EP0177408B1 - Apparatus for the automatic control of the play of a labyrinth seal of a turbo machine - Google Patents

Apparatus for the automatic control of the play of a labyrinth seal of a turbo machine Download PDF

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Publication number
EP0177408B1
EP0177408B1 EP85401863A EP85401863A EP0177408B1 EP 0177408 B1 EP0177408 B1 EP 0177408B1 EP 85401863 A EP85401863 A EP 85401863A EP 85401863 A EP85401863 A EP 85401863A EP 0177408 B1 EP0177408 B1 EP 0177408B1
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EP
European Patent Office
Prior art keywords
annular
clearance
wearing
labyrinth
wipers
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.)
Expired
Application number
EP85401863A
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German (de)
French (fr)
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EP0177408A1 (en
Inventor
Robert Kervistin
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Safran Aircraft Engines SAS
Original Assignee
Societe Nationale dEtude et de Construction de Moteurs dAviation SNECMA
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Publication of EP0177408A1 publication Critical patent/EP0177408A1/en
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Publication of EP0177408B1 publication Critical patent/EP0177408B1/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
    • 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
    • F01D11/14—Adjusting or regulating tip-clearance, i.e. distance between rotor-blade tips and stator casing
    • F01D11/20—Actively adjusting tip-clearance
    • F01D11/24—Actively adjusting tip-clearance by selectively cooling-heating stator or rotor components
    • 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
    • F01D11/001—Preventing or minimising internal leakage of working-fluid, e.g. between stages for sealing space between stator blade and rotor
    • 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
    • F01D11/02—Preventing or minimising internal leakage of working-fluid, e.g. between stages by non-contact sealings, e.g. of labyrinth type

Definitions

  • the invention relates to an automatic control device in operation of the clearance of a labyrinth type turbomachine seal.
  • the seals between fixed parts and rotating parts of a turbomachine frequently use labyrinth type seals composed, on the one hand, of wipers-shaped elements, in variable number according to the operating conditions and according to various technological parameters, and, on the other hand, on the fixed part located opposite, of an element constituting a wear and sealing lining, called "abradable", that is to say usable by friction during possible contact with a wiper without causing significant damage thereto, this element being carried by an annular support connected to a fixed structure of the turbomachine.
  • Such seals can be arranged for example between different movable stages of compressor or turbine, and fixed parts (or rotating at a different speed) in the vicinity.
  • the wipers are in this case carried by spacers or rings and the lining is fixed on the stator (or on the mobile part rotating at the lowest speed preferably).
  • these seals are arranged between various turbomachine enclosures and are found in particular at the ends of the external enclosure of the combustion chamber housing, d on the one hand, on the side of the compressor outlet and, on the other hand, on the side of the turbine inlet.
  • the proper sealing function of the seal is more complex.
  • pressure balancing between various enclosures of the turbomachine is usually sought.
  • Controlled air circulation is also sought in the enclosures in order to create certain ventilation air streams which may be used in other areas of the turbomachine and thus it may be desirable to control the air flows with the best precision.
  • FR-A-2437544 in the name of the Applicant describes a seal in which the support of the wear lining is surrounded by an annular channel connected, at its downstream end, to an air intake provided in the wall of the combustion chamber casing while its other end opens upstream of the seal into the lower pressure air space surrounding the compressor shaft.
  • the adjustment of the circulation flow rate of the cooling air of the seal calls for an adjustable discharge valve controlled by an operating parameter of the turbomachine.
  • FR-A-2025869 seeks to minimize the difference in thermal expansion in a labyrinth seal by equalizing the temperatures between a casing carrying the seal and a ring carrying the wipers and connected to the rotor.
  • the external surface of the casing is isolated from the stream of hot gases by a screen providing a space in which the cooling air circulates.
  • this solution does not provide for any specific adaptation as a function of variations in the operating conditions of the turbomachine, in particular during the transient phases.
  • the invention aims to solve these problems by avoiding the drawbacks of known prior solutions.
  • a rise to full throttle speed by rapid acceleration ensuring minimum clearance between the top of the wipers and the cooperating surface of the wear lining and sealing of the labyrinth seal and also, in the event of a sudden deceleration, to avoid any penetration of the wipers into the wear layer, which would cause, in addition to various mechanical disadvantages (vibratory phenomena, overheating inducing phenomena with divergent effect), the subsequent appearance excessive play clearly detrimental to returns.
  • a minimum of play must even be kept in order to allow that a phase of re-acceleration can follow quickly.
  • the device according to the invention of the aforementioned kind is characterized in that the upstream part of the annular support carrying the wear and sealing lining comprises a series of holes peripherally distributed connecting said annular chamber and the upstream part of said cross section of the seal, so as to be supplied by a sample taken in the cooling air which passes through the labyrinth seal.
  • cooperating parts of the support carrying the wear and sealing lining and of the rotor part carrying the wipers are shaped so as to create upstream of the zone comprising said wipers and said lining an annular convergent-diverging nozzle forming a primary neck.
  • FIG. 1 there is shown schematically, in axial section, under stabilized operating conditions, a part of a turbomachine comprising an embodiment of the invention.
  • a labyrinth seal according to the invention is disposed between a fixed part and a rotating part of the turbomachine.
  • the rotating part is represented diagrammatically by a rotor part 1.
  • the fixed part comprises a stator element 2 connected in a known manner to a part 3 of the fixed structure of the turbomachine.
  • this stator element 2 is formed an annular chamber 5 closed on the interior side by an annular support 6 on the internal face of which is fixed in its downstream part a seal 7 for wear and sealing.
  • This lining is of any known and commonly used type, but preferably in the device according to the invention, the lining 7 consists of a honeycomb or of a type such that the flow rate passing through the labyrinth is not proportional to the clearance.
  • the stator element 2 has on its external diameter one or more air inlet orifices 8 and it also has on its downstream edge one or more air outlet orifices 9. These orifices 9 are placed towards the internal diameter of the element 2 and one or more other air outlet orifices 10 can be placed towards the external diameter of the element 2, always at its downstream edge.
  • Inside the annular chamber 5 of the stator element 2 is disposed a thin sheet 11 pierced with series of multi-holes 12.
  • This sheet 11 divides the annular chamber 5 into two enclosures, one external 5a comprising the air inlets 8 and the other internal 5b comprising the air outlets 9 and possibly 10.
  • the shaft 1 carries wipers 13 (5 wipers in the example shown).
  • the upstream part of the annular support 6 carrying the seal and the rotor part 1 upstream of the part carrying the wipers 13 have cooperating parts 14 on the support 6 and 15 on the rotor part 1.
  • These parts 14 and 15 are respectively shaped so as to create in the upstream space located between the support 6 and the rotor part 1 a nozzle 16 comprising a converging upstream part 17 and a diverging downstream part 18 connected by a neck 19.
  • the upstream part 14 of the support 6 comprises, in line with the neck 19, one or more bores 20 opening out on one side at the neck 19 of the convergent-diverging nozzle 16 and on the other in the external enclosure 5a of the annular chamber 5 of the element of stator 2.
  • the device according to the invention which has just been described makes it possible to obtain an improved operation by ensuring in all the operating conditions of the turbomachine both in stabilized and transient conditions a practically constant clearance guaranteeing a controlled value of the air flow rate passing through the labyrinth seal of the turbomachine on which said device is adapted without inadvertent variations being observed, the consequences of which are harmful for the yields or for the life of certain parts in the leakage rates at the level of the labyrinth seal.
  • the clearance j1 may have a tendency to decrease, as can the section j2 at the neck 19.
  • D1 denotes the air flow at the inlet of the space separating the rotor part 1 and the stator element 2, this air being at a temperature much lower than that of the gases in the vein at the height of the device
  • D2 the air flow entering the annular chamber 5 through the orifices 8 of the stator element 2
  • the point of sampling of this air in the turbomachine being chosen so that this air is hotter than that D1 supplying the joint
  • D3 the air flow taken from D1 at the neck 19 of the nozzle 16 through the orifices 20 of entry into the annular chamber 5
  • D4 the flow of cooling air passing through the joint to labyrinth
  • the clearance j1 may tend to increase and the same is true for the clearance j2.
  • the section at the neck 19 increases and that consequently the local speed decreases and the static pressure increases, this results in an increase in the flow D3 while the flow D2 decreases.
  • the air impacting on the support 6 cools and this support 6 carrying the seal 7 contracts almost immediately.
  • the effects tending to increase the play j1 are compensated for and canceled and the play j1 is again maintained at its objective value and it will be the same in all the operating conditions of the turbomachine tending to increase the play j1.
  • Fig. 2 shows an embodiment for an application of the invention to a labyrinth seal placed in line with the outlet of a combustion chamber on the radially internal side.
  • a fixing means 25 for example of the bolt-on type, to a radial flange 26 of an internal part of stator vane 27.
  • the casing 23 carries a directed radial flange 28 towards the axis of the machine and to which are fixed by fixing means, for example 29, of the bolt type, on the one hand, a radial end flange 30 of an annular support 31 which bears on its face internally a wear and sealing lining 32 and, on the other hand, a radial end flange 33 of an annular thin sheet metal 34 multi-perforated slightly spaced radially outward relative to the support 31 on which it is radial support at 35 at its downstream end.
  • the support 31 carries a radial flange 36 directed radially outwards, making the connection with the internal part of the stator blade 27.
  • the rotary rotor part comprises a disc 37 carrying in the example shown three wipers 38 cooperating with the wear and sealing lining 32.
  • the internal enclosure is separated by the disc 37 into an upstream enclosure 39 where the air is at pressure P1 and a downstream enclosure 40 at a lower pressure P2.
  • the space formed between the annular support 31 and the chamber envelope 23 constitutes an annular chamber 41 allowing the ventilation of the support 31 and separated into two enclosures 41a a and 41b by the annular sheet 34.
  • a passage of air through an opening 42a made in the envelope 23 is provided between the enclosure 24 and the chamber 41.
  • the upstream part of the wear and sealing lining 32, of the support 31 and of the thin sheet 34 have cooperating holes 42, 43 and 44 respectively for the passage of air towards the enclosure 41 a of the chamber 41.
  • the thin sheet 34 also comprises multi-perforations 45 for the ventilation by impacts of the support 31.
  • Side downstream, the support 31 and the wear and sealing lining 32 also have cooperating holes 46 and 47 respectively for the evacuation of the air from the chamber 41.
  • the wiping disc 37 has on its outside diameter upstream side a finger-shaped part 48 whose end 49 as well as the cooperating surface 50 of the upstream part of the wear and sealing lining 32 are respectively shaped so as to create a nozzle of annular convergent-diverging shape by creating a neck 51 at the level of which the catches are open. air towards the chamber 41 through the holes 42.
  • the disc 37 also carries a finger 52, the end 53 of which cooperates with the surface facing the downstream part of the wear and sealing lining 32 , through which the drainage holes 47 open.

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  • 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

L'invention concerne un dispositif de contrôle automatique en fonctionnement du jeu d'un joint de turbomachine du type à labyrinthe.The invention relates to an automatic control device in operation of the clearance of a labyrinth type turbomachine seal.

Les étanchéités entre parties fixes et parties tournantes de turbomachine font fréquemment appel à des joints du type à labyrinthe composés, d'une part, sur la partie tournante, d'éléments en forme de léchettes, en nombre variable selon les conditions de fonctionnement et suivant divers paramètres technologiques, et, d'autre part, sur la partie fixe située en regard, d'un élément constituant une garniture d'usure et d'étanchéité, dite «abradable», c'est-à-dire usable par frottement lors d'un contact éventuel avec une léchette sans entraîner d'endommagement notable de celle-ci, cet élément étant porté par un support annulaire relié à une structure fixe de la turbomachine. De tels joints peuvent être disposés par exemple entre différents étages mobiles de compresseur ou de turbine, et des parties fixes (ou tournant à une vitesse différente) avoisinantes. Les léchettes sont dans ce cas portées par des entretoises ou des anneaux et la garniture est fixée sur le stator (ou sur la partie mobile tournant à la vitesse la plus faible de préférence).The seals between fixed parts and rotating parts of a turbomachine frequently use labyrinth type seals composed, on the one hand, of wipers-shaped elements, in variable number according to the operating conditions and according to various technological parameters, and, on the other hand, on the fixed part located opposite, of an element constituting a wear and sealing lining, called "abradable", that is to say usable by friction during possible contact with a wiper without causing significant damage thereto, this element being carried by an annular support connected to a fixed structure of the turbomachine. Such seals can be arranged for example between different movable stages of compressor or turbine, and fixed parts (or rotating at a different speed) in the vicinity. The wipers are in this case carried by spacers or rings and the lining is fixed on the stator (or on the mobile part rotating at the lowest speed preferably).

Dans une autre utilisation particulière de ces joints qui constitue une application plus directement visée par l'invention, ces joints sont disposés entre diverses enceintes de turbomachine et on les trouve en particulier aux extrémités de l'enceinte externe du carter de chambre de combustion, d'une part, du côté de la sortie de compresseur et, d'autre part, du côté de l'entrée de turbine. Dans ce cas la fonction propre d'étanchéité du joint est plus complexe. En effet, un équilibrage de pressions entre diverses enceintes de la turbomachine est habituellement recherchée. Une circulation d'air contrôlée est également recherchée dans les enceintes en vue de créer certains courants d'air de ventilation utilisable éventuellement dans d'autres zones de la turbomachine et ainsi il peut être souhaitable de contrôler avec la meilleure précision des débits d'air dits «débits de fuite» traversant ce type de joint à labyrinthe et dont la maîtrise se répercute sur divers résultats tels que les rendements de la turbomachine ou la durée de vie de différentes pièces. En dehors des diverses conditions de fonctionnement, telles que la pression dans les enceintes, l'un des paramètres fondamentaux dont dépend ce contrôle des débits d'air est le jeu en fonctionnement entre le sommet des léchettes et la garniture d'usure et d'étanchéité qui forme les sections de passage correspondantes.In another particular use of these seals which constitutes an application more directly targeted by the invention, these seals are arranged between various turbomachine enclosures and are found in particular at the ends of the external enclosure of the combustion chamber housing, d on the one hand, on the side of the compressor outlet and, on the other hand, on the side of the turbine inlet. In this case the proper sealing function of the seal is more complex. In fact, pressure balancing between various enclosures of the turbomachine is usually sought. Controlled air circulation is also sought in the enclosures in order to create certain ventilation air streams which may be used in other areas of the turbomachine and thus it may be desirable to control the air flows with the best precision. so-called “leakage rates” passing through this type of labyrinth seal and whose control has repercussions on various results such as the yields of the turbomachine or the lifetime of different parts. Apart from the various operating conditions, such as the pressure in the chambers, one of the fundamental parameters on which this control of air flow rates depends is the clearance in operation between the top of the wipers and the wear and sealing which forms the corresponding passage sections.

Diverses solutions ont tenté de répondre à ces problèmes posés et en particulier de maintenir à une valeur contrôlée le jeu entre les léchettes et la garniture d'usure et d'étanchéité dans un joint à labyrinthe, quelles que soient les conditions de fonctionnement de la turbomachine, en régime stabilisé ou durant les phases de régime transitoire. Ainsi, FR-A-2437544 au nom de la Demanderesse décrit un joint dans lequel le support de la garniture d'usure est entouré d'un canal annulaire relié, à son extrémité aval, à une prise d'air prévue dans la paroi du carter de la chambre de combustion tandis que son autre extrémité débouche en amont du joint dans l'espace à air à pression plus faible entourant l'arbre du compresseur. Le réglage du débit de circulation de l'air de refroidissement du joint fait appel dans ce cas à une vanne décharge réglable asservie à un paramètre de fonctionnement de la turbomachine. Ce mode de contrôle présente toutefois divers inconvénients inhérents à la méthode car il reste, d'une part, tributaire d'une chaîne complexe d'asservissement en multipliant les risques de panne ou de fonctionnement défectueux tenant aux vannes et autres accessoires et, d'autre part, les temps de réponse, notamment durant les phases de régime transitoire, risquent d'être trop longs pour assurer un fonctionnement pleinement satisfaisant.Various solutions have attempted to respond to these problems posed and in particular to maintain at a controlled value the clearance between the wipers and the wear and seal in a labyrinth seal, whatever the operating conditions of the turbomachine. , in steady state or during transient state phases. Thus, FR-A-2437544 in the name of the Applicant describes a seal in which the support of the wear lining is surrounded by an annular channel connected, at its downstream end, to an air intake provided in the wall of the combustion chamber casing while its other end opens upstream of the seal into the lower pressure air space surrounding the compressor shaft. In this case, the adjustment of the circulation flow rate of the cooling air of the seal calls for an adjustable discharge valve controlled by an operating parameter of the turbomachine. This method of control, however, has various drawbacks inherent in the method because it remains, on the one hand, dependent on a complex chain of control by increasing the risk of failure or faulty operation due to valves and other accessories and, on the other hand, the response times, particularly during the transient phases, may be too long to ensure fully satisfactory operation.

Un autre dispositif connu selon FR-A-2025869 recherche à minimiser la différence des dilatations thermiques dans un joint à labyrinthe par une égalisation des températures entre un carter portant la garniture d'étanchéité et un anneau portant les léchettes et relié au rotor. Dans ce but, la surface externe du carter est isolée du courant de gaz chauds par un écran ménageant un espace dans lequel circule de l'air de refroidissement. Cette solution toutefois ne prévoit aucune adaptation spécifique en fonction des variations des conditions de fonctionnement de la turbomachine, en particulier durant les phases de régime transitoire.Another known device according to FR-A-2025869 seeks to minimize the difference in thermal expansion in a labyrinth seal by equalizing the temperatures between a casing carrying the seal and a ring carrying the wipers and connected to the rotor. For this purpose, the external surface of the casing is isolated from the stream of hot gases by a screen providing a space in which the cooling air circulates. However, this solution does not provide for any specific adaptation as a function of variations in the operating conditions of the turbomachine, in particular during the transient phases.

L'invention vise à résoudre ces problèmes en évitant les inconvénients des solutions antérieures connues. Il s'agit en particulier, lors d'une montée au régime plein gaz par une accélération rapide, d'assurer un jeu minimal entre le sommet des léchettes et la surface coopérante de la garniture d'usure et d'étanchéité du joint à labyrinthe et également, au cas d'une décélération brutale, d'éviter toute pénétration des léchettes dans la couche d'usure, ce qui entraînerait, outre divers inconvénients mécaniques (phénomènes vibratoires, échauffements induisant des phénomènes à effet divergent), l'apparition ultérieure de jeux trop importants nettement préjudiciables aux rendements. Durant cette dernière phase transitoire de décélération, en fait, un minimum de jeu doit même être conservé afin de permettre qu'une phase de réaccélération puisse suivre rapidement.The invention aims to solve these problems by avoiding the drawbacks of known prior solutions. In particular, during a rise to full throttle speed by rapid acceleration, ensuring minimum clearance between the top of the wipers and the cooperating surface of the wear lining and sealing of the labyrinth seal and also, in the event of a sudden deceleration, to avoid any penetration of the wipers into the wear layer, which would cause, in addition to various mechanical disadvantages (vibratory phenomena, overheating inducing phenomena with divergent effect), the subsequent appearance excessive play clearly detrimental to returns. During this last transient phase of deceleration, in fact, a minimum of play must even be kept in order to allow that a phase of re-acceleration can follow quickly.

Le dispositif selon l'invention du genre précité, permettant d'obtenir ces résultats tout en évitant les inconvénients antérieurs est caractérisé en ce que la partie amont du support annulaire portant la garniture d'usure et d'étanchéité comporte une série de perçages périphériquement répartis reliant ladite chambre annulaire et la partie amont de ladite section de passage du joint, de manière à être alimentés par un prélèvement effectué dans l'air de refroidissement qui travese le joint à labyrinthe.The device according to the invention of the aforementioned kind, making it possible to obtain these results while avoiding the previous drawbacks, is characterized in that the upstream part of the annular support carrying the wear and sealing lining comprises a series of holes peripherally distributed connecting said annular chamber and the upstream part of said cross section of the seal, so as to be supplied by a sample taken in the cooling air which passes through the labyrinth seal.

Avantageusement, des parties coopérantes du support portant la garniture d'usure et d'étanchéité et de la pièce de rotor portant les léchettes sont conformées de façon à créer en amont de la zone comportant lesdites léchettes et ladite garniture une tuyère convergente-divergente annulaire formant un col primaire.Advantageously, cooperating parts of the support carrying the wear and sealing lining and of the rotor part carrying the wipers are shaped so as to create upstream of the zone comprising said wipers and said lining an annular convergent-diverging nozzle forming a primary neck.

Les résultats les plus avantageux sont obtenus lorsque lesdits perçages du support annulaire sont à la hauteur de ladite partie coopérante formant le col de la tuyère convergente-divergente, faisant ainsi communiquer la chambre de stator et ledit col primaire de ladite tuyère.The most advantageous results are obtained when said holes in the annular support are at the height of said cooperating part forming the neck of the converging-diverging nozzle, thus making the stator chamber and said primary neck of said nozzle communicate.

D'autres caractéristiques et avantages de l'invention seront mieux compris à l'aide de la description qui va suivre en référence aux dessins annexés dans lesquels:

  • La fig. 1 représente une vue schématique en coupe longitudinale d'une partie de turbomachine comportant un dispositif conforme à l'invention;
  • la fig. 2 représente en coupe longitudinale une partie de turbomachine comportant un joint à labyrinthe sous la partie aval d'une chambre de combustion et muni selon l'invention d'un dispositif de contrôle automatique en fonctionnement du jeu du joint à labyrinthe.
Other characteristics and advantages of the invention will be better understood with the aid of the description which follows with reference to the appended drawings in which:
  • Fig. 1 shows a schematic view in longitudinal section of a part of a turbomachine comprising a device according to the invention;
  • fig. 2 shows in longitudinal section a part of a turbomachine comprising a labyrinth seal under the downstream part of a combustion chamber and provided according to the invention with an automatic control device in operation of the clearance of the labyrinth seal.

Sur la fig. 1, on a représenté schématiquement, en coupe axiale, dans des conditions de fonctionnement stabilisé, une partie de turbomachine comportant un mode de réalisation de l'invention. Un joint à labyrinthe conforme à l'invention est disposé entre une partie fixe et une partie tournante de la turbomachine. La partie tournante est représentée schématiquement par une pièce de rotor 1. La partie fixe comporte un élément de stator 2 relié de manière connue à une pièce 3 de la structure fixe de la turbomachine. Dans cet élément de stator 2 est ménagée une chambre annulaire 5 fermée du côté intérieur par un support annulaire 6 sur la face interne de laquelle est fixée dans sa partie aval une garniture 7 d'usure et d'étanchéité. Cette garniture est de tout type connu et couramment utilisée mais de préférence dans le dispositif selon l'invention, la garniture 7 est constituée d'un nid d'abeilles ou d'un type tel que le débit traversant le labyrinthe ne soit pas proportionnel au jeu. L'élément de stator 2 comporte sur son diamètre externe un ou plusieurs orifices 8 d'arrivée d'air et il comporte également à son bord aval un ou plusieurs orifices 9 de sortie d'air. Ces orifices 9 sont placés vers le diamètre interne de l'élément 2 et un ou plusieurs autres orifices 10 de sortie d'air peuvent être placés vers le diamètre externe de l'élément 2, toujours à son bord aval. A l'intérieur de la chambre annulaire 5 de l'élément de stator 2 est disposée une tôle de faible épaisseur 11 percée de séries de multitrous 12. Cette tôle 11 divise la chambre annulaire 5 en deux enceintes, l'une externe 5a comportant les arrivées d'air 8 et l'autre interne 5b comportant les sorties d'air 9 et éventuellement 10. Au droit de la garniture d'usure et d'étanchéité 7, l'arbre 1 porte des léchettes 13 (5 léchettes dans l'exemple représenté). La partie amont du support annulaire 6 portant la garniture d'étanchéité ainsi que la pièce de rotor 1 en amont de la partie portant les léchettes 13 comportent des parties coopérantes 14 sur le support 6 et 15 sur la pièce de rotor 1. Ces parties 14 et 15 sont respectivement conformées de façon à créer dans l'espace amont situé entre le support 6 et la pièce de rotor 1 une tuyère 16 comportant une partie amont convergente 17 et une partie aval divergente 18 reliées par un col 19. La partie amont 14 du support 6 comporte au droit du col 19 un ou plusieurs perçages 20 débouchant d'un côté au col 19 de la tuyère convergente-divergente 16 et de l'autre dans l'enceinte externe 5a de la chambre annulaire 5 de l'élément de stator 2.In fig. 1, there is shown schematically, in axial section, under stabilized operating conditions, a part of a turbomachine comprising an embodiment of the invention. A labyrinth seal according to the invention is disposed between a fixed part and a rotating part of the turbomachine. The rotating part is represented diagrammatically by a rotor part 1. The fixed part comprises a stator element 2 connected in a known manner to a part 3 of the fixed structure of the turbomachine. In this stator element 2 is formed an annular chamber 5 closed on the interior side by an annular support 6 on the internal face of which is fixed in its downstream part a seal 7 for wear and sealing. This lining is of any known and commonly used type, but preferably in the device according to the invention, the lining 7 consists of a honeycomb or of a type such that the flow rate passing through the labyrinth is not proportional to the clearance. The stator element 2 has on its external diameter one or more air inlet orifices 8 and it also has on its downstream edge one or more air outlet orifices 9. These orifices 9 are placed towards the internal diameter of the element 2 and one or more other air outlet orifices 10 can be placed towards the external diameter of the element 2, always at its downstream edge. Inside the annular chamber 5 of the stator element 2 is disposed a thin sheet 11 pierced with series of multi-holes 12. This sheet 11 divides the annular chamber 5 into two enclosures, one external 5a comprising the air inlets 8 and the other internal 5b comprising the air outlets 9 and possibly 10. In line with the wear and seal 7, the shaft 1 carries wipers 13 (5 wipers in the example shown). The upstream part of the annular support 6 carrying the seal and the rotor part 1 upstream of the part carrying the wipers 13 have cooperating parts 14 on the support 6 and 15 on the rotor part 1. These parts 14 and 15 are respectively shaped so as to create in the upstream space located between the support 6 and the rotor part 1 a nozzle 16 comprising a converging upstream part 17 and a diverging downstream part 18 connected by a neck 19. The upstream part 14 of the support 6 comprises, in line with the neck 19, one or more bores 20 opening out on one side at the neck 19 of the convergent-diverging nozzle 16 and on the other in the external enclosure 5a of the annular chamber 5 of the element of stator 2.

Le dispositif conforme à l'invention qui vient d'être décrit permet d'obtenir un fonctionnement amélioré en assurant dans toutes les conditions de fonctionnement de la turbomachine aussi bien en régime stabilisé qu'en régime transitoire un jeu pratiquement constant garantissant une valeur contrôlée du débit d'air traversant le joint à labyrinthe de turbomachine sur lequel est adapté ledit dispositif sans que l'on observe des variations intempestives dont les conséquences sont néfastes pour les rendements ou pour la durée de vie de certaines pièces dans les débits de fuites au niveau du joint à labyrinthe. En effet, si l'on désigne par j1 le jeu entre le sommet des léchettes 13 et la surface interne correspondante de la garniture 7 d'usure et d'étanchéité et par j2 la section, au col 19 de la tuyère 16, lors d'une phase d'accélération rapide de montée au régime plein gaz de la turbomachine, par exemple, par suite des effets combinés des dilatations notamment d'origine mécanique par effet centrifuge et d'origine thermique appliquées aux différents éléments de structure, le jeu j1 peut avoir tendance à diminuer, ainsi que la section j2 au col 19. Si l'on désigne par D1 le débit d'air à l'entrée de l'espace séparant la pièce de rotor 1 et l'élément de stator 2, cet air étant à une température nettement inférieure à celle des gaz dans la veine à la hauteur du dispositif, par D2 le débit d'air entrant dans la chambre annulaire 5 par les orifices 8 de l'élément de stator 2, le point de prélèvement de cet air dans la turbomachine étant choisi de telle sorte que cet air soit plus chaud que celui D1 alimentant le joint, par D3 le débit d'air prélevé à partir de D1 au col 19 de la tuyère 16 par les orifices 20 d'entrée dans la chambre annulaire 5 et par D4 le débit d'air de refroidissement traversant le joint à labyrinthe, dans ce cas, une variation pratiquement insignifiante du débit D4 est observée pendant que l'augmentation de la vitesse locale au col 19 et la diminution de la pression statique entraînent une diminution du débit D3 alors que le débit D2 augmente. Il en résulte une variation relative des débits d'air D2 et D3 alimentant la chambre annulaire 5 dans le sens d'un échauffement. L'air de l'enceinte externe 5a de la chambre 5 faisant par exemple impact à travers la tôle mince multiperforée 11 sur le support annulaire 6 et cet air se réchauffant, le support 6 portant la garniture d'étanchéité 7 se dilate pratiquement immédiatement. De cette façon, les effets tendant à diminuer le jeu j1 sont compensés et annulés et le jeu j1 est maintenu à la valeur objective déterminée pour les résultats visés en fonctionnement stabilisé. En effet, on constate d'après cet exemple que toute tendance à la réduction du jeu j1 quelle qu'en soit l'origine dans le fonctionnement de la turbomachine est immédiatement compensée au moyen du dispositif selon l'invention et le jeu objectif est maintenu.The device according to the invention which has just been described makes it possible to obtain an improved operation by ensuring in all the operating conditions of the turbomachine both in stabilized and transient conditions a practically constant clearance guaranteeing a controlled value of the air flow rate passing through the labyrinth seal of the turbomachine on which said device is adapted without inadvertent variations being observed, the consequences of which are harmful for the yields or for the life of certain parts in the leakage rates at the level of the labyrinth seal. Indeed, if we denote by j1 the clearance between the top of the wipers 13 and the corresponding internal surface of the seal 7 for wear and sealing and by j2 the section, at the neck 19 of the nozzle 16, during '' a rapid acceleration phase of rise to full throttle speed of the turbomachine, for example, as a result of the combined effects of expansions in particular of mechanical origin by centrifugal effect and of thermal origin applied to the various structural elements, the clearance j1 may have a tendency to decrease, as can the section j2 at the neck 19. If D1 denotes the air flow at the inlet of the space separating the rotor part 1 and the stator element 2, this air being at a temperature much lower than that of the gases in the vein at the height of the device, by D2 the air flow entering the annular chamber 5 through the orifices 8 of the stator element 2, the point of sampling of this air in the turbomachine being chosen so that this air is hotter than that D1 supplying the joint, by D3 the air flow taken from D1 at the neck 19 of the nozzle 16 through the orifices 20 of entry into the annular chamber 5 and by D4 the flow of cooling air passing through the joint to labyrinth, in this case, a practically insignificant variation of the flow D4 is observed while the increase in the local speed at the neck 19 and the decrease in the static pressure lead to a reduction in the flow D3 while the flow D2 increases. This results in a relative variation in the air flow rates D2 and D3 supplying the annular chamber 5 in the direction of heating. The air from the external enclosure 5a of the chamber 5 for example impacts through the multi-perforated thin sheet 11 on the annular support 6 and this air warms up, the support 6 carrying the seal 7 expands practically immediately. In this way, the effects tending to decrease the clearance j1 are compensated for and canceled and the clearance j1 is maintained at the objective value determined for the results targeted in stabilized operation. In Indeed, it can be seen from this example that any tendency to reduce the clearance j1 whatever its origin in the operation of the turbomachine is immediately compensated by means of the device according to the invention and the objective clearance is maintained.

De manière similaire, si on passe par exemple à un régime de décélération de la turbomachine, le jeu j1 peut avoir tendance à augmenter et il en est de même pour le jeu j2. Mais dans ce cas, si la section au col 19 augmente et que par conséquent la vitesse locale diminue et que la pression statique augmente, il en résulte une augmentation du débit D3 alors que le débit D2 diminue. Il en résulte une variation relative des débits d'air D2 et D3 alimentant la chambre annulaire 5 dans le sens d'un refroidissement. Par suite, l'air faisant impact sur le support 6 se refroidit et ce support 6 portant la garniture d'étanchéité 7 se contracte pratiquement immédiatement. De cette façon, les effets tendant à accroître le jeu j1 sont compensés et annulés et le jeu j1 est à nouveau maintenu à sa valeur objective et il en sera de même dans toutes les conditions de fonctionnement de la turbomachine tendant à accroître le jeu j1.Similarly, if we go for example to a deceleration regime of the turbomachine, the clearance j1 may tend to increase and the same is true for the clearance j2. But in this case, if the section at the neck 19 increases and that consequently the local speed decreases and the static pressure increases, this results in an increase in the flow D3 while the flow D2 decreases. This results in a relative variation in the air flow rates D2 and D3 supplying the annular chamber 5 in the direction of cooling. As a result, the air impacting on the support 6 cools and this support 6 carrying the seal 7 contracts almost immediately. In this way, the effects tending to increase the play j1 are compensated for and canceled and the play j1 is again maintained at its objective value and it will be the same in all the operating conditions of the turbomachine tending to increase the play j1.

On note ainsi que pour toute variation des conditions de fonctionnement de la turbomachine, on observe une variation relative entre débit d'air chaud D2 et débit d'air froid D3 alimentant la chambre 5 de l'élément de stator 2 de telle sorte que l'incidence sur le jeu j1 du labyrinthe est en sens inverse de la variation de jeu qui résulterait de ces conditions et les effets se compensent dans tous les cas et le dispositif selon l'invention procure par conséquent un moyen de correction automatique, en temps réel, des variations du jeu j1 du labyrinthe pour le maintenir à la valeur objective déterminée.It is thus noted that for any variation in the operating conditions of the turbomachine, there is a relative variation between the flow of hot air D2 and the flow of cold air D3 supplying the chamber 5 of the stator element 2 so that the impact on the game j1 of the labyrinth is in the opposite direction to the variation of game which would result from these conditions and the effects compensate in all cases and the device according to the invention consequently provides an automatic correction means, in real time , variations of the game j1 of the labyrinth to maintain it at the determined objective value.

La fig. 2 représente un mode de réalisation pour une application de l'invention à un joint de labyrinthe placé au droit de la sortie d'une chambre de combustion du côté radialement interne. On a représenté sur cette figure, en 21, la chemise interne d'une chambre de combustion de type annulaire 22, en 23 une enveloppe annulaire définissant une enceinte 24 de ventilation externe de la chambre de combustion. La chemise 21 est reliée à son extrémité aval par un moyen de fixation 25, par exemple du type à boulonnage, à une bride radiale 26 d'une partie interne d'aubage de stator 27. L'enveloppe 23 porte une bride radiale 28 dirigée vers l'axe de la machine et sur laquelle sont fixées par des moyens de fixation, par exemple 29, du type à boulonnage, d'une part, une bride radiale d'extrémité 30 d'un support annulaire 31 qui porte sur sa face interne une garniture d'usure et d'étanchéité 32 et, d'autre part, une bride radiale d'extrémité 33 d'une tôle mince annulaire 34 multiperforée légèrement écartée radialement vers l'extérieur par rapport au support 31 sur lequel elle est en appui radial en 35 à son extrémité aval. A son extrémité aval, le support 31 porte une bride radiale 36 dirigée radialement vers l'extérieur, effectuant la liaison avec la partie interne de l'aubage de stator 27. Au droit de la partie fixe statorique de turbomachine qui vient d'être décrite, la partie tournante rotorique comporte un disque 37 portant dans l'exemple représenté trois léchettes 38 coopérant avec la garniture d'usure et d'étanchéité 32. L'enceinte interne est séparée par le disque 37 en une enceinte amont 39 où l'air est à la pression P1 et une enceinte aval 40 à une pression inférieure P2. L'espace ménagé entre le support annulaire 31 et l'enveloppe de chambre 23 constitue une chambre annulaire 41 permettant la ventilation du support 31 et séparée en deux enceintes 41a a et 41b par la tôle annulaire 34. A cet effet, un passage d'air à travers une ouverture 42a pratiquée dans l'enveloppe 23 est prévu entre l'enceinte 24 et la chambre 41. De même, la partie amont de la garniture d'usure et d'étanchéité 32, du support 31 et de la tôle mince 34 comportent des trous coopérants respectivement 42, 43 et 44 pour le passage d'air vers l'enceinte 41 a de la chambre 41. La tôle mince 34 comporte par ailleurs des multiperfora- tions 45 pour la ventilation par impacts du support 31. Côté aval, le support 31 et la garniture d'usure et d'étanchéité 32 comportent en outre des trous coopérants respectivement 46 et 47 pour l'évacuation de l'air de la chambre 41. Le disque porte- léchettes 37 comporte sur son diamètre extérieur côté amont une partie en forme de doigt 48 dont l'extrémité 49 ainsi que la surface coopérante 50 de la partie amont de la garniture d'usure et d'étanchéité 32 sont respectivement conformées de façon à créer une tuyère de forme convergente-divergente annulaire en créant un col 51 au niveau duquel sont ouvertes les prises d'air vers la chambre 41 par les trous 42. De même, côté aval, le disque 37 porte également un doigt 52 dont l'extrémité 53 coopère avec la surface en regard de la partie aval de la garniture d'usure et d'étanchéité 32, à travers laquelle débouchent les trous d'évacuation 47.Fig. 2 shows an embodiment for an application of the invention to a labyrinth seal placed in line with the outlet of a combustion chamber on the radially internal side. There is shown in this figure, at 21, the internal jacket of an annular type combustion chamber 22, at 23 an annular casing defining an enclosure 24 for external ventilation of the combustion chamber. The jacket 21 is connected at its downstream end by a fixing means 25, for example of the bolt-on type, to a radial flange 26 of an internal part of stator vane 27. The casing 23 carries a directed radial flange 28 towards the axis of the machine and to which are fixed by fixing means, for example 29, of the bolt type, on the one hand, a radial end flange 30 of an annular support 31 which bears on its face internally a wear and sealing lining 32 and, on the other hand, a radial end flange 33 of an annular thin sheet metal 34 multi-perforated slightly spaced radially outward relative to the support 31 on which it is radial support at 35 at its downstream end. At its downstream end, the support 31 carries a radial flange 36 directed radially outwards, making the connection with the internal part of the stator blade 27. In line with the stator fixed part of the turbomachine which has just been described , the rotary rotor part comprises a disc 37 carrying in the example shown three wipers 38 cooperating with the wear and sealing lining 32. The internal enclosure is separated by the disc 37 into an upstream enclosure 39 where the air is at pressure P1 and a downstream enclosure 40 at a lower pressure P2. The space formed between the annular support 31 and the chamber envelope 23 constitutes an annular chamber 41 allowing the ventilation of the support 31 and separated into two enclosures 41a a and 41b by the annular sheet 34. For this purpose, a passage of air through an opening 42a made in the envelope 23 is provided between the enclosure 24 and the chamber 41. Likewise, the upstream part of the wear and sealing lining 32, of the support 31 and of the thin sheet 34 have cooperating holes 42, 43 and 44 respectively for the passage of air towards the enclosure 41 a of the chamber 41. The thin sheet 34 also comprises multi-perforations 45 for the ventilation by impacts of the support 31. Side downstream, the support 31 and the wear and sealing lining 32 also have cooperating holes 46 and 47 respectively for the evacuation of the air from the chamber 41. The wiping disc 37 has on its outside diameter upstream side a finger-shaped part 48 whose end 49 as well as the cooperating surface 50 of the upstream part of the wear and sealing lining 32 are respectively shaped so as to create a nozzle of annular convergent-diverging shape by creating a neck 51 at the level of which the catches are open. air towards the chamber 41 through the holes 42. Likewise, on the downstream side, the disc 37 also carries a finger 52, the end 53 of which cooperates with the surface facing the downstream part of the wear and sealing lining 32 , through which the drainage holes 47 open.

On obtient à nouveau un contrôle automatique en temps réel des variations du jeu du joint à labyrinthe pour le maintenir à une valeur objective déterminée. Le fonctionnement permettant d'obtenir ce résultat est identique à celui qui a été décrit auparavant en référence à la fig. 1.Once again, automatic control in real time of the variations in the play of the labyrinth seal is obtained in order to maintain it at a determined objective value. The operation enabling this result to be obtained is identical to that which has been described previously with reference to FIG. 1.

Claims (6)

1. Device for automatically controlling, during operation, the clearance (j1) corresponding to a passage cross-section formed in a turbo-engine gasket of the labyrinth type between wiper-like gasket elements (13; 38) carried by a rotor part (1; 37) and an interacting gasket element consisting of a wearing and sealing strip (7; 32) placed opposite the said wipers (13; 38) and carried by an annular support (6; 31) forming the radially inner stator part, the said stator having an annular chamber (5; 41) equipped, on its outer diameter, with heating-air inlet ports (8; 42) and, at its downstream edge, with air outlet ports (9, 10; 47), a thin metal plate (11; 34) containing multiple holes (12; 45) being arranged inside the said chamber (5; 41) at a short distance from the said annular support (6; 31), characterized in that the upstream part of the annular support (6; 31) carrying the wearing and sealing strip (7; 32) has a series of peripherally distributed bores (20; 43) connecting the said annular chamber (5, 41) and the upstream part of the said passage cross-section of the gasket, so as to be fed as a result of a take-off from the cooling air passing through the labyrinth gasket.
2. Device for automatically controlling the clearance of a labyrinth gasket according to claim 1, characterized in that interacting parts (14; 15) of the support (6) carrying the wearing and sealing strip (7) and of the rotor part (1) carrying the wipers (13) are shaped in such a way as to produce, upstream of the zone containing the said wipers (13) and the said strip (7), an annular convergent-divergent nozzle (16) forming a primary neck (19).
3. Device for automatically controlling the clearance of a labyrinth gasket according to claim 1, characterized in that interacting parts (50; 49) of the wearing and sealing strip (32) and of the end of a finger (48) carried, upstream of the wipers (38), by a rotor disc (37) are shaped in such a way as to produce an annular convergent-divergent nozzle forming a primary neck (51).
4. Device for automatically controlling the clearance of a labyrinth gasket according to claim 2, characterized in that the said bores (20) in the annular support (6) are level with the said interacting part (14) forming the convergent-divergent nozzle (16), in line with the neck (19), thereby putting the said outer wall (5a) of the said stator chamber (5) and the said primary neck (19) of the said nozzle (16) in communication with one another.
5. Device for automatically controlling the clearance of a labyrinth gasket according to claim 3, characterized in that the said bores (43) in the annular support (31) and the corresponding bores (42,44) in the wearing and sealing strip (32) and in the thin metal plate (34) respectively are arranged in line with the interacting parts (50, 49) forming the said convergent-divergent nozzle.
6. Device for automatically controlling the clearance of a labyrinth gasket according to any one of claims 1, 3 and 5, characterized in that corresponding bores (46) in the downstream part of the annular support (31) and (47) in the downstream part of the wearing and sealing strip (32) and intended for discharging the air from the annular chamber (41) open out level with the neck of a convergent-divergent nozzle formed by the interacting parts of the end (53) of a finger (52) carried, downstream of the wipers (38), by the rotor disc (37) and of the opposite surface of the wearing and sealing strip (32).
EP85401863A 1984-09-27 1985-09-25 Apparatus for the automatic control of the play of a labyrinth seal of a turbo machine Expired EP0177408B1 (en)

Applications Claiming Priority (2)

Application Number Priority Date Filing Date Title
FR8414818 1984-09-27
FR8414818A FR2570763B1 (en) 1984-09-27 1984-09-27 DEVICE FOR AUTOMATICALLY CONTROLLING THE PLAY OF A TURBOMACHINE LABYRINTH SEAL

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EP0177408A1 EP0177408A1 (en) 1986-04-09
EP0177408B1 true EP0177408B1 (en) 1988-08-24

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US (1) US4668163A (en)
EP (1) EP0177408B1 (en)
JP (1) JPS6183403A (en)
DE (1) DE3564600D1 (en)
FR (1) FR2570763B1 (en)

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US4513975A (en) * 1984-04-27 1985-04-30 General Electric Company Thermally responsive labyrinth seal

Cited By (1)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
DE4110616A1 (en) * 1990-04-03 1991-10-10 Gen Electric THERMALLY TUNED ROTARY BABYRIN SEAL WITH ACTIVE GASKET CONTROL

Also Published As

Publication number Publication date
FR2570763B1 (en) 1986-11-28
JPH0379524B2 (en) 1991-12-19
DE3564600D1 (en) 1988-09-29
US4668163A (en) 1987-05-26
FR2570763A1 (en) 1986-03-28
JPS6183403A (en) 1986-04-28
EP0177408A1 (en) 1986-04-09

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