EP2721305A1 - 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

Info

Publication number
EP2721305A1
EP2721305A1 EP12734964.5A EP12734964A EP2721305A1 EP 2721305 A1 EP2721305 A1 EP 2721305A1 EP 12734964 A EP12734964 A EP 12734964A EP 2721305 A1 EP2721305 A1 EP 2721305A1
Authority
EP
European Patent Office
Prior art keywords
flanges
blades
diffusion
flow
stage
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
EP12734964.5A
Other languages
German (de)
French (fr)
Other versions
EP2721305B1 (en
Inventor
Laurent Tarnowski
Nicolas BULOT
Jérôme PORODO
Current Assignee (The listed assignees may be inaccurate. Google has not performed a legal analysis and makes no representation or warranty as to the accuracy of the list.)
Safran Helicopter Engines SAS
Original Assignee
Turbomeca SA
Priority date (The priority date is an assumption and is not a legal conclusion. Google has not performed a legal analysis and makes no representation as to the accuracy of the date listed.)
Filing date
Publication date
Application filed by Turbomeca SA filed Critical Turbomeca SA
Priority to PL12734964T priority Critical patent/PL2721305T3/en
Publication of EP2721305A1 publication Critical patent/EP2721305A1/en
Application granted granted Critical
Publication of EP2721305B1 publication Critical patent/EP2721305B1/en
Active legal-status Critical Current
Anticipated expiration legal-status Critical

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Classifications

    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F04—POSITIVE - DISPLACEMENT MACHINES FOR LIQUIDS; PUMPS FOR LIQUIDS OR ELASTIC FLUIDS
    • F04D—NON-POSITIVE-DISPLACEMENT PUMPS
    • F04D29/00—Details, component parts, or accessories
    • F04D29/40—Casings; Connections of working fluid
    • F04D29/42—Casings; Connections of working fluid for radial or helico-centrifugal pumps
    • F04D29/44—Fluid-guiding means, e.g. diffusers
    • F04D29/441—Fluid-guiding means, e.g. diffusers especially adapted for elastic fluid pumps
    • 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
    • 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 method of diffusing the air flow in a compression stage of a gas turbine, and a diffusion stage capable of implementing this method.
  • the field of the invention relates to the improvement of the performance and margin pumping of centrifugal and mixed compressors on the diffusion assembly of the stage concerned.
  • This diffusion assembly has the function of transforming 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 compressor stability level 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 able to achieve a flow of air perpendicular to the central axis of the compressor.
  • a mixed compressor has at least one compression stage inclined with respect to said central axis.
  • a diffusion assembly of a compression stage is composed of a wheel formed of two flanges between which flows the fluid centrifugally or inclined from the center to the periphery. Blades are distributed between the flanges all along the wheel. These vanes form a flow grid between the leading edges of these centrally-side blades and the trailing edges of the outer side.
  • the flanges of the radial and mixed diffusion sets are traditionally planar and the fluid passage sections between the vanes are advantageously evolutive.
  • the evolutions of the passage sections are defined by the passage section at the neck of the diffuser and the level of slowing between the leading and trailing edges of the blade grid. .
  • the invention aims to achieve such a flow by the establishment of shaped flasks optimized because these flanges represent the largest area "wet" by the flow.
  • Non-axisymmetric shapes in the direction of flow and tangentially are thus proposed.
  • the present invention relates to a method of diffusing the air flow in a compression stage of a gas turbine comprising a diffusion assembly composed of a wheel formed of two flanges between which flows the fluid centrifugally or inclined from the center to the periphery. Blades of a grid are distributed between the flanges along the wheel to channel the flow of fluid between the leading edges of these blades on the center side and the trailing edges on the periphery side.
  • at least one of the flanges has at least one alternation of concave and convex curvatures in at least one of two substantially perpendicular directions, namely in the flow direction along the blades and in a tangential internal direction. blades.
  • the three-dimensional shape of the vein of the fluid makes it possible to redistribute and homogenize its flow in this vein: the secondary flows, generating losses, are substantially reduced.
  • the position of shocks in transonic blading is modified and their weakened intensity.
  • the aerodynamic blocking input of the combustion chamber following the compression stage is also substantially reduced.
  • the invention also relates to a radial or mixed gas turbine compressor diffusion stage capable of implementing this method.
  • a stage comprises a wheel formed of two flanges between which the fluid flows centrifugally or inclined from the center to the periphery. Blades of a grid are distributed between the flanges all along the wheel and to channel the flow of fluid between the leading edges of these blades on the center side and the trailing edges on the periphery side.
  • At least one of the flanges has an inner face having at least one zone with alternating curvatures hollow and hump between two adjacent blades, in at least one of two substantially perpendicular directions, namely in the direction of flow along the blades and in a tangential inter-blade direction.
  • the diffusion stage has alternating recessed and hump zones between the vanes, in particular up to substantially 80% (preferably up to substantially 50%) of a cord. a blade, at the leading edge of the blades, with a beginning upstream of the leading edge, and / or at the trailing edge, downstream of the trailing edge.
  • These alternating zones of hollow and hump 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.
  • FIGS. 3a to 3c schematic views of profiles of a flange in the direction of flow of air along a blade, with two zones with alternating curvature respectively along the blade, on the edge of flight to dawn downstream, and to the leading edge from upstream of dawn;
  • FIG. 5 is a diagrammatic inter-blade perspective view at the leading edge with a flange having a zone with alternating curvature
  • FIG. 6 a schematic perspective view at the trailing edge of two blades with a flat flange and a flange having a zone with alternating curvature.
  • downstream and upstream qualify positioning 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 drawn into a fresh air inlet sleeve 2, then compressed between the blades 3 of a centrifugal compressor wheel 4 and a cover 10.
  • the turbine is of axial symmetry about an axis X'X.
  • the compressor 5 is here centrifugal and the compressed flow F then comes out radially from the wheel 4.
  • the stream exits inclined at an angle between 0 ° and 90 ° relative to a radial direction, perpendicular to the X'X axis.
  • the flow F then passes through a diffuser or wheel 6, disposed at the outlet of the compressor 4, to be straightened and conveyed to inlet channels 7 of a combustion chamber 8.
  • the wheel 6 consists of a plurality of curved vanes 60, arranged between two flanges 9 at the periphery of the wheel 4 - here radially - and therefore of revolution around the X axis 'X.
  • Figure 2b illustrates more precisely in perspective view the diffuser 6 with vanes 60 secured to two flanges 9.
  • each blade 60 has, in known manner, a face called extrados 6th and a so-called intrados face 6i. In the illustrated example, 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.
  • each blade 60 has plane flanks 6p secured to the flanges 9.
  • the flanges 9 of Figures 2a and 2b are classically planar. According to the invention, at least one of these flanges 9 have, in the space E which they define between them, at least one zone with 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, of the entry at the leading edge 6a of the dawn to channel 7 outlet to the combustion chamber.
  • Two zones with alternating curvature Z1 and Z2 are formed in the flange 9, along the blades 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 bump portion 92.
  • the zones Z1 and Z2 extend globally, in the example shown without limitation, about 80% of the length of the rope 6c of the vanes 60.
  • the flange 9 has in the figures a filamentary thickness to simplify the presentation, but it actually has a certain thickness and the alternately curved zones are formed on the inner face 9i of the flange where flows the air flow F.
  • the outer face 9e of the flange 9 may remain flat or marry alternately curved shapes alternately bump and hollow, inverted in this example with respect to the hollow forms and bump 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 make the areas of alternating curvature: by milling, laser, spark erosion, forming, stamping, etc.
  • the two zones with alternating curvature Z1 and Z2 are respectively formed at the trailing edge 6f of the vanes 60 and downstream blades in the inlet of the channel 7, and / or at the leading edge 6a from the upstream inlet of the blades 60.
  • FIG. 4 illustrates a partial schematic view of the diffusion stage "in the tangential direction" 6t between vanes, that is to say between two vanes 60.
  • the arrow F indicates the direction of flow of the air.
  • the inner face 9i of the flange 9 has two zones with alternating curvature Z1 and Z2 which extend mainly between the intrados face 6i and extrados 6e two blades 60.
  • the perspective view inter-blades leading edge 6a of Figure 5 shows, more specifically, the flange 9 with a zone with alternating curvature Z1 between the two blades 60.
  • the zone has the recessed curved portion 91, at the intrados 6i of a blade 60, and the portion with curvature in the bump 92, at the upper surface 6e of the other blade 60.
  • This alternation of curvatures allows a balancing of the pressures between the intrados and the extrados of each blade 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 in Figure 6.
  • a flat flange 90 shown hatched in the figure
  • a blocking aerodynamic is created in the zone Z0 with a very small amount of movement.
  • the main air flow (arrow F) is high Mach number.
  • the aerodynamic blocking zone is eliminated and the flow of air F is homogenized 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 flow direction of the fluid F but also in the tangential direction 6t.
  • the alternating curvature zones can be juxtaposed so that surface portions of the same curvature, hollow or hump, can be side by side.

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

Abstract

The aim of the invention is to produce an airflow by positioning flanges, the shapes of which are optimized. Non-axisymmetrical shapes in the direction of flow and in the tangential direction are thus provided. According to one embodiment, a radial or mixed gas turbine compressor diffusion stage comprises a wheel consisting of two flanges (9) between which the fluid centrifugally or inclinedly flows from the center towards the periphery. Vanes (60) of a grating are distributed among the flanges (9) in order to channel the flow of the fluid between the leading edges (6a) of said vanes (60) on the central side, and the trailing edges on the peripheral side. At least one of the flanges (9) has an inner surface (9i) comprising at least one area (Z1, Z2) having alternating concave (91) and convex (92) curvatures between two adjacent vanes (60), in at least one of two substantially perpendicular directions, namely in the direction of flow (F) along the vanes (60) and in an inter-vane tangential direction.

Description

PROCÉDÉ DE DIFFUSION D'UN ÉTAGE DE COMPRESSION D'UNE TURBINE A GAZ ET ÉTAGE DE DIFFUSION DE MISE EN OEUVRE  METHOD FOR DIFFUSING A COMPRESSION STAGE OF A GAS TURBINE AND DIFFUSION STAGE USING THE SAME
DESCRIPTION DESCRIPTION
DOMAINE TECHNIQUE TECHNICAL AREA
[0001] L'invention se rapporte à un procédé de diffusion de l'écoulement d'air dans un étage de compression d'une turbine à gaz, ainsi qu'à un étage de diffusion apte à mettre en œuvre ce procédé.  The invention relates to a method of diffusing the air flow in a compression stage of a gas turbine, and a diffusion stage capable of implementing this method.
[0002] 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 the improvement of the performance and margin pumping of centrifugal and mixed compressors on the diffusion assembly of the stage concerned. This diffusion assembly has the function of transforming 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 compressor stability level in order to maintain an acceptable pumping margin for the operation of the turbomachine.
[0003] 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 able to achieve a flow of air perpendicular to the central axis of the compressor. A mixed compressor has at least one compression stage inclined with respect to said central axis.
[0004] 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 of a compression stage is composed of a wheel formed of two flanges between which flows the fluid centrifugally or inclined from the center to the periphery. Blades are distributed between the flanges all along the wheel. These vanes form a flow grid between the leading edges of these centrally-side blades and the trailing edges of the outer side.
ÉTAT DE LA TECHNIQUE STATE OF THE ART
[0005] 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 sets are traditionally planar and the fluid passage sections between the vanes are advantageously evolutive. The evolutions of the passage sections are defined by the passage section at the neck of the diffuser and the level of slowing between the leading and trailing edges of the blade grid. .
[0006] 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.  Other architectures provide axisymmetric flanges in connection with evolutive veins for additional control of the passage section and thus optimize the diffusion in the grid.
[0007] 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 allow a control in one dimension, that of the variation of the passage section. No control of the tangential heterogeneity of the fluid flow between two blades is achieved. This control makes it possible to regulate and optimize the flow.
EXPOSÉ DE L'INVENTION STATEMENT OF THE INVENTION
[0008] 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 invention aims to achieve such a flow by the establishment of shaped flasks optimized because these flanges represent the largest area "wet" by the flow. Non-axisymmetric shapes in the direction of flow and tangentially are thus proposed.
[0009] Plus précisément, la présente invention a pour objet un procédé de diffusion de l'écoulement d'air dans un étage de compression d'une turbine à gaz comportant un ensemble de diffusion 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 d'une grille sont réparties entre les flasques tout le long de la roue pour canaliser l'écoulement du fluide entre les bords d'attaque de ces aubes du côté du centre et les bords de fuite du côté de la périphérie. Dans ce procédé, au moins l'un des flasques présente au moins une alternance de courbures concave et convexe dans au moins une parmi deux directions sensiblement perpendiculaires, à savoir dans le sens d'écoulement le long des aubes et dans une direction tangentielle inter-aubes.  More specifically, the present invention relates to a method of diffusing the air flow in a compression stage of a gas turbine comprising a diffusion assembly composed of a wheel formed of two flanges between which flows the fluid centrifugally or inclined from the center to the periphery. Blades of a grid are distributed between the flanges along the wheel to channel the flow of fluid between the leading edges of these blades on the center side and the trailing edges on the periphery side. In this method, at least one of the flanges has at least one alternation of concave and convex curvatures in at least one of two substantially perpendicular directions, namely in the flow direction along the blades and in a tangential internal direction. blades.
[0010] Dan ces conditions, 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 these conditions, the three-dimensional shape of the vein of the fluid makes it possible to redistribute and homogenize its flow in this vein: the secondary flows, generating losses, are substantially reduced. The position of shocks in transonic blading is modified and their weakened intensity. In addition, the aerodynamic blocking input of the combustion chamber following the compression stage is also substantially reduced.
[0011] L'invention se rapporte également à un étage de diffusion de compresseur radial ou mixte de turbine à gaz apte à mettre en œuvre ce procédé. Un tel étage comporte 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 d'une grille sont réparties entre les flasques tout le long de la roue et pour canaliser l'écoulement du fluide entre les bords d'attaque de ces aubes du côté du centre et les bords de fuite du côté de la périphérie. Au moins l'un des flasques présente une face interne comportant au moins une zone à courbures alternées en creux et de bosse entre deux aubes adjacentes, dans au moins une parmi deux directions sensiblement perpendiculaires, à savoir dans le sens d'écoulement le long des aubes et dans une direction tangentielle inter-aubes.  The invention also relates to a radial or mixed gas turbine compressor diffusion stage capable of implementing this method. Such a stage comprises a wheel formed of two flanges between which the fluid flows centrifugally or inclined from the center to the periphery. Blades of a grid are distributed between the flanges all along the wheel and to channel the flow of fluid between the leading edges of these blades on the center side and the trailing edges on the periphery side. At least one of the flanges has an inner face having at least one zone with alternating curvatures hollow and hump between two adjacent blades, in at least one of two substantially perpendicular directions, namely in the direction of flow along the blades and in a tangential inter-blade direction.
[0012]Selon des particularités avantageuses, 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 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 advantageous features, the diffusion stage has alternating recessed and hump zones between the vanes, in particular up to substantially 80% (preferably up to substantially 50%) of a cord. a blade, at the leading edge of the blades, with a beginning upstream of the leading edge, and / or at the trailing edge, downstream of the trailing edge. These alternating zones of hollow and hump 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 FIGURES PRESENTATION OF FIGURES
[0013] 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 :  Other data, characteristics and advantages of the present invention will appear on reading the following nonlimited description, with reference to the appended figures which represent, respectively:
- la figure 1 , une vue en coupe partielle d'une turbine à gaz comportant un diffuseur d'air ;  - Figure 1, a partial sectional view of a gas turbine having an air diffuser;
- 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 ; - Figures 2a and 2b, perspective views of a vane diffusion stage having one and two flanges; FIGS. 3a to 3c, schematic views of profiles of a flange in the direction of flow of air along a blade, with two zones with alternating curvature respectively along the blade, on the edge of flight to dawn downstream, and to the leading edge from upstream of dawn;
- la figure 4, une vue schématique partielle dans la direction tangentielle inter-aubes, avec un flasque présentant deux zones à courbure alternée ;  - Figure 4, a partial schematic view in the inter-blade tangential direction, with a flange having two zones with alternating curvature;
- la figure 5, une vue schématique inter-aubes perspective en bord d'attaque avec un flasque présentant une zone à courbure alternée ; et  FIG. 5 is a diagrammatic inter-blade perspective view at the leading edge with a flange having a zone with alternating curvature; and
- 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.  - Figure 6, a schematic perspective view at the trailing edge of two blades with a flat flange and a flange having a zone with alternating curvature.
DESCRIPTION DÉTAILLÉE DETAILED DESCRIPTION
[0014] 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 positioning 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.
[0015] 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.  Referring to the schematic partial sectional view of a helicopter gas turbine 1 according to Figure 1, an air flow F is first drawn into a fresh air inlet sleeve 2, then compressed between the blades 3 of a centrifugal compressor wheel 4 and a cover 10. The turbine is of axial symmetry about an axis X'X.
[0016] 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 comes out radially from the wheel 4. When the compressor is mixed, the stream exits inclined at an angle between 0 ° and 90 ° relative to a radial direction, perpendicular to the X'X axis.
[0017] 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, disposed at the outlet of the compressor 4, to be straightened and conveyed to inlet channels 7 of a combustion chamber 8.
[0018] 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. [0019] 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. To perform this rectification, the wheel 6 consists of a plurality of curved vanes 60, arranged between two flanges 9 at the periphery of the wheel 4 - here radially - and therefore of revolution around the X axis 'X. Figure 2b illustrates more precisely in perspective view the diffuser 6 with vanes 60 secured to two flanges 9. In Figure 2a, where a flange has been removed for clarity, each blade 60 has, in known manner, a face called extrados 6th and a so-called intrados face 6i. In the illustrated example, 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. Transversally to the extrados and intrados, each blade 60 has plane flanks 6p secured to the flanges 9.
[0020] 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 planar. According to the invention, at least one of these flanges 9 have, in the space E which they define between them, at least one zone with alternating curvature between two blades 60.
[0021] 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 FIG. 3a, such a flange 9 is illustrated in profile, in the direction of flow of the air flow F along the vanes 60, of the entry at the leading edge 6a of the dawn to channel 7 outlet to the combustion chamber. Two zones with alternating curvature Z1 and Z2 are formed in the flange 9, along the blades 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 bump portion 92. The zones Z1 and Z2 extend globally, in the example shown without limitation, about 80% of the length of the rope 6c of the vanes 60.
[0022] 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 filamentary thickness to simplify the presentation, but it actually has a certain thickness and the alternately curved zones are formed on the inner face 9i of the flange where flows the air flow F. The outer face 9e of the flange 9 may remain flat or marry alternately curved shapes alternately bump and hollow, inverted in this example with respect to the hollow forms and bump 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 make the areas of alternating curvature: by milling, laser, spark erosion, forming, stamping, etc.
[0023] 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/ou en bord d'attaque 6a à partir de l'entrée amont des aubes 60. In FIGS. 3b and 3c, the two zones with alternating curvature Z1 and Z2 are respectively formed at the trailing edge 6f of the vanes 60 and downstream blades in the inlet of the channel 7, and / or at the leading edge 6a from the upstream inlet of the blades 60.
[0024] 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.  FIG. 4 illustrates a partial schematic view of the diffusion stage "in the tangential direction" 6t between vanes, that is to say between two vanes 60. The arrow F indicates the direction of flow of the air. The inner face 9i of the flange 9 has two zones with alternating curvature Z1 and Z2 which extend mainly between the intrados face 6i and extrados 6e two blades 60.
[0025] 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 perspective view inter-blades leading edge 6a of Figure 5 shows, more specifically, the flange 9 with a zone with alternating curvature Z1 between the two blades 60. The zone has the recessed curved portion 91, at the intrados 6i of a blade 60, and the portion with curvature in the bump 92, at the upper surface 6e of the other blade 60. This alternation of curvatures allows a balancing of the pressures between the intrados and the extrados of each blade 60. The section at the neck 6s between the leading edges 6a is retained.
[0026]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 in Figure 6. With a flat flange 90 (shown hatched in the figure) between two vanes 60, a blocking aerodynamic is created in the zone Z0 with a very small amount of movement. In this configuration of the state of the art, the main air flow (arrow F) is 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 occupying the entire passage section offered, with a lower Mach number.
[0027] 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 illustrated examples, the curvatures are alternated in the flow direction of the fluid F but also in the tangential direction 6t. In other variants, the alternating curvature zones can be juxtaposed so that surface portions of the same curvature, hollow or hump, can be side by side.

Claims

REVENDICATIONS
1 . Procédé de diffusion de l'écoulement d'air (F) dans un étage de compression (5) d'une turbine à gaz (1 ) comportant un ensemble de diffusion composé d'une roue (6) formée de deux flasques (9) entre lesquelles s'écoule le fluide de manière centrifuge ou inclinée à partir du centre vers la périphérie, des aubes (60) d'une grille étant réparties entre les flasques (9) tout le long de la roue (6) pour canaliser l'écoulement du fluide entre les bords d'attaque (6a) de ces aubes (6) du côté du centre et les bords de fuite (6f) du côté de la périphérie, caractérisé en ce qu'au moins l'un des flasques (9) présente au moins une alternance de courbures concave (91 ) et convexe (92) dans le sens d'écoulement (F) le long des aubes (6). 1. Method for diffusing the air flow (F) in a compression stage (5) of a gas turbine (1) comprising a diffusion assembly composed of a wheel (6) formed of two flanges (9) between which flows the fluid centrifugally or inclined from the center to the periphery, vanes (60) of a grid being distributed between the flanges (9) all along the wheel (6) to channel the fluid flow between the leading edges (6a) of these centrally-facing blades (6) and the periphery-side trailing edges (6f), characterized in that at least one of the flanges (9) ) has at least one alternating concave (91) and convex (92) curvatures in the flow direction (F) along the vanes (6).
2. Procédé de diffusion de l'écoulement d'air (F) selon la revendication 1 , dans lequel au moins l'un des flasques (9) présente également au moins une alternance de courbures concave (91 ) et convexe (92) dans une direction tangentielle (6t) inter-aubes sensiblement perpendiculaires au sens d'écoulement (F) le long des aubes (6).  The method of diffusing the air flow (F) according to claim 1, wherein at least one of the flanges (9) also has at least one alternating concave (91) and convex (92) curvatures in a tangential direction (6t) between vanes substantially perpendicular to the direction of flow (F) along the vanes (6).
3. Étage de diffusion de compresseur radial ou mixte de turbine à gaz apte à mettre en œuvre le procédé selon la revendication 1 , comportant une roue (6) formée de deux flasques (9) entre lesquelles s'écoule le fluide de manière centrifuge ou inclinée à partir du centre vers la périphérie, des aubes (60) d'une grille étant réparties entre les flasques (9) tout le long de la roue (6) pour canaliser l'écoulement du fluide entre les bords d'attaque (6a) de ces aubes (60) du côté du centre et les bords de fuite (6f) du côté de la périphérie, caractérisé en ce qu'au moins l'un des flasques (9) présente une face interne (9i) comportant au moins une zone (Z1 , Z2) à courbures alternées en creux (91 ) et en bosse (92) entre deux aubes adjacentes (60).  3. Stage of diffusion of radial or mixed gas turbine compressor capable of implementing the method according to claim 1, comprising a wheel (6) formed of two flanges (9) between which the fluid flows centrifugally or inclined from the center to the periphery, blades (60) of a grid being distributed between the flanges (9) all along the wheel (6) to channel the flow of fluid between the leading edges (6a ) of these blades (60) on the central side and the trailing edges (6f) on the periphery side, characterized in that at least one of the flanges (9) has an internal face (9i) comprising at least a zone (Z1, Z2) with alternating recesses (91) and bumps (92) between two adjacent blades (60).
4. Étage de diffusion de compresseur radial ou mixte de turbine à gaz selon la revendication 3, dans lequel au moins l'un des flasques (9) présente une face interne (9i) comportant également au moins une zone (Z1 , Z2) à courbures alternées en creux (91 ) et en bosse (92) entre deux aubes adjacentes (60) dans une direction tangentielle inter-aubes (6t). 4. Radial or mixed gas turbine compressor diffusion stage according to claim 3, wherein at least one of the flanges (9) has an inner face (9i) also comprising at least one zone (Z1, Z2) to alternating hollow (91) and bump (92) curves between two adjacent blades (60) in a tangential inter-blade direction (6t).
5. Étage de diffusion selon la revendication 3 ou 4, caractérisé en ce qu'il présente des zones (Z1 , Z2) alternées en creux (91 ) et en bosse (92) entre les aubes, en particulier jusqu'à sensiblement 80 %, de préférence jusqu'à sensiblement 50%, d'une corde (6c) d'une aube (60). 5. diffusion stage according to claim 3 or 4, characterized in that it has zones (Z1, Z2) alternately recessed (91) and bump (92) between the blades, in particular up to substantially 80% , preferably up to substantially 50%, of a rope (6c) of a blade (60).
6. Étage de diffusion en bord d'attaque des aubes selon l'une des revendications 4 à 5, caractérisé en ce qu'il présente des zones de creux et de bosse (Z1 , Z2) en bord d'attaque (6a) des aubes (60), avec un début en amont du bord d'attaque (6a).  6. Edge diffusion stage of the blades according to one of claims 4 to 5, characterized in that it has zones of hollow and hump (Z1, Z2) leading edge (6a) of blades (60), with a beginning upstream of the leading edge (6a).
7. Étage de diffusion en bord d'attaque des aubes selon l'une des revendications 4 à 6, caractérisé en ce qu'il présente des zones de creux et de bosse (Z1 , Z2) en bord de fuite (6f) des aubes (60), jusqu'en aval du bord de fuite (6f).  7. diffusion stage in the leading edge of the blades according to one of claims 4 to 6, characterized in that it has areas of hollow and hump (Z1, Z2) trailing edge (6f) of the blades (60), downstream of the trailing edge (6f).
8. Étage de diffusion en bord d'attaque des aubes selon l'une des revendications 4 à 7, dans lequel ces zones alternées de creux et de bosse (Z1 , Z2) s'appliquent sur l'un et/ou l'autre des deux flasques (9) de diffusion centrifuges et mixtes.  8. Edge diffusion stage blades according to one of claims 4 to 7, wherein these alternating zones of hollow and hump (Z1, Z2) apply to one and / or the other two centrifugal and mixed diffusion flasks (9).
9. Étage de diffusion selon la revendication précédente, dans lequel ces zones alternées (Z1 , Z2) s'appliquent sur les flasques (9) de manière symétrique par rapport à un plan de symétrie central des flasques (9)ou de manière parallèle.  9. diffusion stage according to the preceding claim, wherein these alternating zones (Z1, Z2) are applied to the flanges (9) symmetrically with respect to a central plane of symmetry of the flanges (9) or in 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)

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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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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

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US6123506A (en) * 1999-01-20 2000-09-26 Pratt & Whitney Canada Corp. Diffuser pipe assembly
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GB0223756D0 (en) * 2002-10-14 2002-11-20 Holset Engineering Co Compressor
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FR2976633B1 (en) 2015-01-09
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CN103635698A (en) 2014-03-12
CN103635698B (en) 2017-06-13
JP6261498B2 (en) 2018-01-17
KR20140047653A (en) 2014-04-22
EP2721305B1 (en) 2021-02-24
IN2014DN00118A (en) 2015-05-22
US20140133957A1 (en) 2014-05-15
FR2976633A1 (en) 2012-12-21
JP2014517217A (en) 2014-07-17
CA2838686C (en) 2019-09-17
CA2838686A1 (en) 2012-12-27
KR101946084B1 (en) 2019-02-08
PL2721305T3 (en) 2021-07-12

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