EP1593913B1 - Gas turbine annular combustion chamber with improved inner support flange - Google Patents

Gas turbine annular combustion chamber with improved inner support flange Download PDF

Info

Publication number
EP1593913B1
EP1593913B1 EP05290623.7A EP05290623A EP1593913B1 EP 1593913 B1 EP1593913 B1 EP 1593913B1 EP 05290623 A EP05290623 A EP 05290623A EP 1593913 B1 EP1593913 B1 EP 1593913B1
Authority
EP
European Patent Office
Prior art keywords
combustion chamber
chamber
holes
turbomachine
air
Prior art date
Legal status (The legal status is an assumption and is not a legal conclusion. Google has not performed a legal analysis and makes no representation as to the accuracy of the status listed.)
Active
Application number
EP05290623.7A
Other languages
German (de)
French (fr)
Other versions
EP1593913A1 (en
Inventor
Martine Bes
Didier Hernandez
Gilles Lepretre
Denis Trahot
Current Assignee (The listed assignees may be inaccurate. Google has not performed a legal analysis and makes no representation or warranty as to the accuracy of the list.)
Safran Aircraft Engines SAS
Original Assignee
SNECMA SAS
Priority date (The priority date is an assumption and is not a legal conclusion. Google has not performed a legal analysis and makes no representation as to the accuracy of the date listed.)
Filing date
Publication date
Application filed by SNECMA SAS filed Critical SNECMA SAS
Publication of EP1593913A1 publication Critical patent/EP1593913A1/en
Application granted granted Critical
Publication of EP1593913B1 publication Critical patent/EP1593913B1/en
Active legal-status Critical Current
Anticipated expiration legal-status Critical

Links

Images

Classifications

    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F23—COMBUSTION APPARATUS; COMBUSTION PROCESSES
    • F23R—GENERATING COMBUSTION PRODUCTS OF HIGH PRESSURE OR HIGH VELOCITY, e.g. GAS-TURBINE COMBUSTION CHAMBERS
    • F23R3/00—Continuous combustion chambers using liquid or gaseous fuel
    • F23R3/42—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
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F23—COMBUSTION APPARATUS; COMBUSTION PROCESSES
    • F23R—GENERATING COMBUSTION PRODUCTS OF HIGH PRESSURE OR HIGH VELOCITY, e.g. GAS-TURBINE COMBUSTION CHAMBERS
    • F23R3/00—Continuous combustion chambers using liquid or gaseous fuel
    • F23R3/42—Continuous combustion chambers using liquid or gaseous fuel characterised by the arrangement or form of the flame tubes or combustion chambers
    • F23R3/60—Support structures; Attaching or mounting means

Definitions

  • the present invention relates to the general field of turbomachine combustion chambers. It is particularly interested in the problem posed by the fixing of a turbomachine annular combustion chamber on the casing of the turbomachine.
  • the annular combustion chamber of a turbomachine is formed of inner and outer annular walls connected by a transverse wall forming chamber bottom.
  • the chamber bottom is provided with a plurality of openings in which fuel injectors are mounted.
  • the inner and outer walls of the combustion chamber are generally extended by internal and external, also annular, flanges which are intended to be respectively fixed on inner and outer casings of the casing of the turbomachine. These flanges have the function of maintaining in position the combustion chamber in the casing of the turbomachine.
  • Part of this air is also intended to supply a cooling circuit of the high-pressure turbine of the turbomachine which is disposed downstream of the combustion chamber.
  • a cooling circuit of the high-pressure turbine of the turbomachine which is disposed downstream of the combustion chamber.
  • the internal fixing flange of the combustion chamber is typically pierced with a plurality of holes which allow the passage of compressor air to a cooling circuit of the high-pressure turbine. These holes are usually regularly distributed in a row around the entire circumference of the internal flange.
  • the inner casing of the casing of the turbomachine is also pierced with a plurality of orifices which open into the annular space defined between the inner casing and the internal fixing flange of the chamber and which open towards the circuit of cooling of the high-pressure turbine.
  • the combustion frequencies of the air / fuel mixture in the chamber cause vibrations at the walls of the chamber that propagate to the clamps.
  • the mounting flanges must therefore be sufficiently flexible to dampen these vibrations, but also sufficiently rigid to play their role of maintaining the combustion chamber in position in the housing.
  • the present invention therefore aims to overcome such drawbacks by providing a combustion chamber which has a better mechanical resistance to vibrations generated by the combustion of the air / fuel mixture.
  • annular turbomachine combustion chamber comprising inner and outer annular walls joined by a transverse wall, the inner and outer walls extending at their downstream end by internal and external fixing flanges intended to be respectively fixed on internal and external casings of a casing of the turbomachine for the maintenance in position of the combustion chamber, the inner flange being provided with a plurality of holes for supplying cooling air to a high-pressure turbine of the turbomachine, characterized in that the air supply holes of the internal flange are distributed circumferentially in at least two rows arranged in staggered rows.
  • the particular distribution of the holes of the internal flange on at least two rows arranged staggered has the effect of "breaking" the harmonic vibrations generated by the combustion of the air / fuel mixture. This distribution thus makes it possible to avoid any vibrational resonance, and thus to limit the risks of breaking the internal fixing flange of the chamber.
  • the air supply holes of the inner flange are offset radially relative to the air supply bores made through the inner wall.
  • the radial offset between the holes of the internal flange and the holes in the internal wall of the combustion chamber thus makes it possible to avoid direct radiation of the combustion gases to the inner casing of the casing, which radiation is particularly detrimental to the duration of life of it.
  • the air supply holes of the inner flange are radially offset relative to orifices provided on the inner casing of the casing.
  • this radial offset makes it possible to avoid any direct radiation of the combustion gases from the chamber to the cooling circuit of the high-pressure turbine.
  • the figure 1 illustrates a turbomachine combustion chamber according to the invention.
  • the turbomachine comprises a compression section (not shown) in which air is compressed before being injected into a chamber housing 2, then into a combustion chamber 4 mounted inside thereof.
  • Compressed air is introduced into the combustion chamber and mixed with fuel before being burned.
  • the gases resulting from this combustion are then directed to a high-pressure turbine 6 disposed at the outlet of the combustion chamber 4.
  • the combustion chamber 4 which is of annular type, is formed of an inner annular wall 4a and an outer annular wall 4b which are joined by a transverse wall 4c forming chamber bottom.
  • the inner walls 4a and outer 4b extend along a longitudinal axis X-X slightly inclined relative to the longitudinal axis Y-Y of the turbomachine.
  • the chamber bottom 4c is provided with a plurality of openings 8 in which fuel injectors 10 are mounted.
  • the chamber casing 2 which is formed of an inner casing 2a and an outer casing 2b, furnishes with the combustion chamber 4 an annular space 12 into which compressed air intended for combustion, at the dilution, is admitted. and cooling the chamber.
  • the chamber 4 is divided into a primary zone (or combustion zone) and a secondary zone (or dilution zone) located downstream of the previous one.
  • the air that feeds the primary and secondary zones of the combustion chamber 4 is introduced by one or more rows of holes 14, 16 made respectively in the inner walls 4a and outer 4b of the chamber.
  • the inner and outer walls 4a and 4b of the chamber 4 extend, at their downstream end, respectively by internal and external annular flanges 18 or tongues 18.
  • inner and outer flanges 18 and 18 are intended to be fastened respectively to the inner casings 2a and outer casings 2b of the chamber casing 2 by means of respective bolted connections 22, 24. Their function is to hold the combustion chamber in position. 4 in the chamber housing 2.
  • Compressed air circulating in the annular space 12 is also intended to supply a cooling circuit of the high-pressure turbine 6 of the turbomachine.
  • the internal flange 18 for holding the combustion chamber 4 is provided with air supply holes 26. These holes 26 allow the circulation of air in the annular space 12 downstream of the internal flange 18 .
  • the inner casing 2a of the chamber casing 2 is pierced by air supply orifices 28, for example distributed in a single row, which open into the annular space 12 downstream of the internal flange 18. and open out of the chamber housing 2, to an air injector 30.
  • This air injector 30 is intended to cool the high-pressure turbine 6 of the turbomachine.
  • the air supply holes 26 of the inner flange 18 are distributed circumferentially on at least two rows 26a, 26b arranged in staggered rows.
  • Staggered rows means that the holes in one of the rows 26a, 26b are not aligned with the holes in the other row along the longitudinal axis X-X of the combustion chamber 4.
  • Such an arrangement of the holes according to two rows arranged in a staggered manner makes it possible to "break" the harmonic of the vibrations generated. by the combustion of the air / fuel mixture in the chamber, and thus to prevent the internal flange from breaking under the effect of its vibrations.
  • the air supply holes 26 of the combustion chamber have a circular section. It is possible, however, to envisage another form of section, for example oblong.
  • the holes 26 of the inner flange 18 are distributed in two staggered rows, their individual section can be reduced compared to a conventional arrangement in a single row so as to keep the same general air flow supplying the air. In this way, the distance separating two adjacent holes is increased, which further reduces the possible risks of breaking the internal flange at this point.
  • the air supply holes 26 of the inner flange 18 are radially offset relative to the air supply bores 14 of the inner wall 4a of the combustion chamber 4.
  • the air supply holes 26 of the inner flange 18 are offset radially with respect to the orifices 28 of the inner casing 2a of the chamber casing 2.

Landscapes

  • Engineering & Computer Science (AREA)
  • Chemical & Material Sciences (AREA)
  • Combustion & Propulsion (AREA)
  • Mechanical Engineering (AREA)
  • General Engineering & Computer Science (AREA)
  • Turbine Rotor Nozzle Sealing (AREA)

Description

Arrière-plan de l'inventionBackground of the invention

La présente invention se rapporte au domaine général des chambres de combustion de turbomachine. Elle s'intéresse plus particulièrement au problème posé par la fixation d'une chambre de combustion annulaire de turbomachine sur le carter de la turbomachine.The present invention relates to the general field of turbomachine combustion chambers. It is particularly interested in the problem posed by the fixing of a turbomachine annular combustion chamber on the casing of the turbomachine.

Classiquement, la chambre de combustion annulaire d'une turbomachine est formée de parois annulaires interne et externe reliées par une paroi transversale formant fond de chambre. Le fond de chambre est pourvu d'une pluralité d'ouvertures dans lequel sont montés des injecteurs de carburant.Conventionally, the annular combustion chamber of a turbomachine is formed of inner and outer annular walls connected by a transverse wall forming chamber bottom. The chamber bottom is provided with a plurality of openings in which fuel injectors are mounted.

A leur extrémité aval, les parois interne et externe de la chambre de combustion se prolongent généralement par des brides interne et externe, également annulaires, qui sont destinées à être fixées respectivement sur des enveloppes interne et externe du carter de la turbomachine. Ces brides ont pour fonction de maintenir en position la chambre de combustion dans le carter de la turbomachine.At their downstream end, the inner and outer walls of the combustion chamber are generally extended by internal and external, also annular, flanges which are intended to be respectively fixed on inner and outer casings of the casing of the turbomachine. These flanges have the function of maintaining in position the combustion chamber in the casing of the turbomachine.

De l'air provenant d'un étage de compresseur de la turbomachine disposé en amont de la chambre de combustion circule entre les enveloppes du carter et les parois annulaires de la chambre. Cet air, qui est introduit dans la chambre notamment par des perçages pratiqués au travers des parois de la chambre, participe à la combustion du mélange air/carburant.Air from a compressor stage of the turbomachine disposed upstream of the combustion chamber flows between the casings of the casing and the annular walls of the chamber. This air, which is introduced into the chamber in particular through holes made through the walls of the chamber, participates in the combustion of the air / fuel mixture.

Une partie de cet air est par ailleurs destiné à alimenter un circuit de refroidissement de la turbine haute-pression de la turbomachine qui est disposée en aval de la chambre de combustion. On se référera par exemple à la publication FR 2 841 591 .Part of this air is also intended to supply a cooling circuit of the high-pressure turbine of the turbomachine which is disposed downstream of the combustion chamber. For example, refer to the publication FR 2 841 591 .

Dans ce but, la bride interne de fixation de la chambre de combustion est typiquement percée d'une pluralité de trous qui permettent le passage de l'air de compresseur vers un circuit de refroidissement de la turbine haute-pression. Ces trous sont généralement régulièrement répartis sur une rangée sur toute la circonférence de la bride interne.For this purpose, the internal fixing flange of the combustion chamber is typically pierced with a plurality of holes which allow the passage of compressor air to a cooling circuit of the high-pressure turbine. These holes are usually regularly distributed in a row around the entire circumference of the internal flange.

L'enveloppe interne du carter de la turbomachine est également percée d'une pluralité d'orifices qui s'ouvrent dans l'espace annulaire défini entre l'enveloppe interne et la bride interne de fixation de la chambre et qui débouchent vers le circuit de refroidissement de la turbine haute-pression.The inner casing of the casing of the turbomachine is also pierced with a plurality of orifices which open into the annular space defined between the inner casing and the internal fixing flange of the chamber and which open towards the circuit of cooling of the high-pressure turbine.

Le perçage de trous d'alimentation en air sur la bride interne de fixation de la chambre de combustion pose des problèmes de résistance mécanique aux vibrations engendrées par la combustion du mélange air/carburant dans la chambre.The drilling of air supply holes on the internal flange of the combustion chamber fixation poses problems of mechanical resistance to vibrations generated by the combustion of the air / fuel mixture in the chamber.

En effet, les fréquences de combustion du mélange air/carburant dans la chambre provoquent des vibrations au niveau des parois de la chambre qui se propagent jusqu'aux brides de fixation. Les brides de fixation doivent donc être suffisamment souples pour amortir ces vibrations, mais aussi suffisamment rigides pour jouer leur rôle de maintien en position de la chambre de combustion dans le carter.Indeed, the combustion frequencies of the air / fuel mixture in the chamber cause vibrations at the walls of the chamber that propagate to the clamps. The mounting flanges must therefore be sufficiently flexible to dampen these vibrations, but also sufficiently rigid to play their role of maintaining the combustion chamber in position in the housing.

Or, la présence de trous sur la bride interne de fixation fragilise la résistance mécanique de la bride aux vibrations. Les vibrations au niveau des parois de la chambre, associées à une répartition régulière de des trous de la bride interne, provoquent un phénomène de résonance vibratoire qui entraîne un risque de cassure de la bride interne, notamment entre deux trous adjacents.However, the presence of holes on the internal fixing flange weakens the mechanical strength of the flange vibration. The vibrations at the walls of the chamber, associated with a regular distribution of holes in the internal flange, cause a vibration resonance phenomenon which causes a risk of breaking of the internal flange, especially between two adjacent holes.

Objet et résumé de l'inventionObject and summary of the invention

La présente invention vise donc à pallier de tels inconvénients en proposant une chambre de combustion qui possède une meilleure tenue mécanique aux vibrations engendrées par la combustion du mélange air/carburant.The present invention therefore aims to overcome such drawbacks by providing a combustion chamber which has a better mechanical resistance to vibrations generated by the combustion of the air / fuel mixture.

A cet effet, il est prévu une chambre de combustion annulaire de turbomachine, comportant des parois annulaires interne et externe réunies par une paroi transversale, les parois interne et externe se prolongeant à leur extrémité aval par des brides de fixation interne et externe destinées à être fixées respectivement sur des enveloppes interne et externe d'un carter de la turbomachine pour le maintien en position de la chambre de combustion, la bride interne étant munie d'une pluralité de trous destinés à alimenter en air de refroidissement une turbine haute-pression de la turbomachine, caractérisée en ce que les trous d'alimentation en air de la bride interne sont répartis circonférentiellement sur au moins deux rangées disposées en quinconce.For this purpose, there is provided an annular turbomachine combustion chamber, comprising inner and outer annular walls joined by a transverse wall, the inner and outer walls extending at their downstream end by internal and external fixing flanges intended to be respectively fixed on internal and external casings of a casing of the turbomachine for the maintenance in position of the combustion chamber, the inner flange being provided with a plurality of holes for supplying cooling air to a high-pressure turbine of the turbomachine, characterized in that the air supply holes of the internal flange are distributed circumferentially in at least two rows arranged in staggered rows.

La répartition particulière des trous de la bride interne sur au moins deux rangées disposées en quinconce a pour effet de « casser » l'harmonique des vibrations engendrées par la combustion du mélange air/carburant. Cette répartition permet ainsi d'éviter toute résonance vibratoire, et donc de limiter les risques de cassure de la bride interne de fixation de la chambre.The particular distribution of the holes of the internal flange on at least two rows arranged staggered has the effect of "breaking" the harmonic vibrations generated by the combustion of the air / fuel mixture. This distribution thus makes it possible to avoid any vibrational resonance, and thus to limit the risks of breaking the internal fixing flange of the chamber.

Selon une caractéristique avantageuse de l'invention, les trous d'alimentation en air de la bride interne sont décalés radialement par rapport à des perçages d'alimentation en air pratiqués au travers de la paroi interne.According to an advantageous characteristic of the invention, the air supply holes of the inner flange are offset radially relative to the air supply bores made through the inner wall.

Le décalage radial entre les trous de la bride interne et les perçages de la paroi interne de la chambre de combustion permet ainsi d'éviter un rayonnement direct des gaz de combustion vers l'enveloppe interne du carter, rayonnement qui est particulièrement préjudiciable à la durée de vie de celle-ci.The radial offset between the holes of the internal flange and the holes in the internal wall of the combustion chamber thus makes it possible to avoid direct radiation of the combustion gases to the inner casing of the casing, which radiation is particularly detrimental to the duration of life of it.

Selon une autre caractéristique avantageuse de l'invention, les trous d'alimentation en air de la bride interne sont décalés radialement par rapport à des orifices pratiqués sur l'enveloppe interne du carter.According to another advantageous characteristic of the invention, the air supply holes of the inner flange are radially offset relative to orifices provided on the inner casing of the casing.

Pour la même raison que précédemment, ce décalage radial permet d'éviter tout rayonnement direct des gaz de combustion depuis la chambre vers le circuit de refroidissement de la turbine haute-pression.For the same reason as above, this radial offset makes it possible to avoid any direct radiation of the combustion gases from the chamber to the cooling circuit of the high-pressure turbine.

Brève description des dessinsBrief description of the drawings

D'autres caractéristiques et avantages de la présente invention ressortiront de la description faite ci-dessous, en référence aux dessins annexés qui en illustrent un exemple de réalisation dépourvu de tout caractère limitatif. Sur les figures :

  • la figure 1 est une vue en coupe longitudinale d'une chambre de combustion dans son environnement selon un mode de réalisation de l'invention;
  • la figure 2 est une vue partielle en perspective et en écorché de la figure 1 ; et
  • la figure 3 est une vue en développé montrant la répartition des trous de la bride interne de la chambre de combustion selon l'invention.
Other features and advantages of the present invention will emerge from the description given below, with reference to the accompanying drawings which illustrate an embodiment having no limiting character. In the figures:
  • the figure 1 is a longitudinal sectional view of a combustion chamber in its environment according to one embodiment of the invention;
  • the figure 2 is a partial view in perspective and skinned of the figure 1 ; and
  • the figure 3 is a view in developed showing the distribution of the holes of the internal flange of the combustion chamber according to the invention.

Description détaillée d'un mode de réalisationDetailed description of an embodiment

La figure 1 illustre une chambre de combustion de turbomachine conforme à l'invention.The figure 1 illustrates a turbomachine combustion chamber according to the invention.

La turbomachine comporte une section de compression (non représentée) dans laquelle de l'air est comprimé avant d'être injecté dans un carter de chambre 2, puis dans une chambre de combustion 4 montée à l'intérieur de celui-ci.The turbomachine comprises a compression section (not shown) in which air is compressed before being injected into a chamber housing 2, then into a combustion chamber 4 mounted inside thereof.

L'air comprimé est introduit dans la chambre de combustion et mélangé à du carburant avant d'y être brûlé. Les gaz issus de cette combustion sont alors dirigés vers une turbine haute-pression 6 disposée en sortie de la chambre de combustion 4.Compressed air is introduced into the combustion chamber and mixed with fuel before being burned. The gases resulting from this combustion are then directed to a high-pressure turbine 6 disposed at the outlet of the combustion chamber 4.

La chambre de combustion 4, qui est de type annulaire, est formée d'une paroi annulaire interne 4a et d'une paroi annulaire externe 4b qui sont réunies par une paroi transversale 4c formant fond de chambre.The combustion chamber 4, which is of annular type, is formed of an inner annular wall 4a and an outer annular wall 4b which are joined by a transverse wall 4c forming chamber bottom.

Les parois interne 4a et externe 4b s'étendent selon un axe longitudinal X-X légèrement incliné par rapport à l'axe longitudinal Y-Y de la turbomachine. Le fond de chambre 4c est pourvu d'une pluralité d'ouvertures 8 dans lequel sont montés des injecteurs de carburant 10.The inner walls 4a and outer 4b extend along a longitudinal axis X-X slightly inclined relative to the longitudinal axis Y-Y of the turbomachine. The chamber bottom 4c is provided with a plurality of openings 8 in which fuel injectors 10 are mounted.

Le carter de chambre 2, qui est formé d'une enveloppe interne 2a et d'une enveloppe externe 2b, ménage avec la chambre de combustion 4 un espace annulaire 12 dans lequel est admis l'air comprimé destiné à la combustion, à la dilution et au refroidissement de la chambre. La chambre 4 se divise en une zone primaire (ou zone de combustion) et une zone secondaire (ou zone de dilution) située en aval de la précédente.The chamber casing 2, which is formed of an inner casing 2a and an outer casing 2b, furnishes with the combustion chamber 4 an annular space 12 into which compressed air intended for combustion, at the dilution, is admitted. and cooling the chamber. The chamber 4 is divided into a primary zone (or combustion zone) and a secondary zone (or dilution zone) located downstream of the previous one.

L'air qui alimente les zones primaire et secondaire de la chambre de combustion 4 est introduit par une ou plusieurs rangées de perçages 14, 16 pratiqués respectivement dans les parois interne 4a et externe 4b de la chambre.The air that feeds the primary and secondary zones of the combustion chamber 4 is introduced by one or more rows of holes 14, 16 made respectively in the inner walls 4a and outer 4b of the chamber.

Les parois interne 4a et externe 4b de la chambre 4 se prolongent, à leur extrémité aval, respectivement par des brides (ou languettes) annulaires interne 18 et externe 20.The inner and outer walls 4a and 4b of the chamber 4 extend, at their downstream end, respectively by internal and external annular flanges 18 or tongues 18.

Ces brides interne 18 et externe 20 sont destinés à être fixées respectivement sur les enveloppes interne 2a et externe 2b du carter de chambre 2 par l'intermédiaire de liaisons boulonnées respectives 22, 24. Elles ont pour fonction de maintenir en position la chambre de combustion 4 dans le carter de chambre 2.These inner and outer flanges 18 and 18 are intended to be fastened respectively to the inner casings 2a and outer casings 2b of the chamber casing 2 by means of respective bolted connections 22, 24. Their function is to hold the combustion chamber in position. 4 in the chamber housing 2.

L'air comprimé circulant dans l'espace annulaire 12 est également destiné à un alimenter un circuit de refroidissement de la turbine haute-pression 6 de la turbomachine.Compressed air circulating in the annular space 12 is also intended to supply a cooling circuit of the high-pressure turbine 6 of the turbomachine.

A cet effet, la bride interne 18 de maintien de la chambre de combustion 4 est munie de trous d'alimentation en air 26. Ces trous 26 permettent la circulation de l'air dans l'espace annulaire 12 en aval de la bride interne 18.For this purpose, the internal flange 18 for holding the combustion chamber 4 is provided with air supply holes 26. These holes 26 allow the circulation of air in the annular space 12 downstream of the internal flange 18 .

De même, l'enveloppe interne 2a du carter de chambre 2 est percée par des orifices d'alimentation en air 28, par exemple répartis sur une seule rangée, qui s'ouvrent dans l'espace annulaire 12 en aval de la bride interne 18 et débouchent à l'extérieur du carter de chambre 2, vers un injecteur d'air 30. Cet injecteur d'air 30 est destiné à refroidir la turbine haute-pression 6 de la turbomachine.Similarly, the inner casing 2a of the chamber casing 2 is pierced by air supply orifices 28, for example distributed in a single row, which open into the annular space 12 downstream of the internal flange 18. and open out of the chamber housing 2, to an air injector 30. This air injector 30 is intended to cool the high-pressure turbine 6 of the turbomachine.

Selon l'invention, les trous d'alimentation en air 26 de la bride interne 18 sont répartis circonférentiellement sur au moins deux rangées 26a, 26b disposées en quinconce.According to the invention, the air supply holes 26 of the inner flange 18 are distributed circumferentially on at least two rows 26a, 26b arranged in staggered rows.

Cette répartition est notamment représentée sur les figures 2 et 3. Sur cette figure, les deux rangées 26a, 26b de trous d'alimentation en air de la bride interne 18 sont bien disposées en quinconce.This distribution is notably represented on Figures 2 and 3 . In this figure, the two rows 26a, 26b of air supply holes of the inner flange 18 are arranged in staggered rows.

Par rangées disposées en quinconce, on entend que les trous de l'une des rangées 26a, 26b ne sont pas alignés avec les trous de l'autre rangée selon l'axe longitudinal X-X de la chambre de combustion 4.Staggered rows means that the holes in one of the rows 26a, 26b are not aligned with the holes in the other row along the longitudinal axis X-X of the combustion chamber 4.

Une telle disposition des trous selon deux rangées disposées en quinconce permet de « casser » l'harmonique des vibrations engendrées par la combustion du mélange air/carburant dans la chambre, et ainsi d'éviter que la bride interne ne se casse sous l'effet de ses vibrations.Such an arrangement of the holes according to two rows arranged in a staggered manner makes it possible to "break" the harmonic of the vibrations generated. by the combustion of the air / fuel mixture in the chamber, and thus to prevent the internal flange from breaking under the effect of its vibrations.

Sur les figures 2 et 3, les trous d'alimentation en air 26 de la chambre de combustion ont une section circulaire. Il est toutefois possible d'envisager une autre forme de section, par exemple oblong.On the Figures 2 and 3 , the air supply holes 26 of the combustion chamber have a circular section. It is possible, however, to envisage another form of section, for example oblong.

On notera également que comme les trous 26 de la bride interne 18 sont répartis sur deux rangées en quinconce, leur section individuelle peut être réduite par rapport à une disposition classique en une seule rangée de façon à garder le même débit d'air général alimentant l'injecteur d'air 30. Ainsi, la distance séparant deux trous adjacents est augmentée, ce qui réduit encore les risques possibles de cassure de la bride interne à cet endroit.Note also that since the holes 26 of the inner flange 18 are distributed in two staggered rows, their individual section can be reduced compared to a conventional arrangement in a single row so as to keep the same general air flow supplying the air. In this way, the distance separating two adjacent holes is increased, which further reduces the possible risks of breaking the internal flange at this point.

Selon une caractéristique avantageuse de l'invention illustrée sur la figure 3, les trous d'alimentation en air 26 de la bride interne 18 sont décalés radialement par rapport aux perçages d'alimentation en air 14 de la paroi interne 4a de la chambre de combustion 4.According to an advantageous characteristic of the invention illustrated on the figure 3 , the air supply holes 26 of the inner flange 18 are radially offset relative to the air supply bores 14 of the inner wall 4a of the combustion chamber 4.

Comme les trous 26 de la bride interne 18 ne sont pas alignés avec les perçages 14 de la paroi interne 4a, il est ainsi possible d'éviter que les gaz issus de la combustion du mélange air/carburant dans la chambre 4 ne rayonnent directement vers l'enveloppe interne 2a du carter de chambre 2 avec le risque de l'endommager.As the holes 26 of the inner flange 18 are not aligned with the holes 14 of the inner wall 4a, it is thus possible to prevent the gases from the combustion of the air / fuel mixture in the chamber 4 from radiating directly to the inner casing 2a of the chamber casing 2 with the risk of damaging it.

Selon une autre caractéristique avantageuse de l'invention également illustrée sur la figure 3, les trous d'alimentation en air 26 de la bride interne 18 sont décalés radialement par rapport aux orifices 28 de l'enveloppe interne 2a du carter de chambre 2.According to another advantageous characteristic of the invention also illustrated on the figure 3 , the air supply holes 26 of the inner flange 18 are offset radially with respect to the orifices 28 of the inner casing 2a of the chamber casing 2.

Ainsi, il est également possible d'éviter un rayonnement direct des gaz de combustion depuis la chambre de combustion 4 vers l'injecteur d'air 30 qui est destiné à assurer le refroidissement de la turbine haute-pression 6. De la sorte, l'efficacité du refroidissement de la turbine haute-pression n'est pas détériorée par la présence des trous d'alimentation en air 26 de la bride interne 18.Thus, it is also possible to avoid direct radiation of the combustion gases from the combustion chamber 4 to the air injector 30 which is intended to ensure the cooling of the high-pressure turbine 6. cooling efficiency of the high-pressure turbine is not impaired by the presence of the air supply holes 26 of the inner flange 18.

On notera que ce décalage entre les trous d'alimentation en air 26 de la bride interne 18 et les orifices 28 de l'enveloppe interne 2a peut être combiné au décalage avantageux entre ces mêmes trous 26 de la bride interne et les perçages 14 de la paroi interne 4a de la chambre de combustion 4.It will be noted that this offset between the air supply holes 26 of the inner flange 18 and the orifices 28 of the inner envelope 2a can be combined with the advantageous offset between these same holes 26 of the internal flange and the holes 14 of the internal wall 4a of the combustion chamber 4.

Claims (4)

  1. An annular combustion chamber (4) for a turbomachine, the chamber comprising inner (4a) and outer (4b) annular walls united by a transverse wall (4c), the inner and outer walls being extended at their downstream ends by inner (18) and outer (20) fastener flanges for being fastened respectively to inner (2a) and outer (2b) shells of a casing (2) of the turbomachine in order to hold the combustion chamber in position, the inner flange (18) being provided with a plurality of holes (26) for feeding cooling air to a high pressure turbine (6) of the turbomachine, characterized in that the air feed holes (26) through the inner flange (18) are distributed circumferentially over at least two rows (26a, 26b) disposed in a staggered configuration.
  2. A combustion chamber according to claim 1, in which the inner (4a) and outer (4b) walls are provided with a plurality of holes (14, 16) for feeding the chamber with air, characterized in that the air feed holes (26) through the inner flange (18) are radially offset relative to the air feed holes (14) through the inner wall (4a).
  3. A combustion chamber according to claim 1 and 2, in which the inner shell (2a) of the turbomachine casing (2) is provided with a plurality of orifices (28), characterized in that the air feed holes (26) through the inner flange (18) are radially offset relative to the orifices (28) through the inner shell (2a) of the casing (2).
  4. A turbomachine comprising a combustion chamber (4) according to any one of claims 1 to 3.
EP05290623.7A 2004-04-15 2005-03-22 Gas turbine annular combustion chamber with improved inner support flange Active EP1593913B1 (en)

Applications Claiming Priority (2)

Application Number Priority Date Filing Date Title
FR0403924A FR2869094B1 (en) 2004-04-15 2004-04-15 ANNULAR COMBUSTION CHAMBER OF INTERNAL FLANGE TURBOMACHINE WITH IMPROVED FASTENING
FR0403924 2004-04-15

Publications (2)

Publication Number Publication Date
EP1593913A1 EP1593913A1 (en) 2005-11-09
EP1593913B1 true EP1593913B1 (en) 2016-11-16

Family

ID=34942026

Family Applications (1)

Application Number Title Priority Date Filing Date
EP05290623.7A Active EP1593913B1 (en) 2004-04-15 2005-03-22 Gas turbine annular combustion chamber with improved inner support flange

Country Status (6)

Country Link
US (1) US7412834B2 (en)
EP (1) EP1593913B1 (en)
JP (1) JP2005300145A (en)
CA (1) CA2500762C (en)
FR (1) FR2869094B1 (en)
RU (1) RU2365822C2 (en)

Families Citing this family (14)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US7360364B2 (en) * 2004-12-17 2008-04-22 General Electric Company Method and apparatus for assembling gas turbine engine combustors
FR2890156A1 (en) 2005-08-31 2007-03-02 Snecma Turbomachine e.g. aircraft turbojet, combustion chamber, has internal and external flanges with orifices of triangular shape, where successive triangular orifices are arranged in staggered and head-to-tail configuration
US7578134B2 (en) * 2006-01-11 2009-08-25 General Electric Company Methods and apparatus for assembling gas turbine engines
US8141370B2 (en) * 2006-08-08 2012-03-27 General Electric Company Methods and apparatus for radially compliant component mounting
FR2922630B1 (en) * 2007-10-22 2015-11-13 Snecma COMBUSTION CHAMBER WALL WITH OPTIMIZED DILUTION AND COOLING, COMBUSTION CHAMBER AND TURBOMACHINE WHILE ENHANCED
FR2929689B1 (en) * 2008-04-03 2013-04-12 Snecma Propulsion Solide GAS TURBINE COMBUSTION CHAMBER WITH SECTORIZED INTERNAL AND EXTERNAL WALLS
FR2944062B1 (en) * 2009-04-06 2011-06-03 Snecma ERGOLS INJECTOR
US8863527B2 (en) * 2009-04-30 2014-10-21 Rolls-Royce Corporation Combustor liner
US10995666B2 (en) * 2015-11-13 2021-05-04 General Electric Company Particle separators for turbomachines and method of operating the same
FR3047544B1 (en) * 2016-02-10 2018-03-02 Safran Aircraft Engines TURBOMACHINE COMBUSTION CHAMBER
WO2019022862A1 (en) * 2017-07-24 2019-01-31 Siemens Aktiengesellschaft Particulate-deflecting arrangement for reducing ingestion of particulates in a combustion turbine engine
FR3120895B1 (en) 2021-03-16 2024-07-12 Safran Aircraft Engines LABYRINTH SEALING DEVICE
US20220390111A1 (en) * 2021-06-07 2022-12-08 General Electric Company Combustor for a gas turbine engine
CN115539986B (en) * 2022-09-22 2024-03-19 中国航发沈阳发动机研究所 Hydrogen fuel honeycomb bionic combustion chamber head structure

Family Cites Families (8)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
GB1578474A (en) * 1976-06-21 1980-11-05 Gen Electric Combustor mounting arrangement
US4466239A (en) * 1983-02-22 1984-08-21 General Electric Company Gas turbine engine with improved air cooling circuit
CA2056592A1 (en) * 1990-12-21 1992-06-22 Phillip D. Napoli Multi-hole film cooled combustor liner with slotted film starter
US5758504A (en) * 1996-08-05 1998-06-02 Solar Turbines Incorporated Impingement/effusion cooled combustor liner
US6434821B1 (en) * 1999-12-06 2002-08-20 General Electric Company Method of making a combustion chamber liner
JP3930252B2 (en) * 2000-01-07 2007-06-13 三菱重工業株式会社 Gas turbine combustor
JP2003328778A (en) * 2002-05-15 2003-11-19 Mitsubishi Heavy Ind Ltd System and method for controlling combustion vibration for gas turbine
FR2841591B1 (en) * 2002-06-27 2006-01-13 Snecma Moteurs VENTILATION CIRCUITS OF THE TURBINE OF A TURBOMACHINE

Also Published As

Publication number Publication date
FR2869094A1 (en) 2005-10-21
FR2869094B1 (en) 2006-07-21
RU2005110358A (en) 2006-10-20
US20050229606A1 (en) 2005-10-20
RU2365822C2 (en) 2009-08-27
CA2500762C (en) 2012-09-25
EP1593913A1 (en) 2005-11-09
JP2005300145A (en) 2005-10-27
CA2500762A1 (en) 2005-10-15
US7412834B2 (en) 2008-08-19

Similar Documents

Publication Publication Date Title
EP1593913B1 (en) Gas turbine annular combustion chamber with improved inner support flange
EP1818614B1 (en) Annular combustion chamber of a turbomachine with alternating mountings
JP7098300B2 (en) A system for dissipating fuel spills in fuel supply conduit assemblies
US8448444B2 (en) Method and apparatus for mounting transition piece in combustor
RU2406937C2 (en) Device used for directing structural element to hole located in wall of gas-turbine engine combustion chamber, gas-turbine engine combustion chamber and gas-turbine engine containing above device
RU2422730C2 (en) Annular combustion chamber of gas turbine engine, and gas turbine engine containing such combustion chamber
RU2507452C2 (en) Gas turbine engine combustion chamber with deflectors made of composite with ceramic matrix
EP1818613A1 (en) Combustion chamber of a turbomachine
EP1793168A1 (en) Device for the injection of mixture of fuel and air, turbomachine and combustor with such a device
FR2751054A1 (en) ANTI-NOX COMBUSTION CHAMBER WITH ANNULAR TYPE FUEL INJECTION
EP1265035A1 (en) Double mounting of a ceramic matrix composite combustion chamber
FR2905166A1 (en) Annular combustion chamber for e.g. turboreactor, has cooling channel made between inner and outer fixation edges of chamber base and upstream fixation edges of inner and outer walls, where channel opens inside chamber
FR2889732A1 (en) Combustion chamber for turbomachine, has annular inner and outer walls including perforations emerging relative to tabs and constituted of holes whose axis forms, with longitudinal axis, angle comprised between preset values
RU2461778C2 (en) Diffusion chamber of gas turbine engine, combustion chamber and gas turbine containing them
RU2660729C2 (en) Combustion chamber for turbine engine with uniform air intake through the fuel injection system
FR2942640A1 (en) POST-COMBUSTION CHAMBER FOR TURBOMACHINE
FR3081494A1 (en) GAS TURBOMACHINE COMBUSTION MODULE WITH BOTTOM BOTTOM
FR2979416A1 (en) WALL OF COMBUSTION CHAMBER
FR3064050A1 (en) COMBUSTION CHAMBER OF A TURBOMACHINE
FR2911666A1 (en) Air and liquid fuel mixture injecting device for e.g. jet engine, of aircraft, has dampening washer inserted in housing, where washer is in contact with annular flange of sliding crosspiece and upstream and downstream wall of housing
FR3017928B1 (en) TURBOMACHINE WITH EXTERNAL FLANGE OF "SANDWICH" COMBUSTION CHAMBER
FR3055663A1 (en) SEALING DEVICE FOR TURBOMACHINE
FR3109430A1 (en) MONOBLOC COMBUSTION CHAMBER CANDLE
FR3081974A1 (en) COMBUSTION CHAMBER OF A TURBOMACHINE
FR3006369A1 (en) TURBOMACHINE WITH CENTRIFUGAL COMPRESSION STAGE

Legal Events

Date Code Title Description
PUAI Public reference made under article 153(3) epc to a published international application that has entered the european phase

Free format text: ORIGINAL CODE: 0009012

17P Request for examination filed

Effective date: 20050325

AK Designated contracting states

Kind code of ref document: A1

Designated state(s): AT BE BG CH CY CZ DE DK EE ES FI FR GB GR HU IE IS IT LI LT LU MC NL PL PT RO SE SI SK TR

AX Request for extension of the european patent

Extension state: AL BA HR LV MK YU

RIN1 Information on inventor provided before grant (corrected)

Inventor name: HERNANDEZ, DIDIER

Inventor name: BES, MARTINE

Inventor name: TRAHOT, DENIS

Inventor name: LEPRETRE, GILLES

AKX Designation fees paid

Designated state(s): DE FR GB IT

17Q First examination report despatched

Effective date: 20060627

GRAP Despatch of communication of intention to grant a patent

Free format text: ORIGINAL CODE: EPIDOSNIGR1

INTG Intention to grant announced

Effective date: 20160525

GRAS Grant fee paid

Free format text: ORIGINAL CODE: EPIDOSNIGR3

GRAA (expected) grant

Free format text: ORIGINAL CODE: 0009210

AK Designated contracting states

Kind code of ref document: B1

Designated state(s): DE FR GB IT

REG Reference to a national code

Ref country code: GB

Ref legal event code: FG4D

Free format text: NOT ENGLISH

REG Reference to a national code

Ref country code: DE

Ref legal event code: R096

Ref document number: 602005050688

Country of ref document: DE

REG Reference to a national code

Ref country code: FR

Ref legal event code: PLFP

Year of fee payment: 13

REG Reference to a national code

Ref country code: DE

Ref legal event code: R097

Ref document number: 602005050688

Country of ref document: DE

PLBE No opposition filed within time limit

Free format text: ORIGINAL CODE: 0009261

STAA Information on the status of an ep patent application or granted ep patent

Free format text: STATUS: NO OPPOSITION FILED WITHIN TIME LIMIT

26N No opposition filed

Effective date: 20170817

REG Reference to a national code

Ref country code: FR

Ref legal event code: PLFP

Year of fee payment: 14

PGFP Annual fee paid to national office [announced via postgrant information from national office to epo]

Ref country code: DE

Payment date: 20240220

Year of fee payment: 20

Ref country code: GB

Payment date: 20240220

Year of fee payment: 20

PGFP Annual fee paid to national office [announced via postgrant information from national office to epo]

Ref country code: IT

Payment date: 20240220

Year of fee payment: 20

Ref country code: FR

Payment date: 20240220

Year of fee payment: 20