EP3956547B1 - Splitter for a turbofan engine - Google Patents
Splitter for a turbofan engine Download PDFInfo
- Publication number
- EP3956547B1 EP3956547B1 EP20716855.0A EP20716855A EP3956547B1 EP 3956547 B1 EP3956547 B1 EP 3956547B1 EP 20716855 A EP20716855 A EP 20716855A EP 3956547 B1 EP3956547 B1 EP 3956547B1
- Authority
- EP
- European Patent Office
- Prior art keywords
- annular wall
- spout
- radial
- deflector
- inner annular
- 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.)
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- 238000004519 manufacturing process Methods 0.000 claims description 20
- 239000000654 additive Substances 0.000 claims description 11
- 230000000996 additive effect Effects 0.000 claims description 11
- 238000000034 method Methods 0.000 claims description 4
- 238000000926 separation method Methods 0.000 description 8
- 210000003323 beak Anatomy 0.000 description 7
- 210000003462 vein Anatomy 0.000 description 4
- 238000007792 addition Methods 0.000 description 3
- 238000002485 combustion reaction Methods 0.000 description 3
- 239000000463 material Substances 0.000 description 3
- 238000010257 thawing Methods 0.000 description 3
- 239000000843 powder Substances 0.000 description 2
- 230000001133 acceleration Effects 0.000 description 1
- 230000008033 biological extinction Effects 0.000 description 1
- 230000015572 biosynthetic process Effects 0.000 description 1
- 230000001427 coherent effect Effects 0.000 description 1
- 230000009977 dual effect Effects 0.000 description 1
- 230000037406 food intake Effects 0.000 description 1
- 238000005457 optimization Methods 0.000 description 1
- 230000002250 progressing effect Effects 0.000 description 1
- 230000005855 radiation Effects 0.000 description 1
- 230000002787 reinforcement Effects 0.000 description 1
- 238000007665 sagging Methods 0.000 description 1
- 238000000638 solvent extraction Methods 0.000 description 1
- 238000011144 upstream manufacturing Methods 0.000 description 1
Images
Classifications
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- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F01—MACHINES OR ENGINES IN GENERAL; ENGINE PLANTS IN GENERAL; STEAM ENGINES
- F01D—NON-POSITIVE DISPLACEMENT MACHINES OR ENGINES, e.g. STEAM TURBINES
- F01D25/00—Component parts, details, or accessories, not provided for in, or of interest apart from, other groups
- F01D25/02—De-icing means for engines having icing phenomena
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- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F01—MACHINES OR ENGINES IN GENERAL; ENGINE PLANTS IN GENERAL; STEAM ENGINES
- F01D—NON-POSITIVE DISPLACEMENT MACHINES OR ENGINES, e.g. STEAM TURBINES
- F01D25/00—Component parts, details, or accessories, not provided for in, or of interest apart from, other groups
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- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F01—MACHINES OR ENGINES IN GENERAL; ENGINE PLANTS IN GENERAL; STEAM ENGINES
- F01D—NON-POSITIVE DISPLACEMENT MACHINES OR ENGINES, e.g. STEAM TURBINES
- F01D9/00—Stators
- F01D9/02—Nozzles; Nozzle boxes; Stator blades; Guide conduits, e.g. individual nozzles
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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
- F05D2220/00—Application
- F05D2220/30—Application in turbines
- F05D2220/32—Application in turbines in gas turbines
- F05D2220/323—Application in turbines in gas turbines for aircraft propulsion, e.g. jet engines
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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
- F05D2230/00—Manufacture
- F05D2230/30—Manufacture with deposition of material
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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
- F05D2230/00—Manufacture
- F05D2230/30—Manufacture with deposition of material
- F05D2230/31—Layer deposition
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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
- F05D2230/00—Manufacture
- F05D2230/50—Building or constructing in particular ways
- F05D2230/53—Building or constructing in particular ways by integrally manufacturing a component, e.g. by milling from a billet or one piece construction
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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
- F05D2240/00—Components
- F05D2240/10—Stators
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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
- F05D2240/00—Components
- F05D2240/10—Stators
- F05D2240/12—Fluid guiding means, e.g. vanes
- F05D2240/128—Nozzles
Definitions
- the present invention relates to the field of turbomachines and more particularly to a system for de-icing an aeronautical turbomachine separation nozzle.
- the flow paths of the primary flow and of the secondary flow are separated downstream of the fan by a separation nozzle.
- the inlet of the low pressure compressor also commonly called “booster”
- IGV Inlet Guide Vane
- icing atmospheric conditions may be encountered by the turbomachine, in particular when the ambient temperature is sufficiently low and in the presence of high humidity. Under these conditions, ice may form on the splitter and inlet guide vanes. When this phenomenon occurs, it can lead to the partial or total obstruction of the primary vein, and to the ingestion of loose ice blocks in the primary vein.
- An obstruction of the primary vein results in an undersupply of the combustion chamber which can then go out or prevent the acceleration of the engine.
- these can damage the compressor located downstream and also lead to the extinction of the combustion chamber.
- techniques are known which consist in taking hot air from the primary stream at the level of a compressor and injecting it inside the separation nozzle.
- the hot air injected into the splitter nozzle can then travel through the nozzle to holes or grooves configured to inject the hot air into the primary stream which can also defrost the inlet guide vanes.
- the flow of hot air necessary to defrost the splitter is important. This bleed of hot air can reduce the performance and operability of the turbomachine.
- a known solution consists in reducing the volume inside the spout, so as to thus reduce the heat losses in the spout. It is thus known to add an annular deflector in the cavity of the spout. Such a deflector is described in the patent application EN 3051016 A1 . The deflector makes it possible to reduce the volume of the spout cavity and to direct the hot air towards the areas of interest to be defrosted.
- the document EP 2481893 A2 describes an annular divider for separating the airflow for combustion from the bypass airflow.
- the addition of a deflector or divider weighs down the nozzle, which results in an increase in the consumption of the turbine in operation.
- the invention relates to a separation nozzle between a primary flow and a secondary flow of a bypass turbomachine.
- the spout has a one-piece structure and includes an outer annular wall, an inner annular wall, a radial annular wall and an inner annular deflector, defining a first cavity between the outer annular wall and the inner annular deflector, and a second cavity between the inner annular ring, the radial annular wall and the inner annular baffle.
- the deflector makes it possible to reduce the interior volume of the spout in which the hot air circulates. This arrangement therefore makes it possible to reduce heat losses and thus to reduce the intake of hot air.
- the deflector helps guide hot air into the spout.
- the one-piece structure makes it possible to dispense with many connecting parts and therefore to reduce the mass of the spout compared to known devices.
- the mechanically coherent assembly formed by the one-piece structure can make it possible to refine all of the walls of the spout and therefore to further reduce its mass.
- the invention makes it possible to increase the efficiency of the defrosting of the separation nozzle without increasing the hot air intake in a pressurized part of the turbomachine, without increasing the mass of the nozzle.
- the outer annular wall may have at a junction region with the inner annular wall a series of radial holes.
- the spout may have at least one axial rib between the inner annular wall and the inner annular deflector.
- the spout may have a plurality of axial ribs each coplanar with an axis of revolution of the spout.
- the spout may have at least one radial rib between the radial annular wall and the internal annular deflector.
- the spout may have a plurality of radial ribs each coplanar with an axis of revolution of the spout.
- the spout may have at least one cavity formed at least partially in the radial annular wall.
- the radial annular wall may have a bore opening into the at least one cell.
- the radial annular wall may have at least one oblong opening suitable for receiving a nozzle opening into the second cavity.
- the invention relates to a rectifier for an aeronautical turbomachine, which has a one-piece structure produced by additive manufacturing, comprising a nozzle having: (i) the one-piece structure comprising an outer annular wall, an inner annular wall, an annular radial and an inner annular deflector, (ii) the first cavity between the outer annular wall and the inner annular deflector, (iii) the second cavity between the inner annular wall, the radial annular wall and the inner annular deflector.
- the invention relates to a method for manufacturing a rectifier of an aeronautical turbomachine having a one-piece structure produced by additive manufacturing and comprising a nozzle having: (i) a one-piece structure comprising an outer annular wall, an annular wall interior, a radial annular wall and an internal annular deflector, (ii) a first cavity between the external annular wall and the internal annular deflector, (iii) a second cavity between the internal annular wall, the radial annular wall and the internal annular deflector .
- the method may include a step of manufacturing the spout starting with the radial annular wall.
- the invention relates to a splitter nozzle 1 for an aeronautical bypass turbomachine.
- Spout 1 separates the primary flow from the secondary flow as explained. It is intended to be positioned downstream of a fan (shown partially in section on the figure 1 ) of the turbomachine to form a separation between annular flow channels (ie veins) of the primary flow and the secondary flow coming from the fan.
- the nozzle 1 is an integral part of a rectifier 10 of the primary flow. Beak 1 and rectifier 10 are parts of revolution. It is thus understood that the spout 1 forms a substantially cylindrical element inside which the primary flow passes, and outside (around) which the secondary flow passes.
- an axis of revolution X of the rectifier 10 (and of the nozzle 1) is defined, and a radial axis Z, substantially perpendicular to the axis of revolution X, represented on the figures 1 and 2 .
- the straightener 10 comprises successively: an inner shroud 101, blades 102 and the nozzle 1.
- the spout 1 also has a one-piece structure.
- the spout 1 is preferably made by additive manufacturing.
- the spout 1 comprises an outer annular wall 12, an inner annular wall 13, a radial annular wall 14 and an internal annular deflector 16.
- a section of the spout 1 according to a plane XoZ substantially has the shape of a right triangle whose sides are the outer annular wall 12, the inner annular wall 13, and the radial annular wall 14, and whose outer annular wall 12 is the hypotenuse.
- the inner annular wall 13 and the outer annular wall 12 meet in the upstream direction (i.e. towards the fan) to form the "nozzle" functionally speaking.
- a junction region of the outer annular wall 12 and the inner annular wall 13 is defined.
- the outer annular wall 12 is preferably slightly curvilinear, in particular curved (convex) so as to improve the overall aerodynamics of the slat 1. Between the outer annular wall 12 and the internal annular deflector 16, the slat 1 has a first cavity 17.
- the spout 1 has a second cavity 18.
- the spout 1 is substantially divided in two by the internal annular deflector 16, this defining the two cavities 17, 18. It is in fact understood that the spout 1 is substantially hollow (with the exception of a zone in the vicinity of the radial annular wall 14, see below).
- the internal annular deflector 16 extends for this from the region of junction of the outer annular wall 12 and of the inner annular wall 13 to a region of junction of the outer annular wall 12 and of the radial annular wall 14. It preferably has a bent shape so that the first cavity 17 occupies most of the volume of the spout 1, the second cavity 18 essentially following the radial annular wall 14 then the inner annular wall 13.
- the second cavity has a first part 18a between the inner annular wall 13 and the internal annular deflector 16, and a second part 18b between the radial annular wall 14 and the internal annular deflector 16. It is specified that the two parts 18a and 18b of the second cavity 18 communicate with each other and define a single volume.
- the inner annular wall 13 has at the junction region of the outer annular wall 12 and the inner annular wall 13 a series of holes 20, in particular radial (ie opening in the direction of the longitudinal axis).
- the radial holes 20 make it possible to optimally evacuate the hot air blown into the second cavity 18 at the end of the latter, in particular to preheat the air entering at the level blades 102 in the primary stream, so as to de-ice the nozzle 1 and the blades 102.
- the nozzle 1 comprises a series of axial ribs 22 between the internal annular wall 13 and the internal annular deflector 16, extending in the first part 18a of the second cavity 18.
- the axial ribs 22 are each coplanar with the axis of revolution X, ie along the plane XoZ.
- the spout 1 comprises a series of radial ribs 24 between the radial annular wall 14 and the internal annular deflector 16, extending into the second part 18b of the second cavity 18. It is specified that the radial ribs 24 are each coplanar with the axis of revolution X, ie again according to the plane XoZ.
- each axial rib 22 can be coplanar with a radial rib 24. It is understood that the axial and radial ribs 22, 24 define azimuthal partitionings (that is to say sectors) of the second cavity 18, but incomplete (that is to say that the ribs 22 and 24 nevertheless remain spaced apart and advantageously do not touch), so that at a junction region of the annular wall interior 13 and of the radial annular wall 14 (ie at the junction of the first and second part of the second cavity...) the second cavity 18 is not ribbed, allowing azimuthal communication. Similarly, the axial ribs 22 do not go as far as the end of the second cavity, so as to also allow at the level of the holes 20 an azimuthal communication.
- the axial 22 and radial 24 ribs have a dual function of mechanical reinforcement and of guiding the flow of hot air.
- the axial 22 and radial 24 ribs make it possible to stiffen the beak 1, which makes it possible to avoid any sagging of the beak 1.
- the axial 22 and radial 24 ribs advantageously make it possible to optimize the mass of the beak 1 by allowing refine the thickness of the internal annular deflector 16, of the radial annular wall 14 and of the internal annular wall 13. It is understood that this mass optimization is based on a compromise between the mass contribution of the ribs and the reduction in thickness walls and the deflector they allow.
- the axial 22 and radial 24 ribs make it possible to guarantee the good mechanical strength of the spout 1 during manufacture.
- the axial 22 and radial 24 ribs make it possible to guide the flow of hot air to defrost the spout 1.
- spout 1 advantageously has a plurality of cavities 28a, 28b, 28c.
- the spout 1 comprises three cells 28a, 28b and 28c.
- a first cell 28a can be arranged in a corner region of the outer annular wall 12 and the radial annular wall 14. It is notable that according to the embodiment presented here, the first cell 28a has a kidney-shaped section in the plane XoZ (ie has substantially a bean-shaped section in the XoZ plane).
- a second and a third cell 28b and 28c are located in a corner region of the inner annular wall 13 and of the radial annular wall 14.
- cells 28a, 28b, 28c correspond to material relief regions.
- the cells 28a, 28b, 28c correspond to areas in which no material is deposited because this does not will not present any added value in terms of mechanical resistance (whereas this would necessarily add mass).
- the production of the beak 1 in additive manufacturing allows obtaining a one-piece structure, but also makes it possible to optimize the geometry of the beak 1 to have the best ratio between the mass and the resistance.
- the cells 28a, 28b, 28c would be very difficult to produce other than by additive manufacturing.
- the radial annular wall 14 may have holes 30 opening into the first and second cells 28a and 28b.
- the holes 30 advantageously make it possible to evacuate part of the powder resulting from the additive manufacturing of the spout 1.
- the radial annular wall 14 may have oblong openings 33 adapted to each accommodate a nozzle opening into the second cavity 18 to blow hot air therein.
- the radial wall 14 may have a plurality of fixing holes 35.
- the rectifier 10 is manufactured using an additive manufacturing process.
- the rectifier 10 is manufactured by successive additions of molten powder layer by layer. As explained above, this manufacturing method makes it possible to obtain a one-piece part having a specific geometry.
- the rectifier 10 is manufactured starting with the radial annular wall 14 of the spout, in a direction of progression (i.e. of addition of the layers of material) substantially parallel to the axis of revolution X.
- a nozzle (not shown) can be connected to each oblong opening 33.
- the nozzles can blow hot air into the second cavity 18.
- the internal annular deflector 16 makes it possible to reduce the interior volume of the spout 1 by dividing it into two cavities.
- the volume in which the hot air circulates is reduced, which reduces the heat losses in the nozzle 1 and makes it possible to reduce the intake of hot air.
- the internal annular deflector 16 makes it possible to direct the hot air towards the areas of interest to be defrosted.
- the caloric radiation of the hot air inside the spout 1 makes it possible to defrost the spout 1.
- the hot air circulating in the second cavity 18 is then diffused through the radial holes 20 to reach the primary stream and defrost the blades 102.
- the invention makes it possible to effectively defrost the slat without thereby increasing the intake of hot air from a pressurized part of the turbomachine and without increasing the mass of the slat.
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- Engineering & Computer Science (AREA)
- Mechanical Engineering (AREA)
- General Engineering & Computer Science (AREA)
- Structures Of Non-Positive Displacement Pumps (AREA)
- Turbine Rotor Nozzle Sealing (AREA)
Description
La présente invention concerne, le domaine des turbomachines et plus particulièrement, un système de dégivrage d'un bec de séparation de turbomachine aéronautique.The present invention relates to the field of turbomachines and more particularly to a system for de-icing an aeronautical turbomachine separation nozzle.
Dans une turbomachine aéronautique du type à double corps et double flux, les veines d'écoulement du flux primaire et du flux secondaire sont séparées en aval de la soufflante par un bec de séparation. Au sein de la veine primaire, à l'entrée du compresseur basse pression (aussi couramment appelé « booster »), se trouvent un ensemble d'aubes directrices d'entrée fixes (aussi appelées IGV pour « Inlet Guide Vane »). Dans certaines phases de vol et au sol, des conditions atmosphériques givrantes peuvent être rencontrées par la turbomachine, notamment lorsque la température ambiante est suffisamment basse et en présence d'une humidité élevée. Dans ces conditions, de la glace peut se former sur le bec de séparation et les aubes directrices d'entrée. Lorsque ce phénomène se produit, il peut conduire à l'obstruction partielle ou totale de la veine primaire, et à l'ingestion de blocs de glace détachés dans la veine primaire. Une obstruction de la veine primaire entraîne une sous-alimentation de la chambre de combustion qui peut alors s'éteindre ou empêcher l'accélération du moteur. Dans le cas du détachement de blocs de glace, ces derniers peuvent endommager le compresseur situé à l'aval et conduire également à l'extinction de la chambre de combustion. Pour éviter la formation de glace sur le bec de séparation, on connait des techniques consistant à venir prélever de l'air chaud dans la veine primaire au niveau d'un compresseur et à l'injecter à l'intérieur du bec de séparation. L'air chaud injecté dans le bec de séparation peut ensuite cheminer dans le bec jusqu'à des perçages ou des rainures configurées pour injecter l'air chaud dans la veine primaire qui peut dégivrer également les aubes directrices d'entrée. Le débit d'air chaud nécessaire pour dégivrer le bec de séparation est important. Ce prélèvement d'air chaud peut réduire les performances et l'opérabilité de la turbomachine.In an aeronautical turbomachine of the double body and double flow type, the flow paths of the primary flow and of the secondary flow are separated downstream of the fan by a separation nozzle. Within the primary stream, at the inlet of the low pressure compressor (also commonly called “booster”), there is a set of fixed inlet guide vanes (also called IGV for “Inlet Guide Vane”). In certain phases of flight and on the ground, icing atmospheric conditions may be encountered by the turbomachine, in particular when the ambient temperature is sufficiently low and in the presence of high humidity. Under these conditions, ice may form on the splitter and inlet guide vanes. When this phenomenon occurs, it can lead to the partial or total obstruction of the primary vein, and to the ingestion of loose ice blocks in the primary vein. An obstruction of the primary vein results in an undersupply of the combustion chamber which can then go out or prevent the acceleration of the engine. In the case of the detachment of blocks of ice, these can damage the compressor located downstream and also lead to the extinction of the combustion chamber. To prevent the formation of ice on the separation nozzle, techniques are known which consist in taking hot air from the primary stream at the level of a compressor and injecting it inside the separation nozzle. The hot air injected into the splitter nozzle can then travel through the nozzle to holes or grooves configured to inject the hot air into the primary stream which can also defrost the inlet guide vanes. The flow of hot air necessary to defrost the splitter is important. This bleed of hot air can reduce the performance and operability of the turbomachine.
Il est apparu souhaitable de pouvoir augmenter l'efficacité du dégivrage du bec.It appeared desirable to be able to increase the efficiency of defrosting the nozzle.
Une solution connue consiste à réduire le volume à l'intérieur du bec, de sorte à ainsi réduire les pertes de chaleur dans le bec. Il est ainsi connu d'ajouter un déflecteur annulaire dans la cavité du bec. Un tel déflecteur est décrit dans la demande de brevet
Il serait donc souhaitable de pouvoir augmenter l'efficacité du dégivrage du bec de séparation sans augmenter pour autant le prélèvement d'air chaud dans une partie pressurisée de la turbomachine, sans augmenter la masse du bec.It would therefore be desirable to be able to increase the effectiveness of the defrosting of the separation nozzle without increasing the hot air intake in a pressurized part of the turbomachine, without increasing the mass of the nozzle.
Selon un premier aspect, l'invention concerne un bec de séparation entre un flux primaire et un flux secondaire d'une turbomachine à double flux. Le bec présente une structure monobloc et comprend une paroi annulaire extérieure, une paroi annulaire intérieure, une paroi annulaire radiale et un déflecteur annulaire interne, définissant une première cavité entre la paroi annulaire extérieure et le déflecteur annulaire interne, et une deuxième cavité entre la paroi annulaire intérieure, la paroi annulaire radiale et le déflecteur annulaire interne.According to a first aspect, the invention relates to a separation nozzle between a primary flow and a secondary flow of a bypass turbomachine. The spout has a one-piece structure and includes an outer annular wall, an inner annular wall, a radial annular wall and an inner annular deflector, defining a first cavity between the outer annular wall and the inner annular deflector, and a second cavity between the inner annular ring, the radial annular wall and the inner annular baffle.
D'une manière particulièrement avantageuse, le déflecteur permet de réduire le volume intérieur du bec dans lequel l'air chaud circule. Cette disposition permet donc de diminuer les pertes caloriques et ainsi de réduire le prélèvement d'air chaud. En outre, le déflecteur permet de guider l'air chaud dans le bec.In a particularly advantageous manner, the deflector makes it possible to reduce the interior volume of the spout in which the hot air circulates. This arrangement therefore makes it possible to reduce heat losses and thus to reduce the intake of hot air. In addition, the deflector helps guide hot air into the spout.
En sus, La structure monobloc permet de s'affranchir de nombreuses pièces de liaison et donc de réduire la masse du bec par rapport au dispositifs connus. En outre, l'ensemble mécaniquement cohérent que constitue la structure monobloc peut autoriser d'affiner l'ensemble des parois du bec et donc d'en diminuer encore la masse.In addition, the one-piece structure makes it possible to dispense with many connecting parts and therefore to reduce the mass of the spout compared to known devices. In addition, the mechanically coherent assembly formed by the one-piece structure can make it possible to refine all of the walls of the spout and therefore to further reduce its mass.
Ainsi, l'invention permet augmenter l'efficacité du dégivrage du bec de séparation sans augmenter pour autant le prélèvement d'air chaud dans une partie pressurisée de la turbomachine, sans augmenter la masse du bec.Thus, the invention makes it possible to increase the efficiency of the defrosting of the separation nozzle without increasing the hot air intake in a pressurized part of the turbomachine, without increasing the mass of the nozzle.
La paroi annulaire extérieure peut présenter au niveau d'une région de jonction avec la paroi annulaire intérieure une série de trous radiaux.The outer annular wall may have at a junction region with the inner annular wall a series of radial holes.
Le bec peut présenter au moins une nervure axiale entre la paroi annulaire intérieure et le déflecteur annulaire interne.The spout may have at least one axial rib between the inner annular wall and the inner annular deflector.
Selon une disposition particulière, le bec peut présenter une pluralité de nervures axiales chacune coplanaire avec un axe de révolution du bec.According to a particular arrangement, the spout may have a plurality of axial ribs each coplanar with an axis of revolution of the spout.
Le bec peut présenter au moins une nervure radiale entre la paroi annulaire radiale et le déflecteur annulaire interne.The spout may have at least one radial rib between the radial annular wall and the internal annular deflector.
Selon une disposition particulière, le bec peut présenter une pluralité de nervures radiales chacune coplanaire avec un axe de révolution du bec.According to a particular arrangement, the spout may have a plurality of radial ribs each coplanar with an axis of revolution of the spout.
Le bec peut présenter au moins une alvéole ménagée au moins partiellement dans la paroi annulaire radiale.The spout may have at least one cavity formed at least partially in the radial annular wall.
La paroi annulaire radiale peut présenter un perçage débouchant dans l'au moins une alvéole.The radial annular wall may have a bore opening into the at least one cell.
La paroi annulaire radiale peut présenter au moins une ouverture oblongue adaptée pour accueillir une buse débouchant dans la deuxième cavité.The radial annular wall may have at least one oblong opening suitable for receiving a nozzle opening into the second cavity.
Selon un deuxième aspect, l'invention concerne un redresseur pour une turbomachine aéronautique, qui présente une structure monobloc réalisée par fabrication additive, comprenant un bec présentant : (i) la structure monobloc comprenant une paroi annulaire extérieure, une paroi annulaire intérieure, une paroi annulaire radiale et un déflecteur annulaire interne, (ii) la première cavité entre la paroi annulaire extérieure et le déflecteur annulaire interne, (iii) la deuxième cavité entre la paroi annulaire intérieure, la paroi annulaire radiale et le déflecteur annulaire interne.According to a second aspect, the invention relates to a rectifier for an aeronautical turbomachine, which has a one-piece structure produced by additive manufacturing, comprising a nozzle having: (i) the one-piece structure comprising an outer annular wall, an inner annular wall, an annular radial and an inner annular deflector, (ii) the first cavity between the outer annular wall and the inner annular deflector, (iii) the second cavity between the inner annular wall, the radial annular wall and the inner annular deflector.
Selon une troisième aspect l'invention concerne un procédé de fabrication d'un redresseur d'une turbomachine aéronautique présentant une structure monobloc réalisée par fabrication additive et comprenant un bec présentant : (i) une structure monobloc comprenant une paroi annulaire extérieure, une paroi annulaire intérieure, une paroi annulaire radiale et un déflecteur annulaire interne, (ii) une première cavité entre la paroi annulaire extérieure et le déflecteur annulaire interne, (iii) une deuxième cavité entre la paroi annulaire intérieure, la paroi annulaire radiale et le déflecteur annulaire interne.According to a third aspect, the invention relates to a method for manufacturing a rectifier of an aeronautical turbomachine having a one-piece structure produced by additive manufacturing and comprising a nozzle having: (i) a one-piece structure comprising an outer annular wall, an annular wall interior, a radial annular wall and an internal annular deflector, (ii) a first cavity between the external annular wall and the internal annular deflector, (iii) a second cavity between the internal annular wall, the radial annular wall and the internal annular deflector .
Le procédé peut comprendre une étape de fabrication du bec en commençant par la paroi annulaire radiale.The method may include a step of manufacturing the spout starting with the radial annular wall.
D'autres caractéristiques et avantages de l'invention ressortiront encore de la description qui suit, laquelle est purement illustrative et non limitative, et doit être lue en regard des figures annexées sur lesquelles :
- La
figure 1 est une vue en coupe partielle d'un bec et d'une aube de redresseur ; - La
figure 2 est une vue en coupe d'un bec selon l'invention ; - La
figure 3 est une vue en perspective partielle d'un bec et d'une aube de redresseur ; - La
figure 4 est une vue en perspective partielle d'une paroi radiale annulaire.
- There
figure 1 is a partial sectional view of a stator nozzle and vane; - There
picture 2 is a sectional view of a spout according to the invention; - There
picture 3 is a partial perspective view of a stator nozzle and vane; - There
figure 4 is a partial perspective view of an annular radial wall.
En référence aux
Selon le mode de réalisation ici présenté le bec 1 fait partie intégrante d'un redresseur 10 du flux primaire. Le bec 1 et le redresseur 10 sont des pièces de révolution. On comprend ainsi que le bec 1 forme un élément sensiblement cylindrique à l'intérieur duquel passe le flux primaire, et à l'extérieur (autour) duquel passe le flux secondaire. Pour la suite de la description, on définit un axe de révolution X du redresseur 10 (et du bec 1), et un axe radial Z, sensiblement perpendiculaire à l'axe de révolution X, représentés sur les
Selon une direction radiale Z progressant de l'intérieur (au plus près de l'axe de révolution X) vers l'extérieur (au plus loin de l'axe de révolution X), le redresseur 10 comprend successivement : une virole intérieure 101, des aubes 102 et le bec 1.In a radial direction Z progressing from the inside (closest to the axis of revolution X) outwards (farthest from the axis of revolution X), the
D'une manière particulièrement avantageuse, le bec 1 présente également une structure monobloc. Tel que cela sera décrit ci-après, le bec 1 est préférentiellement réalisé en fabrication additive.In a particularly advantageous manner, the spout 1 also has a one-piece structure. As will be described below, the spout 1 is preferably made by additive manufacturing.
Le bec 1 comprend une paroi annulaire extérieure 12, une paroi annulaire intérieure 13, une paroi annulaire radiale 14 et un déflecteur annulaire interne 16. En parcourant le bec 1 selon ladite direction radiale Z, on rencontre successivement la paroi intérieure 13, le déflecteur annulaire interne 16 et la paroi annulaire extérieure 12. Une section du bec 1 selon un plan XoZ (comme l'on voit sur les
La paroi annulaire intérieure 13 et la paroi annulaire extérieure 12 se rejoignent en allant vers l'amont (i.e. vers la soufflante) pour former le « bec » fonctionnellement parlant. On définit une région de jonction de la paroi annulaire extérieure 12 et de la paroi annulaire intérieure 13.The inner
La paroi annulaire extérieure 12 est préférentiellement légèrement curviligne, en particulier bombée (convexe) de sorte à améliorer l'aérodynamique globale du bec 1. Entre la paroi annulaire extérieure 12 et le déflecteur annulaire interne 16, le bec 1 présente une première cavité 17.The outer
Entre la paroi annulaire intérieure 13, la paroi annulaire radiale 14 et le déflecteur annulaire interne 16, le bec 1 présente une deuxième cavité 18.Between the inner
En d'autres termes, le bec 1 est sensiblement divisé en deux par le déflecteur annulaire interne 16, cela définissant les deux cavités 17, 18. On comprend en effet que le bec 1 est sensiblement creux (à l'exception d'une zone au voisinage de la paroi annulaire radiale 14, voir plus loin).In other words, the spout 1 is substantially divided in two by the internal
Le déflecteur annulaire interne 16 s'étend pour cela de la région de jonction de la paroi annulaire extérieure 12 et de la paroi annulaire intérieure 13 à une région de jonction la paroi annulaire extérieure 12 et de la paroi annulaire radiale 14. Il présente préférentiellement une forme coudée de sorte que la première cavité 17 occupe la majeure partie du volume du bec 1, la seconde cavité 18 suivant essentiellement la paroi annulaire radiale 14 puis la paroi annulaire intérieure 13. La seconde cavité présente une première partie 18a entre la paroi annulaire intérieure 13 et le déflecteur annulaire interne 16, et une seconde partie 18b entre la paroi annulaire radiale 14 et le déflecteur annulaire interne 16. Il est précisé que les deux parties 18a et 18b de la seconde cavité 18 communiquent entre elles et définissent un seul volume.The internal
En référence notamment aux
Ici par « axial » et « radial » on entend simplement leur direction principale d'extension. En sus, chaque nervure axiale 22 peut être coplanaire avec une nervure radiale 24. On comprend que les nervures axiales et radiales 22, 24 définissent des cloisonnement azimutaux (c'est-à-dire des secteurs) de la deuxième cavité 18, mais incomplets (c'est-à-dire que les nervures 22 et 24 restent néanmoins espacées et avantageusement ne se touchent pas), de sorte qu'au niveau d'une région de jonction de la paroi annulaire intérieure 13 et de la paroi annulaire radiale 14 (i.e. à la jonction des première et deuxième partie de la deuxième cavité...) la deuxième cavité 18 ne soit pas nervurée, permettant une communication azimutale. Similairement, les nervures axiales 22 ne vont pas jusqu'à l'extrémité de la deuxième cavité, de sorte à permettre également au niveau des trous 20 une communication azimutale.Here by “axial” and “radial” is simply meant their main direction of extension. In addition, each
D'une manière particulièrement avantageuse, les nervures axiale 22 et radiales 24 ont une double fonction de renfort mécanique et de guidage du flux d'air chaud.In a particularly advantageous manner, the axial 22 and radial 24 ribs have a dual function of mechanical reinforcement and of guiding the flow of hot air.
En effet, les nervures axiales 22 et radiales 24 permettent de rigidifier le bec 1, ce qui permet d'éviter un éventuel affaissement du bec 1. Les nervures axiales 22 et radiales 24 permettent avantageusement d'optimiser la masse du bec 1 en permettant d'affiner l'épaisseur du déflecteur annulaire interne 16, de la paroi annulaire radiale 14 et de la paroi annulaire intérieur 13. Il est entendu que cette optimisation massique repose sur un compromis entre l'apport en masse des nervures et la réduction d'épaisseur des parois et du déflecteur qu'elles permettent. De plus, lors de la fabrication du bec 1, selon un procédé de fabrication additive, les nervures axiales 22 et radiales 24 permettent de garantir la bonne tenue mécanique du bec 1 en cours de fabrication. Tel que cela sera détaillé, en fonctionnement, les nervures axiales 22 et radiales 24 permettent de guider les flux d'air chaud pour dégivrer le bec 1.Indeed, the axial 22 and radial 24 ribs make it possible to stiffen the beak 1, which makes it possible to avoid any sagging of the beak 1. The axial 22 and radial 24 ribs advantageously make it possible to optimize the mass of the beak 1 by allowing refine the thickness of the internal
Par ailleurs, comme on peut l'observer notamment sur la
Ainsi, il est remarquable que la réalisation du bec 1 en fabrication additive permet l'obtention d'une structure monobloc, mais permet aussi d'optimiser la géométrie du bec 1 pour avoir le meilleur rapport entre la masse et la résistance. En l'espèce, les alvéoles 28a, 28b, 28c seraient très difficilement réalisables autrement qu'en fabrication additive.Thus, it is remarkable that the production of the beak 1 in additive manufacturing allows obtaining a one-piece structure, but also makes it possible to optimize the geometry of the beak 1 to have the best ratio between the mass and the resistance. In this case, the
La paroi annulaire radiale 14 peut présenter des perçages 30 débouchant dans les première et deuxième alvéoles 28a et 28b. Les perçages 30 permettent avantageusement d'évacuer une partie de la poudre résultant de la fabrication additive du bec 1.The radial
Tel que représenté sur la
De plus, la paroi radiale 14 peut présenter une pluralité de perçages de fixation 35.In addition, the
D'une manière particulièrement avantageuse, le redresseur 10 est fabriqué selon un procédé de fabrication additive.In a particularly advantageous manner, the
Ainsi, le redresseur 10 est fabriqué par apports successifs de poudre fondue couche par couche. Comme exposé précédemment, ce procédé de fabrication permet d'obtenir une pièce monobloc présentant une géométrie spécifique.Thus, the
D'une manière préférentielle, le redresseur 10 est fabriqué en commençant par la paroi annulaire radiale 14 du bec, selon une direction de progression (i. e. d'ajout des couches de matière) sensiblement parallèle à l'axe de révolution X.Preferably, the
Une buse (non représentée) peut être connectée à chaque ouverture oblongue 33. Les buses peuvent insuffler de l'air chaud dans la deuxième cavité 18.A nozzle (not shown) can be connected to each
D'une manière particulièrement avantageuse, le déflecteur annulaire interne 16 permet de réduire le volume intérieur du bec 1 en le divisant en deux cavités. Ainsi, le volume dans lequel l'air chaud circule est réduit, ce qui diminue les pertes de chaleur dans le bec 1 et permet de réduire prélèvement d'air chaud. En outre, le déflecteur annulaire interne 16 permet d'orienter l'air chaud vers les zones d'intérêt à dégivrer.In a particularly advantageous manner, the internal
Le rayonnement calorique de l'air chaud à l'intérieur du bec 1 permet de dégivrer le bec 1.The caloric radiation of the hot air inside the spout 1 makes it possible to defrost the spout 1.
L'air chaud circulant dans la deuxième cavité 18 est ensuite diffusé par les trous radiaux 20 pour rejoindre la veine primaire et dégivrer les aubes 102.The hot air circulating in the
Ainsi, l'invention permet de dégivrer efficacement le bec sans augmenter pour autant le prélèvement d'air chaud dans une partie pressurisée de la turbomachine et sans augmenter la masse du bec.Thus, the invention makes it possible to effectively defrost the slat without thereby increasing the intake of hot air from a pressurized part of the turbomachine and without increasing the mass of the slat.
Claims (12)
- Spout (1) for separating a primary flow from a secondary flow in a turbomachine with double flow, the spout (1) being characterized in that it has a one-piece structure comprising an outer annular wall (12), an inner annular wall (13), a radial annular wall (14) and an inner annular deflector (16) defining a first cavity (17) between the outer annular wall (12) and the inner annular deflector (16), and a second cavity (18) between the inner annular wall (13), the radial annular wall (14) and the inner annular deflector (16).
- The spout (1) of claim 1, wherein the outer annular wall (12) has at a region of junction with the inner annular wall (13) a series of radial holes (20).
- The spout (1) according to one of claims 1 or 2, having at least one axial rib (22) between the inner annular wall (13) and the inner annular deflector (16).
- The spout (1) of claim 3 having a plurality of axial ribs (22) each coplanar with an axis of revolution (X) of the spout (1).
- The spout (1) according to any one of claims 1 to 4, having at least one radial rib (24) between the radial annular wall (14) and the inner annular deflector (16).
- The spout (1) of claim 5, having a plurality of radial ribs (24) each coplanar with an axis of revolution (X) of the spout (1).
- The spout (1) according to any one of claims 1 to 6, having at least one cell (28a, 28b, 28c) formed at least partially in the radial annular wall (14).
- The spout (1) according to claim 7, wherein the radial annular wall (14) has a bore (30) opening into the at least one cell (28a, 28b).
- The spout (1) according to any one of claims 1 to 8, wherein the radial annular wall (14) has at least one oblong opening (33) adapted to receive a nozzle opening into the second cavity (18).
- Rectifier (10) for an aeronautical turbomachine, characterized in that it has a one-piece structure produced by additive manufacturing, comprising a spout (1) according to claim 1.
- A method of manufacturing a rectifier (10) for an aeronautical turbomachine having a one-piece structure produced by additive manufacturing and comprising a spout (1) according to claim 1.
- A method according to claim 11 comprising a step of manufacturing the spout (1) starting with the radial annular wall (14).
Applications Claiming Priority (2)
Application Number | Priority Date | Filing Date | Title |
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FR1904065A FR3095230B1 (en) | 2019-04-16 | 2019-04-16 | DEFROST DEVICE |
PCT/EP2020/060453 WO2020212344A1 (en) | 2019-04-16 | 2020-04-14 | Separation nozzle for aeronautic turbomachine |
Publications (2)
Publication Number | Publication Date |
---|---|
EP3956547A1 EP3956547A1 (en) | 2022-02-23 |
EP3956547B1 true EP3956547B1 (en) | 2023-06-07 |
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ID=67956957
Family Applications (1)
Application Number | Title | Priority Date | Filing Date |
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EP20716855.0A Active EP3956547B1 (en) | 2019-04-16 | 2020-04-14 | Splitter for a turbofan engine |
Country Status (5)
Country | Link |
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US (2) | US11982195B2 (en) |
EP (1) | EP3956547B1 (en) |
CN (1) | CN113795650B (en) |
FR (1) | FR3095230B1 (en) |
WO (1) | WO2020212344A1 (en) |
Families Citing this family (1)
Publication number | Priority date | Publication date | Assignee | Title |
---|---|---|---|---|
FR3131939B1 (en) | 2022-01-18 | 2024-01-12 | Safran Aircraft Engines | AXIAL TURBOMACHINE SEPARATION NOZZLE INCLUDING DEFROST AIR FLOW PASSAGE EXTENDING TO THE RECTIFIER |
Family Cites Families (14)
Publication number | Priority date | Publication date | Assignee | Title |
---|---|---|---|---|
US4860534A (en) * | 1988-08-24 | 1989-08-29 | General Motors Corporation | Inlet particle separator with anti-icing means |
US6561760B2 (en) * | 2001-08-17 | 2003-05-13 | General Electric Company | Booster compressor deicer |
US6725645B1 (en) * | 2002-10-03 | 2004-04-27 | General Electric Company | Turbofan engine internal anti-ice device |
US8205426B2 (en) * | 2006-07-31 | 2012-06-26 | General Electric Company | Method and apparatus for operating gas turbine engines |
US9309781B2 (en) * | 2011-01-31 | 2016-04-12 | General Electric Company | Heated booster splitter plenum |
EP2505789B1 (en) * | 2011-03-30 | 2016-12-28 | Safran Aero Boosters SA | Gaseous flow separator with device for thermal-bridge defrosting |
CN104675524B (en) * | 2013-11-27 | 2017-01-18 | 中航商用航空发动机有限责任公司 | Shunting ring, engine anti-icer and turbofan engine |
BE1022957B1 (en) * | 2015-04-20 | 2016-10-21 | Techspace Aero S.A. | AXIAL TURBOMACHINE COMPRESSOR DEGIVERANT SEPARATING SPOUT |
BE1023289B1 (en) * | 2015-07-17 | 2017-01-24 | Safran Aero Boosters S.A. | AXIAL TURBOMACHINE LOW PRESSURE COMPRESSOR SEPARATION SPOUT WITH ANNULAR DEFROST CONDUIT |
BE1023354B1 (en) * | 2015-08-13 | 2017-02-13 | Safran Aero Boosters S.A. | AXIAL TURBOMACHINE COMPRESSOR DEGIVERANT SEPARATING SPOUT |
BE1023531B1 (en) * | 2015-10-15 | 2017-04-25 | Safran Aero Boosters S.A. | AXIAL TURBOMACHINE COMPRESSOR SEPARATION SEPARATION DEVICE DEGIVER DEVICE |
FR3051016B1 (en) * | 2016-05-09 | 2020-03-13 | Safran Aircraft Engines | DEVICE FOR DEFROSTING A SPOUT FOR AERONAUTICAL TURBOMACHINE |
BE1024684B1 (en) * | 2016-10-21 | 2018-05-25 | Safran Aero Boosters S.A. | AXIAL TURBOMACHINE COMPRESSOR DEGIVER |
GB201705734D0 (en) * | 2017-04-10 | 2017-05-24 | Rolls Royce Plc | Flow splitter |
-
2019
- 2019-04-16 FR FR1904065A patent/FR3095230B1/en active Active
-
2020
- 2020-04-14 CN CN202080034311.3A patent/CN113795650B/en active Active
- 2020-04-14 WO PCT/EP2020/060453 patent/WO2020212344A1/en unknown
- 2020-04-14 US US17/604,170 patent/US11982195B2/en active Active
- 2020-04-14 EP EP20716855.0A patent/EP3956547B1/en active Active
-
2024
- 2024-01-31 US US18/428,916 patent/US20240263564A1/en active Pending
Also Published As
Publication number | Publication date |
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FR3095230A1 (en) | 2020-10-23 |
US20220205366A1 (en) | 2022-06-30 |
US20240263564A1 (en) | 2024-08-08 |
FR3095230B1 (en) | 2021-03-19 |
WO2020212344A1 (en) | 2020-10-22 |
EP3956547A1 (en) | 2022-02-23 |
US11982195B2 (en) | 2024-05-14 |
CN113795650A (en) | 2021-12-14 |
CN113795650B (en) | 2023-04-07 |
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