector.
  • the baffle has a retaining groove and a retaining ring has a rim inserted into the retaining groove.
  • the deflector is always mounted by the downstream part of the chamber but is mechanically retained by the flange of the retaining ring inserted into its retaining groove.
  • the deflector can not be sucked into the combustion chamber.
  • the bowl of the injection system is mounted by the front part of the turbojet engine. Its retaining shoulder provides a mechanical attachment so that it can not, either, be sucked into the combustion chamber of the turbojet engine.
  • the deflector and the retaining ring are brazed in the same brazing operation.
  • the injection system is attached to the retaining ring by welding beads.
  • the retaining ring is a split ring.
  • the flange of the injection system further comprises a shoulder directed towards the front of the turbojet engine and the retaining ring has a second flange which blocks the second shoulder of the injection system.
  • the retaining ring consists of a split inner ring or formed of two half rings and a closure ring which surrounds the inner ring.
  • the split ring has a conical bearing to eliminate axial play.
  • the inner ring is attached to the closure ring by welding points.
  • the first shoulder directed towards the front of the turbojet and the second shoulder directed towards the rear of the turbojet engine are formed on a collar of a bowl forming part of the injection system.
  • the injection system generally designated by the general reference 2 consists of a fixed part consisting of a ring 4, a twist 6, a venturi 8 and a bowl 10.
  • the spin 6 and the bowl 10 are connected to each other by an intermediate ring 12.
  • a sliding bushing 14 is slidably mounted on the ring 4.
  • the auger has two stages of blades which have the function of driving the air in rotation around the longitudinal axis YY of the injection system.
  • the bowl 10 has a flared shape 16 whose function is to burst the jet of the mixture of air and fuel leaving the venturi 8.
  • a deflector 20 is mounted on the chamber bottom 22.
  • the chamber bottom itself has two clamping zones 24 and 26.
  • the clamping zone 24 is connected to an outer chamber wall (not shown) and the inner clamping area 26 is connected to an inner chamber wall, also not shown.
  • a plurality of injection systems typically thirteen to thirty two, regularly spaced angularly are mounted on the chamber bottom 22 (only one injection system has been shown on the figure 1 ).
  • the deflector 20 comprises a plate 30 and an annular portion 32 brazed to the chamber bottom.
  • the plate 30 serves to protect the part of the chamber bottom located around the injection system 2 of the flames of the combustion chamber.
  • the annular portion 32 is inserted into a hole 33 formed in the chamber bottom. It comprises a shoulder 100 which bears against the downstream wall of the chamber bottom.
  • the annular portion 32 has a bore 36 in which is housed a cylindrical portion 38 of the bowl 10.
  • the annular portion 32 of the deflector comprises a retaining groove 40.
  • the edge 42 of the annular portion 32 of the deflector constitutes a retaining shoulder.
  • the cylindrical portion 38 of the bowl 10 is extended by a flange 44 of larger diameter having a retaining shoulder 46 directed towards the rear of the turbojet and bearing against the retaining shoulder 42 of the baffle.
  • a split retaining ring 50 has a flange 52 inserted into the retaining groove 40 of the deflector 20.
  • Welding beads 54 for example three or four (see FIG. figure 2 , provide a connection between the flange 44 of the bowl 10 and the retaining ring 50.
  • the assembly of the injection system on the chamber floor is carried out as follows. Firstly, the baffle 20 is inserted into the hole 33 made in the chamber bottom and the split retaining ring 50 is mounted on the deflector in such a way that the flange 52 is housed inside the retaining groove. annular 40 of the deflector. These two parts are then assembled together and at the chamber bottom 22 by a single brazing operation.
  • the injection system is then mounted by the front of the turbojet, as shown schematically by the arrow 56 ( figure 1 ) so that the cylindrical portion 38 of the bowl comes to be mounted within the bore 36 of the baffle. In this position the shoulder 46 formed on the portion 44 of the bowl bears on the edge 42 of the annular portion 32 forming a retaining shoulder.
  • the front end of the portion 44 is at the same level as the front end of the split ring 50 so that it is possible to produce weld beads 54 to secure these two parts.
  • the deflector 20 is mechanically retained by the flange 52 of the split ring 50.
  • the injection system 2, and more particularly the bowl 10 are mounted by the front of the turbojet and they are mechanically retained by the abutment of the shoulder 46 of the flange 44. of the bowl against the shoulder of the deflector 42.
  • the weld points 54 do not provide mechanical strength but simply function to prevent the rotation of the injection system 2 relative to the split ring 50.
  • the disassembly operations of the injection system are facilitated, for example when it is desired to replace a defective injection system. It suffices to grind the welding beads 54, which releases the injection system and allows it to be removed by moving it in a direction opposite to the direction of the arrow 56 ( figure 1 ). The solder baffles on the chamber bottom and the split ring on the baffle are not affected. In the same way, the introduction of the new injection system is very simple since it is sufficient to insert it into the bore 36 and redo new welding beads 54.
  • this device provides many advantages, on the one hand because it eliminates the risk that parts are entrained in the combustion chamber and in the downstream part of the engine, in particular the high pressure turbine, and secondly because it facilitates the operations of maintenance and repair making it much easier to replace a defective injection system.
  • neither the deflector nor the injection system bowl can not be driven to the rear of the turbojet in case of breakage of solders because they are mechanically retained.
  • a bias is exerted on the injection system in opposite direction, that is to say in the opposite direction to that of the arrow 56 of the figure 1 , the effort will be taken up by the weld seams which can then give way.
  • a solicitation of this type can occur when the injectors are placed on the sliding bushing because there may be an arcboutement of the injectors. The forces experienced by the weld points in such a situation could eventually cause them to break. In this case, the bowl would be separated from the bottom chamber 22.
  • the shape of the deflector 20 is identical.
  • the constitution of the retaining ring differs.
  • the retaining ring 60 consists of an inner ring 62 and a closure ring 64.
  • the inner ring can be split as in the embodiment previous or it may consist of two half rings. It comprises, as before, a flange 52 which is housed in the groove 40 of the baffle and further a second flange 66 which immobilizes a flange 44 located at the end of the cylindrical portion 38 of the bowl. The flange 44 is thus immobilized in both directions. Towards the rear of the turbojet, it is immobilized as previously by the edge 42 of the annular portion of the deflector 20.
  • the deflector comprises a lug 70, of section for example substantially rectangular, which is housed in a corresponding notch 72 of the same shape and the same section formed in the collar 44 of the bowl 10. On thus ensures immobilization in rotation of the bowl relative to the deflector which is itself brazed to the bottom wall as previously exposed.
  • the baffle 20 is fixed to the chamber bottom 22 both by brazing and mechanically by means of a brazed split ring 150 having a flange 152 which penetrates into a circular groove 140 formed in the annular portion 32 of the deflector 20.
  • This embodiment is similar to the embodiment of the figures 1 and 2 .
  • the annular portion of the deflector comprises a second circular groove 158 intended to receive one of the flanges of a retaining ring 160.
  • the retaining ring consists of an inner ring 162 and a closure ring 164 which surrounds the inner ring 162.
  • the inner ring 162 may be constituted by a split ring or by two half rings.
  • the inner ring has a first flange 166 and a second flange 168.
  • the inner ring has tapered bearing surfaces for removing axial clearances. The axial forces tending to open the split ring or the two half rings are taken up by the closure ring 164.
  • Welding beads 154 provide a connection between the inner ring 162 and the closure ring 164. These weld seams are not mechanically stressed.
  • This embodiment also works if the staves are not tapered. There then remains a slight axial play due to manufacturing tolerances.

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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)
  • Combustion Methods Of Internal-Combustion Engines (AREA)
  • Turbine Rotor Nozzle Sealing (AREA)
  • Structures Of Non-Positive Displacement Pumps (AREA)

Claims (13)

  1. System zur Befestigung eines Einspritzsystems (2) an einem Brennkammerboden (22) eines Turbostrahltriebwerks, wobei das System einen Deflektor (20), der an den Kammerboden (22) gelötet ist, umfasst, dadurch gekennzeichnet, dass der Deflektor einen ringförmigen Teil (32) mit einer Kante (42), die eine zur Vorderseite des Turbostrahltriebwerks gerichtete Halteschulter bildet, umfasst und dass das Einspritzsystem (2) einen Kragen (44) umfasst, an dem eine Halteschulter (46), welche zur Rückseite des Turbostrahltriebwerks gerichtet ist und sich an der Halteschulter (42) des Deflektors (20) abstützt, ausgebildet ist.
  2. Befestigungssystem nach Anspruch 1, dadurch gekennzeichnet, dass der Deflektor (20) eine Haltekehle (40) umfasst und dass ein Haltering einen in die Haltekehle eingefügten Rand (52) umfasst.
  3. Befestigungssystem nach einem der Ansprüche 1 oder 2, dadurch gekennzeichnet, dass der Haltering (50) und der Deflektor (20) in einem gleichen Lötvorgang gelötet werden.
  4. Befestigungssystem nach Anspruch 3, dadurch gekennzeichnet, dass das Einspritzsystem (2) an dem Haltering (50) durch Schweißnähte (54) befestigt ist.
  5. Befestigungssystem nach einem der Ansprüche 3 oder 4, dadurch gekennzeichnet, dass der Haltering (50) ein Schlitzring ist.
  6. Befestigungssystem nach einem der Ansprüche 1 oder 2, dadurch gekennzeichnet, dass der Kragen (44) des Einspritzsystems (2) ferner eine zur Vorderseite des Turbostrahltriebwerks gerichtete zweite Schulter (68) umfasst und dass der Haltering einen zweiten Rand (66) umfasst, der die zweite Schulter (68) des Einspritzsystems blockiert.
  7. Befestigungssystem nach Anspruch 6, dadurch gekennzeichnet, dass der Haltering (60) von einem Innenring (62), welcher geschlitzt oder von zwei halben Ringen gebildet ist, sowie von einem Schließring (64), welcher den Innenring (62) einfasst, gebildet ist.
  8. Befestigungssystem nach Anspruch 7, dadurch gekennzeichnet, dass der Innenring konische Auflageflächen hat.
  9. Befestigungssystem nach einem der Ansprüche 6 bis 8, dadurch gekennzeichnet, dass die erste Schulter des Einspritzsystems, die zur Rückseite des Turbostrahltriebwerks gerichtet ist, und dass die zweite Schulter des Einspritzsystems, die zur Vorderseite des Turbostrahltriebwerks gerichtet ist, an einem Kragen einer zu einem Einspritzsystem (2) gehörenden Schale ausgebildet sind.
  10. Brennkammer, die mit einem Befestigungssystem nach einem der Ansprüche 1 bis 9 ausgestattet ist.
  11. Turbomaschine, die eine Brennkammer nach Anspruch 10 umfasst.
  12. Befestigungsverfahren eines Systems zur Befestigung an einem Brennkammerboden (22) eines Turbostrahltriebwerks, dadurch gekennzeichnet, dass:
    - ein Deflektor (20), der einen ringförmigen Teil (32) mit einer Kante (42), welche eine zur Vorderseite des Turbostrahltriebwerks gerichtete Halteschulter bildet, umfasst, in ein Loch (33) des Kammerbodens eingeführt wird;
    - ein Haltering (50) über die Vorderseite des Turbostrahltriebwerks an dem Deflektor angebracht wird;
    - der Deflektor an den Kammerboden und gleichzeitig der Haltering an den Deflektor gelötet wird;
    - ein Einspritzsystem (2) über die Vorderseite des Turbostrahltriebwerks in den Deflektor (20) eingeführt wird, wobei das Einspritzsystem (2) eine zur Rückseite des Turbostrahltriebwerks gerichtete Schulter umfasst, die sich an der Halteschulter des Deflektors (20) abstützt;
    - das Einspritzsystem (2) über Schweißnähte (54) an den Haltering geschweißt wird.
  13. Verfahren zur Befestigung eines Einspritzsystems (2) an einem Brennkammerboden (22) eines Turbostrahltriebwerks, dadurch gekennzeichnet, dass:
    - ein Deflektor (20), der einen ringförmigen Teil (32) mit einer Kante (42), welche eine zur Vorderseite des Turbostrahltriebwerks gerichtete Halteschulter bildet, umfasst, in ein Loch (33) des Kammerbodens eingeführt wird, wobei der Deflektor eine Haltekehle umfasst;
    - der Deflektor (20) an den Kammerboden gelötet wird;
    - ein Einspritzsystem (2) über die Vorderseite des Turbostrahltriebwerks in den Deflektor (20) eingeführt wird, wobei das Einspritzsystem (2) eine zur Rückseite des Turbostrahltriebwerks gerichtete erste Schulter, die sich an der Halteschulter des Deflektors abstützt, sowie eine zur Vorderseite des Turbostrahltriebwerks gerichtete zweite Schulter umfasst;
    - ein Haltering, welcher einen ersten Rand, der in der Haltekehle des Deflektors aufgenommen wird, und einen zweiten Rand, der die zweite Schulter des Einspritzsystems blockiert, umfasst, angebracht wird;
    - das Einspritzsystem mit dem Deflektor durch Ausbilden von Schweißnähten (54) zwischen dem Haltering und dem Schließring befestigt wird.
EP06115000.9A 2005-06-07 2006-06-06 Vorrichtung zum Anbringen einer Einspritzungvorrichtung am Boden einer Turbinenbrennkammer und Verfahren zum Anbringen Active EP1731839B1 (de)

Applications Claiming Priority (2)

Application Number Priority Date Filing Date Title
FR0551518A FR2886714B1 (fr) 2005-06-07 2005-06-07 Systeme d'injection anti-rotatif pour turbo-reacteur
FR0552929A FR2886715B1 (fr) 2005-06-07 2005-09-28 Systeme de fixation d'un systeme d'injection sur un fond de chambre de combustion de turboreacteur et procede de fixation

Publications (3)

Publication Number Publication Date
EP1731839A2 EP1731839A2 (de) 2006-12-13
EP1731839A3 EP1731839A3 (de) 2013-05-08
EP1731839B1 true EP1731839B1 (de) 2015-08-05

Family

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EP06115000.9A Active EP1731839B1 (de) 2005-06-07 2006-06-06 Vorrichtung zum Anbringen einer Einspritzungvorrichtung am Boden einer Turbinenbrennkammer und Verfahren zum Anbringen

Country Status (5)

Country Link
US (1) US7673460B2 (de)
EP (1) EP1731839B1 (de)
JP (1) JP4875928B2 (de)
CA (1) CA2548869C (de)
RU (1) RU2406935C2 (de)

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FR2910115B1 (fr) * 2006-12-19 2012-11-16 Snecma Deflecteur pour fond de chambre de combustion, chambre de combustion en etant equipee et turboreacteur les comportant
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FR2964177B1 (fr) * 2010-08-27 2012-08-24 Snecma Chambre de combustion de moteur d?aeronef et procede de fixation d?un systeme d?injection dans une chambre de combustion de moteur d?aeronef
FR2971038B1 (fr) * 2011-01-31 2013-02-08 Snecma Dispositif d'injection pour une chambre de combustion de turbomachine
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FR3026827B1 (fr) * 2014-10-01 2019-06-07 Safran Aircraft Engines Chambre de combustion de turbomachine
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Also Published As

Publication number Publication date
RU2006119912A (ru) 2007-12-20
EP1731839A3 (de) 2013-05-08
CA2548869A1 (fr) 2006-12-07
JP4875928B2 (ja) 2012-02-15
EP1731839A2 (de) 2006-12-13
US20070084215A1 (en) 2007-04-19
JP2006343092A (ja) 2006-12-21
RU2406935C2 (ru) 2010-12-20
CA2548869C (fr) 2014-05-20
US7673460B2 (en) 2010-03-09

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