EP3477049A1 - Indented ring for a turbine engine compressor - Google Patents

Indented ring for a turbine engine compressor Download PDF

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Publication number
EP3477049A1
EP3477049A1 EP18194178.2A EP18194178A EP3477049A1 EP 3477049 A1 EP3477049 A1 EP 3477049A1 EP 18194178 A EP18194178 A EP 18194178A EP 3477049 A1 EP3477049 A1 EP 3477049A1
Authority
EP
European Patent Office
Prior art keywords
compressor
boss
blade
protuberance
connecting surface
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
EP18194178.2A
Other languages
German (de)
French (fr)
Other versions
EP3477049B1 (en
Inventor
Stéphane Hiernaux
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 Aero Boosters SA
Original Assignee
Safran Aero Boosters SA
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Publication date
Application filed by Safran Aero Boosters SA filed Critical Safran Aero Boosters SA
Publication of EP3477049A1 publication Critical patent/EP3477049A1/en
Application granted granted Critical
Publication of EP3477049B1 publication Critical patent/EP3477049B1/en
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Classifications

    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F01—MACHINES OR ENGINES IN GENERAL; ENGINE PLANTS IN GENERAL; STEAM ENGINES
    • F01D—NON-POSITIVE DISPLACEMENT MACHINES OR ENGINES, e.g. STEAM TURBINES
    • F01D5/00—Blades; Blade-carrying members; Heating, heat-insulating, cooling or antivibration means on the blades or the members
    • F01D5/12—Blades
    • F01D5/14—Form or construction
    • F01D5/141—Shape, i.e. outer, aerodynamic form
    • F01D5/142—Shape, i.e. outer, aerodynamic form of the blades of successive rotor or stator blade-rows
    • F01D5/143—Contour of the outer or inner working fluid flow path wall, i.e. shroud or hub contour
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F01—MACHINES OR ENGINES IN GENERAL; ENGINE PLANTS IN GENERAL; STEAM ENGINES
    • F01D—NON-POSITIVE DISPLACEMENT MACHINES OR ENGINES, e.g. STEAM TURBINES
    • F01D9/00—Stators
    • F01D9/02—Nozzles; Nozzle boxes; Stator blades; Guide conduits, e.g. individual nozzles
    • F01D9/04—Nozzles; Nozzle boxes; Stator blades; Guide conduits, e.g. individual nozzles forming ring or sector
    • F01D9/041—Nozzles; Nozzle boxes; Stator blades; Guide conduits, e.g. individual nozzles forming ring or sector using blades
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F04—POSITIVE - DISPLACEMENT MACHINES FOR LIQUIDS; PUMPS FOR LIQUIDS OR ELASTIC FLUIDS
    • F04D—NON-POSITIVE-DISPLACEMENT PUMPS
    • F04D29/00—Details, component parts, or accessories
    • F04D29/26—Rotors specially for elastic fluids
    • F04D29/32—Rotors specially for elastic fluids for axial flow pumps
    • F04D29/321—Rotors specially for elastic fluids for axial flow pumps for axial flow compressors
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F04—POSITIVE - DISPLACEMENT MACHINES FOR LIQUIDS; PUMPS FOR LIQUIDS OR ELASTIC FLUIDS
    • F04D—NON-POSITIVE-DISPLACEMENT PUMPS
    • F04D29/00—Details, component parts, or accessories
    • F04D29/40—Casings; Connections of working fluid
    • F04D29/52—Casings; Connections of working fluid for axial pumps
    • F04D29/54—Fluid-guiding means, e.g. diffusers
    • F04D29/541—Specially adapted for elastic fluid pumps
    • F04D29/542—Bladed diffusers
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F04—POSITIVE - DISPLACEMENT MACHINES FOR LIQUIDS; PUMPS FOR LIQUIDS OR ELASTIC FLUIDS
    • F04D—NON-POSITIVE-DISPLACEMENT PUMPS
    • F04D29/00—Details, component parts, or accessories
    • F04D29/66—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
    • 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
    • F05D2240/00—Components
    • F05D2240/10—Stators
    • F05D2240/12—Fluid guiding means, e.g. vanes
    • F05D2240/121—Fluid guiding means, e.g. vanes related to the leading edge of a stator vane
    • 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
    • F05D2240/00—Components
    • F05D2240/10—Stators
    • F05D2240/12—Fluid guiding means, e.g. vanes
    • F05D2240/122—Fluid guiding means, e.g. vanes related to the trailing edge of a stator vane
    • 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
    • F05D2240/00—Components
    • F05D2240/10—Stators
    • F05D2240/12—Fluid guiding means, e.g. vanes
    • F05D2240/123—Fluid guiding means, e.g. vanes related to the pressure side of a stator vane
    • 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
    • F05D2240/00—Components
    • F05D2240/10—Stators
    • F05D2240/12—Fluid guiding means, e.g. vanes
    • F05D2240/124—Fluid guiding means, e.g. vanes related to the suction side of a stator vane
    • 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
    • F05D2250/70—Shape
    • F05D2250/71—Shape curved
    • 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
    • F05D2250/70—Shape
    • F05D2250/71—Shape curved
    • F05D2250/711—Shape curved convex
    • 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
    • F05D2250/70—Shape
    • F05D2250/71—Shape curved
    • F05D2250/712—Shape curved concave

Definitions

  • the invention relates to a compressor with a profiled inter-blade surface.
  • the invention also relates to an axial turbomachine, in particular an aircraft turbojet engine or an aircraft turboprop engine.
  • the document US 2007/0059177 A1 discloses a turbojet compressor.
  • the compressor has an annular row of vanes.
  • a platform is associated with each blade and has a three-dimensional relief extending between two successive blades.
  • Each relief has two bumps separated by a sinusoidal channel sinking radially into the platform. This geometry improves the aerodynamic efficiency of an axial flow compressor blade. However, it shows a high corner detachment in extrados of the blades.
  • the object of the invention is to solve at least one of the problems posed by the prior art. More specifically, the invention aims to optimize the compression ratio and the detachments in the corner at the extrados. The invention also aims to provide a simple solution, resistant, lightweight, economical, reliable, easy to produce, and convenient maintenance.
  • the invention can be understood as a bump with two main peaks, and / or a convexity with two radial extremums; between two consecutive blades of a compressor.
  • the invention relates to an axial turbomachine compressor according to claim 1.
  • the subject of the invention is also a turbomachine, in particular an aircraft turbojet, comprising a compressor, which is remarkable in that the compressor is in accordance with the invention, preferentially the row of blades comprises at least: fifty or eighty. blades.
  • each embodiment of the invention is combinable with each object of the invention.
  • the terms “internal” and “external” refer to a positioning relative to the axis of rotation of an axial turbomachine.
  • the axial direction corresponds to the direction along the axis of rotation of the turbomachine.
  • the radial direction is perpendicular to the axis of rotation. Upstream and downstream are in reference to the main flow direction of the flow in the turbomachine.
  • the figure 1 represents in simplified manner an axial turbomachine. It is in this case a double-flow turbojet engine.
  • the turbojet engine 2 comprises a low-pressure compressor 4, a high-pressure compressor 6, a combustion chamber 8 and one or more turbine levels 10.
  • the mechanical power of the turbine 10 transmitted via the central shaft up to the rotor 12 sets in motion the two compressors 4 and 6.
  • the latter comprise several rows of rotor blades associated with rows of stator vanes.
  • the rotation of the rotor about its axis of rotation 14 thus makes it possible to generate an air flow and to compress this last to the entrance of the combustion chamber 8.
  • a blower 16 or fan 16 is coupled to the rotor 12 and generates a stream of air which splits into a primary stream 18 and a secondary stream 20 passing through an annular duct (partially shown).
  • the secondary flow can be accelerated so as to generate a thrust reaction necessary for the flight of an aircraft.
  • the primary 18 and secondary 20 streams are annular.
  • the figure 2 is a sectional view of a compressor of an axial turbomachine such as that of the figure 1 .
  • the compressor may be a low-pressure compressor 4. There may be observed a portion of the fan 16 and the separation nozzle 22 of the primary flow 18 and the secondary flow 20.
  • the rotor 12 comprises several rows of rotor blades 24, in this case three. It may be a bladed monobloc drum, or include dovetail blades.
  • the rotor vanes 24 may extend radially from an individual platform, or from an inner ring 25 of the rotor 12.
  • the low-pressure compressor 4 comprises several rectifiers, in this case four, each containing a row of stator vanes 26.
  • the rectifiers are associated with the fan 16 or with a row of rotor vanes to straighten the air flow, so as to convert the speed of the flow into pressure, in particular into static pressure.
  • the stator vanes 26 extend essentially radially from an outer casing 28. They can be fixed and immobilized by means of fixation pins 30. They pass radially through the primary flow 18.
  • the stator vanes can be fixedly oriented by 28.
  • the blades of the same row are identical and aligned. Each row may comprise one hundred twenty blades (26; 24).
  • Internal ferrules 32 may be suspended at the inner ends of the stator vanes 26.
  • the inner ferrules 32 may cooperate sealingly with the rotor 12 to improve the compression ratio of the compressor 4.
  • the row may be one of the rows presented in connection with the preceding figures.
  • the vanes and their support, optionally the inner ferrule 32, are represented in plan.
  • the axis of rotation 14 is traced to a figurative position, and provides a spatial marker.
  • Each blade 26 comprises a leading edge 34, a trailing edge 36, and a lower surface 38 and an extrados surface 40. These surfaces (38; 40) can be curved and curved respectively. Each of these surfaces extends from the leading edge 34 to the corresponding trailing edge 36.
  • the blade 26 may comprise a stack of aerodynamic profiles 41 arched, whose sides generate the intrados surface 38 and the extrados surface 40. At the trailing edges 36, the contours of the profiles 41, in intrados and / or extrados, are parallel and / or tangent to the axis of rotation 14 of the compressor.
  • the consecutive blades 26 of the annular row define between it a passage 42, also called inter-blade passage 42.
  • This passage 42 is partitioned circumferentially by the blades 26, and delimited by the intrados and extrados surfaces.
  • the passage 42 may have a connecting surface 44 between the two consecutive blades 26, and may connect the intrados surface 38 which faces the extrados surface 40 through the passage 42.
  • the connecting surface 44 may be defined axially by an upstream axis 46 and a downstream axis 48 which connect the leading edges 34 and the trailing edges 36 respectively. These axes (46; 48) can be parallel, and can generally define a parallelogram or a trapezoid.
  • the connecting surface 44 may be generally flat.
  • the connecting surface 44 may be a tubular surface part or a cone surface part, in particular because of the radius of the ferrule and the optional diameter variation of the ferrule 32 along the axis of the ferrule. rotation 14. It may comprise four corners 50 corresponding to the intersections between the edges (34; 36) and the support, in this case the ferrule 32, for example internal.
  • the connecting surface 44 may comprise an upstream zone 47 extending downstream from the upstream axis 46, and a downstream zone 49 extending upstream from the downstream axis 48.
  • the connecting surface 44 has an axial asymmetry with respect to the axis of rotation 14. It has a protrusion 52, in particular a main protrusion 52. This protrusion 52 can occupy most of the The axial majority of the protuberance 52 may be contained in the upstream half of the row of blades 26. It forms an addition of radial material on the connecting surface 44. The addition of material can be observed by compared to zones 47 and 49.
  • the protrusion 52 also includes a first boss 54 with a first boss 56, and a second boss 58 with a second boss 60. These bosses 54 and 58 may be the major bosses of the protuberance 52, i.e. they form the main volume reliefs.
  • the bumps (54; 58) may extend over at most the axial majority of the blades 26.
  • the first bump may extend axially on 30% of the rope 62 of the first blade 26, and / or the second bump 58 may extend axially on 20% of the rope 62 of the second blade 26.
  • These bumps (54; 58) may be recessed axially from the leading edges 34, in particular by 10% the axial length of a rope 62.
  • first top 56 may have a main elongation parallel to the rope 62 of the first blade 26.
  • the first bump 54 may extend over 50% of the inter-blade passage 42 and extend from the intrados surface 38. Its top 56 may be at a distance from the intrados surface 38. A channel 64 may be formed against the first bump 54, between the intrados surface 38 of the first blade 26 and the first top 56.
  • the second bump 58 may extend circumferentially over 10% of the passage 42, its top 60 may be attached to the upper surface 40 of the second dawn 26.
  • the first bump 54 and the second bump 58 may be at the same level axially. Their vertices (56; 60) can be aligned axially. The bumps (54; 58) can be separated from one another, and in particular spaced from each other along the circumference. A collar 66, such as a mountain collar, can circumferentially separate them.
  • the curve 67 is the curve of the shortest neck 66 between the vertices 56 and 60. This curve 67 as well as all the points of the neck 66 are in elevation relative to the regular surface in the absence of protuberance, represented by the zones 47 and 49, of constant radius.
  • the bumps (54; 58) and the protuberance 52 are represented by means of level lines 68. These level lines 68 indicate radial level variations with respect to a reference surface, in this case the connecting surface. 44.
  • the figure 4 is a section of the figure 3 along the IV-IV axis. The position as the inclination of the axis of rotation 14 are figurative and can vary in concrete embodiments.
  • the blades may comprise connecting radii 70 at their radial ends.
  • the connecting spokes 70 may surround their respective blades 26.
  • the connecting surface 44 can extend from the connecting spokes 70 so as to connect them in pairs.
  • the radial thickness of the connecting radii 70 is smaller than that of the bumps and possibly of the protuberance 52.
  • This annular surface 33 may have a constant radius RC outside the passages.
  • the annular surface 33 may have axial symmetry.
  • the zones 47 and 49 can extend the annular surface 33 and be axially tangential thereto. They may have constant radius arcs RC depending on the circumference.
  • a first dotted line 72 extends the areas 47 and 49, and connects them.
  • a second dotted line 74 illustrates the general profile of the protuberance 52.
  • the radial spacing between these dashed lines (72; 74) highlights the overmaterial, that is to say the radial development formed by the protrusion 52 on the Likewise, the continuous line 76 which is separated from the second dotted line 74 highlights the radial development that the first bump 54 forms on the protuberance 52, ie the local thickening of the connecting surface 44.
  • continuous line 76 may pass through the first vertex 56. The latter may be flat.
  • the clean radial thickness of the first bump 54 may be twice the thickness of the protuberance 52. These thicknesses may be maximum thicknesses.
  • the bumps (54; 58) have inclinations greater than those of the protuberance 52.
  • the general plane 80 can join at least one or more or each corner of the surface. 44. Upstream and downstream, the protrusion 52 has lower slopes than the adjacent slopes of the bumps.
  • the present teaching can also be applied to an outer shell or to a casing via a symmetry along the axis A-A.
  • the figure 5 is a section of the figure 3 along the VV axis.
  • the section is perpendicular to the axis of rotation 14, and passes through the two bumps (54; 58) as the protuberance 52.
  • the connecting surface 44 has a constant radius RC.
  • This constant radius RC may correspond to that of the first zone 47 and / or that of the second zone 49.
  • the connecting surface 44 shows a variable radius RV.
  • the first top 56 of the first bump 54 is disposed between the neck 66 and the channel 64.
  • the connecting surface 44 is profiled. It has an increase of radial material relative to its base, in particular generated by the zones (47; 49). At a given point of the axis of rotation 14 disposed at the level of the bumps, the radius RV of the connecting surface 44 may vary as it traverses the connecting surface 44 in the circumferential direction 15, in particular by moving a dawn 26 to its neighbor, ie between the intrados surface 38 and the extrados surface 40. Although only two blades are shown, the present teaching can be applied to their entire annular row, or to several, or to each annular row d stator blades of the compressor. Similarly, the bonding surface can be reproduced identically between each blade next to the same row. This can form several annular rows of identical bumps (54; 58) and several identical annular rows of protuberances 52.
  • the teachings of each figure may be independently combined with the teachings of each of the other figures.
  • the invention provides a combination of the teachings of all the figures and / or with a combination of the whole of the technical solution.

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

Abstract

L'invention concerne un compresseur basse-pression de turbomachine axiale, tel un turboréacteur. Le compresseur comprend une rangée annulaire d'aubes (26) et un passage inter-aubes (42) avec une surface de liaison (44) reliant la surface intrados (38) d'une première aube (26) à la surface extrados (40) d'une deuxième aube (26) de la rangée. La surface de liaison (44) comporte une protubérance principale (52) qui comprend une première bosse (54) et une deuxième bosse (58) écartées l'une de l'autre.

Figure imgaf001
The invention relates to a low-pressure axial turbomachine compressor, such as a turbojet engine. The compressor comprises an annular array of vanes (26) and an inter-vane passage (42) with a connecting surface (44) connecting the intrados surface (38) of a first vane (26) to the extrados surface (40). ) a second blade (26) of the row. The connecting surface (44) has a main protuberance (52) that includes a first boss (54) and a second boss (58) spaced apart from each other.
Figure imgaf001

Description

Domaine techniqueTechnical area

L'invention concerne un compresseur avec une surface inter-aubes profilée. L'invention a également trait à une turbomachine axiale, notamment un turboréacteur d'avion ou un turbopropulseur d'aéronef.The invention relates to a compressor with a profiled inter-blade surface. The invention also relates to an axial turbomachine, in particular an aircraft turbojet engine or an aircraft turboprop engine.

Technique antérieurePrior art

Le document US 2007/0059177 A1 divulgue un compresseur de turboréacteur. Le compresseur présente une rangée annulaire d'aubes. Une plateforme est associée à chaque aube et présente un relief tridimensionnel s'étendant entre deux aubes successives. Chaque relief présente deux bosses séparées par un chenal sinusoïdal s'enfonçant radialement dans la plateforme. Cette géométrie améliore l'efficacité aérodynamique d'un aubage de compresseur à écoulement axial. Or, elle montre un décollement de coin élevé en extrados des aubes.The document US 2007/0059177 A1 discloses a turbojet compressor. The compressor has an annular row of vanes. A platform is associated with each blade and has a three-dimensional relief extending between two successive blades. Each relief has two bumps separated by a sinusoidal channel sinking radially into the platform. This geometry improves the aerodynamic efficiency of an axial flow compressor blade. However, it shows a high corner detachment in extrados of the blades.

Résumé de l'inventionSummary of the invention Problème techniqueTechnical problem

L'invention a pour objectif de résoudre au moins un des problèmes posés par l'art antérieur. Plus précisément, l'invention a pour objectif d'optimiser le taux de compression et les décollements en coin au niveau de l'extrados. L'invention a également pour objectif de proposer une solution simple, résistante, légère, économique, fiable, facile à produire, et commode d'entretien.The object of the invention is to solve at least one of the problems posed by the prior art. More specifically, the invention aims to optimize the compression ratio and the detachments in the corner at the extrados. The invention also aims to provide a simple solution, resistant, lightweight, economical, reliable, easy to produce, and convenient maintenance.

Solution techniqueTechnical solution

De manière générale, l'invention peut être entendue comme une bosse à deux sommets principaux, et/ou une convexité à deux extrémums radiaux ; entre deux aubes consécutives d'un compresseur.In general, the invention can be understood as a bump with two main peaks, and / or a convexity with two radial extremums; between two consecutive blades of a compressor.

L'invention a pour objet un compresseur de turbomachine axiale selon la revendication 1.The invention relates to an axial turbomachine compressor according to claim 1.

Selon des modes avantageux de l'invention, le compresseur peut comprendre une ou plusieurs des caractéristiques suivantes, prises isolément ou selon toutes les combinaisons techniques possibles :

  • La protubérance s'étend sur la majorité de la surface de liaison.
  • La première bosse et la deuxième bosse sont disposées en moitié amont de la protubérance et/ou des aubes de la rangée.
  • La première bosse est davantage développée radialement que la deuxième bosse depuis la protubérance et/ou depuis le niveau général de la surface de liaison.
  • La première bosse s'étend depuis la surface intrados de la première aube, et comprend éventuellement un premier sommet à distance de ladite surface intrados. Alternativement, le sommet peut être au contact de la surface intrados.
  • La deuxième bosse s'étend depuis la surface extrados de la deuxième aube, et comprend notamment un deuxième sommet accolé à ladite surface extrados. Alternativement, le sommet peut être à distance de la surface extrados.
  • La surface de liaison présente un tiers amont s'étendant depuis les bords d'attaque, la première bosse et la deuxième bosse étant renfermées dans ledit tiers amont.
  • La surface de liaison comporte quatre coins définissant un plan moyen, lesdits coins étant disposés aux bords d'attaque et aux bords de fuite des aubes, la protubérance formant une augmentation de matière radiale de la surface de liaison par rapport audit plan moyen, notamment le plan général.
  • Axialement, la longueur de la première bosse est comprise entre 30% et 50% ; valeurs comprises ; de la longueur de la première aube.
  • Selon la circonférence, la largeur de la première bosse est comprise entre 40% et 60% ; valeurs comprises ; de la largeur du passage inter-aubes.
  • Axialement, la longueur de la deuxième bosse est comprise entre 15% et 25% ; valeurs comprises ; de la longueur de la deuxième aube.
  • Selon la circonférence, la largeur de la deuxième bosse est comprise entre 5% et 15% ; valeurs comprises ; de la largeur du passage inter-aubes.
  • La surface de la deuxième bosse représente au plus 5% de la surface de la protubérance.
  • La hauteur radiale maximale de la première bosse est supérieure ou égale au triple de la hauteur radiale maximale de la deuxième bosse, et/ou supérieure ou égale à dix fois la hauteur maximale de la protubérance mesurée en dehors des bosses.
  • Le compresseur comprend un stator avec une virole, notamment une virole interne, reliée à la rangée annulaire d'aubes, la surface de liaison étant formée sur ladite virole.
  • La protubérance présente un col entre les bosses, selon la circonférence le col s'étend sur 40% à 60% ; valeurs incluses ; du passage inter-aubes.
  • La première bosse et la deuxième bosse présentent des extremums, notamment leurs sommets, disposés axialement au même niveau.
  • Selon la circonférence, la première bosse est disposée à l'opposé de la deuxième bosse dans le passage inter-aubes.
  • La surface de liaison, notamment les bosses et la protubérance, est/sont en contact du flux du compresseur.
  • La hauteur radiale maximale de la deuxième bosse est supérieure ou égale au triple de la hauteur radiale maximale de la protubérance mesurée en dehors des bosses.
  • Par rapport à la surface de liaison, la protubérance forme une surépaisseur de 0,30 mm.
  • La protubérance présente une moitié aval et une moitié amont dans laquelle sont renfermées la première bosse et la deuxième bosse.
  • La protubérance traverse circonférentiellement le passage et/ou relie les aubes.
  • Chaque aube comprend une corde dont l'angle d'inclinaison par rapport à l'axe de rotation est inférieure ou égale à : 15°, ou 30°, ou 40°.
  • La surface de liaison est libre de creux, notamment de creux s'étendant sur au plus : 20%, ou 10%, ou 5% ou 1% de la surface de liaison, chaque creux étant notamment entendu comme un vide de matière par rapport au plan général.
  • En tout point, la surface de liaison présente une quantité de matière positive ou nulle par rapport au plan général.
  • Le passage comprend un axe amont reliant les bords d'attaque, et un axe aval reliant les bords de fuite, lesdits axes délimitant axialement la surface de liaison.
  • La première aube et la deuxième aube sont des aubes consécutives et/ou voisines, et/ou inclinées circonférentiellement d'au plus : 10° ou 5° l'une par rapport à l'autre.
  • Les aubes de la rangée annulaire sont alignées circonférentiellement, leurs bords d'attaque et leurs bords de fuite sont alignés circonférentiellement.
  • Axialement au niveau du bord de fuite, la surface intrados et/ou la surface extrados est parallèle à l'axe de rotation du compresseur.
  • Chaque bosse et/ou la protubérance sont à distance axialement des bords d'attaque et des bords de fuite.
  • Chaque aube comprend un rayon de raccordement, la surface de liaison s'étendant depuis les rayons de raccordement de la première aube et de la deuxième aube.
  • La bosse est convexe, selon au moins deux directions, et/ou forme un épaississement sur le support.
  • Chaque aube comprend une corde et un espace entre sa surface intrados et ladite corde, le premier sommet étant majoritairement ou totalement à l'intérieur dudit espace, et/ou la première bosse étant majoritairement en dehors dudit espace.
  • Perpendiculairement à la corde, l'envergure de la deuxième bosse est inférieure à l'envergure de l'aube.
  • Par rapport au plan général, les bosses présentent des inclinaisons supérieures à celles de la protubérance.
According to advantageous modes of the invention, the compressor can comprise one or more of the following characteristics, taken separately or according to all the possible technical combinations:
  • The protuberance extends over the majority of the bonding surface.
  • The first bump and the second bump are arranged in half upstream of the protuberance and / or blades of the row.
  • The first bump is more radially developed than the second bump from the protuberance and / or from the general level of the bonding surface.
  • The first hump extends from the intrados surface of the first blade, and optionally includes a first vertex remote from said intrados surface. Alternatively, the top may be in contact with the intrados surface.
  • The second hump extends from the extrados surface of the second blade, and includes in particular a second vertex attached to said extrados surface. Alternatively, the top may be remote from the extrados surface.
  • The connecting surface has an upstream third extending from the leading edges, the first boss and the second boss being enclosed in said upstream third.
  • The connecting surface has four corners defining a mean plane, said corners being arranged at the leading edges and vanishing edges of the blades, the protuberance forming an increase in radial material of the connecting surface with respect to said mean plane, particularly the general plan.
  • Axially, the length of the first hump is between 30% and 50%; values included; the length of the first dawn.
  • Depending on the circumference, the width of the first bump is between 40% and 60%; values included; the width of the inter-blade passage.
  • Axially, the length of the second hump is between 15% and 25%; values included; the length of the second dawn.
  • Depending on the circumference, the width of the second hump is between 5% and 15%; values included; the width of the inter-blade passage.
  • The surface of the second bump represents at most 5% of the surface of the protuberance.
  • The maximum radial height of the first bump is greater than or equal to three times the maximum radial height of the second bump, and / or greater than or equal to ten times the maximum height of the protuberance measured outside the bumps.
  • The compressor comprises a stator with a ferrule, in particular an inner ferrule, connected to the annular row of blades, the bonding surface being formed on said ferrule.
  • The protuberance has a neck between the bumps, according to the circumference the neck extends on 40% to 60%; values included; of the passage between blades.
  • The first bump and the second bump have extremums, including their vertices, arranged axially at the same level.
  • According to the circumference, the first bump is disposed opposite the second bump in the inter-blade passage.
  • The connecting surface, in particular the bumps and the protuberance, is / are in contact with the flow of the compressor.
  • The maximum radial height of the second bump is greater than or equal to three times the maximum radial height of the protuberance measured outside the bumps.
  • With respect to the connecting surface, the protuberance forms an extra thickness of 0.30 mm.
  • The protuberance has a downstream half and an upstream half in which are contained the first hump and the second hump.
  • The protuberance circumferentially traverses the passage and / or connects the blades.
  • Each blade comprises a rope whose inclination angle with respect to the axis of rotation is less than or equal to: 15 °, or 30 °, or 40 °.
  • The connecting surface is free of cavities, in particular recesses extending over at most: 20%, or 10%, or 5% or 1% of the bonding surface, each hollow being in particular understood as a matter vacuum with respect to in general.
  • At all points, the bonding surface has a quantity of positive or zero material with respect to the general plane.
  • The passage comprises an upstream axis connecting the leading edges, and a downstream axis connecting the trailing edges, said axes defining axially the connecting surface.
  • The first blade and the second blade are consecutive blades and / or neighboring, and / or inclined circumferentially at most: 10 ° or 5 ° relative to each other.
  • The blades of the annular row are circumferentially aligned, their leading edges and their trailing edges are circumferentially aligned.
  • Axially at the trailing edge, the intrados surface and / or the extrados surface is parallel to the axis of rotation of the compressor.
  • Each boss and / or protuberance are axially spaced from leading edges and trailing edges.
  • Each blade includes a connecting radius, the connecting surface extending from the connecting radii of the first blade and the second blade.
  • The hump is convex, in at least two directions, and / or forms a thickening on the support.
  • Each blade comprises a rope and a space between its intrados surface and said rope, the first vertex being predominantly or totally within said space, and / or the first hump being predominantly outside said space.
  • Perpendicular to the rope, the span of the second hump is smaller than the span of dawn.
  • In relation to the general plane, the bumps present inclinations greater than those of the protuberance.

L'invention a également pour objet une turbomachine, notamment un turboréacteur d'aéronef, comprenant un compresseur, remarquable en ce que le compresseur est conforme à l'invention, préférentiellement la rangée d'aubes comprend au moins : cinquante, ou quatre-vingt aubes.The subject of the invention is also a turbomachine, in particular an aircraft turbojet, comprising a compressor, which is remarkable in that the compressor is in accordance with the invention, preferentially the row of blades comprises at least: fifty or eighty. blades.

De manière générale, chaque mode de réalisation de l'invention est combinable à chaque objet de l'invention.In general, each embodiment of the invention is combinable with each object of the invention.

Avantages apportésBenefits brought

La compression dans le passage augmente, tout comme le débit le traversant. Dans les conditions de fonctionnement d'un compresseur, la protubérance et les bosses traitent les phénomènes de tourbillons et de décollements. Le flux empruntant le passage regagne l'extrados au cours de sa compression, ce qui limite le décollement en coin.Compression in the passage increases, as does flow through it. In the operating conditions of a compressor, the protrusion and the bumps treat the phenomena of swirls and detachments. The flow borrowing the passage back to the extrados during its compression, which limits the detachment wedge.

Brève description des dessinsBrief description of the drawings

  • La figure 1 représente une turbomachine axiale selon l'invention.The figure 1 represents an axial turbomachine according to the invention.
  • La figure 2 est un schéma d'un compresseur de turbomachine selon l'invention.The figure 2 is a diagram of a turbomachine compressor according to the invention.
  • La figure 3 illustre deux aubes de compresseur bordant une surface de liaison selon l'invention.The figure 3 illustrates two compressor blades bordering a connecting surface according to the invention.
  • La figure 4 est une coupe de la figure 3 selon l'axe IV-IV.The figure 4 is a section of the figure 3 along the IV-IV axis.
  • La figure 5 est une coupe de la figure 3 selon l'axe V-V.The figure 5 is a section of the figure 3 along the VV axis.
Description des modes de réalisationDescription of the embodiments

Dans la description qui va suivre, les termes « interne » et « externe » renvoient à un positionnement par rapport à l'axe de rotation d'une turbomachine axiale. La direction axiale correspond à la direction le long de l'axe de rotation de la turbomachine. La direction radiale est perpendiculaire à l'axe de rotation. L'amont et l'aval sont en référence au sens d'écoulement principal du flux dans la turbomachine.In the following description, the terms "internal" and "external" refer to a positioning relative to the axis of rotation of an axial turbomachine. The axial direction corresponds to the direction along the axis of rotation of the turbomachine. The radial direction is perpendicular to the axis of rotation. Upstream and downstream are in reference to the main flow direction of the flow in the turbomachine.

La figure 1 représente de manière simplifiée une turbomachine axiale. Il s'agit dans ce cas précis d'un turboréacteur double-flux. Le turboréacteur 2 comprend un compresseur basse-pression 4, un compresseur haute-pression 6, une chambre de combustion 8 et un ou plusieurs niveaux de turbines 10. En fonctionnement, la puissance mécanique de la turbine 10 transmise via l'arbre central jusqu'au rotor 12 met en mouvement les deux compresseurs 4 et 6. Ces derniers comportent plusieurs rangées d'aubes de rotor associées à des rangées d'aubes de stator. La rotation du rotor autour de son axe de rotation 14 permet ainsi de générer un débit d'air et de comprimer progressivement ce dernier jusqu'à l'entrée de la chambre de combustion 8.The figure 1 represents in simplified manner an axial turbomachine. It is in this case a double-flow turbojet engine. The turbojet engine 2 comprises a low-pressure compressor 4, a high-pressure compressor 6, a combustion chamber 8 and one or more turbine levels 10. In operation, the mechanical power of the turbine 10 transmitted via the central shaft up to the rotor 12 sets in motion the two compressors 4 and 6. The latter comprise several rows of rotor blades associated with rows of stator vanes. The rotation of the rotor about its axis of rotation 14 thus makes it possible to generate an air flow and to compress this last to the entrance of the combustion chamber 8.

Une soufflante 16 ou ventilateur 16 est couplé au rotor 12 et génère un flux d'air qui se divise en un flux primaire 18 et en un flux secondaire 20 traversant un conduit annulaire (partiellement représenté). Le flux secondaire peut être accéléré de sorte à générer une réaction de poussée nécessaire au vol d'un avion. Les flux primaire 18 et secondaire 20 sont annulaires.A blower 16 or fan 16 is coupled to the rotor 12 and generates a stream of air which splits into a primary stream 18 and a secondary stream 20 passing through an annular duct (partially shown). The secondary flow can be accelerated so as to generate a thrust reaction necessary for the flight of an aircraft. The primary 18 and secondary 20 streams are annular.

La figure 2 est une vue en coupe d'un compresseur d'une turbomachine axiale telle que celle de la figure 1. Le compresseur peut être un compresseur basse-pression 4. On peut y observer une partie de la soufflante 16 et le bec de séparation 22 du flux primaire 18 et du flux secondaire 20.The figure 2 is a sectional view of a compressor of an axial turbomachine such as that of the figure 1 . The compressor may be a low-pressure compressor 4. There may be observed a portion of the fan 16 and the separation nozzle 22 of the primary flow 18 and the secondary flow 20.

Le rotor 12 comprend plusieurs rangées d'aubes rotoriques 24, en l'occurrence trois. Il peut être un tambour monobloc aubagé, ou comprendre des aubes à fixation par queue d'aronde. Les aubes rotoriques 24 peuvent s'étendre radialement depuis une plateforme individuelle, ou depuis une couronne interne 25 du rotor 12.The rotor 12 comprises several rows of rotor blades 24, in this case three. It may be a bladed monobloc drum, or include dovetail blades. The rotor vanes 24 may extend radially from an individual platform, or from an inner ring 25 of the rotor 12.

Le compresseur basse-pression 4 comprend plusieurs redresseurs, en l'occurrence quatre, qui contiennent chacun une rangée d'aubes statoriques 26. Les redresseurs sont associés au fan 16 ou à une rangée d'aubes rotoriques pour redresser le flux d'air, de sorte à convertir la vitesse du flux en pression, notamment en pression statique.The low-pressure compressor 4 comprises several rectifiers, in this case four, each containing a row of stator vanes 26. The rectifiers are associated with the fan 16 or with a row of rotor vanes to straighten the air flow, so as to convert the speed of the flow into pressure, in particular into static pressure.

Les aubes statoriques 26 s'étendent essentiellement radialement depuis un carter extérieur 28. Elles peuvent y être fixées et immobilisées à l'aide d'axes de fixation 30. Elles traversent radialement le flux primaire 18. Les aubes statoriques peuvent être à orientation fixe par rapport au carter 28. Avantageusement, les aubes d'une même rangée sont identiques et alignées. Chaque rangée peut comprendre cent vingt aubes (26 ; 24).The stator vanes 26 extend essentially radially from an outer casing 28. They can be fixed and immobilized by means of fixation pins 30. They pass radially through the primary flow 18. The stator vanes can be fixedly oriented by 28. Advantageously, the blades of the same row are identical and aligned. Each row may comprise one hundred twenty blades (26; 24).

Des viroles internes 32 peuvent être suspendues aux extrémités internes des aubes statoriques 26. Les viroles internes 32 peuvent coopérer de manière étanche avec le rotor 12 afin d'améliorer le taux de compression du compresseur 4.Internal ferrules 32 may be suspended at the inner ends of the stator vanes 26. The inner ferrules 32 may cooperate sealingly with the rotor 12 to improve the compression ratio of the compressor 4.

La figure 3 esquisse deux aubes 26 représentatives d'une rangée annulaire.The figure 3 sketching two blades 26 representative of an annular row.

La rangée peut être une des rangées présentées en relation avec les figures précédentes. Les aubes et leur support, éventuellement la virole interne 32, sont représentés en plan. L'axe de rotation 14 est tracé à une position figurative, et fournit un repère spatial.The row may be one of the rows presented in connection with the preceding figures. The vanes and their support, optionally the inner ferrule 32, are represented in plan. The axis of rotation 14 is traced to a figurative position, and provides a spatial marker.

Chaque aube 26 comprend un bord d'attaque 34, un bord de fuite 36, ainsi qu'une surface intrados 38 et une surface extrados 40. Ces surfaces (38 ; 40) peuvent être incurvées et bombées respectivement. Chacune de ces surfaces s'étend du bord d'attaque 34 au bord de fuite 36 correspondant. L'aube 26 peut comporter un empilement de profils aérodynamiques 41 cambrés, dont les côtés génèrent la surface intrados 38 et la surface extrados 40. Au niveau des bords de fuite 36, les contours des profils 41, en intrados et/ou en extrados, sont parallèles et/ou tangents à l'axe de rotation 14 du compresseur.Each blade 26 comprises a leading edge 34, a trailing edge 36, and a lower surface 38 and an extrados surface 40. These surfaces (38; 40) can be curved and curved respectively. Each of these surfaces extends from the leading edge 34 to the corresponding trailing edge 36. The blade 26 may comprise a stack of aerodynamic profiles 41 arched, whose sides generate the intrados surface 38 and the extrados surface 40. At the trailing edges 36, the contours of the profiles 41, in intrados and / or extrados, are parallel and / or tangent to the axis of rotation 14 of the compressor.

Les aubes 26 consécutives de la rangée annulaire définissent entre elle un passage 42, également appelé passage inter-aubes 42. Ce passage 42 est cloisonné circonférentiellement par les aubes 26, et délimités par les surfaces intrados et extrados. Le passage 42 peut présenter une surface de liaison 44 entre les deux aubes 26 consécutives, et peut relier la surface intrados 38 qui est en regard de la surface extrados 40 au travers du passage 42.The consecutive blades 26 of the annular row define between it a passage 42, also called inter-blade passage 42. This passage 42 is partitioned circumferentially by the blades 26, and delimited by the intrados and extrados surfaces. The passage 42 may have a connecting surface 44 between the two consecutive blades 26, and may connect the intrados surface 38 which faces the extrados surface 40 through the passage 42.

La surface de liaison 44 peut être délimitée axialement par un axe amont 46 et un axe aval 48 qui relient les bords d'attaque 34 et les bords de fuite 36 respectivement. Ces axes (46 ; 48) peuvent être parallèles, et peuvent généralement définir un parallélogramme ou un trapèze. La surface de liaison 44 peut être généralement plane.The connecting surface 44 may be defined axially by an upstream axis 46 and a downstream axis 48 which connect the leading edges 34 and the trailing edges 36 respectively. These axes (46; 48) can be parallel, and can generally define a parallelogram or a trapezoid. The connecting surface 44 may be generally flat.

Plus précisément, la surface de liaison 44 peut être une partie de surface tubulaire ou une partie de surface de cône, notamment en raison du rayon de la virole et de l'optionnelle variation de diamètre de la virole 32 le long de l'axe de rotation 14. Elle peut comprendre quatre coins 50 correspondant aux intersections entre les bords (34 ; 36) et le support, en l'occurrence la virole 32, par exemple interne.More specifically, the connecting surface 44 may be a tubular surface part or a cone surface part, in particular because of the radius of the ferrule and the optional diameter variation of the ferrule 32 along the axis of the ferrule. rotation 14. It may comprise four corners 50 corresponding to the intersections between the edges (34; 36) and the support, in this case the ferrule 32, for example internal.

La surface de liaison 44 peut comprendre une zone amont 47 s'étendant vers l'aval depuis l'axe amont 46, et une zone aval 49 s'étendant vers l'amont depuis l'axe aval 48.The connecting surface 44 may comprise an upstream zone 47 extending downstream from the upstream axis 46, and a downstream zone 49 extending upstream from the downstream axis 48.

La surface de liaison 44 présente une asymétrie axiale par rapport à l'axe de rotation 14. Elle présente une protubérance 52, notamment une protubérance principale 52. Cette protubérance 52 peut occuper la majeure partie de la surface de liaison 44. La majorité axiale de la protubérance 52 peut être contenue dans la moitié amont de la rangée d'aubes 26. Elle forme un ajout de matière radial sur la surface de liaison 44. L'ajout de matière peut être observé par rapport aux zones 47 et 49.The connecting surface 44 has an axial asymmetry with respect to the axis of rotation 14. It has a protrusion 52, in particular a main protrusion 52. This protrusion 52 can occupy most of the The axial majority of the protuberance 52 may be contained in the upstream half of the row of blades 26. It forms an addition of radial material on the connecting surface 44. The addition of material can be observed by compared to zones 47 and 49.

La protubérance 52 comprend également une première bosse 54 avec un premier sommet 56, et une deuxième bosse 58 avec un deuxième sommet 60. Ces bosses 54 et 58 peuvent être les bosses principales de la protubérance 52, c'est-à-dire qu'elles en forment les reliefs de volume principaux.The protrusion 52 also includes a first boss 54 with a first boss 56, and a second boss 58 with a second boss 60. These bosses 54 and 58 may be the major bosses of the protuberance 52, i.e. they form the main volume reliefs.

Les bosses (54 ; 58) peuvent s'étendre sur au plus la majorité axiale des aubes 26. La première bosse peut s'étendre axialement sur 30% de la corde 62 de la première aube 26, et/ou la deuxième bosse 58 peut s'étendre axialement sur 20% de la corde 62 de la deuxième aube 26. Ces bosses (54 ; 58) peuvent être en retrait axialement des bords d'attaque 34, notamment de 10% la longueur axiale d'une corde 62. Le premier sommet 56 peut présenter un allongement principal parallèle à la corde 62 de la première aube 26.The bumps (54; 58) may extend over at most the axial majority of the blades 26. The first bump may extend axially on 30% of the rope 62 of the first blade 26, and / or the second bump 58 may extend axially on 20% of the rope 62 of the second blade 26. These bumps (54; 58) may be recessed axially from the leading edges 34, in particular by 10% the axial length of a rope 62. first top 56 may have a main elongation parallel to the rope 62 of the first blade 26.

Selon la circonférence 15, la première bosse 54 peut s'étendre sur 50% du passage inter-aubes 42 et s'étendre depuis la surface intrados 38. Son sommet 56 peut être à distance de la surface intrados 38. Un chenal 64 peut être formé contre la première bosse 54, entre la surface intrados 38 de la première aube 26 et le premier sommet 56. La deuxième bosse 58 peut s'étendre circonférentiellement sur 10% du passage 42, son sommet 60 peut être accolé à la surface extrados 40 de la deuxième aube 26.According to the circumference 15, the first bump 54 may extend over 50% of the inter-blade passage 42 and extend from the intrados surface 38. Its top 56 may be at a distance from the intrados surface 38. A channel 64 may be formed against the first bump 54, between the intrados surface 38 of the first blade 26 and the first top 56. The second bump 58 may extend circumferentially over 10% of the passage 42, its top 60 may be attached to the upper surface 40 of the second dawn 26.

La première bosse 54 et la deuxième bosse 58 peuvent être au même niveau axialement. Leurs sommets (56 ; 60) peut être alignés axialement. Les bosses (54 ; 58) peuvent être séparées l'une de l'autre, et notamment distantes l'une de l'autre selon la circonférence. Un col 66, tel un col de montagne, peut les séparer circonférentiellement.The first bump 54 and the second bump 58 may be at the same level axially. Their vertices (56; 60) can be aligned axially. The bumps (54; 58) can be separated from one another, and in particular spaced from each other along the circumference. A collar 66, such as a mountain collar, can circumferentially separate them.

La courbe 67 est la courbe du col 66 la plus courte entre les sommets 56 et 60. Cette courbe 67 ainsi que tous les points du col 66 sont en surélévation par rapport à la surface régulière en absence de protubérance, représentée par les zones 47 et 49, de rayon constant.The curve 67 is the curve of the shortest neck 66 between the vertices 56 and 60. This curve 67 as well as all the points of the neck 66 are in elevation relative to the regular surface in the absence of protuberance, represented by the zones 47 and 49, of constant radius.

Les bosses (54 ; 58) et la protubérance 52 sont représentés à l'aide de lignes de niveau 68. Ces lignes de niveau 68 marquent des variations de niveau radial par rapport à une surface de référence, en l'occurrence la surface de liaison 44. La figure 4 est une coupe de la figure 3 selon l'axe IV-IV. La position comme l'inclinaison de l'axe de rotation 14 sont figuratives et peuvent varier dans des réalisations concrètes.The bumps (54; 58) and the protuberance 52 are represented by means of level lines 68. These level lines 68 indicate radial level variations with respect to a reference surface, in this case the connecting surface. 44. The figure 4 is a section of the figure 3 along the IV-IV axis. The position as the inclination of the axis of rotation 14 are figurative and can vary in concrete embodiments.

De manière générale, les aubes peuvent comprendre des rayons de raccordement 70 à leurs extrémités radiales. Les rayons de raccordement 70 peuvent entourer leur aube 26 respective. La surface de liaison 44 peut s'étendre depuis les rayons de raccordement 70 de manière à les relier deux à deux. L'épaisseur radiale des rayons de raccordement 70 est inférieure à celle des bosses et éventuellement de la protubérance 52.In general, the blades may comprise connecting radii 70 at their radial ends. The connecting spokes 70 may surround their respective blades 26. The connecting surface 44 can extend from the connecting spokes 70 so as to connect them in pairs. The radial thickness of the connecting radii 70 is smaller than that of the bumps and possibly of the protuberance 52.

Le bord d'attaque 34 et le bord de fuite 36 de la première aube s'étendant radialement depuis la surface annulaire 33 de la virole interne 32. Cette surface annulaire 33 peut présenter un rayon constant RC en dehors des passages. La surface annulaire 33 peut présenter une symétrie axiale. Les zones 47 et 49 peuvent prolonger la surface annulaire 33 et y être tangentes axialement. Elles peuvent présenter des arcs de rayons constants RC selon la circonférence.The leading edge 34 and the trailing edge 36 of the first blade extending radially from the annular surface 33 of the inner shell 32. This annular surface 33 may have a constant radius RC outside the passages. The annular surface 33 may have axial symmetry. The zones 47 and 49 can extend the annular surface 33 and be axially tangential thereto. They may have constant radius arcs RC depending on the circumference.

Un premier trait pointillé 72 prolonge les zones 47 et 49, et les relie. Un deuxième trait pointillé 74 illustre le profil général de la protubérance 52. L'écart radial entre ces traits pointillés (72 ; 74) met en évidence la surmatière, c'est-à-dire le développement radial que forme la protubérance 52 sur la surface de liaison 44. De même, la ligne continue 76 qui est écartée du deuxième trait pointillé 74 met en évidence le développement radial que forme la première bosse 54 sur la protubérance 52, soit l'épaississement local de la surface de liaison 44. La ligne continue 76 peut passer par le premier sommet 56. Ce dernier peut être plat.A first dotted line 72 extends the areas 47 and 49, and connects them. A second dotted line 74 illustrates the general profile of the protuberance 52. The radial spacing between these dashed lines (72; 74) highlights the overmaterial, that is to say the radial development formed by the protrusion 52 on the Likewise, the continuous line 76 which is separated from the second dotted line 74 highlights the radial development that the first bump 54 forms on the protuberance 52, ie the local thickening of the connecting surface 44. continuous line 76 may pass through the first vertex 56. The latter may be flat.

L'épaisseur radiale propre de la première bosse 54 peut être deux fois supérieure à l'épaisseur propre de la protubérance 52. Ces épaisseurs peuvent être des épaisseurs maximales.The clean radial thickness of the first bump 54 may be twice the thickness of the protuberance 52. These thicknesses may be maximum thicknesses.

Par rapport au plan général 80 de la surface de liaison 44, les bosses (54 ; 58) présentent des inclinaisons supérieures à celles de la protubérance 52. Le plan général 80 peut joindre au moins un ou plusieurs ou chaque coin de la surface de liaison 44. En amont et en aval, la protubérance 52 présente des pentes plus faibles que les pentes attenantes des bosses.With respect to the general plane 80 of the connecting surface 44, the bumps (54; 58) have inclinations greater than those of the protuberance 52. The general plane 80 can join at least one or more or each corner of the surface. 44. Upstream and downstream, the protrusion 52 has lower slopes than the adjacent slopes of the bumps.

Le présent enseignement peut également être appliqué à une virole externe ou à un carter via une symétrie selon l'axe A-A.The present teaching can also be applied to an outer shell or to a casing via a symmetry along the axis A-A.

La figure 5 est une coupe de la figure 3 selon l'axe V-V. La coupe est perpendiculaire à l'axe de rotation 14, et traverse les deux bosses (54 ; 58) comme la protubérance 52.The figure 5 is a section of the figure 3 along the VV axis. The section is perpendicular to the axis of rotation 14, and passes through the two bumps (54; 58) as the protuberance 52.

Autour de l'axe de rotation 14, la surface de liaison 44 présente un rayon constant RC. Ce rayon constant RC peut correspondre à celui de la première zone 47 et/ou à celui de la deuxième zone 49. Au niveau des bosses (54 ; 58), elle montre un rayon variable RV. Le premier sommet 56 de la première bosse 54 est disposé entre le col 66 et le chenal 64.Around the axis of rotation 14, the connecting surface 44 has a constant radius RC. This constant radius RC may correspond to that of the first zone 47 and / or that of the second zone 49. At the level of the bumps (54; 58), it shows a variable radius RV. The first top 56 of the first bump 54 is disposed between the neck 66 and the channel 64.

La surface de liaison 44 est profilée. Elle présente une augmentation de matière radiale par rapport à sa base, notamment générée par les zones (47 ; 49). En un point donné de l'axe de rotation 14 disposé au niveau des bosses, le rayon RV de la surface de liaison 44 peut varier lorsqu'il parcourt la surface de liaison 44 suivant la direction circonférentielle 15, notamment en se déplaçant d'une aube 26 à sa voisine, soit entre la surface intrados 38 et la surface extrados 40. Bien que seulement deux aubes ne soient représentées, le présent enseignement peut s'appliquer à toute leur rangée annulaire, ou à plusieurs, ou à chaque rangée annulaire d'aubes statoriques du compresseur. De même, la surface de liaison peut être reproduite à l'identique entre chaque aube voisine d'une même rangée. Cela peut former plusieurs rangées annulaires de bosses (54 ; 58) identiques ainsi que plusieurs rangées annulaires de protubérances 52 identiques.The connecting surface 44 is profiled. It has an increase of radial material relative to its base, in particular generated by the zones (47; 49). At a given point of the axis of rotation 14 disposed at the level of the bumps, the radius RV of the connecting surface 44 may vary as it traverses the connecting surface 44 in the circumferential direction 15, in particular by moving a dawn 26 to its neighbor, ie between the intrados surface 38 and the extrados surface 40. Although only two blades are shown, the present teaching can be applied to their entire annular row, or to several, or to each annular row d stator blades of the compressor. Similarly, the bonding surface can be reproduced identically between each blade next to the same row. This can form several annular rows of identical bumps (54; 58) and several identical annular rows of protuberances 52.

Les enseignements de chaque figure peuvent être indépendamment combinés aux enseignements de chacune des autres figures. L'invention prévoit une combinaison des enseignements de toutes les figures et/ou avec une combinaison de l'ensemble de la solution technique.The teachings of each figure may be independently combined with the teachings of each of the other figures. The invention provides a combination of the teachings of all the figures and / or with a combination of the whole of the technical solution.

Claims (15)

Compresseur (4 ; 6) de turbomachine axiale (2), notamment un compresseur basse-pression (4) de turbomachine axiale (2), le compresseur (4 ; 6) comprenant : - une rangée annulaire d'aubes (26), chaque aube (26) comprenant un bord d'attaque (34), un bord de fuite (36), une surface intrados (38) et une surface extrados (40) s'étendant du bord d'attaque (34) au bord de fuite (36), - un passage inter-aubes (42) avec une surface de liaison (44) reliant la surface intrados (38) d'une première aube (26) à la surface extrados (40) d'une deuxième aube (26) de la rangée, caractérisé en ce que
la surface de liaison (44) comporte : - une protubérance principale (52) comprenant une première bosse (54) et une deuxième bosse (58), présentant chacune un sommet (56 ; 60) ; - une zone amont (47) en amont de la protubérance (52) et une zone aval (49) en aval de la protubérance (52), lesdites zones (47 ; 49) étant chacune à rayon constant RC selon la circonférence ; - un col (66) rejoignant la première bosse (54) à la deuxième bosse (58) et ayant une courbe (67) de plus courte longueur entre les deux sommets (56 ; 60), tous les points de la courbe (67) étant radialement plus éloignés de l'axe (14) du compresseur (4 ; 6) que lesdites zones (47 ; 49) à rayon constant RC. Axial turbomachine compressor (4; 6), in particular a low-pressure axial-turbomachine compressor (4) (2), the compressor (4; 6) comprising: an annular array of vanes (26), each vane (26) comprising a leading edge (34), a trailing edge (36), an intrados surface (38) and an extrados surface (40) extending from the leading edge (34) to the trailing edge (36), - an inter-blade passage (42) with a connecting surface (44) connecting the intrados surface (38) of a first blade (26) to the extrados surface (40) of a second blade (26) of the row , characterized in that
the connecting surface (44) comprises: - a main protrusion (52) comprising a first boss (54) and a second boss (58), each having an apex (56; 60); an upstream zone (47) upstream of the protuberance (52) and a downstream zone (49) downstream of the protuberance (52), said zones (47; 49) being each of constant radius RC according to the circumference; - a neck (66) joining the first hump (54) to the second hump (58) and having a curve (67) of shorter length between the two vertices (56; 60), all the points of the curve (67) being radially further away from the axis (14) of the compressor (4; 6) than said zones (47; 49) of constant radius RC. Compresseur (4; 6) selon la revendication 1, caractérisé en ce que la deuxième bosse (58) s'étend depuis la surface extrados (40) de la deuxième aube (26), et comprend notamment un deuxième sommet (60) accolé à ladite surface extrados (40).Compressor (4; 6) according to claim 1, characterized in that the second boss (58) extends from the extrados surface (40) of the second blade (26), and comprises in particular a second vertex (60) attached to said extrados surface (40). Compresseur (4 ; 6) selon l'une des revendications 1 ou 2, caractérisé en ce que la surface de liaison (44) comporte quatre coins (50) définissant un plan général (80), lesdits coins (50) étant disposés aux bords d'attaque (34) et aux bords de fuite (36) des aubes (26), la protubérance (52) formant une augmentation de matière radiale de la surface de liaison (44) par rapport audit plan général (80).Compressor (4; 6) according to one of claims 1 or 2, characterized in that the connecting surface (44) has four corners (50) defining a general plane (80), said corners (50) being arranged at the edges at the trailing edges (36) of the vanes (26), the protuberance (52) forming a increasing radial material of the connecting surface (44) with respect to said general plane (80). Compresseur (4 ; 6) selon l'une des revendications 1 à 3, caractérisé en ce que la protubérance (52) s'étend sur la majorité de la surface de liaison (44).Compressor (4; 6) according to one of claims 1 to 3, characterized in that the protrusion (52) extends over the majority of the connecting surface (44). Compresseur (4 ; 6) selon l'une des revendications 1 à 4, caractérisé en ce que la première bosse (54) et la deuxième bosse (58) sont disposées en moitié amont de la protubérance (52) et/ou des aubes (26) de la rangée d'aubes.Compressor (4; 6) according to one of claims 1 to 4, characterized in that the first boss (54) and the second boss (58) are arranged in half-upstream of the protuberance (52) and / or blades ( 26) of the row of blades. Compresseur (4 ; 6) selon l'une des revendications 1 à 5, caractérisé en ce que la première bosse (54) est davantage développée radialement que la deuxième bosse (58) depuis la protubérance (52) et/ou depuis le plan général (80) de la surface de liaison (44).Compressor (4; 6) according to one of claims 1 to 5, characterized in that the first boss (54) is more radially developed than the second boss (58) from the protuberance (52) and / or from the general plane (80) of the connecting surface (44). Compresseur (4 ; 6) selon l'une des revendications 1 à 6, caractérisé en ce que la première bosse (54) s'étend depuis la surface intrados (38) de la première aube (26), et comprend éventuellement un premier sommet (56) à distance de ladite surface intrados (38).Compressor (4; 6) according to one of claims 1 to 6, characterized in that the first boss (54) extends from the intrados surface (38) of the first blade (26), and optionally comprises a first vertex (56) away from said intrados surface (38). Compresseur (4 ; 6) selon l'une des revendications 1 à 7, caractérisé en ce qu'axialement, la longueur de la première bosse (54) est comprise entre 30% et 50% ; valeurs comprises ; de la longueur de la première aube (26).Compressor (4; 6) according to one of claims 1 to 7, characterized in that axially, the length of the first boss (54) is between 30% and 50%; values included; the length of the first blade (26). Compresseur (4 ; 6) selon l'une des revendications 1 à 8, caractérisé en ce que selon la circonférence, la largeur de la première bosse (54) est comprise entre 40% et 60% ; valeurs comprises ; de la largeur du passage inter-aubes (42).Compressor (4; 6) according to one of claims 1 to 8, characterized in that the circumference, the width of the first boss (54) is between 40% and 60%; values included; the width of the inter-blade passage (42). Compresseur (4 ; 6) selon l'une des revendications 1 à 9, caractérisé en ce qu'axialement, la longueur de la deuxième bosse (58) est comprise entre 15% et 25% ; valeurs comprises ; de la longueur de la deuxième aube (26).Compressor (4; 6) according to one of claims 1 to 9, characterized in that axially, the length of the second boss (58) is between 15% and 25%; values included; the length of the second blade (26). Compresseur (4 ; 6) selon l'une des revendications 1 à 10, caractérisé en ce que selon la circonférence, la largeur de la deuxième bosse (58) est comprise entre 5% et 15% ; valeurs comprises ; de la largeur du passage inter-aubes (42).Compressor (4; 6) according to one of claims 1 to 10, characterized in that circumferentially, the width of the second boss (58) is between 5% and 15%; values included; the width of the inter-blade passage (42). Compresseur (4 ; 6) selon l'une des revendications 1 à 11, caractérisé en ce que la hauteur radiale maximale de la première bosse (54) est supérieure ou égale au triple de la hauteur radiale maximale de la deuxième bosse (58), et/ou supérieure ou égale à dix fois la hauteur maximale de la protubérance (52) mesurée en dehors des bosses (54 ; 58).Compressor (4; 6) according to one of claims 1 to 11, characterized in that the maximum radial height of the first boss (54) is greater than or equal to three times the maximum radial height of the second boss (58), and / or greater than or equal to ten times the maximum height of the protuberance (52) measured outside the bumps (54; 58). Compresseur (4 ; 6) selon l'une des revendications 1 à 12, caractérisé en ce que selon la circonférence, le col (66) s'étend sur 40% à 60% ; valeurs incluses ; du passage inter-aubes (42).Compressor (4; 6) according to one of claims 1 to 12, characterized in that circumferentially, the neck (66) extends over 40% to 60%; values included; the inter-blade passage (42). Compresseur (4 ; 6) selon l'une des revendications 1 à 13, caractérisé en ce que les sommets (56 ; 60) sont disposés axialement au même niveau.Compressor (4; 6) according to one of claims 1 to 13, characterized in that the vertices (56; 60) are arranged axially at the same level. Turbomachine (2), notamment un turboréacteur d'aéronef, comprenant un compresseur (4 ; 6), caractérisée en ce que le compresseur (4 ; 6) est conforme à l'une des revendications 1 à 14, la rangée d'aubes (26) comprenant au moins : cinquante, ou quatre-vingt aubes (26).Turbine engine (2), in particular an aircraft turbojet, comprising a compressor (4; 6), characterized in that the compressor (4; 6) is according to one of claims 1 to 14, the blade row ( 26) comprising at least: fifty, or eighty vanes (26).
EP18194178.2A 2017-10-26 2018-09-13 Turbine engine compressor with ring comprising elevations Active EP3477049B1 (en)

Applications Claiming Priority (1)

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BE2017/5764A BE1025668B1 (en) 2017-10-26 2017-10-26 DAMPER VIROLET FOR TURBOMACHINE COMPRESSOR

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US20190128121A1 (en) 2019-05-02
US11377960B2 (en) 2022-07-05
EP3477049B1 (en) 2023-11-22
BE1025668A1 (en) 2019-05-21

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