EP1693572A2 - Bleeding air from the tip of the rotating blades in a high pressure compressor of a turbine engine - Google Patents

Bleeding air from the tip of the rotating blades in a high pressure compressor of a turbine engine Download PDF

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Publication number
EP1693572A2
EP1693572A2 EP20060100669 EP06100669A EP1693572A2 EP 1693572 A2 EP1693572 A2 EP 1693572A2 EP 20060100669 EP20060100669 EP 20060100669 EP 06100669 A EP06100669 A EP 06100669A EP 1693572 A2 EP1693572 A2 EP 1693572A2
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EP
European Patent Office
Prior art keywords
compressor according
turbomachine
sampling
blades
sampling holes
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
EP20060100669
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German (de)
French (fr)
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EP1693572B1 (en
EP1693572A3 (en
Inventor
Armel Touyeras
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Safran Aircraft Engines SAS
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SNECMA SAS
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Publication of EP1693572A3 publication Critical patent/EP1693572A3/en
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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
    • F04D29/66—Combating cavitation, whirls, noise, vibration or the like; Balancing
    • F04D29/68—Combating cavitation, whirls, noise, vibration or the like; Balancing by influencing boundary layers
    • F04D29/681—Combating cavitation, whirls, noise, vibration or the like; Balancing by influencing boundary layers especially adapted for elastic fluid pumps
    • F04D29/682—Combating cavitation, whirls, noise, vibration or the like; Balancing by influencing boundary layers especially adapted for elastic fluid pumps by fluid extraction
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F04—POSITIVE - DISPLACEMENT MACHINES FOR LIQUIDS; PUMPS FOR LIQUIDS OR ELASTIC FLUIDS
    • F04D—NON-POSITIVE-DISPLACEMENT PUMPS
    • F04D27/00—Control, e.g. regulation, of pumps, pumping installations or pumping systems specially adapted for elastic fluids
    • F04D27/02—Surge control
    • F04D27/0207—Surge control by bleeding, bypassing or recycling fluids
    • F04D27/023—Details or means for fluid extraction
    • 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
    • F04D29/522—Casings; Connections of working fluid for axial pumps especially adapted for elastic fluid pumps
    • F04D29/526—Details of the casing section radially opposing blade tips
    • 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
    • F04D29/66—Combating cavitation, whirls, noise, vibration or the like; Balancing
    • F04D29/68—Combating cavitation, whirls, noise, vibration or the like; Balancing by influencing boundary layers
    • F04D29/681—Combating cavitation, whirls, noise, vibration or the like; Balancing by influencing boundary layers especially adapted for elastic fluid pumps
    • F04D29/685—Inducing localised fluid recirculation in the stator-rotor interface
    • Y—GENERAL TAGGING OF NEW TECHNOLOGICAL DEVELOPMENTS; GENERAL TAGGING OF CROSS-SECTIONAL TECHNOLOGIES SPANNING OVER SEVERAL SECTIONS OF THE IPC; TECHNICAL SUBJECTS COVERED BY FORMER USPC CROSS-REFERENCE ART COLLECTIONS [XRACs] AND DIGESTS
    • Y10—TECHNICAL SUBJECTS COVERED BY FORMER USPC
    • Y10S—TECHNICAL SUBJECTS COVERED BY FORMER USPC CROSS-REFERENCE ART COLLECTIONS [XRACs] AND DIGESTS
    • Y10S415/00—Rotary kinetic fluid motors or pumps
    • Y10S415/914—Device to control boundary layer

Definitions

  • the present invention relates to the specific field of turbomachines and more particularly relates to a device for sampling air in the aerodynamic stream of a high-pressure axial compressor of these turbomachines.
  • turbomachines In the high-pressure axial compressors of turbojet engines or turboprop engines (hereinafter referred to as turbomachines), it is known that the clearance between the ends of the compressor blades and the casing forming the internal wall of the flow duct air degrades the efficiency of the engine of the turbomachine. In addition, this game can significantly modify and degrade the operation of the compressor until the occurrence of a phenomenon of "pumping".
  • patent FR 2,564,533 which, to avoid pumping in an axial compressor, shows a specific shaping of the casing associated with a specific arrangement of an air flow system. This development is however relatively complex and delicate implementation.
  • the subject of the present invention is a turbomachine compressor which makes it possible to obtain a noticeable improvement over the devices of the prior art from the efficiency and the margin of safety with respect to pumping, also known as pumping margin.
  • a turbomachine compressor comprising a plurality of blades and, spaced in an axial direction relative to a longitudinal central axis of the turbomachine, a plurality of blades, a fixed casing enveloping said plurality of blades characterized in that said fixed housing comprises a plurality of sampling holes centered between 5 and 50% of the length of rope of the blade and a diameter less than or equal to 30% of said length of rope of the blade, each of said sampling holes having a double inclination with respect to said longitudinal central axis.
  • the ratio between the overall air flow rate of the compressor and the air flow rate taken is between 0.1 and 5%.
  • said fixed casing further comprises oblique lamellae arranged in line with said plurality of blades on both sides of each sampling hole and oriented at said angle ⁇ .
  • said sampling holes each comprise a first inclination axis having an angle ⁇ with respect to the longitudinal central axis of between 30 and 90 ° and a second axis of inclination perpendicular to the first and having an angle ⁇ relative to the central longitudinal axis between 30 and 90 °.
  • sampling holes may be arranged in staggered rows or formed of axisymmetric slots. These sampling holes can also be non-circular.
  • FIG. 1 is a schematic view of a section of a high-pressure axial compressor 10 disposed about a longitudinal central axis (motor axis 12) of a turbomachine and delimited at its outer portion by a casing 14 forming a surface of revolution around this central longitudinal axis.
  • This compressor comprises several successive stages of compression (in an axial direction), each stage comprising distributed over the circumference a plurality of blades (rotor 16) rotatable about the motor axis and a plurality of blades (stator 18).
  • a clearance e exists between the upper end 20 of each moving blade and the fixed casing 14 which surrounds the compressor.
  • This game can be the place of violent turbulence which can deteriorate the configuration of the flow between the different stages and thus lead to a degradation of the performances of the compressor or, in the extreme, to cause a phenomenon known as "pumping" or "stalling". Consisting of an instantaneous fall in the compression ratio and an inversion of the air flow through the compressor which then leaves the upstream compressor.
  • the safety range in operation with respect to pumping is increased by the addition of an air sampling device disposed at the top of the blades, that is to say substantially at the level of from his leading edge 22.
  • This sampling device comprises a plurality of holes 24, preferably cylindrical, made in the fixed casing 14, centered between 5 and 50% of the length of rope of the blade and having a diameter less than or equal to 30% of the rope length of dawn, the rope of dawn being the line segment connecting the leading edge to the trailing edge of a moving blade.
  • the number of sampling holes is determined as a function of the air flow rate to be taken with respect to the overall air flow through the compressor. Typically, an air flow rate of between 0.1 and 5% guarantees operating efficiency of the device according to the different measurements made by the inventors.
  • sampling holes have a double inclination with a first axis projected in the blade vane plane having an angle ⁇ relative to the motor axis of between 30 and 90 ° (see FIG. 2) and a second axis projected in the plane. meridian (perpendicular to the first) having an angle ⁇ relative to the motor axis between 30 and 90 °.
  • FIG. 3 shows, for example, an arrangement of these sampling holes in two rows, the holes being staggered in the previously defined limit of 5 to 50% of the length of rope of the blade.
  • these sampling holes have a non-circular shape, square or oblong, for example.
  • sampling holes in the form of an axisymmetric slit.
  • the air which conventionally sneaks by the clearance e above the ends 20 of the blades because of the pressure difference existing between the intrados and extrados faces of these blades is in fact Part sucked by the sampling holes 24.
  • the decrease in this parasitic flux between the two faces of the same blade has the immediate effect of increasing the stability and performance of the compressor.
  • the collected air can join, possibly via a system of protective sheets (not shown), existing sampling collectors of the turbomachine for use engine or other, for example avionics.
  • FIG. 5 shows the variation of the compression ratio in compressor efficiency function for a compressor of the prior art (curve 30) and for a compressor provided with the device according to the invention (curve 32)
  • FIG. 6 shows the variation of the compression ratio as a function of the inlet flow rate compressor for a compressor of the prior art (curve 40) and for a compressor provided with the device according to the invention (curve 42).
  • the efficiency of the device can be further improved by directing the air directly towards the sampling holes as illustrated in FIGS. 7 and 8 which show the addition of oblique lamellae 50 arranged on the fixed casing to the right of the plurality of Vane moving on either side of each sampling hole 24.
  • These lamellae machined directly in the housing or reported thereto are oriented at the same angle ⁇ relative to the motor axis 12 as the sampling holes.
  • this configuration can be implanted on a housing 14 comprising a withdrawal at the right of the blade (called trench 52) as shown in FIG. 9, or else including a groove 54 at the right of the blade (called housing treatment) as shown in Figures 10 and 11.
  • the grooving is distributed around the sampling hole 24 while, in Figure 11, the sampling hole opens bottom grooving.
  • the device of the invention can also be used at one or more transonic stages of a high pressure compressor or on a low pressure compressor.
  • the present invention can not be limited to the fastening and driving structure of the blades shown in Figure 1 and a structure employing so-called staples or hammer is also conceivable.

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  • Engineering & Computer Science (AREA)
  • Mechanical Engineering (AREA)
  • General Engineering & Computer Science (AREA)
  • Life Sciences & Earth Sciences (AREA)
  • Sustainable Development (AREA)
  • Structures Of Non-Positive Displacement Pumps (AREA)

Abstract

The compressor (10) has several stator vanes (18) and moving blades (16) which are spaced apart in axial direction relative to a central longitudinal axis. The blades are surrounded by a stationary casing (14). The stationary casing has several bleed holes (24) which are centered in a range of 5-50% of the blade chord length. The diameter of the bleed hole is 30% of the blade chord length. The bleed hole is inclined at two different angles relative to the longitudinal axis. An independent claim is also included for turbomachine.

Description

Domaine de l'inventionField of the invention

La présente invention se rapporte au domaine spécifique des turbomachines et elle concerne plus particulièrement un dispositif de prélèvement d'air dans la veine aérodynamique d'un compresseur axial haute pression de ces turbomachines.The present invention relates to the specific field of turbomachines and more particularly relates to a device for sampling air in the aerodynamic stream of a high-pressure axial compressor of these turbomachines.

Art antérieurPrior art

Dans les compresseurs axiaux haute pression des turboréacteurs ou des turbopropulseurs (appelés dans la suite de la description turbomachines), il est connu que le jeu existant entre les extrémités des aubes mobiles du compresseur et le carter formant la paroi interne de la veine d'écoulement de l'air dégrade le rendement du moteur de la turbomachine. En outre, ce jeu peut notablement modifier et dégrader le fonctionnement du compresseur jusq'à l'apparition d'un phénomène de « pompage ». Une solution à ce problème est donnée par le brevet FR 2 564 533 qui, pour éviter le pompage dans un compresseur axial, montre un façonnement spécifique du carter associé à un agencement spécifique d'un système de débit d'air. Cet aménagement est toutefois relativement complexe et de mise en oeuvre délicate.In the high-pressure axial compressors of turbojet engines or turboprop engines (hereinafter referred to as turbomachines), it is known that the clearance between the ends of the compressor blades and the casing forming the internal wall of the flow duct air degrades the efficiency of the engine of the turbomachine. In addition, this game can significantly modify and degrade the operation of the compressor until the occurrence of a phenomenon of "pumping". A solution to this problem is given by patent FR 2,564,533 which, to avoid pumping in an axial compressor, shows a specific shaping of the casing associated with a specific arrangement of an air flow system. This development is however relatively complex and delicate implementation.

Objet et définition de l'inventionObject and definition of the invention

La présente invention a pour objet un compresseur de turbomachine permettant d'obtenir une amélioration notable par rapport aux dispositifs de l'art antérieur du rendement et de la marge de sécurité de fonctionnement vis à vis du pompage dite aussi marge au pompage.The subject of the present invention is a turbomachine compressor which makes it possible to obtain a noticeable improvement over the devices of the prior art from the efficiency and the margin of safety with respect to pumping, also known as pumping margin.

Ces buts sont atteints par un compresseur de turbomachine comportant une pluralité d'aubes mobiles et, espacée dans une direction axiale par rapport à un axe central longitudinal de la turbomachine, une pluralité d'aubes fixes, un carter fixe enveloppant ladite pluralité d'aubes mobiles, caractérisé en ce que ledit carter fixe comporte une pluralité de trous de prélèvement centrés entre 5 et 50% de la longueur de corde de l'aube et d'un diamètre inférieur ou égal à 30% de ladite longueur de corde de l'aube, chacun desdits trous de prélèvement présentant une double inclinaison par rapport audit axe central longitudinal.These objects are achieved by a turbomachine compressor comprising a plurality of blades and, spaced in an axial direction relative to a longitudinal central axis of the turbomachine, a plurality of blades, a fixed casing enveloping said plurality of blades characterized in that said fixed housing comprises a plurality of sampling holes centered between 5 and 50% of the length of rope of the blade and a diameter less than or equal to 30% of said length of rope of the blade, each of said sampling holes having a double inclination with respect to said longitudinal central axis.

Ainsi, avec cette configuration de prélèvement en tête des aubes mobiles, la marge au pompage est augmentée et le rendement est amélioré sensiblement.Thus, with this sampling configuration at the top of the blades, the pumping margin is increased and the yield is significantly improved.

De préférence, le rapport entre le débit d'air global du compresseur et le débit d'air prélevé est compris entre 0,1 et 5 %.Preferably, the ratio between the overall air flow rate of the compressor and the air flow rate taken is between 0.1 and 5%.

Selon un mode de réalisation avantageux, ledit carter fixe comporte en outre des lamelles obliques disposées au droit de ladite pluralité d'aubes mobiles de part et d'autre de chaque trou de prélèvement et orientées selon ledit angle ϕ.According to an advantageous embodiment, said fixed casing further comprises oblique lamellae arranged in line with said plurality of blades on both sides of each sampling hole and oriented at said angle φ.

Avantageusement, lesdits trous de prélèvement comportent chacun un premier axe d'inclinaison présentant un angle ϕ par rapport à l'axe central longitudinal compris entre 30 et 90° et un second axe d'inclinaison perpendiculaire au premier et présentant un angle θ par rapport à l'axe central longitudinal compris entre 30 et 90°.Advantageously, said sampling holes each comprise a first inclination axis having an angle φ with respect to the longitudinal central axis of between 30 and 90 ° and a second axis of inclination perpendicular to the first and having an angle θ relative to the central longitudinal axis between 30 and 90 °.

Selon le mode de réalisation envisagé, lesdits trous de prélèvement peuvent être disposés en quinconce ou formés de fentes axisymétriques. Ces trous de prélèvement peuvent aussi être non circulaires.According to the embodiment envisaged, said sampling holes may be arranged in staggered rows or formed of axisymmetric slots. These sampling holes can also be non-circular.

Brève description des dessinsBrief description of the drawings

Les caractéristiques et avantages de la présente invention ressortiront mieux de la description suivante, faite à titre indicatif et non limitatif, en regard des dessins annexés sur lesquels :

  • la figure 1 est une vue schématique fragmentaire d'une section de compresseur selon l'invention comportant plusieurs étages d'aubes mobiles encadré chacun par deux étages d'aubes fixes,
  • la figure 2 est une vue de dessus du carter de la figure 1 dans un premier mode de réalisation de l'invention,
  • la figure 3 est une vue de dessus du carter de la figure 1 dans un deuxième mode de réalisation de l'invention,
  • la figure 4 est une vue de dessus du carter de la figure 1 dans un troisième mode de réalisation de l'invention,
  • les figures 5 et 6 sont des courbes illustrant l'évolution du taux de compression en fonction respectivement du rendement et du débit d'entrée du compresseur selon l'art antérieur et avec l'invention, et
  • la figure 7 est une vue de l'intérieur du carter de la figure 1 dans une variante du premier mode de réalisation de l'invention,
  • la figure 8 est une coupe selon le plan VIII-VIII de la figure 7,
  • la figure 9 est une section semblable à celle de la figure 7 pour une première variante de réalisation du carter, et
  • les figures 10 et 11 sont des vues semblables à celle de la figure 9 pour deux autres variantes de réalisation du carter.
The features and advantages of the present invention will emerge more clearly from the following description, given by way of non-limiting indication, with reference to the appended drawings in which:
  • FIG. 1 is a fragmentary schematic view of a compressor section according to the invention comprising several stages of moving blades each framed by two stages of fixed vanes,
  • FIG. 2 is a view from above of the casing of FIG. 1 in a first embodiment of the invention,
  • FIG. 3 is a view from above of the casing of FIG. 1 in a second embodiment of the invention,
  • FIG. 4 is a view from above of the casing of FIG. 1 in a third embodiment of the invention,
  • FIGS. 5 and 6 are curves illustrating the evolution of the compression ratio as a function respectively of the efficiency and the compressor inlet flow rate according to the prior art and with the invention, and
  • FIG. 7 is a view of the interior of the casing of FIG. 1 in a variant of the first embodiment of the invention,
  • FIG. 8 is a section along plane VIII-VIII of FIG. 7,
  • FIG. 9 is a section similar to that of FIG. 7 for a first embodiment of the housing, and
  • Figures 10 and 11 are views similar to that of Figure 9 for two other variants of the housing.

Description détaillée d'un mode de réalisation préférentielDetailed description of a preferred embodiment

La figure 1 est une vue schématique d'une section d'un compresseur axial haute pression 10 disposé autour d'un axe central longitudinal (axe moteur 12) d'une turbomachine et délimitée à sa partie extérieure par un carter 14 formant une surface de révolution autour de cet axe central longitudinal. Ce compresseur comporte plusieurs étages successifs de compression (dans une direction axiale), chaque étage comportant réparties sur toute la circonférence une pluralité d'aubes mobiles (rotor 16) pouvant tourner autour de l'axe moteur et une pluralité d'aubes fixes (stator 18). Un jeu e existe entre l'extrémité supérieure 20 de chaque aube mobile et le carter fixe 14 qui enveloppe le compresseur. Ce jeu peut être le lieu de violentes turbulences qui peuvent détériorer la configuration de l'écoulement entre les différents étages et donc entraîner une dégradation des performances du compresseur ou, à l'extrême, provoquer un phénomène dit de « pompage » ou de « décrochage » constitué par une chute instantanée du taux de compression et une inversion du débit d'air traversant le compresseur qui sort alors par l'amont du compresseur.FIG. 1 is a schematic view of a section of a high-pressure axial compressor 10 disposed about a longitudinal central axis (motor axis 12) of a turbomachine and delimited at its outer portion by a casing 14 forming a surface of revolution around this central longitudinal axis. This compressor comprises several successive stages of compression (in an axial direction), each stage comprising distributed over the circumference a plurality of blades (rotor 16) rotatable about the motor axis and a plurality of blades (stator 18). A clearance e exists between the upper end 20 of each moving blade and the fixed casing 14 which surrounds the compressor. This game can be the place of violent turbulence which can deteriorate the configuration of the flow between the different stages and thus lead to a degradation of the performances of the compressor or, in the extreme, to cause a phenomenon known as "pumping" or "stalling". Consisting of an instantaneous fall in the compression ratio and an inversion of the air flow through the compressor which then leaves the upstream compressor.

Selon l'invention, la plage de sécurité en fonctionnement vis-à-vis du pompage est augmentée par l'adjonction d'un dispositif de prélèvement d'air disposé en tête des aubes mobiles, c'est-à-dire sensiblement au niveau de son bord d'attaque 22.According to the invention, the safety range in operation with respect to pumping is increased by the addition of an air sampling device disposed at the top of the blades, that is to say substantially at the level of from his leading edge 22.

Ce dispositif de prélèvement comporte une pluralité de trous 24, de préférence cylindriques, pratiqués dans le carter fixe 14, centrés entre 5 et 50% de la longueur de corde de l'aube et d'un diamètre inférieur ou égal à 30% de la longueur de corde de l'aube, la corde de l'aube étant le segment de droite reliant le bord d'attaque au bord de fuite d'une aube mobile. Le nombre des trous de prélèvement est déterminé en fonction du débit d'air à prélever par rapport au débit d'air global traversant le compresseur. Typiquement, un débit d'air compris entre 0,1 et 5 % garantit une efficacité de fonctionnement du dispositif selon les différentes mesures effectuées par les inventeurs.This sampling device comprises a plurality of holes 24, preferably cylindrical, made in the fixed casing 14, centered between 5 and 50% of the length of rope of the blade and having a diameter less than or equal to 30% of the rope length of dawn, the rope of dawn being the line segment connecting the leading edge to the trailing edge of a moving blade. The number of sampling holes is determined as a function of the air flow rate to be taken with respect to the overall air flow through the compressor. Typically, an air flow rate of between 0.1 and 5% guarantees operating efficiency of the device according to the different measurements made by the inventors.

Ces trous de prélèvement présentent une double inclinaison avec un premier axe projeté dans le plan aube à aube présentant un angle ϕ par rapport à l'axe moteur compris entre 30 et 90° (voir la figure 2) et un second axe projeté dans le plan méridien (perpendicularité au premier) présentant un angle θ par rapport à l'axe moteur compris entre 30 et 90°. Le choix des angles optimaux ϕ et θ est effectué notamment en fonction de la charge aérodynamique désirée (i.e au travail de compression de l'air fourni par le rotor) donnée par la relation suivante :
ψ = ΔH/V2 avec ΔH l'augmentation d'enthalpie au passage du rotor et V la vitesse de rotation du compresseur.These sampling holes have a double inclination with a first axis projected in the blade vane plane having an angle φ relative to the motor axis of between 30 and 90 ° (see FIG. 2) and a second axis projected in the plane. meridian (perpendicular to the first) having an angle θ relative to the motor axis between 30 and 90 °. The choice of the optimum angles φ and θ is made in particular according to the desired aerodynamic load (ie to the work of compression of the air supplied by the rotor) given by the following relation:
ψ = ΔH / V 2 with ΔH the enthalpy increase at the passage of the rotor and V the speed of rotation of the compressor.

Bien entendu, cette configuration cylindrique des trous de prélèvement et cette disposition linéaire sur une seule rangée ne sauraient être limitatives. La figure 3 montre par exemple une disposition de ces trous de prélèvement selon deux rangées, les trous étant disposés en quinconce dans la limite définie précédemment de 5 à 50% de la longueur de corde de l'aube. Sur la figure 4, ces trous de prélèvement ont une forme non circulaire, carré ou oblong par exemple.Of course, this cylindrical configuration of sampling holes and this linear arrangement on a single row can not be limiting. FIG. 3 shows, for example, an arrangement of these sampling holes in two rows, the holes being staggered in the previously defined limit of 5 to 50% of the length of rope of the blade. On the Figure 4, these sampling holes have a non-circular shape, square or oblong, for example.

On peut aussi envisager des trous de prélèvement en forme de fente axisymétrique. Avec ces exemples de réalisation de la présente invention, l'air qui se faufile classiquement par le jeu e au-dessus des extrémités 20 des aubes mobiles du fait de la différence de pression existant entre les faces intrados et extrados de ces aubes, est en partie aspiré par les trous de prélèvement 24. La diminution de ce flux parasite entre les deux faces d'une même aube a pour effet immédiat d'augmenter la stabilité et les performances du compresseur. En outre, l'air prélevé peut rejoindre, éventuellement via un système de tôles protectrices (non représentées), les collecteurs de prélèvement existants de la turbomachine pour une utilisation moteur ou autre, par exemple avionique.It is also possible to envisage sampling holes in the form of an axisymmetric slit. With these exemplary embodiments of the present invention, the air which conventionally sneaks by the clearance e above the ends 20 of the blades because of the pressure difference existing between the intrados and extrados faces of these blades, is in fact Part sucked by the sampling holes 24. The decrease in this parasitic flux between the two faces of the same blade has the immediate effect of increasing the stability and performance of the compressor. In addition, the collected air can join, possibly via a system of protective sheets (not shown), existing sampling collectors of the turbomachine for use engine or other, for example avionics.

Ainsi, l'amélioration obtenue par ce dispositif de prélèvement est particulièrement importante et procure une augmentation notable du rendement de l'aube et de la plage de fonctionnement du compresseur comme l'illustrent la figure 5, qui montre la variation du taux de compression en fonction du rendement du compresseur pour un compresseur de l'art antérieur (courbe 30) et pour compresseur muni du dispositif selon l'invention (courbe 32) et la figure 6 qui montre la variation du taux de compression en fonction du débit d'entrée du compresseur pour un compresseur de l'art antérieur (courbe 40) et pour un compresseur muni du dispositif selon l'invention (courbe 42).Thus, the improvement obtained by this sampling device is particularly important and provides a significant increase in the efficiency of the blade and the operating range of the compressor as shown in Figure 5, which shows the variation of the compression ratio in compressor efficiency function for a compressor of the prior art (curve 30) and for a compressor provided with the device according to the invention (curve 32) and FIG. 6 which shows the variation of the compression ratio as a function of the inlet flow rate compressor for a compressor of the prior art (curve 40) and for a compressor provided with the device according to the invention (curve 42).

L'efficacité du dispositif peut encore être amélioré en orientant l'air directement vers les trous de prélèvement comme l'illustre les figures 7 et 8 qui montrent l'adjonction de lamelles obliques 50 disposées sur le carter fixe au droit de la pluralité d'aubes mobiles de part et d'autre de chaque trou de prélèvement 24. Ces lamelles usinées directement dans le carter ou rapportées à celui-ci sont orientées selon le même angle ϕ par rapport à l'axe moteur 12 que les trous de prélèvement.The efficiency of the device can be further improved by directing the air directly towards the sampling holes as illustrated in FIGS. 7 and 8 which show the addition of oblique lamellae 50 arranged on the fixed casing to the right of the plurality of Vane moving on either side of each sampling hole 24. These lamellae machined directly in the housing or reported thereto are oriented at the same angle φ relative to the motor axis 12 as the sampling holes.

On notera que cette configuration comme les précédentes peuvent être implantées sur un carter 14 comprenant un retrait au droit de l'aube (appellé trench 52) comme le montre la figure 9, ou encore comprenant un rainurage 54 au droit de l'aube (appellé traitement de carter) comme le montrent les figures 10 et 11. On notera que sur la figure 10, le rainurage est répartie autour du trou de prélèvement 24 alors que, sur la figure 11, le trou de prélèvement débouche en fond de rainurage.It will be noted that this configuration, like the previous ones, can be implanted on a housing 14 comprising a withdrawal at the right of the blade (called trench 52) as shown in FIG. 9, or else including a groove 54 at the right of the blade (called housing treatment) as shown in Figures 10 and 11. Note that in Figure 10, the grooving is distributed around the sampling hole 24 while, in Figure 11, the sampling hole opens bottom grooving.

Bien entendu, si la description ci-dessus a été faite essentiellement en référence à un compresseur axial haute pression, le dispositif de l'invention peut trouver application aussi au niveau d'un ou plusieurs étages transsoniques d'un compresseur haute pression ou sur un compresseur basse pression. De même, la présente invention ne saurait être limitée à la structure de fixation et d'entrainement des aubes mobiles représentée sur la figure 1 et une structure mettant en oeuvre des attaches dites brochées ou marteau est tout aussi envisageable.Of course, if the above description has been made essentially with reference to a high pressure axial compressor, the device of the invention can also be used at one or more transonic stages of a high pressure compressor or on a low pressure compressor. Similarly, the present invention can not be limited to the fastening and driving structure of the blades shown in Figure 1 and a structure employing so-called staples or hammer is also conceivable.

Claims (9)

Compresseur de turbomachine comportant au moins une pluralité d'aubes mobiles (16) et, espacée dans une direction axiale par rapport à un axe central longitudinal de la turbomachine (12), une pluralité d'aubes fixes (18), un carter fixe (14) enveloppant ladite pluralité d'aubes mobiles, caractérisé en ce que ledit carter fixe comporte une pluralité de trous de prélèvement (24) centrés entre 5 et 50% de la longueur de corde de l'aube et d'un diamètre inférieur ou égal à 30% de ladite longueur de corde de l'aube, chacun desdits trous de prélèvement présentant une double inclinaison par rapport audit axe central longitudinal.A turbomachine compressor comprising at least a plurality of moving blades (16) and, spaced in an axial direction relative to a longitudinal central axis of the turbomachine (12), a plurality of stationary vanes (18), a stationary housing ( 14) enclosing said plurality of blades, characterized in that said stationary housing comprises a plurality of sampling holes (24) centered between 5 and 50% of the length of rope of the blade and of a diameter less than or equal to at 30% of said length of rope of the blade, each of said sampling holes having a double inclination with respect to said longitudinal central axis. Compresseur de turbomachine selon la revendication 1, caractérisé en ce que lesdits trous de prélèvement comportent chacun un premier axe d'inclinaison présentant un angle ϕ par rapport à l'axe central longitudinal compris entre 30 et 90° et un second axe d'inclinaison perpendiculaire au premier et présentant un angle θ par rapport à l'axe central longitudinal compris entre 30 et 90°.A turbomachine compressor according to claim 1, characterized in that said sampling holes each comprise a first inclination axis having an angle φ with respect to the longitudinal central axis of between 30 and 90 ° and a second axis of perpendicular inclination at the first and having an angle θ with respect to the longitudinal central axis of between 30 and 90 °. Compresseur de turbomachine selon la revendication 1 ou la revendication 2, caractérisé en ce que le rapport entre le débit d'air global de la turbomachine et le débit d'air prélevé est compris entre 0,1 et 5 %.Turbomachine compressor according to claim 1 or claim 2, characterized in that the ratio between the overall air flow of the turbomachine and the air flow rate taken is between 0.1 and 5%. Compresseur de turbomachine selon la revendication 1 ou la revendication 2, caractérisé en ce que ledit carter fixe comporte en outre des lamelles obliques (50) disposées au droit de ladite pluralité d'aubes mobiles de part et d'autre de chaque trou de prélèvement et orientées selon ledit angle ϕ.A turbomachine compressor according to claim 1 or claim 2, characterized in that said fixed casing further comprises oblique lamellae (50) arranged in line with said plurality of blades on both sides of each sampling hole and oriented according to said angle φ. Compresseur de turbomachine selon l'une quelconque de revendications 1 à 4, caractérisé en ce que ledit carter fixe comporte en outre un rainurage (54) disposé autour de de chaque trou de prélèvement.A turbomachine compressor according to any one of claims 1 to 4, characterized in that said fixed housing further comprises a groove (54) disposed around each sampling hole. Compresseur de turbomachine selon l'une quelconque de revendications 1 à 5, caractérisé en ce que lesdits trous de prélèvement sont disposés en quinconce.Turbomachine compressor according to any one of claims 1 to 5, characterized in that said sampling holes are arranged in staggered rows. Compresseur de turbomachine selon l'une quelconque de revendications 1 à 5, caractérisé en ce que lesdits trous de prélèvement sont non circulaires.Turbomachine compressor according to any one of claims 1 to 5, characterized in that said sampling holes are non-circular. Compresseur de turbomachine selon l'une quelconque de revendications 1 à 5, caractérisé en ce que lesdits trous de prélèvement sont formés de fentes axisymétriques.Turbomachine compressor according to any one of claims 1 to 5, characterized in that said sampling holes are formed axially symmetrical slots. Turbomachine comportant un compresseur axial haute pression selon l'une quelconque de revendications 1 à 8.Turbine engine comprising a high-pressure axial compressor according to any one of claims 1 to 8.
EP06100669.8A 2005-02-16 2006-01-20 Bleeding air from the tip of the rotating blades in a high pressure compressor of a turbine engine Active EP1693572B1 (en)

Applications Claiming Priority (1)

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FR0501567A FR2882112B1 (en) 2005-02-16 2005-02-16 HEAD SAMPLING OF HIGH PRESSURE COMPRESSOR MOBILE WHEELS FROM TURBOREACTOR

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CA2536132A1 (en) 2006-08-16
JP2006226285A (en) 2006-08-31
FR2882112A1 (en) 2006-08-18
CN1840864B (en) 2010-05-26
RU2006104789A (en) 2007-09-27
US20060182623A1 (en) 2006-08-17
CN1840864A (en) 2006-10-04
US7549838B2 (en) 2009-06-23
FR2882112B1 (en) 2007-05-11
JP5004476B2 (en) 2012-08-22
CA2536132C (en) 2013-06-18
EP1693572B1 (en) 2015-11-04
RU2395010C2 (en) 2010-07-20
EP1693572A3 (en) 2011-05-18

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