EP2458157B1 - Abradable interior stator ferrule - Google Patents

Abradable interior stator ferrule Download PDF

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Publication number
EP2458157B1
EP2458157B1 EP10193061.8A EP10193061A EP2458157B1 EP 2458157 B1 EP2458157 B1 EP 2458157B1 EP 10193061 A EP10193061 A EP 10193061A EP 2458157 B1 EP2458157 B1 EP 2458157B1
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EP
European Patent Office
Prior art keywords
seal
turbomachine
pressure seal
abradable
stator
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.)
Active
Application number
EP10193061.8A
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German (de)
French (fr)
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EP2458157A1 (en
Inventor
Stéphane Hiernaux
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 Aero Boosters SA
Original Assignee
Techspace Aero SA
Priority date (The priority date is an assumption and is not a legal conclusion. Google has not performed a legal analysis and makes no representation as to the accuracy of the date listed.)
Filing date
Publication date
Application filed by Techspace Aero SA filed Critical Techspace Aero SA
Priority to EP10193061.8A priority Critical patent/EP2458157B1/en
Priority to CA2758830A priority patent/CA2758830C/en
Priority to RU2011147534/02A priority patent/RU2581328C2/en
Priority to US13/305,407 priority patent/US8926271B2/en
Priority to CN201110383947.1A priority patent/CN102536882B/en
Publication of EP2458157A1 publication Critical patent/EP2458157A1/en
Application granted granted Critical
Publication of EP2458157B1 publication Critical patent/EP2458157B1/en
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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
    • 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
    • F01D11/12—Preventing or minimising internal leakage of working-fluid, e.g. between stages for sealing space between rotor blade tips and stator using a rubstrip, e.g. erodible. deformable or resiliently-biased part
    • F01D11/122—Preventing or minimising internal leakage of working-fluid, e.g. between stages for sealing space between rotor blade tips and stator using a rubstrip, e.g. erodible. deformable or resiliently-biased part with erodable or abradable material

Definitions

  • the present invention aims to provide a new family of abradables having a non-axisymmetrical shape for generating a greater pressure drop and thus ensuring a better seal.

Landscapes

  • Engineering & Computer Science (AREA)
  • Mechanical Engineering (AREA)
  • General Engineering & Computer Science (AREA)
  • Turbine Rotor Nozzle Sealing (AREA)
  • Structures Of Non-Positive Displacement Pumps (AREA)
  • Sealing Using Fluids, Sealing Without Contact, And Removal Of Oil (AREA)

Description

Objet de l'inventionObject of the invention

La présente invention se rapporte à un stator de compresseur ou de turbine pour turbomachines terrestres, marines ou aéronautiques. Elle se rapporte plus particulièrement à un joint d'étanchéité abradable du stator.The present invention relates to a compressor or turbine stator for terrestrial, marine or aeronautical turbomachines. It relates more particularly to an abradable gasket of the stator.

Etat de la techniqueState of the art

Les compresseurs axiaux de turbomachines comportent plusieurs étages d'aubes tournantes, encore appelées aubes rotoriques, qui sont séparés par des étages redresseurs qui ont pour but de repositionner le vecteur vitesse du fluide sortant de l'étage précédent avant de l'envoyer vers l'étage suivant, tout en ralentissant l'écoulement du fluide, ce qui engendre une augmentation de la pression de celui-ci.Axial turbomachine compressors comprise several stages of rotating blades, also called rotor blades, which are separated by rectifier stages which are intended to reposition the velocity vector of the fluid leaving the preceding stage before sending it to the turbine. next stage, while slowing the flow of the fluid, which causes an increase in the pressure thereof.

Les étages redresseurs ou stators sont constitués essentiellement d'aubes fixes, encore appelées aubes statoriques, reliant une virole extérieure à une virole intérieure, toutes deux concentriques et délimitant la zone d'écoulement d'air ou veine aérodynamique. Les étages d'aubes rotoriques sont attachés à un tambour et un abradable est présent sur la virole intérieure du stator pour assurer l'étanchéité de la cavité située entre le stator et le tambour. L'abradable est déposé sous la virole intérieure en vis-à-vis de léchettes présentes sur le tambour ou rotor. La figure 1 présente une coupe partielle d'une turbomachine et permet de visualiser les aubes rotoriques 1, les aubes statoriques 2, respectivement les viroles intérieures 3 et extérieures 4 du stator, le tambour 5, les léchettes 6 du rotor et les abradables 7 des viroles intérieures.The rectifier stages or stators essentially consist of fixed vanes, also called stator vanes, connecting an outer ferrule to an inner ferrule, both concentric and delimiting the air flow zone or aerodynamic vein. The rotor blade stages are attached to a drum and an abradable is present on the inner shell of the stator to seal the cavity between the stator and the drum. The abradable is deposited under the shell interior vis-à-vis wipers present on the drum or rotor. The figure 1 presents a partial section of a turbomachine and makes it possible to visualize the rotor blades 1, the stator blades 2, respectively the inner ferrules 3 and outer 4 of the stator, the drum 5, the wipers 6 of the rotor and the abradable 7 of the inner ferrules.

Le système léchettes/abradables forme un labyrinthe destiné à limiter le débit de recirculation sous le stator induit par la différence de pression entre les parties respectives aval et amont de chaque étage statorique et vise ainsi à augmenter le rendement du compresseur.The wiping / abradable system forms a labyrinth designed to limit the recirculation flow rate under the stator induced by the pressure difference between the respective downstream and upstream parts of each stator stage and thus aims at increasing the efficiency of the compressor.

Actuellement, l'abradable présent sous le pied du stator a une forme axisymétrique, parfois étagée, telle qu'illustrée à la figure 2, et permet d'obtenir une perte de charge en opposant un obstacle (marche axiale 8) à la composante axiale (selon l'axe de la turbomachine) de l'écoulement de fuite. Cependant, l'écoulement, de par la rotation des aubes rotoriques, présente également une composante circonférentielle importante à laquelle les formes des abradables actuels n'offrent pas d'obstacles.Currently, the abradable present under the foot of the stator has an axisymmetric shape, sometimes staggered, as illustrated in FIG. figure 2 , and makes it possible to obtain a pressure drop by opposing an obstacle (axial step 8) to the axial component (along the axis of the turbomachine) of the leakage flow. However, the flow, due to the rotation of the rotor vanes, also has an important circumferential component to which the present forms of abradables do not offer obstacles.

On connaît également des documents FR 2 339 741 A , US 2001/004436 A1 et US 2003/175116 A1 des abradables présentant une structure alvéolaire. Cependant, ces documents décrivent des abradables disposés entre la virole extérieure et les aubes rotoriques.Documents are also known FR 2 339 741 A , US 2001/004436 A1 and US 2003/175116 A1 abradables having a honeycomb structure. However, these documents describe abradables disposed between the outer shell and the rotor blades.

Le document EP 1302559 A1 divulgue un joint disposé sur une virole intérieure de stator.The document EP 1302559 A1 discloses a seal disposed on an inner ferrule of a stator.

Buts de l'inventionGoals of the invention

La présente invention vise à fournir une nouvelle famille d'abradables présentant une forme non axisymétrique permettant de générer une plus grande perte de charge et assurant ainsi une meilleure étanchéité.The present invention aims to provide a new family of abradables having a non-axisymmetrical shape for generating a greater pressure drop and thus ensuring a better seal.

Résumé de l'invention Summary of the invention

La présente invention se rapporte à un joint d'étanchéité d'un stator de turbomachine conformément à la revendication 1.The present invention relates to a seal of a turbomachine stator according to claim 1.

Selon des modes particuliers de l'invention, le joint comporte au moins une ou une combinaison appropriée des caractéristiques suivantes:

  • la marche circonférentielle et la marche axiale de l'unité constitutive définissent les contours d'un profil qui peut revêtir une pluralité de formes distinctes;
  • les unités constitutives ont des profils et/ou des dimensions variables selon la direction circonférentielle de la virole intérieure;
  • les profils des différentes unités constitutives sont décalés selon la direction axiale de la turbomachine;
  • les unités constitutives ont un même profil se répétant périodiquement le long de la circonférence de la virole intérieure, formant alors des unités répétitives;
  • chaque unité répétitive couvre dans la direction circonférentielle de la virole intérieure un secteur angulaire correspondant à quatre à dix pas des aubes rotoriques entraînées par ladite partie rotorique;
  • la partie rotorique en regard de la première surface abradable comporte des léchettes solidaires d'un tambour;
  • le joint est en silicone ou époxy.
According to particular embodiments of the invention, the seal comprises at least one or a suitable combination of the following characteristics:
  • the circumferential step and the axial step of the constituent unit define the contours of a profile that can take a plurality of distinct forms;
  • the constituent units have profiles and / or variable dimensions in the circumferential direction of the inner ferrule;
  • the profiles of the different constituent units are offset in the axial direction of the turbomachine;
  • the constituent units have the same profile repeating periodically along the circumference of the inner ferrule, thus forming repetitive units;
  • each repeating unit covers in the circumferential direction of the inner ferrule an angular sector corresponding to four to ten steps of the rotor blades driven by said rotor part;
  • the rotor part opposite the first abradable surface comprises wipers integral with a drum;
  • the seal is silicone or epoxy.

La présente invention se rapporte également à un stator de turbomachine comportant au moins un joint d'étanchéité tel que décrit ci-dessus.The present invention also relates to a turbomachine stator comprising at least one seal as described above.

Brève description des figuresBrief description of the figures

  • La figure 1 représente une coupe partielle et axiale d'une turbomachine selon l'état de la technique.The figure 1 represents a partial and axial section of a turbomachine according to the state of the art.
  • La figure 2 représente une partie d'un abradable selon l'état de la technique.The figure 2 represents a part of an abradable according to the state of the art.
  • La figure 3 représente huit unités constitutives d'un abradable selon l'invention.The figure 3 represents eight units constituting an abradable according to the invention.
  • La figure 4 représente une pluralité de formes que peut revêtir le profil des unités constitutives de la piste de l'abradable selon l'invention.The figure 4 represents a plurality of shapes that can take the profile of the constituent units of the track of the abradable according to the invention.
Légende:Legend:

  1. (1) Aube rotorique(1) Rotor blade
  2. (2) Aube statorique(2) Stator blade
  3. (3) Virole intérieure(3) Inner ferrule
  4. (4) Virole extérieure(4) outer shell
  5. (5) Tambour(5) Drum
  6. (6) Léchette(6) Lechette
  7. (7) Abradable ou joint d'étanchéité(7) Abradable or seal
  8. (8) Marche axiale de la piste de l'abradable(8) Axial walk of the abradable track
  9. (9) Marche circonférentielle de la piste de l'abradable(9) Circumferential walk of the abradable track
  10. (10) Unité constitutive de l'abradable(10) Constitutive unit of the abradable
Description détaillée de l'inventionDetailed description of the invention

Comme déjà mentionné, l'efficacité du labyrinthe créé par le système léchettes/abradables est conditionnée par les pertes de charge générées au travers de ce dernier. Un des mécanismes utilisés pour augmenter les pertes de charge est de créer des marches dans l'abradable qui forcent la création de tourbillons générateurs de pertes. La présente invention se base sur le fait que l'écoulement dans la cavité n'est pas strictement axial mais possède une forte composante giratoire issue de l'écoulement principal dans la veine.As already mentioned, the efficiency of the labyrinth created by the system wipers / abradable is conditioned by the pressure losses generated through the latter. One of the mechanisms used to increase the pressure drop is to create steps in the abradable which force the creation of whirlpools generating losses. The present invention is based on the fact that the flow in the cavity is not strictly axial but has a strong gyratory component from the main flow in the vein.

Ainsi, selon l'invention, l'abradable 7, et plus précisément la piste de l'abradable, c'est-à-dire la face en regard des léchettes, comporte également des marches dans le sens circonférentiel (c.à.d. selon la direction circonférentielle de la virole intérieure) afin d'augmenter encore les pertes de charge. La figure 3 présente une partie de l'abradable 7 selon l'invention comportant huit marches axiales 8 et huit marches circonférentielles 9 sur la piste d'abradable. L'abradable 7 dans son entièreté est constitué d'une pluralité d'unités constitutives 10 comportant chacune une marche axiale 8 et une marche circonférentielle 9. Dans l'exemple de la figure 3, huit unités constitutives 10 de l'abradable 7 sont ainsi représentées.Thus, according to the invention, the abradable 7, and more precisely the track of the abradable, that is to say the face opposite the wipers, also comprises steps in the circumferential direction (ie in the circumferential direction of the inner ring) in order to further increase the pressure drops. The figure 3 presents a portion of the abradable 7 according to the invention comprising eight axial steps 8 and eight circumferential steps 9 on the abradable track. The abradable 7 in its entirety consists of a plurality of constituent units 10 each comprising an axial step 8 and a circumferential step 9. In the example of FIG. figure 3 eight constituent units 10 of the abradable 7 are thus represented.

La marche circonférentielle 9 et la marche axiale 8 de l'unité constitutive 10 définissent les contours d'un profil qui peut revêtir plusieurs formes. A titre indicatif et non limitatif pour la présente invention, la figure 4 présente six profils différents des unités constitutives de la piste d'abradable. Selon l'invention, tout abradable comportant des marches circonférentielles permettant de générer une perte de charge convient.The circumferential step 9 and the axial step 8 of the constituent unit 10 define the contours of a profile that can take several forms. As an indication and not limiting for the present invention, the figure 4 presents six different profiles of the constituent units of the abradable track. According to the invention, any abradable having steps circumferences to generate a suitable pressure drop.

Les unités constituant l'abradable peuvent présenter sur leurs pistes d'abradable un même profil ou des profils différents tout comme elles peuvent être de même dimension dans le sens circonférentiel ou de dimensions différentes. A la figure 3, les profils des unités 10 sont identiques ou similaires et alignés selon la direction circonférentielle. Selon l'invention, les profils peuvent être également décalés l'un par rapport à l'autre selon la direction axiale de la turbomachine. Préférentiellement, les unités constitutives présentent une répétitivité cyclique vu le caractère cyclique de la virole, on parlera alors d'unité répétitive. Toujours préférentiellement selon l'invention, l'unité répétitive couvre un secteur angulaire correspondant à quatre à dix pas des aubes mobiles entraînées par le tambour.The units constituting the abradable may have on their abradable tracks the same profile or different profiles just as they may be of the same dimension in the circumferential direction or of different dimensions. To the figure 3 the profiles of the units 10 are identical or similar and aligned in the circumferential direction. According to the invention, the profiles may also be offset relative to each other in the axial direction of the turbomachine. Preferably, the constituent units have a cyclic repeatability given the cyclic nature of the ferrule, it will be called repetitive unit. Still preferentially according to the invention, the repetitive unit covers an angular sector corresponding to four to ten steps of the blades driven by the drum.

Les profils des unités constitutives ne peuvent généralement pas être réalisés par tournage, comme c'est actuellement le cas. Par contre, le profil peut facilement être obtenu par moulage à cote(s) finie(s) ou quasiment finie(s), notamment sur des secteurs de viroles.The profiles of the constituent units can not generally be made by shooting, as is currently the case. By cons, the profile can easily be obtained by molding finished (s) or almost finished (s), especially on sectors of ferrules.

Préférentiellement, l'abradable est en silicone ou en époxy.Preferably, the abradable is silicone or epoxy.

Avantages de l'invention Advantages of the invention

La composante circonférentielle de l'écoulement de fuite étant généralement nettement plus importante que la composante axiale, l'obstacle formé par les marches circonférentielles selon l'invention permet une perte de charge plus importante et donc une efficacité accrue par rapport aux formes traditionnelles.As the circumferential component of the leakage flow is generally much larger than the axial component, the obstacle formed by the circumferential steps according to the invention allows a greater pressure drop and therefore an increased efficiency compared with traditional shapes.

Claims (9)

  1. A pressure seal (7) of a turbomachine stator comprising stator vanes connecting an outer ferrule to an inner ferrule, both concentric and delimiting an air flow zone, said seal (7) comprising a first abradable surface designed to be positioned opposite a rotor portion of the turbomachine and a second surface designed to be in contact with the inner ferrule (3) of the stator, said seal (7) having a stepped profile and comprising a plurality of component units (10), each component unit (10), characterized in that each component unit (10) comprises, on its first abradable surface, a circumferential step (9) creating an obstacle in the circumferential direction of the inner ferrule (3) and an axial step (8) creating an obstacle in the axial direction of the turbomachine, each component unit (10) having a non-axisymmetric shape.
  2. The pressure seal (7) according to claim 1, characterized in that the circumferential step (9) and the axial step (8) of the component unit (10) define the contours of a profile that may assume a plurality of distinct shapes.
  3. The pressure seal (7) according to claim 2, characterized in that the component units (10) have profiles and/or dimensions that vary according to the circumferential direction of the inner ferrule (3).
  4. The pressure seal (7) according to claim 2, characterized in that the profiles of the different component units (10) are offset according to the axial direction of the turbomachine.
  5. The pressure seal (7) according to claim 2, characterized in that the component units (10) have a same profile that repeats itself periodically along the circumference of the inner ferrule (3), thus forming repetitive units.
  6. The pressure seal (7) according to claim 5, characterized in that each repetitive unit covers, in the circumferential direction of the inner ferrule (3), an angular sector corresponding to four to ten pitches of the rotor vanes (1) driven by said rotor portion.
  7. The pressure seal (7) according to any one of the preceding claims, characterized in that the first abradable surface of the seal is designed to be positioned opposite the rotor portion of the turbomachine, said rotor portion comprising knife edge seal (6) secured to a drum (5).
  8. The pressure seal (7) according to any one of the preceding claims, characterized in that said seal (7) is made of silicone or epoxy.
  9. A turbomachine stator comprising at least one pressure seal (7) according to any one of the previous claims.
EP10193061.8A 2010-11-30 2010-11-30 Abradable interior stator ferrule Active EP2458157B1 (en)

Priority Applications (5)

Application Number Priority Date Filing Date Title
EP10193061.8A EP2458157B1 (en) 2010-11-30 2010-11-30 Abradable interior stator ferrule
CA2758830A CA2758830C (en) 2010-11-30 2011-11-21 Abradable for stator inner shroud
RU2011147534/02A RU2581328C2 (en) 2010-11-30 2011-11-24 Abradable seal for inner stator cover
US13/305,407 US8926271B2 (en) 2010-11-30 2011-11-28 Abradable for stator inner shroud
CN201110383947.1A CN102536882B (en) 2010-11-30 2011-11-28 The wear-resistant seal of stator inner loop

Applications Claiming Priority (1)

Application Number Priority Date Filing Date Title
EP10193061.8A EP2458157B1 (en) 2010-11-30 2010-11-30 Abradable interior stator ferrule

Publications (2)

Publication Number Publication Date
EP2458157A1 EP2458157A1 (en) 2012-05-30
EP2458157B1 true EP2458157B1 (en) 2015-10-14

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EP10193061.8A Active EP2458157B1 (en) 2010-11-30 2010-11-30 Abradable interior stator ferrule

Country Status (5)

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US (1) US8926271B2 (en)
EP (1) EP2458157B1 (en)
CN (1) CN102536882B (en)
CA (1) CA2758830C (en)
RU (1) RU2581328C2 (en)

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FR3022578B1 (en) * 2014-06-23 2016-06-03 Snecma PROCESS FOR MAKING AND REPAIRING A TURBINE DISPENSER OF A TURBOMACHINE
US20170130732A1 (en) * 2015-11-06 2017-05-11 United Technologies Corporation Compressor exit seal
FR3048018B1 (en) * 2016-02-22 2018-03-02 Safran Aircraft Engines DEVICE FOR APPLYING ABRADABLE MATERIAL TO A SURFACE OF A TURBOMACHINE CASING
ES2933806T3 (en) 2017-02-21 2023-02-14 Illumina Inc Tagmentation using linker-immobilized transposomes

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EP1302559A1 (en) * 2001-10-16 2003-04-16 Snecma Moteurs Process of protection by aluminization of metallic parts constituted at least partially of a honeycomb structure

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US4063742A (en) * 1976-08-18 1977-12-20 Kentucky Metals, Inc. Abradable fluid seal for aircraft gas turbines
US4477089A (en) * 1982-07-26 1984-10-16 Avco Corporation Honeycomb seal for turbine engines
EP1302559A1 (en) * 2001-10-16 2003-04-16 Snecma Moteurs Process of protection by aluminization of metallic parts constituted at least partially of a honeycomb structure

Also Published As

Publication number Publication date
US20120134787A1 (en) 2012-05-31
RU2011147534A (en) 2013-05-27
CN102536882B (en) 2016-05-18
US8926271B2 (en) 2015-01-06
CN102536882A (en) 2012-07-04
RU2581328C2 (en) 2016-04-20
CA2758830C (en) 2018-02-13
CA2758830A1 (en) 2012-05-30
EP2458157A1 (en) 2012-05-30

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