EP3084308B1 - Combustion chamber in a turbomachine - Google Patents
Combustion chamber in a turbomachine Download PDFInfo
- Publication number
- EP3084308B1 EP3084308B1 EP14828233.8A EP14828233A EP3084308B1 EP 3084308 B1 EP3084308 B1 EP 3084308B1 EP 14828233 A EP14828233 A EP 14828233A EP 3084308 B1 EP3084308 B1 EP 3084308B1
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- EP
- European Patent Office
- Prior art keywords
- internal
- external
- revolution
- annular
- radial
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- 238000002485 combustion reaction Methods 0.000 title claims description 30
- 238000011144 upstream manufacturing Methods 0.000 claims description 35
- 239000000446 fuel Substances 0.000 claims description 12
- 230000014759 maintenance of location Effects 0.000 claims description 11
- 238000012423 maintenance Methods 0.000 description 4
- 230000002349 favourable effect Effects 0.000 description 3
- 238000002347 injection Methods 0.000 description 3
- 239000007924 injection Substances 0.000 description 3
- 238000000034 method Methods 0.000 description 3
- 238000003466 welding Methods 0.000 description 3
- 238000005219 brazing Methods 0.000 description 2
- 238000006073 displacement reaction Methods 0.000 description 2
- 238000005520 cutting process Methods 0.000 description 1
- 238000005304 joining Methods 0.000 description 1
- 238000004519 manufacturing process Methods 0.000 description 1
- 238000012986 modification Methods 0.000 description 1
- 230000004048 modification Effects 0.000 description 1
- 239000000243 solution Substances 0.000 description 1
- 238000005507 spraying Methods 0.000 description 1
Images
Classifications
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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
- F23R3/28—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
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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
- F23R3/002—Wall structures
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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
- F23R3/06—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
- F23R3/42—Continuous combustion chambers using liquid or gaseous fuel characterised by the arrangement or form of the flame tubes or combustion chambers
- F23R3/50—Combustion chambers comprising an annular flame tube within an annular casing
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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
- F23R3/42—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
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- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F05—INDEXING SCHEMES RELATING TO ENGINES OR PUMPS IN VARIOUS SUBCLASSES OF CLASSES F01-F04
- F05D—INDEXING SCHEME FOR ASPECTS RELATING TO NON-POSITIVE-DISPLACEMENT MACHINES OR ENGINES, GAS-TURBINES OR JET-PROPULSION PLANTS
- F05D2260/00—Function
- F05D2260/30—Retaining components in desired mutual position
-
- 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
- F23R2900/00—Special features of, or arrangements for continuous combustion chambers; Combustion processes therefor
- F23R2900/00005—Preventing fatigue failures or reducing mechanical stress in gas turbine components
-
- 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
- F23R2900/00—Special features of, or arrangements for continuous combustion chambers; Combustion processes therefor
- F23R2900/00012—Details of sealing devices
Definitions
- the present invention relates to an annular turbomachine combustion chamber and a turbomachine equipped with an annular combustion chamber.
- annular combustion chamber comprises two inner and outer coaxial revolution walls, connected to each other upstream by an annular so-called bottom wall wall having fuel injector head through openings. between the walls of internal and external revolution.
- Each injector is engaged in centering means which are movable radially in support means integral with support means.
- the centering means of each injector are formed by a centering ring in which is engaged an injector and having a radial annular flange extending radially outward and slidably mounted in an annular groove means of support.
- the annular groove of the support means allows a radial displacement of the centering ring housing the injector to compensate for manufacturing tolerances as well as differential expansions in operation.
- the annular groove of radial displacement of the ring is defined by retaining means axially upstream and downstream of the radial annular flange of the centering ring.
- the axially downstream retaining means are formed by a downstream radial wall of an annular sheath fixed on the annular chamber bottom, the radial wall being connected to a cylindrical rim extending upstream and on which is attached by welding or brazing a washer attached to the cylindrical rim.
- This washer is therefore fixed releasably on the support means.
- this washer In case it is necessary to replace everything or part of the centering means of an injector during a maintenance operation, it is necessary to destroy this washer, which is a delicate operation because the sleeve which is fixed on the annular wall of the chamber bottom must not be damaged . Furthermore, it has been found breaks welding seams, which is not permissible, and does not ensure a perfect mechanical integrity of the fuel injection systems.
- the invention aims in particular to provide a simple, effective and economical solution to the problems of the prior art described above.
- the axial retaining means upstream of the centering means are fixed on at least one of the internal and external walls of revolution of the combustion chamber and no longer on the support means, which allows quick and easy assembly and disassembly axial upstream retaining means for carrying out maintenance operations.
- the removable attachment can be made for example by bolting using the fasteners used to integrally assemble an annular chamber bottom and the inner and outer walls of revolution, which is simple to implement.
- the annular ring will advantageously comprise a plurality of rings regularly spaced circumferentially from each other and delimiting said orifices of passages of the injectors.
- the crown thus comprises free spaces between the rings avoiding a significant increase in the mass of the axial retaining means upstream of the centering means.
- At least some of the rings of the crown are connected to at least one lug extending radially inwards or outwards whose end opposite the ring is connected to a flange. extending axially, preferably downstream, and serving for attachment to the internal or external revolution wall, respectively.
- the crown comprises a unitary pattern whose successive repetition circumferentially forms the annular ring.
- the pattern comprises a ring connected to two inner and outer radial tabs, the inner radial tab being internally connected to an inner flange extending downstream and fixed on the inner wall of revolution and the outer radial tab. being connected externally to an outer rim extending downstream and fixed on the outer wall of revolution.
- the pattern comprises at least three rings whose circumferential end rings of the pattern are connected to at least one radial tab carrying at its end opposite the ring a flange extending downstream and fixed on the inner or outer wall of revolution, the ring or rings circumferentially interposed between the two rings of circumferential ends of the pattern being connected to said end rings by circumferential arms.
- the rings of circumferential ends of the pattern are each connected to two inner and outer radial tabs, the inner radial tab being internally connected to an inner flange extending downstream and fixed on the inner wall of revolution and the tab outer radial being externally connected to an outer flange extending downstream and fixed to the outer wall of revolution.
- the annular ring may be a one-piece piece or comprise a plurality of crown portions which are juxtaposed circumferentially.
- the use of several crown portions, although requiring several independent assembly operations, may make it possible to have to change only one crown portion rather than the entire crown during a maintenance operation.
- the support means comprise axial retaining means downstream of the centering means, said support means being fixed on an annular chamber bottom.
- the upstream axial retaining means are fixed on the inner and outer walls of revolution by means of the same fasteners of said internal and external walls of revolution to an annular chamber bottom, which makes it possible to use pre-existing fixing zones and avoids the modifications of the walls of internal and external revolution.
- the fasteners are for example bolts which provide a more robust link means of axial retention upstream with respect to welds as in the prior art.
- the invention also relates to a turbomachine, such as a turbojet or a turboprop, comprising a combustion chamber as described above.
- the invention also relates to an axial retaining member of the fuel injector centering means in an annular turbomachine combustion chamber according to claim 11.
- FIG. 1 represents the upstream part of a combustion chamber 10 in a turbomachine according to the known technique comprising two walls of internal revolution 12 and external 14 extending around the axis 16 of the combustion chamber and fixed at their upstream ends on an annular chamber bottom 18 extending between the walls of internal revolution 12 and external 14 and traversed by fuel injectors 19.
- the annular chamber bottom 18 comprises a radial annular wall 20 connected at its outer periphery to an outer cylindrical rim 22 extending upstream and fixed by bolting elements 24 on the upstream end of the outer wall of revolution 14
- the radial wall 20 of the annular chamber bottom 18 is connected at its inner periphery to an internal cylindrical rim 26 extending upstream and fixed by bolting elements 28 to the upstream end of the internal wall of revolution 12 .
- the upstream end of the outer wall of revolution 14 is arranged radially between the end external downstream 34 of the fairing 30 and the external cylindrical rim 22 of the annular chamber bottom 18.
- the upstream end of the inner wall of revolution 12 is arranged radially between the inner downstream end 32 of the fairing 30 and the inner cylindrical rim 26 of the annular chamber bottom 18.
- the annular chamber bottom 18 comprises a plurality of openings for the passage of the injector heads 19 for the spraying of fuel between the walls of internal revolution 12 and external 14 and downstream of the chamber bottom 18.
- Each injector 19 is engaged axially in centering means 36 of the injector 19, which centering means 36 are freely movable in the radial direction in support means 38 integral with the annular chamber bottom 18.
- each injector 19 comprise a radial annular wall 40 fixed on the inner periphery and facing upstream of the passage opening of an injector 19.
- the radial annular wall 40 also comprises a cylindrical flange 42 extending upstream.
- a plate 44 or washer is fixed by welding or brazing its outer periphery on the upstream end of the cylindrical rim 42 of the sheath.
- each injector 19 comprise a cylindrical ring 46 traversed axially by the head and comprising an annular flange 48 extending radially outwards and mounted to slide radially in the groove delimited upstream by the washer 44, downstream. by the radial annular wall 40. The bottom of the groove is delimited by the cylindrical rim 42.
- the weld seams of the washers 44 holding upstream centering means can be weakened and are thus likely to break in operation, which impacts the injection of fuel between the walls of internal revolution 12 and external 14.
- the invention overcomes this problem by removably fixing the axial retaining means on at least one of the inner wall 12 and outer wall 14 so as to facilitate the dismounting of the removable fastening means.
- the axial retaining means comprise an annular ring 50 whose inner periphery is fixed on the internal wall of revolution 12 and whose outer periphery is fixed on the outer wall of revolution 14.
- the ring 50 may be a one-piece piece comprising a plurality of rings 52 each formed of a radial annular wall forming a passage opening 53 of an injector 19 intended to come axially opposite an annular flange 48 of a centering ring 36 of an injector 19 so as to form an axial stop upstream of said annular collar 48.
- Each ring 52 is connected to two tabs, one of which extends radially inwards and the other 56 extends radially outwards.
- the radially outer ends of the outer tabs 56 are connected to an outer cylindrical rim 58 extending axially downstream.
- the radially inner ends of the inner tabs 54 are connected to an inner cylindrical rim 60 extending axially downstream.
- the annular ring 50 is thus formed of a plurality of unitary patterns repeating successively in the circumferential direction and integral with each other. Each pattern is then formed of a ring 52, two inner radial tabs 54 and outer 56 and inner cylindrical rim portions 62 and outer 64.
- Each inner cylindrical rim 60 and outer 58 comprises orifices 66 for the passage of a fixing screw, these orifices 66 being regularly distributed around the axis 16 of the combustion chamber.
- Each pattern thus comprises two orifices 66 whose centers are aligned with the center of the ring 50 and located in the same radial plane containing the axis 16 of the combustion chamber.
- the outer cylindrical rim 58 of the ring 50 is attached to the outer cylindrical rim 22 of the chamber bottom 18 and is fixed to the outer wall of revolution 14 by means of the fixing screws 24.
- the internal cylindrical rim 60 of the ring 50 is attached to the inner cylindrical rim 26 of the chamber bottom 18 and is fixed to the upstream end of the internal wall of revolution 12 by means of the fixing screws 28.
- the assembly and disassembly of the crown 50 are thus simple and easy to perform when a maintenance operation is necessary.
- the double internal and external fixation of the ring 50 on the inner and outer walls 12 of revolution 14 ensures good mechanical strength to the crown and ensures its integrity in operation.
- a ring 68 In a second embodiment of a ring 68 according to the invention, it is formed of a plurality of independent patterns 70 juxtaposed circumferentially to form the annular ring 68.
- Each portion of internal cylindrical rim 72 or outer 74 of a pattern at its circumferential ends which are arranged with clearance vis-a-vis the circumferential ends of the inner cylindrical rim portions 72 or outer 74, respectively, adjacent patterns.
- the figure 5 represents a third embodiment of an annular ring 76 according to the invention, formed of a circumferential repetition of a plurality of H-shaped patterns 78 integral with each other and each comprising three rings 80, 82 successive.
- Each pattern 78 thus comprises two circumferential end rings 82, each connected to two tabs extending radially inward 84 and outward 86.
- the outer radial tabs 86 of the circumferential end rings 82 of each pattern 78 are connected to an outer cylindrical rim 88 extending downstream and the inner radial lugs 84 of the circumferential end rings 82 of each pattern 78 are connected to an inner cylindrical rim 90 extending downstream.
- Ring 80 of each pattern 78 which is interspaced circumferentially between two circumferential end rings 82 is devoid of radial tabs and is connected to the circumferential end rings 82 by circumferential joining arms 92.
- the figure 6 represents a fourth embodiment of an annular ring 94 according to the invention, formed of a circumferential repetition of several units 96 independent of each other and juxtaposed circumferentially without contact.
- Each pattern 96 includes an inner cylindrical rim portion 98 and an outer cylindrical rim portion 100 for attachment of each pattern 96 to the internal and external 12 and outer revolution walls 14.
- the crown may comprise only one cylindrical fixing flange on one of the walls of internal or external revolution.
- this type of embodiment is less reliable than those shown in the figures of fact of the double internal and external fixation of the annular ring.
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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)
Description
La présente invention concerne une chambre annulaire de combustion de turbomachine ainsi qu'une turbomachine équipée d'une chambre annulaire de combustion.The present invention relates to an annular turbomachine combustion chamber and a turbomachine equipped with an annular combustion chamber.
De manière connue, une chambre annulaire de combustion comprend deux parois de révolution coaxiales interne et externe, reliées l'une à l'autre en amont par une paroi annulaire dite de fond de chambre comportant des ouvertures de passage de tête d'injecteurs de carburant entre les parois de révolution interne et externe. Chaque injecteur est engagé dans des moyens de centrage qui sont déplaçables en direction radiale dans des moyens de support solidaires de moyens de support.In known manner, an annular combustion chamber comprises two inner and outer coaxial revolution walls, connected to each other upstream by an annular so-called bottom wall wall having fuel injector head through openings. between the walls of internal and external revolution. Each injector is engaged in centering means which are movable radially in support means integral with support means.
Dans la technique actuelle, les moyens de centrage de chaque injecteur sont formés par une bague de centrage dans laquelle est engagé un injecteur et comportant une collerette annulaire radiale s'étendant radialement vers l'extérieur et montée à coulissement dans une gorge annulaire des moyens de support.In the current technique, the centering means of each injector are formed by a centering ring in which is engaged an injector and having a radial annular flange extending radially outward and slidably mounted in an annular groove means of support.
La gorge annulaire des moyens de support permet un déplacement radial de la bague de centrage logeant l'injecteur afin de compenser les tolérances de fabrication ainsi que les dilatations différentielles en fonctionnement.The annular groove of the support means allows a radial displacement of the centering ring housing the injector to compensate for manufacturing tolerances as well as differential expansions in operation.
La gorge annulaire de déplacement radial de la bague est définie par des moyens de retenue axialement vers l'amont et vers l'aval de la collerette annulaire radiale de la bague de centrage. En pratique, les moyens de retenue axialement vers l'aval sont formés par une paroi radiale aval d'un fourreau annulaire fixé sur le fond de chambre annulaire, la paroi radiale étant reliée à un rebord cylindrique s'étendant vers l'amont et sur lequel est fixé par soudage ou brasure une rondelle rapportée sur le rebord cylindrique.The annular groove of radial displacement of the ring is defined by retaining means axially upstream and downstream of the radial annular flange of the centering ring. In practice, the axially downstream retaining means are formed by a downstream radial wall of an annular sheath fixed on the annular chamber bottom, the radial wall being connected to a cylindrical rim extending upstream and on which is attached by welding or brazing a washer attached to the cylindrical rim.
Cette rondelle est donc fixée de manière indémontable sur les moyens de support. Dans le cas où il est nécessaire de remplacer tout ou
partie des moyens de centrage d'un injecteur lors d'une opération de maintenance, on est amené à détruire cette rondelle, ce qui constitue une opération délicate car le fourreau qui est fixé sur la paroi annulaire de fond de chambre ne doit pas être endommagé. Par ailleurs, on a constaté des ruptures des cordons de soudure, ce qui n'est pas admissible, et ne permet pas de garantir une intégrité mécanique parfaite des systèmes d'injection de carburant.This washer is therefore fixed releasably on the support means. In case it is necessary to replace everything or
part of the centering means of an injector during a maintenance operation, it is necessary to destroy this washer, which is a delicate operation because the sleeve which is fixed on the annular wall of the chamber bottom must not be damaged . Furthermore, it has been found breaks welding seams, which is not permissible, and does not ensure a perfect mechanical integrity of the fuel injection systems.
Il est notamment connu les chambres de combustion décrites dans le document
L'invention a notamment pour but d'apporter une solution simple, efficace et économique aux problèmes de l'art antérieur décrit précédemment.The invention aims in particular to provide a simple, effective and economical solution to the problems of the prior art described above.
A cet effet, elle propose une chambre annulaire de combustion dans une turbomachine selon la revendication 1.For this purpose, it proposes an annular combustion chamber in a turbomachine according to claim 1.
Selon l'invention, les moyens de retenue axiale vers l'amont des moyens de centrage sont fixés sur au moins l'une des parois de révolution interne et externe de la chambre de combustion et non plus sur les moyens de support, ce qui permet un montage et un démontage simple et rapide
des moyens de retenue axiale amont pour réaliser des opérations de maintenance.According to the invention, the axial retaining means upstream of the centering means are fixed on at least one of the internal and external walls of revolution of the combustion chamber and no longer on the support means, which allows quick and easy assembly and disassembly
axial upstream retaining means for carrying out maintenance operations.
La fixation amovible peut être réalisée par exemple par boulonnage en utilisant les éléments de fixation utilisés pour assembler solidairement un fond de chambre annulaire et les parois de révolution interne et externe, ce qui simple à mettre en oeuvre.The removable attachment can be made for example by bolting using the fasteners used to integrally assemble an annular chamber bottom and the inner and outer walls of revolution, which is simple to implement.
Dans ce dernier cas, seules les longueurs des vis de fixation des éléments de boulonnage doivent être légèrement augmentées pour réaliser la fixation.In the latter case, only the lengths of the fastening screws of the bolting elements must be slightly increased to achieve the fastening.
Selon une autre caractéristique, la couronne annulaire comprendra favorablement une pluralité d'anneaux régulièrement espacés circonférentiellement les uns des autres et délimitant lesdits orifices de passages des injecteurs.According to another characteristic, the annular ring will advantageously comprise a plurality of rings regularly spaced circumferentially from each other and delimiting said orifices of passages of the injectors.
Dans cette réalisation particulière, la couronne comprend ainsi des espaces libres entre les anneaux évitant une augmentation importante de la masse des moyens de retenus axiale vers l'amont des moyens de centrage.In this particular embodiment, the crown thus comprises free spaces between the rings avoiding a significant increase in the mass of the axial retaining means upstream of the centering means.
Selon encore une autre caractéristique favorable, au moins certains des anneaux de la couronne sont reliés à au moins une patte s'étendant radialement vers l'intérieur ou vers l'extérieur dont l'extrémité opposée à l'anneau est reliée à un rebord s'étendant axialement, de préférence vers l'aval, et servant à la fixation sur la paroi de révolution interne ou externe, respectivement.According to yet another favorable characteristic, at least some of the rings of the crown are connected to at least one lug extending radially inwards or outwards whose end opposite the ring is connected to a flange. extending axially, preferably downstream, and serving for attachment to the internal or external revolution wall, respectively.
Avantageusement, la couronne comprend un motif unitaire dont la répétition successive circonférentiellement forme la couronne annulaire.Advantageously, the crown comprises a unitary pattern whose successive repetition circumferentially forms the annular ring.
Dans une première variante, le motif comprend un anneau relié à deux pattes radiales interne et externe, la patte radiale interne étant reliée intérieurement à un rebord interne s'étendant vers l'aval et fixé sur la paroi de révolution interne et la patte radiale externe étant reliée extérieurement à un rebord externe s'étendant vers l'aval et fixé sur la paroi de révolution externe.In a first variant, the pattern comprises a ring connected to two inner and outer radial tabs, the inner radial tab being internally connected to an inner flange extending downstream and fixed on the inner wall of revolution and the outer radial tab. being connected externally to an outer rim extending downstream and fixed on the outer wall of revolution.
Dans une deuxième variante, le motif comprend au moins trois anneaux dont les anneaux d'extrémités circonférentielles du motif sont reliés à au moins une patte radiale portant à son extrémité opposée à l'anneau un rebord s'étendant vers l'aval et fixé sur la paroi de révolution interne ou externe, le ou les anneaux intercalés circonférentiellement entre les deux anneaux d'extrémités circonférentielles du motif étant reliés audits anneaux d'extrémités par des bras circonférentiels.In a second variant, the pattern comprises at least three rings whose circumferential end rings of the pattern are connected to at least one radial tab carrying at its end opposite the ring a flange extending downstream and fixed on the inner or outer wall of revolution, the ring or rings circumferentially interposed between the two rings of circumferential ends of the pattern being connected to said end rings by circumferential arms.
Préférentiellement, les anneaux d'extrémités circonférentielles du motif sont chacun reliés à deux pattes radiales interne et externe, la patte radiale interne étant reliée intérieurement à un rebord interne s'étendant vers l'aval et fixé sur la paroi de révolution interne et la patte radiale externe étant reliée extérieurement à un rebord externe s'étendant vers l'aval et fixé sur la paroi de révolution externe.Preferably, the rings of circumferential ends of the pattern are each connected to two inner and outer radial tabs, the inner radial tab being internally connected to an inner flange extending downstream and fixed on the inner wall of revolution and the tab outer radial being externally connected to an outer flange extending downstream and fixed to the outer wall of revolution.
La couronne annulaire peut être une pièce monobloc ou comprendre une pluralité de portions de couronne qui sont juxtaposées circonférentiellement. L'utilisation de plusieurs portions de couronne, bien que nécessitant plusieurs opérations de montage indépendantes, peut permettre de n'avoir à changer qu'une seule portions de couronne plutôt que toute la couronne lors d'une opération de maintenance.The annular ring may be a one-piece piece or comprise a plurality of crown portions which are juxtaposed circumferentially. The use of several crown portions, although requiring several independent assembly operations, may make it possible to have to change only one crown portion rather than the entire crown during a maintenance operation.
Selon une autre caractéristique favorable, les moyens de support comprennent des moyens de retenue axiale vers l'aval des moyens de centrage, lesdits moyens de support étant fixés sur un fond de chambre annulaire.According to another favorable feature, the support means comprise axial retaining means downstream of the centering means, said support means being fixed on an annular chamber bottom.
Selon encore une autre caractéristique favorable, les moyens de retenue axiale vers l'amont sont fixés sur la ou lesdites parois de révolution interne et externe au moyen des mêmes organes de fixation desdites parois de révolution interne et externe à un fond de chambre annulaire, ce qui permet d'utiliser des zones de fixation préexistantes et évite les modifications des parois de révolution interne et externe.According to yet another favorable characteristic, the upstream axial retaining means are fixed on the inner and outer walls of revolution by means of the same fasteners of said internal and external walls of revolution to an annular chamber bottom, which makes it possible to use pre-existing fixing zones and avoids the modifications of the walls of internal and external revolution.
Les organes de fixation sont par exemple des boulons qui offrent une liaison plus robuste des moyens de retenues axiale vers l'amont par rapport à des soudures comme dans l'art antérieur.The fasteners are for example bolts which provide a more robust link means of axial retention upstream with respect to welds as in the prior art.
L'invention concerne également une turbomachine, telle qu'un turboréacteur ou un turbopropulseur, comprenant une chambre de combustion telle que décrite précédemment.The invention also relates to a turbomachine, such as a turbojet or a turboprop, comprising a combustion chamber as described above.
L'invention concerne encore un organe de retenue axiale des moyens de centrage d'injecteurs de carburant dans une chambre annulaire de combustion de turbomachine selon la revendication 11.The invention also relates to an axial retaining member of the fuel injector centering means in an annular turbomachine combustion chamber according to claim 11.
L'invention sera mieux comprise et d'autres détails, avantages et caractéristiques de l'invention apparaîtront à la lecture de la description suivante faite à titre d'exemple non limitatif, en référence aux dessins annexés dans lesquels :
- la
figure 1 est une vue schématique en coupe axiale de la partie amont d'une chambre de combustion selon la technique antérieure ; - la
figure 2 est une vue schématique en coupe axiale de la partie amont d'une chambre de combustion selon l'invention ; - la
figure 3 est une vue schématique en perspective des moyens de retenue axiale vers l'amont d'une pièce de centrage d'un injecteur selon une première réalisation de l'invention ; - la
figure 4 est une vue schématique en perspective des moyens de retenue axiale vers l'amont d'une pièce de centrage d'un injecteur selon une deuxième réalisation de l'invention ; - la
figure 5 est une vue schématique en perspective des moyens de retenue axiale vers l'amont d'une pièce de centrage d'un injecteur selon une troisième réalisation de l'invention ; - la
figure 6 est une vue schématique en perspective des moyens de retenue axiale vers l'amont d'une pièce de centrage d'un injecteur selon une quatrième réalisation de l'invention.
- the
figure 1 is a schematic view in axial section of the upstream portion of a combustion chamber according to the prior art; - the
figure 2 is a schematic view in axial section of the upstream portion of a combustion chamber according to the invention; - the
figure 3 is a schematic perspective view of the axial retention means upstream of a centering piece of an injector according to a first embodiment of the invention; - the
figure 4 is a schematic perspective view of the axial retention means upstream of a centering piece of an injector according to a second embodiment of the invention; - the
figure 5 is a schematic perspective view of the axial retention means upstream of a centering part of an injector according to a third embodiment of the invention; - the
figure 6 is a schematic perspective view of the axial retention means upstream of a centering piece of an injector according to a fourth embodiment of the invention.
On se réfère tout d'abord à la
Un carénage annulaire 30 ayant une forme incurvée concave vers l'aval selon un plan de coupe contenant l'axe 16 de la chambre de combustion 10, est également traversé par les injecteurs 19 de carburant et ses extrémités aval radialement interne 32 et externe 34 sont fixées par boulonnage sur les rebords cylindrique interne 26 et externe 22 du fond de chambre 18 et sur les extrémités amont des parois de révolution interne 12 et externe 14. L'extrémité amont de la paroi de révolution externe 14 est agencée radialement entre l'extrémité aval externe 34 du carénage 30 et le rebord cylindrique externe 22 du fond de chambre annulaire 18. L'extrémité amont de la paroi de révolution interne 12 est agencée radialement entre l'extrémité aval interne 32 du carénage 30 et le rebord cylindrique interne 26 du fond de chambre annulaire 18.An
Le fond de chambre annulaire 18 comprend une pluralité d'ouvertures de passage des têtes d'injecteurs 19 pour la pulvérisation de carburant entre les parois de révolution interne 12 et externe 14 et en aval du fond de chambre 18.The
Chaque injecteur 19 est engagé axialement dans des moyens de centrage 36 de l'injecteur 19, lesquels moyens de centrage 36 sont librement déplaçable en direction radiale dans des moyens de support 38 solidaires du fond de chambre annulaire 18.Each
Les moyens de support 38 de chaque injecteur 19 comprennent une paroi annulaire radiale 40 fixée sur le pourtour interne et orientée vers l'amont de l'ouverture de passage d'un injecteur 19. La paroi annulaire radiale 40 comprend également un rebord cylindrique 42 s'étendant vers l'amont.The support means 38 of each
Dans la technique antérieure (
Les moyens de centrage de chaque injecteur 19 comprennent une bague cylindrique 46 traversée axialement par la tête et comportant une collerette annulaire 48 s'étendant radialement vers l'extérieur et montée à coulissement radial dans la gorge délimitée en amont par la rondelle 44, en aval par la paroi annulaire radiale 40. Le fond de la gorge est délimité par le rebord cylindrique 42.The centering means of each
Comme expliqué dans ce qui précède, les cordons de soudure des rondelles 44 de tenue des moyens de centrage vers l'amont peuvent être fragilisés et sont ainsi susceptibles de se rompre en fonctionnement, ce qui impacte l'injection de carburant entre les parois de révolution interne 12 et externe 14.As explained above, the weld seams of the
L'invention permet de remédier à ce problème en fixant de manière amovible les moyens de retenue axiale sur au moins l'une de la paroi de révolution interne 12 et externe 14 de manière à faciliter le démontage des moyens de fixation amovible.The invention overcomes this problem by removably fixing the axial retaining means on at least one of the
Dans la configuration de l'invention représentée en
Comme représenté en
Chaque anneau 52 est relié à deux pattes dont l'une 54 s'étend radialement vers l'intérieur et l'autre 56 s'étend radialement vers l'extérieur. Les extrémités radialement externes des pattes externes 56 sont reliées à un rebord cylindrique externe 58 s'étendant axialement vers l'aval. Les extrémités radialement internes des pattes internes 54 sont reliées à un rebord cylindrique interne 60 s'étendant axialement vers l'aval.Each
Dans cette réalisation, la couronne annulaire 50 est ainsi formée d'une pluralité de motifs unitaires se répétant successivement en direction circonférentielle et solidaires les uns des autres. Chaque motif est alors formé d'un anneau 52, de deux pattes radiales interne 54 et externe 56 et de portions de rebords cylindriques interne 62 et externe 64.In this embodiment, the
Chaque rebord cylindrique interne 60 et externe 58 comprend des orifices 66 pour le passage d'une vis de fixation, ces orifices 66 étant régulièrement répartis autour de l'axe 16 de la chambre de combustion. Chaque motif comprend ainsi deux orifices 66 dont les centres sont alignés avec le centre de l'anneau 50 et situés dans un même plan radial contenant l'axe 16 de la chambre de combustion. Ainsi, le rebord cylindrique externe 58 de la couronne 50 est accolé au rebord cylindrique externe 22 du fond de chambre 18 et est fixé à la paroi de révolution externe 14 au moyen des vis de fixation 24. De la même manière, le rebord cylindrique interne 60 de la couronne 50 est accolé au rebord cylindrique interne 26 du fond de chambre 18 et est fixé à l'extrémité amont de la paroi de révolution interne 12 au moyen des vis de fixation 28.Each inner
Le montage et le démontage de la couronne 50 sont ainsi simples et faciles à réaliser lorsqu'une opération de maintenance s'avère nécessaire. De plus, la double fixation interne et externe de la couronne 50 sur les parois de révolution interne 12 et externe 14 assure une bonne tenue mécanique à la couronne et garantit son intégrité en fonctionnement.The assembly and disassembly of the
Dans une seconde réalisation d'une couronne 68 selon l'invention, celle-ci est formée d'une pluralité de motifs 70 indépendants juxtaposés circonférentiellement pour former la couronne annulaire 68. Chaque portion de rebord cylindrique interne 72 ou externe 74 d'un motif a ses extrémités circonférentielles qui sont agencées avec jeu en vis-à-vis des extrémités circonférentielles des portions de rebord cylindriques interne 72 ou externe 74, respectivement, des motifs adjacents.In a second embodiment of a
La
La
Dans d'autres réalisations non représentées, la couronne pourrait ne comprendre qu'un seul rebord cylindrique de fixation sur l'une des parois de révolution interne ou externe. Bien que tout à fait réalisable, ce type de réalisation s'avère moins fiable que celles représentées aux figures de fait de la double fixation interne et externe de la couronne annulaire.In other embodiments not shown, the crown may comprise only one cylindrical fixing flange on one of the walls of internal or external revolution. Although quite feasible, this type of embodiment is less reliable than those shown in the figures of fact of the double internal and external fixation of the annular ring.
Claims (11)
- An annular combustion chamber in a turbine engine, comprising injectors (19) of fuel, means for centring means (36), and two coaxial walls of revolution, one an internal wall (12) and the other an external wall (14), between which emerge the fuel injectors (19) each engaged in the centring means (36) which are moveable in the radial direction in support means (38), the chamber also comprising means (50, 68) of axial retention in the upstream direction of the centring means, with said means (50, 68) of axial retention, in the upstream direction being removably fixed on at least one of the internal (12) and external (14) walls of revolution,
the means of axial retention comprising a radial annular crown (50, 68, 76, 94) radially fixed internally or externally on at least one of the internal (12) and external (14) walls of revolution and comprising an annular row of openings (53) for the passage of the injectors (19), with the edge of each opening (53) being adapted to form an axial stop in the upstream direction of a radial annular collar (48) of the centring means of one of the fuel injectors (19), characterized in that the annular crown (50, 68, 76, 94) comprises a plurality of rings (52) regularly spaced apart circumferentially and delineating said openings for the passage of the injectors. - A combustion chamber according to claim 1, characterized in that at least some of the rings (52) of the annular crown (50, 68, 76, 94) are connected to at least one lug (54, 56, 84, 86) which radially extends inwards or outwards, the end opposite the ring (52) of which is connected to a rim which axially extends and is used for fixing purposes on the internal (12) and external (14) walls of revolution, respectively.
- A combustion chamber according to claim 1 or 2, characterized in that the crown (50, 68, 76, 94) comprises a unitary pattern (70, 76, 96) the successive repeating of which, on the circumference, forms the annular crown (50, 68, 76, 94).
- A combustion chamber according to claim 3, characterized in that the pattern (70, 76, 96) comprises a ring (52) connected to two radial internal (54) and external (56) lugs, with the radial internal lug (54) being internally connected to an internal rim (60, 72) which extends in the downstream direction and is fixed to the internal (12) wall of revolution and the radial external lug (56) being externally connected to an external rim (58, 74) which extends in the downstream direction and is fixed to the external (14) wall of revolution.
- A combustion chamber according to claim 3, characterized in that the pattern (76, 96) comprises at least three rings (80, 82) among which the circumferential end rings (82) of the pattern (76, 96) are connected to at least one radial lug (84, 86) the end opposite the ring of which is provided with a rim (88, 90, 98, 100) extending in the downstream direction and fixed on the internal (12) or external (14) wall of revolution, with the rings (80) circumferentially inserted between the two circumferential end rings (82) of the pattern being connected to said circumferential end rings (82) by circumferential arms (92).
- A combustion chamber according to claim 5, characterized in that the circumferential end rings (82) of the pattern are, each, connected to two radial internal (84) and external (86) lugs, with the radial internal lug (84) being internally connected to an internal rim which extends in the downstream direction and is fixed to the internal (12) wall of revolution and the radial external lug (86) being externally connected to an external rim which extends in the downstream direction and is fixed to the external (14) wall of revolution.
- A combustion chamber according to one of the claims 1 to 6, characterized in that the annular crown (50, 68, 76, 94) is a single-piece part or comprises a plurality of crown portions which are circumferentially juxtaposed.
- A combustion chamber according to one of the preceding claims, characterized in that the support means comprise means of axial retention in the downstream direction of the centring means, with said support means being fixed on the bottom of an annular chamber (18).
- A combustion chamber according to one of the preceding claims, characterized in that the means of axial retention in the upstream direction are fixed on said internal and external walls of revolution using the same means for fixing said internal and external walls of revolution to the bottom of an annular chamber.
- A turbine engine such as a turbojet or a turboprop, characterized in that it comprises a combustion chamber according to one of the preceding claims.
- Axial retention element of centring means (36) of fuel injectors in an annular combustion chamber of a turbine engine, comprising a radial annular crown (50, 68, 76, 94) which:- must be internally and/or externally fixed on at least one of the internal (12) or external (14) walls of revolution of the annular combustion chamber of a turbine engine, and- comprises an annular row of openings (53) for the passage of the fuel injectors (19), with the edge of each opening (53) being adapted to form an axial stop in the upstream direction of a radial annular collar (48) of the centring means of one of the injectors (19), characterized in that it comprises a plurality of rings (52, 82) regularly spaced apart circumferentially and delineating said openings for the passage of the injectors and at least some of which are provided with two lugs (54, 56, 84, 86) which extend diametrally opposite one another from the ring (52, 82), with the two lugs (54, 56, 84, 86) each comprising a rim which extends along the axis of the ring (52, 82).
Applications Claiming Priority (2)
Application Number | Priority Date | Filing Date | Title |
---|---|---|---|
FR1363348A FR3015639B1 (en) | 2013-12-20 | 2013-12-20 | COMBUSTION CHAMBER IN A TURBOMACHINE |
PCT/FR2014/053401 WO2015092284A1 (en) | 2013-12-20 | 2014-12-17 | Combustion chamber in a turbomachine |
Publications (2)
Publication Number | Publication Date |
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EP3084308A1 EP3084308A1 (en) | 2016-10-26 |
EP3084308B1 true EP3084308B1 (en) | 2019-09-11 |
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Family Applications (1)
Application Number | Title | Priority Date | Filing Date |
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EP14828233.8A Active EP3084308B1 (en) | 2013-12-20 | 2014-12-17 | Combustion chamber in a turbomachine |
Country Status (4)
Country | Link |
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US (1) | US10458654B2 (en) |
EP (1) | EP3084308B1 (en) |
FR (1) | FR3015639B1 (en) |
WO (1) | WO2015092284A1 (en) |
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Publication number | Priority date | Publication date | Assignee | Title |
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US11131458B2 (en) * | 2018-04-10 | 2021-09-28 | Delavan Inc. | Fuel injectors for turbomachines |
Family Cites Families (19)
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US4454711A (en) * | 1981-10-29 | 1984-06-19 | Avco Corporation | Self-aligning fuel nozzle assembly |
US4686823A (en) * | 1986-04-28 | 1987-08-18 | United Technologies Corporation | Sliding joint for an annular combustor |
DE19515537A1 (en) * | 1995-04-27 | 1996-10-31 | Bmw Rolls Royce Gmbh | Head part of a gas turbine annular combustion chamber |
US6412272B1 (en) * | 1998-12-29 | 2002-07-02 | United Technologies Corporation | Fuel nozzle guide for gas turbine engine and method of assembly/disassembly |
US7121095B2 (en) * | 2003-08-11 | 2006-10-17 | General Electric Company | Combustor dome assembly of a gas turbine engine having improved deflector plates |
US7062920B2 (en) * | 2003-08-11 | 2006-06-20 | General Electric Company | Combustor dome assembly of a gas turbine engine having a free floating swirler |
US7628019B2 (en) * | 2005-03-21 | 2009-12-08 | United Technologies Corporation | Fuel injector bearing plate assembly and swirler assembly |
US7546739B2 (en) * | 2005-07-05 | 2009-06-16 | General Electric Company | Igniter tube and method of assembling same |
FR2897144B1 (en) * | 2006-02-08 | 2008-05-02 | Snecma Sa | COMBUSTION CHAMBER FOR TURBOMACHINE WITH TANGENTIAL SLOTS |
FR2897145B1 (en) * | 2006-02-08 | 2013-01-18 | Snecma | ANNULAR COMBUSTION CHAMBER FOR TURBOMACHINE WITH ALTERNATE FIXINGS. |
US7975487B2 (en) * | 2006-09-21 | 2011-07-12 | Solar Turbines Inc. | Combustor assembly for gas turbine engine |
US7765809B2 (en) * | 2006-11-10 | 2010-08-03 | General Electric Company | Combustor dome and methods of assembling such |
FR2911668B1 (en) * | 2007-01-18 | 2009-03-20 | Snecma Sa | COMBUSTION CHAMBER OF A TURBOMACHINE |
US7926280B2 (en) * | 2007-05-16 | 2011-04-19 | Pratt & Whitney Canada Corp. | Interface between a combustor and fuel nozzle |
DE102011014972A1 (en) * | 2011-03-24 | 2012-09-27 | Rolls-Royce Deutschland Ltd & Co Kg | Combustor head with brackets for seals on burners in gas turbines |
GB201107095D0 (en) * | 2011-04-28 | 2011-06-08 | Rolls Royce Plc | A head part of an annular combustion chamber |
US8745988B2 (en) * | 2011-09-06 | 2014-06-10 | Pratt & Whitney Canada Corp. | Pin fin arrangement for heat shield of gas turbine engine |
US8893382B2 (en) * | 2011-09-30 | 2014-11-25 | General Electric Company | Combustion system and method of assembling the same |
US10378775B2 (en) * | 2012-03-23 | 2019-08-13 | Pratt & Whitney Canada Corp. | Combustor heat shield |
-
2013
- 2013-12-20 FR FR1363348A patent/FR3015639B1/en active Active
-
2014
- 2014-12-17 WO PCT/FR2014/053401 patent/WO2015092284A1/en active Application Filing
- 2014-12-17 US US15/104,835 patent/US10458654B2/en active Active
- 2014-12-17 EP EP14828233.8A patent/EP3084308B1/en active Active
Non-Patent Citations (1)
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None * |
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US20180163965A1 (en) | 2018-06-14 |
FR3015639B1 (en) | 2018-08-31 |
US10458654B2 (en) | 2019-10-29 |
EP3084308A1 (en) | 2016-10-26 |
FR3015639A1 (en) | 2015-06-26 |
WO2015092284A1 (en) | 2015-06-25 |
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