EP2558728A1 - Method for adapting the air flow of a turbine engine having a centrifugal compressor and diffuser for implementing same - Google Patents

Method for adapting the air flow of a turbine engine having a centrifugal compressor and diffuser for implementing same

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Publication number
EP2558728A1
EP2558728A1 EP11730371A EP11730371A EP2558728A1 EP 2558728 A1 EP2558728 A1 EP 2558728A1 EP 11730371 A EP11730371 A EP 11730371A EP 11730371 A EP11730371 A EP 11730371A EP 2558728 A1 EP2558728 A1 EP 2558728A1
Authority
EP
European Patent Office
Prior art keywords
blades
blade
variable
pitch
diffuser
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
EP11730371A
Other languages
German (de)
French (fr)
Other versions
EP2558728B2 (en
EP2558728B1 (en
Inventor
Pierre Biscay
Patrick Marconi
Hubert Hippolyte Vignau
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
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Application filed by Turbomeca SA filed Critical Turbomeca SA
Priority to PL11730371.9T priority Critical patent/PL2558728T5/en
Publication of EP2558728A1 publication Critical patent/EP2558728A1/en
Application granted granted Critical
Publication of EP2558728B1 publication Critical patent/EP2558728B1/en
Publication of EP2558728B2 publication Critical patent/EP2558728B2/en
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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
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F04—POSITIVE - DISPLACEMENT MACHINES FOR LIQUIDS; PUMPS FOR LIQUIDS OR ELASTIC FLUIDS
    • F04D—NON-POSITIVE-DISPLACEMENT PUMPS
    • F04D29/00—Details, component parts, or accessories
    • F04D29/40—Casings; Connections of working fluid
    • F04D29/42—Casings; Connections of working fluid for radial or helico-centrifugal pumps
    • F04D29/44—Fluid-guiding means, e.g. diffusers
    • F04D29/441—Fluid-guiding means, e.g. diffusers especially adapted for elastic fluid pumps
    • F04D29/444—Bladed diffusers
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F04—POSITIVE - DISPLACEMENT MACHINES FOR LIQUIDS; PUMPS FOR LIQUIDS OR ELASTIC FLUIDS
    • F04D—NON-POSITIVE-DISPLACEMENT PUMPS
    • F04D29/00—Details, component parts, or accessories
    • F04D29/40—Casings; Connections of working fluid
    • F04D29/42—Casings; Connections of working fluid for radial or helico-centrifugal pumps
    • F04D29/44—Fluid-guiding means, e.g. diffusers
    • F04D29/46—Fluid-guiding means, e.g. diffusers adjustable
    • 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
    • F04D29/46—Fluid-guiding means, e.g. diffusers adjustable
    • F04D29/462—Fluid-guiding means, e.g. diffusers adjustable 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
    • F05D2250/00—Geometry
    • F05D2250/50—Inlet or outlet
    • F05D2250/52—Outlet

Definitions

  • the invention relates to a method of adapting the air flow rate of a turbomachine comprising a centrifugal compressor, in particular helicopter turbine engines or auxiliary power units (abbreviated as APU) to a request variable flow or mechanical or electrical power.
  • the invention also relates to a diffuser equipped with variable pitch blades capable of implementing this method.
  • the field of the invention is the compression of gases in turbomachinery engines and, more particularly, the adaptation of the compressed air flow to respect the performance of the engines, whether turboshaft engines or APUs, particular its specific consumption (abbreviated Cs) at partial load.
  • a general problem is to meet the needs of pumping margin and to offset compression rate reductions at the intermediate speeds of the turboshaft engines, as well as variations in demand for compressed air flow and power. in the case of APUs.
  • IGV inlet guide vanes
  • variable setting is achieved by appropriate commands in connection with a control unit according to the physical parameters involved (rotational speed, pressures, temperatures).
  • rotational speed, pressures, temperatures the ranges of wedges that the control system must cover require a control cylinder of high power, cause significant variations in the inlet and outlet diameters of the diffuser, which can generate high mechanical stresses between rotating parts (wheel) and static (radial variable valve) and decreases the efficiency at partial load (intermediate regime).
  • the invention aims to overcome these disadvantages, in particular by maintaining the efficiency of the compressor to substantially reduce the Cs while ensuring a sufficient pumping margin with a better efficiency of the engine cycle at partial load. To do this, it proposes an optimized method of variable diffusion of the air flow in a centrifugal compressor of turbomachines.
  • the subject of the invention is a method for diffusing variable airflow in a centrifugal compressor of turbomachine engines, consisting in providing a diffusion of air through a first annular grid of paddle blades. variable radially bordered by a second annular grid of same number of fixed-pitch blades of equivalent extension, directing the diffusion in the radial direction by coupling the blades of the two blades, each blade of the first blade being rotated away from the blade.
  • Turbomachines should be understood as turbine engines, in particular helicopter turboshaft engines with a single-stage or two-stage centrifugal compressor, and APUs equipped with a centrifugal compressor of single or two-stage power.
  • the radial extension of the variable pitch blades is substantially reduced by the presence of the fixed blade comprising true blades, which limits the efforts to vary their rigging and the clearance between the mobile blade and the support flange and thus the upstream / downstream recirculation, which has the effect of reducing deterioration of the pumping line and pressure losses.
  • the decentralized implantation of the axis of rotation of the variable-pitch blades substantially reduces the variations in radial extension of these iso-diffusion blades: the increase in closing is less, thus favoring the efficiency, partial load and decreasing opening less also, which limits the mechanical stresses due to unsteady aerodynamic fluctuations by wheel / diffuser interaction.
  • the method applying to turbomachines equipped with a power turbine, the variable-pitch radial diffusion on a centrifugal compressor, as defined above, is coupled to a wedge power turbine distributor.
  • variable. Power production can be carried out according to several configurations: free power turbine - or linked, of axial or centripetal type, with or without downstream heat exchange.
  • the coupling between the diffuser and the variable valve distributor makes it possible to adapt the operating line to the flow reduction, which improves the efficiency of the engine cycle (by a better pressure ratio) and therefore the Cs of the turboshaft engines. helicopters and APUs.
  • the invention also relates to a turbomachine variable valve diffuser capable of implementing the method defined above, and the turbomachine equipped with such a diffuser.
  • the diffuser comprises a first annular grid of variable pitch blades radially bordered by a second annular grid of fixed pitch blades of equivalent extension, forming successive diffusion channels by coupling the blades of the two grids in radial extension.
  • each blade of the first gate is driven by control means capable of exerting a proper rotation of each blade off-center with respect to its axis of rotation.
  • each variable-pitch blade extends between two cups opposite and parallel and off-center with respect to the common axis of the cups coinciding with the axis of rotation;
  • each blade is coupled to a drive rod which has at least one orifice in which is introduced a locking pin of a washer for adjusting the axial position of the cups;
  • the rod is secured to a lever having a spherical ball received in a cylindrical housing (38) of a control ring adapted to drive in rotation about the motor axis the lever adapted to slide in the cylindrical housing;
  • the cylindrical housing has a depth which is a function of the stroke of the levers, itself a function of the predetermined rotation interval of the blades; the leading edge of each variable-pitch blade is close to the peripheries of the cups, the distance from the blade to the axis of rotation being greater than or equal to half a radius;
  • the diffuser upstream is a smooth diffuser, that is to say, not aubé; the inlet air duct of the diffuser located between the impeller and the variable-pitch grille is convergent, which improves the performances;
  • the fixed blades of the second grid have a thicker leading edge profile than those of the first grid in order to absorb the variations of incidence; the blades with fixed wedging have a thickness sufficient to be traversed by screws allowing the passage of structural forces;
  • the fixed blades have an evolutionary law of skeleton angle between the leading and trailing edges, which makes it possible to control the diffusion in the fixed grid and to optimize its aerodynamic efficiency;
  • the fixed blades are wedged in azimuth with respect to the blades of the first movable grid so as to resume the wake on the extrados of the blades of this first gate to limit the pressure drops of the diffuser;
  • the pitch angles of the variable blades are between +12 and - 5 ° compared to the nominal setting, which would be that of a fixed diffuser.
  • FIG. 3 an overall frontal view of the upstream annular flange of the diffuser equipped with the blade grids according to the invention
  • FIGS. 4a to 4c a partial schematic view in the diffuser for three wedges of movable blades, the two extreme shims. around the nominal setting, and
  • upstream and downstream refer to the direction of flow of the air flow in a turbine engine.
  • the centrifugal compressor 10 of a turbomachine such as a turbine engine, turbojet engine, turboprop engine or an APU, comprises a casing 12 coupled to a covering cover 14.
  • radial wheel 16 last centrifugal stage of the compressor, rotatably mounted on the drive shaft 18 along the axis ⁇ .
  • the flow of air F flows from the impeller 16 to the annular diffuser 19, in a converging inlet vein by radial shrinkage.
  • the diffuser 19 is defined between two upstream and downstream flanges 20 and 22.
  • the cover 14 is held by a fastener 23 fixed to the casing and to the upstream flange 20.
  • the blades 24, forming a first annular grid are mounted in the diffuser 19.
  • the cups are centered in the flanges 20 and 22 with appropriate clearances, from 0.03 to 0.05 mm in the example illustrated, on a washer 9 inserted in the centering 25 (see below with reference to FIG. ).
  • Blades 28 secured to the flange 22, forming a second annular grid externally bordering the first gate are mounted on the annular flange 20 by through screws 29 housed in holes 29t. These screws also allow the passage of structural forces.
  • the control of the variable blades 24 is performed by means of rods 30 integrally extending the upstream cup 17.
  • rods 30 X'X axis are mounted in a cylindrical bore 32 of the upstream flange 20 and centered with a set almost zero by 30j joints mounted in grooves 30g.
  • each rod 30 has a flat portion 31 articulated on a drive lever 33 clamped by two screws 35 on this flat portion 31.
  • the positions of the ends 31 of the rods 30 are adjusted with appropriate play tolerances.
  • the rod 30 also has a hole 30t in which a pin 36 is inserted which makes it possible to lock a washer 30u - for adjusting the axial position of the cups 17 and 27 - in a locking ring 12a formed in the casing 12.
  • the pin 36 secures the rod 30 and the locking ring 12a.
  • the lever 33 is driven by a control ring 34 forming a cylindrical hole 38 for housing the spherical ball 37 of the lever 33 with an adapted axial position tolerance and a contact on a generatrix of the ball joint.
  • the control ring 34 is centered on sectors having needle bearings 39.
  • the control ring 34 rotated about the motor axis ⁇ by a rod (not shown), rotates the levers 33 which slide in the cylindrical housing 38 through their ball joint 37.
  • the depth of the housing 38 is a function of the stroke of the levers 33, itself a function of the rotation interval of the blades 24.
  • This architecture is particularly suitable for rotation blades up to + 12 ° with a 50% section closure, and up to -5 ° with a 20% section opening.
  • a movable blade 24 is shown between the parallel cups 17, 27 and secured by welding 21 to them, so that the blade extends parallel to the axis X'X cups opposite.
  • the leading edge 24c of the blade 24 is flush with the outer circumferences 17c and 27c of the cups, the thickness of the blade 24 being relatively thin, 2 mm in the illustrated example.
  • the distance between the blade 24 and the axis X'X of the rod 30 is equal to about 80% of the radius of the cups in the illustrated example.
  • the rod 30 also has the cylindrical centering grooves 30g and the locking hole 30t of the adjusting washer of the axial position of the cups 17 and 27. Its flat portion 31 is traversed by holes 30a for receiving the mounting screws 35. to the control lever.
  • FIG. 3 illustrates the upstream annular flange 20 equipped with annular gates G1 and G2, mounted respectively mobile and fixed and composed of blades 24 and 28.
  • the blades 28 have a substantially thicker profile in the leading edge Ba than that of the blades 24, respectively 0.5 and 2.5 mm, to preserve a good resistance to variations in incidence during the rotation of the movable blades 24.
  • the skeleton angle law of the blades 28 between the leading edges BA and LF leakage is scalable, to optimize the aerodynamic efficiency of the fixed gate by a maximum recovery of static pressure.
  • the blades 28 of the fixed gate have a maximum thickness of 7 mm in the example shown, for fixing the flange 20 of the diffuser by screws housed in the holes 29t, while allowing the passage structural efforts.
  • the air flow F flows along a fixed blade 28 in radial extension of a movable blade 24 and between two adjacent blades of the same type, mobile or fixed. Thanks to the off-centering of the mobile blades 24 with respect to the axes of rotation X'X of their cups 17, the variations of the radial extensions formed by these movable blades 24 are limited compared to variations of extensions that should be made of centered blades. This limitation makes it possible to improve the performance of a centrifugal compressor: it makes it possible to move the operating line away from the pumping line, by shifting towards lower flow rates, and to raise this operating line close to the yield maxima. higher diets.
  • the radial extensions of the movable blades 24 with respect to the fixed blades 28 are illustrated by the diagrams of Figures 4a to 4c, which also appear, in dashed lines, the cups 17, 27 of the blades.
  • the nominal setting of 0 ° corresponds to a flow of the reference air flow F for which the adjustment of the mobile blades 24 with respect to the fixed blades 28 is adapted to stable intermediate speeds.
  • FIG. 4a illustrates the case of a closure of 25% associated with a setting of 6 °, the neck section then being 75% of the section Sb.
  • the calibration setting can also go down to -5 °.
  • FIG. 4c illustrates the case of an opening of 2.5 °, the section at the neck being then a relative value of 1 10%.
  • the fixed blades 28 are wedged in azimuth with respect to the blades 24 of the first movable gate G1 so as to resume the wake on the extrados Ex of the blades of this first gate G1.
  • the radial extensions of the blades 24, limited by the presence of the fixed blades 28, allow to maintain control games between the cups 17 and 27 of the blades 24 and the flanges 20 and 22, as shown in Figure 5.
  • the values of the clearances remain less than or equal to 0.02 mm (for J1 or J2), 0.10 mm (for J3) and 0.25 mm (for J4).
  • the clearance (set J1 and J2) of the blade 24 on the washer 9 remains about 0.03 mm or slightly higher.
  • the invention is not limited to the examples described and shown. It is for example possible to set the pitch of the mobile blades by only mechanical adjustment, individual or centralized, or by electrical, electronic control with or without digital control.

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

Abstract

The invention relates to a method for maintaining the efficiency and duty of a turbine engine compressor in order substantially to reduce the specific consumption Cs, while guaranteeing a high enough pumping margin with partial load. For this purpose, the invention proposes an optimised method for adapting the airflow to a variable demand for flow or mechanical or electric power in a centrifugal compressor of a turbine engine. The method includes diffusing the airflow (F) through a first annular blade ring (G1) having variable-pitch blades (24), radially bordered by a second annular blade ring (G2) having the same number of fixed-pitch blades (28) with an equivalent extension, guiding the radial extension diffusion by coupling the blades (24, 28) of the two blade rings. According to said method, each blade (24) of the first blade ring (G1) is spun off-axis.

Description

PROCÉDÉ D'ADAPTATION DE DEBIT D'AIR DE TURBOMACHINE A COMPRESSEUR CENTRIFUGE ET DIFFUSEUR DE MISE EN ŒUVRE  METHOD FOR ADJUSTING TURBOMACHINE AIR FLOW WITH CENTRIFUGAL COMPRESSOR AND DIFFUSER FOR IMPLEMENTING THE SAME
[0001] L'invention concerne un procédé d'adaptation du débit d'air d'une turbomachine comprenant un compresseur centrifuge, en particulier de moteurs de turbomoteur d'hélicoptères ou d'unités de puissance auxiliaires (en abrégé APU) à une demande variable de débit ou de puissance mécanique ou électrique. L'invention se rapporte également à un diffuseur équipé de pales à calage variable apte à mettre en œuvre ce procédé. [0002] Le domaine de l'invention est la compression des gaz dans les moteurs de turbomachines et, plus particulièrement, l'adaptation du flux d'air comprimé pour respecter les performances des moteurs, que ce soient des turbomoteurs ou des APU, en particulier sa consommation spécifique (en abrégé Cs) à charge partielle. [0003] Dans ce contexte, un problème général est de répondre aux besoins de marge au pompage et de pallier aux baisses de taux de compression aux régimes intermédiaires des turbomoteurs, ainsi qu'aux variations de demande de débit d'air comprimé et de puissance électrique dans le cas des APU. The invention relates to a method of adapting the air flow rate of a turbomachine comprising a centrifugal compressor, in particular helicopter turbine engines or auxiliary power units (abbreviated as APU) to a request variable flow or mechanical or electrical power. The invention also relates to a diffuser equipped with variable pitch blades capable of implementing this method. The field of the invention is the compression of gases in turbomachinery engines and, more particularly, the adaptation of the compressed air flow to respect the performance of the engines, whether turboshaft engines or APUs, particular its specific consumption (abbreviated Cs) at partial load. In this context, a general problem is to meet the needs of pumping margin and to offset compression rate reductions at the intermediate speeds of the turboshaft engines, as well as variations in demand for compressed air flow and power. in the case of APUs.
[0004] Il est connu qu'une marge au pompage suffisante peut être obtenue en abaissant la ligne de fonctionnement des turbomoteurs. Cependant, un abaissement du taux de cycle moteur entraîne une dégradation du rendement et cette solution nécessite alors de faire fonctionner le compresseur en-dessous de son rendement maximum, notamment à haut régime. It is known that a sufficient pumping margin can be obtained by lowering the operating line of the turboshaft engines. However, a lowering of the engine cycle rate leads to a degradation of the efficiency and this solution then requires operating the compressor below its maximum efficiency, especially at high speed.
[0005] Il est également connu d'introduire, à l'entrée du compresseur, une grille de pré-rotation, formée d'ailettes de guidage d'entrée (en abrégé IGV, initiales de « Inlet Guide Vanes » en langue anglaise). Mais, dans ce cas, le taux de compression est sensiblement abaissé pour un régime de rotation donné. [0006] Il convient dans ces conditions de chercher à faire fonctionner un compresseur avec un taux de compression quasi constant tout en restant près de son rendement maximum, quelle que soit la variation de la charge. It is also known to introduce, at the compressor inlet, a pre-rotation grid, formed of inlet guide vanes (abbreviated IGV, initials of "Inlet Guide Vanes" in English). . But in this case, the compression ratio is substantially lowered for a given rotational speed. It is appropriate in these conditions to seek to operate a compressor with a nearly constant compression ratio while remaining close to its maximum efficiency, regardless of the variation of the load.
[0007] Dans le domaine des compresseurs mono-étages, il existe des diffuseurs radiaux présentant des assemblages de pales à calage variable. De tels diffuseurs sont décrits par exemple dans les documents de brevet US 5 207 559 ou EP 0 589 745, ce dernier déposé au nom de la demanderesse. Ces diffuseurs permettent de décaler vers de plus faibles débits les caractéristiques des taux débit/pression du compresseur en régime intermédiaire, sans dégrader significativement le taux de compression ni le rendement. In the field of single-stage compressors, there are radial diffusers having blade assemblies variable pitch. Such diffusers are described for example in patent documents US 5 207 559 or EP 0 589 745, the latter filed in the name of the applicant. These diffusers make it possible to shift towards lower flow rates the characteristics of the flow / pressure rates of the compressor in intermediate mode, without significantly degrading the compression ratio or efficiency.
[0008] Le calage variable est réalisé par des commandes appropriées en liaison avec une unité de commande en fonction des paramètres physiques en jeu (régime de rotation, pressions, températures). Cependant les plages d'angles de calage que doit couvrir le système de commande nécessitent un vérin de commande d'une puissance élevée, entraînent des variations importantes des diamètres d'entrée et de sortie du diffuseur, ce qui peut générer des sollicitations mécaniques élevées entre parties tournantes (rouet) et statiques (diffuseur radial à calage variable) et diminue le rendement à charge partielle (régime intermédiaire). EXPOSE DE L'INVENTION The variable setting is achieved by appropriate commands in connection with a control unit according to the physical parameters involved (rotational speed, pressures, temperatures). However, the ranges of wedges that the control system must cover require a control cylinder of high power, cause significant variations in the inlet and outlet diameters of the diffuser, which can generate high mechanical stresses between rotating parts (wheel) and static (radial variable valve) and decreases the efficiency at partial load (intermediate regime). SUMMARY OF THE INVENTION
[0009] L'invention vise à pallier ces inconvénients, en particulier en maintenant le rendement du compresseur pour diminuer sensiblement la Cs tout en garantissant une marge au pompage suffisante avec un meilleur rendement du cycle moteur à charge partielle. Pour ce faire, elle propose un procédé optimisé de diffusion variable du flux d'air dans un compresseur centrifuge de turbomachines. The invention aims to overcome these disadvantages, in particular by maintaining the efficiency of the compressor to substantially reduce the Cs while ensuring a sufficient pumping margin with a better efficiency of the engine cycle at partial load. To do this, it proposes an optimized method of variable diffusion of the air flow in a centrifugal compressor of turbomachines.
[0010] Plus précisément, l'invention a pour objet un procédé de diffusion de flux d'air variable dans un compresseur centrifuge de moteurs de turbomachine, consistant à prévoir une diffusion de l'air à travers une première grille annulaire de pales à calage variable bordé radialement d'une deuxième grille annulaire de même nombre de pales à calage fixe d'extension équivalente, orientant la diffusion dans la direction radiale par couplage des pales des deux aubages, chaque pale du premier aubage étant entraînée en rotation à distance de la pale. Par turbomachines, il convient de comprendre les turbomoteurs, en particulier les turbomoteurs d'hélicoptères avec compresseur centrifuge mono-étage ou bi- étages, et les APU équipées de compresseur centrifuge de puissance mono- ou bi-étages. More specifically, the subject of the invention is a method for diffusing variable airflow in a centrifugal compressor of turbomachine engines, consisting in providing a diffusion of air through a first annular grid of paddle blades. variable radially bordered by a second annular grid of same number of fixed-pitch blades of equivalent extension, directing the diffusion in the radial direction by coupling the blades of the two blades, each blade of the first blade being rotated away from the blade. Turbomachines should be understood as turbine engines, in particular helicopter turboshaft engines with a single-stage or two-stage centrifugal compressor, and APUs equipped with a centrifugal compressor of single or two-stage power.
[0011] Dans ces conditions, d'une part, l'extension radiale des pales à calage variable est sensiblement diminuée par la présence de l'aubage fixe comprenant de véritables pales, ce qui permet de limiter les efforts pour faire varier leur calage ainsi que les jeux entre l'aubage mobile et le flasque support et donc les recirculations amont/aval, ce qui a pour effet de diminuer les détériorations de la ligne de pompage et les pertes de charge. D'autre part, l'implantation décentrée de l'axe de rotation des pales à calage variable réduit sensiblement les variations d'extension radiale de ces pales à iso-diffusion : l'augmentation à la fermeture est moindre, favorisant ainsi le rendement, à charge partielle et la diminution à l'ouverture moindre également, ce qui limite les sollicitations mécaniques du fait des fluctuations aérodynamiques instationnaires par interaction rouet / diffuseur. Under these conditions, on the one hand, the radial extension of the variable pitch blades is substantially reduced by the presence of the fixed blade comprising true blades, which limits the efforts to vary their rigging and the clearance between the mobile blade and the support flange and thus the upstream / downstream recirculation, which has the effect of reducing deterioration of the pumping line and pressure losses. On the other hand, the decentralized implantation of the axis of rotation of the variable-pitch blades substantially reduces the variations in radial extension of these iso-diffusion blades: the increase in closing is less, thus favoring the efficiency, partial load and decreasing opening less also, which limits the mechanical stresses due to unsteady aerodynamic fluctuations by wheel / diffuser interaction.
[0012] Une marge au pompage suffisante permet alors à la turbomachine de fonctionner sans apparition de pompage - offrant une grande capacité d'accélération -, et à l'APU de faire face à des variations de charge importantes, sans faire appel à une vanne de décharge, tout en maintenant la vitesse de rotation de la turbomachine et son taux de pression à des niveaux proches de leurs valeurs nominales et en fournissant un niveau de rendement suffisant. [0013]Selon des modes particuliers, le procédé s'appliquant à des turbomachines équipées de turbine de puissance, la diffusion radiale à calage variable sur compresseur centrifuge, telle que définie ci-dessus, est couplée à un distributeur de turbine de puissance à calage variable. La production de puissance peut être réalisée selon plusieurs configurations : turbine de puissance libre - ou liée, de type axiale ou centripète, avec ou sans échange thermique aval. [0014] Le couplage entre le diffuseur et le distributeur à calage variable permet d'adapter la ligne de fonctionnement à la diminution de débit, ce qui améliore le rendement du cycle moteur (par un meilleur taux de pression) et donc la Cs des turbomoteurs d'hélicoptères et des APU. [0015] L'invention a également pour objet un diffuseur de turbomachine à calage variable apte à mettre en œuvre le procédé défini ci-dessus, ainsi que la turbomachine équipée d'un tel diffuseur. Le diffuseur comporte une première grille annulaire de pales à calage variable radialement bordée par une deuxième grille annulaire de pales à calage fixe d'extension équivalente, formant des canaux de diffusion successifs par couplage des pales des deux grilles en extension radiales. De plus, chaque pale de la première grille est entraînée par des moyens de commande aptes à exercer une rotation propre de chaque pale décentrée par rapport à son axe de rotation. A sufficient pumping margin then allows the turbomachine to operate without pumping appearance - offering a large acceleration capacity - and the APU to cope with significant load variations without resorting to a valve while maintaining the speed of rotation of the turbomachine and its pressure ratio to levels close to their nominal values and providing a sufficient level of efficiency. According to particular embodiments, the method applying to turbomachines equipped with a power turbine, the variable-pitch radial diffusion on a centrifugal compressor, as defined above, is coupled to a wedge power turbine distributor. variable. Power production can be carried out according to several configurations: free power turbine - or linked, of axial or centripetal type, with or without downstream heat exchange. The coupling between the diffuser and the variable valve distributor makes it possible to adapt the operating line to the flow reduction, which improves the efficiency of the engine cycle (by a better pressure ratio) and therefore the Cs of the turboshaft engines. helicopters and APUs. The invention also relates to a turbomachine variable valve diffuser capable of implementing the method defined above, and the turbomachine equipped with such a diffuser. The diffuser comprises a first annular grid of variable pitch blades radially bordered by a second annular grid of fixed pitch blades of equivalent extension, forming successive diffusion channels by coupling the blades of the two grids in radial extension. In addition, each blade of the first gate is driven by control means capable of exerting a proper rotation of each blade off-center with respect to its axis of rotation.
[0016] Selon des modes de réalisation particuliers : - chaque pale à calage variable s'étend entre deux coupelles en regard et de manière parallèle et décentrée par rapport à l'axe commun des coupelles coïncidant avec l'axe de rotation; According to particular embodiments: - each variable-pitch blade extends between two cups opposite and parallel and off-center with respect to the common axis of the cups coinciding with the axis of rotation;
- chaque pale est couplée à une tige d'entraînement qui présente au moins un orifice dans lequel est introduite une goupille de blocage d'une rondelle de réglage de la position axiale des coupelles ; each blade is coupled to a drive rod which has at least one orifice in which is introduced a locking pin of a washer for adjusting the axial position of the cups;
- la tige est solidarisé à un levier présentant une rotule sphérique logée dans un logement cylindrique (38) d'une couronne de commande apte à entraîner en rotation autour de l'axe moteur le levier apte à coulisser dans le logement cylindrique ; - les logements cylindriques présente une profondeur qui est fonction de la course des leviers, elle-même fonction de l'intervalle de rotation prédéterminé des pales ; - le bord d'attaque de chaque pale à calage variable se trouve à proximité des périphéries des coupelles, la distance de la pale à l'axe de rotation étant supérieure ou égale à un demi-rayon ; - The rod is secured to a lever having a spherical ball received in a cylindrical housing (38) of a control ring adapted to drive in rotation about the motor axis the lever adapted to slide in the cylindrical housing; - The cylindrical housing has a depth which is a function of the stroke of the levers, itself a function of the predetermined rotation interval of the blades; the leading edge of each variable-pitch blade is close to the peripheries of the cups, the distance from the blade to the axis of rotation being greater than or equal to half a radius;
- le diffuseur en amont est un diffuseur lisse, c'est-à-dire non aubé ; - la veine d'air d'entrée du diffuseur située entre le rouet et la grille à calage variable est convergente, ce qui améliore les performances ; - The diffuser upstream is a smooth diffuser, that is to say, not aubé; the inlet air duct of the diffuser located between the impeller and the variable-pitch grille is convergent, which improves the performances;
- les pales fixes de la deuxième grille présentent un profil de bord d'attaque plus épais que celles de la première grille afin d'absorber les variations d'incidence; - les pales à calage fixe présentent une épaisseur suffisante pour être traversées par des vis permettant le passage des efforts structuraux ; the fixed blades of the second grid have a thicker leading edge profile than those of the first grid in order to absorb the variations of incidence; the blades with fixed wedging have a thickness sufficient to be traversed by screws allowing the passage of structural forces;
- les pales fixes présentent une loi évolutive d'angle squelette entre les bords d'attaque et de fuite, ce qui permet de contrôler la diffusion dans la grille fixe et d'optimiser son efficacité aérodynamique ; - les pales fixes sont calées en azimut par rapport aux pales de la première grille mobile de sorte à reprendre le sillage sur l'extrados des pales de cette première grille pour limiter les pertes de charge du diffuseur ; the fixed blades have an evolutionary law of skeleton angle between the leading and trailing edges, which makes it possible to control the diffusion in the fixed grid and to optimize its aerodynamic efficiency; the fixed blades are wedged in azimuth with respect to the blades of the first movable grid so as to resume the wake on the extrados of the blades of this first gate to limit the pressure drops of the diffuser;
- les angles de calage des pales variables sont compris entre +12 et - 5 ° par rapport au calage nominal, qui serait celui d'un diffuseur fixe. - The pitch angles of the variable blades are between +12 and - 5 ° compared to the nominal setting, which would be that of a fixed diffuser.
BREVE DESCRIPTION DES FIGURES BRIEF DESCRIPTION OF THE FIGURES
[0017] D'autres caractéristiques et avantages de l'invention ressortiront à la lecture de la description qui suit, en référence aux figures annexées qui représentent, respectivement : - la figure 1 , une demi-vue en coupe axiale partielle d'un diffuseur selon l'invention ; - les figures 2a et 2b, deux vues en perspective d'une pale à calage variable couplée à sa tige de commande en rotation; Other features and advantages of the invention will emerge on reading the description which follows, with reference to the appended figures which represent, respectively: - Figure 1, a half-view in partial axial section of a diffuser according to the invention; - Figures 2a and 2b, two perspective views of a variable-pitch blade coupled to its control rod in rotation;
- la figure 3, une vue globale frontale du flasque annulaire amont du diffuseur équipé des grilles de pales selon l'invention, - les figures 4a à 4c, une vue schématique partielle dans le diffuseur pour trois calages de pales mobiles, les deux calages extrêmes autour du calage nominal, et FIG. 3, an overall frontal view of the upstream annular flange of the diffuser equipped with the blade grids according to the invention, FIGS. 4a to 4c, a partial schematic view in the diffuser for three wedges of movable blades, the two extreme shims. around the nominal setting, and
- la figure 5, les jeux entre une pale mobile et les flasques annulaires du diffuseur. DESCRIPTION DETAILLEE D'UN EXEMPLE DE REALISATION - Figure 5, the games between a movable blade and the annular flanges of the diffuser. DETAILED DESCRIPTION OF AN EXEMPLARY EMBODIMENT
[0018] Les termes « amont » et « aval » se rapportent au sens d'écoulement du flux d'air dans un turbomoteur.  The terms "upstream" and "downstream" refer to the direction of flow of the air flow in a turbine engine.
[0019] En référence à la vue axiale en coupe partielle de la figure 1 , le compresseur centrifuge 10 d'une turbomachine, telle qu'un turbomoteur, turboréacteur, turbopropulseur ou un APU, comporte un carter 12 couplé à un couvercle 14 de recouvrement radial du rouet 16, dernier étage centrifuge du compresseur, monté en rotation sur l'arbre moteur 18 selon l'axe ΥΎ. Le flux d'air F circule du rouet 16 vers le diffuseur annulaire 19, dans une veine d'entrée convergente par rétrécissement radial. Le diffuseur 19 est défini entre deux flasques amont et aval 20 et 22. Le couvercle 14 est maintenu par une attache 23 fixée au carter et au flasque amont 20. With reference to the axial view in partial section of FIG. 1, the centrifugal compressor 10 of a turbomachine, such as a turbine engine, turbojet engine, turboprop engine or an APU, comprises a casing 12 coupled to a covering cover 14. radial wheel 16, last centrifugal stage of the compressor, rotatably mounted on the drive shaft 18 along the axis ΥΎ. The flow of air F flows from the impeller 16 to the annular diffuser 19, in a converging inlet vein by radial shrinkage. The diffuser 19 is defined between two upstream and downstream flanges 20 and 22. The cover 14 is held by a fastener 23 fixed to the casing and to the upstream flange 20.
[0020] Les pales 24, formant une première grille annulaire, sont montées dans le diffuseur 19. Des centrages 25 et 26, formées en regard dans les flasques 20 et 22, accueillent les coupelles 17 et 27 sur lesquelles les pales 24 sont montées de manière décentrée. Les coupelles sont centrées dans les flasques 20 et 22 avec des jeux adaptés, de 0,03 à 0,05 mm dans l'exemple illustré, sur une rondelle 9 insérée dans le centrage 25 (voir ci-dessous en référence à la figure 5). [0021] Des pales 28 solidaires du flasque 22, formant une deuxième grille annulaire bordant extérieurement la première grille, sont montées sur le flasque annulaire 20 par des vis traversantes 29 logées dans des trous 29t. Ces vis permettent également le passage des efforts structuraux. [0022] La commande des pales variables 24 est réalisée par l'intermédiaire de tiges 30 prolongeant solidairement la coupelle amont 17. Ces tiges 30 d'axe X'X sont montées dans un alésage cylindrique 32 du flasque amont 20 et centrées avec un jeu quasi-nul par des joints 30j montés dans des gorges 30g. En extrémité, chaque tige 30 présente une partie plate 31 articulée sur un levier d'entraînement 33 pincé par deux vis 35 sur cette partie plate 31 . Les positions des extrémités 31 des tiges 30 sont ajustées avec des tolérances de jeux adaptées. La tige 30 présente également un orifice 30t dans lequel est introduite une goupille 36 qui permet de bloquer une rondelle 30u - de réglage de la position axiale des coupelles 17 et 27 - dans un anneau de blocage 12a formé dans le carter 12. Dans ce but, la goupille 36 solidarise la tige 30 et l'anneau de blocage 12a. The blades 24, forming a first annular grid, are mounted in the diffuser 19. Centerings 25 and 26, formed opposite in the flanges 20 and 22, accommodate the cups 17 and 27 on which the blades 24 are mounted. off-center way. The cups are centered in the flanges 20 and 22 with appropriate clearances, from 0.03 to 0.05 mm in the example illustrated, on a washer 9 inserted in the centering 25 (see below with reference to FIG. ). Blades 28 secured to the flange 22, forming a second annular grid externally bordering the first gate, are mounted on the annular flange 20 by through screws 29 housed in holes 29t. These screws also allow the passage of structural forces. The control of the variable blades 24 is performed by means of rods 30 integrally extending the upstream cup 17. These rods 30 X'X axis are mounted in a cylindrical bore 32 of the upstream flange 20 and centered with a set almost zero by 30j joints mounted in grooves 30g. At the end, each rod 30 has a flat portion 31 articulated on a drive lever 33 clamped by two screws 35 on this flat portion 31. The positions of the ends 31 of the rods 30 are adjusted with appropriate play tolerances. The rod 30 also has a hole 30t in which a pin 36 is inserted which makes it possible to lock a washer 30u - for adjusting the axial position of the cups 17 and 27 - in a locking ring 12a formed in the casing 12. For this purpose , the pin 36 secures the rod 30 and the locking ring 12a.
[0023] En fonctionnement, le levier 33 est entraîné par une couronne de commande 34 formant un trou cylindrique 38 de logement de la rotule sphérique 37 du levier 33 avec une tolérance de position axiale adaptée et un contact sur une génératrice de la rotule. Pour ce faire, la couronne de commande 34 est centrée sur des secteurs présentant des roulements à aiguilles 39. La couronne de commande 34, mise en rotation autour de l'axe moteur ΥΎ par une biellette (non représentée), entraîne en rotation les leviers 33 qui coulissent dans les logements cylindriques 38 grâce à leur rotule 37. La profondeur des logements 38 est fonction de la course des leviers 33, elle-même fonction de l'intervalle de rotation des pales 24. Cette architecture est particulièrement adaptée à une rotation des pales pouvant aller jusqu'à +12° avec une fermeture de 50% de section, et jusqu'à -5 ° avec une ouverture de section de 20%. Les angles de position des tiges et donc des pales 24 en fonction des régimes de puissance pour fournir la compression d'air appropriée à ces régimes. [0024] En référence aux figures 2a et 2b, une pale mobile 24 est représentée entre les coupelles parallèles 17, 27 et solidarisée par soudage 21 à celles-ci, de sorte que la pale s'étend parallèlement à l'axe X'X des coupelles en regard. Le bord d'attaque 24c de la pale 24 affleure les circonférences externes 17c et 27c des coupelles, l'épaisseur de la pale 24 étant relativement fine, de 2 mm dans l'exemple illustré. Par ailleurs, la distance entre la pale 24 et l'axe X'X de la tige 30 est égale à environ 80% du rayon des coupelles dans l'exemple illustré. Ceci confère à la pale 24 un fort décentrage par rapport à l'axe X'X de la tige qui coïncide avec l'axe de rotation de l'ensemble. La tige 30 présente également les gorges cylindriques 30g de centrage et l'orifice 30t de blocage de la rondelle de réglage de la position axiale des coupelles 17 et 27. Sa partie plate 31 est traversée par des trous 30a de réception des vis 35 de montage au levier de commande. In operation, the lever 33 is driven by a control ring 34 forming a cylindrical hole 38 for housing the spherical ball 37 of the lever 33 with an adapted axial position tolerance and a contact on a generatrix of the ball joint. To do this, the control ring 34 is centered on sectors having needle bearings 39. The control ring 34, rotated about the motor axis ΥΎ by a rod (not shown), rotates the levers 33 which slide in the cylindrical housing 38 through their ball joint 37. The depth of the housing 38 is a function of the stroke of the levers 33, itself a function of the rotation interval of the blades 24. This architecture is particularly suitable for rotation blades up to + 12 ° with a 50% section closure, and up to -5 ° with a 20% section opening. The position angles of the rods and thus of the blades 24 as a function of the power regimes to provide the appropriate air compression to these regimes. Referring to Figures 2a and 2b, a movable blade 24 is shown between the parallel cups 17, 27 and secured by welding 21 to them, so that the blade extends parallel to the axis X'X cups opposite. The leading edge 24c of the blade 24 is flush with the outer circumferences 17c and 27c of the cups, the thickness of the blade 24 being relatively thin, 2 mm in the illustrated example. Moreover, the distance between the blade 24 and the axis X'X of the rod 30 is equal to about 80% of the radius of the cups in the illustrated example. This confers on the blade 24 a strong off-centering with respect to the axis X'X of the rod which coincides with the axis of rotation of the assembly. The rod 30 also has the cylindrical centering grooves 30g and the locking hole 30t of the adjusting washer of the axial position of the cups 17 and 27. Its flat portion 31 is traversed by holes 30a for receiving the mounting screws 35. to the control lever.
[0025] La vue globale de la figure 3 illustre le flasque annulaire amont 20 équipé des grilles annulaires G1 et G2, montées respectivement mobile et fixe et composées des pales 24 et 28. The overall view of Figure 3 illustrates the upstream annular flange 20 equipped with annular gates G1 and G2, mounted respectively mobile and fixed and composed of blades 24 and 28.
[0026] Les pales 28 présentent un profil sensiblement plus épais en bord d'attaque Ba que celui des pales 24, respectivement 0.5 et 2.5 mm, afin de préserver une bonne tenue aux variations d'incidence lors de la rotation des pales mobiles 24. De plus, la loi d'angle squelette des pales 28 entre les bords d'attaque BA et de fuite BF est évolutive, permettant d'optimiser l'efficacité aérodynamique de la grille fixe par une récupération maximale de pression statique. The blades 28 have a substantially thicker profile in the leading edge Ba than that of the blades 24, respectively 0.5 and 2.5 mm, to preserve a good resistance to variations in incidence during the rotation of the movable blades 24. In addition, the skeleton angle law of the blades 28 between the leading edges BA and LF leakage is scalable, to optimize the aerodynamic efficiency of the fixed gate by a maximum recovery of static pressure.
[0027] En outre, les pales 28 de la grille fixe présentent une épaisseur maximale, de 7 mm dans l'exemple illustré, permettant de fixer le flasque 20 du diffuseur par des vis se logeant dans les trous 29t, tout en permettant le passage des efforts structuraux. In addition, the blades 28 of the fixed gate have a maximum thickness of 7 mm in the example shown, for fixing the flange 20 of the diffuser by screws housed in the holes 29t, while allowing the passage structural efforts.
[0028] Le flux d'air F circule le long d'une pale fixe 28 en extension radiale d'une pale mobile 24 et entre deux pales adjacentes de même nature, mobile ou fixe. Grâce au décentrage des pales mobiles 24 par rapport aux axes de rotation X'X de leurs coupelles 17, les variations des extensions radiales formées par ces pales mobiles 24 sont limitées par rapport à des variations d'extensions que devraient réaliser des pales centrées. Cette limitation permet d'améliorer les performances d'un compresseur centrifuge : elle permet d'éloigner la ligne de fonctionnement de la ligne de pompage, par décalage vers des débits plus bas, et d'élever cette ligne de fonctionnement près des maximas de rendement aux régimes plus élevés. The air flow F flows along a fixed blade 28 in radial extension of a movable blade 24 and between two adjacent blades of the same type, mobile or fixed. Thanks to the off-centering of the mobile blades 24 with respect to the axes of rotation X'X of their cups 17, the variations of the radial extensions formed by these movable blades 24 are limited compared to variations of extensions that should be made of centered blades. This limitation makes it possible to improve the performance of a centrifugal compressor: it makes it possible to move the operating line away from the pumping line, by shifting towards lower flow rates, and to raise this operating line close to the yield maxima. higher diets.
[0029] Les extensions radiales des pales mobiles 24 au regard des pales fixes 28 sont illustrées par les schémas des figures 4a à 4c, sur lesquelles apparaissent également, en lignes pointillées, les coupelles 17, 27 des pales. En référence à la figure 4b, le calage nominal de 0° correspond à un écoulement du flux d'air F de référence pour lequel le réglage des pales mobiles 24 par rapport aux pales fixes 28 est adapté aux régimes intermédiaires stables. The radial extensions of the movable blades 24 with respect to the fixed blades 28 are illustrated by the diagrams of Figures 4a to 4c, which also appear, in dashed lines, the cups 17, 27 of the blades. With reference to FIG. 4b, the nominal setting of 0 ° corresponds to a flow of the reference air flow F for which the adjustment of the mobile blades 24 with respect to the fixed blades 28 is adapted to stable intermediate speeds.
[0030]Aux faibles demandes de charge, le calage des pales mobiles 24 peut monter jusqu'à +12°, ce calage correspondant à une section de passage à l'entrée du col Sa, entre les pales 24 et 28, fermée de 50% par rapport au calage nominal correspondant à une section au col Sb. La figure 4a illustre le cas d'une fermeture de 25% associée à un calage de 6°, la section au col valant alors 75% de la section Sb. Aux fortes demandes de charge, le réglage du calage peut également descendre jusqu'à -5°. La figure 4c illustre le cas d'une ouverture de 2,5°, la section au col Se présentant alors une valeur relative de 1 10%. At low load demands, the wedging of the movable blades 24 can go up to + 12 °, this wedging corresponding to a passage section at the entrance of the neck Sa, between the blades 24 and 28, closed 50 % compared to the nominal setting corresponding to a Sb neck section. Figure 4a illustrates the case of a closure of 25% associated with a setting of 6 °, the neck section then being 75% of the section Sb. At high load demands, the calibration setting can also go down to -5 °. FIG. 4c illustrates the case of an opening of 2.5 °, the section at the neck being then a relative value of 1 10%.
[0031] les pales fixes 28 sont calées en azimut par rapport aux pales 24 de la première grille mobile G1 de sorte à reprendre le sillage sur l'extrados Ex des pales de cette première grille G1 . [0032] Les extensions radiales des pales 24, limitées par la présence des pales fixes 28, permettent de conserver une maîtrise des jeux entre les coupelles 17 et 27 des pales 24 et les flasques 20 et 22, comme illustré par la figure 5. Ainsi, dans cet exemple, les valeurs des jeux restent inférieures ou égales respectivement à 0,02 mm (pour J1 ou J2), à 0,10 mm (pour J3) et 0,25 mm (pour J4). Le jeu (ensemble J1 et J2) de la pale 24 sur la rondelle 9 reste donc d'environ 0,03 mm ou légèrement supérieur. The fixed blades 28 are wedged in azimuth with respect to the blades 24 of the first movable gate G1 so as to resume the wake on the extrados Ex of the blades of this first gate G1. The radial extensions of the blades 24, limited by the presence of the fixed blades 28, allow to maintain control games between the cups 17 and 27 of the blades 24 and the flanges 20 and 22, as shown in Figure 5. Thus in this example, the values of the clearances remain less than or equal to 0.02 mm (for J1 or J2), 0.10 mm (for J3) and 0.25 mm (for J4). The clearance (set J1 and J2) of the blade 24 on the washer 9 remains about 0.03 mm or slightly higher.
[0033] L'invention n'est pas limitée aux exemples décrits et représentés. Il est par exemple possible d'effectuer le calage des pales mobiles par réglage uniquement mécanique, individuel ou centralisé, ou par commande électrique, électronique avec ou sans régulation numérique. The invention is not limited to the examples described and shown. It is for example possible to set the pitch of the mobile blades by only mechanical adjustment, individual or centralized, or by electrical, electronic control with or without digital control.

Claims

REVENDICATIONS
Procédé d'adaptation de débit d'air dans un compresseur centrifuge (10) de turbomachine, consistant à prévoir une diffusion de l'air à travers un premier aubage annulaire (G1 ) de pales à calage variable (24) bordé radialement d'un deuxième aubage annulaire (G2) de même nombre de pales à calage fixe (28) d'extension équivalente, orientant la diffusion en extension radiale par couplage des pales (24, 28) des deux aubages, ce procédé étant caractérisé en ce que chaque pale (24) du premier aubage (G1 ) est entraînée en rotation d'axe (X'X) à distance de la pale (24). A method of adjusting air flow in a centrifugal compressor (10) of a turbomachine, comprising providing a diffusion of air through a first annular blading (G1) of variable pitch blades (24) radially flanked by a second annular blade (G2) of the same number of fixed-pitch blades (28) of equivalent extension, orienting the diffusion in radial extension by coupling of the blades (24, 28) of the two blades, this method being characterized in that each blade (24) of the first vane (G1) is rotated axis (X'X) away from the blade (24).
Procédé d'adaptation selon la revendication 1 , dans lequel la diffusion radiale à calage variable sur compresseur centrifuge est couplée à une distribution de puissance à calage variable, la distribution de puissance étant libre avec échange aval ou liée, de manière axiale ou centripète, avec ou sans échange aval. An adaptation method according to claim 1, wherein the variable-pitch radial diffusion on a centrifugal compressor is coupled to a variable-pitch power distribution, the power distribution being free with downstream exchange or connected, axially or centripetally, with or without downstream exchange.
Diffuseur de turbomachine à calage variable apte à mettre en œuvre le procédé selon la revendication 1 ou 2, comportant une première grille annulaire (G1 ) de pales à calage variable (24) radialement bordée par une deuxième grille annulaire (G2) de pales à calage fixe (28) d'extension équivalente et de même nombre de pales, formant des canaux de diffusion successifs par couplage des pales (24, 28) des deux grilles (G1 , G2) en extension radiales, caractérisé en ce que chaque pale (24) de la première grille (G1 ) est entraînée par des moyens d'entraînement (30, 33, 34) aptes à exercer une rotation propre de pale (24) décentrée par rapport à son axe de rotation (X'X). Variable valve turbomachine diffuser adapted to implement the method according to claim 1 or 2, comprising a first annular grid (G1) of variable pitch blades (24) radially bordered by a second annular grid (G2) of paddle blades fixed (28) of equivalent extension and the same number of blades, forming successive diffusion channels by coupling the blades (24, 28) of the two grids (G1, G2) in radial extension, characterized in that each blade (24 ) of the first gate (G1) is driven by drive means (30, 33, 34) capable of exerting a self-rotation of blade (24) off-center with respect to its axis of rotation (X'X).
Diffuseur selon la revendication précédente, dans lequel chaque pale à calage variable (24) s'étend entre deux coupelles (17, 27) en regard et de manière parallèle et décentrée par rapport à l'axe commun des coupelles coïncidant avec l'axe de rotation (X'X). Diffuser according to the preceding claim, in which each variable-pitch blade (24) extends between two cups (17, 27) facing each other and parallel and off-center with respect to the common axis of the cups coinciding with the axis of rotation (X'X).
Diffuseur selon l'une des revendications 3 ou 4, dans lequel chaque pale (24) est couplée à une tige d'entraînement (30) qui présente au moins un orifice (30t) dans lequel est introduite une goupille (36) de blocage d'une rondelle (30u) de réglage de la position axiale des coupelles (17, 27). Diffuser according to one of claims 3 or 4, wherein each blade (24) is coupled to a drive rod (30) having at least one orifice (30t) into which is introduced a pin (36) for blocking a washer (30u) for adjusting the axial position of the cups (17, 27).
Diffuseur selon la revendication précédente, dans lequel la tige (30) est solidarisé à un levier (33) présentant une rotule sphérique (37) logée dans un logement cylindrique (38) d'une couronne de commande (34) apte à entraîner en rotation autour de l'axe moteur (ΥΎ) le levier (33) apte à coulisser dans le logement cylindrique 38. Diffuser according to the preceding claim, wherein the rod (30) is secured to a lever (33) having a spherical ball (37) housed in a cylindrical housing (38) of a control ring (34) adapted to drive in rotation around the motor axis (ΥΎ) the lever (33) slidable in the cylindrical housing 38.
Diffuseur selon la revendication précédente, dans lequel la profondeur des logements cylindriques (38) est fonction de la course des leviers (33), elle- même fonction de l'intervalle de rotation prédéterminé des pales (24). Diffuser according to the preceding claim, wherein the depth of the cylindrical housings (38) is a function of the stroke of the levers (33), itself a function of the predetermined rotation interval of the blades (24).
Diffuseur selon l'une quelconque des revendications 4 à 7, dans lequel le bord d'attaque (24c) de chaque pale à calage variable (24) se trouve à proximité des périphéries (17c, 27c) des coupelles (17, 27), la distance de la pale (24) à l'axe de rotation (X'X) étant supérieure ou égale à un demi- rayon. Diffuser according to any one of claims 4 to 7, wherein the leading edge (24c) of each variable-pitch blade (24) is close to the peripheries (17c, 27c) of the cups (17, 27), the distance from the blade (24) to the axis of rotation (X'X) being greater than or equal to half a radius.
Diffuseur selon l'une quelconque des revendications 3 à 8, dans lequel les pales fixes (28) de la deuxième grille (G2) présentent un profil de bord d'attaque (Ba) plus épais que celui (24c) des pales (24) de la première grille (G1 ). Diffuser according to any one of claims 3 to 8, wherein the fixed blades (28) of the second gate (G2) have a leading edge profile (Ba) thicker than that (24c) of the blades (24) of the first grid (G1).
Diffuseur selon l'une quelconque des revendications 3 à 9, dans lequel k angles de calage des pales mobiles (24) sont compris entre +12 et -5 correspondant à une section de col (Sa, Se) respectivement de 50% et de 120% par rapport à la section correspondant au calage nominal. Diffuser according to any one of claims 3 to 9, wherein k wedge angles of the movable blades (24) are between +12 and -5 corresponding to a neck section (Sa, Se) respectively of 50% and 120% with respect to the section corresponding to the nominal setting.
EP11730371.9A 2010-04-14 2011-04-13 Method for adapting the air flow of a turbine engine having a centrifugal compressor and diffuser for implementing same Active EP2558728B2 (en)

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FR1052827A FR2958967B1 (en) 2010-04-14 2010-04-14 METHOD FOR ADJUSTING TURBOMACHINE AIR FLOW WITH CENTRIFUGAL COMPRESSOR AND DIFFUSER THEREFOR
PCT/FR2011/050846 WO2011128587A1 (en) 2010-04-14 2011-04-13 Method for adapting the air flow of a turbine engine having a centrifugal compressor and diffuser for implementing same

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WO2011128587A1 (en) 2011-10-20
PL2558728T3 (en) 2019-10-31
EP2558728B2 (en) 2022-10-12
FR2958967A1 (en) 2011-10-21
JP2013524099A (en) 2013-06-17
PL2558728T5 (en) 2023-02-06
FR2958967B1 (en) 2013-03-15
EP2558728B1 (en) 2019-07-24
CN102834622B (en) 2016-02-10
KR20130079326A (en) 2013-07-10
CA2794825C (en) 2018-06-12
CN102834622A (en) 2012-12-19
RU2012148378A (en) 2014-05-20
CA2794825A1 (en) 2011-10-20
JP2017061936A (en) 2017-03-30
JP6483074B2 (en) 2019-03-13
RU2564158C2 (en) 2015-09-27
US20130034425A1 (en) 2013-02-07

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