EP2978977A1 - Radial or mixed-flow compressor diffuser having vanes - Google Patents

Radial or mixed-flow compressor diffuser having vanes

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Publication number
EP2978977A1
EP2978977A1 EP14718669.6A EP14718669A EP2978977A1 EP 2978977 A1 EP2978977 A1 EP 2978977A1 EP 14718669 A EP14718669 A EP 14718669A EP 2978977 A1 EP2978977 A1 EP 2978977A1
Authority
EP
European Patent Office
Prior art keywords
leading edge
diffuser
radial
trailing edge
rope
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
EP14718669.6A
Other languages
German (de)
French (fr)
Other versions
EP2978977B1 (en
Inventor
Laurent Tarnowski
Nicolas BULOT
Current Assignee (The listed assignees may be inaccurate. Google has not performed a legal analysis and makes no representation or warranty as to the accuracy of the list.)
Safran Helicopter Engines SAS
Original Assignee
Turbomeca SA
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 SA filed Critical Turbomeca SA
Publication of EP2978977A1 publication Critical patent/EP2978977A1/en
Application granted granted Critical
Publication of EP2978977B1 publication Critical patent/EP2978977B1/en
Active legal-status Critical Current
Anticipated expiration legal-status Critical

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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
    • F04D29/40—Casings; Connections of working fluid
    • F04D29/42—Casings; Connections of working fluid for radial or helico-centrifugal pumps
    • F04D29/44—Fluid-guiding means, e.g. diffusers
    • F04D29/441—Fluid-guiding means, e.g. diffusers especially adapted for elastic fluid pumps
    • F04D29/444—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
    • F04D29/40—Casings; Connections of working fluid
    • F04D29/42—Casings; Connections of working fluid for radial or helico-centrifugal pumps
    • F04D29/44—Fluid-guiding means, e.g. 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
    • F04D17/00—Radial-flow pumps, e.g. centrifugal pumps; Helico-centrifugal pumps
    • F04D17/08—Centrifugal pumps
    • F04D17/10—Centrifugal pumps for compressing or evacuating
    • F04D17/12—Multi-stage pumps
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F05—INDEXING SCHEMES RELATING TO ENGINES OR PUMPS IN VARIOUS SUBCLASSES OF CLASSES F01-F04
    • F05D—INDEXING SCHEME FOR ASPECTS RELATING TO NON-POSITIVE-DISPLACEMENT MACHINES OR ENGINES, GAS-TURBINES OR JET-PROPULSION PLANTS
    • F05D2250/00—Geometry
    • F05D2250/50—Inlet or outlet
    • F05D2250/52—Outlet

Definitions

  • the invention generally relates to gas turbine engines, and more particularly to a diffusion stage of a radial or mixed compressor of a gas turbine, as well as to an associated compressor.
  • a compressor comprises one or more rotating disks (rotor or wheel), bladed or not and one or more fixed vane wheels (rectifier stages).
  • a radial (or centrifugal) compressor has at least one radial compression stage, that is to say capable of producing a flow of gas perpendicular to the central axis of the compressor. It comprises at least one radial impeller which sucks the air axially, which, under the effect of the radial force, is accelerated, compressed and discharged radially. This air is then straightened in a diffuser (fixed blade) which transforms part of its speed into static pressure by slowing the gases at the exit of the wheel. The operation must take place with a minimum of total pressure loss while maintaining a satisfactory compressor stability level in order to maintain an acceptable pumping margin for the operation of the turbomachine.
  • the gases are then guided to the combustion chamber.
  • a mixed compressor (or helico-radial) has at least one compression stage inclined with respect to said central axis, so that the fluid leaves the compressor impeller at a non-zero angle with the radial direction.
  • a diffuser of a radial compressor is composed of a wheel formed of two flanges between which the gases flow radially or inclined from the center to the periphery.
  • the fins are distributed between the flanges along the wheel. These fins form a flow grid between the leading edges of these fins and the trailing edges.
  • the deflection of the air flow at the exit of the impeller by the fins of the diffuser can cause a detachment of the fluid on the lower surface or the upper surface of the fins, which detachment, as long as it is important, can lead to the stall. fluid and, consequently, pumping. It is known that this pumping phenomenon is harmful to the constituent elements of the compressor, so that we try to avoid it as far as possible.
  • the vanes of the diffuser are constructed from a lower surface and an extrados wall in the shape of a circular arc, and comprise a quasi-linear angle law.
  • An example of such a fin is illustrated in FIG.
  • these fins have a limitation in terms of diffusing capacity. Indeed, an increase in the diffusion by these fins causes a drop in isentropic efficiency and an increase in the instability of the compressor.
  • An object of the invention is to improve the performance and pumping margin of diffusers of radial and mixed compressors of the prior art.
  • the invention aims to provide a diffuser of a radial or mixed compressor capable of limiting the fall of the isentropic efficiency of the compressor and improve the ability to slow down and straighten the flow delivered by the impeller of the compressor while maintaining the stability of this flow.
  • the invention proposes a fin of a diffuser for a radial or mixed compressor of a motor, comprising a leading edge disposed opposite a gas flow, a trailing edge opposite the leading edge. , a lower side wall and an extrados side wall which connect the leading edge to the trailing edge.
  • the fin profile includes a camber line having at least two points of inflection between the leading edge and the trailing edge. The curvature of the intrados wall and the curvature of the extrados wall also substantially follow the curvature of the camber line, so that:
  • the intrados wall comprises, between the leading edge and the trailing edge, at least two convex parts separated by a concave part, and
  • the upper surface comprises, between the leading edge and the trailing edge, at least two concave parts separated by a convex part, and the profile defines a rope which extends between the leading edge and the edge; leakage, and the convex portions of the intrados wall and the concave portions of the extrados wall extend at least partially on the same side of said rope.
  • the invention also proposes a diffuser comprising at least one fin as described above, as well as a radial or mixed compressor comprising such a diffuser, and an engine comprising such a compressor.
  • FIG. 1 illustrates an example of blade profile of a diffuser according to the prior art
  • FIG. 2 illustrates an example of blade profile of a diffuser according to the invention
  • FIG. 3 is a detailed view of a blade of FIG. 2, on which a rope and a median line of the blade have been represented, and
  • FIG. 4 illustrates an example of an engine that can comprise a diffuser according to the invention.
  • a radial diffuser according to the present invention is particularly intended to be used with a compressor 2 of radial or mixed type.
  • FIG. 4 is a partial sectional view of a motor 1 comprising a radial compressor 2.
  • a gas flow F is first drawn into an air inlet sleeve and then compressed between the blades 3a of a compressor wheel 3 radial 2 and its housing.
  • the compressor 2 is of axial symmetry around an axis X.
  • the compressed gas flow F then exits radially from the wheel 3. If the compressor 2 was mixed, the gas flow would exit inclined at a non-zero angle with respect to a radial direction to the X axis.
  • the compressed air leaves the wheel 3 radially while having a kinetic moment and passes through a diffuser 5.
  • the role of the diffuser 5 is to convert a portion of the kinetic energy of the gas from the compressor 2 in static pressure by slowing the speed of gases, and straighten the flow from the wheel 3. It comprises for this a plurality of fins 10 arranged along its circumference, which extend between a front flange 5a and a rear flange 5b.
  • Each of the fins 10 has, in known manner, a leading edge 1 1 arranged opposite a gas flow, a trailing edge 12 opposite to the leading edge 1 1, an extrados side wall 13 and a side wall 14 that connect the leading edge 1 1 to the trailing edge 12.
  • the front flanges 5a and rear 5b may be planar.
  • at least one of the flanges 5a, 5b may comprise, in the space they define between them, at least one zone with alternating curvature between two fins 10, so that the air stream may comprise evolutionary head and foot meridians.
  • the flanges 5a, 5b may be evolutionary shapes axisymmetric.
  • front flanges 5a and 5b rear can be arranged to allow suction and blowing into the diffuser 5.
  • At least one of the fins 10 of the diffuser 5, preferably all of the fins 10, comprises, from upstream to downstream in the direction of the gas flow:
  • a first so-called capture zone whose shape is configured to adapt to the upstream flow
  • the fin 10 comprises a profile whose camber line 15 has at least two points of inflection 11, 12 between its leading edge 11 and its trailing edge 12, that is to say at least two changes of concavity.
  • the inflection points 11, 12 together define the capture zone, which comprises the portion of the fin 10 extending upstream of the first point of inflection 11, of the diffusion zone, which comprises the part of the fin 10 extending downstream of the second point of inflection 12.
  • the inflection points 11, 12 are situated between 10% and 90% of the cord 16, preferably between 30% and 70%. %.
  • a first 11 of the inflection points may be between 35% and 55% of the cord 16, while the second inflection point 12 is between 55% and 65% of the cord 16.
  • the inflection 11, 12 may be arranged symmetrically with respect to the center of the rope 16.
  • the profile of the fin 10 may comprise more points of inflection 11, 12.
  • the camber line 15 presents successively at least, between the leading edge 1 1 and the trailing edge 12, a first concavity, a second concavity different from the first concavity, then a third concavity.
  • the points of inflection 11, 12 are symmetrical relative to the center of the rope 16, the second concavity is then centered in the fin 10.
  • the intrados wall 14 and the extrados wall 13 substantially follow the curvature of the camber line 15, and therefore have as many points of inflection 11, 12.
  • the intrados wall 14 and the extrados wall 13 therefore comprise two inflection points 11, 12.
  • the intrados wall 14 comprises a convex portion 14 a between the leading edge 11 and the first point of inflection, then a concave portion 14b between the two points of inflection 11, 12, and a convex portion 14c between the second point of inflection and the trailing edge 12.
  • the upper surface 13 as for it comprises a concave part 13a between the leading edge 1 1 and the first point of inflection, then a convex part 13b between the two points of inflection 11, 12, and then a concave part 13c between the second inflection point and the trailing edge 12.
  • camber line 15 extends between the intrados wall 14 and the rope 16.
  • the line of camber 15 and the intrados wall 14 extend away from the rope 16.
  • the concave areas of the upper wall 13 pass through the rope 16, and are therefore at least partially on the same side as the line of camber 15 of said rope 16.
  • the leading edge 11 and the trailing edge 12 are oriented in the same general direction with respect to the flow. gases that are usually encountered in conventional diffusers, thereby preserving the neck section, i.e., the fluid inlet section between two adjacent fins. In this way, the stability of the diffuser 5 is maintained while improving the diffusion of the flow.
  • the angle of attack ⁇ (which corresponds to the angle between the tangent to the camber line 15 at the leading edge 11 and the rope 16) may be substantially identical to that of the conventional fins. For example, the angle of attack may be between about 0 ° and about 45 °.
  • the presence of the second inflection point 12 makes it possible to modify the shape of the fins 10 in their diffusion zone to increase the efficiency of the diffuser 5, without modifying the shape of the capture zone. Indeed, it is now possible to increase the angle between the camber line 15 at the trailing edge 12 and the rope 16, regardless of the shape of the capture area, which allows to straighten more strongly. the flow of gases and therefore increase the static pressure and the total pressure ratio iso-heating output of the diffuser 5, and thus improve the isentropic efficiency of the diffuser 5 while maintaining the margin pumping and therefore the stability compressor 2.
  • the camber line 15 of the fin profile 10 comprises at least two inflection points 11, 12.
  • the number of inflection points 11, 12 can be even in order to maintain the orientation. general of the leading edge 1 1 and the trailing edge 12 relative to the flow, and thus to preserve section at the neck.
  • the corresponding camber line 15 again extends between the intrados wall 14 and the rope 16, so that at any point between the leading edge 11 and the edge 12, the camber line 15 and the intrados wall 14 extend at a distance from the rope 16, and the concave zones of the extrados wall 13 pass through the rope 16.

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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 vane (10) of a diffuser (5) for a radial or mixed-flow compressor (2) of an engine (1), including a leading edge (11) arranged facing a flow of gas, a trailing edge (12) being opposite the leading edge (11), a side upper surface wall (13) and a side lower surface wall (14) which connect the leading edge (11) to the trailing edge (12), and a profile including a curved line (15) having at least two points of inflection (I1, I2) between the leading edge (11) and the trailing edge (12). The invention also relates to a corresponding radial diffuser (2).

Description

DIFFUSEUR A AILETTES D'UN COMPRESSEUR RADIAL OU MIXTE  FINAL DIFFUSER OF A RADIAL OR MIXED COMPRESSOR
DOMAINE DE L'INVENTION FIELD OF THE INVENTION
L'invention concerne de manière générale les moteurs à turbine à gaz, et plus particulièrement un étage de diffusion d'un compresseur radial ou mixte d'une turbine à gaz, ainsi qu'à un compresseur associé.  The invention generally relates to gas turbine engines, and more particularly to a diffusion stage of a radial or mixed compressor of a gas turbine, as well as to an associated compressor.
ARRIERE-PLAN TECHNOLOGIQUE BACKGROUND
Un compresseur comprend un ou plusieurs disques tournants (rotor ou rouet), aubagés ou non et une ou plusieurs roues à aubes fixes (étages redresseurs).  A compressor comprises one or more rotating disks (rotor or wheel), bladed or not and one or more fixed vane wheels (rectifier stages).
Un compresseur radial (ou centrifuge) possède au moins un étage de compression radial, c'est-à-dire apte à réaliser un écoulement de gaz perpendiculaire à l'axe central du compresseur. Il comprend au moins un rouet à pales radiales qui aspirent l'air axialement, qui, sous l'effet de la force radial, est accéléré, comprimé et refoulé radialement. Cet air est ensuite redressé dans un diffuseur (aubage fixe) qui transforme une partie de sa vitesse en pression statique en ralentissant les gaz en sortie du rouet. L'opération doit se dérouler avec un minimum de perte de pression totale tout en maintenant un niveau de stabilité du compresseur satisfaisant afin de maintenir une marge au pompage acceptable pour le fonctionnement de la turbomachine.  A radial (or centrifugal) compressor has at least one radial compression stage, that is to say capable of producing a flow of gas perpendicular to the central axis of the compressor. It comprises at least one radial impeller which sucks the air axially, which, under the effect of the radial force, is accelerated, compressed and discharged radially. This air is then straightened in a diffuser (fixed blade) which transforms part of its speed into static pressure by slowing the gases at the exit of the wheel. The operation must take place with a minimum of total pressure loss while maintaining a satisfactory compressor stability level in order to maintain an acceptable pumping margin for the operation of the turbomachine.
Les gaz sont alors guidés vers la chambre de combustion.  The gases are then guided to the combustion chamber.
Un compresseur mixte (ou hélico-radial) possède au moins un étage de compression incliné par rapport audit axe central, de sorte que le fluide sort du rouet du compresseur en faisant un angle non nul avec la direction radiale.  A mixed compressor (or helico-radial) has at least one compression stage inclined with respect to said central axis, so that the fluid leaves the compressor impeller at a non-zero angle with the radial direction.
Un diffuseur d'un compresseur radial est composé d'une roue formée de deux flasques entre lesquelles s'écoulent les gaz de manière radiale ou inclinée à partir du centre vers la périphérie. Des ailettes sont réparties entre les flasques tout le long de la roue. Ces ailettes forment une grille d'écoulement entre les bords d'attaque de ces ailettes et les bords de fuite. Cependant, la déviation du flux d'air en sortie du rouet par les ailettes du diffuseur peut provoquer un décollement du fluide sur l'intrados ou l'extrados des ailettes, lequel décollement, dès lors qu'il est important, peut conduire au décrochage du fluide et, par suite, au pompage. Il est connu que ce phénomène de pompage est néfaste pour les éléments constitutifs du compresseur, en sorte qu'on cherche à l'éviter dans la mesure du possible. A diffuser of a radial compressor is composed of a wheel formed of two flanges between which the gases flow radially or inclined from the center to the periphery. The fins are distributed between the flanges along the wheel. These fins form a flow grid between the leading edges of these fins and the trailing edges. However, the deflection of the air flow at the exit of the impeller by the fins of the diffuser can cause a detachment of the fluid on the lower surface or the upper surface of the fins, which detachment, as long as it is important, can lead to the stall. fluid and, consequently, pumping. It is known that this pumping phenomenon is harmful to the constituent elements of the compressor, so that we try to avoid it as far as possible.
Habituellement, les ailettes du diffuseur sont construites à partir d'une paroi intrados et d'une paroi extrados en forme d'arc de cercle, et comprennent une loi d'angle quasi linéaire. Un exemple d'une telle ailette est illustré en figure 1 . Cependant, ces ailettes présentent une limitation en termes de capacité diffusante. En effet, une augmentation de la diffusion par ces ailettes provoque une chute de rendement isentropique et un accroissement de l'instabilité du compresseur.  Usually, the vanes of the diffuser are constructed from a lower surface and an extrados wall in the shape of a circular arc, and comprise a quasi-linear angle law. An example of such a fin is illustrated in FIG. However, these fins have a limitation in terms of diffusing capacity. Indeed, an increase in the diffusion by these fins causes a drop in isentropic efficiency and an increase in the instability of the compressor.
II a été proposé dans le document WO 2012/019650 un diffuseur pour un compresseur radial comprenant des ailettes conformes au préambule de la revendication 1 . En particulier, ce document décrit des ailettes dont le profil présente une ligne de cambrure définie par une fonction ayant un point d'inflexion. La ligne de cambrure présente à cet effet une forme de « S », et permet de distribuer les charges le long du profil de l'ailette, avec un faible chargement dans la zone du bord d'attaque, qui augmente progressivement jusqu'au point d'inflexion de l'ailette où il devient maximal. Cependant, la mise en œuvre d'une ailette présentant un tel profilé en « S » nécessite de restreindre la section au col du diffuseur (c'est- à-dire la section d'entrée du fluide). Ceci a pour effet de décaler la caractéristique Débit/Taux vers de plus faibles débits, et réduit le débit de blocage aérodynamique du diffuseur.  It has been proposed in WO 2012/019650 a diffuser for a radial compressor comprising fins conforming to the preamble of claim 1. In particular, this document describes fins whose profile has a camber line defined by a function having a point of inflection. The camber line has an "S" shape for this purpose, and allows the loads to be distributed along the fin profile, with low loading in the leading edge area, which progressively increases to the point of inflection of the fin where it becomes maximal. However, the implementation of a fin having such an "S" profile requires restricting the section to the neck of the diffuser (that is to say the inlet section of the fluid). This has the effect of shifting the Flow / Rate characteristic to lower flow rates, and reduces the aerodynamic blocking flow of the diffuser.
Des ailettes de profilé similaire en forme de « S » ont également été décrites dans le document JP 201 1 -252424. En particulier, les ailettes de ce document sont configurées de sorte qu'un angle formé entre la ligne de courbure et le profilé circonférentiel augmente, puis diminue, puis augmente à nouveau entre le bord d'attaque et le bord de fuite de l'ailette. Ici encore, la section au col du diffuseur doit donc être restreinte, ce qui a pour effet réduire la stabilité du diffuseur. Like-shaped "S" -shaped fins have also been described in JP 201 1 -252424. In particular, the fins of this document are configured so that an angle formed between the line of curvature and the circumferential profile increases, then decreases, then increases again between the leading edge and the trailing edge of the fin . Here again, the section at the neck of the diffuser must be restricted, which has the effect of reducing the stability of the diffuser.
RESUME DE L'INVENTION SUMMARY OF THE INVENTION
Un objectif de l'invention est d'améliorer les performances et la marge au pompage des diffuseurs des compresseurs radiaux et mixtes de l'art antérieur.  An object of the invention is to improve the performance and pumping margin of diffusers of radial and mixed compressors of the prior art.
En particulier, l'invention a pour objectif de proposer un diffuseur d'un compresseur radial ou mixte capable de limiter la chute du rendement isentropique du compresseur et d'améliorer la capacité à ralentir et à redresser l'écoulement délivré par le rouet du compresseur tout en maintenant la stabilité de cet écoulement.  In particular, the invention aims to provide a diffuser of a radial or mixed compressor capable of limiting the fall of the isentropic efficiency of the compressor and improve the ability to slow down and straighten the flow delivered by the impeller of the compressor while maintaining the stability of this flow.
Pour cela, l'invention propose une ailette d'un diffuseur pour un compresseur radial ou mixte d'un moteur, comprenant un bord d'attaque disposé en regard d'un écoulement de gaz, un bord de fuite opposé au bord d'attaque, d'une paroi latérale d'intrados et d'une paroi latérale d'extrados qui relient le bord d'attaque au bord de fuite. Le profil de l'ailette comprend une ligne de cambrure présentant au moins deux points d'inflexion entre le bord d'attaque et le bord de fuite. La courbure de la paroi d'intrados et la courbure de la paroi d'extrados suivent par ailleurs sensiblement la courbure de la ligne de cambrure, de sorte que :  For this, the invention proposes a fin of a diffuser for a radial or mixed compressor of a motor, comprising a leading edge disposed opposite a gas flow, a trailing edge opposite the leading edge. , a lower side wall and an extrados side wall which connect the leading edge to the trailing edge. The fin profile includes a camber line having at least two points of inflection between the leading edge and the trailing edge. The curvature of the intrados wall and the curvature of the extrados wall also substantially follow the curvature of the camber line, so that:
- la paroi d'intrados comprend, entre le bord d'attaque et le bord de fuite, au moins deux parties convexes séparées par une partie concave, et the intrados wall comprises, between the leading edge and the trailing edge, at least two convex parts separated by a concave part, and
- la paroi d'extrados comprend, entre le bord d'attaque et le bord de fuite, au moins deux parties concaves séparées par une partie convexe, et le profil définit une corde qui s'étend entre le bord d'attaque et le bord de fuite, et les parties convexes de la paroi d'intrados et les parties concaves de la paroi d'extrados s'étendent au moins partiellement du même côté de ladite corde. L'invention propose également un diffuseur comprenant au moins une ailette comme décrit ci-dessus, ainsi qu'un compresseur radial ou mixte comprenant un tel diffuseur, et un moteur comprenant un tel compresseur. BREVE DESCRIPTION DES DESSINS the upper surface comprises, between the leading edge and the trailing edge, at least two concave parts separated by a convex part, and the profile defines a rope which extends between the leading edge and the edge; leakage, and the convex portions of the intrados wall and the concave portions of the extrados wall extend at least partially on the same side of said rope. The invention also proposes a diffuser comprising at least one fin as described above, as well as a radial or mixed compressor comprising such a diffuser, and an engine comprising such a compressor. BRIEF DESCRIPTION OF THE DRAWINGS
D'autres caractéristiques, buts et avantages de la présente invention apparaîtront mieux à la lecture de la description détaillée qui va suivre, et au regard des dessins annexés donnés à titre d'exemples non limitatifs et sur lesquels :  Other features, objects and advantages of the present invention will appear better on reading the detailed description which follows, and with reference to the appended drawings given by way of non-limiting examples and in which:
La figure 1 illustre un exemple de profil de pales d'un diffuseur conforme à l'art antérieur,  FIG. 1 illustrates an example of blade profile of a diffuser according to the prior art,
La figure 2 illustre un exemple de profil de pales d'un diffuseur conforme à l'invention,  FIG. 2 illustrates an example of blade profile of a diffuser according to the invention,
La figure 3 est une vue en détail d'une pale de la figure 2, sur laquelle a été représentée une corde et une ligne médiane de la pale, et FIG. 3 is a detailed view of a blade of FIG. 2, on which a rope and a median line of the blade have been represented, and
La figure 4 illustre un exemple de moteur pouvant comprendre un diffuseur conforme à l'invention. FIG. 4 illustrates an example of an engine that can comprise a diffuser according to the invention.
DESCRIPTION DETAILLEE D'UN MODE DE REALISATION DETAILED DESCRIPTION OF AN EMBODIMENT
Un diffuseur radial selon la présente invention est notamment destiné à être utilisé avec un compresseur 2 de type radial ou mixte.  A radial diffuser according to the present invention is particularly intended to be used with a compressor 2 of radial or mixed type.
La figure 4 est une coupe partielle d'un moteur 1 comportant un compresseur radial 2. Un flux gazeux F est d'abord aspiré dans une manche d'entrée d'air, puis comprimé entre les pales 3a d'un rouet 3 du compresseur radial 2 et son carter. Le compresseur 2 est de symétrie axiale autour d'un axe X. Le flux gazeux F comprimé sort alors radialement du rouet 3. Si le compresseur 2 était mixte, le flux gazeux sortirait incliné selon un angle non nul par rapport à une direction radiale à l'axe X.  FIG. 4 is a partial sectional view of a motor 1 comprising a radial compressor 2. A gas flow F is first drawn into an air inlet sleeve and then compressed between the blades 3a of a compressor wheel 3 radial 2 and its housing. The compressor 2 is of axial symmetry around an axis X. The compressed gas flow F then exits radially from the wheel 3. If the compressor 2 was mixed, the gas flow would exit inclined at a non-zero angle with respect to a radial direction to the X axis.
L'air comprimé sort radialement du rouet 3 tout en présentant un moment cinétique et passe dans un diffuseur 5. Le rôle du diffuseur 5 est de convertir une partie de l'énergie cinétique des gaz en provenance du compresseur 2 en pression statique en ralentissant la vitesse des gaz, et de redresser l'écoulement issu du rouet 3. Il comprend pour cela une pluralité d'ailettes 10 disposées selon sa circonférence, qui s'étendent entre un flasque avant 5a et un flasque arrière 5b. Chacune des ailettes 10 présente, de manière connue, un bord d'attaque 1 1 disposé en regard d'un écoulement de gaz, un bord de fuite 12 opposé au bord d'attaque 1 1 , une paroi latérale d'extrados 13 et une paroi latérale d'intrados 14 qui relient le bord d'attaque 1 1 au bord de fuite 12. The compressed air leaves the wheel 3 radially while having a kinetic moment and passes through a diffuser 5. The role of the diffuser 5 is to convert a portion of the kinetic energy of the gas from the compressor 2 in static pressure by slowing the speed of gases, and straighten the flow from the wheel 3. It comprises for this a plurality of fins 10 arranged along its circumference, which extend between a front flange 5a and a rear flange 5b. Each of the fins 10 has, in known manner, a leading edge 1 1 arranged opposite a gas flow, a trailing edge 12 opposite to the leading edge 1 1, an extrados side wall 13 and a side wall 14 that connect the leading edge 1 1 to the trailing edge 12.
Les flasques avant 5a et arrière 5b peuvent être plans. En variante, l'un au moins des flasques 5a, 5b peut comprendre, dans l'espace qu'ils définissent entre eux, au moins une zone à courbure alternée entre deux ailettes 10, de sorte que la veine d'air peut comprendre des méridiennes tête et pied évolutives. On pourra se référer au document FR 2 976 633 au nom de la Demanderesse pour plus de détail sur les flasques avant 5a et/ou arrière 5b présentant une telle courbure alternée.  The front flanges 5a and rear 5b may be planar. In a variant, at least one of the flanges 5a, 5b may comprise, in the space they define between them, at least one zone with alternating curvature between two fins 10, so that the air stream may comprise evolutionary head and foot meridians. We can refer to the document FR 2 976 633 in the name of the Applicant for more details on the front flanges 5a and / or rear 5b having such an alternating curvature.
Selon une autre variante encore, les flasques 5a, 5b peuvent être à formes évolutives axisymétriques.  According to another variant, the flanges 5a, 5b may be evolutionary shapes axisymmetric.
Par ailleurs, les flasques avant 5a et arrière 5b peuvent être aménagés de manière à permettre l'aspiration et le soufflage dans le diffuseur 5.  Furthermore, the front flanges 5a and 5b rear can be arranged to allow suction and blowing into the diffuser 5.
Au moins l'une des ailettes 10 du diffuseur 5, de préférence l'ensemble des ailettes 10, comprend, d'amont en aval dans le sens de l'écoulement des gaz :  At least one of the fins 10 of the diffuser 5, preferably all of the fins 10, comprises, from upstream to downstream in the direction of the gas flow:
- une première zone, dite de captation, dont la forme est configurée pour s'adapter à l'écoulement amont, et  a first so-called capture zone, whose shape is configured to adapt to the upstream flow, and
- une deuxième zone, dite de diffusion, dont la forme est configurée pour redresser plus fortement l'écoulement en provenance de la zone de captation, afin d'obtenir une pression statique plus importante en sortie du diffuseur 5 et de faciliter l'alimentation de la pièce aval, généralement un diffuseur 5 axial. L'ailette 10 comprend un profil dont la ligne de cambrure 15 présente au moins deux points d'inflexion 11 , 12 entre son bord d'attaque 1 1 et son bord de fuite 12, c'est-à-dire au moins deux changements de concavité. a second zone, called diffusion zone, the shape of which is configured to straighten more strongly the flow coming from the capture zone, in order to obtain a greater static pressure at the diffuser outlet 5 and to facilitate the feeding of the downstream part, usually an axial diffuser. The fin 10 comprises a profile whose camber line 15 has at least two points of inflection 11, 12 between its leading edge 11 and its trailing edge 12, that is to say at least two changes of concavity.
Dans ce qui suit, on comprendra par « point d'inflexion » un point d'une courbe au niveau duquel la courbe traverse sa tangente. Par ailleurs, par profil de l'ailette 10, on comprendra ici une section transversale de l'ailette 10, c'est-à-dire une section de l'ailette 10 selon un plan globalement perpendiculaire à l'extrados 13 et à l'intrados 14 de l'ailette 10. Enfin, la « ligne de cambrure 15 » du profil correspond à la ligne fictive qui comprend l'ensemble des points équidistants de l'extrados 13 et de l'intrados 14 de l'ailette 10, tandis que la « corde 16 » correspond au segment qui a pour extrémités le bord d'attaque 1 1 et le bord de fuite 12.  In what follows, we will understand by "point of inflection" a point of a curve at which the curve crosses its tangent. Furthermore, by profile of the fin 10, here will be understood a cross section of the fin 10, that is to say a section of the fin 10 in a plane generally perpendicular to the upper surface 13 and the upper surface. the intrados 14 of the fin 10. Finally, the "camber line 15" of the profile corresponds to the imaginary line which comprises all the equidistant points of the upper surface 13 and the lower surface 14 of the fin 10, while the "rope 16" corresponds to the segment which ends with the leading edge 11 and the trailing edge 12.
Les points d'inflexion 11 , 12 délimitent ensemble la zone de captation, qui comprend la partie de l'ailette 10 s'étendant en amont du premier point d'inflexion 11 , de la zone de diffusion, qui comprend la partie de l'ailette 10 qui s'étend en aval du deuxième point d'inflexion 12.  The inflection points 11, 12 together define the capture zone, which comprises the portion of the fin 10 extending upstream of the first point of inflection 11, of the diffusion zone, which comprises the part of the fin 10 extending downstream of the second point of inflection 12.
De préférence, afin d'optimiser la stabilité du diffuseur 5 et la pression statique en sortie du diffuseur 5, les points d'inflexion 11 , 12 sont situés entre 10% et 90% de la corde 16, de préférence entre 30% et 70%. Par exemple, un premier 11 des points d'inflexion peut être situé entre 35% et 55% de la corde 16, tandis que le deuxième point d'inflexion 12 est situé entre 55% et 65% de la corde 16. Les points d'inflexion 11 , 12 peuvent en particulier être disposés symétriquement par rapport au centre de la corde 16.  Preferably, in order to optimize the stability of the diffuser 5 and the static pressure at the outlet of the diffuser 5, the inflection points 11, 12 are situated between 10% and 90% of the cord 16, preferably between 30% and 70%. %. For example, a first 11 of the inflection points may be between 35% and 55% of the cord 16, while the second inflection point 12 is between 55% and 65% of the cord 16. The dots In particular, the inflection 11, 12 may be arranged symmetrically with respect to the center of the rope 16.
En variante, le profil de l'ailette 10 peut comprendre davantage de points d'inflexion 11 , 12.  Alternatively, the profile of the fin 10 may comprise more points of inflection 11, 12.
Ainsi, la ligne de cambrure 15 présente successivement au moins, entre le bord d'attaque 1 1 et le bord de fuite 12, une première concavité, une deuxième concavité différente de la première concavité, puis une troisième concavité. Lorsque les points d'inflexion 11 , 12 sont symétriques par rapport au centre de la corde 16, la deuxième concavité est alors centrée dans l'ailette 10. Thus, the camber line 15 presents successively at least, between the leading edge 1 1 and the trailing edge 12, a first concavity, a second concavity different from the first concavity, then a third concavity. When the points of inflection 11, 12 are symmetrical relative to the center of the rope 16, the second concavity is then centered in the fin 10.
Selon une forme de réalisation, la paroi d'intrados 14 et la paroi d'extrados 13 suivent sensiblement la courbure de la ligne de cambrure 15, et présentent donc autant de points d'inflexion 11 , 12.  According to one embodiment, the intrados wall 14 and the extrados wall 13 substantially follow the curvature of the camber line 15, and therefore have as many points of inflection 11, 12.
Dans l'exemple de réalisation illustré sur les figures 2 et 3, la paroi d'intrados 14 et la paroi d'extrados 13 comprennent donc deux points d'inflexion 11 , 12. La paroi d'intrados 14 comprend une partie convexe 14a entre le bord d'attaque 1 1 et le premier point d'inflexion, puis une partie concave 14b entre les deux points d'inflexion 11 , 12, puis une partie convexe 14c entre le deuxième point d'inflexion et le bord de fuite 12. La paroi d'extrados 13 quant à elle comprend une partie concave 13a entre le bord d'attaque 1 1 et le premier point d'inflexion, puis une partie convexe 13b entre les deux points d'inflexion 11 , 12, puis une partie concave 13c entre le deuxième point d'inflexion et le bord de fuite 12.  In the exemplary embodiment illustrated in FIGS. 2 and 3, the intrados wall 14 and the extrados wall 13 therefore comprise two inflection points 11, 12. The intrados wall 14 comprises a convex portion 14 a between the leading edge 11 and the first point of inflection, then a concave portion 14b between the two points of inflection 11, 12, and a convex portion 14c between the second point of inflection and the trailing edge 12. The upper surface 13 as for it comprises a concave part 13a between the leading edge 1 1 and the first point of inflection, then a convex part 13b between the two points of inflection 11, 12, and then a concave part 13c between the second inflection point and the trailing edge 12.
Par ailleurs, la ligne de cambrure 15 s'étend entre la paroi d'intrados 14 et la corde 16. En d'autres termes, en tout point entre le bord d'attaque 1 1 et le bord de fuite 12, la ligne de cambrure 15 et la paroi d'intrados 14 s'étendent à distance de la corde 16. De plus, les zones concaves de la paroi d'extrados 13 traversent la corde 16, et se trouvent par conséquent au moins partiellement du même côté que la ligne de cambrure 15 de ladite corde 16.  Furthermore, the camber line 15 extends between the intrados wall 14 and the rope 16. In other words, at any point between the leading edge 1 1 and the trailing edge 12, the line of camber 15 and the intrados wall 14 extend away from the rope 16. In addition, the concave areas of the upper wall 13 pass through the rope 16, and are therefore at least partially on the same side as the line of camber 15 of said rope 16.
Grâce à cette configuration, rendue possible par les deux points d'inflexion 11 , 12 de la ligne de cambrure 15, le bord d'attaque 1 1 et le bord de fuite 12 sont orientés dans le même sens général par rapport à l'écoulement des gaz que celui rencontré habituellement dans les diffuseurs 5 conventionnels, ce qui permet de préserver la section au col, c'est-à-dire la section d'entrée du fluide entre deux ailettes 10 adjacentes. De la sorte, la stabilité du diffuseur 5 est conservée tout en améliorant la diffusion de l'écoulement. L'angle d'attaque a (qui correspond à l'angle entre la tangente à la ligne de cambrure 15 au niveau du bord d'attaque 1 1 et la corde 16) peut être sensiblement identique à celui des ailettes 10 conventionnelles. Par exemple, l'angle d'attaque a peut être compris entre environ 0° et environ 45°. De la sorte, il est possible de conserver sensiblement la forme des ailettes 10 de diffuseurs 5 conventionnelles dans leur zone de captation, ce qui permet de préserver la stabilité de l'écoulement. De plus, la présence du deuxième point d'inflexion 12 permet de modifier la forme des ailettes 10 dans leur zone de diffusion pour augmenter le rendement du diffuseur 5, sans pour autant modifier la forme de la zone de captation. En effet, il est à présent possible d'augmenter l'angle entre la ligne de cambrure 15 au niveau du bord de fuite 12 et la corde 16, indépendamment de la forme de la zone de captation, ce qui permet de redresser plus fortement l'écoulement des gaz et donc d'augmenter la pression statique et le taux de pression totale à iso-échauffement en sortie du diffuseur 5, et donc d'améliorer le rendement isentropique du diffuseur 5 tout en maintenant la marge au pompage et donc la stabilité du compresseur 2. Thanks to this configuration, made possible by the two points of inflection 11, 12 of the camber line 15, the leading edge 11 and the trailing edge 12 are oriented in the same general direction with respect to the flow. gases that are usually encountered in conventional diffusers, thereby preserving the neck section, i.e., the fluid inlet section between two adjacent fins. In this way, the stability of the diffuser 5 is maintained while improving the diffusion of the flow. The angle of attack α (which corresponds to the angle between the tangent to the camber line 15 at the leading edge 11 and the rope 16) may be substantially identical to that of the conventional fins. For example, the angle of attack may be between about 0 ° and about 45 °. In this way, it is possible to substantially retain the shape of the conventional diffuser fins 5 in their area of capture, thereby preserving the stability of the flow. In addition, the presence of the second inflection point 12 makes it possible to modify the shape of the fins 10 in their diffusion zone to increase the efficiency of the diffuser 5, without modifying the shape of the capture zone. Indeed, it is now possible to increase the angle between the camber line 15 at the trailing edge 12 and the rope 16, regardless of the shape of the capture area, which allows to straighten more strongly. the flow of gases and therefore increase the static pressure and the total pressure ratio iso-heating output of the diffuser 5, and thus improve the isentropic efficiency of the diffuser 5 while maintaining the margin pumping and therefore the stability compressor 2.
Comme indiqué précédemment, la ligne de cambrure 15 du profil de l'ailette 10 comprend au moins deux points d'inflexion 11 , 12. De préférence, le nombre de points d'inflexion 11 , 12 peut être pair afin de conserver l'orientation générale du bord d'attaque 1 1 et du bord de fuite 12 par rapport à l'écoulement, et donc de préserver section au col. Par ailleurs, selon une forme de réalisation, la ligne de cambrure 15 correspondante s'étend ici encore entre la paroi d'intrados 14 et la corde 16, de sorte que, en tout point entre le bord d'attaque 1 1 et le bord de fuite 12, la ligne de cambrure 15 et la paroi d'intrados 14 s'étendent à distance de la corde 16, et les zones concaves de la paroi d'extrados 13 traversent la corde 16. As indicated above, the camber line 15 of the fin profile 10 comprises at least two inflection points 11, 12. Preferably, the number of inflection points 11, 12 can be even in order to maintain the orientation. general of the leading edge 1 1 and the trailing edge 12 relative to the flow, and thus to preserve section at the neck. Furthermore, according to one embodiment, the corresponding camber line 15 again extends between the intrados wall 14 and the rope 16, so that at any point between the leading edge 11 and the edge 12, the camber line 15 and the intrados wall 14 extend at a distance from the rope 16, and the concave zones of the extrados wall 13 pass through the rope 16.

Claims

REVENDICATIONS
1 . Ailette (10) d'un diffuseur (5) pour un compresseur (2) radial ou mixte d'un moteur (1 ), comprenant un bord d'attaque (1 1 ) disposé en regard d'un écoulement de gaz, un bord de fuite (12) opposé au bord d'attaque1. Flange (10) of a diffuser (5) for a radial or mixed compressor (2) of an engine (1), comprising a leading edge (1 1) disposed opposite a gas flow, an edge leak (12) opposite to the leading edge
(1 1 ) , d'une paroi latérale d'extrados (13) et d'une paroi latérale d'intrados (14) qui relient le bord d'attaque (1 1 ) au bord de fuite (12), (1 1), an upper side wall (13) and a lower side wall (14) which connect the leading edge (1 1) to the trailing edge (12),
l'ailette (10) comprenant un profil dont une ligne de cambrure (15) présente au moins deux points d'inflexion (11 , 12) entre le bord d'attaque (1 1 ) et le bord de fuite (12), the fin (10) comprising a profile whose camber line (15) has at least two points of inflection (11, 12) between the leading edge (1 1) and the trailing edge (12),
l'ailette étant caractérisée en ce que la courbure de la paroi d'intrados (14) et la courbure de la paroi d'extrados (13) suivent sensiblement la courbure de la ligne de cambrure (15), de sorte que : the fin being characterized in that the curvature of the intrados wall (14) and the curvature of the extrados wall (13) substantially follow the curvature of the camber line (15), so that:
- la paroi d'intrados (14) comprend, entre le bord d'attaque (1 1 ) et le bord de fuite (12), au moins deux parties convexes (14a, 14c) séparées par une partie concave (14b), et  - the intrados wall (14) comprises, between the leading edge (1 1) and the trailing edge (12), at least two convex portions (14a, 14c) separated by a concave portion (14b), and
- la paroi d'extrados (13) comprend, entre le bord d'attaque (1 1 ) et le bord de fuite (12), au moins deux parties concaves (13a, 13c) séparées par une partie convexe (13b),  the extrados wall (13) comprises, between the leading edge (1 1) and the trailing edge (12), at least two concave parts (13a, 13c) separated by a convex part (13b),
et en ce que le profil définit une corde (16) qui s'étend entre le bord d'attaque (1 1 ) et le bord de fuite (12), et les parties convexes (14a, 14c) de la paroi d'intrados (14) et les parties concaves (13a, 13c) de la paroi d'extrados (13) s'étendent au moins partiellement du même côté de ladite corde (16). and in that the profile defines a rope (16) extending between the leading edge (1 1) and the trailing edge (12), and the convex portions (14a, 14c) of the intrados wall (14) and the concave portions (13a, 13c) of the upper surface (13) extend at least partially on the same side of said rope (16).
2. Ailette (10) selon la revendication 1 , dans laquelle le profil définit une corde (16) qui s'étend entre le bord d'attaque (1 1 ) et le bord de fuiteA fin (10) according to claim 1, wherein the profile defines a rope (16) extending between the leading edge (1 1) and the trailing edge
(12) et, en tout point entre le bord d'attaque (1 1 ) et le bord de fuite (12), ladite corde (16) est située à distance de la ligne de cambrure (15). (12) and at any point between the leading edge (1 1) and the trailing edge (12), said rope (16) is located at a distance from the camber line (15).
3. Ailette (10) selon l'une des revendications 1 ou 2, dans laquelle le profil définit une corde (16) qui s'étend entre le bord d'attaque (1 1 ) et le bord de fuite (12), et les points d'inflexion (11 , 12) sont situés entre 10% et 90% de ladite corde (16). 3. Wing (10) according to one of claims 1 or 2, wherein the profile defines a rope (16) extending between the leading edge (1 1) and the trailing edge (12), and the inflection points (11, 12) are between 10% and 90% of said cord (16).
4. Ailette (10) selon la revendication 3, dans laquelle un premier (11 ) desdits points d'inflexion est situé entre 35% et 55% de la corde (16), et un deuxième (12) desdits points d'inflexion est situé entre 55% et 65% de ladite corde (16). A fin (10) according to claim 3, wherein a first (11) of said inflection points is between 35% and 55% of the cord (16), and a second (12) of said inflection points is between 55% and 65% of said rope (16).
5. Ailette (10) selon l'une des revendications 1 à 4, comprenant un angle d'attaque (a) compris entre environ 0° et environ 45°. 5. Wing (10) according to one of claims 1 to 4, comprising an angle of attack (a) between about 0 ° and about 45 °.
6. Diffuseur (5) d'un compresseur radial ou mixte d'un moteur (1 ), comprenant au moins une ailette (10) selon l'une des revendications 1 à 5. 6. Diffuser (5) of a radial or mixed compressor of a motor (1), comprising at least one fin (10) according to one of claims 1 to 5.
7. Compresseur (2) radial ou mixte d'un moteur (1 ), comprenant un diffuseur (5) selon la revendication 6. 7. Compressor (2) radial or mixed motor (1), comprising a diffuser (5) according to claim 6.
8. Moteur (1 ), comprenant un compresseur (2) radial ou mixte selon la revendication 7. Motor (1), comprising a radial or mixed compressor (2) according to claim 7.
EP14718669.6A 2013-03-28 2014-03-25 Vane for radial or mixed-flow compressor Active EP2978977B1 (en)

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FR1352829A FR3003908B1 (en) 2013-03-28 2013-03-28 DIFFUSER WITH FINES OF A RADIAL OR MIXED COMPRESSOR
PCT/FR2014/050693 WO2014154997A1 (en) 2013-03-28 2014-03-25 Radial or mixed-flow compressor diffuser having vanes

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