EP4121636A1 - Turbomachine compressor having a stationary wall provided with a shape treatment - Google Patents

Turbomachine compressor having a stationary wall provided with a shape treatment

Info

Publication number
EP4121636A1
EP4121636A1 EP21731220.6A EP21731220A EP4121636A1 EP 4121636 A1 EP4121636 A1 EP 4121636A1 EP 21731220 A EP21731220 A EP 21731220A EP 4121636 A1 EP4121636 A1 EP 4121636A1
Authority
EP
European Patent Office
Prior art keywords
wall
grooves
compressor
fixed
blades
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.)
Pending
Application number
EP21731220.6A
Other languages
German (de)
French (fr)
Inventor
Fabien Jean-Michel ARTUS
Laurent Pierre Tarnowski
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
Safran Helicopter Engines SAS
Priority date (The priority date is an assumption and is not a legal conclusion. Google has not performed a legal analysis and makes no representation as to the accuracy of the date listed.)
Filing date
Publication date
Application filed by Safran Helicopter Engines SAS filed Critical Safran Helicopter Engines SAS
Publication of EP4121636A1 publication Critical patent/EP4121636A1/en
Pending legal-status Critical Current

Links

Classifications

    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F01—MACHINES OR ENGINES IN GENERAL; ENGINE PLANTS IN GENERAL; STEAM ENGINES
    • F01D—NON-POSITIVE DISPLACEMENT MACHINES OR ENGINES, e.g. STEAM TURBINES
    • F01D17/00—Regulating or controlling by varying flow
    • F01D17/10—Final actuators
    • F01D17/12—Final actuators arranged in stator parts
    • F01D17/14—Final actuators arranged in stator parts varying effective cross-sectional area of nozzles or guide conduits
    • F01D17/16—Final actuators arranged in stator parts varying effective cross-sectional area of nozzles or guide conduits by means of nozzle vanes
    • F01D17/162—Final actuators arranged in stator parts varying effective cross-sectional area of nozzles or guide conduits by means of nozzle vanes for axial flow, i.e. the vanes turning around axes which are essentially perpendicular to the rotor centre line
    • 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
    • F01D11/00—Preventing or minimising internal leakage of working-fluid, e.g. between stages
    • F01D11/08—Preventing or minimising internal leakage of working-fluid, e.g. between stages for sealing space between rotor blade tips and stator
    • 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
    • F01D17/00—Regulating or controlling by varying flow
    • F01D17/10—Final actuators
    • F01D17/12—Final actuators arranged in stator parts
    • F01D17/14—Final actuators arranged in stator parts varying effective cross-sectional area of nozzles or guide conduits
    • F01D17/16—Final actuators arranged in stator parts varying effective cross-sectional area of nozzles or guide conduits by means of nozzle vanes
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F01—MACHINES OR ENGINES IN GENERAL; ENGINE PLANTS IN GENERAL; STEAM ENGINES
    • F01D—NON-POSITIVE DISPLACEMENT MACHINES OR ENGINES, e.g. STEAM TURBINES
    • F01D5/00—Blades; Blade-carrying members; Heating, heat-insulating, cooling or antivibration means on the blades or the members
    • F01D5/12—Blades
    • F01D5/14—Form or construction
    • F01D5/141—Shape, i.e. outer, aerodynamic form
    • F01D5/142—Shape, i.e. outer, aerodynamic form of the blades of successive rotor or stator blade-rows
    • F01D5/143—Contour of the outer or inner working fluid flow path wall, i.e. shroud or hub contour
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • 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
    • F04D29/522—Casings; Connections of working fluid for axial pumps especially adapted for elastic fluid pumps
    • F04D29/526—Details of the casing section radially opposing blade tips
    • 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
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F04—POSITIVE - DISPLACEMENT MACHINES FOR LIQUIDS; PUMPS FOR LIQUIDS OR ELASTIC FLUIDS
    • F04D—NON-POSITIVE-DISPLACEMENT PUMPS
    • F04D29/00—Details, component parts, or accessories
    • F04D29/66—Combating cavitation, whirls, noise, vibration or the like; Balancing
    • F04D29/68—Combating cavitation, whirls, noise, vibration or the like; Balancing by influencing boundary layers
    • F04D29/681—Combating cavitation, whirls, noise, vibration or the like; Balancing by influencing boundary layers especially adapted for elastic fluid pumps
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F04—POSITIVE - DISPLACEMENT MACHINES FOR LIQUIDS; PUMPS FOR LIQUIDS OR ELASTIC FLUIDS
    • F04D—NON-POSITIVE-DISPLACEMENT PUMPS
    • F04D29/00—Details, component parts, or accessories
    • F04D29/66—Combating cavitation, whirls, noise, vibration or the like; Balancing
    • F04D29/68—Combating cavitation, whirls, noise, vibration or the like; Balancing by influencing boundary layers
    • F04D29/681—Combating cavitation, whirls, noise, vibration or the like; Balancing by influencing boundary layers especially adapted for elastic fluid pumps
    • F04D29/685—Inducing localised fluid recirculation in the stator-rotor interface
    • 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
    • F05D2220/00—Application
    • F05D2220/30—Application in turbines
    • F05D2220/32—Application in turbines in gas turbines
    • 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
    • F05D2220/00—Application
    • F05D2220/30—Application in turbines
    • F05D2220/32—Application in turbines in gas turbines
    • F05D2220/321—Application in turbines in gas turbines for a special turbine stage
    • F05D2220/3216—Application in turbines in gas turbines for a special turbine stage for a special compressor stage
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F05—INDEXING SCHEMES RELATING TO ENGINES OR PUMPS IN VARIOUS SUBCLASSES OF CLASSES F01-F04
    • F05D—INDEXING SCHEME FOR ASPECTS RELATING TO NON-POSITIVE-DISPLACEMENT MACHINES OR ENGINES, GAS-TURBINES OR JET-PROPULSION PLANTS
    • F05D2240/00—Components
    • F05D2240/10—Stators
    • F05D2240/12—Fluid guiding means, e.g. vanes
    • 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
    • F05D2250/20—Three-dimensional
    • F05D2250/29—Three-dimensional machined; miscellaneous
    • F05D2250/294—Three-dimensional machined; miscellaneous grooved
    • 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
    • F05D2260/00—Function
    • F05D2260/60—Fluid transfer
    • 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
    • F05D2260/00—Function
    • F05D2260/60—Fluid transfer
    • F05D2260/606—Bypassing the fluid
    • Y—GENERAL TAGGING OF NEW TECHNOLOGICAL DEVELOPMENTS; GENERAL TAGGING OF CROSS-SECTIONAL TECHNOLOGIES SPANNING OVER SEVERAL SECTIONS OF THE IPC; TECHNICAL SUBJECTS COVERED BY FORMER USPC CROSS-REFERENCE ART COLLECTIONS [XRACs] AND DIGESTS
    • Y02—TECHNOLOGIES OR APPLICATIONS FOR MITIGATION OR ADAPTATION AGAINST CLIMATE CHANGE
    • Y02T—CLIMATE CHANGE MITIGATION TECHNOLOGIES RELATED TO TRANSPORTATION
    • Y02T50/00—Aeronautics or air transport
    • Y02T50/60—Efficient propulsion technologies, e.g. for aircraft

Definitions

  • TITLE Turbomachine compressor comprising a fixed wall provided with a form treatment
  • the invention relates to a stator element of a turbomachine comprising variable-pitch fixed vanes fitted to a compressor of this turbomachine, this compressor being able to be axial or centrifugal, the invention being equally applicable to a turbomachine of the engine type. aircraft than a helicopter turbine-type turbomachine.
  • a turbomachine compressor comprises a rotor rotating around a main axis, which carries several stages of movable blades spaced from each other along this axis, and a fixed casing of revolution surrounding the assembly which is crossed from upstream to downstream by an air flow when the assembly is in service.
  • the assembly is crossed by an air flow circulating in an annular space delimited internally by the rotor and externally by the casing.
  • a stage of fixed blades called a rectifier, making it possible to channel the air longitudinally to unwind it before it enters the next moving stage.
  • a rectifier is in the form of a fixed bladed wheel carried by the housing which locally surrounds the rotor.
  • the blades of one or more of these fixed stages are advantageously with variable pitch, so that their angular position around a radial or inclined axis can be adjusted in order to adapt it to the operating conditions of the turbomachine which fluctuate during its use. .
  • variable pitch fixed blades are controlled by control elements dynamically adjusting their pitch. In general, they make it possible to adapt the fluid flow before admission into the mobile stage which follows them. immediately, to extend the range of operating conditions under which the compressor can be used without risk of aerodynamic stall.
  • the aim of the invention is to provide a solution making it possible to limit the risk of aerodynamic stalling in a compressor comprising a stator carrying variable-pitch blades.
  • the invention relates to a compressor comprising a fixed casing carrying fixed variable-pitch vanes each extending radially from this fixed casing to a rotary hub surrounded by this fixed casing, each variable-timing vane comprising a blade having a base spaced by a radial clearance from a fixed wall of the housing, and in which the fixed wall of the housing comprises, in line with the bases of the blades, a shaped treatment arranged to channel an air leak passing through the clearance.
  • the invention also relates to a compressor thus defined, in which each blade has a top spaced by another radial clearance of a rotating wall of the rotating hub, and in which the rotating wall comprises, at the right of the tops of the blades, a shaped treatment arranged to channel an air leak passing through this other set.
  • the invention also relates to a compressor thus defined, in which the fixed wall comprises a form treatment comprising grooves, these grooves being open towards the bases of the blades over their entire lengths.
  • the invention also relates to a compressor thus defined, in which the rotating wall comprises a form treatment comprising grooves, these grooves being open towards the tops of the blades over their entire lengths.
  • the invention also relates to a turbomachine comprising a compressor thus defined.
  • FIG. 1 is a schematic sectional view of a compressor portion according to the invention
  • Fig. 2 is a schematic view of a fixed variable-pitch vane of a compressor according to the invention
  • Fig. 3 is a schematic view showing axial grooves formed on a fixed wall of the compressor according to the invention.
  • Fig. 4 is a schematic view showing circumferential grooves formed on a rotating wall of the compressor according to the invention.
  • the invention is based on the observation that the presence of leakage flow in the compressor causes a risk of aerodynamic stall, so that the decrease in certain leakage rates makes it possible to limit the risk of aerodynamic stall, that is to say: say to increase the extent of the range of operating conditions of the compressor. More concretely, the invention makes it possible to reduce the risk of aerodynamic stalling by limiting the leakage flows which exist at the level of the top and / or the base of the variable-pitch fixed blades of the compressor.
  • a portion 1 of the turbomachine compressor is traversed by a fluid flowing along a longitudinal axis AX of the turbomachine from upstream AM to downstream AV.
  • This compressor portion 1 is here delimited externally by a fixed wall 2 of a fixed casing 3 generally of revolution, and internally by a rotating wall 4 of a rotor hub 6, this internal wall being generally of revolution and coaxial with the 'longitudinal axis AX.
  • This compressor portion 1 here comprises a rotary stage 7, followed immediately downstream AV by a fixed stage 8.
  • the rotary stage comprises rotary vanes carried by the hub rotating around the axis AX, one of these Rotating vanes can be seen in FIG. 1 where it is marked with 9.
  • the fixed stage 8 carries fixed vanes, one of these fixed vanes is visible in the figure where it is marked with 11.
  • Each fixed vane 11 of stage 8 is a variable-pitch vane, comprising a blade 12 carried by a root 13 which is held by the casing 3, being able to rotate around a radial axis AR which can be inclined or oblique. with respect to the axis AX.
  • the blade 12 comprises a base 14 located opposite the fixed wall 2, extended by a blade body 16 terminated by an apex 17 located opposite the rotating wall 4, that is to say - say the wall of the rotating hub 6.
  • the air to be rectified by the fixed stage 8 leaks by passing through the gap formed by the first set J1 and through the gap formed by the second set J2.
  • This air circulates from the intrados side of the variable-pitch fixed vane to the extrados side thereof, along the fixed wall 2 and the rotating wall 4.
  • these leakage flows generate a deflection of the fluid flow passing through the fixed stage, which penalizes the unwinding effect of this fixed stage.
  • the fact that the fluid is not sufficiently untwisted results in a risk of aerodynamic stalling of the compressor.
  • the fixed wall 2 of the casing comprises a form treatment, marked by 18 in FIG. 2, in the region of the blade 11, intended to limit the disturbance introduced into the main flow E by the leaking fluid. through the clearance Jl.
  • This shaping treatment aims to correct the direction of flow of the flow escaping through the clearance to bring it back parallel to the longitudinal axis.
  • This shape treatment is materialized for example by grooves formed on the internal face of the wall 2, these grooves being arranged to straighten the fluid flowing through the clearance Jl, from the lower surface side towards the upper surface side of the blade.
  • the fluid passing through the clearance Jl is reintroduced into the main flow E while having at the outlet of this clearance Jl an orientation as close as possible to that of the fluid of the main flow E running along l 'extrados at the base 14 of the blade.
  • the rotating wall 4 of the hub also comprises a shape treatment, marked 19, which is located to the right of the blade top 17, so as to reduce the disturbance introduced into the main flow E by the fluid leaking through the second set J2.
  • the grooves are oriented to promote guidance of the leakage flow in an axial direction, so as to promote unwinding of the flow including in the leakage zones.
  • the orientation of the grooves depends on the case considered, and on the design of the compressor. These grooves are generally rectilinear, having either an orientation relatively close to that of the axis in the case longitudinal or axial grooves, ie an orientation close to the normal to the longitudinal axis to form circumferential or helical grooves.
  • the fixed wall 2 of the casing comprises axial grooves 21, having a small angle with respect to the axis AX to help straighten the leakage flow through the clearance J1 towards the longitudinal direction, the wall 2 of the housing being a fixed wall.
  • These grooves 21 cover a length, along the axis AX, which is less than the length of the blades in the axial direction multiplied by 1.2, and they form an angle with the axial direction AX between + 45 ° and - 45 °.
  • the grooves 22 which equip the rotating wall 4 of the hub are of the helical type with an orientation close to the perpendicular to the axis AX. These grooves thus form helicoids in the manner of an endless screw which progresses from upstream to downstream when the hub turns, so as to straighten the leakage flow through the clearance J2 towards the axial direction AX.
  • These grooves 22 are arranged side by side, extending as a whole over a length less than the length of the blades in the axial direction multiplied by 1.2, and they form an angle with the normal to the axial direction AX between + 45 ° and -45 °.
  • grooves shown in FIGS. 3 and 4 are given only as an indication, the grooves being able, more generally, to have any shape suited to the case considered, these grooves being able in particular to be curved instead of rectilinear.
  • axial grooves of the type shown in Fig. 3 can be provided on a rotating wall
  • helical grooves of the type shown in Fig. 4 can be provided on a fixed wall.

Landscapes

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

Abstract

The invention relates to a turbomachine having a compressor comprising variable pitch stator vanes (11) each extending radially between a rotating hub (6) and a stationary casing (3) surrounding this rotating hub (6), each variable pitch vane (11) comprising a blade (12) having a base (14) spaced by a first radial clearance (J1) from a stationary wall (2) of the casing (3), and a tip (17) spaced by a second radial clearance (J2) from a rotating wall (4) of the rotating hub (6). The stationary wall of the casing (3) or the rotating wall (4) of the rotating hub (6) has a shape treatment opposite the blade (12) for channeling an air leak passing through the corresponding clearance.

Description

DESCRIPTION DESCRIPTION
TITRE : Compresseur de turbomachine comportant une paroi fixe pourvue d'un traitement de forme TITLE: Turbomachine compressor comprising a fixed wall provided with a form treatment
DOMAINE TECHNIQUE TECHNICAL AREA
L'invention concerne un élément de stator d'une turbomachine comportant des aubes fixes à calage variable équipant un compresseur de cette turbomachine, ce compresseur pouvant être axial ou centrifuge, l'invention s'appliquant aussi bien à une turbomachine de type moteur d'aéronef qu'à une turbomachine de type turbine d'hélicoptère. The invention relates to a stator element of a turbomachine comprising variable-pitch fixed vanes fitted to a compressor of this turbomachine, this compressor being able to be axial or centrifugal, the invention being equally applicable to a turbomachine of the engine type. aircraft than a helicopter turbine-type turbomachine.
ÉTAT DE LA TECHNIQUE ANTÉRIEURE STATE OF THE PRIOR ART
D'une manière générale, un compresseur de turbomachine comporte un rotor tournant autour d'un axe principal, qui porte plusieurs étages de pales mobiles espacés les uns des autres le long de cet axe, et un carter fixe de révolution entourant l'ensemble qui est traversé d'amont en aval par un flux d'air lorsque l'ensemble est en service. L'ensemble est traversé par un flux d'air circulant dans un espace annulaire délimité intérieurement par le rotor et extérieurement par le carter. In general, a turbomachine compressor comprises a rotor rotating around a main axis, which carries several stages of movable blades spaced from each other along this axis, and a fixed casing of revolution surrounding the assembly which is crossed from upstream to downstream by an air flow when the assembly is in service. The assembly is crossed by an air flow circulating in an annular space delimited internally by the rotor and externally by the casing.
Entre deux étages mobiles consécutifs est interposé un étage de pales fixes, dit redresseur, permettant de canaliser l'air longitudinalement pour le dévriller avant qu'il n'entre dans l'étage mobile suivant. Un tel redresseur se présente sous forme d'une roue aubagée fixe portée par le carter qui entoure localement le rotor. Between two consecutive moving stages is interposed a stage of fixed blades, called a rectifier, making it possible to channel the air longitudinally to unwind it before it enters the next moving stage. Such a rectifier is in the form of a fixed bladed wheel carried by the housing which locally surrounds the rotor.
Les pales d'un ou plusieurs de ces étages fixes sont avantageusement à calage variable, pour que leur position angulaire autour d'un axe radial ou incliné puisse être ajustée afin de l'adapter aux conditions de fonctionnement de la turbomachine qui fluctuent durant son utilisation. The blades of one or more of these fixed stages are advantageously with variable pitch, so that their angular position around a radial or inclined axis can be adjusted in order to adapt it to the operating conditions of the turbomachine which fluctuate during its use. .
Ces pales fixes à calage variable sont pilotées par des éléments de commande ajustant dynamiquement leur calage. D'une manière générale, elles permettent d'adapter l'écoulement fluide avant admission dans l'étage mobile qui les suit immédiatement, pour étendre la gamme des conditions de fonctionnement dans laquelle le compresseur peut être utilisé sans risque de décrochage aérodynamique. These variable pitch fixed blades are controlled by control elements dynamically adjusting their pitch. In general, they make it possible to adapt the fluid flow before admission into the mobile stage which follows them. immediately, to extend the range of operating conditions under which the compressor can be used without risk of aerodynamic stall.
En cas de décrochage aérodynamique, un bouchon de fluide se forme, appelé pompage, qui s'oppose à la circulation d'air dans le compresseur. Une telle situation peut conduire à la rupture d'aubes du compresseur, c'est-à-dire à détériorer voire détruire le compresseur. A cet effet, des vannes de décharge peuvent être prévues pour s'ouvrir afin de décomprimer l'air présent dans le compresseur, dans certaines situations, pour éviter l'établissement d'un régime de pompage, c'est-à-dire de décrochage aérodynamique. Néanmoins, le décrochage aérodynamique constitue un facteur déterminant qui limite l'étendue de la plage des conditions d'utilisation du compresseur, de sorte qu'il constitue un élément important dans la conception et le dimensionnement d'un compresseur. In the event of an aerodynamic stall, a fluid plug forms, called pumping, which opposes the flow of air in the compressor. Such a situation can lead to the compressor blades breaking, that is to say to deteriorating or even destroying the compressor. For this purpose, relief valves can be provided to open in order to decompress the air present in the compressor, in certain situations, to avoid the establishment of a pumping regime, that is to say of aerodynamic stall. Nevertheless, the aerodynamic stall is a determining factor which limits the extent of the range of operating conditions of the compressor, so it is an important element in the design and sizing of a compressor.
Le but de l'invention est d'apporter une solution permettant de limiter le risque de décrochage aérodynamique dans un compresseur comportant un stator portant des pales à calage variable. The aim of the invention is to provide a solution making it possible to limit the risk of aerodynamic stalling in a compressor comprising a stator carrying variable-pitch blades.
EXPOSÉ DE L'INVENTION DISCLOSURE OF THE INVENTION
A cet effet, l'invention a pour objet un compresseur comprenant un carter fixe portant des aubes fixes à calage variable s'étendant chacune radialement depuis ce carter fixe jusqu'à un moyeu rotatif entouré par ce carter fixe, chaque aube à calage variable comprenant une pale ayant une base espacée par un jeu radial d'une paroi fixe du carter, et dans lequel la paroi fixe du carter comporte au droit des bases des pales un traitement de forme agencé pour canaliser une fuite d'air traversant le jeu. To this end, the invention relates to a compressor comprising a fixed casing carrying fixed variable-pitch vanes each extending radially from this fixed casing to a rotary hub surrounded by this fixed casing, each variable-timing vane comprising a blade having a base spaced by a radial clearance from a fixed wall of the housing, and in which the fixed wall of the housing comprises, in line with the bases of the blades, a shaped treatment arranged to channel an air leak passing through the clearance.
Avec cette solution, le flux d'air traversant les jeux en base de pale est redressé vers la direction axiale, de sorte que le dévrillage du flux est plus efficacement réalisé, ce qui limite le risque de décrochage aérodynamique du compresseur. Ceci permet par conséquent d'étendre la plage des conditions de fonctionnement où le compresseur peut être utilisé, c'est-à-dire l'opérabilité du compresseur. L'invention concerne également un compresseur ainsi défini, dans lequel chaque pale comporte un sommet espacé par un autre jeu radial d'une paroi rotative du moyeu rotatif, et dans lequel la paroi rotative comporte au droit des sommets des pales un traitement de forme agencé pour canaliser une fuite d'air traversant cet autre jeu. With this solution, the air flow passing through the clearances at the base of the blade is straightened towards the axial direction, so that the unwinding of the flow is more efficiently carried out, which limits the risk of aerodynamic stalling of the compressor. This therefore makes it possible to extend the range of operating conditions where the compressor can be used, i.e. the operability of the compressor. The invention also relates to a compressor thus defined, in which each blade has a top spaced by another radial clearance of a rotating wall of the rotating hub, and in which the rotating wall comprises, at the right of the tops of the blades, a shaped treatment arranged to channel an air leak passing through this other set.
L'invention concerne également un compresseur ainsi défini, dans lequel la paroi fixe comporte un traitement de forme comprenant des rainures, ces rainures étant ouvertes vers les bases de pales sur toute leurs longueurs. The invention also relates to a compressor thus defined, in which the fixed wall comprises a form treatment comprising grooves, these grooves being open towards the bases of the blades over their entire lengths.
L'invention concerne également un compresseur ainsi défini, dans lequel la paroi rotative comporte un traitement de forme comprenant des rainures, ces rainures étant ouvertes vers les sommets de pales sur toute leurs longueurs. The invention also relates to a compressor thus defined, in which the rotating wall comprises a form treatment comprising grooves, these grooves being open towards the tops of the blades over their entire lengths.
L'invention concerne également une turbomachine comprenant un compresseur ainsi défini. The invention also relates to a turbomachine comprising a compressor thus defined.
BREVE DESCRIPTION DES DESSINS Fig. 1 est une vue schématique en coupe d'une portion de compresseur selon l'invention ; BRIEF DESCRIPTION OF THE DRAWINGS Fig. 1 is a schematic sectional view of a compressor portion according to the invention;
Fig. 2 est une vue schématique d'une aube fixe à calage variable d'un compresseur selon l'invention ; Fig. 2 is a schematic view of a fixed variable-pitch vane of a compressor according to the invention;
Fig. 3 est une vue schématique montrant des rainures axiales formées sur une paroi fixe du compresseur selon l'invention ; Fig. 3 is a schematic view showing axial grooves formed on a fixed wall of the compressor according to the invention;
Fig. 4 est une vue schématique montrant des rainures circonférentielles formées sur une paroi rotative du compresseur selon l'invention. Fig. 4 is a schematic view showing circumferential grooves formed on a rotating wall of the compressor according to the invention.
EXPOSÉ DÉTAILLÉ DE L'INVENTION DETAILED DISCLOSURE OF THE INVENTION
L'invention est basée sur le constat selon la présence de flux de fuite dans le compresseur provoque un risque de décrochage aérodynamique, de sorte que la diminution de certains débits de fuite permet de limiter le risque de décrochage aérodynamique, c'est-à-dire d'augmenter l'étendue de la plage des conditions d'utilisation du compresseur. Plus concrètement, l'invention permet de réduire le risque de décrochage aérodynamique en limitant les flux de fuite qui existent au niveau du sommet et/ou de la base des pales fixes à calage variable du compresseur. The invention is based on the observation that the presence of leakage flow in the compressor causes a risk of aerodynamic stall, so that the decrease in certain leakage rates makes it possible to limit the risk of aerodynamic stall, that is to say: say to increase the extent of the range of operating conditions of the compressor. More concretely, the invention makes it possible to reduce the risk of aerodynamic stalling by limiting the leakage flows which exist at the level of the top and / or the base of the variable-pitch fixed blades of the compressor.
Sur la figure 1, une portion 1 de compresseur de turbomachine est traversée par un fluide s'écoulant selon un axe longitudinal AX de la turbomachine depuis l'amont AM vers l'aval AV. Cette portion de compresseur 1 est ici délimitée extérieurement par une paroi fixe 2 d'un carter fixe 3 généralement de révolution, et intérieurement par une paroi rotative 4 d'un moyeu 6 de rotor, cette paroi interne étant généralement de révolution et coaxiale avec l'axe longitudinal AX. In FIG. 1, a portion 1 of the turbomachine compressor is traversed by a fluid flowing along a longitudinal axis AX of the turbomachine from upstream AM to downstream AV. This compressor portion 1 is here delimited externally by a fixed wall 2 of a fixed casing 3 generally of revolution, and internally by a rotating wall 4 of a rotor hub 6, this internal wall being generally of revolution and coaxial with the 'longitudinal axis AX.
Cette portion de compresseur 1 comporte ici un étage rotatif 7, suivi immédiatement à son aval AV d'un étage fixe 8. L'étage rotatif comprend des aubes rotatives portées par le moyeu tournant autour de l'axe AX, l'une de ces aubes rotatives est visible sur la figure 1 où elle est repérée par 9. L'étage fixe 8 porte des aubes fixes, l'une de ces aubes fixes est visible sur la figure où elle est repérée par 11. This compressor portion 1 here comprises a rotary stage 7, followed immediately downstream AV by a fixed stage 8. The rotary stage comprises rotary vanes carried by the hub rotating around the axis AX, one of these Rotating vanes can be seen in FIG. 1 where it is marked with 9. The fixed stage 8 carries fixed vanes, one of these fixed vanes is visible in the figure where it is marked with 11.
Chaque aube fixe 11 de l'étage 8 est une aube à calage variable, comprenant une pale 12 portée par un pied 13 qui est maintenu par le carter 3, en étant apte à tourner autour d'un axe radial AR pouvant être incliné ou oblique par rapport à l'axe AX. La pale 12 comporte une base 14 située en vis-à-vis de la paroi fixe 2, prolongée par un corps de pale 16 terminé par un sommet 17 situé en vis-à-vis de la paroi rotative 4, c'est-à-dire la paroi du moyeu rotatif 6. Each fixed vane 11 of stage 8 is a variable-pitch vane, comprising a blade 12 carried by a root 13 which is held by the casing 3, being able to rotate around a radial axis AR which can be inclined or oblique. with respect to the axis AX. The blade 12 comprises a base 14 located opposite the fixed wall 2, extended by a blade body 16 terminated by an apex 17 located opposite the rotating wall 4, that is to say - say the wall of the rotating hub 6.
Comme visible sur la figure 2, il existe d'une part un premier jeu radial J1 entre la base 14 et la paroi fixe 2, et d'une manière analogue il existe un second jeu radial J2 entre le sommet 17 qui est fixe et la paroi rotative 4. As visible in Figure 2, there is on the one hand a first radial clearance J1 between the base 14 and the fixed wall 2, and in a similar manner there is a second radial clearance J2 between the top 17 which is fixed and the rotating wall 4.
Ces jeux résultent de contraintes de montage et de dilatations thermiques intervenant dans la turbomachine en service, de sorte qu'il n'est pas possible de les supprimer. En fonctionnement, de l'air à redresser par l'étage fixe 8 fuit en passant à travers l'interstice formé par le premier jeu J1 et à travers l'interstice formé par le second jeu J2. Cet air circule depuis le côté intrados de l'aube fixe à calage variable vers le côté extrados de celle-ci, en longeant la paroi fixe 2 et la paroi rotative 4. D'une manière générale, ces flux de fuite engendrent une déviation de l'écoulement fluide traversant l'étage fixe, qui pénalise l'effet de dévrillage de cet étage fixe. Concrètement, le fait que le fluide n'est pas suffisamment dévrillé se traduit par un risque de décrochage aérodynamique du compresseur. These clearances result from mounting constraints and thermal expansions occurring in the turbomachine in service, so that it is not possible to eliminate them. In operation, the air to be rectified by the fixed stage 8 leaks by passing through the gap formed by the first set J1 and through the gap formed by the second set J2. This air circulates from the intrados side of the variable-pitch fixed vane to the extrados side thereof, along the fixed wall 2 and the rotating wall 4. In general, these leakage flows generate a deflection of the fluid flow passing through the fixed stage, which penalizes the unwinding effect of this fixed stage. Concretely, the fact that the fluid is not sufficiently untwisted results in a risk of aerodynamic stalling of the compressor.
Autrement dit, ces fuites limitent l'opérabilité du compresseur c'est-à- dire l'étendue de la gamme des conditions de fonctionnement dans laquelle le compresseur peut être utilisé sans risque de décrochage aérodynamique. In other words, these leaks limit the operability of the compressor, that is to say the extent of the range of operating conditions in which the compressor can be used without risk of aerodynamic stall.
Selon l'invention, la paroi fixe 2 du carter comporte un traitement de forme, repéré par 18 sur la figure 2, dans la région de l'aube 11, destiné à limiter la perturbation introduite dans l'écoulement principal E par le fluide fuyant à travers le jeu Jl. Ce traitement de forme vise à corriger la direction d'écoulement du flux fuyant à travers le jeu pour le ramener parallèlement à l'axe longitudinal. According to the invention, the fixed wall 2 of the casing comprises a form treatment, marked by 18 in FIG. 2, in the region of the blade 11, intended to limit the disturbance introduced into the main flow E by the leaking fluid. through the clearance Jl. This shaping treatment aims to correct the direction of flow of the flow escaping through the clearance to bring it back parallel to the longitudinal axis.
Ce traitement de forme se matérialise par exemple par des rainures formées à la face interne de la paroi 2, ces rainures étant agencées pour redresser le fluide s'écoulant à travers le jeu Jl, depuis le côté intrados vers le côté extrados de la pale. This shape treatment is materialized for example by grooves formed on the internal face of the wall 2, these grooves being arranged to straighten the fluid flowing through the clearance Jl, from the lower surface side towards the upper surface side of the blade.
Grâce à ce traitement de forme, le fluide traversant le jeu Jl est réintroduit dans l'écoulement principal E en ayant au niveau de la sortie de ce jeu Jl une orientation la plus proche possible de celle du fluide de l'écoulement principal E longeant l'extrados au niveau de la base 14 de la pale. Thanks to this shaping treatment, the fluid passing through the clearance Jl is reintroduced into the main flow E while having at the outlet of this clearance Jl an orientation as close as possible to that of the fluid of the main flow E running along l 'extrados at the base 14 of the blade.
Avantageusement, la paroi rotative 4 du moyeu comporte elle aussi un traitement de forme, repéré par 19, qui est situé au droit du sommet de pale 17, de façon à réduire la perturbation introduite dans l'écoulement principal E par le fluide fuyant à travers le second jeu J2. Advantageously, the rotating wall 4 of the hub also comprises a shape treatment, marked 19, which is located to the right of the blade top 17, so as to reduce the disturbance introduced into the main flow E by the fluid leaking through the second set J2.
D'une manière générale, les rainures sont orientées pour favoriser un guidage du flux de fuite dans une direction axiale, de manière à favoriser le dévrillage du flux y compris dans les zones de fuites. In general, the grooves are oriented to promote guidance of the leakage flow in an axial direction, so as to promote unwinding of the flow including in the leakage zones.
D'une manière générale, l'orientation des rainures dépend de cas considéré, et de la conception du compresseur. Ces rainures sont d'une manière générale rectilignes, en ayant soit une orientation relativement proche de celle de l'axe dans le cas de rainures longitudinales ou axiales, soit une orientation proche de la normale à l'axe longitudinal pour former des rainures circonférentielles ou hélicoïdales. In general, the orientation of the grooves depends on the case considered, and on the design of the compressor. These grooves are generally rectilinear, having either an orientation relatively close to that of the axis in the case longitudinal or axial grooves, ie an orientation close to the normal to the longitudinal axis to form circumferential or helical grooves.
Dans l'exemple de la figure 3, la paroi fixe 2 du carter comporte des rainures 21 axiales, ayant un angle faible par rapport à l'axe AX pour contribuer à redresser le flux de fuite à travers le jeu J1 vers la direction longitudinale, la paroi 2 du carter étant une paroi fixe. In the example of FIG. 3, the fixed wall 2 of the casing comprises axial grooves 21, having a small angle with respect to the axis AX to help straighten the leakage flow through the clearance J1 towards the longitudinal direction, the wall 2 of the housing being a fixed wall.
Ces rainures 21 couvrent une longueur, le long de l'axe AX, qui est inférieure à la longueur des pales selon la direction axiale multipliée par 1,2, et elles forment un angle avec la direction axiale AX compris entre +45° et -45°. These grooves 21 cover a length, along the axis AX, which is less than the length of the blades in the axial direction multiplied by 1.2, and they form an angle with the axial direction AX between + 45 ° and - 45 °.
Dans l'exemple de la figure 4, les rainures 22 qui équipent la paroi rotative 4 du moyeu sont de type hélicoïdal en ayant une orientation proche de la perpendiculaire à l'axe AX. Ces rainures forment ainsi des hélicoïdes à la manière d'une vis sans fin qui progresse de l'amont vers l'aval lorsque le moyeu tourne, de manière à redresser le flux de fuite à travers le jeu J2 vers la direction axiale AX. In the example of FIG. 4, the grooves 22 which equip the rotating wall 4 of the hub are of the helical type with an orientation close to the perpendicular to the axis AX. These grooves thus form helicoids in the manner of an endless screw which progresses from upstream to downstream when the hub turns, so as to straighten the leakage flow through the clearance J2 towards the axial direction AX.
Ces rainures 22 sont disposées côte à côte en s'étendant dans leur ensemble sur une longueur inférieure à la longueur des pales selon la direction axiale multipliée par 1,2, et elles forment un angle avec la normale à la direction axiale AX compris entre +45° et -45°. These grooves 22 are arranged side by side, extending as a whole over a length less than the length of the blades in the axial direction multiplied by 1.2, and they form an angle with the normal to the axial direction AX between + 45 ° and -45 °.
Les exemples de rainures représentés sur les figures 3 et 4 sont donnés uniquement à titre indicatif, les rainures pouvant d'une façon plus générale avoir toute forme adaptée au cas considéré, ces rainures pouvant notamment être incurvées au lieu de rectilignes. En particulier, des rainures axiales du type représentées sur la figure 3 peuvent être prévues sur une paroi rotative, et des rainures hélicoïdales du type représentées sur la figure 4 peuvent être prévues sur une paroi fixe. The examples of grooves shown in FIGS. 3 and 4 are given only as an indication, the grooves being able, more generally, to have any shape suited to the case considered, these grooves being able in particular to be curved instead of rectilinear. In particular, axial grooves of the type shown in Fig. 3 can be provided on a rotating wall, and helical grooves of the type shown in Fig. 4 can be provided on a fixed wall.

Claims

REVENDICATIONS
1. Compresseur comprenant un carter fixe (3) portant des aubes fixes à calage variable (11) s'étendant chacune radialement depuis ce carter fixe (3) jusqu'à un moyeu rotatif (6) entouré par ce carter fixe (3), chaque aube à calage variable (11) comprenant une pale (12) ayant une base (14) espacée par un jeu radial (Jl) d'une paroi fixe (2) du carter (3), et dans lequel la paroi fixe du carter (3) comporte au droit des bases (14) des pales (12) un traitement de forme agencé pour canaliser une fuite d'air traversant le jeu (Jl). 1. Compressor comprising a fixed casing (3) carrying variable-pitch fixed vanes (11) each extending radially from this fixed casing (3) to a rotary hub (6) surrounded by this fixed casing (3), each variable-pitch vane (11) comprising a blade (12) having a base (14) spaced by a radial clearance (Jl) from a fixed wall (2) of the housing (3), and in which the fixed wall of the housing (3) comprises the right of the bases (14) of the blades (12) a shaped treatment arranged to channel an air leak passing through the clearance (Jl).
2. Compresseur selon la revendication 1, dans lequel chaque pale (12) comporte un sommet (17) espacé par un autre jeu radial (J2) d'une paroi rotative (4) du moyeu rotatif (6), et dans lequel la paroi rotative (4) comporte au droit des sommets (17) des pales (12) un traitement de forme (19) agencé pour canaliser une fuite d'air traversant cet autre jeu (J2). 2. Compressor according to claim 1, wherein each blade (12) has an apex (17) spaced by another radial clearance (J2) from a rotary wall (4) of the rotary hub (6), and wherein the wall rotary (4) comprises at the right of the tops (17) of the blades (12) a shaping treatment (19) arranged to channel an air leak passing through this other set (J2).
3. Compresseur selon la revendication 1, dans lequel la paroi fixe (2) comporte un traitement de forme (18) comprenant des rainures (21) axiales ou circonférentielles, ces rainures (21) étant ouvertes vers les bases (14) de pales (12) sur toutes leurs longueurs. 3. Compressor according to claim 1, wherein the fixed wall (2) comprises a form treatment (18) comprising grooves (21) axial or circumferential, these grooves (21) being open towards the bases (14) of the blades ( 12) over all their lengths.
4. Compresseur selon la revendication 2, dans lequel la paroi rotative (4) comporte un traitement de forme (19) comprenant des rainures (22) axiales ou circonférentielles, ces rainures (22) étant ouvertes vers les sommets (17) de pales (12) sur toutes leurs longueurs. 4. Compressor according to claim 2, wherein the rotating wall (4) comprises a form treatment (19) comprising grooves (22) axial or circumferential, these grooves (22) being open towards the tops (17) of the blades ( 12) over all their lengths.
5. Turbomachine comprenant un compresseur selon l'une des revendications précédentes. 5. Turbomachine comprising a compressor according to one of the preceding claims.
6. Turbomachine comprenant un compresseur selon l'une des revendications 1 à 4 comportant des rainures axiales et des rainures circonférentielles. 6. Turbomachine comprising a compressor according to one of claims 1 to 4 comprising axial grooves and circumferential grooves.
EP21731220.6A 2020-05-06 2021-04-23 Turbomachine compressor having a stationary wall provided with a shape treatment Pending EP4121636A1 (en)

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FR2004496A FR3109959B1 (en) 2020-05-06 2020-05-06 Turbomachine compressor comprising a fixed wall provided with a shaped treatment
PCT/FR2021/050704 WO2021224558A1 (en) 2020-05-06 2021-04-23 Turbomachine compressor having a stationary wall provided with a shape treatment

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Family Cites Families (37)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
GB1518293A (en) * 1975-09-25 1978-07-19 Rolls Royce Axial flow compressors particularly for gas turbine engines
DE2740192C2 (en) * 1977-09-07 1981-11-12 Mtu Motoren- Und Turbinen-Union Muenchen Gmbh, 8000 Muenchen Gap seal for an axially flow-around guide vane of a turbomachine that is adjustable about its longitudinal axis
US4278398A (en) * 1978-12-04 1981-07-14 General Electric Company Apparatus for maintaining variable vane clearance
US4479755A (en) * 1982-04-22 1984-10-30 A/S Kongsberg Vapenfabrikk Compressor boundary layer bleeding system
CA1314486C (en) * 1984-06-19 1993-03-16 Michael John Charles Waterman Axial flow compressor surge margin improvement
US4798515A (en) * 1986-05-19 1989-01-17 The United States Of America As Represented By The Secretary Of The Air Force Variable nozzle area turbine vane cooling
FR2603340B1 (en) * 1986-09-03 1988-11-04 Snecma TURBOMACHINE COMPRISING A DEVICE FOR ADJUSTING THE GAMES OF A LABYRINTH JOINT BETWEEN ROTOR AND STATOR AND OF THE GAS VEIN ALIGNMENT AND METHOD OF APPLICATION
US4768922A (en) * 1986-09-15 1988-09-06 Avco Corporation Variable stator and shroud assembly
US5184459A (en) * 1990-05-29 1993-02-09 The United States Of America As Represented By The Secretary Of The Air Force Variable vane valve in a gas turbine
JPH04132899A (en) * 1990-09-25 1992-05-07 Mitsubishi Heavy Ind Ltd Axial blower
CA2082709A1 (en) * 1991-12-02 1993-06-03 Srinivasan Venkatasubbu Variable stator vane assembly for an axial flow compressor of a gas turbine engine
US5281087A (en) * 1992-06-10 1994-01-25 General Electric Company Industrial gas turbine engine with dual panel variable vane assembly
FR2696500B1 (en) * 1992-10-07 1994-11-25 Snecma Turbomachine equipped with means for adjusting the clearance between the rectifiers and the rotor of a compressor.
JPH09203371A (en) * 1996-01-26 1997-08-05 Hitachi Ltd Hydraulic apparatus capable of coping with sediment abrasion
US5752802A (en) * 1996-12-19 1998-05-19 Solar Turbines Incorporated Sealing apparatus for airfoils of gas turbine engines
US6283705B1 (en) * 1999-02-26 2001-09-04 Allison Advanced Development Company Variable vane with winglet
FR2814205B1 (en) * 2000-09-18 2003-02-28 Snecma Moteurs IMPROVED FLOW VEIN TURBOMACHINE
US20060280597A1 (en) * 2003-06-11 2006-12-14 Ishikawajima-Harima Heavy Industries Co., Ltd. Rotating member, housing, bearing, gearbox, rotating machine, shaft structure, and surface treatment method
GB0326544D0 (en) * 2003-11-14 2003-12-17 Rolls Royce Plc Variable stator vane arrangement for a compressor
FR2875559B1 (en) * 2004-09-21 2007-02-23 Snecma Moteurs Sa LEVER FOR CONTROLLING THE ANGULAR SETTING OF A STATOR BLADE IN A TURBOMACHINE
US20080044273A1 (en) * 2006-08-15 2008-02-21 Syed Arif Khalid Turbomachine with reduced leakage penalties in pressure change and efficiency
DE102008010283A1 (en) * 2008-02-21 2009-08-27 Mtu Aero Engines Gmbh Circulation structure for a turbocompressor
DE102008014743A1 (en) * 2008-03-18 2009-09-24 Rolls-Royce Deutschland Ltd & Co Kg Compressor stator with partial cover tape
DE102008019603A1 (en) * 2008-04-18 2009-10-22 Rolls-Royce Deutschland Ltd & Co Kg Turbomachine with scoop internal fluid recirculation
US8714908B2 (en) * 2010-11-05 2014-05-06 General Electric Company Shroud leakage cover
EP3071796B1 (en) * 2013-11-18 2021-12-01 Raytheon Technologies Corporation Gas turbine engine variable area vane with contoured endwalls
US9995166B2 (en) * 2014-11-21 2018-06-12 General Electric Company Turbomachine including a vane and method of assembling such turbomachine
DE102015110249A1 (en) * 2015-06-25 2017-01-12 Rolls-Royce Deutschland Ltd & Co Kg Stator device for a turbomachine with a housing device and a plurality of guide vanes
DE102015110250A1 (en) * 2015-06-25 2016-12-29 Rolls-Royce Deutschland Ltd & Co Kg Stator device for a turbomachine with a housing device and a plurality of guide vanes
US20170335712A1 (en) * 2016-05-23 2017-11-23 United Technologies Corporation Variable area vane having minimized end gap losses
US10648484B2 (en) * 2017-02-14 2020-05-12 Honeywell International Inc. Grooved shroud casing treatment for high pressure compressor in a turbine engine
US10830082B2 (en) * 2017-05-10 2020-11-10 General Electric Company Systems including rotor blade tips and circumferentially grooved shrouds
BE1025470B1 (en) * 2017-08-14 2019-03-18 Safran Aero Boosters S.A. COMPRESSOR VARIABLE SHAFT AUB SYSTEM FOR TURBOMACHINE
WO2019123787A1 (en) * 2017-12-21 2019-06-27 株式会社Ihi Axial flow compressor
US11346367B2 (en) * 2019-07-30 2022-05-31 Pratt & Whitney Canada Corp. Compressor rotor casing with swept grooves
WO2021083442A1 (en) * 2019-10-29 2021-05-06 MTU Aero Engines AG Turbomachine guide vane assembly
US11572798B2 (en) * 2020-11-27 2023-02-07 Pratt & Whitney Canada Corp. Variable guide vane for gas turbine engine

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CN115552099A (en) 2022-12-30
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FR3109959B1 (en) 2022-04-22
WO2021224558A1 (en) 2021-11-11
US20230175527A1 (en) 2023-06-08

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