EP0192516B1 - Gas turbine shroud - Google Patents

Gas turbine shroud Download PDF

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Publication number
EP0192516B1
EP0192516B1 EP86400133A EP86400133A EP0192516B1 EP 0192516 B1 EP0192516 B1 EP 0192516B1 EP 86400133 A EP86400133 A EP 86400133A EP 86400133 A EP86400133 A EP 86400133A EP 0192516 B1 EP0192516 B1 EP 0192516B1
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EP
European Patent Office
Prior art keywords
segments
turbine
grooves
support lugs
sectors
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
EP86400133A
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German (de)
French (fr)
Other versions
EP0192516A1 (en
Inventor
Jean-François Robert Imbault
Rolant René Mestre
Carmen Miraucourt
Rémy Paul Charles Ritt
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 Aircraft Engines SAS
Original Assignee
Societe Nationale dEtude et de Construction de Moteurs dAviation SNECMA
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Publication date
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Publication of EP0192516A1 publication Critical patent/EP0192516A1/en
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Publication of EP0192516B1 publication Critical patent/EP0192516B1/en
Expired legal-status Critical Current

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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
    • 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
    • F01D25/00—Component parts, details, or accessories, not provided for in, or of interest apart from, other groups
    • F01D25/24—Casings; Casing parts, e.g. diaphragms, casing fastenings
    • F01D25/246—Fastening of diaphragms or stator-rings

Definitions

  • the latter is made of a metallic material, so that when the wear material is a ceramic material, due to the large difference between the coefficients of expansion of metallic materials and ceramic materials the ring made of ceramic material must be formed from sectors independent of each other and coupled by their respective ends in order to allow the radius of the ring to follow the variations in the radius of the annular support as a function of the different temperatures that the latter takes for the different regimes of the turbine. This prevents the ring from being subjected to stresses incompatible with the mechanical resistance of the ceramic material which constitutes it.
  • the seal between contiguous sectors can be ensured by tongues engaged axially in first grooves made at the same radial level on the sides opposite said contiguous sectors.
  • the present invention relates to a turbine ring of this kind, but more specifically aims at an improved attachment method of the sectors on the annular support in order to minimize the thermal tensile stresses therein which ceramic materials have difficulty in cash out.
  • each sector has a median recess formed from the radially outer face of the sector two second axial grooves, circumferentially spaced, opening facing the side faces of the recess and in said second grooves engage the support fingers integral with a ferrule connected to the turbine casing and ensuring the attachment of the sectors one after the other all around the turbine, these attachment support fingers being housed in the grooves sheltered from the reintroduction of hot gases.
  • sealing between contiguous sectors can be advantageously ensured by tongues engaged axially in suitable grooves made at the same radial level on the flanks facing said contiguous sectors, as described in French patent 2,540,938 above- mentionned.
  • the ferrule has orifices through which pass jets of cooling air, these orifices being inclined so as to direct the jets on said support fingers.
  • springs arranged between the sectors and a cylindrical outer shell element ensure positive contact between finger-supports and axial grooves.
  • the pressure of these springs contributes to the damping of vibrations of which the sectors could be the object.
  • the annular space located beyond the sectors in the radial direction is subdivided into two cavities serving one for the cooling of the sectors and the other for controlling the expansions of the stator and by Consequently, the resulting play between the rotor and the turbine stator, these two cavities being separated by a sheet, the support of which on the radially external face of the sectors and the sealing are provided by said springs.
  • the insulation of the turbine casing from hot gases is also thus improved.
  • the present invention allows its use, thereby obtaining the advantages which result therefrom: thermal protection of the stator, reduction of the ventilation flow rate of the sectors due to their low thermal conductivity.
  • the ring illustrated in the drawings consists of a circumferential succession of sectors 1 of a suitable abradable ceramic material such as a known composite formed of silicon carbide fibers embedded in a matrix of this same material, having good resistance to high temperatures, low thermal conductivity and good wear properties.
  • a suitable abradable ceramic material such as a known composite formed of silicon carbide fibers embedded in a matrix of this same material, having good resistance to high temperatures, low thermal conductivity and good wear properties.
  • Each ceramic sector 1 has two axial grooves 1a, 1 circumferentially spaced and facing each other. These grooves 1a, 1b allow the attachment of the sector 1 on support fingers 4 projecting in the axial direction of an upstream ferrule 3 connected forwards to the turbine casing at 3a and rearwards to a ferrule downstream 2.
  • the latter has a notch 8 obtained by machining to allow centering of the support fingers 4.
  • a cavity 9 located just above the ring is put at a pressure higher than the pressure prevailing in the vein (by means of air from the bottom of the chamber, taken from the enclosure of the combustion chamber), this which has the effect of preventing hot air from coming up from the vein.
  • the ring sectors 1 are mounted cold pinched slightly upstream and downstream, which leads hot to a slight clearance allowing the evacuation of the pressurization air from the cavity 9 and the ventilation of the ferrules 2 and 3 at their inner radius, as shown by the arrows F1 in FIG. 3.
  • a sheet 7 separates the cavity 9 from a cavity 10.
  • the piloting air is circulated, as shown by the arrows F2, making it possible to control the expansions of the assembly by acting on the temperature of the ferrules 2 and 3.
  • This pilot air from the support ring can be taken from an intermediate stage of the compressor and reused for other ventilation (BP distributor for example) or evacuated in the secondary channel.
  • the support fingers 4 can be cooled by air jets exiting from orifices 11, as shown by the arrows F3 in FIG. 5.
  • This air for ventilation of the support ring can be taken from an intermediate stage of the compressor and evacuated then in the secondary channel.
  • the position of the grooves la, Ib makes it possible to place the fastening fingers 4 in a cooler zone while having a high temperature for the ring sectors 1, the proposed shape allowing effective thermal protection of the fastening.

Description

Les brevets français publiés sous les numéros 2 371 575, 2 540 937, 2 540 938, 2 540 939 décrivent des anneaux de turbine à gaz comportant chacun d'une part un support annulaire fixé à l'intérieur du carter de turbine et d'autre part un anneau constitué au moins partiellement en un matériau d'usure (appelé ci-après « abradable ») et fixé à son tour à l'intérieur de ce support annulaire. Dans la plupart de ces réalisations, ce dernier est en un matériau métallique, de sorte que lorsque le matériau d'usure est un matériau céramique, par suite de la grande différence entre les coefficients de dilatation des matériaux métalliques et des matériaux céramiques l'anneau en matériau céramique doit être formé de secteurs indépendants les uns des autres et accouplés par leurs extrémités respectives afin de permettre au rayon de l'anneau de suivre les variations du rayon du support annulaire en fonction des températures différentes que prend ce dernier pour les différents régimes de fonctionnement de la turbine. On évite ainsi que l'anneau ne soit soumis à des contraintes incompatibles avec la résistance mécanique du matériau céramique qui le constitue.French patents published under the numbers 2 371 575, 2 540 937, 2 540 938, 2 540 939 describe gas turbine rings each comprising on the one hand an annular support fixed inside the turbine casing and on the other hand a ring made at least partially of a wear material (hereinafter called "abradable") and fixed in turn inside this annular support. In most of these embodiments, the latter is made of a metallic material, so that when the wear material is a ceramic material, due to the large difference between the coefficients of expansion of metallic materials and ceramic materials the ring made of ceramic material must be formed from sectors independent of each other and coupled by their respective ends in order to allow the radius of the ring to follow the variations in the radius of the annular support as a function of the different temperatures that the latter takes for the different regimes of the turbine. This prevents the ring from being subjected to stresses incompatible with the mechanical resistance of the ceramic material which constitutes it.

Par ailleurs, l'étanchéité entre secteurs contigus peut être assurée par des languettes engagées axialement dans des premières rainures pratiquées au même niveau radial sur les flancs en regard desdits secteurs contigus.Furthermore, the seal between contiguous sectors can be ensured by tongues engaged axially in first grooves made at the same radial level on the sides opposite said contiguous sectors.

La présente invention a pour objet un anneau de turbine de ce genre, mais vise plus spécialement un mode d'accrochage perfectionné des secteurs sur le support annulaire afin d'y réduire au minimum les contraintes thermiques de traction que les matériaux céramiques ont du mal à encaisser.The present invention relates to a turbine ring of this kind, but more specifically aims at an improved attachment method of the sectors on the annular support in order to minimize the thermal tensile stresses therein which ceramic materials have difficulty in cash out.

Ainsi, à la différence du brevet français 2 371 575 mentionné en premier où les secteurs comportent sur leurs bords des cavités dans lesquelles sont montés des tubes, le mode d'accrochage de la présente invention se caractérise en ce que chaque secteur présente un évidement médian ménagé à partir de la face radialement extérieure du secteur deux secondes rainures axiales, espacées circonférentiellement, débouchant en vis à vis sur les faces latérales de l'évidement et dans lesdites secondes rainures s'engagent les doigts-supports solidaires d'une virole reliée au carter de turbine et assurant l'accrochage des secteurs les uns à la suite des autres tout autour de la turbine, ces doigts-supports d'accrochage se trouvant logés dans les rainures à l'abri des réintroductions de gaz chauds.Thus, unlike the French patent 2 371 575 mentioned first where the sectors have cavities on their edges in which tubes are mounted, the method of attachment of the present invention is characterized in that each sector has a median recess formed from the radially outer face of the sector two second axial grooves, circumferentially spaced, opening facing the side faces of the recess and in said second grooves engage the support fingers integral with a ferrule connected to the turbine casing and ensuring the attachment of the sectors one after the other all around the turbine, these attachment support fingers being housed in the grooves sheltered from the reintroduction of hot gases.

D'ailleurs, l'étanchéité entre secteurs contigus peut être avantageusement assurée par des languettes engagées axialement dans des rainures adéquates pratiquées au même niveau radial sur les flancs en regard desdits secteurs contigus, de la façon décrite dans le brevet français 2 540 938 sus-mentionné.Moreover, the sealing between contiguous sectors can be advantageously ensured by tongues engaged axially in suitable grooves made at the same radial level on the flanks facing said contiguous sectors, as described in French patent 2,540,938 above- mentionned.

Dans un mode de réalisation préféré de la présente invention, la virole comporte des orifices par lesquels passent des jets d'air de refroidissement, ces orifices étant inclinés de manière à diriger les jets sur lesdits doigts-supports.In a preferred embodiment of the present invention, the ferrule has orifices through which pass jets of cooling air, these orifices being inclined so as to direct the jets on said support fingers.

Par ailleurs, des ressorts en disposés entre les secteurs et un élément cylindrique de virole externe assurent un contact positif entre doigts-supports et rainures axiales. La pression de ces ressorts contribue à l'amortissement des vibrations dont les secteurs pourraient être l'objet.Furthermore, springs arranged between the sectors and a cylindrical outer shell element ensure positive contact between finger-supports and axial grooves. The pressure of these springs contributes to the damping of vibrations of which the sectors could be the object.

Selon une particularité technique de la présente invention, l'espace annulaire situé au-delà des secteurs dans le sens radial est subdivisé en deux cavités servant l'une pour le refroidissement des secteurs et l'autre pour le pilotage des dilatations du stator et par conséquent des jeux qui en résultent entre rotor et stator de turbine, ces deux cavités étant séparées par une tôle dont l'appui sur la face radialement externe des secteurs et l'étanchéité sont assurés par lesdits ressorts.According to a technical feature of the present invention, the annular space located beyond the sectors in the radial direction is subdivided into two cavities serving one for the cooling of the sectors and the other for controlling the expansions of the stator and by Consequently, the resulting play between the rotor and the turbine stator, these two cavities being separated by a sheet, the support of which on the radially external face of the sectors and the sealing are provided by said springs.

L'isolation du carter de turbine vis-à-vis des gaz chauds se trouve également ainsi amélioré.The insulation of the turbine casing from hot gases is also thus improved.

Ainsi, en assurant une meilleure tenue en service des secteurs en matériaux céramiques, la . présente invention en permet l'utilisation, procurant de la sorte les avantages qui en découlent : protection thermique du stator, réduction du débit de ventilation des secteurs du fait de leur faible conductivité thermique.Thus, by ensuring better service performance of the ceramic material sectors, the. the present invention allows its use, thereby obtaining the advantages which result therefrom: thermal protection of the stator, reduction of the ventilation flow rate of the sectors due to their low thermal conductivity.

Un avantage important qui résulte de la position des secondes rainures axiales de support à l'intérieur des secteurs est la protection thermique des doigts-supports ainsi obtenue. En outre, cette disposition permet seule d'adjoindre des joints d'étanchéité intersecteurs logés dans les rainures supplémentaires ménagées dans les bords axiaux de deux secteurs consécutifs.An important advantage which results from the position of the second axial support grooves inside the sectors is the thermal protection of the support fingers thus obtained. In addition, this arrangement alone makes it possible to add intersector seals housed in the additional grooves formed in the axial edges of two consecutive sectors.

La description qui va suivre en regard des dessins annexés, donnée à titre d'exemple non limitatif, fera bien comprendre comment l'invention peut être réalisée.

  • La figure 1 est une vue schématique partielle en coupe selon la ligne I-I de la figure 3, d'un mode de réalisation d'anneau de turbine conforme à la présente invention.
  • La figure 2 est une vue analogue en coupe circonférentielle selon la ligne II-II de la figure 1.
  • Les figures 3 et 4 sont des vues en coupe radiale selon les lignes III-III et IV-IV respectivement de la figure 1. La figure 5 montre en perspective la configuration des doigts-supports solidaires d'une virole de turbine.
The description which follows with reference to the appended drawings, given by way of nonlimiting example, will make it clear how the invention can be implemented.
  • Figure 1 is a partial schematic sectional view along line II of Figure 3, of an embodiment of the turbine ring according to the present invention.
  • FIG. 2 is a similar view in circumferential section along the line II-II of FIG. 1.
  • Figures 3 and 4 are views in radial section along lines III-III and IV-IV respectively of Figure 1. Figure 5 shows in perspective the configuration of the support fingers integral with a turbine shell.

L'anneau illustré sur les dessins est constitué d'une succession circonférentielle de secteurs 1 en un matériau céramique abradable adéquat tel qu'un composite connu formé de fibres de carbure de silicium noyées dans une matrice de cette même matière, présentant une bonne tenue aux températures élevées, une faible conductivité thermique et de bonnes propriétés d'usure.The ring illustrated in the drawings consists of a circumferential succession of sectors 1 of a suitable abradable ceramic material such as a known composite formed of silicon carbide fibers embedded in a matrix of this same material, having good resistance to high temperatures, low thermal conductivity and good wear properties.

Chaque secteur céramique 1 comporte deux rainures axiales 1a, 1 espacées circonférentiellement et en vis-à-vis l'une de l'autre. Ces rainures 1a, 1 b permettent l'accrochage du secteur 1 sur des doigts-supports 4 faisant saillie dans le sens axial d'une virole amont 3 reliée vers l'avant au carter de turbine en 3a et vers l'arrière à une virole aval 2. Cette dernière présente une encoche 8 obtenue par usinage pour permettre le centrage des doigts-supports 4.Each ceramic sector 1 has two axial grooves 1a, 1 circumferentially spaced and facing each other. These grooves 1a, 1b allow the attachment of the sector 1 on support fingers 4 projecting in the axial direction of an upstream ferrule 3 connected forwards to the turbine casing at 3a and rearwards to a ferrule downstream 2. The latter has a notch 8 obtained by machining to allow centering of the support fingers 4.

Des ressorts 5 maintiennent les secteurs d'anneau 1 plaqués contre les doigts 4. L'étanchéité entre deux secteurs d'anneau adjacents est assurée par une languette 6 (en même composite céramique par exemple) que l'on glisse axialement dans deux rainures 1c, 1d pratiquées dans les flancs en regard des secteurs 1.Springs 5 hold the ring sectors 1 pressed against the fingers 4. The seal between two adjacent ring sectors is ensured by a tongue 6 (in the same ceramic composite for example) which is slid axially in two grooves 1c , 1d practiced in the flanks facing sectors 1.

La ventilation de cet anneau de turbine est exécutée de la façon suivante :The ventilation of this turbine ring is carried out as follows:

Une cavité 9 située juste au-dessus de l'anneau est mise à une pression supérieure à la pression régnant dans la veine (grâce à de l'air du fond de chambre, prélevé dans l'enceinte de la chambre de combustion), ce qui a pour effet d'empêcher les remontées d'air chaud provenant de la veine. Les secteurs d'anneau 1 sont montés à froid légèrement pincés à l'amont et à l'aval, ce qui conduit à chaud à un léger jeu permettant l'évacuation de l'air de pressurisation de la cavité 9 et la ventilation des viroles 2 et 3 à leur rayon intérieur, comme montré par les flèches F1 sur la figure 3.A cavity 9 located just above the ring is put at a pressure higher than the pressure prevailing in the vein (by means of air from the bottom of the chamber, taken from the enclosure of the combustion chamber), this which has the effect of preventing hot air from coming up from the vein. The ring sectors 1 are mounted cold pinched slightly upstream and downstream, which leads hot to a slight clearance allowing the evacuation of the pressurization air from the cavity 9 and the ventilation of the ferrules 2 and 3 at their inner radius, as shown by the arrows F1 in FIG. 3.

Une tôle 7 sépare la cavité 9 d'une cavité 10. Dans cette dernière cavité, on fait circuler l'air de pilotage, comme montré par les flèches F2, permettant de piloter les dilatations de l'ensemble en agissant sur la température des viroles 2 et 3. Cet air de pilotage de l'anneau support peut être prélevé à un étage intermédiaire du compresseur et réutilisé pour d'autres ventilations (distributeur BP par exemple) ou évacué dans le canal secondaire.A sheet 7 separates the cavity 9 from a cavity 10. In this last cavity, the piloting air is circulated, as shown by the arrows F2, making it possible to control the expansions of the assembly by acting on the temperature of the ferrules 2 and 3. This pilot air from the support ring can be taken from an intermediate stage of the compressor and reused for other ventilation (BP distributor for example) or evacuated in the secondary channel.

Les doigts-supports 4 peuvent être refroidis par jets d'air sortant d'orifices 11, comme le montrent les flèches F3 de la figure 5. Cet air de ventilation de l'anneau support peut être prélevé à un étage intermédiaire du compresseur et évacué ensuite dans le canal secondaire. La position des rainures la, Ib permet de placer les doigts d'accrochage 4 dans une zone plus froide tout en ayant une température élevée pour les secteurs d'anneau 1, la forme proposée permettant une protection thermique efficace de l'accrochage.The support fingers 4 can be cooled by air jets exiting from orifices 11, as shown by the arrows F3 in FIG. 5. This air for ventilation of the support ring can be taken from an intermediate stage of the compressor and evacuated then in the secondary channel. The position of the grooves la, Ib makes it possible to place the fastening fingers 4 in a cooler zone while having a high temperature for the ring sectors 1, the proposed shape allowing effective thermal protection of the fastening.

Claims (4)

1. Turbine ring mounted on an annular support fixed inside the turbine housing and consisting of a succession of contiguous segments made of abradable ceramic material and comprising, at the same radial height on their facing sides, a first set of axial grooves (1 c, 1d) inside which sealing tongues (6) are arranged, characterized in that each segment (1) has a middle recess formed in the radially external surface of the segment (1), a second set of axial grooves (1a, 1b) located circumferentially at a distance from each other and opening out opposite each other on the side faces of the recess and into which second set of grooves (1a, 1b) engage support lugs (4) integral with a collar (3) connected to the turbine housing and ensuring fixing of the segments (1) in succession, these fixing support lugs (4) being accommodated inside the grooves (ia, 1b) so as to be protected from the reintroduction of hot gases.
2. Turbine ring according to Claim 1, characterized in that the collar (3) has orifices (11) through which jets of cooling air pass, these orifices being inclined so as to direct the jets onto the said support lugs (4).
3. Turbine ring according to one of Claims 1 and 2, characterized in that omega-shaped springs (5) are arranged between the radially external surface of the segments (1) and the corresponding internal surface of a cylindrical collar element (2) so as to ensure positive radial contact between support lugs (4) and axial grooves (1a, 1b) of a segment.
4. Turbine ring according to any one of Claims 1 to 3, characterized in that the annular space located beyond the segments (1) in the radial direction is subdivided into two cavities (9, 10), one of which is used for cooling the segments and the other for controlling the expansions of the stator and consequently the play resulting therefrom between the turbine stator and rotor, these two cavities (9, 10) being separated by a metal sheet (7), the said springs (5) ensuring that the said metal sheet bears against the radially external surface of the segments (1) and forms a seal.
EP86400133A 1985-01-30 1986-01-23 Gas turbine shroud Expired EP0192516B1 (en)

Applications Claiming Priority (2)

Application Number Priority Date Filing Date Title
FR8501266 1985-01-30
FR8501266A FR2576637B1 (en) 1985-01-30 1985-01-30 GAS TURBINE RING.

Publications (2)

Publication Number Publication Date
EP0192516A1 EP0192516A1 (en) 1986-08-27
EP0192516B1 true EP0192516B1 (en) 1988-09-28

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Application Number Title Priority Date Filing Date
EP86400133A Expired EP0192516B1 (en) 1985-01-30 1986-01-23 Gas turbine shroud

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US (1) US4676715A (en)
EP (1) EP0192516B1 (en)
DE (1) DE3660826D1 (en)
FR (1) FR2576637B1 (en)

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Also Published As

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DE3660826D1 (en) 1988-11-03
FR2576637A1 (en) 1986-08-01
US4676715A (en) 1987-06-30
EP0192516A1 (en) 1986-08-27
FR2576637B1 (en) 1988-11-18

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