EP2721305B1 - Method for diffusing a gas turbine compression stage, and diffusion stage for implementing same - Google Patents

Method for diffusing a gas turbine compression stage, and diffusion stage for implementing same Download PDF

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Publication number
EP2721305B1
EP2721305B1 EP12734964.5A EP12734964A EP2721305B1 EP 2721305 B1 EP2721305 B1 EP 2721305B1 EP 12734964 A EP12734964 A EP 12734964A EP 2721305 B1 EP2721305 B1 EP 2721305B1
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European Patent Office
Prior art keywords
blades
plates
zones
diffusion
bump
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EP12734964.5A
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German (de)
French (fr)
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EP2721305A1 (en
Inventor
Laurent Tarnowski
Nicolas BULOT
Jérôme PORODO
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Safran Helicopter Engines SAS
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Safran Helicopter Engines SAS
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    • 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
    • F04D19/002—Axial flow fans
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F04—POSITIVE - DISPLACEMENT MACHINES FOR LIQUIDS; PUMPS FOR LIQUIDS OR ELASTIC FLUIDS
    • F04D—NON-POSITIVE-DISPLACEMENT PUMPS
    • F04D29/00—Details, component parts, or accessories
    • F04D29/40—Casings; Connections of working fluid
    • F04D29/42—Casings; Connections of working fluid for radial or helico-centrifugal pumps
    • F04D29/44—Fluid-guiding means, e.g. diffusers
    • F04D29/441—Fluid-guiding means, e.g. diffusers especially adapted for elastic fluid pumps
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F04—POSITIVE - DISPLACEMENT MACHINES FOR LIQUIDS; PUMPS FOR LIQUIDS OR ELASTIC FLUIDS
    • F04D—NON-POSITIVE-DISPLACEMENT PUMPS
    • F04D29/00—Details, component parts, or accessories
    • F04D29/40—Casings; Connections of working fluid
    • F04D29/42—Casings; Connections of working fluid for radial or helico-centrifugal pumps
    • F04D29/44—Fluid-guiding means, e.g. diffusers
    • F04D29/441—Fluid-guiding means, e.g. diffusers especially adapted for elastic fluid pumps
    • F04D29/444—Bladed diffusers
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F05—INDEXING SCHEMES RELATING TO ENGINES OR PUMPS IN VARIOUS SUBCLASSES OF CLASSES F01-F04
    • F05D—INDEXING SCHEME FOR ASPECTS RELATING TO NON-POSITIVE-DISPLACEMENT MACHINES OR ENGINES, GAS-TURBINES OR JET-PROPULSION PLANTS
    • F05D2250/00—Geometry
    • F05D2250/50—Inlet or outlet
    • F05D2250/52—Outlet

Definitions

  • the invention relates to a diffusion stage of a radial or mixed compressor of a gas turbine.
  • the field of the invention relates to improving the performance and the pumping margin of centrifugal and mixed compressors on the diffusion assembly of the stage concerned.
  • the function of this diffusion assembly is to transform the kinetic energy of the fluid, obtained at the outlet of the centrifugal wheel constituting the stage, into static pressure.
  • the operation must take place with a minimum of total pressure loss while maintaining a satisfactory level of compressor stability in order to maintain an acceptable pumping margin for the operation of the turbomachine.
  • a centrifugal compressor has at least one radial compression stage, that is to say capable of producing an air flow perpendicular to the central axis of the compressor.
  • a mixed compressor has at least one compression stage inclined relative to said central axis.
  • a diffusion assembly with a compression stage is composed of a wheel formed by two flanges between which the fluid flows in a centrifugal or inclined manner from the center to the periphery.
  • the vanes are distributed between the flanges all along the wheel. These blades form a flow grid between the leading edges of these blades on the center side and the trailing edges on the outer side.
  • the flanges of the radial and mixed diffusion assemblies are traditionally planar and the fluid passage sections between the vanes are advantageously scalable.
  • the changes in the passage sections are defined by the passage section at the diffuser neck and by the level of deceleration between the leading and trailing edges of the blade grid.
  • the aim of the invention is to achieve such a flow by installing flanges optimized in shape because these flanges represent the largest surface “wetted” by the flow.
  • Non-axisymmetric shapes in the direction of flow and tangentially are thus proposed.
  • the present invention relates to a diffusion stage of a radial or mixed compressor of a gas turbine according to claim 1.
  • the three-dimensional shape of the stream of the fluid makes it possible to redistribute and homogenize its flow in this stream: the secondary flows, which generate pressure losses, are appreciably reduced.
  • the position of the shocks in the transonic vanes is modified and their weakened intensity.
  • the aerodynamic blocking at the inlet of the combustion chamber which follows the compression stage is also significantly reduced.
  • the diffusion stage has alternating hollow and hump zones between the blades, in particular up to substantially 80% (preferably up to substantially 50%) of a chord of a blade, at the leading edge of the blades, with a start upstream of the leading edge, and / or, according to an advantageous feature, at the trailing edge, downstream of the trailing edge.
  • These alternating areas of hollow and bump can be applied to one and / or the other of the two centrifugal (radial) and mixed diffusion flanges, in particular symmetrically, with respect to a central plane of symmetry of the flanges, or in a parallel manner in the case where the two flanges of the stage are concerned.
  • downstream and upstream qualify positions relative to the flow of the air flow.
  • identical reference signs refer to the passages of the description in which the elements corresponding to these reference signs are defined.
  • an air flow F is first sucked into a fresh air inlet sleeve 2, then compressed between the blades 3 of an impeller 4 of a centrifugal compressor 5 and a cover 10.
  • the turbine is axially symmetrical around an X'X axis.
  • the compressor 5 is here centrifugal and the compressed flow F then exits radially from the impeller 4.
  • the flow comes out inclined at an angle between 0 ° and 90 ° with respect to a radial direction, perpendicular to the axis X'X.
  • the flow F then passes through a diffuser or wheel 6, arranged at the outlet of the compressor 4, to be straightened and conveyed to the inlet channels 7 of a combustion chamber 8.
  • the wheel 6 consists of a plurality of curved blades 60, arranged between two flanges 9 at the periphery of the impeller 4 - here radially - and therefore of revolution about the axis X'X.
  • each blade 60 has, in a known manner, a face called the upper surface 6e and a face called the lower surface 6i. In the example illustrated, these faces are connected by a tapered leading edge 6a and a rounded trailing edge 6f, in the direction of flow of the air flow. Transversely to the upper and lower surfaces, each blade 60 has flat sides 6p secured to the side plates 9.
  • the flanges 9 of figures 2a and 2b are classically flat. According to the invention, at least one of these flanges 9 has, in the space E which they define between them, at least one region of alternating curvature between two blades 60.
  • such a flange 9 is illustrated in profile, in the direction of flow of the air flow F along the vanes 60, from the entry at the leading edge 6a of the vane to the outlet channel 7 towards the combustion chamber.
  • Two zones of alternating curvature Z1 and Z2 are produced in the flange 9, along the vanes 60. Each of these zones has, on the side of the flow F, and with respect to the flat face portion 9p of the flange 9, a recessed portion 91 and a humped portion 92.
  • the zones Z1 and Z2 extend overall, in the non-limiting example illustrated, over approximately 80% of the length of the chord 6c of the blades 60.
  • the flange 9 has in the figures a filiform thickness to simplify the presentation, but it actually has a certain thickness and the zones of alternating curvature are formed on the internal face 9i of the flange where the air flow F.
  • outer face 9e of the flange 9 can remain flat or also match shapes with alternating bump and hollow curvature, reversed in this example with respect to the hollow and bump shapes of the inner face 9i.
  • the flange has a variable thickness and, in the second case, a constant thickness.
  • the shape of the flanges may depend in particular on the method used to produce the areas of alternating curvature: by milling, laser, electroerosion, forming, stamping, etc.
  • the two zones of alternating curvature Z1 and Z2 are respectively formed at the trailing edge 6f of the blades 60 and downstream vanes in the inlet of channel 7, and on the leading edge 6a from the upstream inlet of the vanes 60.
  • the figure 4 illustrates a partial schematic view of the inter-vane “tangential direction” diffusion stage 6t, that is to say between two vanes 60.
  • the arrow F indicates the direction of air flow.
  • the internal face 9i of the flange 9 has two zones of alternating curvature Z1 and Z2 which extend mainly between the lower surface 6i and upper surface 6th two blades 60.
  • the inter-blade perspective view at the leading edge 6a of the figure 5 shows, more precisely, the flange 9 with a zone of alternating curvature Z1 between the two blades 60.
  • the zone has the portion with recessed curvature 91, at the lower surface 6i of a blade 60, and the portion with hump curvature 92, at the 6th upper surface of the other vane 60. This alternation of curvatures balances the pressures between the lower surface and the upper surface of each vane 60.
  • the section at the neck 6s between the leading edges 6a is retained .
  • the homogenization of the flow of the air flow F is illustrated in perspective by the figure 6 .
  • a flat flange 90 shown hatched in the figure
  • an aerodynamic blockage is created in the zone Z0 with a very low amount of movement.
  • the main air flow (arrow F) has a high Mach number.
  • the aerodynamic blocking zone is eliminated and the flow of air F is homogenized by occupying the entire passage section offered, with a lower Mach number.
  • the invention is not limited to the embodiments described and shown.
  • the curvatures are alternated in the direction of flow of the fluid F but also in the tangential direction 6t.
  • the zones of alternating curvature can be juxtaposed so that surface portions of the same curvature, hollow or humped, can rub shoulders.

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

Description

DOMAINE TECHNIQUETECHNICAL AREA

L'invention se rapporte à un étage de diffusion de compresseur radial ou mixte de turbine à gaz.The invention relates to a diffusion stage of a radial or mixed compressor of a gas turbine.

Le domaine de l'invention concerne l'amélioration des performances et de la marge au pompage des compresseurs centrifuges et mixtes sur l'ensemble de diffusion de l'étage concerné. Cet ensemble de diffusion a pour fonction de transformer l'énergie cinétique du fluide, obtenue en sortie de la roue centrifuge constituant l'étage, en pression statique. L'opération doit se dérouler avec un minimum de perte de pression totale tout en maintenant un niveau de stabilité du compresseur satisfaisant afin de maintenir une marge au pompage acceptable pour le fonctionnement de la turbomachine.The field of the invention relates to improving the performance and the pumping margin of centrifugal and mixed compressors on the diffusion assembly of the stage concerned. The function of this diffusion assembly is to transform the kinetic energy of the fluid, obtained at the outlet of the centrifugal wheel constituting the stage, into static pressure. The operation must take place with a minimum of total pressure loss while maintaining a satisfactory level of compressor stability in order to maintain an acceptable pumping margin for the operation of the turbomachine.

Un compresseur centrifuge possède au moins un étage de compression radial, c'est-à-dire apte à réaliser un écoulement de l'air perpendiculaire à l'axe central du compresseur. Un compresseur mixte possède au moins un étage de compression incliné par rapport audit axe central.A centrifugal compressor has at least one radial compression stage, that is to say capable of producing an air flow perpendicular to the central axis of the compressor. A mixed compressor has at least one compression stage inclined relative to said central axis.

Un ensemble de diffusion d'un étage de compression est composé d'une roue formée de deux flasques entre lesquelles s'écoule le fluide de manière centrifuge ou inclinée à partir du centre vers la périphérie. Des aubes sont réparties entre les flasques tout le long de la roue. Ces aubes forment une grille d'écoulement entre les bords d'attaque de ces aubes du côté du centre et les bords de fuite du côté externe.A diffusion assembly with a compression stage is composed of a wheel formed by two flanges between which the fluid flows in a centrifugal or inclined manner from the center to the periphery. The vanes are distributed between the flanges all along the wheel. These blades form a flow grid between the leading edges of these blades on the center side and the trailing edges on the outer side.

ÉTAT DE LA TECHNIQUESTATE OF THE ART

Les flasques des ensembles de diffusion radiaux et mixtes sont traditionnellement plans et les sections de passage du fluide entre les aubes sont avantageusement évolutives. Les évolutions des sections de passage sont définies par la section de passage au col du diffuseur et par le niveau de ralentissement entre les bords d'attaque et de fuite de la grille d'aubes..The flanges of the radial and mixed diffusion assemblies are traditionally planar and the fluid passage sections between the vanes are advantageously scalable. The changes in the passage sections are defined by the passage section at the diffuser neck and by the level of deceleration between the leading and trailing edges of the blade grid.

D'autres architectures prévoient des flasques axisymétriques en liaison avec des veines évolutives pour un contrôle supplémentaire de la section de passage et optimiser ainsi la diffusion dans la grille. Une autre architecture est connue du document US2003/235497 A1 .Other architectures provide axisymmetric flanges in connection with scalable veins for additional control of the passage section and thus optimize the diffusion in the grid. Another architecture is known from the document US2003 / 235497 A1 .

Ces solutions ne permettent un contrôle que dans une dimension, celle de la variation de la section de passage. Aucun contrôle de l'hétérogénéité tangentielle de l'écoulement du fluide, entre deux aubes, n'est réalisé. Or ce contrôle permet de réguler et d'optimiser l'écoulement.These solutions only allow control in one dimension, that of the variation of the passage section. No control of the tangential heterogeneity of the flow of the fluid, between two blades, is carried out. However, this control makes it possible to regulate and optimize the flow.

EXPOSÉ DE L'INVENTIONDISCLOSURE OF THE INVENTION

L'invention vise à réaliser un tel écoulement par la mise en place de flasques optimisés en forme car ces flasques représentent la plus grande surface « mouillée » par l'écoulement. Des formes non-axisymétriques dans le sens de l'écoulement et tangentiellement sont ainsi proposées.The aim of the invention is to achieve such a flow by installing flanges optimized in shape because these flanges represent the largest surface “wetted” by the flow. Non-axisymmetric shapes in the direction of flow and tangentially are thus proposed.

Plus précisément, la présente invention a pour objet un étage de diffusion de compresseur radial ou mixte de turbine à gaz selon la revendication 1.More precisely, the present invention relates to a diffusion stage of a radial or mixed compressor of a gas turbine according to claim 1.

Dans cet étage de diffusion de compresseur radial ou mixte de turbine à gaz, la forme tridimensionnelle de la veine du fluide permet de redistribuer et d'homogénéiser son écoulement dans cette veine : les écoulements secondaires, générateurs de pertes de charge, sont sensiblement réduits. La position des chocs dans les aubages transsoniques est modifiée et leur intensité affaiblie. De plus, le blocage aérodynamique en entrée de la chambre de combustion qui suit l'étage de compression est également sensiblement réduit.In this radial or mixed gas turbine compressor diffusion stage, the three-dimensional shape of the stream of the fluid makes it possible to redistribute and homogenize its flow in this stream: the secondary flows, which generate pressure losses, are appreciably reduced. The position of the shocks in the transonic vanes is modified and their weakened intensity. In addition, the aerodynamic blocking at the inlet of the combustion chamber which follows the compression stage is also significantly reduced.

Selon l'invention, l'étage de diffusion présente des zones alternée en creux et en bosse entre les aubes, en particulier jusqu'à sensiblement 80 % (de préférence jusqu'à sensiblement 50%) d'une corde d'une aube, en bord d'attaque des aubes, avec un début en amont du bord d'attaque, et/ou, selon une particularité avantageuse, en bord de fuite, jusqu'en aval du bord de fuite. Ces zones alternées de creux et de bosse peuvent s'appliquer sur l'un et/ou l'autre des deux flasques de diffusion centrifuges (radiaux) et mixtes, notamment de manière symétrique, par rapport à un plan de symétrie central des flasques, ou de manière parallèle dans le cas où les deux flasques de l'étage sont concernés.According to the invention, the diffusion stage has alternating hollow and hump zones between the blades, in particular up to substantially 80% (preferably up to substantially 50%) of a chord of a blade, at the leading edge of the blades, with a start upstream of the leading edge, and / or, according to an advantageous feature, at the trailing edge, downstream of the trailing edge. These alternating areas of hollow and bump can be applied to one and / or the other of the two centrifugal (radial) and mixed diffusion flanges, in particular symmetrically, with respect to a central plane of symmetry of the flanges, or in a parallel manner in the case where the two flanges of the stage are concerned.

PRÉSENTATION DES FIGURESPRESENTATION OF FIGURES

D'autres données, caractéristiques et avantages de la présente invention apparaîtront à la lecture de la description non limitée qui suit, en référence aux figures annexées qui représentent, respectivement :

  • la figure 1, une vue en coupe partielle d'une turbine à gaz comportant un diffuseur d'air ;
  • les figures 2a et 2b, des vues en perspective d'un étage de diffusion à aubes comportant un et deux flasques ;
  • les figures 3a à 3c, des vues schématiques de profils d'un flasque dans le sens d'écoulement de l'air le long d'une aube, avec deux zones à courbure alternée respectivement le long de l'aube, en bord de fuite jusqu'en aval de l'aube, et en bord d'attaque à partir de l'amont de l'aube ;
  • la figure 4, une vue schématique partielle dans la direction tangentielle inter-aubes, avec un flasque présentant deux zones à courbure alternée ;
  • la figure 5, une vue schématique inter-aubes perspective en bord d'attaque avec un flasque présentant une zone à courbure alternée ; et
  • la figure 6, une vue schématique perspective en bord de fuite de deux aubes avec un flasque plan et un flasque présentant une zone à courbure alternée.
Other data, characteristics and advantages of the present invention will become apparent on reading the non-limited description which follows, with reference to the appended figures which represent, respectively:
  • the figure 1 , a partial sectional view of a gas turbine comprising an air diffuser;
  • the figures 2a and 2b , perspective views of a vane diffusion stage comprising one and two flanges;
  • the figures 3a to 3c , schematic profile views of a flange in the direction of air flow along a blade, with two areas of alternating curvature respectively along the blade, at the trailing edge downstream of dawn, and on the leading edge from upstream of dawn;
  • the figure 4 , a partial schematic view in the tangential inter-blade direction, with a flange having two zones of alternating curvature;
  • the figure 5 , a schematic inter-vane perspective view at the leading edge with a flange having an area of alternating curvature; and
  • the figure 6 , a schematic perspective view at the trailing edge of two blades with a flat flange and a flange having an area of alternating curvature.

DESCRIPTION DÉTAILLÉEDETAILED DESCRIPTION

Les termes « aval » et « amont » qualifient des positionnements par rapport à l'écoulement du flux d'air. Sur toutes les figures, des signes de références identiques renvoient aux passages de la description dans lesquels les éléments correspondant à ces signes de référence sont définis.The terms “downstream” and “upstream” qualify positions relative to the flow of the air flow. In all the figures, identical reference signs refer to the passages of the description in which the elements corresponding to these reference signs are defined.

En référence à la vue schématique en coupe partielle d'une turbine à gaz 1 d'hélicoptère selon la figure 1, un flux d'air F est d'abord aspiré dans une manche d'entrée d'air frais 2, puis comprimé entre les pales 3 d'un rouet 4 de compresseur centrifuge 5 et un couvercle 10. La turbine est de symétrie axiale autour d'un axe X'X.With reference to the schematic view in partial section of a helicopter gas turbine 1 according to figure 1 , an air flow F is first sucked into a fresh air inlet sleeve 2, then compressed between the blades 3 of an impeller 4 of a centrifugal compressor 5 and a cover 10. The turbine is axially symmetrical around an X'X axis.

Le compresseur 5 est ici centrifuge et le flux F comprimé sort alors radialement du rouet 4. Lorsque le compresseur est mixte, le flux sort incliné selon un angle compris entre 0° et 90° par rapport à une direction radiale, perpendiculaire à l'axe X'X.The compressor 5 is here centrifugal and the compressed flow F then exits radially from the impeller 4. When the compressor is mixed, the flow comes out inclined at an angle between 0 ° and 90 ° with respect to a radial direction, perpendicular to the axis X'X.

Le flux F passe alors par un diffuseur ou roue 6, disposé en sortie du compresseur 4, pour être redressé et acheminé vers des canaux 7 d'entrée d'une chambre de combustion 8.The flow F then passes through a diffuser or wheel 6, arranged at the outlet of the compressor 4, to be straightened and conveyed to the inlet channels 7 of a combustion chamber 8.

Pour effectuer ce redressement, la roue 6 se compose d'une pluralité d'aubes courbes 60, agencées entre deux flasques 9 à la périphérie du rouet 4 - ici de manière radiale - et donc de révolution autour de l'axe X'X.To perform this straightening, the wheel 6 consists of a plurality of curved blades 60, arranged between two flanges 9 at the periphery of the impeller 4 - here radially - and therefore of revolution about the axis X'X.

La figure 2b illustre plus précisément en vue perspective le diffuseur 6 à aubes 60 solidarisées à deux flasques 9. Sur la figure 2a, où un flasque a été supprimé pour plus de clarté, chaque aube 60 présente, de manière connue, une face dite extrados 6e et une face dite intrados 6i. Dans l'exemple illustré, ces faces sont reliées par un bord d'attaque effilé 6a et un bord de fuite arrondi 6f, dans le sens d'écoulement du flux d'air. Transversalement aux extrados et intrados, chaque aube 60 présente des flancs plans 6p solidarisés aux flasques 9.The figure 2b illustrates more precisely in perspective view the diffuser 6 with vanes 60 secured to two flanges 9. On the figure 2a , where a flange has been omitted for greater clarity, each blade 60 has, in a known manner, a face called the upper surface 6e and a face called the lower surface 6i. In the example illustrated, these faces are connected by a tapered leading edge 6a and a rounded trailing edge 6f, in the direction of flow of the air flow. Transversely to the upper and lower surfaces, each blade 60 has flat sides 6p secured to the side plates 9.

Les flasques 9 des figures 2a et 2b sont classiquement plans. Selon l'invention, l'un au moins de ces flasques 9 présentent, dans l'espace E qu'ils définissent entre eux, au moins une zone à courbure alternée entre deux aubes 60.The flanges 9 of figures 2a and 2b are classically flat. According to the invention, at least one of these flanges 9 has, in the space E which they define between them, at least one region of alternating curvature between two blades 60.

En référence à la figure 3a, un tel flasque 9 est illustré de profil, dans le sens d'écoulement du flux d'air F le long des aubes 60, de l'entrée en bord d'attaque 6a de l'aube jusqu'au canal 7 de sortie vers la chambre de combustion. Deux zones à courbure alternée Z1 et Z2 sont réalisées dans le flasque 9, le long des aubes 60. Chacune de ces zones présente du côté du flux F, et par rapport à la portion de face plane 9p du flasque 9, une portion en creux 91 et une portion en bosse 92. Les zones Z1 et Z2 s'étendent globalement, dans l'exemple illustré non limitatif, sur environ 80% de la longueur de la corde 6c des aubes 60.With reference to the figure 3a , such a flange 9 is illustrated in profile, in the direction of flow of the air flow F along the vanes 60, from the entry at the leading edge 6a of the vane to the outlet channel 7 towards the combustion chamber. Two zones of alternating curvature Z1 and Z2 are produced in the flange 9, along the vanes 60. Each of these zones has, on the side of the flow F, and with respect to the flat face portion 9p of the flange 9, a recessed portion 91 and a humped portion 92. The zones Z1 and Z2 extend overall, in the non-limiting example illustrated, over approximately 80% of the length of the chord 6c of the blades 60.

Le flasque 9 présente sur les figures une épaisseur filiforme pour simplifier la présentation, mais il présente en réalité une certaine épaisseur et les zones à courbure alternée sont formées sur la face interne 9i du flasque où s'écoule le flux d'air F. La face externe 9e du flasque 9 peut rester plane ou épouser également des formes à courbure alternée en bosse et creux, inversées dans cet exemple par rapport aux formes en creux et bosse de la face interne 9i. Dans le premier cas, le flasque présente une épaisseur variable et, dans le second cas, une épaisseur constante. La forme des flasques peut dépendre en particulier de la méthode utilisée pour réaliser les zones de courbure alternée : par fraisage, laser, électroérosion, formage, emboutissage, etc.The flange 9 has in the figures a filiform thickness to simplify the presentation, but it actually has a certain thickness and the zones of alternating curvature are formed on the internal face 9i of the flange where the air flow F. outer face 9e of the flange 9 can remain flat or also match shapes with alternating bump and hollow curvature, reversed in this example with respect to the hollow and bump shapes of the inner face 9i. In the first case, the flange has a variable thickness and, in the second case, a constant thickness. The shape of the flanges may depend in particular on the method used to produce the areas of alternating curvature: by milling, laser, electroerosion, forming, stamping, etc.

Sur les figures 3b et 3c, les deux zones à courbure alternée Z1 et Z2 sont respectivement formées en bord de fuite 6f des aubes 60 et jusqu'en aval des aubes dans l'entrée du canal 7, et en bord d'attaque 6a à partir de l'entrée amont des aubes 60.On the figures 3b and 3c , the two zones of alternating curvature Z1 and Z2 are respectively formed at the trailing edge 6f of the blades 60 and downstream vanes in the inlet of channel 7, and on the leading edge 6a from the upstream inlet of the vanes 60.

La figure 4 illustre une vue schématique partielle de l'étage de diffusion « dans la direction tangentielle » 6t inter-aubes, c'est-à-dire entre deux aubes 60. La flèche F indique le sens d'écoulement de l'air. La face interne 9i du flasque 9 présente deux zones à courbure alternée Z1 et Z2 qui s'étendent principalement entre les faces intrados 6i et extrados 6e deux aubes 60.The figure 4 illustrates a partial schematic view of the inter-vane “tangential direction” diffusion stage 6t, that is to say between two vanes 60. The arrow F indicates the direction of air flow. The internal face 9i of the flange 9 has two zones of alternating curvature Z1 and Z2 which extend mainly between the lower surface 6i and upper surface 6th two blades 60.

La vue en perspective inter-aubes en bord d'attaque 6a de la figure 5 montre, plus précisément, le flasque 9 avec une zone à courbure alternée Z1 entre les deux aubes 60. La zone présente la portion à courbure en creux 91, à l'intrados 6i d'une aube 60, et la portion à courbure en bosse 92, à l'extrados 6e de l'autre aube 60. Cette alternance de courbures permet un équilibrage des pressions entre l'intrados et l'extrados de chaque aube 60. La section au col 6s entre les bords d'attaque 6a est conservée.The inter-blade perspective view at the leading edge 6a of the figure 5 shows, more precisely, the flange 9 with a zone of alternating curvature Z1 between the two blades 60. The zone has the portion with recessed curvature 91, at the lower surface 6i of a blade 60, and the portion with hump curvature 92, at the 6th upper surface of the other vane 60. This alternation of curvatures balances the pressures between the lower surface and the upper surface of each vane 60. The section at the neck 6s between the leading edges 6a is retained .

Aux bords de fuite 6f, l'homogénéisation de l'écoulement du flux d'air F est illustrée en perspective par la figure 6. Avec un flasque plan 90 (représenté hachuré sur la figure) entre deux aubes 60, un blocage aérodynamique se créé dans la zone Z0 à très faible quantité de mouvement. Dans cette configuration de l'état de la technique, l'écoulement d'air principal (flèche F) est à fort nombre de Mach. Par contraste, avec un flasque 9 à courbure alternée selon l'invention, la zone de blocage aérodynamique est supprimée et l'écoulement de l'air F est homogénéisé en occupant toute la section de passage offerte, avec un nombre de Mach plus faible.At the trailing edges 6f, the homogenization of the flow of the air flow F is illustrated in perspective by the figure 6 . With a flat flange 90 (shown hatched in the figure) between two blades 60, an aerodynamic blockage is created in the zone Z0 with a very low amount of movement. In this configuration of the state of the art, the main air flow (arrow F) has a high Mach number. In contrast, with a flange 9 with alternating curvature according to the invention, the aerodynamic blocking zone is eliminated and the flow of air F is homogenized by occupying the entire passage section offered, with a lower Mach number.

L'invention n'est pas limitée aux exemples de réalisation décrits et représentés. Ainsi, dans les exemples illustrés les courbures sont alternées dans le sens d'écoulement du fluide F mais également dans la direction tangentielle 6t. Dans d'autres variantes, les zones à courbure alternée peuvent se juxtaposer de sorte que des portions de surface de même courbure, en creux ou en bosse, peuvent se côtoyer.The invention is not limited to the embodiments described and shown. Thus, in the examples illustrated, the curvatures are alternated in the direction of flow of the fluid F but also in the tangential direction 6t. In other variants, the zones of alternating curvature can be juxtaposed so that surface portions of the same curvature, hollow or humped, can rub shoulders.

Claims (5)

  1. Diffusion stage of a radial or mixed gas turbine engine compressor comprising an impeller (6) formed by two plates (9), between which the fluid flows in a centrifugal or inclined manner from the centre towards the periphery, blades (60) of a cascade being distributed around said impeller (6) between said plates (9) so as to channel the flow of the fluid between the leading edges (6a) of said blades (60) at the centre and the trailing edges (6f) at the periphery, at least one of said plates (9) has an internal face (9i) comprising at least one zone (Z1, Z2) with alternating hollow (91) and bump (92) curvatures between two adjacent blades (60) in the direction of flow along said blades (60), and wherein at least one of said plates (9) has an internal face (9i) further comprising at least one zone (Z1, Z2) with alternating hollow (91) and bump (92) curvatures between two adjacent blades (60) in an inter-blade tangential direction (6t) substantially perpendicular to the direction of flow (F) along said blades, characterized in that it has hollow and bump zones (Z1, Z2) at said leading edge (6a) of said blades (60), starting upstream of said leading edge (6a).
  2. Diffusion stage according to claim 1, characterised in that it has alternating hollow (91) and bump (92) zones (Z1, Z2) between said blades, in particular up to substantially 80%, and preferably up to substantially 50%, of a chord line (6c) of a blade (60).
  3. Diffusion stage at the leading edge of said blades according to any one of claims 1 to 2, characterised in that it has hollow and bump zones (Z1, Z2) at said trailing edge (6f) of said blades (60), continuing to downstream of said trailing edge (6f).
  4. Diffusion stage at the leading edge of said blades according to any one of claims 1 to 3, wherein said alternating hollow and bump zones (Z1, Z2) are applied to one and/or the other of said two plates (9) for centrifugal and mixed diffusion.
  5. Diffusion stage according to the preceding claim, wherein said alternating zones (Z1, Z2) are applied to said plates (9) in a symmetrical manner, relative to a central plane of symmetry of said plates (9), or in a parallel manner.
EP12734964.5A 2011-06-20 2012-06-19 Method for diffusing a gas turbine compression stage, and diffusion stage for implementing same Active EP2721305B1 (en)

Priority Applications (1)

Application Number Priority Date Filing Date Title
PL12734964T PL2721305T3 (en) 2011-06-20 2012-06-19 Method for diffusing a gas turbine compression stage, and diffusion stage for implementing same

Applications Claiming Priority (2)

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FR1155370A FR2976633B1 (en) 2011-06-20 2011-06-20 METHOD OF DIFFUSING A COMPRESSION STAGE OF A GAS TURBINE AND THE DIFFUSION STAGE THEREFOR
PCT/FR2012/051367 WO2012175855A1 (en) 2011-06-20 2012-06-19 Method for diffusing a gas turbine compression stage, and diffusion stage for implementing same

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EP2721305B1 true EP2721305B1 (en) 2021-02-24

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EP (1) EP2721305B1 (en)
JP (1) JP6261498B2 (en)
KR (1) KR101946084B1 (en)
CN (1) CN103635698B (en)
CA (1) CA2838686C (en)
FR (1) FR2976633B1 (en)
IN (1) IN2014DN00118A (en)
PL (1) PL2721305T3 (en)
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FR3003908B1 (en) 2013-03-28 2017-07-07 Turbomeca DIFFUSER WITH FINES OF A RADIAL OR MIXED COMPRESSOR
DE102017122524A1 (en) * 2017-09-28 2019-03-28 Abb Turbo Systems Ag Diffuser for a compressor
US11286952B2 (en) 2020-07-14 2022-03-29 Rolls-Royce Corporation Diffusion system configured for use with centrifugal compressor

Citations (1)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US20030235497A1 (en) * 2002-06-20 2003-12-25 The Boeing Company Diffuser having a variable blade height

Family Cites Families (7)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
GB685814A (en) * 1950-03-03 1953-01-14 Escher Wyss Ag Improvements in and relating to radial centrifugal compressors and pumps
US6123506A (en) * 1999-01-20 2000-09-26 Pratt & Whitney Canada Corp. Diffuser pipe assembly
RU2197644C1 (en) * 2001-07-30 2003-01-27 Открытое акционерное общество "Татнефть" Centrifugal pump impeller
GB0223756D0 (en) * 2002-10-14 2002-11-20 Holset Engineering Co Compressor
RU2330994C2 (en) * 2006-05-16 2008-08-10 Открытое акционерное общество "Климов" Centrifugal compressor
US8100643B2 (en) * 2009-04-30 2012-01-24 Pratt & Whitney Canada Corp. Centrifugal compressor vane diffuser wall contouring
CN201461538U (en) * 2009-07-30 2010-05-12 大同北方天力增压技术有限公司 Parabola-shaped blade type pressure diffuser

Patent Citations (1)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US20030235497A1 (en) * 2002-06-20 2003-12-25 The Boeing Company Diffuser having a variable blade height

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US20140133957A1 (en) 2014-05-15
EP2721305A1 (en) 2014-04-23
FR2976633B1 (en) 2015-01-09
FR2976633A1 (en) 2012-12-21
CA2838686A1 (en) 2012-12-27
JP2014517217A (en) 2014-07-17
RU2596691C2 (en) 2016-09-10
JP6261498B2 (en) 2018-01-17
CN103635698B (en) 2017-06-13
IN2014DN00118A (en) 2015-05-22
WO2012175855A1 (en) 2012-12-27
KR101946084B1 (en) 2019-02-08
PL2721305T3 (en) 2021-07-12
CA2838686C (en) 2019-09-17
CN103635698A (en) 2014-03-12
KR20140047653A (en) 2014-04-22
RU2013156047A (en) 2015-07-27

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