EP1561998B1 - Diffusor for a gas turbine engine - Google Patents
Diffusor for a gas turbine engine Download PDFInfo
- Publication number
- EP1561998B1 EP1561998B1 EP05290094A EP05290094A EP1561998B1 EP 1561998 B1 EP1561998 B1 EP 1561998B1 EP 05290094 A EP05290094 A EP 05290094A EP 05290094 A EP05290094 A EP 05290094A EP 1561998 B1 EP1561998 B1 EP 1561998B1
- Authority
- EP
- European Patent Office
- Prior art keywords
- diffuser
- combustion chamber
- compressor
- frustoconical
- wall
- Prior art date
- Legal status (The legal status is an assumption and is not a legal conclusion. Google has not performed a legal analysis and makes no representation as to the accuracy of the status listed.)
- Active
Links
- 238000002485 combustion reaction Methods 0.000 claims description 35
- 238000011144 upstream manufacturing Methods 0.000 claims description 17
- 239000000725 suspension Substances 0.000 claims description 10
- 238000005070 sampling Methods 0.000 description 4
- 238000000034 method Methods 0.000 description 3
- 238000003780 insertion Methods 0.000 description 1
- 230000037431 insertion Effects 0.000 description 1
- 238000004519 manufacturing process Methods 0.000 description 1
Images
Classifications
-
- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F04—POSITIVE - DISPLACEMENT MACHINES FOR LIQUIDS; PUMPS FOR LIQUIDS OR ELASTIC FLUIDS
- F04D—NON-POSITIVE-DISPLACEMENT PUMPS
- F04D29/00—Details, component parts, or accessories
- F04D29/40—Casings; Connections of working fluid
- F04D29/52—Casings; Connections of working fluid for axial pumps
- F04D29/54—Fluid-guiding means, e.g. diffusers
- F04D29/541—Specially adapted for elastic fluid pumps
- F04D29/542—Bladed diffusers
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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
- F05B—INDEXING SCHEME RELATING TO WIND, SPRING, WEIGHT, INERTIA OR LIKE MOTORS, TO MACHINES OR ENGINES FOR LIQUIDS COVERED BY SUBCLASSES F03B, F03D AND F03G
- F05B2230/00—Manufacture
- F05B2230/60—Assembly methods
- F05B2230/604—Assembly methods using positioning or alignment devices for aligning or centering, e.g. pins
- F05B2230/606—Assembly methods using positioning or alignment devices for aligning or centering, e.g. pins using maintaining alignment while permitting differential dilatation
Definitions
- the present invention relates to a turbojet diffuser as defined in the preamble of claim 1.
- a turbojet diffuser as defined in the preamble of claim 1.
- Such a diffuser is known from the document EP-A-0 523 935 .
- the diffuser is often fixed inside an outer casing of the combustion chamber by a thin wall or a frustoconical web that extends from an outer longitudinal wall of the diffuser in the direction of the combustion chamber and which is welded at its radially outer end to the outer casing of the combustion chamber.
- the disadvantage of this known technique is that the diffuser, which has a life substantially less than that of the combustion chamber, can not be removed from this housing.
- EP-A1-0 523 935 describes a discharge element for a turbomachine, this element comprising compressor rectifiers (OGVs) integral with a diffuser.
- GOVs compressor rectifiers
- the document EP-A2-1 223 382 discloses a turbomachine diffuser, which is suspended from an outer casing by upstream and downstream walls and is supported by an upstream rectifier.
- the document EP-A1-0 059 420 describes a high-pressure compressor stator.
- the object of the invention is in particular to provide a simple, economical and inexpensive solution to the problem of the removable mounting of the diffuser in a turbojet engine.
- turbojet diffuser according to claim 1.
- the two frustoconical fastening walls of the diffuser according to the invention make it possible to circumvent the downstream advance of the annular space which surrounds the compressor and thus to fix the diffuser to the outer casing of the combustion chamber without modifying the specifications of the compressor air sampling and without the use of structural arms.
- the attachment of the second frustoconical wall on the outer casing of the combustion chamber is at the connection between the outer casings of the compressor and the combustion chamber, particularly simple manner by insertion of an annular flange of the second aforesaid frustoconical wall between the annular flanges connecting compressor housings and the annular chamber.
- first frustoconical wall of the suspension means to be connected to the upstream end of the outer longitudinal wall of the diffuser, which ensures optimum alignment of the upstream end of the diffuser on the downstream end of the compressor, so that a fixed blade of the upstream end of the diffuser is well positioned and centered on the axis of the compressor.
- the biconical shape of the suspension means increases the flexibility of the attachment of the diffuser and reduces the stresses at the connection on the outer longitudinal wall of the diffuser, which increases its life.
- the two walls or frustoconical webs of the suspension means are formed in one piece and their junction comprises an annular rib extending in the direction of the combustion chamber.
- This annular rib stiffens the junction zone of the two walls or frustoconical webs and distributes the stresses in this zone. It preferably has a thickness between 1.3 and 1.7 times the thickness of the sails, and optimally a thickness equal to about 1.5 times the thickness of the sails.
- This rib has, in its simplest embodiment, a cylindrical shape centered on the axis of the turbojet engine.
- it may extend in the extension of the bisector of the angle formed between the two walls or frustoconical webs of the suspension means of the diffuser.
- an advantage of the diffuser according to the invention is that it can be dismantled in a simple manner while complying with the air sampling specifications of the compressor.
- figure 1 1 denotes a diffuser according to the known technique, arranged between a compressor 2 upstream and a combustion chamber 3 downstream in a turbojet engine.
- the compressor 2 is a high-pressure compressor and comprises several stages of moving blades 4, 5 mounted on a rotor 6 of the turbojet engine by appropriate means, for example of the dovetail type 7, and stages of fixed vanes 8 forming rectifiers, mounted on a stator 9 of the turbojet engine by appropriate means.
- On the figure 1 only two stages of moving blades 4 and 5 and a stationary vane stage 8 are arranged between the two stages of moving blades 4 and 5.
- An annular space 10 is delimited around the stator 9 of the compressor 2 by an outer casing 11 and by a rear transverse wall 12 which is mounted by an internal annular flange 13 on an annular flange 14 of the stator 9 and by an external annular flange 15 on an annular flange 16 of the outer casing 11 of the compressor 2.
- the combustion chamber 3 is delimited by an outer casing 17 and by an inner casing (not shown), the outer casing 17 being fixed on the upstream side on the outer casing 11 of the compressor 2 by means of an annular flange 18 applied to the casing.
- external annular flange 15 of the transverse wall 12 of the compressor 2 the fixing of the three flanges being provided by appropriate means of the screw-nut type 19.
- the rear transverse wall 12 extends downstream around an upstream portion of the diffuser 1.
- the diffuser 1 comprises fixed vanes 20 arranged radially between an outer longitudinal wall 21 and an inner longitudinal wall 22 for guiding the air leaving the compressor 2 towards the combustion chamber 3.
- the diffuser 1 is fixed to the bottom of the outer casing 17 of the combustion chamber 3 by a thin wall or veil 23 of frustoconical shape which extends from the outer longitudinal wall 21 of the diffuser 1 in the direction of the combustion chamber 3 and which is welded at its radially outer end 24 to the outer casing 17 of the combustion chamber 3.
- the wall or sail 23 of frustoconical shape is attached to the outer longitudinal wall 21 of the diffuser in the middle part of this wall 21.
- the diffuser 1 is also fixed by an inner wall or web 25 of frustoconical shape which extends from the inner longitudinal wall 22 of the diffuser 1 in the direction of the combustion chamber 3, to an inner casing (not shown) of the combustion chamber 3.
- a cylindrical wall 26 extends from the outer longitudinal wall 21 of the diffuser 1 in the direction of the compressor 2 and is fixed on the stator 9 of the compressor 2 by means of an annular flange 27 applied to the connecting flanges 14 and 13 of the stator 9 and the transverse wall 12 of the compressor. sseur 2 respectively, the fixing being provided by means 28 suitable screw-nut type.
- This diffuser of the prior art is not removable independently of the casings of the combustion chamber.
- FIG 2 is shown a diffuser 29 according to the present invention, arranged between a compressor 2 and a combustion chamber 3 of the same type as those described above.
- the diffuser 29 comprises fixed vanes 30 arranged radially between its outer longitudinal wall 31 and its inner longitudinal wall 32 for guiding the air leaving the compressor 2 towards the combustion chamber 3.
- the diffuser 29 is mounted inside the outer casing 17 of the combustion chamber 3 by suspension means which comprise a first wall or sail 33 of frustoconical shape which extends from the outer longitudinal wall 31 of the diffuser 29 in the direction of the combustion chamber 3 and a second wall or sail 34 of frustoconical shape which extends between the first frustoconical wall 33 and the outer casing 17 of the combustion chamber 3 in the direction of the compressor 2 and ends with a radially outer annular flange 35 clamped between the connecting flange 15 of the transverse wall 12 of the compressor 2 and the upstream flange 18 of the outer casing of the combustion chamber 3, the annular flange 16 of the compressor housing. being applied to the annular flange 15 of the transverse wall 12.
- the diffuser 29 also comprises an inner wall or sail 36 of frustoconical shape which extends from the inner longitudinal wall 32 of the diffuser 29 in the direction of the combustion chamber 3 and which is attached to its downstream end (not shown) on the inner casing of the combustion chamber 3.
- the two walls or sails 33 and 34 frustoconical suspension means are formed in one piece and their junction comprises an annular rib 37 which extends towards the combustion chamber 3 and which stiffens the junction area of the two walls 33 and 34 and distribute the stresses in this area.
- the annular rib 37 has a thickness of between 1.3 and 1.7 times the thickness of the webs 33 and 34, and is preferably equal to about 1.5 times the thickness of the webs 33 and 34.
- This annular rib 37 is for example of cylindrical shape and centered on the axis (not shown) of the turbojet engine. Alternatively, it extends in the extension of the bisector of the angle formed between the two walls or sails 33 and 34 frustoconical suspension means.
- the radius of the connection 38 between the upstream side surfaces of the two frustoconical walls 33, 34 is for example about three millimeters.
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- Engineering & Computer Science (AREA)
- Mechanical Engineering (AREA)
- General Engineering & Computer Science (AREA)
- Chemical & Material Sciences (AREA)
- Combustion & Propulsion (AREA)
- Structures Of Non-Positive Displacement Pumps (AREA)
Description
La présente invention concerne un diffuseur pour turboréacteur comme défini dans le préambule de la revendication 1. Un tel diffuseur est connu du document
Dans la technique connue, le diffuseur est souvent fixé à l'intérieur d'un carter extérieur de la chambre de combustion par une paroi mince ou un voile de forme tronconique qui s'étend depuis une paroi longitudinale externe du diffuseur dans la direction de la chambre de combustion et qui est soudée à son extrémité radialement externe sur le carter externe de la chambre de combustion.In the known art, the diffuser is often fixed inside an outer casing of the combustion chamber by a thin wall or a frustoconical web that extends from an outer longitudinal wall of the diffuser in the direction of the combustion chamber and which is welded at its radially outer end to the outer casing of the combustion chamber.
L'inconvénient de cette technique connue est que le diffuseur qui a une durée de vie notablement inférieure à celle du carter de la chambre de combustion, n'est pas démontable de ce carter.The disadvantage of this known technique is that the diffuser, which has a life substantially less than that of the combustion chamber, can not be removed from this housing.
Il est donc souhaitable de fixer le diffuseur de façon démontable sur le carter extérieur de la chambre de combustion. Pour faciliter le démontage du diffuseur, la meilleure solution serait de le fixer au moyen d'une bride annulaire externe qui serait insérée entre les brides annulaires de raccordement des carters extérieurs du compresseur et de la chambre de combustion.It is therefore desirable to fix the diffuser removably on the outer casing of the combustion chamber. To facilitate disassembly of the diffuser, the best solution would be to fix it by means of an external annular flange which would be inserted between the annular flanges connecting the outer casings of the compressor and the combustion chamber.
Il faudrait pour cela qu'une paroi ou un voile tronconique de fixation du diffuseur s'étende depuis le diffuseur dans la direction du compresseur. Cela est toutefois impossible en raison des contraintes de prélèvement d'air du compresseur, selon lesquelles un espace annulaire formé autour du stator du compresseur s'étend vers l'aval jusqu'au niveau de la partie amont du diffuseur et est délimité par une paroi transversale qui est fixée au carter extérieur du compresseur et qui fait obstacle à la disposition en cet endroit d'une paroi ou d'un voile tronconique de fixation du diffuseur qui s'étendrait depuis le diffuseur dans la direction du compresseur.This would require a wall or a frustoconical flange fixing the diffuser extends from the diffuser in the direction of the compressor. However, this is not possible because of the compressor air sampling constraints, according to which an annular space formed around the compressor stator extends downstream to the level of the upstream portion of the diffuser and is delimited by a wall. transverse which is fixed to the outer casing of the compressor and which hinders the provision in this place of a wall or a frustoconical fastening web of the diffuser which extends from the diffuser in the direction of the compressor.
On pourrait résoudre ce problème au moyen de bras structuraux qui seraient raccordés à la paroi longitudinale externe du diffuseur en aval des redresseurs, mais il faudrait pour cela que le diffuseur soit constitué de deux parties, ce qui compliquerait sa fabrication et augmenterait son coût.This problem could be solved by means of structural arms which would be connected to the external longitudinal wall of the diffuser downstream of the rectifiers, but it would require that the diffuser consists of two parts, which would complicate its manufacture and increase its cost.
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L'invention a notamment pour but d'apporter une solution simple, économique et peu coûteuse au problème de la fixation démontable du diffuseur dans un turboréacteur.The object of the invention is in particular to provide a simple, economical and inexpensive solution to the problem of the removable mounting of the diffuser in a turbojet engine.
Elle propose à cet effet un diffuseur pour turboréacteur selon la revendication 1.It proposes for this purpose a turbojet diffuser according to claim 1.
Les deux parois tronconiques de fixation du diffuseur selon l'invention permettent de contourner l'avancée vers l'aval de l'espace annulaire qui entoure le compresseur et donc de fixer le diffuseur au carter extérieur de la chambre de combustion sans modifier les spécifications de prélèvement d'air du compresseur et sans utiliser de bras structuraux.The two frustoconical fastening walls of the diffuser according to the invention make it possible to circumvent the downstream advance of the annular space which surrounds the compressor and thus to fix the diffuser to the outer casing of the combustion chamber without modifying the specifications of the compressor air sampling and without the use of structural arms.
Avantageusement, la fixation de la seconde paroi tronconique sur le carter extérieur de la chambre de combustion se fait au niveau du raccordement entre les carters extérieurs du compresseur et de la chambre de combustion, de façon particulièrement simple par insertion d'une bride annulaire de la seconde paroi tronconique précitée entre les brides annulaires de raccordement des carters du compresseur et de la chambre annulaire.Advantageously, the attachment of the second frustoconical wall on the outer casing of the combustion chamber is at the connection between the outer casings of the compressor and the combustion chamber, particularly simple manner by insertion of an annular flange of the second aforesaid frustoconical wall between the annular flanges connecting compressor housings and the annular chamber.
Cela permet également que la première paroi tronconique des moyens de suspension soit raccordée à l'extrémité amont de la paroi longitudinale externe du diffuseur, ce qui assure un alignement optimal de l'extrémité amont du diffuseur sur l'extrémité aval du compresseur, de sorte qu'un aubage fixe de l'extrémité amont du diffuseur soit bien positionné et centré sur l'axe du compresseur.This also allows the first frustoconical wall of the suspension means to be connected to the upstream end of the outer longitudinal wall of the diffuser, which ensures optimum alignment of the upstream end of the diffuser on the downstream end of the compressor, so that a fixed blade of the upstream end of the diffuser is well positioned and centered on the axis of the compressor.
De plus, la forme biconique des moyens de suspension augmente la souplesse de la fixation du diffuseur et réduit les contraintes au niveau du raccordement sur la paroi longitudrflale externe du diffuseur, ce qui augmente sa durée de vie.In addition, the biconical shape of the suspension means increases the flexibility of the attachment of the diffuser and reduces the stresses at the connection on the outer longitudinal wall of the diffuser, which increases its life.
Les deux parois ou voiles tronconiques des moyens de suspension sont formés d'une seule pièce et leur jonction comprend une nervure annulaire qui s'étend en direction de la chambre de combustion. Cette nervure annulaire rigidifie la zone de jonction des deux parois ou voiles tronconiques et répartit les contraintes dans cette zone. Elle a de préférence une épaisseur comprise entre 1,3 et 1,7 fois l'épaisseur des voiles, et de façon optimale une épaisseur égale à 1,5 fois environ l'épaisseur des voiles.The two walls or frustoconical webs of the suspension means are formed in one piece and their junction comprises an annular rib extending in the direction of the combustion chamber. This annular rib stiffens the junction zone of the two walls or frustoconical webs and distributes the stresses in this zone. It preferably has a thickness between 1.3 and 1.7 times the thickness of the sails, and optimally a thickness equal to about 1.5 times the thickness of the sails.
Cette nervure a, dans sa réalisation la plus simple, une forme cylindrique centrée sur l'axe du turboréacteur.This rib has, in its simplest embodiment, a cylindrical shape centered on the axis of the turbojet engine.
En variante, elle peut s'étendre dans le prolongement de la bissectrice de l'angle formé entre les deux parois ou voiles tronconiques des moyens de suspension du diffuseur.Alternatively, it may extend in the extension of the bisector of the angle formed between the two walls or frustoconical webs of the suspension means of the diffuser.
De manière générale, un avantage du diffuseur selon l'invention est qu'il est démontable de façon simple tout en respectant les spécifications de prélèvement d'air du compresseur.In general, an advantage of the diffuser according to the invention is that it can be dismantled in a simple manner while complying with the air sampling specifications of the compressor.
D'autres avantages et caractéristiques de l'invention apparaîtront à la lecture de la description suivante faite à titre d'exemple non limitatif et en référence aux dessins annexés dans lesquels :
- la
figure 1 est une vue schématique partielle en coupe axiale du dernier étage d'un compresseur haute pression et d'un diffuseur dans un turboréacteur de la technique connue ; - le
figure 2 est une vue schématique partielle en coupe axiale du dernier étage d'un compresseur haute pression et du diffuseur selon l'invention.
- the
figure 1 is a partial diagrammatic view in axial section of the last stage of a high pressure compressor and a diffuser in a jet engine of the prior art; - the
figure 2 is a partial schematic view in axial section of the last stage of a high pressure compressor and the diffuser according to the invention.
Dans les dessins, ce qui est à gauche est en amont ou en avant et ce qui est à droite est en aval ou en arrière dans le turboréacteur.In the drawings, what is left is upstream or forward and what is right is downstream or backward in the turbojet engine.
En
Le compresseur 2 est un compresseur haute pression et comprend plusieurs étages d'aubes mobiles 4, 5 montées sur un rotor 6 du turboréacteur par des moyens appropriés par exemple du type à queue d'aronde 7, et des étages d'aubes fixes 8 formant redresseurs, montées sur un stator 9 du turboréacteur par des moyens appropriés. Sur la
Un espace annulaire 10 est délimité autour du stator 9 du compresseur 2 par un carter extérieur 11 et par une paroi transversale arrière 12 qui est montée par une bride annulaire interne 13 sur une bride annulaire 14 du stator 9 et par une bride annulaire externe 15 sur une bride annulaire 16 du carter extérieur 11 du compresseur 2.An
La chambre de combustion 3 est délimitée par un carter extérieur 17 et par un carter intérieur (non représenté), le carter extérieur 17 étant fixé du côté amont sur le carter extérieur 11 du compresseur 2 au moyen d'une bride annulaire 18 appliquée sur la bride annulaire externe 15 de la paroi transversale 12 du compresseur 2, la fixation des trois brides étant assurée par des moyens appropriés du type vis-écrou 19.The
Pour des raisons de contraintes de prélèvement d'air du compresseur 2, la paroi transversale arrière 12 s'étend vers l'aval autour d'une partie amont du diffuseur 1.For reasons of air sampling constraints of the
Le diffuseur 1 comprend des aubages fixes 20 disposés radialement entre une paroi longitudinale externe 21 et une paroi longitudinale interne 22 pour le guidage de l'air en sortie du compresseur 2 vers la chambre de combustion 3.The diffuser 1 comprises fixed
Le diffuseur 1 est fixé à l'inférieur du carter extérieur 17 de la chambre de combustion 3 par une paroi de faible épaisseur ou voile 23 de forme tronconique qui s'étend depuis la paroi longitudinale externe 21 du diffuseur 1 dans la direction de la chambre de combustion 3 et qui est soudée à son extrémité radialement externe 24 sur le carter externe 17 de la chambre de combustion 3. La paroi ou voile 23 de forme tronconique est rattachée à la paroi longitudinale externe 21 du diffuseur dans la partie médiane de cette paroi 21. Le diffuseur 1 est également fixé par une paroi ou voile interne 25 de forme tronconique qui s'étend depuis la paroi longitudinale interne 22 du diffuseur 1 dans la direction de la chambre de combustion 3, à un carter interne (non représenté) de la chambre de combustion 3. De plus, une paroi cylindrique 26 s'étend depuis la paroi longitudinale externe 21 du diffuseur 1 dans la direction du compresseur 2 et est fixée sur le stator 9 du compresseur 2 au moyen d'une bride annulaire 27 appliquée sur les brides de raccordement 14 et 13 du stator 9 et de la paroi transversale 12 du compresseur 2 respectivement, la fixation étant assurée par des moyens 28 appropriés du type vis-écrou.The diffuser 1 is fixed to the bottom of the
Ce diffuseur de la technique antérieure n'est pas démontable indépendamment des carters de la chambre de combustion.This diffuser of the prior art is not removable independently of the casings of the combustion chamber.
En
Le diffuseur 29 comprend des aubages fixes 30 disposés radialement entre sa paroi longitudinale externe 31 et sa paroi longitudinale interne 32 pour le guidage de l'air en sortie du compresseur 2 vers la chambre de combustion 3.The
Le diffuseur 29 est monté à l'intérieur du carter extérieur 17 de la chambre de combustion 3 par des moyens de suspension qui comprennent une première paroi ou voile 33 de forme tronconique qui s'étend depuis la paroi longitudinale externe 31 du diffuseur 29 dans la direction de la chambre de combustion 3 et une seconde paroi ou voile 34 de forme tronconique qui s'étend entre la première paroi tronconique 33 et le carter extérieur 17 de la chambre de combustion 3 dans la direction du compresseur 2 et se termine par une bride annulaire radialement externe 35 serrée entre la bride de raccordement 15 de la paroi transversale 12 du compresseur 2 et la bride amont 18 du carter externe de la chambre de combustion 3, la bride annulaire 16 du carter du compresseur étant appliquée sur la bride annulaire 15 de-la paroi transversale 12. Le diffuseur 29 comprend également une paroi ou voile interne 36 de forme tronconique qui s'étend depuis la paroi longitudinale interne 32 du diffuseur 29 dans la direction de la chambre de combustion 3 et qui est fixée à son extrémité aval (non représentée) sur le carter interne de la chambre de combustion 3.The
Les deux parois ou voiles 33 et 34 tronconiques des moyens de suspension sont formés d'une seule pièce et leur jonction comprend une nervure annulaire 37 qui s'étend en direction de la chambre de combustion 3 et qui permet de rigidifier la zone de jonction des deux parois 33 et 34 et de répartir les contraintes dans cette zone.The two walls or
La nervure annulaire 37 a une épaisseur comprise entre 1,3 et 1,7 fois l'épaisseur des voiles 33 et 34, et égale de préférence à 1,5 fois environ l'épaisseur des voiles 33 et 34.The
Cette nervure annulaire 37 est par exemple de forme cylindrique et centrée sur l'axe (non représenté) du turboréacteur. En variante, elle s'étend dans le prolongement de la bissectrice de l'angle formé entre les deux parois ou voiles 33 et 34 tronconiques des moyens de suspension.This
Le rayon du raccordement 38 entre les surfaces côté amont des deux parois 33, 34 tronconiques est par exemple de trois millimètres environ.The radius of the
Ces deux parois tronconiques 33 et 34 contournent l'avancée vers l'aval de la paroi transversale 12 du compresseur 2, ce qui permet de raccorder la première paroi tronconique 33 des moyens de suspension à l'extrémité amont de la paroi longitudinale externe 31 du diffuseur 29 et ainsi d'améliorer la stabilité et l'alignement des aubages fixes 30 par rapport au compresseur 2.These two
Claims (8)
- A diffuser for a turbojet, said diffuser (29) being disposed between a compressor (2) and a combustion chamber (3) and being independent from the compressor and secured to an outer casing (17) of the combustion chamber (3) by a single suspension mean formed as a single piece with the diffuser and extending between the outer casing (17) and an outer longitudinal wall (31) of the diffuser (29) and including an outer annular flange (35) for fastening to an upstream annular flange (18) of the outer casing (17) of the combustion chamber (3), characterized in that the suspension mean comprises a first frustoconical wall (33) extending from the upstream end of the outer longitudinal wall (31) of the diffuser (29) towards the combustion chamber (3), and a second frustoconical wall (34) connected to the first frustoconical wall (33) and extending towards the compressor (2) between the first frustoconical wall (33) and the outer casing (17) of the combustion chamber (3), said second frustoconical wall (34) comprising said annular flange (35).
- A diffuser according to claim 1, characterized in that the outer annular flange (35) of the second frustoconical wall (34) is clamped between two annular end flanges (16, 18) of the outer casings (11, 17) of the compressor (2) and of the combustion chamber (3).
- A diffuser according to claim 1 or 2, characterized in that the junction between the two frustoconical walls (33, 34) includes an annular rib (37) extending towards the combustion chamber (3).
- A diffuser according to claim 3, characterized in that the annular rib (37) is of cylindrical shape centered on the axis of rotation of the compressor (2).
- A diffuser according to claim 3, characterized in that the annular rib (37) extends along the bisector of the angle formed by the two frustoconical walls (33, 34).
- A diffuser according to any one of claims 3 to 5, characterized in that the thickness of the annular rib (37) lies in the range 1.3 to 1.7 times the thickness of the frustoconical walls (33, 34).
- A diffuser according to claim 6, characterized in that the thickness of the annular rib (37) is equal to about 1.5 times the thickness of the frustoconical walls (33, 34).
- A diffuser according to any preceding claim, characterized in that the radius of curvature of the connection (38) between the surfaces on the upstream side of the two frustoconical walls (33, 34) is about three millimeters.
Applications Claiming Priority (2)
Application Number | Priority Date | Filing Date | Title |
---|---|---|---|
FR0401084A FR2866079B1 (en) | 2004-02-05 | 2004-02-05 | DIFFUSER FOR TURBOREACTOR |
FR0401084 | 2004-02-05 |
Publications (2)
Publication Number | Publication Date |
---|---|
EP1561998A1 EP1561998A1 (en) | 2005-08-10 |
EP1561998B1 true EP1561998B1 (en) | 2012-03-07 |
Family
ID=34673895
Family Applications (1)
Application Number | Title | Priority Date | Filing Date |
---|---|---|---|
EP05290094A Active EP1561998B1 (en) | 2004-02-05 | 2005-01-14 | Diffusor for a gas turbine engine |
Country Status (8)
Country | Link |
---|---|
US (1) | US7197882B2 (en) |
EP (1) | EP1561998B1 (en) |
JP (1) | JP2005220904A (en) |
CN (1) | CN1651735A (en) |
CA (1) | CA2494943C (en) |
ES (1) | ES2382552T3 (en) |
FR (1) | FR2866079B1 (en) |
RU (1) | RU2365762C2 (en) |
Families Citing this family (15)
Publication number | Priority date | Publication date | Assignee | Title |
---|---|---|---|---|
GB2415749B (en) * | 2004-07-02 | 2009-10-07 | Demag Delaval Ind Turbomachine | A gas turbine engine including an exhaust duct comprising a diffuser for diffusing the exhaust gas produced by the engine |
US20110176917A1 (en) * | 2004-07-02 | 2011-07-21 | Brian Haller | Exhaust Gas Diffuser Wall Contouring |
FR2920525B1 (en) * | 2007-08-31 | 2014-06-13 | Snecma | SEPARATOR FOR SUPPLYING THE COOLING AIR OF A TURBINE |
FR2925109B1 (en) * | 2007-12-14 | 2015-05-15 | Snecma | TURBOMACHINE MODULE PROVIDED WITH A DEVICE FOR IMPROVING RADIAL GAMES |
FR2942267B1 (en) * | 2009-02-19 | 2011-05-06 | Turbomeca | EROSION LAMP FOR COMPRESSOR WHEEL |
US8534076B2 (en) * | 2009-06-09 | 2013-09-17 | Honeywell Internationl Inc. | Combustor-turbine seal interface for gas turbine engine |
US8388307B2 (en) * | 2009-07-21 | 2013-03-05 | Honeywell International Inc. | Turbine nozzle assembly including radially-compliant spring member for gas turbine engine |
WO2014051690A1 (en) * | 2012-09-26 | 2014-04-03 | United Technologies Corporation | Fastened joint for a tangential on board injector |
US11732892B2 (en) | 2013-08-14 | 2023-08-22 | General Electric Company | Gas turbomachine diffuser assembly with radial flow splitters |
EP3066318B1 (en) * | 2013-11-04 | 2023-06-21 | Raytheon Technologies Corporation | Inner diffuser case for a gas turbine engine |
CN105716114B (en) * | 2014-12-04 | 2018-05-08 | 中国航空工业集团公司沈阳发动机设计研究所 | A kind of disconnectable rectangle diffuser |
CN106226056A (en) * | 2016-08-12 | 2016-12-14 | 中国航空工业集团公司沈阳发动机设计研究所 | A kind of diffuser |
CN107339712B (en) * | 2017-06-13 | 2020-03-24 | 中国航发湖南动力机械研究所 | Radial flow combustor diffuser and gas turbine |
CN113983494B (en) * | 2021-09-22 | 2022-10-21 | 南京航空航天大学 | Diffusion ratio intelligent adjustable gas turbine main combustion chamber multi-channel diffuser |
CN114412594B (en) * | 2022-01-25 | 2024-08-23 | 中国联合重型燃气轮机技术有限公司 | Heavy gas turbine shell structure |
Citations (2)
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EP1059420A1 (en) * | 1999-06-10 | 2000-12-13 | Snecma Moteurs | Housing for a high pressure compressor |
EP1223382A2 (en) * | 2001-01-12 | 2002-07-17 | General Electric Company | Methods and apparatus for supplying air to turbine engine combustors |
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GB589541A (en) * | 1941-09-22 | 1947-06-24 | Hayne Constant | Improvements in axial flow turbines, compressors and the like |
US5165850A (en) * | 1991-07-15 | 1992-11-24 | General Electric Company | Compressor discharge flowpath |
FR2706534B1 (en) * | 1993-06-10 | 1995-07-21 | Snecma | Multiflux diffuser-separator with integrated rectifier for turbojet. |
-
2004
- 2004-02-05 FR FR0401084A patent/FR2866079B1/en not_active Expired - Lifetime
-
2005
- 2005-01-14 EP EP05290094A patent/EP1561998B1/en active Active
- 2005-01-14 ES ES05290094T patent/ES2382552T3/en active Active
- 2005-01-24 US US11/039,887 patent/US7197882B2/en active Active
- 2005-01-25 JP JP2005016575A patent/JP2005220904A/en not_active Withdrawn
- 2005-01-31 CA CA2494943A patent/CA2494943C/en active Active
- 2005-02-02 CN CN200510006289.9A patent/CN1651735A/en active Pending
- 2005-02-04 RU RU2005102776/06A patent/RU2365762C2/en active
Patent Citations (2)
Publication number | Priority date | Publication date | Assignee | Title |
---|---|---|---|---|
EP1059420A1 (en) * | 1999-06-10 | 2000-12-13 | Snecma Moteurs | Housing for a high pressure compressor |
EP1223382A2 (en) * | 2001-01-12 | 2002-07-17 | General Electric Company | Methods and apparatus for supplying air to turbine engine combustors |
Also Published As
Publication number | Publication date |
---|---|
EP1561998A1 (en) | 2005-08-10 |
RU2365762C2 (en) | 2009-08-27 |
ES2382552T3 (en) | 2012-06-11 |
JP2005220904A (en) | 2005-08-18 |
FR2866079A1 (en) | 2005-08-12 |
CN1651735A (en) | 2005-08-10 |
US7197882B2 (en) | 2007-04-03 |
FR2866079B1 (en) | 2006-03-17 |
US20050172632A1 (en) | 2005-08-11 |
CA2494943C (en) | 2012-04-24 |
CA2494943A1 (en) | 2005-08-05 |
RU2005102776A (en) | 2006-07-10 |
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