EP1731839A2 - System for fixing an injection system to the dome of turbine combustion chamber and method of fixation - Google Patents
System for fixing an injection system to the dome of turbine combustion chamber and method of fixation Download PDFInfo
- Publication number
- EP1731839A2 EP1731839A2 EP06115000A EP06115000A EP1731839A2 EP 1731839 A2 EP1731839 A2 EP 1731839A2 EP 06115000 A EP06115000 A EP 06115000A EP 06115000 A EP06115000 A EP 06115000A EP 1731839 A2 EP1731839 A2 EP 1731839A2
- Authority
- EP
- European Patent Office
- Prior art keywords
- deflector
- injection system
- shoulder
- retaining
- ring
- 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
Links
- 238000002347 injection Methods 0.000 title claims abstract description 78
- 239000007924 injection Substances 0.000 title claims abstract description 78
- 238000002485 combustion reaction Methods 0.000 title claims abstract description 20
- 238000000034 method Methods 0.000 title claims abstract description 7
- 239000011324 bead Substances 0.000 claims description 14
- 238000003466 welding Methods 0.000 claims description 11
- 238000005219 brazing Methods 0.000 claims description 5
- 230000014759 maintenance of location Effects 0.000 abstract 2
- 229910000679 solder Inorganic materials 0.000 description 9
- 230000000717 retained effect Effects 0.000 description 6
- 239000000446 fuel Substances 0.000 description 4
- 239000000203 mixture Substances 0.000 description 4
- 230000002950 deficient Effects 0.000 description 2
- 238000012423 maintenance Methods 0.000 description 2
- 230000009172 bursting Effects 0.000 description 1
- 239000000567 combustion gas Substances 0.000 description 1
- 238000004880 explosion Methods 0.000 description 1
- 238000004519 manufacturing process Methods 0.000 description 1
- 238000011144 upstream manufacturing Methods 0.000 description 1
Images
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 auger 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 comprises 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 in 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. 2, provide a connection between the flange 44 of the bowl 10 and the ring restraint 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 from 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 weld beads 54 which releases the injection system and allows to remove it 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.
- FIG. 3 shows an alternative embodiment of the fastening system of FIGS. 1 and 2.
- FIGS. 3 and 4 there is provided an embodiment of the invention shown in FIGS. 3 and 4 in which the injection system, and particularly the bowl forming part of the injection system, is mechanically retained. in both directions without any effort being exerted on the weld seams.
- 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 anti-rotation function is provided by the solder points 54 themselves, which is no longer the case in the present embodiment.
- 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 of the same section formed in the flange 44 of the bowl 10. thus ensures immobilization in rotation of the bowl relative to the deflector which is itself brazed to the bottom wall as previously exposed.
- FIG. 5 shows a third embodiment of the invention which combines the characteristics of the first mode and the second embodiment of FIGS. 1 and 2 on the one hand and 3 and 4 on the other hand.
- 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
- This embodiment is similar to the embodiment of FIGS. 1 and 2.
- the annular part 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)
- Structures Of Non-Positive Displacement Pumps (AREA)
- Combustion Methods Of Internal-Combustion Engines (AREA)
- Turbine Rotor Nozzle Sealing (AREA)
Abstract
Description
L'invention concerne un système de fixation d'un système d'injection sur un fond de chambre de combustion de turboréacteur.The invention relates to a system for fixing an injection system on a turbojet engine combustion chamber bottom.
Les chambres de combustion des turboréacteurs comprennent une paroi intérieure et une paroi extérieure reliées à leur extrémité amont par un fond annulaire pour définir un fond de chambre de combustion. Des systèmes d'injection régulièrement répartis sur la périphérie du fond de la chambre de combustion délivrent un mélange d'air et de carburant qui est enflammé pour fournir des gaz de combustion.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.
Chaque système d'injection comprend un venturi dans lequel l'air et le carburant se mélangent. Un bol, situé en aval du venturi, a pour fonction d'éclater le jet de mélange air/carburant sortant du venturi. En outre, un déflecteur protège le fond de chambre des flammes de la chambre de combustion.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. In addition, a deflector protects the chamber bottom of the flames of the combustion chamber.
Dans une réalisation connue (
En outre, en dehors de ce problème de risque de rupture d'une brasure, il est malaisé de démonter un système d'injection afin d'assurer sa maintenance ou son remplacement. En effet, cette opération nécessite de retirer trois brasures en même temps, ce qui est délicat et nécessite le plus souvent le sacrifice d'une pièce, généralement le système d'injection lui-même. La présente invention a pour objet un système d'injection et un procédé de fixation qui remédient à ces inconvénients.In addition, apart from this problem of risk of breaking a solder, it is difficult to disassemble an injection system to ensure its maintenance or replacement. Indeed, this operation requires removing three solders at the same time, which is difficult and usually requires the sacrifice of a part, usually the injection system itself. The present invention relates to an injection system and a fixing method that overcomes these disadvantages.
Ces buts sont atteints par le fait que le déflecteur comporte une partie annulaire ayant un chant formant un épaulement de retenue dirigé vers l'avant du turboréacteur et par le fait que le système d'injection comporte une collerette sur laquelle est formé un épaulement de retenue dirigé vers l'arrière du turboréacteur et prenant appui contre l'épaulement de retenue du déflecteur.These aims are achieved by the fact that 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.
Dans une réalisation, le déflecteur comporte une gorge de retenue et une bague de retenue comporte un rebord inséré dans la gorge de retenue.In one embodiment, the baffle has a retaining groove and a retaining ring has a rim inserted into the retaining groove.
Avec ces caractéristiques, le déflecteur est toujours monté par la partie aval du fond de chambre mais il est retenu mécaniquement par le rebord de la bague de retenue insérée dans sa gorge de retenue. Ainsi, même en cas de rupture de la brasure entre le fond de chambre et le déflecteur, ce dernier ne peut pas être aspiré dans la chambre de combustion.With these characteristics, 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. Thus, even in case of breakage of the solder between the chamber bottom and the deflector, the latter can not be sucked into the combustion chamber.
D'autre part, le bol du système d'injection est monté par la partie avant du turboréacteur. Son épaulement de retenue assure une fixation mécanique de telle sorte qu'il ne peut pas, lui non plus, être aspiré dans la chambre de combustion du turboréacteur.On the other hand, 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.
Avantageusement, le déflecteur et la bague de retenue sont brasés dans une même opération de brasage.Advantageously, the deflector and the retaining ring are brazed in the same brazing operation.
Le système d'injection est fixé à la bague de retenue par des cordons de soudure.The injection system is attached to the retaining ring by welding beads.
Ces cordons de soudure n'assurent pas une résistance mécanique étant donné que les efforts sont repris par l'épaulement de retenue du système d'injection. Ils sont donc moins susceptibles de se rompre et, même si cela venait à se produire, le système d'injection serait tout de même maintenu en avant du fond de chambre.These weld seams do not provide mechanical strength since the forces are taken up by the retaining shoulder of the injection system. They are therefore less likely to break, and even if this were to happen, the injection system would still be held in front of the chamber floor.
Dans une réalisation particulière, la bague de retenue est une bague fendue.In a particular embodiment, the retaining ring is a split ring.
Dans une autre réalisation, la collerette du système d'injection comporte en outre un épaulement dirigé vers l'avant du turboréacteur et la bague de retenue comporte un second rebord qui vient bloquer le second épaulement du système d'injection.In another embodiment, 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.
Dans une réalisation particulière la bague de retenue est constituée d'une bague intérieure fendue ou formée de deux demies bagues et d'une bague de fermeture qui cercle la bague intérieure.In a particular embodiment the retaining ring consists of a split inner ring or formed of two half rings and a closure ring which surrounds the inner ring.
Avantageusement, la bague fendue a une portée conique pour supprimer les jeux axiaux.Advantageously, the split ring has a conical bearing to eliminate axial play.
La bague intérieure est fixée à la bague de fermeture par des points de soudure.The inner ring is attached to the closure ring by welding points.
Avantageusement encore, le premier épaulement dirigé vers l'avant du turboréacteur et le second épaulement dirigé vers l'arrière du turboréacteur sont formés sur une collerette d'un bol faisant partie du système d'injection.Advantageously, 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.
Selon le procédé de fixation d'un système d'injection sur un fond de chambre de combustion de turboréacteur :
- on introduit un déflecteur comportant une partie annulaire présentant un chant formant un épaulement de retenue dirigé vers l'avant du turboréacteur dans un trou du fond de chambre ;
- on monte une bague de retenue sur le déflecteur par l'avant du turboréacteur ;
- on brase le déflecteur sur le fond de chambre et simultanément la bague de retenue sur le déflecteur ;
- on introduit par l'avant du turboréacteur un système d'injection dans le déflecteur, le système d'injection comportant un épaulement dirigé vers l'arrière du turboréacteur qui vient prendre appui sur l'épaulement de retenue du déflecteur ;
- on soude le système d'injection sur la bague de retenue par des cordons de soudure.
- introducing a baffle having an annular portion having a singing forming a retaining shoulder directed towards the front of the turbojet in a hole of the chamber bottom;
- a retaining ring is mounted on the deflector by the front of the turbojet engine;
- the deflector is pressed against the chamber bottom and simultaneously the retaining ring on the deflector;
- an injection system is introduced through the front of the turbojet engine into the deflector, the injection system having a shoulder directed towards the rear of the turbojet which comes to rest on the retaining shoulder of the deflector;
- the injection system is welded to the retaining ring by welding beads.
Selon une variante du procédé :
- on introduit un déflecteur comportant une partie annulaire présentant un chant formant un épaulement de retenue dirigé vers l'avant du turboréacteur dans un trou du fond de chambre, le déflecteur comportant une gorge de retenue ;
- on brase le déflecteur sur le fond de chambre ;
- on introduit par l'avant du turboréacteur un système d'injection dans le déflecteur le système d'injection comportant un premier épaulement dirigé vers l'arrière du turboréacteur qui vient prendre appui sur l'épaulement de retenue du déflecteur et un second épaulement dirigé vers l'avant du turboréacteur ;
- on monte une bague de retenue comportant un premier rebord qui vient se loger dans la gorge de retenue du déflecteur et un second rebord qui vient bloquer le second épaulement du système d'injection ;
- on fixe le système d'injection sur le déflecteur en réalisant des cordons de soudure entre la bague de retenue et la bague de fermeture.
- introducing a deflector comprising an annular portion having a singing forming a retaining shoulder directed towards the front of the turbojet in a hole of the chamber bottom, the deflector having a retaining groove;
- the deflector is pressed against the chamber floor;
- a injection system is introduced through the front of the turbojet into the deflector, the injection system comprising a first shoulder directed towards the rear of the turbojet which bears on the retaining shoulder of the deflector and a second shoulder directed towards the the front of the turbojet engine;
- mounting a retaining ring having a first rim which is housed in the retaining groove of the deflector and a second rim which blocks the second shoulder of the injection system;
- the injection system is fixed on the deflector by producing weld beads between the retaining ring and the closure ring.
D'autres caractéristiques et avantages de l'invention apparaîtront encore à la lecture de la description qui suit d'exemples de réalisation donnés à titre illustratif en référence aux figures annexées.Other features and advantages of the invention will become apparent on reading the following description of exemplary embodiments given by way of illustration with reference to the appended figures.
Sur ces figures :
- la figure 1 est une vue en coupe d'un premier mode de réalisation d'un système d'injection conforme à la présente invention ;
- la figure 2 est une vue de détail agrandie de la figure 1 ;
- la figure 3 est une demie vue en coupe d'un deuxième mode de réalisation du système de fixation de l'invention ;
- la figure 4 est une vue en perspective du bol monté sur le déflecteur du système d'injection de la figure 3 ;
- la figure 5 est une vue en coupe d'un troisième mode de réalisation du système de fixation de l'invention.
- Figure 1 is a sectional view of a first embodiment of an injection system according to the present invention;
- Figure 2 is an enlarged detail view of Figure 1;
- Figure 3 is a half sectional view of a second embodiment of the fastening system of the invention;
- Figure 4 is a perspective view of the bowl mounted on the deflector of the injection system of Figure 3;
- Figure 5 is a sectional view of a third embodiment of the fastening system of the invention.
Sur la figure 1, le système d'injection, désigné dans son ensemble par la référence générale 2 est constitué d'une partie fixe constituée d'une bague 4, d'une vrille 6, d'un venturi 8 et d'un bol 10. La vrille 6 et le bol 10 sont raccordés l'un à l'autre par une bague intermédiaire 12. Une traversée coulissante 14 est montée coulissante sur la bague 4. La vrille comporte deux étages d'aubes qui ont pour fonction d'entraîner l'air en rotation autour de l'axe longitudinal YY du système d'injection. Le bol 10 comporte une forme évasée 16 qui a pour fonction de faire éclater le jet du mélange d'air et de carburant sortant du venturi 8.In Figure 1, the injection system, generally designated by the general reference 2 consists of a fixed part consisting of a
Un déflecteur 20 est monté sur le fond de chambre 22. Le fond de chambre lui-même comporte deux zones de bridage 24 et 26. La zone de bridage 24 est raccordée à une paroi de chambre extérieure (non représentée) et la zone de bridage intérieure 26 est raccordée à une paroi de chambre intérieure, également non représentée. Une pluralité de systèmes d'injection, typiquement de treize à trente deux, régulièrement espacés angulairement sont montés sur le fond de chambre 22 (un seul système d'injection a été représenté sur la figure 1).A
Le déflecteur 20 comporte un plateau 30 et une partie annulaire 32 brasée sur le fond de chambre. Le plateau 30 a pour fonction de protéger la partie du fond de chambre située autour du système d'injection 2 des flammes de la chambre de combustion. La partie annulaire 32 est insérée dans un trou 33 formé dans le fond de chambre. Elle comporte un épaulement 100 qui vient en appui contre la paroi aval du fond de chambre. Intérieurement, la partie annulaire 32 comporte un alésage 36 dans lequel vient se loger une partie cylindrique 38 du bol 10. En outre, la partie annulaire 32 du déflecteur comporte une gorge de retenue 40. Le chant 42 de la partie annulaire 32 du déflecteur constitue un épaulement de retenue. La partie cylindrique 38 du bol 10 est prolongée par une collerette 44 de plus grand diamètre comportant un épaulement de retenue 46 dirigé vers l'arrière du turboréacteur et prenant appui contre l'épaulement de retenue 42 du déflecteur. Une bague fendue de retenue 50 comporte un rebord 52 inséré dans la gorge de retenue 40 du déflecteur 20. Des cordons de soudure 54, par exemple trois ou quatre (voir figure 2, assurent une liaison entre la collerette 44 du bol 10 et la bague de retenue 50.The
Le montage du système d'injection sur le fond de chambre s'effectue de la manière suivante. On insère d'abord le déflecteur 20 dans l'orifice 33 pratiqué dans le fond de chambre puis on monte la bague de retenue fendue 50 sur le déflecteur de telle manière que le rebord 52 vienne se loger à l'intérieur de la gorge de retenue annulaire 40 du déflecteur. Ces deux pièces sont alors assemblées entre elles et au fond de chambre 22 par une opération unique de brasage. Le système d'injection est alors monté par l'avant du turboréacteur, comme schématisé par la flèche 56 (figure 1) de telle manière que la partie cylindrique 38 du bol vienne se monter à l'intérieur de l'alésage 36 du déflecteur. Dans cette position l'épaulement 46 formé sur la partie 44 du bol vient en appui sur le chant 42 de la partie annulaire 32 formant un épaulement de retenue. Avantageusement, l'extrémité avant de la partie 44 est au même niveau que l'extrémité avant de la bague fendue 50 de telle sorte qu'il est possible de réaliser des cordons de soudure 54 pour solidariser ces deux pièces.The assembly of the injection system on the chamber floor is carried out as follows. Firstly, the
Dans cette réalisation, comme on peut le constater, le déflecteur 20 est retenu mécaniquement par le rebord 52 de la bague fendue 50. De la sorte, en admettant même que la brasure reliant le déflecteur au fond de chambre 22 vienne à céder, ce dernier ne peut pas être aspiré dans la partie avant du turboréacteur. D'autre part, le système d'injection 2, et plus particulièrement le bol 10, sont montés par l'avant du turboréacteur et ils sont retenus mécaniquement par la venue en butée de l'épaulement 46 de la collerette 44 du bol contre l'épaulement du déflecteur 42. Ainsi, les points de soudure 54 n'assurent pas une résistance mécanique mais ont simplement pour fonction d'empêcher la rotation du système d'injection 2 par rapport à la bague fendue 50.In this embodiment, as can be seen, the
Par ailleurs, les opérations de démontage du système d'injection sont facilitées, par exemple lorsque l'on souhaite remplacer un système d'injection défectueux. Il suffit en effet de meuler les cordons de soudure 54 ce qui libère le système d'injection et permet de le retirer en le déplaçant dans un sens opposé au sens de la flèche 56 (figure 1). Les brasures du déflecteur sur le fond de chambre et de la bague fendue sur le déflecteur ne sont pas touchées. De la même manière, la mise en place du nouveau système d'injection s'effectue très simplement puisqu'il suffit de l'insérer dans l'alésage 36 et de refaire de nouveaux cordons de soudure 54. Ainsi, ce dispositif apporte de nombreux avantages, d'une part parce qu'il élimine le risque que des pièces soient entraînées dans la chambre de combustion et dans la partie aval du moteur, notamment la turbine à haute pression et d'autre part parce qu'il facilite les opération de maintenance et de réparation en permettant de remplacer beaucoup plus facilement un système d'injection défectueux.Furthermore, 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
On a représenté sur la figure 3 une variante de réalisation du système de fixation des figures 1 et 2.FIG. 3 shows an alternative embodiment of the fastening system of FIGS. 1 and 2.
Dans le mode de réalisation des figures 1 et 2, comme on l'a expliqué, ni le déflecteur, ni le bol du système d'injection ne peuvent être entraînés vers l'arrière du turboréacteur en cas de rupture des brasures parce qu'ils sont retenus mécaniquement. Toutefois, si une sollicitation est exercée sur le système d'injection en sens inverse, c'est-à-dire dans le sens opposé à celui de la flèche 56 de la figure 1, l'effort sera repris par les cordons de soudure qui peuvent alors céder. Une sollicitation de ce type peut se produire au moment où l'on place les injecteurs sur la traversée coulissante parce qu'il peut y avoir un arcboutement des injecteurs. Les efforts subis par les points de soudure dans une telle situation pourraient éventuellement provoquer leur rupture. Dans ce cas, le bol serait désolidarisé du fond de chambre 22. Cette situation présenterait moins d'inconvénients que la situation inverse dans laquelle le bol pourrait être entraîné vers l'arrière du turboréacteur parce que le système d'injection serait maintenu par les injecteurs et la pression. Toutefois, afin d'éviter cet inconvénient, on a prévu un mode de réalisation de l'invention représenté sur les figures 3 et 4 dans lequel le système d'injection, et particulièrement le bol faisant partie du système d'injection, est retenu mécaniquement dans les deux sens sans qu'aucun effort ne soit exercé sur les cordons de soudures.In the embodiment of FIGS. 1 and 2, as explained, 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. However, if a bias is exerted on the injection system in the opposite direction, that is to say in the opposite direction to that of the
Dans ce mode de réalisation, la forme du déflecteur 20 est identique. En revanche la constitution de la bague de retenue diffère. La bague de retenue 60 est constituée d'une bague intérieure 62 et d'une bague de fermeture 64. La bague intérieure peut être fendue comme dans le mode de réalisation précédent ou bien elle peut être constituée de deux demi bagues. Elle comporte, comme précédemment, un rebord 52 qui vient se loger dans la gorge 40 du déflecteur et en outre un second rebord 66 qui vient immobiliser une collerette 44 située à l'extrémité de la partie cylindrique 38 du bol. La collerette 44 est ainsi immobilisée dans les deux sens. Vers l'arrière du turboréacteur, elle est immobilisée comme précédemment par le chant 42 de la partie annulaire du déflecteur 20. Dans l'autre sens, c'est-à-dire vers l'avant du turboréacteur, elle est immobilisée par le second rebord 66 de la bague intérieure 62. La bague de fermeture 64 cercle la bague intérieure 62 de manière à empêcher la bague fendue ou les deux demi bagues de s'écarter. Des cordons de soudure 54 solidarisent la bague de fermeture 64 et la bague intérieure 62. Toutefois, dans ce mode de réalisation, contrairement au précédent les cordons de soudure 54 ne supportent aucune charge mécanique. L'arrêt en translation du système d'injection, dans les deux sens étant assuré exclusivement par les rebords 52 et 66. Cependant, comme on peut le voir sur la figure 4, il est nécessaire de prévoir des moyens anti-rotation. En effet, dans le mode de réalisation des figures 1 et 2, la fonction d'anti-rotation est assurée par les points de soudure 54 eux mêmes, ce qui n'est plus le cas dans le présent mode de réalisation. C'est pourquoi (figure 4), le déflecteur comporte un ergot 70, de section par exemple sensiblement rectangulaire, qui vient se loger dans une encoche correspondante 72 de même forme et de même section formée dans la collerette 44 du bol 10. On assure ainsi l'immobilisation en rotation du bol par rapport au déflecteur qui est lui-même brasé sur la paroi de fond comme on l'a exposé précédemment.In this embodiment, the shape of the
On a représenté sur la figure 5 un troisième mode de réalisation de l'invention qui combine les caractéristiques du premier mode et du second mode de réalisation des figures 1 et 2 d'une part et 3 et 4 d'autre part. Dans ce mode de réalisation, le déflecteur 20 est fixé sur le fond de chambre 22 à la fois par brasage et mécaniquement au moyen d'une bague fendue brasée 150 comportant un rebord 152 qui pénètre dans une gorge circulaire 140 formée dans la partie annulaire 32 du déflecteur 20. Cette réalisation est similaire au mode de réalisation des figures 1 et 2. Par ailleurs, la partie annulaire du déflecteur comporte une seconde gorge circulaire 158 destinée à recevoir l'un des rebords d'une bague de retenue 160. Comme on l'a décrit précédemment en référence aux figures 3 et 4, la bague de retenue est constituée d'une bague intérieure 162 et d'une bague de fermeture 164 qui cercle la bague intérieure 162.FIG. 5 shows a third embodiment of the invention which combines the characteristics of the first mode and the second embodiment of FIGS. 1 and 2 on the one hand and 3 and 4 on the other hand. In this embodiment, the
Comme précédemment, la bague intérieure 162 peut être constituée par une bague fendue ou par deux demi bagues. La bague intérieure comporte un premier rebord 166 et un second rebord 168. La bague intérieure présente des portées coniques permettant la suppression des jeux axiaux. Les efforts axiaux qui tendent à ouvrir la bague fendue ou les deux demies bagues sont repris par la bague de fermeture 164. Des cordons de soudure 154 assurent une liaison entre la bague intérieure 162 et la bague de fermeture 164. Ces cordons de soudure ne sont pas sollicités mécaniquement.As before, the
Ce mode de réalisation fonctionne également si les portées ne sont pas coniques. Il subsiste alors un léger jeu axial dû aux tolérances de fabrication.This embodiment also works if the staves are not tapered. There then remains a slight axial play due to manufacturing tolerances.
Claims (13)
Applications Claiming Priority (2)
Application Number | Priority Date | Filing Date | Title |
---|---|---|---|
FR0551518A FR2886714B1 (en) | 2005-06-07 | 2005-06-07 | ANTI-ROTARY INJECTION SYSTEM FOR TURBO-REACTOR |
FR0552929A FR2886715B1 (en) | 2005-06-07 | 2005-09-28 | SYSTEM FOR FASTENING AN INJECTION SYSTEM ON A TURBOREACTOR COMBUSTION CHAMBER BOTTOM AND METHOD OF FASTENING |
Publications (3)
Publication Number | Publication Date |
---|---|
EP1731839A2 true EP1731839A2 (en) | 2006-12-13 |
EP1731839A3 EP1731839A3 (en) | 2013-05-08 |
EP1731839B1 EP1731839B1 (en) | 2015-08-05 |
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ID=36972884
Family Applications (1)
Application Number | Title | Priority Date | Filing Date |
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EP06115000.9A Active EP1731839B1 (en) | 2005-06-07 | 2006-06-06 | System for fixing an injection system to the dome of turbine combustion chamber and method of fixation |
Country Status (5)
Country | Link |
---|---|
US (1) | US7673460B2 (en) |
EP (1) | EP1731839B1 (en) |
JP (1) | JP4875928B2 (en) |
CA (1) | CA2548869C (en) |
RU (1) | RU2406935C2 (en) |
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EP2040001A2 (en) * | 2007-09-21 | 2009-03-25 | Snecma | Annular combustion chamber for a gas turbine engine |
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WO2012025682A2 (en) | 2010-08-27 | 2012-03-01 | Snecma | Combustion chamber for an aircraft engine, and method for attaching an injection system in a combustion chamber of an aircraft engine |
FR3026827A1 (en) * | 2014-10-01 | 2016-04-08 | Snecma | TURBOMACHINE COMBUSTION CHAMBER |
EP2012062B1 (en) * | 2007-07-04 | 2019-08-28 | Safran Aircraft Engines | Combustion chamber comprising deflectors for thermal protection of the chamber dome and gas turbine engine equipped with same |
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FR2903169B1 (en) * | 2006-06-29 | 2011-11-11 | Snecma | DEVICE FOR INJECTING A MIXTURE OF AIR AND FUEL, COMBUSTION CHAMBER AND TURBOMACHINE HAVING SUCH A DEVICE |
FR2910115B1 (en) * | 2006-12-19 | 2012-11-16 | Snecma | DEFLECTOR FOR BOTTOM OF COMBUSTION CHAMBER, COMBUSTION CHAMBER WHERE IT IS EQUIPPED AND TURBOREACTOR COMPRISING THEM |
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FR2932251B1 (en) * | 2008-06-10 | 2011-09-16 | Snecma | COMBUSTION CHAMBER FOR A GAS TURBINE ENGINE COMPRISING CMC DEFLECTORS |
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FR2963061B1 (en) * | 2010-07-26 | 2012-07-27 | Snecma | FUEL INJECTION SYSTEM FOR TURBO-REACTOR AND METHOD FOR ASSEMBLING SUCH AN INJECTION SYSTEM |
FR2971038B1 (en) * | 2011-01-31 | 2013-02-08 | Snecma | INJECTION DEVICE FOR A TURBOMACHINE COMBUSTION CHAMBER |
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GB2543803B (en) * | 2015-10-29 | 2019-10-30 | Rolls Royce Plc | A combustion chamber assembly |
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EP2012062B1 (en) * | 2007-07-04 | 2019-08-28 | Safran Aircraft Engines | Combustion chamber comprising deflectors for thermal protection of the chamber dome and gas turbine engine equipped with same |
EP2040001A2 (en) * | 2007-09-21 | 2009-03-25 | Snecma | Annular combustion chamber for a gas turbine engine |
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Also Published As
Publication number | Publication date |
---|---|
RU2006119912A (en) | 2007-12-20 |
CA2548869C (en) | 2014-05-20 |
EP1731839B1 (en) | 2015-08-05 |
JP4875928B2 (en) | 2012-02-15 |
RU2406935C2 (en) | 2010-12-20 |
JP2006343092A (en) | 2006-12-21 |
CA2548869A1 (en) | 2006-12-07 |
US7673460B2 (en) | 2010-03-09 |
EP1731839A3 (en) | 2013-05-08 |
US20070084215A1 (en) | 2007-04-19 |
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