EP2859240A2 - Compressor casing comprising cavities having an optimised upstream shape - Google Patents

Compressor casing comprising cavities having an optimised upstream shape

Info

Publication number
EP2859240A2
EP2859240A2 EP13742669.8A EP13742669A EP2859240A2 EP 2859240 A2 EP2859240 A2 EP 2859240A2 EP 13742669 A EP13742669 A EP 13742669A EP 2859240 A2 EP2859240 A2 EP 2859240A2
Authority
EP
European Patent Office
Prior art keywords
cavities
upstream
compressor
downstream
housing
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
EP13742669.8A
Other languages
German (de)
French (fr)
Other versions
EP2859240B1 (en
Inventor
Thierry Jean-Jacques Obrecht
Olivier Stéphane DOMERCQ
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 Aircraft Engines SAS
Original Assignee
SNECMA SAS
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 SNECMA SAS filed Critical SNECMA SAS
Publication of EP2859240A2 publication Critical patent/EP2859240A2/en
Application granted granted Critical
Publication of EP2859240B1 publication Critical patent/EP2859240B1/en
Active legal-status Critical Current
Anticipated expiration legal-status Critical

Links

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
    • F04D29/52—Casings; Connections of working fluid for axial pumps
    • F04D29/54—Fluid-guiding means, e.g. diffusers
    • F04D29/541—Specially adapted for elastic fluid pumps
    • F04D29/545—Ducts
    • F04D29/547—Ducts having a special shape in order to influence fluid flow
    • 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
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F04—POSITIVE - DISPLACEMENT MACHINES FOR LIQUIDS; PUMPS FOR LIQUIDS OR ELASTIC FLUIDS
    • F04D—NON-POSITIVE-DISPLACEMENT PUMPS
    • F04D19/00—Axial-flow pumps
    • 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
    • F04D29/08—Sealings
    • F04D29/16—Sealings between pressure and suction sides
    • F04D29/161—Sealings between pressure and suction sides especially adapted for elastic fluid pumps
    • F04D29/164—Sealings between pressure and suction sides especially adapted for elastic fluid pumps of an axial flow wheel
    • 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
    • F04D29/4206—Casings; Connections of working fluid for radial or helico-centrifugal pumps especially adapted for elastic fluid pumps
    • 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
    • F04D29/40—Casings; Connections of working fluid
    • F04D29/52—Casings; Connections of working fluid for axial pumps
    • F04D29/54—Fluid-guiding means, e.g. diffusers
    • F04D29/541—Specially adapted for elastic fluid pumps
    • 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
    • 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

Definitions

  • the field of the present invention is that of propulsion and more particularly that of axial or axial-centrifugal compressors for propulsion assembly (turbojet or turboprop, referred to as turbomachines in the following description) and more specifically to high-pressure compressors heavily loaded.
  • the aeronautical turbomachines are mainly constituted by one or more compressors, in which the air sucked into the air intake is compressed, by a combustion chamber in which the injected fuel is burned, then by a turbine in which the burnt gases are relaxed to drive the compressor or compressors and finally by an ejection device.
  • Aeronautical compressors consist of blades, or blades, which are rotated inside a housing that seals the air stream with the outside of the engine. It is known that the clearance between the ends of the compressor blades and the casing forming the inner wall of the air flow line degrades the efficiency of the engine of the turbomachine.
  • this game can significantly modify and degrade the operation of the compressor until the occurrence of a phenomenon of "pumping", which results from the stalling of the airflow from the surface of the blades.
  • the control of the air circulation at the end of the blades is thus a major challenge to obtain both a good aerodynamic efficiency of the compressor and a sufficient margin against the pumping phenomenon.
  • the improvement brought by this realization comes only from an optimization of the axial position of the cavities and the search for optimization on other parameters of these cavities must be pursued to try to further improve the aerodynamic efficiency and / or the pumping margin of existing compressors.
  • the present invention therefore aims to provide a compressor housing with cavities, aerodynamic performance further improved.
  • the subject of the invention is a casing for a turbomachine compressor comprising recessed cavities, non-communicating with one another, in the thickness of said casing from its internal face and arranged parallel to each other on a circumference said housing, said cavities having an elongate shape in a main direction of orientation between two side walls and closing respectively upstream and downstream by an upstream face and a downstream face whose intersections with the inner face of the carter respectively form an upstream boundary and a downstream boundary, characterized in that the upstream boundary of these cavities has the form of a corrugated line having at least two alternations along its length between said side walls.
  • corrugated line promotes the mixing of the re-injected air with the main air and thus improves the efficiency and / or the pumping margin of the stage of the compressor using said casing.
  • said side walls converge towards each other while moving from downstream to upstream.
  • This configuration makes it possible to accelerate the air flowing between the dawn and the casing and to improve its reinjection into the vein, which again results in an improvement in the yield and / or the pumping margin of the floor concerned.
  • the wavy line is a broken line in zigzag, consisting of segments forming between them alternately projecting angles and re-entrant angles.
  • the upstream face of said cavities is constituted by a succession of teeth extending, radially, between the upstream boundary and the bottom of the cavity and, axially, alternately upstream and downstream of said cavity.
  • the downstream face has a convex shape. This facilitates the suction of air downstream of the cavity.
  • the cavities are evenly distributed around the circumference of the casing.
  • the cavities are unequally distributed around the circumference of the housing.
  • the invention also relates to a compressor for a turbomachine comprising a housing as described above and a turbomachine comprising such a compressor.
  • Figure 1 is a schematic sectional view of a compressor stage whose housing has a recirculating cavity of the air flowing between the blade and the housing;
  • Figure 2 is a schematic view, from above, of a rotor blade and a housing according to the prior art;
  • Figure 3 is a schematic view, from above, of a rotor blade and a housing according to one embodiment of the invention
  • FIG. 4 is a schematic view of the cutting of a cavity in a housing according to the invention.
  • Figure 5 is a perspective view of the cavities cut in a housing according to the invention.
  • FIG. 1 there is shown a compressor stage comprising a stator vane, or fixed vane 2, positioned upstream of a rotor vane, or mobile vane 1, attached to a disk 3 (or directly attached to this disk according to a so-called blisk technology monobloc).
  • the vanes are held in place by attachment to a compressor casing 4, which surrounds the blades 1 leaving a predefined clearance with them.
  • the casing 4 is hollowed out, from its internal face, of multiple cavities 5, not communicating with one another, which are regularly arranged on its circumference, opposite the path of passage of the blades 1.
  • These cavities have, roughly, the shape of a rectangular parallelepiped which sinks radially into the housing and which has in section along an axial plane, the shape of a rectangle with rounded corners.
  • Their shape, in section in a plane tangential to the circumference of the casing 4 is, in turn, substantially that of an elongated rectangle extending along two long sides and comprising, upstream and downstream, two short sides forming so-called upstream 7 and downstream borders 6. It should be noted that in the prior art, these two boundaries are classically straight line segments.
  • the cavities 5 are offset upstream of the motor, with respect to the leading edge 11 of the moving blade 1.
  • the length from which the upstream 7 of the cavity 5 protrudes with respect to the leading edge of the blades, is however, limited by the space between the blade wheel 1 and the blade wheel 2. Because of the implantation of these cavities, the parasitic air is sucked to a certain percentage of the rope of the dawn moving and reinjected into the vein upstream of dawn.
  • This configuration allows the recycling of air passing in the game between the blade 1 and the casing 4; this game can indeed be the place of violent turbulence which would disturb the configuration of the flow between the different stages and therefore which could lead to a degradation of the performances of the compressor or, at the extreme, to a phenomenon called "pumping" or of "stall".
  • a phenomenon is characterized by an instantaneous drop in the compression ratio and a transient inversion of the air flow through the compressor, which then leaves the upstream of the compressor.
  • FIG. 2 and 3 we see the circumferential position of a series of cavities 5 aligned along the casing 4, respectively according to the prior art and according to the invention.
  • the number of cavities is much greater than the number of blades 1 constituting the mobile wheel of the compressor stage. This number is in practice between 2 and 4 times the number of blades 1.
  • the circumferential distribution of the cavities as shown in the figures is a uniform arrangement; it has, moreover, already been proposed to make this provision irregular to break the aerodynamic excitation on the blades that could be caused by these cavities, particularly at the ends of each of the two half-shells that constitute the housing.
  • the cut formed by the cavities 5 at their intersection with the inner face of the casing 4 has a substantially rectangular shape with the two large sides substantially parallel.
  • the cavities are cut in a trapezoidal shape, with two small sides upstream and downstream that are substantially parallel and two long sides that are convergent upstream, so that the downstream boundary 6 has a greater length than that of the upstream boundary 7.
  • FIG. 4 shows in detail the shape of the cutout of a cavity 5 in a casing 4, according to the invention, at the inner face of the casing 4. While the small downstream side, that is to say the frontier downstream 6, is, as in the prior art, rectilinear, the short upstream side, that is to say the upstream border 7, is not but it has a herringbone shape that develop from side and other of the circumferential line connecting the upstream boundaries of the different cavities 5.
  • FIG. 5 shows in perspective and in recess, the shape of the cavities 5 and their relative position with respect to a wheel of moving blades 1, in the case of a casing 4 according to the invention.
  • the front face of the parallelepiped forming the cavity 5 is corrugated in a herringbone shape which extends all along the front face of the cavity, starting in the bottom of the cavity and ending with a zigzag line at the bottom. of the internal face of the casing 4 and the upstream frontier 7.
  • the first concerns the axial position of the downstream cavity, which defines the location air suction
  • the second the axial position of the upstream cavity that defines the place of reinjection of air
  • the third the volume of the cavity that determines the amount of air removed and reinjected, thus the efficiency of the crankcase treatment.
  • it should also take into account a point that directly influences the efficiency of the crankcase treatment and which concerns the quality of the reinjection of the air upstream of the moving wheel.
  • the reinjection speed must be as high as possible to obtain the most improvement in the pumping margin, and, on the other hand, the air reintroduced into the vein must mix best possible with the main flow, otherwise there is a risk of generating yield losses.
  • the invention proposes, firstly, to have cavities 5 whose width is variable and which tapers laterally from downstream to upstream. Keeping a large width in the cavity downstream is important to suck air recirculation in good conditions and avoid the appearance of a whirlpool play; and the decrease of the upstream cavity makes it possible to increase the speed of the air which will be reinjected into the vein. Then the arrangement of rafters allows to improve the mixture of air reinjected with the main air, in the same way that rafters on the nozzle of a turbomachine allow

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

Abstract

The invention relates to a casing for a turbine engine compressor, comprising: cavities (5) in the thickness of the casing, extending in parallel to one another from the inner face of the casing along a circumference thereof, said cavities not being in communication with one another. The cavities, which are elongate and extend along a main direction of orientation between two side walls, are closed upstream and downstream by upstream and downstream faces respectively, and an upstream border (7) and a downstream border (6) are formed at the intersections between same and the inner face of the casing (4). The casing is characterised in that the upstream border (7) of the cavities (5) takes the form of a wavy line comprising at least two alternate undulations over the length thereof between the aforementioned side walls. Figure pour l'abrégé : figure

Description

CARTER DE COMPRESSEUR Â CAVITÉS A FORME AMONT OPTIMISÉE  OPTIMIZED UPSTREAM CAVITY COMPRESSOR HOUSING
Le domaine de la présente invention est celui de la propulsion et plus particulièrement celui des compresseurs axiaux ou axialo-centrifuges pour ensemble propulsif (turboréacteur ou turbopropulseur, dénommés turbomachines dans la suite de la description) et plus spécifiquement aux compresseurs haute-pression fortement chargés. The field of the present invention is that of propulsion and more particularly that of axial or axial-centrifugal compressors for propulsion assembly (turbojet or turboprop, referred to as turbomachines in the following description) and more specifically to high-pressure compressors heavily loaded.
Les turbomachines aéronautiques sont principalement constituées par un ou plusieurs compresseurs, dans lesquels l'air aspiré dans l'entrée d'air est comprimé, par une chambre de combustion dans laquelle le carburant injecté est brûlé, puis par une turbine dans laquelle les gaz brûlés sont détendus pour entraîner le ou les compresseurs et enfin par un dispositif d'éjection. Les compresseurs aéronautiques, sont constitués d'ailettes, ou aubes, qui sont mues en rotation à l'intérieur d'un carter qui assure l'étanchéité de la veine d'air avec l'extérieur du moteur. 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 jusqu'à l'apparition d'un phénomène de « pompage », qui résulte du décrochage du flux d'air de la surface des aubes. Le contrôle de la circulation de l'air en bout des aubes constitue ainsi un enjeu primordial pour obtenir à la fois un bon rendement aérodynamique du compresseur et une marge suffisante contre le phénomène de pompage.  The aeronautical turbomachines are mainly constituted by one or more compressors, in which the air sucked into the air intake is compressed, by a combustion chamber in which the injected fuel is burned, then by a turbine in which the burnt gases are relaxed to drive the compressor or compressors and finally by an ejection device. Aeronautical compressors, consist of blades, or blades, which are rotated inside a housing that seals the air stream with the outside of the engine. It is known that the clearance between the ends of the compressor blades and the casing forming the inner wall of the air flow line 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", which results from the stalling of the airflow from the surface of the blades. The control of the air circulation at the end of the blades is thus a major challenge to obtain both a good aerodynamic efficiency of the compressor and a sufficient margin against the pumping phenomenon.
Une approche développée pour limiter l'impact de cet écoulement parasite entre l'extrémité de l'aube et le carter consiste à creuser des cavités disposées dans la paroi du carter au niveau du chemin de passage des aubes. Ces cavités sont placées en regard de l'aube ou préférentiellement décalées axialement, en direction de l'amont du moteur, dans le but de réinjecter l'air circulant dans le jeu entre l'aube et le carter, dans la veine en amont de l'aube en question. Un exemple d'une telle réalisation est donné dans la demande de brevet de la demanderesse qui a été publiée sous le numéro FR 2940374.  An approach developed to limit the impact of this parasitic flow between the end of the blade and the housing is to dig cavities disposed in the housing wall at the blade path. These cavities are placed opposite the blade or preferably axially offset, towards the upstream of the engine, in order to reinject the air circulating in the clearance between the blade and the casing, in the vein upstream of the dawn in question. An example of such an embodiment is given in the applicant's patent application which was published under the number FR 2940374.
L'amélioration apportée par cette réalisation ne provient que d'une optimisation de la position axiale des cavités et la recherche d'optimisation sur d'autres paramètres de ces cavités doit être poursuivie pour tenter d'améliorer encore le rendement aérodynamique et/ou la marge au pompage des compresseurs existants. La présente invention a donc pour but de proposer un carter de compresseur muni de cavités, aux performances aérodynamiques encore améliorées. The improvement brought by this realization comes only from an optimization of the axial position of the cavities and the search for optimization on other parameters of these cavities must be pursued to try to further improve the aerodynamic efficiency and / or the pumping margin of existing compressors. The present invention therefore aims to provide a compressor housing with cavities, aerodynamic performance further improved.
A cet effet, l'invention a pour objet un carter pour compresseur de turbomachine comportant des cavités creusées, de façon non communicantes entre elles, dans l'épaisseur dudit carter à partir de sa face interne et disposées parallèlement les unes aux autres sur une circonférence dudit carter, lesdites cavités ayant une forme allongée selon une direction principale d'orientation entre deux parois latérales et se refermant respectivement vers l'amont et vers l'aval par une face amont et par une face aval dont les intersections avec la face interne du carter forment respectivement une frontière amont et une frontière aval, caractérisé en ce que la frontière amont de ces cavités a la forme d'une ligne ondulée comportant au moins deux alternances sur sa longueur comprise entre lesdites parois latérales.  For this purpose, the subject of the invention is a casing for a turbomachine compressor comprising recessed cavities, non-communicating with one another, in the thickness of said casing from its internal face and arranged parallel to each other on a circumference said housing, said cavities having an elongate shape in a main direction of orientation between two side walls and closing respectively upstream and downstream by an upstream face and a downstream face whose intersections with the inner face of the carter respectively form an upstream boundary and a downstream boundary, characterized in that the upstream boundary of these cavities has the form of a corrugated line having at least two alternations along its length between said side walls.
La présence d'une ligne ondulée favorise le mélange de l'air réinjecté avec l'air principal et, ainsi, améliore le rendement et/ou la marge au pompage de l'étage concerné du compresseur utilisant ledit carter.  The presence of a corrugated line promotes the mixing of the re-injected air with the main air and thus improves the efficiency and / or the pumping margin of the stage of the compressor using said casing.
Avantageusement lesdites parois latérales convergent l'une vers l'autre en se dirigeant de l'aval vers l'amont. Cette configuration permet d'accélérer l'air qui circule entre l'aube et le carter et d'améliorer sa réinjection dans la veine, ce qui se traduit, là encore, par une amélioration du rendement et/ou de la marge au pompage de l'étage concerné.  Advantageously, said side walls converge towards each other while moving from downstream to upstream. This configuration makes it possible to accelerate the air flowing between the dawn and the casing and to improve its reinjection into the vein, which again results in an improvement in the yield and / or the pumping margin of the floor concerned.
Dans un mode particulier de réalisation la ligne ondulée est une ligne brisée en zigzag, constituée de segments formant entre eux alternativement des angles saillants et des angles rentrants.  In a particular embodiment, the wavy line is a broken line in zigzag, consisting of segments forming between them alternately projecting angles and re-entrant angles.
Préférentiellement la face amont desdites cavités est constituée par une succession de dents s'étendant, radialement, entre la frontière amont et le fond de la cavité et, axialement, alternativement vers l'amont et vers l'aval de ladite cavité.  Preferably, the upstream face of said cavities is constituted by a succession of teeth extending, radially, between the upstream boundary and the bottom of the cavity and, axially, alternately upstream and downstream of said cavity.
Avantageusement la face aval a une forme convexe. Cela facilite l'aspiration de l'air en aval de la cavité.  Advantageously, the downstream face has a convex shape. This facilitates the suction of air downstream of the cavity.
Dans un mode particulier de réalisation les cavités sont réparties de façon régulière sur la circonférence du carter.  In a particular embodiment, the cavities are evenly distributed around the circumference of the casing.
Dans un mode alternatif de réalisation les cavités sont réparties de façon non régulière sur la circonférence du carter.  In an alternative embodiment the cavities are unequally distributed around the circumference of the housing.
L'invention porte également sur un compresseur pour turbomachine comportant un carter tel que décrit ci-dessus et sur une turbomachine comportant un tel compresseur. 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 also relates to a compressor for a turbomachine comprising a housing as described above and a turbomachine comprising such a compressor. 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 :  On these drawings:
la figure 1 est une vue schématique en coupe d'un étage de compresseur dont le carter présente une cavité de recyclage de l'air circulant entre l'aube et le carter ; la figure 2 est une vue schématique, de dessus, d'une pale de rotor et d'un carter selon l'art antérieur ;  Figure 1 is a schematic sectional view of a compressor stage whose housing has a recirculating cavity of the air flowing between the blade and the housing; Figure 2 is a schematic view, from above, of a rotor blade and a housing according to the prior art;
la figure 3 est une vue schématique, de dessus, d'une pale de rotor et d'un carter selon un mode de réalisation de l'invention ;  Figure 3 is a schematic view, from above, of a rotor blade and a housing according to one embodiment of the invention;
la figure 4 est une vue schématique de la découpe d'une cavité dans un carter selon l'invention, et  FIG. 4 is a schematic view of the cutting of a cavity in a housing according to the invention, and
la figure 5 est une vue en perspective des cavités découpées dans un carter selon l'invention.  Figure 5 is a perspective view of the cavities cut in a housing according to the invention.
En se référant à la figure 1 , on voit un étage de compresseur comportant une aube de stator, ou aube fixe 2, positionnée en amont d'une aube de rotor, ou aube mobile 1 , attachée à un disque 3 (ou directement solidaire de ce disque selon une technologie dite de disque aubagé monobloc). Les aubes fixes sont maintenues en place par fixation sur un carter de compresseur 4, qui entoure les aubes mobiles 1 en laissant un jeu prédéfini avec elles. Referring to FIG. 1, there is shown a compressor stage comprising a stator vane, or fixed vane 2, positioned upstream of a rotor vane, or mobile vane 1, attached to a disk 3 (or directly attached to this disk according to a so-called blisk technology monobloc). The vanes are held in place by attachment to a compressor casing 4, which surrounds the blades 1 leaving a predefined clearance with them.
Le carter 4 est creusé, à partir de sa face interne, de multiples cavités 5, non communicantes entre elles, qui sont régulièrement disposées sur sa circonférence, en vis-à-vis du chemin de passage des aubes mobiles 1 . Ces cavités ont, grossièrement, la forme d'un parallélépipède rectangle qui s'enfonce radialement dans le carter et qui présente en coupe selon un plan axial, la forme d'un rectangle aux coins arrondis. Leur forme, en coupe dans un plan tangent à la circonférence du carter 4, est, quant à elle, sensiblement celle d'un rectangle allongé s'étendant selon deux grands côtés et comportant, à l'amont et à l'aval, deux petits côtés formant des frontières dites amont 7 et aval 6. Il convient de noter que, dans l'art antérieur, ces deux frontières sont classiquement des segments de droite.  The casing 4 is hollowed out, from its internal face, of multiple cavities 5, not communicating with one another, which are regularly arranged on its circumference, opposite the path of passage of the blades 1. These cavities have, roughly, the shape of a rectangular parallelepiped which sinks radially into the housing and which has in section along an axial plane, the shape of a rectangle with rounded corners. Their shape, in section in a plane tangential to the circumference of the casing 4, is, in turn, substantially that of an elongated rectangle extending along two long sides and comprising, upstream and downstream, two short sides forming so-called upstream 7 and downstream borders 6. It should be noted that in the prior art, these two boundaries are classically straight line segments.
Comme on peut le voir sur la figure 1 , les cavités 5 sont décalées vers l'amont du moteur, par rapport au bord d'attaque 1 1 de l'aube mobile 1 . La longueur dont dépasse l'amont 7 de la cavité 5 par rapport au bord d'attaque des aubes, est toutefois limitée par l'espace existant entre la roue d'aubes mobiles 1 et la roue d'aubes fixes 2. Du fait de l'implantation de ces cavités, l'air parasite est aspiré à un certain pourcentage de la corde de l'aube mobile et réinjecté dans la veine en amont de l'aube. Cette configuration permet le recyclage de l'air qui passe dans le jeu entre l'aube 1 et le carter 4 ; ce jeu peut en effet être le lieu de violentes turbulences qui perturberaient la configuration de l'écoulement entre les différents étages et donc qui pourraient entraîner une dégradation des performances du compresseur ou, à l'extrême, provoquer un phénomène dit de « pompage » ou de « décrochage ». Un tel phénomène se caractérise par une chute instantanée du taux de compression et une inversion transitoire du débit d'air traversant le compresseur, qui sort alors par l'amont du compresseur. As can be seen in FIG. 1, the cavities 5 are offset upstream of the motor, with respect to the leading edge 11 of the moving blade 1. The length from which the upstream 7 of the cavity 5 protrudes with respect to the leading edge of the blades, is however, limited by the space between the blade wheel 1 and the blade wheel 2. Because of the implantation of these cavities, the parasitic air is sucked to a certain percentage of the rope of the dawn moving and reinjected into the vein upstream of dawn. This configuration allows the recycling of air passing in the game between the blade 1 and the casing 4; this game can indeed be the place of violent turbulence which would disturb the configuration of the flow between the different stages and therefore which could lead to a degradation of the performances of the compressor or, at the extreme, to a phenomenon called "pumping" or of "stall". Such a phenomenon is characterized by an instantaneous drop in the compression ratio and a transient inversion of the air flow through the compressor, which then leaves the upstream of the compressor.
En se référant maintenant aux figures 2 et 3, on voit la position circonférentielle d'une série de cavités 5 alignées le long du carter 4, respectivement selon l'art antérieur et selon l'invention. Le nombre de cavités est très supérieur au nombre d'aubes 1 constituant la roue mobile de l'étage de compresseur. Ce nombre est dans la pratique compris entre 2 et 4 fois le nombre d'aubes mobiles 1 . La répartition circonférentielle des cavités, telle que montrée sur les figures est une disposition uniforme ; il a, par ailleurs, déjà été proposé de rendre cette disposition irrégulière pour casser l'excitation aérodynamique sur les aubages qui pourrait être provoquée par ces cavités, notamment aux extrémités de chacune des deux demi- coquilles qui constituent le carter.  Referring now to Figures 2 and 3, we see the circumferential position of a series of cavities 5 aligned along the casing 4, respectively according to the prior art and according to the invention. The number of cavities is much greater than the number of blades 1 constituting the mobile wheel of the compressor stage. This number is in practice between 2 and 4 times the number of blades 1. The circumferential distribution of the cavities as shown in the figures is a uniform arrangement; it has, moreover, already been proposed to make this provision irregular to break the aerodynamic excitation on the blades that could be caused by these cavities, particularly at the ends of each of the two half-shells that constitute the housing.
Sur la figure 2, qui représente l'art antérieur, la découpe que forment les cavités 5 à leur intersection avec la face interne du carter 4 a une forme sensiblement rectangulaire avec les deux grands côtés sensiblement parallèles. A contrario, sur la figure 3 qui représente un mode de réalisation de l'invention, la découpe des cavités a une forme trapézoïdale, avec deux petits côtés à l'amont et à l'aval qui sont sensiblement parallèles et deux grands côtés qui sont convergents vers l'amont, de sorte que la frontière aval 6 a une longueur plus importante que celle de la frontière amont 7.  In Figure 2, which shows the prior art, the cut formed by the cavities 5 at their intersection with the inner face of the casing 4 has a substantially rectangular shape with the two large sides substantially parallel. In contrast, in FIG. 3, which represents one embodiment of the invention, the cavities are cut in a trapezoidal shape, with two small sides upstream and downstream that are substantially parallel and two long sides that are convergent upstream, so that the downstream boundary 6 has a greater length than that of the upstream boundary 7.
La figure 4 montre en détail la forme de la découpe d'une cavité 5 dans un carter 4, selon l'invention, au niveau de la face interne du carter 4. Alors que le petit côté aval, c'est à dire la frontière aval 6, est, comme dans l'art antérieur, rectiligne, le petit côté amont, c'est-à-dire la frontière amont 7, ne l'est pas mais il présente une forme en chevrons qui se développent de part et d'autre de la ligne circonférentielle reliant les frontières amont des différentes cavités 5. La figure 5 montre en perspective et en creux, la forme des cavités 5 et leur position relative par rapport à une roue d'aubes mobiles 1 , dans le cas d'un carter 4 selon l'invention. La face avant du parallélépipède formant la cavité 5 est ondulée selon une forme en chevrons qui s'étendent tout le long de la face avant de la cavité, en prenant naissance dans le fond de la cavité pour se terminer par une ligne en zigzag au niveau de la face interne du carter 4 et de la frontière amont 7. FIG. 4 shows in detail the shape of the cutout of a cavity 5 in a casing 4, according to the invention, at the inner face of the casing 4. While the small downstream side, that is to say the frontier downstream 6, is, as in the prior art, rectilinear, the short upstream side, that is to say the upstream border 7, is not but it has a herringbone shape that develop from side and other of the circumferential line connecting the upstream boundaries of the different cavities 5. FIG. 5 shows in perspective and in recess, the shape of the cavities 5 and their relative position with respect to a wheel of moving blades 1, in the case of a casing 4 according to the invention. The front face of the parallelepiped forming the cavity 5 is corrugated in a herringbone shape which extends all along the front face of the cavity, starting in the bottom of the cavity and ending with a zigzag line at the bottom. of the internal face of the casing 4 and the upstream frontier 7.
On va maintenant expliquer l'apport de l'invention, en rappelant tout d'abord le principe de fonctionnement des traitements de carters par l'implantation dans leur épaisseur de cavités 5. Deux effets aérodynamiques sont combinés : en premier lieu, l'aspiration de l'air au bord d'attaque en sommet de rotor permet de contrer le développement du tourbillon de jeu entre le rotor et le carter, ce qui permet de gagner en rendement et en limite de stabilité ; en second lieu, la réinjection de l'air en amont de la roue mobile permet par une ré-énergisation de la couche limite, de gagner en limite de stabilité, et donc en marge au pompage.  We will now explain the contribution of the invention, recalling first of all the principle of operation of the casing treatments by the implantation in their thickness cavities 5. Two aerodynamic effects are combined: first, the suction air at the leading edge at the top of the rotor makes it possible to counter the development of the swirl of play between the rotor and the casing, which makes it possible to gain in yield and stability limit; secondly, the reinjection of the air upstream of the mobile wheel allows by a re-energizing of the boundary layer, to gain in stability limit, and therefore in margin to pumping.
On considère en général qu'il convient de prendre en compte trois paramètres particuliers pour obtenir le meilleur résultat avec un traitement de carter par incorporation de cavités 5. Le premier concerne la position axiale de l'aval de la cavité, qui définit l'endroit d'aspiration de l'air, le second, la position axiale de l'amont de la cavité qui définit l'endroit de réinjection de l'air et, le troisième, le volume de la cavité qui détermine la quantité d'air prélevé et réinjecté, donc l'efficacité du traitement de carter. Mais il convient de prendre également en compte un point qui influence directement l'efficacité du traitement de carter et qui concerne la qualité de la réinjection de l'air en amont de la roue mobile. En particulier, d'une part, la vitesse de réinjection doit être la plus élevée possible pour obtenir le plus d'amélioration de la marge au pompage, et, d'autre part, l'air réintroduit dans la veine doit se mélanger le mieux possible avec l'écoulement principal, faute de quoi on risque de générer des pertes de rendement.  It is generally considered that three particular parameters should be taken into account in order to obtain the best result with a casing treatment by incorporation of cavities 5. The first concerns the axial position of the downstream cavity, which defines the location air suction, the second, the axial position of the upstream cavity that defines the place of reinjection of air and the third, the volume of the cavity that determines the amount of air removed and reinjected, thus the efficiency of the crankcase treatment. But it should also take into account a point that directly influences the efficiency of the crankcase treatment and which concerns the quality of the reinjection of the air upstream of the moving wheel. In particular, on the one hand, the reinjection speed must be as high as possible to obtain the most improvement in the pumping margin, and, on the other hand, the air reintroduced into the vein must mix best possible with the main flow, otherwise there is a risk of generating yield losses.
Pour traiter ces deux points, l'invention propose, tout d'abord, d'avoir des cavités 5 dont la largeur est variable et qui vont en se rétrécissant latéralement de l'aval vers l'amont. Le fait de garder une grande largeur à la cavité vers l'aval est importante pour aspirer l'air de recirculation dans de bonnes conditions et éviter l'apparition d'un tourbillon de jeu ; et la diminution de la cavité vers l'amont permet d'augmenter la vitesse de l'air qui sera réinjecté dans la veine. Ensuite l'aménagement de chevrons permet d'améliorer le mélange de l'air réinjecté avec l'air principal, de la même manière que des chevrons sur la tuyère d'une turbomachine permettent  To treat these two points, the invention proposes, firstly, to have cavities 5 whose width is variable and which tapers laterally from downstream to upstream. Keeping a large width in the cavity downstream is important to suck air recirculation in good conditions and avoid the appearance of a whirlpool play; and the decrease of the upstream cavity makes it possible to increase the speed of the air which will be reinjected into the vein. Then the arrangement of rafters allows to improve the mixture of air reinjected with the main air, in the same way that rafters on the nozzle of a turbomachine allow

Claims

d'améliorer le mélange entre l'air chaud en sortie du flux primaire et l'air froid en sortie du flux secondaire. Avec ces aménagements effectués sur les cavités 5 d'un carter 4 de compresseur, on améliore l'efficacité d'aspiration du tourbillon de jeu et on obtient ainsi, en plus d'une augmentation de la marge au pompage, une légère amélioration du rendement de l'étage de compresseur. REVENDICATIONS to improve the mixing between the hot air at the outlet of the primary flow and the cold air at the outlet of the secondary flow. With these adjustments made on the cavities 5 of a compressor casing 4, the suction efficiency of the gaming vortex is improved, thus obtaining, in addition to an increase in the pumping margin, a slight improvement in the efficiency. compressor stage. CLAIMS
1 . Carter pour compresseur de turbomachine comportant des cavités (5) creusées, de façon non communicantes entre elles, dans l'épaisseur dudit carter à partir de sa face interne et disposées parallèlement les unes aux autres sur une circonférence dudit carter (4), lesdites cavités ayant une forme allongée selon une direction principale d'orientation entre deux parois latérales et se refermant respectivement vers l'amont et vers l'aval par une face amont et par une face aval dont les intersections avec la face interne du carter (4) forment respectivement une frontière amont (7) et une frontière aval (6), 1. Carter for a turbomachine compressor comprising cavities (5) hollowed, non-communicating with one another, in the thickness of said housing from its internal face and arranged parallel to each other on a circumference of said housing (4), said cavities having an elongate shape in a main direction of orientation between two side walls and closing respectively upstream and downstream by an upstream face and a downstream face whose intersections with the inner face of the housing (4) form respectively an upstream boundary (7) and a downstream boundary (6),
caractérisé en ce que la frontière amont (7) de ces cavités (5) a la forme d'une ligne ondulée comportant au moins deux alternances sur sa longueur comprise entre lesdites parois latérales. characterized in that the upstream boundary (7) of these cavities (5) is in the form of a corrugated line having at least two alternations along its length between said side walls.
2. Carter pour compresseur selon la revendication 1 dans lequel lesdites parois latérales convergent l'une vers l'autre en se dirigeant de l'aval vers l'amont.  2. Compressor housing according to claim 1 wherein said side walls converge towards each other from the downstream to the upstream.
3. Carter pour compresseur selon l'une des revendications 1 ou 2 dans lequel la ligne ondulée est une ligne brisée en zigzag, constituée de segments formant entre eux alternativement des angles saillants et des angles rentrants.  3. Carter compressor according to one of claims 1 or 2 wherein the corrugated line is a broken line in zigzag, consisting of segments forming between them alternately projecting angles and re-entrant angles.
4. Carter pour compresseur selon l'une des revendications 1 à 3 dans lequel la face amont desdites cavités est constituée par une succession de dents s'étendant, radialement, entre la frontière amont (7) et le fond de la cavité (5) et, axialement, alternativement vers l'amont et vers l'aval de ladite cavité.  4. Carter compressor according to one of claims 1 to 3 wherein the upstream face of said cavities is constituted by a succession of teeth extending radially between the upstream boundary (7) and the bottom of the cavity (5). and, axially, alternately upstream and downstream of said cavity.
5. Carter pour compresseur selon l'une des revendications 1 à 4 dans lequel la face aval a une forme convexe.  5. Carter compressor according to one of claims 1 to 4 wherein the downstream face has a convex shape.
6. Carter pour compresseur selon l'une des revendications 1 à 5 dans lequel les cavités (5) sont réparties de façon régulière sur la circonférence du carter (4).  6. Carter compressor according to one of claims 1 to 5 wherein the cavities (5) are evenly distributed on the circumference of the housing (4).
7. Carter pour compresseur selon l'une des revendications 1 à 5 dans lequel les cavités (5) sont réparties de façon non régulière sur la circonférence du carter (4).  7. Carter compressor according to one of claims 1 to 5 wherein the cavities (5) are distributed unevenly on the circumference of the housing (4).
8. Compresseur pour turbomachine comportant un carter selon l'une des revendications 1 à 7.  8. A turbomachine compressor comprising a casing according to one of claims 1 to 7.
9. Turbomachine comportant un compresseur selon la revendication précédente.  9. Turbomachine comprising a compressor according to the preceding claim.
EP13742669.8A 2012-04-19 2013-04-15 Compressor casing comprising cavities having an optimised upstream shape Active EP2859240B1 (en)

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FR1201160A FR2989742B1 (en) 2012-04-19 2012-04-19 UPRIGHT CAVITY COMPRESSOR HOUSING OPTIMIZED
PCT/FR2013/050829 WO2013156726A2 (en) 2012-04-19 2013-04-15 Compressor casing comprising cavities having an optimised upstream shape

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BR112014025385A2 (en) 2018-04-10
BR112014025385B1 (en) 2022-02-01
EP2859240B1 (en) 2016-11-09
CA2868456A1 (en) 2013-10-24
US20150078889A1 (en) 2015-03-19
FR2989742B1 (en) 2014-05-09
CN104220758B (en) 2016-04-13
CN104220758A (en) 2014-12-17
RU2014141066A (en) 2016-06-10
CA2868456C (en) 2020-01-14
RU2626874C2 (en) 2017-08-02
FR2989742A1 (en) 2013-10-25
US9638213B2 (en) 2017-05-02
WO2013156726A2 (en) 2013-10-24

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