EP0506516A1 - Combustion air control device for turbomachine combustor - Google Patents

Combustion air control device for turbomachine combustor Download PDF

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Publication number
EP0506516A1
EP0506516A1 EP92400715A EP92400715A EP0506516A1 EP 0506516 A1 EP0506516 A1 EP 0506516A1 EP 92400715 A EP92400715 A EP 92400715A EP 92400715 A EP92400715 A EP 92400715A EP 0506516 A1 EP0506516 A1 EP 0506516A1
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EP
European Patent Office
Prior art keywords
combustion chamber
sleeve
enclosure
combustion
wall
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
Application number
EP92400715A
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German (de)
French (fr)
Other versions
EP0506516B1 (en
Inventor
Gérard Yves Georges Barbier
Xavier Marie Henri Bardey
Michel André Albert Desaulty
Serge Marcel Meunier
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
SNECMA SAS
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Publication of EP0506516A1 publication Critical patent/EP0506516A1/en
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    • 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
    • F23R3/045—Air inlet arrangements using pipes
    • 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
    • F23R3/06—Arrangement of apertures along the flame tube
    • 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

Definitions

  • FR-A-2 028 599 describes several variants of devices for adjusting the oxidant flow.
  • the invention relates to a device for adjusting the oxidant flow rate which is both simple and precise.
  • the subject of the invention is therefore a combustion chamber of a turbo-machine comprising: a combustion chamber, which is delimited by a wall and inside which combustion of a fuel is carried out; a peripheral enclosure, which surrounds said combustion enclosure and which is capable of containing an oxidizer under pressure; and, a plurality of oxidant intake orifices which pass through said wall and which are capable of establishing communication between the peripheral enclosure and the combustion enclosure.
  • At least one of said oxidant intake orifices is associated with a sleeve; which passes through it and is adjusted to it; which commnicates with the peripheral enclosure by an inlet opening device and with the combustion enclosure by a delivery opening device, the inside of the sleeve providing mutual communication between said inlet opening devices and repression; and which has a pivot axis about which it is pivotally mounted; however, that at least one of said inlet and outlet opening devices is asymmetrical with respect to said pivot axis.
  • the main advantage of the invention lies in the modulation of the distribution of the air flow in the different orifices of the flame tube, depending on the speed, by means of mobile elements which is the solution offering the most potential gains. on the different performances. It makes it possible to adjust the richness and the residence time in the primary zone according to the thermodynamic conditions, in order to be placed as close as possible to the optimal operating point.
  • the combustion chamber of FIG. 1 is of the annular type, of axis 1, and comprises an internal wall 2 and an external wall 3, which define between them the combustion chamber 4, as well as a casing 5, inside which said combustion chamber 4 is contained, this casing 5 being itself delimited by an internal envelope 6 and by an external envelope 7 .
  • the combustion chamber 4 is provided, at one of its ends, with a fuel injection device 8 combined with a device 9 for admitting primary oxidizer, and comprises, at its other end , an orifice 10 for discharging the burnt gases.
  • the casing 5 also contains, during the operation of the combustion chamber, a compressed oxidizer, such as compressed air, coming from a source of compressed oxidizer symbolized by the arrow F, generally constituted by an air compressor. .
  • orifices 11 for additional oxidant intake, connecting the casing 5 to the combustion chamber 4, orifices 11 for admission of secondary oxidant and / or dilution.
  • Other orifices 12 also establish communication between the casing 5 and the combustion chamber 4 and will more particularly be described below.
  • the orifice 12 in FIGS. 2 and 3 crosses the external wall 3 which has an opening 13 for this purpose.
  • a cylindrical duct 14 has a first transverse end shaped as a flange 15 perpendicular to the axis 16 of said duct 14, comprising an opening 26, and a second transverse end, contained in a plane P inclined relative to the axis 16 of the casing 14 and therefore comprising, seen in section, a sort of spout 17, and an opening 36.
  • a plate 18, forming a support washer, is screwed (19) to the outside face of the internal wall 3 and has an orifice 20.
  • a tubular section 21 has its internal wall 22 adjusted and made integral with the external face 23 of the cylindrical conduit 14; has its outer wall 24 rotatably mounted inside the orifice 20 of the plate 18; and is provided with a transverse flange 25, perpendicular to the axis 16 of the cylindrical conduit 14.
  • Figures 4 and 5 is similar to that of Figures 2 and 3 except the following feature: the cylindrical duct 14 is extended, beyond the flange 15, outside of the combustion chamber 4, by a section 27, the end of which constitutes a bottom 28 for closing off this section, and the cylindrical wall of which is crossed by an orifice 29 for communication of the casing 5 with the interior 12 of the section 27 and of the conduit 14.
  • the compressed oxidizer is admitted into the casing 5 according to a flow of direction L (substantially parallel to the direction H of gas flow inside the combustion chamber 4) and passes through the orifice 12 of the duct 14, either according to the arrow M (FIG. 4), on the one hand, by penetrating inside the orifice 12, passing directly through the orifice 29 located, like the spout 17, upstream from the axis 16 relative to the direction H of gas flow, on the other hand, arriving inside the combustion chamber 4 substantially in the same direction as direction H, ie according to arrow N (FIG. 5), on the one hand , bypassing the wall of the section 27 to penetrate inside the orifice 12 by crossing the orifice?
  • the spout 17 may be on the side opposite to the orifice 29.
  • a jacket for adjusting the flow rate passing through the orifice 12 may be provided.
  • the tubular section 21 extends beyond the plate 18 to near an external transverse rim 31 extending the bottom 28 of the section 27.
  • the tubular section 21 has an orifice 32 permanently disposed opposite the orifice 29 of the tubular section 27.
  • the jacket 30 has an orifice 33 which can be arranged opposite the orifices 29 and 32. This jacket can on the other hand be oriented around the axis 16, by means of a lever 34, which is integral with it and which passes through a lumen 35 formed in the wall of the section 27 and opposite to the orifice 32, and partially, or even completely, block the orifices 32 and 29 in certain embodiments.
  • a device for adjusting the value of the flow rate passing through the orifice 12 which is added to the possibility of orienting the assembly of the duct 14, the tubular section 21 and the jacket 30 around the axis 16.
  • the realization of figure 6 is c ompatible with the addition of a spout at the internal end of the duct 14, similar to the spout 17 of Figures 2 and 3, and, 4 and 5.
  • the rotation controls of the various cylindrical conduits 14 are advantageously coupled, for example by means of individual rack and pinion systems, to a single motor device for adjusting the rotations of all the conduits 14 simultaneously.
  • a single motor device for adjusting the orientations of all the liners 30 of the embodiment according to FIG. 6 is simultaneously coupled to the various levers 34 for adjusting the orientation of said liners and allows simultaneous adjustments of the oxidant flow rates passing through. the holes 12.
  • FIGS. 2 and 3 makes it possible to modify the direction of introduction (arrows J or K) of the oxidizer admitted into the combustion chamber 4 relative to the direction H of general flow of gases inside said combustion chamber 4.
  • the transit time of the oxidizer is therefore adjustable by this means, this adjustment being useful to enable satisfactory operation to be obtained at very different gaits, previously almost incompatible, such as those of operations at full load and in slow motion.
  • the gradient for adjusting the transit time of the gases inside the combustion chamber 4 is increased compared to that obtained with the embodiment of FIGS. 2 and 3.
  • FIG. 6 also makes it possible to adjust the value at the flow rate of oxidant admitted into the combustion chamber 4. It is recalled that this solution is moreover compatible with those providing for a spout 17 (FIGS. 2 to 5) to the internal end of the cylindrical duct 14.

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  • Engineering & Computer Science (AREA)
  • Chemical & Material Sciences (AREA)
  • Combustion & Propulsion (AREA)
  • Mechanical Engineering (AREA)
  • General Engineering & Computer Science (AREA)
  • Pressure-Spray And Ultrasonic-Wave- Spray Burners (AREA)
  • Exhaust Gas After Treatment (AREA)
  • Fluidized-Bed Combustion And Resonant Combustion (AREA)

Abstract

The invention relates to a combustion chamber of a turbo machine comprising: a combustion enclosure (4) delimited by a wall (3); a peripheral enclosure (5) surrounding the combustion enclosure (4) and containing a pressurised oxygen carrier; and, a plurality of oxygen carrier inlet orifices (12) passing through the said wall and establishing communication between the peripheral enclosure and the combustion enclosure. <??>According to the invention, at least one of the said orifices (12) is associated with a sleeve (14); which passes through it; which communicates with the peripheral enclosure (5) via an outflow aperture device (36); and which has a pivoting shaft (16) around which it is mounted so as to be steerable; the outflow aperture device (36) being asymmetric with respect to the said pivoting shaft (16). <??>One application is the production of a gas turbine having a large range of operating regimes. <IMAGE>

Description

Les turbo-machines modernes sont conçues pour fonctionner à des régimes très différents entre le ralenti et la pleine charge. Il est apparu nécessaire de régler le débit de comburant admis dans la chambre de combustion : FR-A-2 028 599 décrit plusieurs variantes de dispositifs de réglage du débit de comburant.Modern turbo-machines are designed to operate at very different speeds between idle and full load. It appeared necessary to regulate the flow of oxidant admitted into the combustion chamber: FR-A-2 028 599 describes several variants of devices for adjusting the oxidant flow.

L'invention est relative à un dispositif de réglage du débit de comburant qui est à la fois simple et précis.The invention relates to a device for adjusting the oxidant flow rate which is both simple and precise.

L'invention a donc pour objet une chambre de combustion de turbo-machine comportant : une enceinte de combustion, qui est délimitée par une paroi et à l'intérieur de laquelle est réalisée la combustion d'un carburant ; une enceinte périphérique, qui entoure ladite enceinte de combustion et qui est susceptible de contenir un comburant sous pression ; et, une pluralité d'orifices d'admission de comburant, qui traversent ladite paroi et qui sont susceptibles d'établir la communication entre l'enceinte périphérique et l'enceinte de combustion.The subject of the invention is therefore a combustion chamber of a turbo-machine comprising: a combustion chamber, which is delimited by a wall and inside which combustion of a fuel is carried out; a peripheral enclosure, which surrounds said combustion enclosure and which is capable of containing an oxidizer under pressure; and, a plurality of oxidant intake orifices which pass through said wall and which are capable of establishing communication between the peripheral enclosure and the combustion enclosure.

Selon l'invention, au moins l'un desdits orifices d'admission de comburant est associé à un manchon ; qui le traverse et y est ajusté ; qui commnique avec l'enceinte périphérique par un dispositif d'ouvertures d'admission et avec l'enceinte de combustion par un dispositif d'ouvertures de refoulement, l'intérieur du manchon réalisant la communication mutuelle desdits dispositifs d'ouvertures d'admission et refoulement ; et qui possède un axe de pivotement autour duquel il est monté orientable ; cependant que l'un au moins desdits dispositifs d'ouvertures d'admission et de refoulement est dissymétrique par rapport audit axe de pivotement.According to the invention, at least one of said oxidant intake orifices is associated with a sleeve; which passes through it and is adjusted to it; which commnicates with the peripheral enclosure by an inlet opening device and with the combustion enclosure by a delivery opening device, the inside of the sleeve providing mutual communication between said inlet opening devices and repression; and which has a pivot axis about which it is pivotally mounted; however, that at least one of said inlet and outlet opening devices is asymmetrical with respect to said pivot axis.

Les avantageuses dispositions suivantes sont en outre de préférence adoptées :

  • le dispositif d'ouvertures de refoulement du manchon comporte une coupe dudit manchon par un plan incliné par rapport audit axe de pivotement ;
  • le dispositif d'ouvertures d'admission du manchon comporte un orifice traversant la paroi du manchon, non symétrique par rapport audit axe de pivotement ;
  • le dispositif d'ouvertures d'admission comporte un volet réglable susceptible de former diaphragme ;
  • la chambre de combustion comporte plusieurs manchons munis d'orifices d'admission de comburant, cependant que chaque manchon est attelé à un organe de réglage de son pivotement et que les divers organes de réglage de pivotement desdits manchons sont reliés à un dispositif unique de commande.
The following advantageous arrangements are also preferably adopted:
  • the device for discharging openings of the sleeve comprises a section of said sleeve by a plane inclined with respect to said pivot axis;
  • the sleeve inlet opening device has an orifice passing through the wall of the sleeve, which is not symmetrical with respect to to said pivot axis;
  • the intake opening device comprises an adjustable flap capable of forming a diaphragm;
  • the combustion chamber comprises several sleeves provided with oxidant inlet orifices, while each sleeve is coupled to a member for adjusting its pivoting and that the various pivoting adjusting members for said sleeves are connected to a single control device .

L'avantage principal de l'invention réside dans la modulation de la répartition du débit d'air dans les différents orifices du tube à flamme, en fonction du régime, au moyen d'éléments mobiles qui est la solution offrant le plus de gains potentiels sur les différentes performances. Elle permet en effet d'ajuster la richesse et le temps de séjour en zone primaire en fonction des conditions thermodynamiques, afin de se placer le plus près possible du point de fonctionnement optimal.The main advantage of the invention lies in the modulation of the distribution of the air flow in the different orifices of the flame tube, depending on the speed, by means of mobile elements which is the solution offering the most potential gains. on the different performances. It makes it possible to adjust the richness and the residence time in the primary zone according to the thermodynamic conditions, in order to be placed as close as possible to the optimal operating point.

L'invention sera mieux comprise, et des caractéristiques secondaires et leurs avantages apparaîtront au cours de la description de réalisations donnée ci-dessous à titre d'exemple.The invention will be better understood, and secondary characteristics and their advantages will appear during the description of embodiments given below by way of example.

Il est entendu que la description et les dessins ne sont donnés qu'à titre indicatif et non limitatifIt is understood that the description and the drawings are given for information only and are not limitative

Il sera fait référence aux dessins annexés dans lesquels :

  • la figure 1 est une coupe axiale d'une chambre de combustion conforme à l'invention ;
  • les figures 2 et 3 sont des coupes axiales agrandies du détail A de la figure 1, représenté dans deux configurations distinctes ;
  • les figures 4 et 5 sont des coupes axiales analogues à celles des figures 2 et 3, d'une autre réalisation conforme à l'invention, également représentée dans deux configurations distinctes de fonctionnement, respectivement ; et
  • la figure 6 est une coupe axiale, analogue à celle de la figure 2, d'une troisième réalisation conforme à l'invention.
Reference will be made to the appended drawings in which:
  • Figure 1 is an axial section of a combustion chamber according to the invention;
  • Figures 2 and 3 are enlarged axial sections of detail A of Figure 1, shown in two separate configurations;
  • Figures 4 and 5 are axial sections similar to those of Figures 2 and 3, of another embodiment according to the invention, also shown in two separate operating configurations, respectively; and
  • Figure 6 is an axial section, similar to that of Figure 2, of a third embodiment according to the invention.

La chambre de combustion de la figure 1 est du type annulaire, d'axe 1, et comprend une paroi interne 2 et une paroi externe 3, qui définissent entre elles l'enceinte de combustion 4, ainsi qu'un carter 5, à l'intérieur duquel est contenue ladite enceinte de combustion 4, ce carter 5 étant lui-même délimité par une enveloppe interne 6 et par une enveloppe externe 7.The combustion chamber of FIG. 1 is of the annular type, of axis 1, and comprises an internal wall 2 and an external wall 3, which define between them the combustion chamber 4, as well as a casing 5, inside which said combustion chamber 4 is contained, this casing 5 being itself delimited by an internal envelope 6 and by an external envelope 7 .

De manière classique, l'enceinte de combustion 4 est munie, à l'une de ses extrémités, d'un dispositif d'injection de carburant 8 combiné à un dispositif 9 d'admission de comburant primaire, et comporte, à son autre extrémité, un orifice 10 d'évacuation des gaz brûlés. Le carter 5 contient en outre, pendant le fonctionnement de la chambre de combustion, un comburant comprimé, tel que de l'air comprimé, provenant d'une source de comburant comprimé symbolisée par la flèche F, généralement constituée par un compresseur d'air.Conventionally, the combustion chamber 4 is provided, at one of its ends, with a fuel injection device 8 combined with a device 9 for admitting primary oxidizer, and comprises, at its other end , an orifice 10 for discharging the burnt gases. The casing 5 also contains, during the operation of the combustion chamber, a compressed oxidizer, such as compressed air, coming from a source of compressed oxidizer symbolized by the arrow F, generally constituted by an air compressor. .

Les parois interne 2 et externe 3 sont traversées par des orifices 11 d'admission complémentaire de comburant, reliant le carter 5 à l'enceinte de combustion 4, orifices 11 d'admission de comburant secondaire et/ou de dilution. D'autres orifices 12 établissent également une communication entre le carter 5 et l'enceinte de combustion 4 et vont plus particulièrement être décrits ci-après.The internal 2 and external 3 walls are traversed by orifices 11 for additional oxidant intake, connecting the casing 5 to the combustion chamber 4, orifices 11 for admission of secondary oxidant and / or dilution. Other orifices 12 also establish communication between the casing 5 and the combustion chamber 4 and will more particularly be described below.

L'orifice 12 des figures 2 et 3 traverse la paroi externe 3 qui présente à cet effet une ouverture 13.The orifice 12 in FIGS. 2 and 3 crosses the external wall 3 which has an opening 13 for this purpose.

Un conduit cylindrique 14 présente une première extrémité transversale conformée en une bride 15 perpendiculaire à l'axe 16 dudit conduit 14, comportant une ouverture 26, et une deuxième extrémité transversale, contenue dans un plan P incliné par rapport à l'axe 16 du carter 14 et comportant donc, vue en coupe, une sorte de bec 17, et une ouverture 36. Une plaque 18, formant rondelle d'appui, est vissée (19) sur la face extérieure de la paroi interne 3 et comporte un orifice 20. Un tronçon tubulaire 21 a sa paroi interne 22 ajustée et rendue solidaire de la face externe 23 du conduit cylindrique 14 ; a sa paroi externe 24 montée rotative à l'intérieur de l'orifice 20 de la plaque 18 ; et est munie d'une bride transversale 25, perpendiculaire à l'axe 16 du conduit cylindrique 14.A cylindrical duct 14 has a first transverse end shaped as a flange 15 perpendicular to the axis 16 of said duct 14, comprising an opening 26, and a second transverse end, contained in a plane P inclined relative to the axis 16 of the casing 14 and therefore comprising, seen in section, a sort of spout 17, and an opening 36. A plate 18, forming a support washer, is screwed (19) to the outside face of the internal wall 3 and has an orifice 20. A tubular section 21 has its internal wall 22 adjusted and made integral with the external face 23 of the cylindrical conduit 14; has its outer wall 24 rotatably mounted inside the orifice 20 of the plate 18; and is provided with a transverse flange 25, perpendicular to the axis 16 of the cylindrical conduit 14.

Après assemblage, l'ensemble du conduit cylindrique 14 et du tronçon tubulaire 21 est monté rotatif, pratiquement sans jeu, par rapport à l'orifice 20 de la plaque 18, c'est-à-dire, aussi, par rapport à la paroi externe 3 ; et, la lisière de l'ouverture 13 de ladite paroi externe 3 sont disposées entre la plaque 18 et la bride 25 du tronçon tubulaire 21, pratiquement sans jeu. Ainsi, le conduit cylindrique 14, et son bec interne 17, sont orientables autour de l'axe 16.After assembly, all of the cylindrical conduit 14 and the tubular section 21 is rotatably mounted, practically without play, relative to the orifice 20 of the plate 18, that is to say, also, relative to the outer wall 3; and, the edge of the opening 13 of said external wall 3 are disposed between the plate 18 and the flange 25 of the tubular section 21, practically without play. Thus, the cylindrical conduit 14, and its internal spout 17, are orientable around axis 16.

Lorsque le bec 17 est situé en amont de l'axe 16 par rapport au sens d'écoulement H des gaz à l'intérieur de l'enceinte de combustion 4, le comburant comprimé traverse l'orifice 12 suivant la flèche J et parvient dans l'enceinte de combustion 4 sensiblement dans le même sens que la flèche H (figure 2).When the nozzle 17 is located upstream of the axis 16 with respect to the direction of flow H of the gases inside the combustion chamber 4, the compressed oxidizer passes through the orifice 12 along the arrow J and arrives in the combustion chamber 4 substantially in the same direction as the arrow H (Figure 2).

Au contraire, lorsque le bec 17 est situé en aval de l'axe 16 par rapport au sens d'écoulement H des gaz, le comburant comprimé traverse l'orifice 12 en parvenant à l'intérieur de l'enceinte de combustion 4 suivant la flèche K, sensiblement à contrecourant par rapport au sens de la flèche H (figure 3).On the contrary, when the spout 17 is located downstream from the axis 16 with respect to the direction of flow H of the gases, the compressed oxidizer passes through the orifice 12 arriving inside the combustion chamber 4 according to the arrow K, substantially counter-current with respect to the direction of arrow H (FIG. 3).

La réalisation des figures 4 et 5 est semblable à celle des figures 2 et 3 sauf la particularité suivante : le conduit cylindrique 14 est prolongé, au-delà de la bride 15, à l'extérieur de l'enceinte de combustion 4, par un tronçon 27, dont l'extrémité constitue un fond 28 d'obturation de ce tronçon, et dont la paroi cylindrique est traversée par un orifice 29 de communication du carter 5 avec l'intérieur 12 du tronçon 27 et du conduit 14.The embodiment of Figures 4 and 5 is similar to that of Figures 2 and 3 except the following feature: the cylindrical duct 14 is extended, beyond the flange 15, outside of the combustion chamber 4, by a section 27, the end of which constitutes a bottom 28 for closing off this section, and the cylindrical wall of which is crossed by an orifice 29 for communication of the casing 5 with the interior 12 of the section 27 and of the conduit 14.

Le comburant comprimé est admis dans le carter 5 selon un flux de sens L (sensiblement parallèle au sens H d'écoulement des gaz à l'intérieur de l'enceinte de combustion 4) et traverse l'orifice 12 du conduit 14, soit selon la flèche M (figure 4), d'une part, en pénétrant, à l'intérieur de l'orifice 12, en traversant directement l'orifice 29 situé, comme le bec 17, en amont de l'axe 16 par rapport au sens H d'écoulement des gaz, d'autre part, en parvenant à l'intérieur de l'enceinte de combustion 4 sensiblement dans le même sens que le sens H, soit selon la flèche N (figure 5), d'une part, en contournant la paroi du tronçon 27 pour pénétrer à l'intérieur de l'orifice 12 en traversant l'orifice ?9, disposé cette fois en aval de l'axe 16 par rapport au sens d'écoulement H, d'autre part, en pénétrant à l'intérieur de l'enceinte de combustion 4 à contrecourant du sens H.
En variante à cette réalisation, le bec 17 peut se trouver du côté opposé à l'orifice 29.The compressed oxidizer is admitted into the casing 5 according to a flow of direction L (substantially parallel to the direction H of gas flow inside the combustion chamber 4) and passes through the orifice 12 of the duct 14, either according to the arrow M (FIG. 4), on the one hand, by penetrating inside the orifice 12, passing directly through the orifice 29 located, like the spout 17, upstream from the axis 16 relative to the direction H of gas flow, on the other hand, arriving inside the combustion chamber 4 substantially in the same direction as direction H, ie according to arrow N (FIG. 5), on the one hand , bypassing the wall of the section 27 to penetrate inside the orifice 12 by crossing the orifice? 9, arranged this time downstream of the axis 16 with respect to the direction of flow H, on the other hand, by penetrating inside the combustion chamber 4 against the direction of direction H.
As a variant to this embodiment, the spout 17 may be on the side opposite to the orifice 29.

Enfin, dans le cadre d'une réalisation analogue à celle des figures 4 et 5, avec ou sans bec 17, une chemise de réglage du débit traversant l'orifice 12 peut-être prévue. La réalisation de la figure 6, analogue à celle de la figure 4 mais exempte de bec 17, comporte une telle chemise.Finally, in the context of an embodiment similar to that of FIGS. 4 and 5, with or without spout 17, a jacket for adjusting the flow rate passing through the orifice 12 may be provided. The embodiment of Figure 6, similar to that of Figure 4 but free of spout 17, includes such a jacket.

Dans cette réalisation, le tronçon tubulaire 21 se prolonge au-delà de la plaque 18 jusqu'à proximité d'un rebord transversal externe 31 prolongeant la fond 28 du tronçon 27. Le tronçon tubulaire 21 comporte un orifice 32 disposé en permanence en regard de l'orifice 29 du tronçon tubulaire 27. La chemise 30 a un orifice 33 qui peut être disposé en regard des orifices 29 et 32. Cette chemise peut par contre être orientée autour de l'axe 16, au moyen d'un levier 34, qui en est solidaire et qui traverse une lumière 35 ménagée dans la paroi du tronçon 27 et opposée à l'orifice 32, et obturer partiellement, voire totalement, dans certaines réalisations, les orifices 32 et 29. Ainsi est réalisé un dispositif de réglage de la valeur du débit traversant l'orifice 12, qui vient s'ajouter à la possibilité d'orientation de l'ensemble du conduit 14, du tronçon tubulaire 21 et de la chemise 30 autour de l'axe 16. Comme déjà indiqué, la réalisation de la figure 6 est compatible avec l'adjonction d'un bec à l'extrémité interne du conduit 14, analogue au bec 17 des figures 2 et 3, et, 4 et 5.In this embodiment, the tubular section 21 extends beyond the plate 18 to near an external transverse rim 31 extending the bottom 28 of the section 27. The tubular section 21 has an orifice 32 permanently disposed opposite the orifice 29 of the tubular section 27. The jacket 30 has an orifice 33 which can be arranged opposite the orifices 29 and 32. This jacket can on the other hand be oriented around the axis 16, by means of a lever 34, which is integral with it and which passes through a lumen 35 formed in the wall of the section 27 and opposite to the orifice 32, and partially, or even completely, block the orifices 32 and 29 in certain embodiments. Thus, a device for adjusting the the value of the flow rate passing through the orifice 12, which is added to the possibility of orienting the assembly of the duct 14, the tubular section 21 and the jacket 30 around the axis 16. As already indicated, the realization of figure 6 is c ompatible with the addition of a spout at the internal end of the duct 14, similar to the spout 17 of Figures 2 and 3, and, 4 and 5.

Il va également de soi que les commandes de rotation des divers conduits cylindriques 14 sont avantageusement attelées, par exemple au moyen de systèmes individuels à pignons-crémaillères, à un dispositif moteur unique de réglage des rotations de tous les conduits 14 simultanément. De manière analogue, un dispositif moteur unique de réglage des orientations de toutes les chemises 30 de la réalisation conforme à la figure 6 simultanément est attelé aux divers leviers 34 de réglage d'orientation desdites chemises et permet les réglages simultanés des débits de comburant traversant les orifices 12.It also goes without saying that the rotation controls of the various cylindrical conduits 14 are advantageously coupled, for example by means of individual rack and pinion systems, to a single motor device for adjusting the rotations of all the conduits 14 simultaneously. Similarly, a single motor device for adjusting the orientations of all the liners 30 of the embodiment according to FIG. 6 is simultaneously coupled to the various levers 34 for adjusting the orientation of said liners and allows simultaneous adjustments of the oxidant flow rates passing through. the holes 12.

La réalisation représentée selon les figures 2 et 3 permet de modifier le sens de l'introduction (flèches J ou K) du comburant admis dans l'enceinte de combustion 4 par rapport au sens H d'écoulement général des gaz à l'intérieur de ladite enceinte de combustion 4. La durée du transit du comburant est donc réglable par ce moyen, ce réglage étant utile pour permettre l'obtention de fonctionnement satisfaisante à des allures très différentes, auparavant presque incompatibles, telles que celles des fonctionnements à pleine charge et au ralenti.The embodiment shown in FIGS. 2 and 3 makes it possible to modify the direction of introduction (arrows J or K) of the oxidizer admitted into the combustion chamber 4 relative to the direction H of general flow of gases inside said combustion chamber 4. The transit time of the oxidizer is therefore adjustable by this means, this adjustment being useful to enable satisfactory operation to be obtained at very different gaits, previously almost incompatible, such as those of operations at full load and in slow motion.

La réalisation représentée sur les figures 4 et 5 bénéficie déjà du même mode de réglage que la précédente. En outre, la dissymétrie de la position de l'orifice 29 par rapport à l'axe 16 permet soit de bénéficier (figure 4) de l'énergie cinétique du flux du comburant admis dans le carter 5 selon le sens L, et d'admettre dans l'enceinte de combustion 4 le comburant suivant la flèche M, d'une part parallèle au sens H, d'autre part sous une pression relativement importante, somme de la pression statique du comburant et de la transformation en pression de son énergie cinétique, soit (figure 5) de ne pas bénéficier de l'énergie cinétique du comburant admis dans le carter 5, et en outre d'admettre le comburant dans l'enceinte de combustion 4 suivant le sens de la flèche N sensiblement opposé à celui de la flèche H.The embodiment shown in Figures 4 and 5 already benefits from the same mode of adjustment as the previous one. In addition, the asymmetry of the position of the orifice 29 with respect to the axis 16 makes it possible either to benefit (FIG. 4) from the kinetic energy of the flow of oxidant admitted into the casing 5 in the direction L, and admit the oxidizer into combustion chamber 4 according to arrow M, on the one hand parallel to the direction H, on the other hand under a relatively high pressure, sum of the static pressure of the oxidant and the transformation into pressure of its energy kinetic, or (Figure 5) not to benefit from the kinetic energy of the oxidant admitted into the casing 5, and further to admit the oxidant into the combustion chamber 4 in the direction of the arrow N substantially opposite to that of arrow H.

Le gradient de réglage de la durée du transit des gaz à l'intérieur de l'enceinte de combustion 4 est accru par rapport à celui obtenu avec la réalisation des figures 2 et 3.The gradient for adjusting the transit time of the gases inside the combustion chamber 4 is increased compared to that obtained with the embodiment of FIGS. 2 and 3.

La réalisation de la figure 6 permet en outre le réglage de la valeur au débit de comburant admis dans l'enceinte de combustion 4. Il est rappelé que cette solution est par ailleurs compatible avec celles prévoyant un bec 17 (figures 2 à 5) à l'extrémité interne du conduit cylindrique 14.The embodiment of FIG. 6 also makes it possible to adjust the value at the flow rate of oxidant admitted into the combustion chamber 4. It is recalled that this solution is moreover compatible with those providing for a spout 17 (FIGS. 2 to 5) to the internal end of the cylindrical duct 14.

L'invention n'est pas limitée aux réalisations décrites, mais en couvre au contraire toutes les variantes qui pourraient leur être apportées sans sortir de leur cadre, ni de leur esprit.The invention is not limited to the embodiments described, but on the contrary covers all the variants which could be made to them without departing from their scope or their spirit.

Claims (5)

Chambre de combustion de turbo-machine comportant : - une enceinte de combustion (4), qui est délimitée par une paroi (2-3) et à l'intérieur de laquelle est réalisée la combustion d'un carburant ; - une enceinte périphérique (5), qui entoure ladite enceinte de combustion (4) et qui est susceptible de contenir un comburant sous pression ; et, - une pluralité d'orifices (12) d'admission de comburant, qui traversent ladite paroi et qui sont susceptibles d'établir la communication entre l'enceinte périphérique (5) et l'enceinte de combustion (4) ; caractérisée en ce qu'au moins l'un desdits orifices (12) d'admission de comburant est associé à un manchon (14) ; qui le traverse et y est ajusté ; qui communique avec l'enceinte périphérique (5) par un dispositif d'ouvertures d'admission (26 ; 29) et avec l'enceinte de combustion (4) par un dispositif d'ouvertures de refoulement (36), l'intérieur (12) du manchon réalisant la communication mutuelle desdits dispositifs d'ouvertures d'admission et refoulement ; et qui possède un axe de pivotement (16) autour duquel il est monté orientable ; cependant que l'un au moins desdits dispositifs d'ouvertures d'admission et de refoulement est dissymétrique par rapport audit axe de pivotement (16).Turbo-machine combustion chamber comprising: - a combustion chamber (4), which is delimited by a wall (2-3) and inside which the combustion of a fuel is carried out; - A peripheral enclosure (5), which surrounds said combustion enclosure (4) and which is capable of containing an oxidizer under pressure; and, - A plurality of orifices (12) for admitting oxidizer, which pass through said wall and which are capable of establishing communication between the peripheral enclosure (5) and the combustion enclosure (4); characterized in that at least one of said oxidant inlet orifices (12) is associated with a sleeve (14); which passes through it and is adjusted to it; which communicates with the peripheral enclosure (5) by an intake opening device (26; 29) and with the combustion enclosure (4) by a discharge opening device (36), the interior ( 12) of the sleeve carrying out the mutual communication of said inlet and outlet opening devices; and which has a pivot axis (16) around which it is pivotally mounted; however, that at least one of said inlet and outlet opening devices is asymmetrical with respect to said pivot axis (16). Chambre de combustion selon la revendication 1, caractérisée en ce que le dispositif d'ouvertures de refoulement du manchon (14) comporte une coupe (36) dudit manchon par un plan (P) incliné par rapport audit axe de pivotement (16).Combustion chamber according to claim 1, characterized in that the sleeve opening device (14) comprises a section (36) of said sleeve by a plane (P) inclined relative to said pivot axis (16). Chambre de combustion selon l'une quelconque ds revendications 1 et 2, caractérisée en ce que le dispositif d'ouvertures d'admission du manchon comporte un orifice (29) traversant la paroi du manchon (14), non symétrique par rapport audit axe de pivotement (16).Combustion chamber according to either of Claims 1 and 2, characterized in that the device for the inlet openings of the sleeve has an orifice (29) passing through the wall of the sleeve (14), which is not symmetrical with respect to said axis of pivot (16). Chambre de combustion selon l'une quelconque des revendications 1 à 3, caractérisée en ce que le dispositif d'ouvertures d'admission comporte un volet réglable (30) susceptible de former diaphragme.Combustion chamber according to any one of Claims 1 to 3, characterized in that the intake opening device comprises an adjustable flap (30) likely to form a diaphragm. Chambre de combustion selon l'une quelconque des revendications 1 à 4, caractérisée en ce qu'elle comporte plusieurs manchons (14) munis d'orifices d'admission de comburant cependant que chaque manchon est attelé à un organe de réglage de son pivotement et que les divers organes de réglage de pivotement desdits manchons sont reliés à un dispositif unique de commande.Combustion chamber according to any one of Claims 1 to 4, characterized in that it comprises several sleeves (14) provided with oxidant inlet orifices, however each sleeve is coupled to a member for adjusting its pivoting and that the various pivoting adjustment members of said sleeves are connected to a single control device.
EP92400715A 1991-03-20 1992-03-18 Combustion air control device for turbomachine combustor Expired - Lifetime EP0506516B1 (en)

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FR9103374 1991-03-20
FR9103374A FR2674317B1 (en) 1991-03-20 1991-03-20 COMBUSTION CHAMBER OF A TURBOMACHINE COMPRISING AN ADJUSTMENT OF THE FUEL FLOW.

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EP0506516B1 EP0506516B1 (en) 1994-11-30

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EP (1) EP0506516B1 (en)
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DE69200735D1 (en) 1995-01-12
FR2674317B1 (en) 1993-05-28
EP0506516B1 (en) 1994-11-30
FR2674317A1 (en) 1992-09-25
US5235805A (en) 1993-08-17
DE69200735T2 (en) 1995-04-27

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