WO2010103055A1 - Axial centrifugal compressor with scalable rake angle - Google Patents

Axial centrifugal compressor with scalable rake angle Download PDF

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Publication number
WO2010103055A1
WO2010103055A1 PCT/EP2010/053057 EP2010053057W WO2010103055A1 WO 2010103055 A1 WO2010103055 A1 WO 2010103055A1 EP 2010053057 W EP2010053057 W EP 2010053057W WO 2010103055 A1 WO2010103055 A1 WO 2010103055A1
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WO
WIPO (PCT)
Prior art keywords
trailing edge
blade
head
compressor
foot
Prior art date
Application number
PCT/EP2010/053057
Other languages
French (fr)
Inventor
Geoffroy Louis Henri Billotey
Jean-Philippe Ousty
Nicolas Rochuon
Original Assignee
Turbomeca
Priority date (The priority date is an assumption and is not a legal conclusion. Google has not performed a legal analysis and makes no representation as to the accuracy of the date listed.)
Filing date
Publication date
Application filed by Turbomeca filed Critical Turbomeca
Priority to JP2011553449A priority Critical patent/JP5687215B2/en
Priority to US13/256,371 priority patent/US20110318188A1/en
Priority to RU2011141460/06A priority patent/RU2011141460A/en
Priority to CN201080010678.8A priority patent/CN102341602B/en
Priority to CA2755017A priority patent/CA2755017C/en
Priority to KR1020117024047A priority patent/KR101746870B1/en
Priority to EP10707910A priority patent/EP2406500A1/en
Publication of WO2010103055A1 publication Critical patent/WO2010103055A1/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
    • F04D29/26—Rotors specially for elastic fluids
    • F04D29/28—Rotors specially for elastic fluids for centrifugal or helico-centrifugal pumps for radial-flow or helico-centrifugal pumps
    • F04D29/30—Vanes
    • 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
    • F01D5/04—Blade-carrying members, e.g. rotors for radial-flow machines or engines
    • F01D5/043—Blade-carrying members, e.g. rotors for radial-flow machines or engines of the axial inlet- radial outlet, or vice versa, type
    • F01D5/048—Form or construction
    • 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
    • F04D29/28—Rotors specially for elastic fluids for centrifugal or helico-centrifugal pumps for radial-flow or helico-centrifugal pumps
    • F04D29/284—Rotors specially for elastic fluids for centrifugal or helico-centrifugal pumps for radial-flow or helico-centrifugal pumps for 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
    • F04D29/26—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
    • F04D29/324—Blades
    • 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
    • Y02—TECHNOLOGIES OR APPLICATIONS FOR MITIGATION OR ADAPTATION AGAINST CLIMATE CHANGE
    • Y02T—CLIMATE CHANGE MITIGATION TECHNOLOGIES RELATED TO TRANSPORTATION
    • Y02T50/00—Aeronautics or air transport
    • Y02T50/60—Efficient propulsion technologies, e.g. for aircraft

Definitions

  • the field of the present invention is that of turbomachines and more particularly that of turbomachine compressors comprising at least one centrifugal or mixed (axial-centrifugal) compression stage.
  • Aeronautical turboshaft engines and in particular helicopter turboshaft engines generally comprise a compressor of the centrifugal or mixed type, as the compression stage of the gas generator.
  • These compressors are formed of moving wheels or wheels, which have a substantially axial air inlet and a more radial outlet, the vanes being fixed on a bell-shaped base, which serves as a guide to the flow of air and the deviation of the direction of entry to the exit direction. The flow thus circulates between this base and a compressor casing; it is compressed and propelled by the different vanes of the wheel.
  • the head of the blades is free and positioned facing the housing, or cover, which closes the air vein.
  • the trailing edge is rectilinear in the prior art and may be inclined relative to the meridian plane of the wheel passing through the root of the blade. The angle it makes with this meridian plane is referred to as the rake angle, or slope angle of the trailing edge, and is one of the relevant geometrical parameters for describing a spinning wheel impeller.
  • the object of the present invention is to remedy these drawbacks by proposing a centrifugal or mixed axial-centrifugal compressor which does not have some of the drawbacks of the prior art and, in particular, which has a trailing edge with a significant slope angle. at its foot, without a phenomenon of self-engagement of the dawn head in case of contact of the latter with the lid.
  • the subject of the invention is a mobile wheel for a centrifugal or mixed axial-centrifugal turbomachine compressor, comprising a base on which are fixed by their feet a plurality of blades extending between a leading edge and a trailing edge, said trailing edge being inclined at the root of the blade of an angle of inclination with respect to the meridian plane which passes through it in its foot, in the direction of rotation of said compressor, characterized in that the edge leakage present at the head of the blade an angle of slope ⁇ less than its slope angle ⁇ at the bottom of the blade.
  • the wedge formed by the trailing edge and the head of the blade moves more tangentially with respect to the housing and is therefore less able to penetrate into it. accidental contact.
  • the slope angle ⁇ of the trailing edge at the head of the blade is close to zero, or even zero.
  • even more preferential slope angle ⁇ of the trailing edge at the head of blade is negative.
  • the curvature of the trailing edge is continuously variable between the foot and the head of said trailing edge.
  • the trailing edge is then in the form of a helix.
  • the invention also relates to a turbomachine comprising a compressor having one of the characteristics described above. Finally, it relates to an aircraft equipped with such a turbomachine.
  • FIG. 1 is a perspective view of a centrifugal compressor impeller according to one embodiment of the invention
  • FIG. 2 is a front view of a trailing edge of a centrifugal compressor blade according to the prior art
  • FIG. 3 is a front view of a trailing edge of a centrifugal compressor blade according to one embodiment of the invention.
  • centrifugal compressor 1 comprising a base 2, bell-shaped, on which are fixed compressor blades 3 regularly distributed on the periphery of the base 2.
  • the base 2 ends at its part upper, which corresponds to the plane of entry of the air to be compressed by a hub cylinder 4 for the compressor, and at its bottom by a disk 5 oriented radially relative to the axis of rotation of said compressor.
  • the blades 3 are held by the base 2 at their foot 6; the heads 7 of these blades are free and rotate inside a compressor housing (not shown).
  • the vanes In the direction of the flow of the air vein the vanes extend between a leading edge 8 located at the hub 4 and a trailing edge 9 located at the disc 5.
  • FIG 2 shows a trailing edge 9 of a compressor blade 3, according to the prior art.
  • This trailing edge is, at its foot, inclined relative to the meridian plane which passes through, in the direction of rotation, a slope angle ⁇ .
  • This trailing edge 9 is rectilinear, that is to say that it has the same inclination, equal to its value ⁇ at the bottom of the blade, over its entire height, from the foot to the head of the edge of 9.
  • the trailing edge 9 has an evolutionary shape along its height.
  • the proposed invention thus consists in choosing, at the trailing edge 9, a slope angle ⁇ high at the blade root 6, then applying a curvature to the blade 3 so as to find a lower slope angle or even zero or negative at the head of blading.
  • a high slope angle ⁇ at the blade root 6 makes it possible to reduce the bending stresses in the foot, whereas the low angle of inclination ⁇ at the level of the head 7 reduces the risks of self-engagement of the blade 3 in the housing in case of accidental contact between the head 7 of the blade at the trailing edge 9 and the housing.
  • the invention therefore allows a gain in mass and inertia, or iso-mass and iso-inertia an increase in the speed of rotation, without degrading the behavior in case of contact between the blade 3 and the housing.
  • the curvature may for example be constant, the trailing edge having a shape of an arc of circle, or be continuously variable, the profile of the trailing edge then having the shape of a helix.
  • the choice of curvature between the foot and the head of the dawn is based on the impact it has on the aerodynamic performance of the compressor.

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  • Engineering & Computer Science (AREA)
  • Mechanical Engineering (AREA)
  • General Engineering & Computer Science (AREA)
  • Structures Of Non-Positive Displacement Pumps (AREA)

Abstract

The invention relates to a mobile wheel for a centrifugal or axial centrifugal compressor for a turbine engine, that comprises a base (2) on which a plurality of vanes (3) are attached at their feet (6) and extend between a leading edge (8) and a trailing edge (9), said trailing edge being inclined at the base (6) of the vane (3) by a slope angle α relative to the middle plane extending through the base thereof in the rotation direction of said compressor (1), characterised in that the trailing edge (9) has at the head (7) of the vane (3) a slope angle β smaller than the slope angle α at the vane base.

Description

COMPRESSEUR AXIALO -CENTRIFUGE A ANGLE DE RAKE AXIALO COMPRESSOR -CENTRIFUGE WITH ANGLE OF RAKE
EVOLUTIFSCALABLE
Le domaine de la présente invention est celui des turbomachines et plus particulièrement celui des compresseurs pour turbomachine comprenant au moins un étage de compression centrifuge ou mixte (axialo-centrifuge).The field of the present invention is that of turbomachines and more particularly that of turbomachine compressors comprising at least one centrifugal or mixed (axial-centrifugal) compression stage.
Les turbomoteurs aéronautiques et en particulier les turbomoteurs pour hélicoptères comportent généralement un compresseur de type centrifuge ou mixte, comme étage de compression du générateur de gaz. Ces compresseurs sont formés de roues mobiles ou rouets, qui ont une entrée d'air sensiblement axiale et une sortie plus radiale, les aubes étant fixées sur un socle en forme de cloche, qui sert de guide au flux d'air et le dévie de la direction d'entrée vers la direction de sortie. Le flux circule ainsi entre ce socle et un carter de compresseur ; il est comprimé et propulsé par les différentes aubes du rouet.Aeronautical turboshaft engines and in particular helicopter turboshaft engines generally comprise a compressor of the centrifugal or mixed type, as the compression stage of the gas generator. These compressors are formed of moving wheels or wheels, which have a substantially axial air inlet and a more radial outlet, the vanes being fixed on a bell-shaped base, which serves as a guide to the flow of air and the deviation of the direction of entry to the exit direction. The flow thus circulates between this base and a compressor casing; it is compressed and propelled by the different vanes of the wheel.
La tête des aubages est libre et positionnée en regard du carter, ou couvercle, qui referme la veine d'air. Le bord de fuite est rectiligne dans l'art antérieur et peut être incliné par rapport au plan méridien du rouet passant par le pied de l'aube. L'angle qu'il fait avec ce plan méridien est désigné sous le nom d'angle de rake, ou angle de pente du bord de fuite, et constitue un des paramètres géométriques pertinents pour décrire un aubage de rouet centrifuge.The head of the blades is free and positioned facing the housing, or cover, which closes the air vein. The trailing edge is rectilinear in the prior art and may be inclined relative to the meridian plane of the wheel passing through the root of the blade. The angle it makes with this meridian plane is referred to as the rake angle, or slope angle of the trailing edge, and is one of the relevant geometrical parameters for describing a spinning wheel impeller.
Le choix d'un angle de pente significatif (de l'ordre, par exemple, de 20°) en bord de fuite d'un rouet centrifuge est un moyen connu de réduire les contraintes en pied d'aube, qui sont dues en particulier à la flexion de l' aubage sous effort centrifuge. Il permet ainsi une conception plus performante du compresseur, et notamment :The choice of a significant slope angle (of the order of, for example, 20 °) at the trailing edge of a centrifugal impeller is a known way of reducing the stresses at the root of the blade, which are due in particular bending of the blade under centrifugal force. It thus allows a more efficient design of the compressor, and in particular:
- de réduire, à iso-vitesse de rotation, l'épaisseur de l' aubage, et donc celle du voile du socle et ainsi de diminuer de façon significative la masse et l'inertie du rotor.- To reduce, at iso-rotational speed, the thickness of the vane, and therefore that of the veil of the base and thus significantly reduce the mass and inertia of the rotor.
- ou bien, à iso-masse et inertie pour le rouet, d'augmenter la vitesse de rotation.- or, at iso-mass and inertia for the impeller, to increase the speed of rotation.
On connaît par exemple le document US 5730582 qui décrit un rouet centrifuge pour un compresseur de turbomachine. Sur ce rouet, qui a la forme d'une hélice inscrite dans un cylindre, l'angle de pente est constant tout le long du bord de fuite.For example, document US Pat. No. 5,730,582 describes a centrifugal wheel for a turbomachine compressor. On this wheel, which in the form of a helix inscribed in a cylinder, the slope angle is constant all along the trailing edge.
Le choix d'un angle de pente significatif a pour conséquence, avec un bord de fuite rectiligne, que la tête de l'aubage est inclinée du même angle que le pied par rapport à ce plan méridien. En cas de contact accidentel de l'aubage avec le couvercle, si le bord de fuite est incliné dans le sens de rotation du rouet, la tête de l'aube a tendance à s'auto- engager dans le métal ce qui risque de générer des dégradations importantes. On connaît par ailleurs le document US 4819884, qui porte sur un dispositif de ventilation comportant un rouet dont l'angle de pente va en augmentant du pied des pales vers leur tête et dont la tête est prise dans un plateau, évitant ainsi tout risque d'engagement des aubes dans le carter du dispositif. La présente invention a pour but de remédier à ces inconvénients en proposant un compresseur centrifuge ou mixte axialo- centrifuge qui ne présente pas certains des inconvénients de l'art antérieur et, en particulier, qui présente un bord de fuite avec un angle de pente significatif à son pied, sans que se produise un phénomène d'auto- engagement de la tête de l'aube en cas de contact de celle-ci avec le couvercle.The choice of a significant slope angle has the consequence, with a rectilinear trailing edge, that the head of the blade is inclined at the same angle as the foot relative to this meridian plane. In case of accidental contact of the blade with the lid, if the trailing edge is inclined in the direction of rotation of the impeller, the head of the blade tends to self-engage in the metal which may generate significant damage. Document US Pat. No. 4,819,884 is also known, which relates to a ventilation device comprising a spinning wheel whose angle of inclination is increasing from the foot of the blades towards their head and whose head is caught in a plate, thus avoiding any risk of engagement of the blades in the housing of the device. The object of the present invention is to remedy these drawbacks by proposing a centrifugal or mixed axial-centrifugal compressor which does not have some of the drawbacks of the prior art and, in particular, which has a trailing edge with a significant slope angle. at its foot, without a phenomenon of self-engagement of the dawn head in case of contact of the latter with the lid.
A cet effet, l'invention a pour objet une roue mobile pour compresseur centrifuge ou mixte axialo-centrifuge de turbomachine, comportant un socle sur lequel sont fixées par leur pied une pluralité d'aubes s'étendant entre un bord d'attaque et un bord de fuite, ledit bord de fuite étant incliné au niveau du pied de l'aube d'un angle de pente par rapport au plan méridien qui le traverse en son pied, dans le sens de rotation dudit compresseur, caractérisé en ce que le bord de fuite présente au niveau de la tête de l'aube un angle de pente β inférieur à son angle de pente α en pied d'aube.For this purpose, the subject of the invention is a mobile wheel for a centrifugal or mixed axial-centrifugal turbomachine compressor, comprising a base on which are fixed by their feet a plurality of blades extending between a leading edge and a trailing edge, said trailing edge being inclined at the root of the blade of an angle of inclination with respect to the meridian plane which passes through it in its foot, in the direction of rotation of said compressor, characterized in that the edge leakage present at the head of the blade an angle of slope β less than its slope angle α at the bottom of the blade.
L'angle de pente au niveau de la tête étant plus faible, le coin constitué par le bord de fuite et la tête de l'aube se déplace plus tangentiellement par rapport au carter et est donc moins à même de pénétrer dans celui-ci en cas de contact accidentel. De façon préférentielle l'angle de pente β du bord de fuite en tête d'aube est proche de zéro, voire nul. Et de façon encore plus préférentielle l'angle de pente β du bord de fuite en tête d'aube est négatif. Ces configurations améliorent l'assurance que le coin en tête du bord de fuite ne pourra pas s'implanter dans le carter en cas de contact accidentel. Dans un mode particulier de réalisation la courbure du bord de fuite est constante entre le pied et la tête dudit bord de fuite. Le bord de fuite a alors la forme d'un arc de cercle.Since the angle of inclination at the head is lower, the wedge formed by the trailing edge and the head of the blade moves more tangentially with respect to the housing and is therefore less able to penetrate into it. accidental contact. Preferably, the slope angle β of the trailing edge at the head of the blade is close to zero, or even zero. And even more preferential slope angle β of the trailing edge at the head of blade is negative. These configurations improve the assurance that the leading edge of the trailing edge can not be installed in the housing in case of accidental contact. In a particular embodiment, the curvature of the trailing edge is constant between the foot and the head of the trailing edge. The trailing edge then has the shape of an arc.
Dans un autre mode de réalisation la courbure du bord de fuite est continûment variable entre le pied et la tête dudit bord de fuite. Le bord de fuite a alors la forme d'une hélice.In another embodiment the curvature of the trailing edge is continuously variable between the foot and the head of said trailing edge. The trailing edge is then in the form of a helix.
L'invention concerne également une turbomachine comprenant un compresseur comportant une des caractéristiques décrites ci-dessus. Il concerne enfin un aéronef équipé d'une telle turbomachine.The invention also relates to a turbomachine comprising a compressor having one of the characteristics described above. Finally, it relates to an aircraft equipped with such a turbomachine.
L'invention sera mieux comprise, et d'autres buts, détails, caractéristiques et avantages de celle-ci apparaîtront plus clairement au cours de la description explicative détaillée qui va suivre, d'un mode de réalisation de l'invention donné à titre d'exemple purement illustratif et non limitatif, en référence aux dessins schématiques annexés.The invention will be better understood, and other objects, details, features and advantages thereof will appear more clearly in the following detailed explanatory description of an embodiment of the invention given as a purely illustrative and non-limiting example, with reference to the accompanying schematic drawings.
Sur ces dessins : - la figure 1 est une vue en perspective d'un rouet de compresseur centrifuge selon un mode de réalisation de l'invention ;In these drawings: FIG. 1 is a perspective view of a centrifugal compressor impeller according to one embodiment of the invention;
- la figure 2 est une vue de face d'un bord de fuite d'une aube de compresseur centrifuge selon l'art antérieur, etFIG. 2 is a front view of a trailing edge of a centrifugal compressor blade according to the prior art, and
- la figure 3 est une vue de face d'un bord de fuite d'une aube de compresseur centrifuge selon un mode de réalisation de l'invention.- Figure 3 is a front view of a trailing edge of a centrifugal compressor blade according to one embodiment of the invention.
En se référant à la figure 1, on voit un compresseur centrifuge 1 comprenant un socle 2, en forme de cloche, sur lequel sont fixées des aubes de compresseur 3 réparties régulièrement sur la périphérie du socle 2. Le socle 2 se termine à sa partie supérieure, qui correspond au plan d'entrée de l'air à comprimer, par un cylindre formant moyeu 4 pour le compresseur, et à sa partie inférieure par un disque 5 orienté radialement par rapport à l'axe de rotation dudit compresseur. Les aubes 3 sont tenues par le socle 2 au niveau de leur pied 6 ; les têtes 7 de ces aubes sont libres et tournent à l'intérieur d'un carter de compresseur (non représenté). Dans le sens de l'écoulement de la veine d'air les aubes s'étendent entre un bord d'attaque 8 situé au niveau du moyeu 4 et un bord de fuite 9 situé au niveau du disque 5.Referring to Figure 1, we see a centrifugal compressor 1 comprising a base 2, bell-shaped, on which are fixed compressor blades 3 regularly distributed on the periphery of the base 2. The base 2 ends at its part upper, which corresponds to the plane of entry of the air to be compressed by a hub cylinder 4 for the compressor, and at its bottom by a disk 5 oriented radially relative to the axis of rotation of said compressor. The blades 3 are held by the base 2 at their foot 6; the heads 7 of these blades are free and rotate inside a compressor housing (not shown). In the direction of the flow of the air vein the vanes extend between a leading edge 8 located at the hub 4 and a trailing edge 9 located at the disc 5.
En se référant maintenant à la figure 2 on voit un bord de fuite 9 d'une aube de compresseur 3, selon l'art antérieur. Ce bord de fuite est, au niveau de son pied, incliné par rapport au plan méridien qui le traverse, dans le sens de rotation, d'un angle de pente α. Ce bord de fuite 9 est rectiligne, c'est-à-dire qu'il présente une même inclinaison, égale à sa valeur α en pied d'aube, sur toute sa hauteur, depuis le pied jusqu'à la tête du bord de fuite 9. En revanche, sur la figure 3, le bord de fuite 9 présente une forme évolutive le long de sa hauteur. Il est incliné d'un angle de pente α dans le sens de rotation, au niveau du pied 6 de l'aube 3, qui est défini comme dans l'art antérieur, mais cet angle se réduit progressivement en montant le long du bord de fuite pour atteindre une valeur β au niveau de la tête 7 de l'aube 3, qui est inférieure à α. Cette valeur β peut être nulle ou même négative, c'est-à-dire que la tête de l'aube est alors inclinée dans le sens inverse du sens de rotation du rouet.Referring now to Figure 2 shows a trailing edge 9 of a compressor blade 3, according to the prior art. This trailing edge is, at its foot, inclined relative to the meridian plane which passes through, in the direction of rotation, a slope angle α. This trailing edge 9 is rectilinear, that is to say that it has the same inclination, equal to its value α at the bottom of the blade, over its entire height, from the foot to the head of the edge of 9. In contrast, in Figure 3, the trailing edge 9 has an evolutionary shape along its height. It is inclined by an angle of slope α in the direction of rotation, at the level of the root 6 of the blade 3, which is defined as in the prior art, but this angle is gradually reduced by climbing along the edge of leak to reach a value β at the head 7 of the blade 3, which is less than α. This β value can be zero or even negative, that is to say that the head of the blade is then inclined in the opposite direction of rotation of the impeller.
L'invention proposée consiste donc à choisir, au niveau du bord de fuite 9, un angle de pente α élevé en pied d'aube 6, puis à appliquer une courbure à l'aubage 3 de façon à retrouver un angle de pente plus faible, voire nul ou négatif, en tête d'aubage. La présence d'un angle de pente α élevé en pied d'aube 6 permet la diminution des contraintes de flexion en pied, tandis que l'angle de pente faible β au niveau de la tête 7 réduit les risques d'auto-engagement de l'aube 3 dans le carter en cas de contact accidentel entre la tête 7 de l'aube au bord de fuite 9 et le carter.The proposed invention thus consists in choosing, at the trailing edge 9, a slope angle α high at the blade root 6, then applying a curvature to the blade 3 so as to find a lower slope angle or even zero or negative at the head of blading. The presence of a high slope angle α at the blade root 6 makes it possible to reduce the bending stresses in the foot, whereas the low angle of inclination β at the level of the head 7 reduces the risks of self-engagement of the blade 3 in the housing in case of accidental contact between the head 7 of the blade at the trailing edge 9 and the housing.
La réalisation d'un tel profil au bord de fuite 9 s'appuie sur la méthode d'usinage par points qui permet des géométries d'aubages 3D ; par opposition l'usinage par flanc utilisé antérieurement, restreignait les possibilités en imposant des surfaces réglées (c'est-à-dire constituées d'un empilement de lignes droites) pour la conception du profil des aubes.The production of such a profile at the trailing edge 9 is based on the method of machining by points which allows 3D blade geometries; as opposed to previously used flanging, restricted the possibilities by imposing regulated surfaces (i.e., consisting of a stack of straight lines) for the design of the blade profile.
Cette modification de la géométrie du profil ne se traduit pas par un impact aérodynamique significatif. Le recours à des aubes 3 selon l'invention contribue même, de façon surprenante, plutôt à une augmentation des performances du compresseur, résultant de la diminution de l'angle de pente le long de la hauteur du bord de fuite 9.This modification of the geometry of the profile does not result in a significant aerodynamic impact. The use of blades 3 according to the invention even contributes, surprisingly, rather to a increased compressor performance as a result of decreasing the slope angle along the trailing edge height 9.
La double diminution des contraintes dans l'aubage et du caractère auto-engageant de la tête de l'aube, par application de l'invention, ont été vérifiées par calcul sur un aubage réel.The double decrease of the stresses in the vane and the self-engaging nature of the blade head, by application of the invention, were verified by calculation on a real vane.
L'invention permet donc un gain de masse et d'inertie, ou à iso-masse et iso-inertie une augmentation de la vitesse de rotation, sans dégrader le comportement en cas de contact entre l'aube 3 et le carter.The invention therefore allows a gain in mass and inertia, or iso-mass and iso-inertia an increase in the speed of rotation, without degrading the behavior in case of contact between the blade 3 and the housing.
Plusieurs variantes peuvent être envisagées pour l'évolution de la courbure de l'aube 3 au bord de fuite 9 entre son pied 6 et sa tête 7. La courbure peut par exemple être constante, le bord de fuite ayant une forme d'arc de cercle, ou bien être continûment variable, le profil du bord de fuite ayant alors la forme d'une hélice. Le choix de la courbure entre le pied et la tête de l'aube s'effectue en fonction de l'impact qu'elle a sur les performances aérodynamiques du compresseur.Several variants can be envisaged for the evolution of the curvature of the blade 3 at the trailing edge 9 between its foot 6 and its head 7. The curvature may for example be constant, the trailing edge having a shape of an arc of circle, or be continuously variable, the profile of the trailing edge then having the shape of a helix. The choice of curvature between the foot and the head of the dawn is based on the impact it has on the aerodynamic performance of the compressor.
Bien que l'invention ait été décrite en relation avec un mode de réalisation particulier, il est bien évident qu'elle n'y est nullement limitée et qu'elle comprend tous les équivalents techniques des moyens décrits ainsi que leurs combinaisons si celles-ci entrent dans le cadre de l'invention. Although the invention has been described in connection with a particular embodiment, it is obvious that it is not limited thereto and that it comprises all the technical equivalents of the means described and their combinations if they are within the scope of the invention.

Claims

REVENDICATIONS
1. Roue mobile pour compresseur centrifuge ou mixte axialo- centrifuge de turbomachine, comportant un socle (2) sur lequel sont fixées par leur pied (6) une pluralité d'aubes (3) s'étendant entre un bord d'attaque (8) et un bord de fuite (9), ledit bord de fuite étant incliné au niveau du pied (6) de l'aube (3) d'un angle de pente α par rapport au plan méridien qui le traverse en son pied, dans le sens de rotation dudit compresseur (1), caractérisé en ce que le bord de fuite (9) présente au niveau de la tête (7) de l'aube (3) un angle de pente β inférieur à son angle de pente α en pied d'aube.1. A mobile wheel for centrifugal or combined axial-centrifugal turbomachine compressor, comprising a base (2) on which are fixed by their foot (6) a plurality of blades (3) extending between a leading edge (8). ) and a trailing edge (9), said trailing edge being inclined at the level of the foot (6) of the blade (3) of an angle of slope α with respect to the meridian plane which passes through it in its foot, in the direction of rotation of said compressor (1), characterized in that the trailing edge (9) has at the head (7) of the blade (3) an angle of slope β less than its slope angle α in dawn foot.
2. Roue mobile selon la revendication 1 dans lequel l'angle de pente β du bord de fuite (9) en tête d'aube est proche de zéro, voire nul. 2. Mobile wheel according to claim 1 wherein the slope angle β of the trailing edge (9) at the head of the blade is close to zero or zero.
3. Roue mobile selon la revendication 1 dans lequel l'angle de pente β du bord de fuite (9) en tête d'aube est négatif.3. Mobile wheel according to claim 1 wherein the slope angle β of the trailing edge (9) at the head of the blade is negative.
4. Roue mobile selon l'une des revendications 1 à 3 dans lequel la courbure du bord de fuite (9) est constante entre le pied (6) et la tête (7) dudit bord de fuite. 4. Mobile wheel according to one of claims 1 to 3 wherein the curvature of the trailing edge (9) is constant between the foot (6) and the head (7) of said trailing edge.
5. Roue mobile selon l'une des revendications 1 à 3 dans lequel la courbure du bord de fuite (9) est continûment variable entre le pied (6) et la tête (7) dudit bord de fuite.5. Mobile wheel according to one of claims 1 to 3 wherein the curvature of the trailing edge (9) is continuously variable between the foot (6) and the head (7) of said trailing edge.
6. Compresseur comprenant une roue mobile selon l'une des revendications 1 à 56. Compressor comprising a mobile wheel according to one of claims 1 to 5
7. Turbomachine comprenant un compresseur selon la revendication 6.7. A turbomachine comprising a compressor according to claim 6.
8. Aéronef équipé d'une turbomachine selon la revendication précédente. 8. Aircraft equipped with a turbomachine according to the preceding claim.
PCT/EP2010/053057 2009-03-13 2010-03-10 Axial centrifugal compressor with scalable rake angle WO2010103055A1 (en)

Priority Applications (7)

Application Number Priority Date Filing Date Title
JP2011553449A JP5687215B2 (en) 2009-03-13 2010-03-10 Axial flow centrifugal compressor with scalable rake angle
US13/256,371 US20110318188A1 (en) 2009-03-13 2010-03-10 Axial centrifugal compressor with scalable rake angle
RU2011141460/06A RU2011141460A (en) 2009-03-13 2010-03-10 AXIAL-CENTRIFUGAL COMPRESSOR WITH VARIABLE ANGLE OF SLOPE OF THE SHOVEL
CN201080010678.8A CN102341602B (en) 2009-03-13 2010-03-10 Axial centrifugal compressor with scalable rake angle
CA2755017A CA2755017C (en) 2009-03-13 2010-03-10 Axial centrifugal compressor with scalable rake angle
KR1020117024047A KR101746870B1 (en) 2009-03-13 2010-03-10 Axial centrifugal compressor with scalable rake angle
EP10707910A EP2406500A1 (en) 2009-03-13 2010-03-10 Axial centrifugal compressor with scalable rake angle

Applications Claiming Priority (2)

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FR0951604A FR2943103B1 (en) 2009-03-13 2009-03-13 AXIALO-CENTRIFUGAL COMPRESSOR WITH AN EVOLVING RAKE ANGLE
FR0951604 2009-03-13

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JP (1) JP5687215B2 (en)
KR (1) KR101746870B1 (en)
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FR (1) FR2943103B1 (en)
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CA2755017A1 (en) 2010-09-16
CA2755017C (en) 2017-04-04
RU2011141460A (en) 2013-04-20
CN102341602A (en) 2012-02-01
JP2012520412A (en) 2012-09-06
JP5687215B2 (en) 2015-03-18
FR2943103A1 (en) 2010-09-17
US20110318188A1 (en) 2011-12-29
CN102341602B (en) 2015-07-01
EP2406500A1 (en) 2012-01-18
KR101746870B1 (en) 2017-06-14
KR20110129465A (en) 2011-12-01

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