EP2917590B1 - Compression assembly for a turbine engine - Google Patents

Compression assembly for a turbine engine Download PDF

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Publication number
EP2917590B1
EP2917590B1 EP13795842.7A EP13795842A EP2917590B1 EP 2917590 B1 EP2917590 B1 EP 2917590B1 EP 13795842 A EP13795842 A EP 13795842A EP 2917590 B1 EP2917590 B1 EP 2917590B1
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EP
European Patent Office
Prior art keywords
air
rotation
vanes
duct
grille
Prior art date
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EP13795842.7A
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German (de)
French (fr)
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EP2917590A1 (en
Inventor
Jean-François Escuret
Pierre Biscay
Guillaume SEVESTRE
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
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Safran Helicopter Engines SAS
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Priority to PL13795842T priority Critical patent/PL2917590T3/en
Publication of EP2917590A1 publication Critical patent/EP2917590A1/en
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    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F01—MACHINES OR ENGINES IN GENERAL; ENGINE PLANTS IN GENERAL; STEAM ENGINES
    • F01D—NON-POSITIVE DISPLACEMENT MACHINES OR ENGINES, e.g. STEAM TURBINES
    • F01D7/00—Rotors with blades adjustable in operation; Control thereof
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F04—POSITIVE - DISPLACEMENT MACHINES FOR LIQUIDS; PUMPS FOR LIQUIDS OR ELASTIC FLUIDS
    • F04D—NON-POSITIVE-DISPLACEMENT PUMPS
    • F04D29/00—Details, component parts, or accessories
    • F04D29/40—Casings; Connections of working fluid
    • F04D29/52—Casings; Connections of working fluid for axial pumps
    • F04D29/54—Fluid-guiding means, e.g. diffusers
    • F04D29/541—Specially adapted for elastic fluid pumps
    • F04D29/542—Bladed diffusers
    • F04D29/544—Blade shapes
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F01—MACHINES OR ENGINES IN GENERAL; ENGINE PLANTS IN GENERAL; STEAM ENGINES
    • F01D—NON-POSITIVE DISPLACEMENT MACHINES OR ENGINES, e.g. STEAM TURBINES
    • F01D1/00—Non-positive-displacement machines or engines, e.g. steam turbines
    • F01D1/02—Non-positive-displacement machines or engines, e.g. steam turbines with stationary working-fluid guiding means and bladed or like rotor, e.g. multi-bladed impulse steam turbines
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F01—MACHINES OR ENGINES IN GENERAL; ENGINE PLANTS IN GENERAL; STEAM ENGINES
    • F01D—NON-POSITIVE DISPLACEMENT MACHINES OR ENGINES, e.g. STEAM TURBINES
    • F01D9/00—Stators
    • F01D9/02—Nozzles; Nozzle boxes; Stator blades; Guide conduits, e.g. individual nozzles
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F04—POSITIVE - DISPLACEMENT MACHINES FOR LIQUIDS; PUMPS FOR LIQUIDS OR ELASTIC FLUIDS
    • F04D—NON-POSITIVE-DISPLACEMENT PUMPS
    • F04D29/00—Details, component parts, or accessories
    • F04D29/40—Casings; Connections of working fluid
    • F04D29/52—Casings; Connections of working fluid for axial pumps
    • F04D29/54—Fluid-guiding means, e.g. diffusers
    • F04D29/56—Fluid-guiding means, e.g. diffusers adjustable
    • F04D29/563—Fluid-guiding means, e.g. diffusers adjustable specially adapted for elastic fluid pumps

Definitions

  • the invention relates to the field of turbomachines, in particular for aircraft.
  • the invention more particularly relates to a compression assembly for a turbomachine, in particular for a helicopter turbine engine, and a turbomachine equipped with such an assembly.
  • a turbine engine comprises, in known manner, a compression assembly comprising an air inlet duct and at least one air compression stage, or compressor, which comprises at least one mobile compressor wheel on which the duct opens.
  • Such compression assemblies have an aerodynamic stability limit, commonly known as a pumping line, which limits in particular the acceleration capabilities of the turbine engine. At low operating speeds, the aerodynamic stability limit of the compression assembly is related to an aerodynamic overload of the first compression stage, which results in too high incidences of the air flow reaching the first moving wheel.
  • a known solution described in the patent application FR2970508 filed by the Applicant, consists in mounting a gate, said pre-rotation, in the air intake duct of the turbine engine upstream of the first mobile wheel of the compressor to reduce the incidence of the air flow reaching said first moving wheel by orienting it in the direction of rotation of the first moving wheel.
  • Such a pre-rotation grid comprises steerable, variable-pitch inlet guide vanes mounted on a casing and equidistributed in the air intake duct.
  • the setting of the gate that is to say the orientation of the blades, is effected via a control ring and allows to regulate the speed of the air flow at the inlet of the impeller so as to adapt the incidence of airflow reaching the first moving wheel.
  • a known arrangement of such a pre-rotation grid is to arrange the blades of the grid so that the pre-rotation angle of the blades and thus the orientation angle of the airflow is scalable according to the height in the air duct, the airflow orientation angle being defined as the relative deviation of the airflow by a blade of the pre-rotation grid to a given height of the air duct.
  • the angle of orientation of the air flow varies with the radial distance in the air inlet duct relative to the axis of the turbine engine.
  • FIGS 1 to 3 illustrate a diagrammatic cross-sectional view at the head of an arrangement of two blades 10 of a pre-rotation grid 5 and two blades 20 of a compressor moving wheel 15 of the prior art.
  • the consecutive blades 10 of the grid 5 are spaced apart by a distance S1 called "pitch".
  • Each blade 10 has a curved section and defines a rope C1 between the upstream end and the downstream end of the blades 10, that is to say between the leading edge and the trailing edge of the blade 10.
  • pre-rotation angle of the blades 10 of the gate 5 is usually between values of the order of 0 ° at the bottom of the air duct and up to about 15 ° at the top of the air duct (relative to to the axis X'X).
  • the flow of air F entering the grid is then deviated by an angle of orientation ⁇ 1 close to the pre-rotation angle of the blades and between 0 ° to 15 ° according to the height in the air duct with an absolute speed V 1 at the gate exit whose axial component (along the axis X'X) is Vz1.
  • Such calibration of the grid 5 is used for the high operating speeds of the compressor, especially in maximum operating conditions, for example, in the take-off mode in the case of a helicopter turbine engine.
  • the gate 5 is at least partially closed in order to reduce the aerodynamic load and to increase the pumping margin by shifting the compressor pumping line to the low flow rates while shifting the operating line towards the high flow rates, which allows to obtain a large capacity of acceleration of the turbine engine.
  • the control ring (not shown) of the pre-rotation grid 5 is usually set to a value, for example about 65 °, for which the pre-rotation angle of the blades 10 of the grid 5 is between 65 ° and 80 ° depending on the height of the flow in the air duct.
  • the pre-rotation angle of the blades reaches values of the order of 85 ° at the top of the air duct, that is to say that the flow of air is deflected from an orientation angle ⁇ 1 close to about 85 ° by the blades 10 in the highest part of the duct, in particular at the distal end of the blades 10.
  • the air flow at the outlet of the pre-rotation grid 5 at the top of the air duct becomes so low that it can cause an aerodynamic malfunction of the blades 20 of the mobile wheel 15 of the compressor.
  • the air boundary layers no longer hold on the shape of the blade head profiles 20 of the impeller 15, which can lead to aerodynamic detachment within the impeller 15, commonly known as detachment rotating, detrimental to the aerodynamic stability of the compressor, and therefore has a disadvantage.
  • the aim of the invention is to improve the structure of the existing pre-rotation gates by increasing the pre-rotation angle of the blades above 15 ° at the top of the air duct at high operating speed of the turbine engine while avoiding the aerodynamic malfunctions of the blades of the moving wheel at low operating speed of the turbine engine.
  • turbomachine comprising a pre-rotation grid such as exists in the turboshaft engines, turbojets, auxiliary power units.
  • auxiliary power units Auxiliary Power Unit or APU in English
  • land-based turbomachines land-based turbomachines
  • turbochargers turbochargers etc.
  • compressors any type of compressor that is axial, centrifugal, mixed etc.
  • the subject of the invention is a compression assembly for a turbomachine, in particular a turbine engine, according to claim 1.
  • pitch means the distance between two identical points of two blades of the grid arranged consecutively.
  • rope is meant the distance of the segment extending between the upstream end and the downstream end of a blade of the pre-rotation grid, that is to say between the end of the edge of the attack and the end of the trailing edge of a blade of the pre-rotation grid.
  • upstream and downstream is meant in relation to the direction of the flow of air flowing in the turbomachine.
  • the pitch between two consecutive blades is greater than the rope of one of the two blades in the upper part of the air duct, for example at the distal ends of said blades.
  • upper part of the air duct is meant that part of the air duct furthest radially from the longitudinal axis of the turbine engine.
  • at the top of the air duct is meant the distal end of the blade with respect to the longitudinal axis of the turbine engine.
  • lower part of the duct is the portion of the duct closest to the longitudinal axis of the turbine engine.
  • at the bottom of the air duct is meant the proximal end of the blade with respect to the longitudinal axis of the turbine engine.
  • the pitch between the distal ends of two consecutive blades of the pre-rotation grid was equal to or less than the string of a blade of the grid.
  • the ratio of the pitch on the string (S1 / C1) took values between 0.9 and 1.
  • the pitch between two consecutive blades of the gate being greater than the rope of one of the two blades, the blades do not overlap in the closed position of the grid as in the solutions of the prior art, which allows the use of blades whose pre-rotation angle is greater than 15 ° in the upper part of the air duct at high operating speeds of the compressor stage (with very stable open of the pre-rotation grid) while allowing efficient aerodynamic operation of the mobile wheel of the compressor at low speeds (with very closed wedges of the pre-rotation grid).
  • the pre-rotation angle of the blades is greater than 15 ° in the upper part of the air duct, in particular at their distal ends, preferably between 15 ° and 25 °, when the pre-rotation grid is in the open position of operation at high speeds of the compression stage, for example for a setting value of the gate control ring of 0 °.
  • the pre-rotation angle of the blades is between 80 ° and 90 ° in the upper part of the air duct, in particular at their distal ends, when the pre-rotation grid is in the closed position of operating at low speeds of the compression stage, for example for a setting value of the gate control ring of 65 °.
  • the spacing of the blades in the closed position of the grid makes it possible to obtain an axial speed of the air flow greater than the axial velocity of the flux in a assembly of the prior art for the same setting of the control ring of the pre-rotation grid.
  • the spacing of the blades makes it possible to increase the axial speed of the flow of air passing through the pre-rotation grid, in particular with very closed wedges, so as to avoid aerodynamic malfunctions of the blades of the wheel. mobile compressor.
  • the blades of the gate extend radially with respect to the axis of the turbomachine and are configured so that the pre-rotation angle of the blades of the pre-rotation gate changes in the duct. air with radial distance.
  • the blades can be twisted, for example.
  • the pre-rotation angle is approximately equal to 0 ° at the bottom of the air duct, that is to say as close as radially to the axis of the turbine engine, and of the order of 25 ° at the top of the air duct, that is to say at most radially from the axis of the turbine engine, for a setting value of the gate control ring of 0 °.
  • the blade string is constant among the plurality of blades of the pre-rotation grid.
  • the pre-rotation grid is positioned in a radial portion, a bend or an axial portion of the air intake duct.
  • the terms "radial portion” and “axial portion” meaning in relation to the axis of the turbomachine.
  • the blades are arranged equidistributed in the air inlet duct.
  • the pitch between the blades of the grid is constant.
  • the invention also relates to a turbomachine according to claim 7, such as, for example, a turbine engine, particularly for an aircraft such as, for example, a helicopter, comprising an air inlet duct adapted to receive a flow of air.
  • a turbomachine such as, for example, a turbine engine, particularly for an aircraft such as, for example, a helicopter, comprising an air inlet duct adapted to receive a flow of air.
  • air at least one air compression stage comprising at least one mobile compressor wheel on which the duct opens and a pre-rotation grille, positioned in the air intake duct upstream of the mobile compressor wheel for regulating the air speed of said flow at the inlet of the moving wheel and comprising a plurality of variable-pitch blades, the assembly being remarkable in that the pitch between two consecutive blades of the gate is greater than the rope of one of the two blades at a given height, preferably in the upper part, of the air duct.
  • the invention also relates to a method for controlling a pre-rotation grid of a compression assembly, as defined in claim 8, comprising an air intake duct adapted to receive a flow of air, at least one air compression stage comprising at least one mobile compressor wheel on which the duct opens and a pre-rotation grille, positioned in the air intake duct upstream of the mobile compressor wheel for regulating the air speed of said flow at the inlet of the moving wheel and comprising a plurality of variable pitch blades, the method being remarkable in that, the pitch between two consecutive blades of the gate being greater than the rope of one of the two blades at a given height of the air duct, preferably in its upper part in particular at their distal ends, is positioned the blades of the grid at a pre-rotation angle between 80 ° and 90 ° at low speeds of functioning of the compression stage.
  • the invention also relates to a method for controlling a pre-rotation grid of a compression assembly, as defined above, comprising an air intake duct adapted to receive an air flow, at the least one air compression stage comprising at least one mobile compressor wheel on which the duct opens and a pre-rotation grille, positioned in the air inlet duct upstream of the mobile compressor wheel to regulate the air speed of said flow at the inlet of the moving wheel and comprising a plurality of variable-pitch blades, the method being remarkable in that, the pitch between two consecutive blades of the gate being greater than the rope of one of the two blades at a given height of the air duct, preferably in its upper part, particularly at their distal ends, the blades of the grid are positioned at a pre-rotation angle greater than 15 °, preferably between 15 ° and 25 °, to ha Operating modes of the compression stage.
  • the invention further relates to any type of compressor that is axial, centrifugal, mixed etc.
  • the compression assembly of a turbomachine comprises an air intake duct adapted to receive an air flow, an air compression stage comprising a mobile compressor wheel on which the duct opens and a pre-rotation grid.
  • the pre-rotation grid is positioned in the air intake duct upstream of the mobile compressor wheel to straighten the upstream air flow which is directed towards the moving wheel and regulate the speed at the inlet of the wheel mobile.
  • the gate comprises a plurality of variable-pitch blades extending radially with respect to the axis of the turbomachine and arranged in the same transverse plane perpendicular to the axis of the turbomachine.
  • the air enters the air inlet duct, passes through the pre-rotation grid and is conveyed to the compressor impeller.
  • the flow of compressed air by the mobile compressor wheel is then injected into a combustion chamber to be mixed with the fuel and to provide, after combustion, the kinetic energy for rotating one or more turbines.
  • turbomachine may further comprise other compression stages arranged between the first compression stage and the combustion chamber.
  • FIGS. 4 and 5 illustrate in the arrangement of two blades 110 of a pre-rotation grid 105 according to the invention.
  • Control means (not shown) of the grid of pre-rotation 105 allow to orient the blades 110 of the gate 105 according to an opening / closing law of the blades 110 which depends on the rotational speed of the turbomachine.
  • Such a calibration law is set to guarantee a minimum pumping margin between the operating line and the pumping line.
  • the blades 110 of the grid 105 are spaced apart by a pitch S2 and have, between their upstream and downstream end, that is to say between the leading edge and the trailing edge, a curvature defining a rope C2.
  • the pre-rotation gate 105 is arranged upstream, in the overall direction of the air flow F, the blades 120 of the mobile wheel 115 of the compressor.
  • the moving wheel 115 is rotated according to the speed vector U so as to accelerate the flow of air deflected by the pre-rotation grid.
  • the pitch S2 between two consecutive blades 110 of the grid 5 is greater than the rope C2 of the blades 110 of the grid 5 at the top of the air duct so that the blades 110 do not overlap in the closed position of the grid 105.
  • the ratio of the pitch S2 on the chord C2, that is to say the parameter S2 / C2, can take values comprised between 1 and 1.5.
  • pre-rotation angle values of the air flow a2 between 15 ° and 25 ° at the top of the air duct make it possible to significantly reduce the relative speed. W2 air inlet of the impeller 115 and thus very substantially improve the efficiency of the compression stage.
  • the spacing of the blades 110 of the grid 105 allows, despite pre-rotation angle values of the blades between 80 and 90 ° at the top of the air duct, to obtain pre-rotation angles of the air flow a2 lower and thus to maintain an axial velocity Vz2 sufficiently high to avoid aerodynamic malfunctions of the mobile wheel 115 of the compressor at low speeds with very closed wedges of the grid pre-rotation 105.
  • the increase of the pitch S2 compared with the prior art makes it possible to limit the deflection of the flow of air flowing between the leading edge BA of a blade 110 and the trailing edge BF of a blade 110 consecutive from the pre-rotation grid 105.

Description

DOMAINE DE L'INVENTIONFIELD OF THE INVENTION

L'invention se rapporte au domaine des turbomachines, notamment pour aéronef. L'invention concerne plus particulièrement un assemblage de compression pour une turbomachine, notamment pour un turbomoteur d'hélicoptère, ainsi qu'une turbomachine équipée d'un tel assemblage.The invention relates to the field of turbomachines, in particular for aircraft. The invention more particularly relates to a compression assembly for a turbomachine, in particular for a helicopter turbine engine, and a turbomachine equipped with such an assembly.

ÉTAT DE LA TECHNIQUESTATE OF THE ART

Un turbomoteur comprend de manière connue un assemblage de compression comprenant un conduit d'entrée d'air et au moins un étage de compression d'air, ou compresseur, qui comprend au moins une roue mobile de compresseur sur laquelle débouche le conduit.A turbine engine comprises, in known manner, a compression assembly comprising an air inlet duct and at least one air compression stage, or compressor, which comprises at least one mobile compressor wheel on which the duct opens.

De tels assemblages de compression présentent une limite de stabilité aérodynamique, communément appelée ligne de pompage, qui limite notamment les capacités d'accélération du turbomoteur. Aux bas régimes de fonctionnement, la limite de stabilité aérodynamique de l'assemblage de compression est liée à une surcharge aérodynamique du premier étage de compression, ce qui se traduit par des incidences trop fortes du flux d'air atteignant la première roue mobile.Such compression assemblies have an aerodynamic stability limit, commonly known as a pumping line, which limits in particular the acceleration capabilities of the turbine engine. At low operating speeds, the aerodynamic stability limit of the compression assembly is related to an aerodynamic overload of the first compression stage, which results in too high incidences of the air flow reaching the first moving wheel.

Une solution connue, décrite dans la demande de brevet FR2970508 déposée par la Demanderesse, consiste à monter une grille, dite de pré-rotation, dans le conduit d'entrée d'air du turbomoteur en amont de la première roue mobile du compresseur pour diminuer l'incidence du flux d'air atteignant ladite première roue mobile en l'orientant dans le sens de rotation de la première roue mobile.A known solution, described in the patent application FR2970508 filed by the Applicant, consists in mounting a gate, said pre-rotation, in the air intake duct of the turbine engine upstream of the first mobile wheel of the compressor to reduce the incidence of the air flow reaching said first moving wheel by orienting it in the direction of rotation of the first moving wheel.

Une telle grille de pré-rotation comprend des pales de guidage d'entrée orientables, dites à calage variable, montées sur un carter et équiréparties dans le conduit d'entrée d'air. Le calage de la grille, c'est-à-dire l'orientation des pales, s'effectue via un anneau de commande et permet de réguler la vitesse du flux d'air en entrée de la roue mobile de manière à adapter l'incidence du flux d'air atteignant la première roue mobile.Such a pre-rotation grid comprises steerable, variable-pitch inlet guide vanes mounted on a casing and equidistributed in the air intake duct. The setting of the gate, that is to say the orientation of the blades, is effected via a control ring and allows to regulate the speed of the air flow at the inlet of the impeller so as to adapt the incidence of airflow reaching the first moving wheel.

Un agencement connu d'une telle grille de pré-rotation consiste à disposer les pales de la grille de sorte que l'angle de pré-rotation des pales et donc l'angle d'orientation du flux d'air soit évolutif selon la hauteur dans le conduit d'air, l'angle d'orientation du flux d'air étant défini comme étant la déviation relative du flux d'air par une pale de la grille de pré-rotation à une hauteur donnée du conduit d'air. En d'autres termes, l'angle d'orientation du flux d'air varie avec la distance radiale dans le conduit d'entrée d'air par rapport à l'axe du turbomoteur.A known arrangement of such a pre-rotation grid is to arrange the blades of the grid so that the pre-rotation angle of the blades and thus the orientation angle of the airflow is scalable according to the height in the air duct, the airflow orientation angle being defined as the relative deviation of the airflow by a blade of the pre-rotation grid to a given height of the air duct. In other words, the angle of orientation of the air flow varies with the radial distance in the air inlet duct relative to the axis of the turbine engine.

Les figures 1 à 3 illustrent une vue schématique en section transversale au niveau de la tête d'un agencement de deux pales 10 d'une grille de pré-rotation 5 et de deux pales 20 d'une roue mobile de compresseur 15 de l'art antérieur. Les pales 10 consécutives de la grille 5 sont espacées d'une distance S1 appelée «pas ». Chaque pale 10 possède une section courbe et définit une corde C1 entre l'extrémité amont et l'extrémité aval des pales 10, c'est-à-dire entre le bord d'attaque et le bord de fuite de la pale 10.The Figures 1 to 3 illustrate a diagrammatic cross-sectional view at the head of an arrangement of two blades 10 of a pre-rotation grid 5 and two blades 20 of a compressor moving wheel 15 of the prior art. The consecutive blades 10 of the grid 5 are spaced apart by a distance S1 called "pitch". Each blade 10 has a curved section and defines a rope C1 between the upstream end and the downstream end of the blades 10, that is to say between the leading edge and the trailing edge of the blade 10.

Lorsque la grille de pré-rotation 5 est ouverte dans les hauts régimes de fonctionnement du compresseur, par exemple pour une valeur de calage de l'anneau de commande (non représenté) de la grille de pré-rotation 5 égale à 0°, l'angle de pré-rotation des pales 10 de la grille 5 est usuellement compris entre des valeurs de l'ordre de 0° en bas du conduit d'air et jusqu'à 15° environ en haut du conduit d'air (par rapport à l'axe X'X). Le flux d'air F entrant dans la grille est alors dévié d'un angle d'orientation α1 proche de l'angle de pré-rotation des pales et compris entre 0° à 15° suivant la hauteur dans le conduit d'air avec une vitesse absolue V1 en sortie de grille dont la composante axiale (selon l'axe X'X) est Vz1. Un tel calage de la grille 5 est utilisé pour les hauts régimes de fonctionnement du compresseur, notamment en régime de fonctionnement maximal, par exemple, en régime de décollage dans le cas d'un turbomoteur d'hélicoptère.When the pre-rotation gate 5 is open in the high operating speeds of the compressor, for example for a setting value of the control ring (not shown) of the pre-rotation gate 5 equal to 0 °, pre-rotation angle of the blades 10 of the gate 5 is usually between values of the order of 0 ° at the bottom of the air duct and up to about 15 ° at the top of the air duct (relative to to the axis X'X). The flow of air F entering the grid is then deviated by an angle of orientation α 1 close to the pre-rotation angle of the blades and between 0 ° to 15 ° according to the height in the air duct with an absolute speed V 1 at the gate exit whose axial component (along the axis X'X) is Vz1. Such calibration of the grid 5 is used for the high operating speeds of the compressor, especially in maximum operating conditions, for example, in the take-off mode in the case of a helicopter turbine engine.

A bas régimes de fonctionnement du compresseur, comme illustré sur la figure 2, la grille 5 est au moins partiellement fermée afin de diminuer la charge aérodynamique et d'augmenter la marge au pompage en décalant la ligne de pompage du compresseur vers les faibles débits tout en décalant la ligne de fonctionnement vers les hauts débits, ce qui permet d'obtenir une grande capacité d'accélération du turbomoteur. Dans un tel agencement, l'anneau de commande (non représenté) de la grille de pré-rotation 5 est usuellement réglé à une valeur, par exemple environ 65°, pour laquelle l'angle de pré-rotation des pales 10 de la grille 5 est compris entre 65° et 80° suivant la hauteur du flux dans le conduit d'air.At low operating speeds of the compressor, as shown in figure 2 , the gate 5 is at least partially closed in order to reduce the aerodynamic load and to increase the pumping margin by shifting the compressor pumping line to the low flow rates while shifting the operating line towards the high flow rates, which allows to obtain a large capacity of acceleration of the turbine engine. In such an arrangement, the control ring (not shown) of the pre-rotation grid 5 is usually set to a value, for example about 65 °, for which the pre-rotation angle of the blades 10 of the grid 5 is between 65 ° and 80 ° depending on the height of the flow in the air duct.

A hauts régimes de fonctionnement du turbomoteur (grille ouverte), lorsque la vitesse relative W1 du flux d'air atteignant la première roue mobile 15 du compresseur en haut de le conduit d'air est élevée, par exemple telle que le nombre de Mach relatif en tête de la roue mobile est supérieur à 1.4, il conviendrait d'augmenter l'angle de pré-rotation des pales 10 de la grille 5 au-delà de 15° en haut du conduit d'air, par exemple jusqu'à 20°, afin de réduire notablement la vitesse relative W1 de l'air en entrée de la roue mobile 15 et ainsi d'améliorer très sensiblement le rendement de l'étage de compression.At high operating speeds of the turbine engine (open grid), when the relative speed W 1 of the air flow reaching the first mobile wheel 15 of the compressor at the top of the air duct is high, for example such as the relative Mach number at the head of the moving wheel is greater than 1.4, it would be advisable to increase the pre-rotation angle of the blades 10 of the gate 5 beyond 15 ° at the top of the air duct, for example up to 20 °, in order to significantly reduce the relative speed W1 of the inlet air of the impeller 15 and thus very substantially improve the efficiency of the compression stage.

Cependant, avec un tel agencement, lorsque l'anneau de commande de la grille de pré-rotation 5 est réglé à une valeur de fermeture de la grille 5, par exemple environ 65°, à bas régimes, comme illustré par la figure 2, l'angle de pré-rotation des pales atteint des valeurs de l'ordre de 85° en haut du conduit d'air, c'est-à-dire que le flux d'air est dévié d'un angle d'orientation α1 proche d'environ 85° par les pales 10 dans la partie la plus haute du conduit, notamment au niveau de l'extrémité distale des pales 10. Dans un tel cas, la vitesse axiale Vz1, selon l'axe X'X, du flux d'air en sortie de grille de pré-rotation 5 en haut du conduit d'air devient si faible qu'elle peut provoquer un dysfonctionnement aérodynamique des pales 20 de la roue mobile 15 du compresseur. En d'autres termes, les couches limites de l'air ne tiennent plus sur la forme des profils de tête des pales 20 de la roue mobile 15, ce qui peut entrainer un décollement aérodynamique au sein de la roue mobile 15, communément appelé décollement tournant, préjudiciable à la stabilité aérodynamique du compresseur, et présente donc un inconvénient.However, with such an arrangement, when the control ring of the pre-rotation gate 5 is set to a closing value of the gate 5, for example about 65 °, at low speeds, as illustrated by FIG. figure 2 , the pre-rotation angle of the blades reaches values of the order of 85 ° at the top of the air duct, that is to say that the flow of air is deflected from an orientation angle α1 close to about 85 ° by the blades 10 in the highest part of the duct, in particular at the distal end of the blades 10. In such a case, the axial speed Vz1 along the axis X'X, the air flow at the outlet of the pre-rotation grid 5 at the top of the air duct becomes so low that it can cause an aerodynamic malfunction of the blades 20 of the mobile wheel 15 of the compressor. In other words, the air boundary layers no longer hold on the shape of the blade head profiles 20 of the impeller 15, which can lead to aerodynamic detachment within the impeller 15, commonly known as detachment rotating, detrimental to the aerodynamic stability of the compressor, and therefore has a disadvantage.

Une solution immédiate pour éliminer cet inconvénient serait d'opérer un réglage de l'anneau de commande à une valeur inférieure à bas régimes, par exemple de l'ordre de 50° ou 60°, dans le but de fermer un peu moins la grille de pré-rotation et d'augmenter ainsi la vitesse axiale Vz1 du flux d'air en haut du conduit d'air. Toutefois, un tel réglage diminuerait les angles d'orientation du flux d'air pour le reste de la hauteur du conduit d'air, ce qui présente un inconvénient. Une autre solution connue est décrite dans le WO 98/09066 .An immediate solution to eliminate this drawback would be to make a setting of the control ring to a lower value at low speeds, for example of the order of 50 ° or 60 °, in order to close a little less the grid pre-rotation and thus increase the axial velocity Vz1 of the air flow at the top of the air duct. However, such a setting would decrease the angles of orientation of the air flow for the rest of the height of the air duct, which has a disadvantage. Another known solution is described in WO 98/09066 .

EXPOSÉ DE L'INVENTIONSTATEMENT OF THE INVENTION

L'invention vise à améliorer la structure des grilles de pré-rotation existantes en augmentant l'angle de pré-rotation des pales au-delà de 15° en haut du conduit d'air à haut régime de fonctionnement du turbomoteur tout en évitant les dysfonctionnements aérodynamiques des pales de la roue mobile à bas régime de fonctionnement du turbomoteur.The aim of the invention is to improve the structure of the existing pre-rotation gates by increasing the pre-rotation angle of the blades above 15 ° at the top of the air duct at high operating speed of the turbine engine while avoiding the aerodynamic malfunctions of the blades of the moving wheel at low operating speed of the turbine engine.

Bien que l'invention ait été conçue pour un turbomoteur d'aéronef, elle concerne tout assemblage de compression d'une turbomachine comprenant une grille de pré-rotation tel qu'il en existe dans les turbomoteurs, les turboréacteurs, les unités de puissance auxiliaires (Auxiliary Power Unit ou APU en anglais), les turbomachines terrestres, les turbocompresseurs etc. Elle concerne également tout type de compresseur qu'il soit axial, centrifuge, mixte etc.Although the invention was designed for an aircraft turbine engine, it relates to any compression assembly of a turbomachine comprising a pre-rotation grid such as exists in the turboshaft engines, turbojets, auxiliary power units. (Auxiliary Power Unit or APU in English), land-based turbomachines, turbochargers etc. It also relates to any type of compressor that is axial, centrifugal, mixed etc.

Ainsi, l'invention a pour objet un assemblage de compression pour une turbomachine, notamment un turbomoteur, selon la revendication 1.Thus, the subject of the invention is a compression assembly for a turbomachine, in particular a turbine engine, according to claim 1.

Par le terme « pas », on entend la distance entre deux points identiques de deux pales de la grille disposées consécutivement. Par le terme « corde », on entend la distance du segment s'étendant entre l'extrémité amont et l'extrémité aval d'une pale de la grille de pré-rotation, c'est à dire entre l'extrémité du bord d'attaque et l'extrémité du bord de fuite d'une pale de la grille de pré-rotation. Par les termes « amont » et « aval », on entend par rapport au sens du flux d'air circulant dans la turbomachine.The term "pitch" means the distance between two identical points of two blades of the grid arranged consecutively. By the term "rope" is meant the distance of the segment extending between the upstream end and the downstream end of a blade of the pre-rotation grid, that is to say between the end of the edge of the attack and the end of the trailing edge of a blade of the pre-rotation grid. By the terms "upstream" and "downstream" is meant in relation to the direction of the flow of air flowing in the turbomachine.

Avantageusement, le pas entre deux pales consécutives est supérieur à la corde d'une des deux pales dans la partie haute du conduit d'air, par exemple au niveau des extrémités distales desdites pales. Par les termes « partie haute du conduit d'air », on entend la partie du conduit d'air la plus éloignée radialement de l'axe longitudinal du turbomoteur. Par les termes « en haut du conduit d'air », on entend l'extrémité distale de la pale par rapport à l'axe longitudinal du turbomoteur. De même, par les termes « partie basse du conduit », on entend la partie du conduit la plus proche de l'axe longitudinal du turbomoteur. Par les termes « en bas du conduit d'air », on entend l'extrémité proximale de la pale par rapport à l'axe longitudinal du turbomoteur.Advantageously, the pitch between two consecutive blades is greater than the rope of one of the two blades in the upper part of the air duct, for example at the distal ends of said blades. By the terms "upper part of the air duct" is meant that part of the air duct furthest radially from the longitudinal axis of the turbine engine. By the terms "at the top of the air duct" is meant the distal end of the blade with respect to the longitudinal axis of the turbine engine. Similarly, the term "lower part of the duct" is the portion of the duct closest to the longitudinal axis of the turbine engine. By the terms "at the bottom of the air duct" is meant the proximal end of the blade with respect to the longitudinal axis of the turbine engine.

Dans les solutions de l'art antérieur, le pas entre les extrémités distales de deux pales consécutives de la grille de pré-rotation était égal ou inférieur à la corde d'une pale de la grille. En d'autres termes, le rapport du pas sur la corde (S1/C1) prenait des valeurs comprises entre 0.9 et 1. Les pales de la grille se chevauchaient alors partiellement en position fermée de la grille ce qui réduisait de manière trop importante la vitesse axiale du flux d'air à bas régimes et entrainaient les dysfonctionnements aérodynamiques susmentionnés.In the solutions of the prior art, the pitch between the distal ends of two consecutive blades of the pre-rotation grid was equal to or less than the string of a blade of the grid. In other words, the ratio of the pitch on the string (S1 / C1) took values between 0.9 and 1. The blades of the grid then overlapped partially in the closed position of the grid which reduced too much the axial speed of the air flow at low speeds and caused the aerodynamic malfunctions mentioned above.

Dans l'assemblage de compression selon l'invention, le pas entre deux pales consécutives de la grille étant supérieur à la corde d'une des deux pales, les pales ne se recouvrent plus en position fermée de la grille comme dans les solutions de l'art antérieur, ce qui permet d'utiliser des pales dont l'angle de pré-rotation est supérieur à 15° dans la partie haute du conduit d'air à hauts régimes de fonctionnement de l'étage de compresseur (avec des calages très ouverts de la grille de pré-rotation) tout en permettant un fonctionnement aérodynamique efficace de la roue mobile du compresseur aux bas régimes (avec des calages très fermés de la grille de pré-rotation).In the compression assembly according to the invention, the pitch between two consecutive blades of the gate being greater than the rope of one of the two blades, the blades do not overlap in the closed position of the grid as in the solutions of the prior art, which allows the use of blades whose pre-rotation angle is greater than 15 ° in the upper part of the air duct at high operating speeds of the compressor stage (with very stable open of the pre-rotation grid) while allowing efficient aerodynamic operation of the mobile wheel of the compressor at low speeds (with very closed wedges of the pre-rotation grid).

Selon une caractéristique de l'invention, l'angle de pré-rotation des pales est supérieur à 15° dans la partie haute du conduit d'air, notamment au niveau de leurs extrémités distales, de préférence compris entre 15°et 25°, lorsque la grille de pré-rotation est en position ouverte de fonctionnement à hauts régimes de l'étage de compression, par exemple pour une valeur de calage de l'anneau de commande de la grille de 0°. Ainsi, quand la vitesse relative du flux d'air atteignant la première roue mobile du compresseur est élevée, par exemple telle que le nombre de Mach relatif en tête de la roue mobile est supérieur à 1.4, une telle plage de valeurs d'angle de pré-rotation des pales de la grille dans la partie haute du conduit d'air permet de réduire suffisamment la vitesse relative du flux d'air en régime de fonctionnement maximal du compresseur de sorte à améliorer notablement le rendement de l'étage de compression.According to one characteristic of the invention, the pre-rotation angle of the blades is greater than 15 ° in the upper part of the air duct, in particular at their distal ends, preferably between 15 ° and 25 °, when the pre-rotation grid is in the open position of operation at high speeds of the compression stage, for example for a setting value of the gate control ring of 0 °. Thus, when the relative velocity of the airflow reaching the first mobile wheel of the compressor is high, for example such that the relative Mach number at the head of the moving wheel is greater than 1.4, such a range of values of angle of pre-rotation of the blades of the grid in the upper part of the air duct makes it possible to sufficiently reduce the relative speed of the air flow at the maximum operating speed of the compressor so as to appreciably improve the efficiency of the compression stage.

De préférence, l'angle de pré-rotation des pales est compris entre 80° et 90° dans la partie haute du conduit d'air, notamment au niveau de leurs extrémités distales, lorsque la grille de pré-rotation est en position fermée de fonctionnement à bas régimes de l'étage de compression, par exemple pour une valeur de calage de l'anneau de commande de la grille de 65°. Dans un tel cas, étant donné que le pas entre deux pales consécutives est supérieur à la corde d'une pale, l'espacement des pales en position fermée de la grille permet d'obtenir une vitesse axiale du flux d'air supérieure à la vitesse axiale du flux dans un assemblage de l'art antérieur pour un même calage de l'anneau de commande de la grille de pré-rotation. En d'autres termes, l'espacement des pales permet d'augmenter la vitesse axiale du flux d'air traversant la grille de pré-rotation, notamment avec des calages très fermés, de manière à éviter les dysfonctionnements aérodynamiques des pales de la roue mobile de compresseur.Preferably, the pre-rotation angle of the blades is between 80 ° and 90 ° in the upper part of the air duct, in particular at their distal ends, when the pre-rotation grid is in the closed position of operating at low speeds of the compression stage, for example for a setting value of the gate control ring of 65 °. In such a case, since the pitch between two consecutive blades is greater than the rope of a blade, the spacing of the blades in the closed position of the grid makes it possible to obtain an axial speed of the air flow greater than the axial velocity of the flux in a assembly of the prior art for the same setting of the control ring of the pre-rotation grid. In other words, the spacing of the blades makes it possible to increase the axial speed of the flow of air passing through the pre-rotation grid, in particular with very closed wedges, so as to avoid aerodynamic malfunctions of the blades of the wheel. mobile compressor.

De manière préférée, les pales de la grille s'étendent radialement par rapport à l'axe de la turbomachine et sont configurées de sorte que l'angle de pré-rotation des pales de la grille de pré-rotation évolue dans le conduit d'air avec la distance radiale. Pour ce faire, les pales peuvent être par exemple torsadées.In a preferred manner, the blades of the gate extend radially with respect to the axis of the turbomachine and are configured so that the pre-rotation angle of the blades of the pre-rotation gate changes in the duct. air with radial distance. To do this, the blades can be twisted, for example.

De préférence, l'angle de pré-rotation est environ égale à 0° en bas du conduit d'air, c'est-à-dire au plus près radialement de l'axe du turbomoteur, et de l'ordre de 25° en haut du conduit d'air, c'est-à-dire au plus loin radialement de l'axe du turbomoteur, pour une valeur de calage de l'anneau de commande de la grille de 0°.Preferably, the pre-rotation angle is approximately equal to 0 ° at the bottom of the air duct, that is to say as close as radially to the axis of the turbine engine, and of the order of 25 ° at the top of the air duct, that is to say at most radially from the axis of the turbine engine, for a setting value of the gate control ring of 0 °.

Selon un aspect de l'invention, la corde des pales est constante parmi la pluralité de pales de la grille de pré-rotation.According to one aspect of the invention, the blade string is constant among the plurality of blades of the pre-rotation grid.

Selon une caractéristique de l'invention, la grille de pré-rotation est positionnée dans une partie radiale, un coude ou une partie axiale du conduit d'entrée d'air. Les termes « partie radiale » et « partie axiale » s'entendant par rapport à l'axe de la turbomachine.According to one characteristic of the invention, the pre-rotation grid is positioned in a radial portion, a bend or an axial portion of the air intake duct. The terms "radial portion" and "axial portion" meaning in relation to the axis of the turbomachine.

Avantageusement, les pales sont disposées de manière équiréparties dans le conduit d'entrée d'air. En d'autres termes, le pas entre les pales de la grille est constant.Advantageously, the blades are arranged equidistributed in the air inlet duct. In other words, the pitch between the blades of the grid is constant.

L'invention concerne aussi une turbomachine selon la revendication 7, tel que, par exemple, un turbomoteur, notamment pour un aéronef tel que, par exemple, un hélicoptère, comprenant un conduit d'entrée d'air apte à recevoir un flux d'air, au moins un étage de compression d'air comprenant au moins une roue mobile de compresseur sur laquelle débouche le conduit et une grille de pré-rotation, positionnée dans le conduit d'entrée d'air en amont de la roue mobile de compresseur pour réguler la vitesse de l'air dudit flux en entrée de la roue mobile et comprenant une pluralité de pales à calage variable, l'assemblage étant remarquable en ce que le pas entre deux pales consécutives de la grille est supérieur à la corde d'une des deux pales à une hauteur donnée, de préférence dans la partie haute, du conduit d'air.The invention also relates to a turbomachine according to claim 7, such as, for example, a turbine engine, particularly for an aircraft such as, for example, a helicopter, comprising an air inlet duct adapted to receive a flow of air. air, at least one air compression stage comprising at least one mobile compressor wheel on which the duct opens and a pre-rotation grille, positioned in the air intake duct upstream of the mobile compressor wheel for regulating the air speed of said flow at the inlet of the moving wheel and comprising a plurality of variable-pitch blades, the assembly being remarkable in that the pitch between two consecutive blades of the gate is greater than the rope of one of the two blades at a given height, preferably in the upper part, of the air duct.

L'invention concerne aussi un procédé de commande d'une grille de pré-rotation d'un assemblage de compression, tel que défini dans la revendication 8, comprenant un conduit d'entrée d'air apte à recevoir un flux d'air, au moins un étage de compression d'air comprenant au moins une roue mobile de compresseur sur laquelle débouche le conduit et une grille de pré-rotation, positionnée dans le conduit d'entrée d'air en amont de la roue mobile de compresseur pour réguler la vitesse de l'air dudit flux en entrée de la roue mobile et comprenant une pluralité de pales à calage variable, le procédé étant remarquable en ce que, le pas entre deux pales consécutives de la grille étant supérieur à la corde d'une des deux pales à une hauteur donnée du conduit d'air, de préférence dans sa partie haute notamment au niveau de leurs extrémités distales, on positionne les pales de la grille selon un angle de pré-rotation entre 80° et 90° à bas régimes de fonctionnement de l'étage de compression.The invention also relates to a method for controlling a pre-rotation grid of a compression assembly, as defined in claim 8, comprising an air intake duct adapted to receive a flow of air, at least one air compression stage comprising at least one mobile compressor wheel on which the duct opens and a pre-rotation grille, positioned in the air intake duct upstream of the mobile compressor wheel for regulating the air speed of said flow at the inlet of the moving wheel and comprising a plurality of variable pitch blades, the method being remarkable in that, the pitch between two consecutive blades of the gate being greater than the rope of one of the two blades at a given height of the air duct, preferably in its upper part in particular at their distal ends, is positioned the blades of the grid at a pre-rotation angle between 80 ° and 90 ° at low speeds of functioning of the compression stage.

L'invention concerne aussi un procédé de commande d'une grille de pré-rotation d'un assemblage de compression, tel que défini ci-dessus, comprenant un conduit d'entrée d'air apte à recevoir un flux d'air, au moins un étage de compression d'air comprenant au moins une roue mobile de compresseur sur laquelle débouche le conduit et une grille de pré-rotation, positionnée dans le conduit d'entrée d'air en amont de la roue mobile de compresseur pour réguler la vitesse de l'air dudit flux en entrée de la roue mobile et comprenant une pluralité de pales à calage variable, le procédé étant remarquable en ce que, le pas entre deux pales consécutives de la grille étant supérieur à la corde d'une des deux pales à une hauteur donnée du conduit d'air, de préférence dans sa partie haute notamment au niveau de leurs extrémités distales, on positionne les pales de la grille selon un angle de pré-rotation supérieur à 15°, de préférence compris entre 15° et 25°, à hauts régimes de fonctionnement de l'étage de compression.The invention also relates to a method for controlling a pre-rotation grid of a compression assembly, as defined above, comprising an air intake duct adapted to receive an air flow, at the least one air compression stage comprising at least one mobile compressor wheel on which the duct opens and a pre-rotation grille, positioned in the air inlet duct upstream of the mobile compressor wheel to regulate the air speed of said flow at the inlet of the moving wheel and comprising a plurality of variable-pitch blades, the method being remarkable in that, the pitch between two consecutive blades of the gate being greater than the rope of one of the two blades at a given height of the air duct, preferably in its upper part, particularly at their distal ends, the blades of the grid are positioned at a pre-rotation angle greater than 15 °, preferably between 15 ° and 25 °, to ha Operating modes of the compression stage.

D'autres caractéristiques et avantages de l'invention apparaîtront lors de la description qui suit faite en regard des figures annexées données à titre d'exemples non limitatifs et dans lesquelles des références identiques sont données à des objets semblables :

  • la figure 1 est une vue en section transversale d'un ensemble formé de deux pales d'une grille de pré-rotation et de deux pales d'une roue mobile d'un turbomoteur de l'art antérieur, la grille de pré-rotation étant en position ouverte;
  • la figure 2 est une vue en section transversale de l'ensemble de la figure 1 dans lequel la grille de pré-rotation est en position fermée;
  • la figure 3 est une vue en section transversale d'un agencement de pales d'une grille de pré-rotation de l'art antérieur ;
  • la figure 4 est une vue en section transversale d'un agencement de pales d'une grille de pré-rotation selon l'invention ;
  • la figure 5 est une vue en section transversale d'un ensemble formé de deux pales d'une grille de pré-rotation et de deux pales d'une roue mobile d'un turbomoteur selon l'invention, la grille de pré-rotation étant en position fermée.
Other features and advantages of the invention will become apparent from the following description made with reference to the appended figures given by way of non-limiting examples and in which identical references are given to similar objects:
  • the figure 1 is a cross-sectional view of an assembly formed of two blades of a pre-rotation grid and two blades of a mobile wheel of a turbine engine of the prior art, the pre-rotation grid being in position opened;
  • the figure 2 is a cross-sectional view of the entire figure 1 wherein the pre-rotation grid is in the closed position;
  • the figure 3 is a cross-sectional view of a blade arrangement of a pre-rotation grid of the prior art;
  • the figure 4 is a cross-sectional view of a blade arrangement of a pre-rotation grid according to the invention;
  • the figure 5 is a cross-sectional view of an assembly formed of two blades of a pre-rotation grid and two blades of a mobile wheel of a turbine engine according to the invention, the pre-rotation grid being in the closed position .

DESCRIPTION DETAILLÉEDETAILED DESCRIPTION

Bien que l'invention ait été réalisée dans le cadre d'un turbomoteur d'hélicoptère, il va de soi qu'elle peut trouver son application dans tout assemblage de compression comprenant une grille de pré-rotation tel qu'il en existe dans les turbomoteurs, les turboréacteurs, les unités de puissance auxiliaires (Auxiliary Power Unit ou APU en anglais), les turbomachines terrestres, les turbocompresseurs etc.Although the invention was carried out in the context of a helicopter turbine engine, it goes without saying that it can find its application in any compression assembly comprising a pre-rotation grid such as exists in the turboshaft engines, turbojets, auxiliary power units (APUs), land-based turbomachines, turbochargers, etc.

L'invention concerne en outre tout type de compresseur qu'il soit axial, centrifuge, mixte etc.The invention further relates to any type of compressor that is axial, centrifugal, mixed etc.

L'assemblage de compression d'une turbomachine selon l'invention comprend un conduit d'entrée d'air apte à recevoir un flux d'air, un étage de compression d'air comprenant une roue mobile de compresseur sur laquelle débouche le conduit et une grille de pré-rotation. La grille de pré-rotation est positionnée dans le conduit d'entrée d'air en amont de la roue mobile de compresseur pour redresser le flux d'air amont qui est dirigé vers la roue mobile et en réguler la vitesse en entrée de la roue mobile. La grille comprend une pluralité de pales à calage variable s'étendant radialement par rapport à l'axe de la turbomachine et disposées dans un même plan transversal perpendiculaire à l'axe de la turbomachine.The compression assembly of a turbomachine according to the invention comprises an air intake duct adapted to receive an air flow, an air compression stage comprising a mobile compressor wheel on which the duct opens and a pre-rotation grid. The pre-rotation grid is positioned in the air intake duct upstream of the mobile compressor wheel to straighten the upstream air flow which is directed towards the moving wheel and regulate the speed at the inlet of the wheel mobile. The gate comprises a plurality of variable-pitch blades extending radially with respect to the axis of the turbomachine and arranged in the same transverse plane perpendicular to the axis of the turbomachine.

En fonctionnement de la turbomachine, l'air pénètre dans le conduit d'entrée d'air, traverse la grille de pré-rotation et est acheminée jusqu'à la roue mobile de compresseur. Le flux d'air comprimé par la roue mobile de compresseur est ensuite injecté dans une chambre de combustion pour y être mélangé au carburant et fournir, après combustion, l'énergie cinétique d'entraînement en rotation d'une ou plusieurs turbines.In operation of the turbomachine, the air enters the air inlet duct, passes through the pre-rotation grid and is conveyed to the compressor impeller. The flow of compressed air by the mobile compressor wheel is then injected into a combustion chamber to be mixed with the fuel and to provide, after combustion, the kinetic energy for rotating one or more turbines.

Il va de soi que la turbomachine peut en outre comprendre d'autres étages de compression disposés entre le premier étage de compression et la chambre de combustion.It goes without saying that the turbomachine may further comprise other compression stages arranged between the first compression stage and the combustion chamber.

Les figures 4 et 5 illustrent en agencement de deux pales 110 d'une grille de pré-rotation 105 selon l'invention. Des moyens de commande (non représentés) de la grille de pré-rotation 105 permettent d'orienter les pales 110 de la grille 105 selon une loi de calage d'ouverture/fermeture des pales 110 qui dépend du régime de rotation de la turbomachine. Une telle loi de calage est réglée pour garantir une marge au pompage minimale entre la ligne de fonctionnement et la ligne de pompage.The Figures 4 and 5 illustrate in the arrangement of two blades 110 of a pre-rotation grid 105 according to the invention. Control means (not shown) of the grid of pre-rotation 105 allow to orient the blades 110 of the gate 105 according to an opening / closing law of the blades 110 which depends on the rotational speed of the turbomachine. Such a calibration law is set to guarantee a minimum pumping margin between the operating line and the pumping line.

Les pales 110 de la grille 105 sont espacées d'un pas S2 et présentent, entre leur extrémité amont et aval, c'est-à-dire entre le bord d'attaque et le bord de fuite, une courbure définissant une corde C2.The blades 110 of the grid 105 are spaced apart by a pitch S2 and have, between their upstream and downstream end, that is to say between the leading edge and the trailing edge, a curvature defining a rope C2.

Comme illustré par la figure 5, la grille de pré-rotation 105 est disposée en amont, selon le sens global du flux d'air F, des pales 120 de la roue mobile 115 de compresseur. La roue mobile 115 est entrainée en rotation selon le vecteur vitesse U de manière à accélérer le flux d'air dévié par la grille de pré-rotation.As illustrated by figure 5 , the pre-rotation gate 105 is arranged upstream, in the overall direction of the air flow F, the blades 120 of the mobile wheel 115 of the compressor. The moving wheel 115 is rotated according to the speed vector U so as to accelerate the flow of air deflected by the pre-rotation grid.

Selon l'invention, le pas S2 entre deux pales 110 consécutives de la grille 5 est supérieur à la corde C2 des pales 110 de la grille 5 en haut du conduit d'air de sorte que les pales 110 ne se recouvrent pas en position fermée de la grille 105. Le rapport du pas S2 sur la corde C2, c'est-à-dire le paramètre S2/C2, peut prendre des valeurs comprises entre 1 et 1.5.According to the invention, the pitch S2 between two consecutive blades 110 of the grid 5 is greater than the rope C2 of the blades 110 of the grid 5 at the top of the air duct so that the blades 110 do not overlap in the closed position of the grid 105. The ratio of the pitch S2 on the chord C2, that is to say the parameter S2 / C2, can take values comprised between 1 and 1.5.

Ainsi, à hauts régimes de fonctionnement du compresseur (grille ouverte), des valeurs d'angle de pré-rotation du flux d'air a2 comprises entre 15° et 25° en haut du conduit d'air permettent de diminuer notablement la vitesse relative W2 de l'air en entrée de la roue mobile 115 et ainsi d'améliorer très sensiblement le rendement de l'étage de compression.Thus, at high operating speeds of the compressor (open grid), pre-rotation angle values of the air flow a2 between 15 ° and 25 ° at the top of the air duct make it possible to significantly reduce the relative speed. W2 air inlet of the impeller 115 and thus very substantially improve the efficiency of the compression stage.

A bas régimes de fonctionnement du compresseur (grille fermée), l'espacement des pales 110 de la grille 105 permet, malgré des valeurs d'angle de pré-rotation des pales comprises entre 80 et 90° en haut du conduit d'air, d'obtenir des angles de pré-rotation du flux d'air a2 plus faibles et ainsi de conserver une vitesse axiale Vz2 suffisamment élevée pour éviter les dysfonctionnements aérodynamiques de la roue mobile 115 du compresseur aux bas régimes avec des calages très fermés de la grille de pré-rotation 105.At low operating speeds of the compressor (closed grid), the spacing of the blades 110 of the grid 105 allows, despite pre-rotation angle values of the blades between 80 and 90 ° at the top of the air duct, to obtain pre-rotation angles of the air flow a2 lower and thus to maintain an axial velocity Vz2 sufficiently high to avoid aerodynamic malfunctions of the mobile wheel 115 of the compressor at low speeds with very closed wedges of the grid pre-rotation 105.

En effet, comme illustré à la figure 5, l'augmentation du pas S2 par comparaison à l'art antérieur permet de limiter la déviation du flux d'air circulant entre le bord d'attaque BA d'une pale 110 et le bord de fuite BF d'une pale 110 consécutive de la grille de pré-rotation 105.Indeed, as illustrated in figure 5 , the increase of the pitch S2 compared with the prior art makes it possible to limit the deflection of the flow of air flowing between the leading edge BA of a blade 110 and the trailing edge BF of a blade 110 consecutive from the pre-rotation grid 105.

Claims (9)

  1. Compression assembly for a turbine engine, in particular a turboshaft engine, said assembly comprising an air inlet duct capable of receiving an air flow, at least one air compression stage comprising at least one movable compressor wheel (115) onto which the duct discharges, and a pre-rotation grille (105) which is positioned in the air inlet duct upstream of the movable compressor wheel (115) in order to adjust the speed of the air in said flow at the inlet of the movable wheel and comprises a plurality of variable-setting vanes (110), the pitch (S2) between two consecutive vanes (110) of the grille (105) being greater than the chord (C2) of one of the two vanes (110) at a given height of the air duct in its upper part, the assembly being characterised in that the pre-rotation angle of the vanes (110) is between 80° and 90° in the upper part of the air duct when the pre-rotation grille (105) is in the closed operating position at low speeds of the compression stage.
  2. Compression assembly according to claim 1, wherein the pre-rotation angle of the vanes (110) is greater than 15° in the upper part of the air duct, preferably between 15° and 25°, when the pre-rotation grille (105) is in the open operating position at high speeds of the compression stage.
  3. Compression assembly according to any of the preceding claims, wherein the pre-rotation angle of the vanes (110) of the pre-rotation grille (105) changes depending on the radial distance in the air duct.
  4. Compression assembly according to the preceding claim, wherein the pre-rotation angle is approximately 0° at the bottom of the air duct and is approximately 25° at the top of the air duct for a setting value of the control ring of the grille of 0°.
  5. Compression assembly according to any of the preceding claims, wherein the chord (C2) of the vanes (110) is constant for the plurality of vanes (110) of the pre-rotation grille (105).
  6. Compression assembly according to any of the preceding claims, wherein the vanes (110) are evenly distributed within the air inlet duct.
  7. Turbine engine, in particular for an aircraft, comprising the compression assembly as defined according to any of the preceding claims.
  8. Method for controlling a pre-rotation grille (105) of a compression assembly according to any of claims 1 to 6 comprising an air inlet duct capable of receiving an air flow, at least one air compression stage comprising at least one movable compressor wheel (115) onto which the duct discharges, and a pre-rotation grille (105) which is positioned in the air inlet duct upstream of the movable compressor wheel (115) in order to adjust the speed of the air in said flow at the inlet of the movable wheel (115) and comprising a plurality of variable-setting vanes (110), the pitch (S2) between two consecutive vanes (110) of the grille (105) being greater than the chord (C2) of one of the two vanes (110) at a given height of the air duct, the method being characterised in that in the upper part of the air duct, the vanes (110) of the grille (105) are positioned at a pre-rotation angle of between 80° and 90° at low operating speeds of the compression stage.
  9. Method according to claim 8, wherein the vanes (110) of the grille (105) are further positioned at a pre-rotation angle of greater than 15°, preferably of between 15° and 25°, in the upper part of the air duct and at high operating speeds of the compression stage.
EP13795842.7A 2012-11-09 2013-11-07 Compression assembly for a turbine engine Active EP2917590B1 (en)

Priority Applications (1)

Application Number Priority Date Filing Date Title
PL13795842T PL2917590T3 (en) 2012-11-09 2013-11-07 Compression assembly for a turbine engine

Applications Claiming Priority (2)

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FR1260637A FR2998012B1 (en) 2012-11-09 2012-11-09 COMPRESSION ASSEMBLY FOR TURBOMACHINE
PCT/FR2013/052660 WO2014072642A1 (en) 2012-11-09 2013-11-07 Compression assembly for a turbine engine

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EP2917590A1 EP2917590A1 (en) 2015-09-16
EP2917590B1 true EP2917590B1 (en) 2019-03-20

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US (1) US10352179B2 (en)
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JP (1) JP6352284B2 (en)
KR (1) KR102197775B1 (en)
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CA (1) CA2887119C (en)
FR (1) FR2998012B1 (en)
IN (1) IN2015DN03015A (en)
PL (1) PL2917590T3 (en)
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US11268453B1 (en) 2021-03-17 2022-03-08 Pratt & Whitney Canada Corp. Lubrication system for aircraft engine reduction gearbox

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US11174916B2 (en) 2019-03-21 2021-11-16 Pratt & Whitney Canada Corp. Aircraft engine reduction gearbox
US11268453B1 (en) 2021-03-17 2022-03-08 Pratt & Whitney Canada Corp. Lubrication system for aircraft engine reduction gearbox

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KR102197775B1 (en) 2021-01-04
CA2887119A1 (en) 2014-05-15
CN104884816B (en) 2017-03-22
US10352179B2 (en) 2019-07-16
JP2015535049A (en) 2015-12-07
RU2651103C2 (en) 2018-04-18
CN104884816A (en) 2015-09-02
WO2014072642A1 (en) 2014-05-15
IN2015DN03015A (en) 2015-10-02
FR2998012B1 (en) 2018-07-13
FR2998012A1 (en) 2014-05-16
US20150275681A1 (en) 2015-10-01
PL2917590T3 (en) 2019-07-31
CA2887119C (en) 2021-01-19
EP2917590A1 (en) 2015-09-16
KR20150082223A (en) 2015-07-15
RU2015115157A (en) 2017-01-10
JP6352284B2 (en) 2018-07-04

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