EP1329639A1 - Centripetal air bleed device - Google Patents

Centripetal air bleed device Download PDF

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Publication number
EP1329639A1
EP1329639A1 EP03290061A EP03290061A EP1329639A1 EP 1329639 A1 EP1329639 A1 EP 1329639A1 EP 03290061 A EP03290061 A EP 03290061A EP 03290061 A EP03290061 A EP 03290061A EP 1329639 A1 EP1329639 A1 EP 1329639A1
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EP
European Patent Office
Prior art keywords
air
compressor
gap
groove
compressor according
Prior art date
Legal status (The legal status is an assumption and is not a legal conclusion. Google has not performed a legal analysis and makes no representation as to the accuracy of the status listed.)
Granted
Application number
EP03290061A
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German (de)
French (fr)
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EP1329639B1 (en
Inventor
Antoine Robert Alain Brunet
Patrick Pasquis
Alexandre Jean-Claude Auguste Roy
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Safran Aircraft Engines SAS
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SNECMA Moteurs SA
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Publication of EP1329639A1 publication Critical patent/EP1329639A1/en
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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
    • F01D5/00—Blades; Blade-carrying members; Heating, heat-insulating, cooling or antivibration means on the blades or the members
    • F01D5/02—Blade-carrying members, e.g. rotors
    • F01D5/08—Heating, heat-insulating or cooling means
    • F01D5/085—Heating, heat-insulating or cooling means cooling fluid circulating inside the rotor
    • F01D5/087—Heating, heat-insulating or cooling means cooling fluid circulating inside the rotor in the radial passages of the rotor disc
    • 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
    • F04D29/26—Rotors specially for elastic fluids
    • F04D29/32—Rotors specially for elastic fluids for axial flow pumps
    • F04D29/321—Rotors specially for elastic fluids for axial flow pumps for axial flow compressors
    • 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
    • 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
    • F04D29/58—Cooling; Heating; Diminishing heat transfer
    • F04D29/582—Cooling; Heating; Diminishing heat transfer specially adapted for elastic fluid pumps
    • F04D29/584—Cooling; Heating; Diminishing heat transfer specially adapted for elastic fluid pumps cooling or heating the machine

Definitions

  • the invention relates to an axial compressor for a turbomachine equipped with a centripetal air sampling device in the vein of the compressor, this bleed air being intended for cooling the turbine, said compressor comprising two rings of movable blades which extend radially outward at the periphery of two discs consecutive assembled by an outer ferrule provided with holes and a fixed crown of straightening vanes arranged in the vein between said two crowns of movable blades, said holes serving as air inlets said sampling device and opening into an annular groove provided under the gap separating the inner platforms from the blades straighteners, from the rim of the upstream disc, said groove communicating with said vein through said interstice.
  • centripetal air sampling device arranged to the inside of the high pressure rotor, is to bring a flow of air taken in a compressor stage to the turbine stages to be cooled. It is important that the cooling air entering the blades of the high pressure turbine, subjected to high temperatures, has a sufficient pressure to allow the formation of an air film of protection around the turbine blades, and such a low temperature as possible.
  • the sampling device can include channels for sample taken from the upstream disc, as disclosed by FR 2 609 500 and FR 2 614 654, or collection tubes arranged in the annular cavity separating the two discs, as is disclosed by US 5,475,313.
  • the air flow taken from the vein enters the throat annular by the gap separating the inner platforms from the blades upstream disc rim straighteners in a direction substantially axial and then passes through the holes in the rotating shell.
  • the relative air velocities at the entry of the holes, by ratio to the spinning disc is relatively high, which results in an increase in the relative total air temperature in the holes and a significant pressure drop in this area. This elevation of temperature is obviously found in the air flow delivered in the turbine blades. The pressure drop results in a decrease of the sampled air flow.
  • the object of the invention is to propose easy means to implement and inexpensive which can significantly reduce the temperature of the air supplied to the high pressure turbine and reduce the pressure drops, all other things being equal.
  • the throat is equipped with fixed guide means which print on the air flow circulating in throat a centripetal vortex movement in the direction of rotation of the compressor, in order to decrease the relative speed of the air entering the holes in relation to said rotary holes.
  • the relative total air temperature in the holes is significantly lowered compared to the same temperature in a traditional compressor, which improves the cooling of turbine blades for the same flow rate, and increases their service life.
  • the pressure drops are also reduced, which improves the air flow rate compared to the state of the art, to identical holes and sampling devices and increases the rate overpressure in the turbine blades.
  • the set of two improvements obtained thanks to the invention reduces the air flow required for the cooling of the turbine blades, and thereby specific fuel consumption, for the same lifetime of blades of the turbine to be cooled.
  • Said guide means are arranged at least in part under the inner platforms of straightening vanes.
  • the means for guiding the air in the groove have a plurality of blade profiles regularly distributed around of the axis of rotation of the compressor.
  • the leading edges of the blade profiles extend at least in part into the gap.
  • the angle of attack of the profiles is determined according to the tangential velocity and the local radial velocity of the air passing through the gap.
  • the blading profiles increases the training coefficient of air in the throat, allowing for the same total temperature of air, to decrease the relative total temperature.
  • Improving the training coefficient thanks to the profiles of proposed blading is about 30% compared to the state of the technical, which corresponds to a decrease in the total temperature relative of about 40 ° C. This increases the lifespan of turbine blades in pairs, for the same flow rate.
  • FIG. 1 shows a compressor 1 of an axis turbomachine X according to the state of the art equipped with a sampling device centripetal 2.
  • This compressor 1 comprises an upstream disc 3 having at its periphery a first ring of movable blades 4 arranged in the vein 5, a downstream disc 6 having at its periphery a second crown of movable blades 7 offset axially in the vein 5, and a crown of straightening vanes 8 fixed arranged in the vein 5 between the first and second crown of movable blades.
  • the upstream disc 3 and the downstream disc 6 are interconnected by an outer shell 9 provided with a sealing labyrinth 10 cooperating with the inner face of the inner platforms 11 of the blades straighteners 8.
  • a groove 12 is formed under the gap 13 which separates the rim of the upstream disc 3, of the inner platforms 11.
  • holes 14 formed in the outer shell 9 open into the groove 12. These holes 14 allow the introduction of an air flow of sampling in the centripetal sampling device 2 which in the example shown in FIG. 1 comprises radial channels 15 formed in the wall of the upstream disc 3. The sampled air is led radially towards the interior by the radial channels 15 and deflected backwards by the part radially inside 16 of the upstream disc 3, and flows axially towards the stages of the turbine driving the compressor 1.
  • the speed diagram of FIG. 3 shows that the relative speed Vr 1 of the air in the vicinity of the holes 14, relative to the periphery of the upstream disc 3 is relatively high.
  • Va 1 indicates the absolute speed of the air and
  • Ve represents the speed of the rim of the disc 3.
  • Figure 2 shows the same compressor 1 equipped with means fixed guide 20 intended to imprint the air circulating in the groove 12 between the gap 13 and the holes 14 a vortex movement centripetal in the direction of rotation of the compressor 1.
  • the air has an absolute speed Va 2 whose standard is equal to the standard of the absolute speed Va 1 , but which is substantially directed tangentially to the periphery of the outer shell 9, so that the speed relative Vr 2 of the air relative to the upstream disc 3 is significantly lower than the relative speed Vr 1 of the prior art, as shown in FIG. 4.
  • the means guide 20 are arranged in the groove 12 under the upstream part of the inner platforms 11 of the straightening vanes 8.
  • These guide means 20 comprise a plurality of profiles blade 21 or fins regularly distributed around the axis of rotation X of compressor 1 and whose leading edges 22 extend at least in part in the interstice 13.
  • the angle of attack ⁇ of these profiles 21 is determined as a function of tangential speed and radial speed local air passing through gap 13.
  • the airfoil profiles 21 are drawn in such a way that the air entering through the gap 13 and flowing between the airfoil profiles 21 comes out with a speed Va 2 , represented by an arrow or vector in FIGS. 4 and 6, substantially tangential to the drive speed Ve of the rotor, in order to significantly reduce the relative speed Vr 2 of the air entering the holes 14.

Abstract

An annular groove (12) is linked with a stream (5) via an interstice (13). The groove is fitted with a fixed air guide (20) which imparts a centripetal swirling motion on air flowing in the groove. The centripetal swirling motion rotates in the same direction as the compressor to reduce the velocity of air entering into the holes (14) of an outer shroud (9).

Description

L'invention concerne un compresseur axial de turbomachine équipé d'un dispositif de prélèvement centripète d'air dans la veine du compresseur, cet air de prélèvement étant destiné au refroidissement de la turbine, ledit compresseur comportant deux couronnes d'aubes mobiles qui s'étendent radialement vers l'extérieur à la périphérie de deux disques consécutifs assemblés par une virole extérieure munie de perçages et une couronne d'aubes redresseuses fixe disposée dans la veine entre lesdites deux couronnes d'aubes mobiles, lesdits perçages servant d'entrées d'air audit dispositif de prélèvement et débouchant dans une gorge annulaire prévue sous l'interstice séparant les plates-formes intérieures des aubes redresseuses, de la jante du disque amont, ladite gorge communiquant avec ladite veine par ledit interstice.The invention relates to an axial compressor for a turbomachine equipped with a centripetal air sampling device in the vein of the compressor, this bleed air being intended for cooling the turbine, said compressor comprising two rings of movable blades which extend radially outward at the periphery of two discs consecutive assembled by an outer ferrule provided with holes and a fixed crown of straightening vanes arranged in the vein between said two crowns of movable blades, said holes serving as air inlets said sampling device and opening into an annular groove provided under the gap separating the inner platforms from the blades straighteners, from the rim of the upstream disc, said groove communicating with said vein through said interstice.

Le rôle du dispositif de prélèvement centripète d'air, disposé à l'intérieur du rotor à haute pression, est d'amener un débit d'air prélevé dans un étage de compresseur vers les étages de turbine à refroidir. Il est important que l'air de refroidissement arrivant dans les aubages de la turbine à haute pression, soumis à des températures élevées, ait une pression suffisante pour permettre la formation d'un film d'air de protection autour des aubes de la turbine, et une température aussi faible que possible.The role of the centripetal air sampling device, arranged to the inside of the high pressure rotor, is to bring a flow of air taken in a compressor stage to the turbine stages to be cooled. It is important that the cooling air entering the blades of the high pressure turbine, subjected to high temperatures, has a sufficient pressure to allow the formation of an air film of protection around the turbine blades, and such a low temperature as possible.

Le dispositif de prélèvement peut comporter des canaux de prélèvement ménagés dans le disque amont, ainsi que cela est divulgué par FR 2 609 500 et FR 2 614 654, ou des tubes de prélèvement disposés dans la cavité annulaire séparant les deux disques, ainsi que cela est dévoilé par US 5 475 313.The sampling device can include channels for sample taken from the upstream disc, as disclosed by FR 2 609 500 and FR 2 614 654, or collection tubes arranged in the annular cavity separating the two discs, as is disclosed by US 5,475,313.

Le débit d'air prélevé dans la veine pénètre dans la gorge annulaire par l'interstice séparant les plates-formes intérieures des aubes redresseuses de la jante du disque amont dans une direction sensiblement axiale et transite ensuite par les perçages de la virole en rotation. On conçoit donc que les vitesses relatives de l'air à l'entrée des perçages, par rapport au disque en rotation est relativement élevée, ce qui se traduit par une élévation de la température totale relative de l'air dans les perçages et une perte de charge non négligeable dans cette zone. Cette élévation de température se retrouve évidemment dans le débit d'air délivré dans les aubes de la turbine. La perte de charge se traduit par une diminution du débit d'air prélevé. The air flow taken from the vein enters the throat annular by the gap separating the inner platforms from the blades upstream disc rim straighteners in a direction substantially axial and then passes through the holes in the rotating shell. We conceives therefore that the relative air velocities at the entry of the holes, by ratio to the spinning disc is relatively high, which results in an increase in the relative total air temperature in the holes and a significant pressure drop in this area. This elevation of temperature is obviously found in the air flow delivered in the turbine blades. The pressure drop results in a decrease of the sampled air flow.

Le but de l'invention est de proposer des moyens faciles à mettre en oeuvre et peu coûteux qui permettent de diminuer sensiblement la température de l'air délivré dans la turbine à haute pression et de diminuer les pertes de charge, toutes choses étant égales par ailleurs.The object of the invention is to propose easy means to implement and inexpensive which can significantly reduce the temperature of the air supplied to the high pressure turbine and reduce the pressure drops, all other things being equal.

Le but est atteint selon l'invention par le fait que la gorge est équipée de moyens de guidage fixes imprimant au flux d'air circulant dans la gorge un mouvement tourbillonnaire centripète dans le sens de rotation du compresseur, afin de diminuer la vitesse relative de l'air entrant dans les perçages par rapport auxdits perçages en rotation.The object is achieved according to the invention by the fact that the throat is equipped with fixed guide means which print on the air flow circulating in throat a centripetal vortex movement in the direction of rotation of the compressor, in order to decrease the relative speed of the air entering the holes in relation to said rotary holes.

Il en résulte que la température totale relative de l'air dans les perçages est sensiblement abaissée par rapport à la même température dans un compresseur traditionnel, ce qui améliore le refroidissement des aubes de turbine pour un même débit, et augmente leur durée de vie.As a result, the relative total air temperature in the holes is significantly lowered compared to the same temperature in a traditional compressor, which improves the cooling of turbine blades for the same flow rate, and increases their service life.

Les pertes de charge sont également diminuées, ce qui améliore le débit d'air prélevé par rapport à l'état de la technique, pour des perçages et dispositifs de prélèvement identiques et augmente le taux de surpression dans les aubes de la turbine.The pressure drops are also reduced, which improves the air flow rate compared to the state of the art, to identical holes and sampling devices and increases the rate overpressure in the turbine blades.

L'ensemble des deux améliorations obtenues grâce à l'invention, permet de diminuer le débit d'air nécessaire pour le refroidissement des aubes de la turbine, et par le fait même la consommation spécifique de carburant, pour une même durée de vie des aubages de la turbine à refroidir.The set of two improvements obtained thanks to the invention reduces the air flow required for the cooling of the turbine blades, and thereby specific fuel consumption, for the same lifetime of blades of the turbine to be cooled.

Lesdits moyens de guidage sont disposés au moins en partie sous les plates-formes intérieures des aubes redresseuses.Said guide means are arranged at least in part under the inner platforms of straightening vanes.

Avantageusement les moyens de guidage de l'air dans la gorge comportent une pluralité de profils d'aubage régulièrement répartis autour de l'axe de rotation du compresseur.Advantageously the means for guiding the air in the groove have a plurality of blade profiles regularly distributed around of the axis of rotation of the compressor.

De préférence, les bords d'attaque des profils d'aubage s'étendent au moins en partie dans l'interstice.Preferably, the leading edges of the blade profiles extend at least in part into the gap.

L'angle d'attaque des profils est déterminé en fonction de la vitesse tangentielle et de la vitesse radiale locale de l'air passant par l'interstice.The angle of attack of the profiles is determined according to the tangential velocity and the local radial velocity of the air passing through the gap.

Ceci permet de ne pas modifier la norme de la vitesse de l'air dans la gorge et par le fait même de ne pas modifier la pression statique. This does not change the standard of air speed in the throat and thereby not to change the static pressure.

Les profils d'aubage augmente le coefficient d'entraínement de l'air dans la gorge, ce qui permet pour la même température totale de l'air, d'en diminuer la température totale relative.The blading profiles increases the training coefficient of air in the throat, allowing for the same total temperature of air, to decrease the relative total temperature.

L'amélioration du coefficient d'entraínement grâce aux profils d'aubage proposés est de 30 % environ par rapport à l'état de la technique, ce qui correspond à une diminution de la température totale relative de 40°C environ. Ceci permet de multiplier la durée de vie des aubes de la turbine par deux, pour le même débit prélevé.Improving the training coefficient thanks to the profiles of proposed blading is about 30% compared to the state of the technical, which corresponds to a decrease in the total temperature relative of about 40 ° C. This increases the lifespan of turbine blades in pairs, for the same flow rate.

D'autres avantages et caractéristiques de l'invention ressortiront à la lecture de la description suivante faite à titre d'exemple et en référence aux dessins annexés dans lesquels :

  • la figure 1 est une demi-vue axiale d'un compresseur de turbomachine équipé d'un dispositif de prélèvement d'air centripète, selon l'art antérieur,
  • la figure 2 est une demi-vue axiale d'un compresseur de turbomachine selon l'invention équipé du même dispositif de prélèvement d'air centripète,
  • la figure 3 montre le diagramme des vitesses de l'air près des perçages en l'absence de moyens de guidage de l'air,
  • la figure 4 montre le diagramme des vitesses de l'air près des perçages obtenues grâce aux moyens de guidage de l'air selon l'invention,
  • la figure 5 est une vue axiale des profils de guidage de l'air dans la gorge, et
  • la figure 6 est une vue en perspective de l'avant des plates-formes des aubes redresseuses équipées de profils de guidage selon l'invention.
    • Other advantages and characteristics of the invention will emerge on reading the following description given by way of example and with reference to the appended drawings in which:
  • FIG. 1 is an axial half-view of a turbomachine compressor equipped with a centripetal air sampling device, according to the prior art,
  • FIG. 2 is an axial half-view of a turbomachine compressor according to the invention equipped with the same centripetal air sampling device,
  • FIG. 3 shows the diagram of the air speeds near the holes in the absence of air guiding means,
  • FIG. 4 shows the diagram of the air velocities near the holes obtained thanks to the air guiding means according to the invention,
  • FIG. 5 is an axial view of the profiles for guiding the air in the groove, and
  • Figure 6 is a perspective view of the front of the platforms of the straightening vanes equipped with guide profiles according to the invention.

    • La figure 1 montre un compresseur 1 d'une turbomachine d'axe X selon l'état de la technique équipé d'un dispositif de prélèvement centripète 2.FIG. 1 shows a compressor 1 of an axis turbomachine X according to the state of the art equipped with a sampling device centripetal 2.

    Ce compresseur 1 comporte un disque amont 3 ayant à sa périphérie une première couronne d'aubes mobiles 4 disposée dans la veine 5, un disque aval 6 présentant à sa périphérie une deuxième couronne d'aubes mobiles 7 décalée axialement dans la veine 5, et une couronne d'aubes redresseuses 8 fixes disposée dans la veine 5 entre la première et la deuxième couronne d'aubes mobiles. This compressor 1 comprises an upstream disc 3 having at its periphery a first ring of movable blades 4 arranged in the vein 5, a downstream disc 6 having at its periphery a second crown of movable blades 7 offset axially in the vein 5, and a crown of straightening vanes 8 fixed arranged in the vein 5 between the first and second crown of movable blades.

    Le disque amont 3 et le disque aval 6 sont reliés entre eux par une virole extérieure 9 munie d'un labyrinthe d'étanchéité 10 coopérant avec la face intérieure des plates-formes intérieures 11 des aubes redresseuses 8. Une gorge 12 est ménagée sous l'interstice 13 qui sépare la jante du disque amont 3, des plates-formes intérieures 11. Des perçages 14 ménagés dans la virole extérieure 9 débouchent dans la gorge 12. Ces perçages 14 permettent l'introduction d'un débit d'air de prélèvement dans le dispositif de prélèvement centripète 2 qui dans l'exemple montré sur la figure 1 comporte des canaux radiaux 15 ménagés dans la paroi du disque amont 3. L'air prélevé est conduit radialement vers l'intérieur par les canaux radiaux 15 et dévié vers l'arrière par la partie radialement intérieure 16 du disque amont 3, et s'écoule axialement vers les étages de la turbine entraínant le compresseur 1.The upstream disc 3 and the downstream disc 6 are interconnected by an outer shell 9 provided with a sealing labyrinth 10 cooperating with the inner face of the inner platforms 11 of the blades straighteners 8. A groove 12 is formed under the gap 13 which separates the rim of the upstream disc 3, of the inner platforms 11. holes 14 formed in the outer shell 9 open into the groove 12. These holes 14 allow the introduction of an air flow of sampling in the centripetal sampling device 2 which in the example shown in FIG. 1 comprises radial channels 15 formed in the wall of the upstream disc 3. The sampled air is led radially towards the interior by the radial channels 15 and deflected backwards by the part radially inside 16 of the upstream disc 3, and flows axially towards the stages of the turbine driving the compressor 1.

    Le diagramme des vitesses de la figure 3 montre que la vitesse relative Vr1 de l'air au voisinage des perçages 14, par rapport à la périphérie du disque amont 3 est relativement élevée. Va1 désigne la vitesse absolue de l'air et Ve représente la vitesse de la jante du disque 3.The speed diagram of FIG. 3 shows that the relative speed Vr 1 of the air in the vicinity of the holes 14, relative to the periphery of the upstream disc 3 is relatively high. Va 1 indicates the absolute speed of the air and Ve represents the speed of the rim of the disc 3.

    La figure 2 montre le même compresseur 1 équipé de moyens de guidage fixes 20 destinés à imprimer à l'air circulant dans la gorge 12 entre l'interstice 13 et les perçages 14 un mouvement tourbillonnaire centripète dans le sens de rotation du compresseur 1.Figure 2 shows the same compressor 1 equipped with means fixed guide 20 intended to imprint the air circulating in the groove 12 between the gap 13 and the holes 14 a vortex movement centripetal in the direction of rotation of the compressor 1.

    A la sortie de ces moyens, l'air a une vitesse absolue Va2 dont la norme est égale à la norme de la vitesse absolue Va1, mais qui est sensiblement dirigée tangentiellement à la périphérie de la virole externe 9, afin que la vitesse relative Vr2 de l'air par rapport au disque amont 3 soit nettement inférieure à la vitesse relative Vr1 de l'état de la technique, ainsi que cela est montré sur la figure 4.At the outlet of these means, the air has an absolute speed Va 2 whose standard is equal to the standard of the absolute speed Va 1 , but which is substantially directed tangentially to the periphery of the outer shell 9, so that the speed relative Vr 2 of the air relative to the upstream disc 3 is significantly lower than the relative speed Vr 1 of the prior art, as shown in FIG. 4.

    Ainsi que cela est montré sur les figures 2, 5 et 6, les moyens de guidage 20 sont disposés dans la gorge 12 sous la partie amont des plates-formes intérieures 11 des aubes redresseuses 8.As shown in Figures 2, 5 and 6, the means guide 20 are arranged in the groove 12 under the upstream part of the inner platforms 11 of the straightening vanes 8.

    Ces moyens de guidage 20 comportent une pluralité de profils d'aubage 21 ou ailettes régulièrement répartis autour de l'axe de rotation X du compresseur 1 et dont les bords d'attaque 22 s'étendent au moins en partie dans l'interstice 13. L'angle d'attaque α de ces profils 21 est déterminé en fonction de la vitesse tangentielle et de la vitesse radiale locale de l'air passant par l'interstice 13. These guide means 20 comprise a plurality of profiles blade 21 or fins regularly distributed around the axis of rotation X of compressor 1 and whose leading edges 22 extend at least in part in the interstice 13. The angle of attack α of these profiles 21 is determined as a function of tangential speed and radial speed local air passing through gap 13.

    Les profils d'aubage 21 sont dessinés de telle manière que l'air entrant par l'interstice 13 et s'écoulant entre les profils d'aubage 21 en ressort avec une vitesse Va2, représentée par une flèche ou vecteur sur les figures 4 et 6, sensiblement tangentielle à la vitesse d'entraínement Ve du rotor, afin de diminuer sensiblement la vitesse relative Vr2 de l'air pénétrant dans les perçages 14.The airfoil profiles 21 are drawn in such a way that the air entering through the gap 13 and flowing between the airfoil profiles 21 comes out with a speed Va 2 , represented by an arrow or vector in FIGS. 4 and 6, substantially tangential to the drive speed Ve of the rotor, in order to significantly reduce the relative speed Vr 2 of the air entering the holes 14.

    Claims (6)

    Compresseur axial de turbomachine équipé d'un dispositif (2) de prélèvement centripète d'air dans la veine (5) dudit compresseur, cet air étant destiné au refroidissement de la turbine, ledit compresseur comportant deux couronnes d'aubes mobiles (4, 7) qui s'étendent radialement vers l'extérieur à la périphérie de deux disques consécutifs (3, 6) assemblés par une virole extérieure (9) munie de perçages (14) et une couronne d'aubes redresseuses (8) fixes disposée dans la veine (5) entre lesdits deux couronnes d'aubes mobiles, lesdits perçages servant d'entrées d'air audit dispositif de prélèvement et débouchant dans une gorge annulaire (12) prévue sous l'interstice (13) séparant les plates-formes intérieures (11) des aubes redresseuses (8) de la jante du disque amont, ladite gorge communiquant avec ladite veine par ledit interstice, caractérisé en ce que la gorge (12) est équipée de moyens de guidage fixes (20) imprimant au flux d'air circulant dans ladite gorge (12) un mouvement tourbillonnaire centripète dans le sens de rotation du compresseur afin de diminuer la vitesse relative de l'air entrant dans les perçages (14) par rapport auxdits perçages en rotation.Axial compressor of a turbomachine equipped with a device (2) for centripetal sampling of air in the vein (5) of said compressor, this air being intended for cooling the turbine, said compressor comprising two crowns of movable blades (4, 7 ) which extend radially outwards at the periphery of two consecutive discs (3, 6) assembled by an outer ring (9) provided with bores (14) and a crown of stationary straightening vanes (8) arranged in the vein (5) between said two crowns of movable blades, said holes serving as air inlets to said sampling device and opening into an annular groove (12) provided under the gap (13) separating the interior platforms ( 11) straightening vanes (8) of the rim of the upstream disc, said groove communicating with said vein through said gap, characterized in that the groove (12) is equipped with fixed guide means (20) printing on the air flow circulating in said g barley (12) a centripetal vortex movement in the direction of rotation of the compressor in order to reduce the relative speed of the air entering the bores (14) with respect to said rotary bores. Compresseur selon la revendication 1, caractérisé par le fait que lesdits moyens de guidage sont disposés au moins en partie sous les plates-formes intérieures (11) des aubes redresseuses (8).Compressor according to Claim 1, characterized in that the said guide means are arranged at least partly under the internal platforms (11) of the straightening vanes (8). Compresseur selon la revendication 2, caractérisé par le fait que lesdits moyens de guidage de l'air dans la gorge comportent une pluralité de profils d'aubage (21) régulièrement répartis autour de l'axe de rotation (X) dudit compresseur.Compressor according to claim 2, characterized in that said means for guiding the air in the groove comprise a plurality of blade profiles (21) regularly distributed around the axis of rotation (X) of said compressor. Compresseur selon la revendication 3, caractérisé par le fait que les bords d'attaque (22) des profils d'aubage (21) s'étendent au moins en partie dans l'interstice (13).Compressor according to claim 3, characterized in that the leading edges (22) of the blade profiles (21) extend at least partially in the gap (13). Compresseur selon la revendication 4, caractérisé par le fait que l'angle d'attaque (α) des profils est déterminé en fonction de la vitesse tangentielle et de la vitesse radiale locale de l'air passant par l'interstice.Compressor according to claim 4, characterized in that the angle of attack (α) of the profiles is determined as a function of the tangential speed and the local radial speed of the air passing through the gap. Compresseur selon l'une quelconque des revendications 1 à 5, caractérisé par le fait que le dispositif de prélèvement (20) comporte des canaux de prélèvement (15) ménagés dans le disque amont (3).Compressor according to any one of Claims 1 to 5, characterized in that the sampling device (20) comprises sampling channels (15) formed in the upstream disc (3).
    EP03290061A 2002-01-17 2003-01-10 Centripetal air bleed device Expired - Lifetime EP1329639B1 (en)

    Applications Claiming Priority (2)

    Application Number Priority Date Filing Date Title
    FR0200519 2002-01-17
    FR0200519A FR2834758B1 (en) 2002-01-17 2002-01-17 DEVICE FOR STRAIGHTENING THE SUPPLY AIR OF A CENTRIPETE SAMPLING IN A COMPRESSOR

    Publications (2)

    Publication Number Publication Date
    EP1329639A1 true EP1329639A1 (en) 2003-07-23
    EP1329639B1 EP1329639B1 (en) 2008-03-12

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    EP03290061A Expired - Lifetime EP1329639B1 (en) 2002-01-17 2003-01-10 Centripetal air bleed device

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    EP (1) EP1329639B1 (en)
    CA (1) CA2416157C (en)
    DE (1) DE60319607T2 (en)
    FR (1) FR2834758B1 (en)
    RU (1) RU2295656C2 (en)

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    DE102010063071A1 (en) 2010-12-14 2012-06-14 Rolls-Royce Deutschland Ltd & Co Kg Cooling device for a jet engine
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    Also Published As

    Publication number Publication date
    US6908278B2 (en) 2005-06-21
    FR2834758A1 (en) 2003-07-18
    CA2416157A1 (en) 2003-07-17
    DE60319607D1 (en) 2008-04-24
    CA2416157C (en) 2011-05-17
    US20030133787A1 (en) 2003-07-17
    EP1329639B1 (en) 2008-03-12
    DE60319607T2 (en) 2009-04-02
    FR2834758B1 (en) 2004-04-02
    RU2295656C2 (en) 2007-03-20

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