EP1593814B1 - Feather seal configuration for a gas turbine shroud - Google Patents
Feather seal configuration for a gas turbine shroud Download PDFInfo
- Publication number
- EP1593814B1 EP1593814B1 EP05290784A EP05290784A EP1593814B1 EP 1593814 B1 EP1593814 B1 EP 1593814B1 EP 05290784 A EP05290784 A EP 05290784A EP 05290784 A EP05290784 A EP 05290784A EP 1593814 B1 EP1593814 B1 EP 1593814B1
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- European Patent Office
- Prior art keywords
- axial
- radial
- segments
- slots
- slot
- Prior art date
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- 210000003746 feather Anatomy 0.000 title 1
- 238000007789 sealing Methods 0.000 claims description 30
- 125000006850 spacer group Chemical group 0.000 claims description 29
- 238000011144 upstream manufacturing Methods 0.000 claims description 10
- 210000002105 tongue Anatomy 0.000 description 19
- 238000001816 cooling Methods 0.000 description 12
- 239000007789 gas Substances 0.000 description 12
- 238000002485 combustion reaction Methods 0.000 description 5
- 230000000712 assembly Effects 0.000 description 2
- 238000000429 assembly Methods 0.000 description 2
- 230000004888 barrier function Effects 0.000 description 2
- 230000008602 contraction Effects 0.000 description 2
- 230000001627 detrimental effect Effects 0.000 description 2
- 238000003754 machining Methods 0.000 description 1
- 238000012423 maintenance Methods 0.000 description 1
- 239000000463 material Substances 0.000 description 1
- 238000012986 modification Methods 0.000 description 1
- 230000004048 modification Effects 0.000 description 1
- 230000001629 suppression Effects 0.000 description 1
Images
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
- F01D11/005—Sealing means between non relatively rotating elements
Definitions
- the present invention relates to the general field of stationary ring assemblies of a gas turbine. It is more particularly fixed ring assemblies of a high-pressure turbomachine turbine consisting of a plurality of segments joined end to end with the interposition of sealing tabs.
- the rotor blades are surrounded by a fixed ring assembly forming an envelope.
- the fixed ring assembly thus defines one of the walls of the flow passage of hot gases from the combustion chamber of the turbomachine and passing through the turbine.
- the fixed ring assembly consists of a turbine ring attached to the turbine casing via a spacer.
- the ring and the spacer of such a fixed ring assembly are sectored, that is to say that they each consist of a plurality of segments joined end to end.
- the fixed ring assembly thus defined being directly in contact with the hot gases from the combustion chamber, it is necessary to cool the various segments that compose it.
- air taken from the chamber bottom circulates in a cooling circuit arranged in each segment of the fixed ring assembly and is discharged into the gas flow line upstream of the turbine blades.
- the radial and axial slots in which the sealing tabs are housed are generally machined so that they are contiguous, ie they communicate with each other. This arrangement is necessitated by the fact that the sealing tabs must cover a maximum surface of the lateral faces of the segments in order to obtain an optimum seal.
- FIG. 5 there are shown partially two segments 100, 100 'of the fixed ring assembly each provided with an axial slot 102, 102' and a radial slot 104, 104 '. Sealing tabs 106, 108 are respectively housed in the axial and radial slots.
- the clearance 110 existing between the tongues and the slots arises from the fact that, as the segments are exposed to the hot gases coming from the combustion chamber, they undergo thermal expansions and contractions which are reflected at the level of the clearance 112 existing between the two segments. adjacent.
- the present invention therefore aims to overcome such drawbacks by proposing a gas turbine fixed ring assembly whose segments which constitute it have a particular geometry of the slots and sealing tabs to reduce leakage between two adjacent segments.
- a fixed ring assembly forming a rotor envelope of a gas turbine, the fixed ring assembly having a plurality of segments including adjacent side faces are placed end to end with the interposition of sealing means, the sealing means comprising at least one axial sealing tongue and at least one radial sealing tongue housed respectively in at least one axial slot and at least one radial slot; formed opposite the adjacent side faces of the segments, the radial slot opening at least at one of its ends in the axial slot, characterized in that the axial slot of the lateral faces of each segment has a greater depth to that of the radial slot and in that the axial sealing tongue has a width greater than that of the radial tongue.
- the axial sealing tab housed in a deeper slot makes it possible to cover the leakage sections observed in the prior art. In this way, it is possible to reduce air leakage between two adjacent segments which improves their cooling. With identical cooling, it is also possible to reduce the air flow required for cooling, and therefore to increase the efficiency of the turbine.
- Another advantage of the invention resides in the fact that this suppression of these air leaks is carried out without the addition of ancillary parts (angle-type) detrimental to the mass of the assembly, does not require significant modifications. slots and sealing tabs and does not involve maintenance problems.
- the fixed ring assembly may constitute a high-pressure turbine ring of a turbomachine.
- each ring segment may comprise, at its lateral faces, two axial slots disposed on the inner and outer wall side and in which axial tongues are housed, and two radial slots arranged on the upstream side of walls and downstream and in which are housed radial tongues.
- the fixed ring assembly may also constitute a spacer on which is fixed the high-pressure turbine ring of the turbomachine.
- each spacer segment may comprise, at its lateral faces, an axial slot in which is housed an axial tongue, and at least three radial slots, two of which are housed on the side of its upstream and downstream walls and in which are accommodated radial tongues.
- a turbomachine high-pressure turbine 2 having a longitudinal axis XX is composed in particular of a plurality of rotor blades 4 and arranged in the annular duct 6 for the flow of hot gases from the combustion chamber (not shown).
- a plurality of fixed vanes 8 forming a high-pressure distributor are also arranged in the flow duct 6, upstream of the blades 4 relative to the direction of flow 10 of the gases.
- the blades 4 are surrounded by a fixed ring assembly 12 forming an envelope.
- This fixed ring assembly consists of a turbine ring attached to a casing 14 of the turbine through a plurality of spacer segments 18. More particularly, the turbine ring is composed of a plurality ring segments 16 joined end to end. By way of example, there can be two ring segments 16 mounted on a single spacer segment 18.
- the fixed ring assembly 12 thus defined comprises an air circulation circuit for cooling the ring segments 16 and spacer 18 which are exposed to hot gases from the combustion chamber.
- the fixed ring assembly 12 is provided with a cooling circuit.
- a hole 20 is drilled in the upstream radial wall 22a of each spacer segment 18 and opens into a cavity 24 formed between the casing 14 and the spacer segment 18.
- the air distributed in this cavity 24 comes from a sample performed at the bottom of the chamber and then feeds a cooling circuit of the spacer segment 18 and the ring segment or segments 16 mounted thereon. The air is finally discharged into the flow line 6 of the hot gases, upstream of the blades 4 of the turbine.
- sealing barriers are interposed between two adjacent ring 16 and spacer 18 segments. These barriers consist of sealing tabs housed in axial and radial slots made opposite each other in the slots. adjacent side faces of the segments 16, 18.
- axial slots it is meant that these slots extend substantially axially, that is to say along the longitudinal axis XX of the high-pressure turbine 2.
- radial slots means that these slots extend substantially radially, ie in a direction perpendicular to the longitudinal axis XX.
- each ring segment 16 is provided with at least one axial slot 26 and at least one radial slot 28 formed on its lateral faces 30.
- the lateral faces 30 of the ring segment each comprise two axial slots 26 and two radial slots 28.
- the axial slots 26 are for example arranged on the side of the inner walls 32a and outer 32b of the ring segment 16.
- the radial slots 28 they are for example positioned on the side of the upstream axial walls 34a and downstream 34b of the segment 16.
- Such a distribution of the axial and radial slots 26 thus allows the sealing tabs to cover a large surface of the lateral faces 30 of the ring segment 16 to ensure optimum sealing between two adjacent ring segments.
- each spacer segment 18 is provided with at least one axial slot 36 and at least one radial slot 38 formed on its lateral faces 40.
- each side face 40 of the spacer segment 18 comprises for example an axial slot 36 and three radial slots 38, two of which are disposed on the side of its upstream axial walls 22a and downstream 22b.
- ring segments 16 and spacer 18 are housed sealing tabs which partially obstruct the clearance between two adjacent segments in order to limit the leakage. 'air.
- the axial slot (s) 26, 36 of the lateral faces 30, 40 of each ring segment 16 and spacer 18 have a depth greater than that of the radial slot (s) 28, 38 and that the sealing tongue housed in each axial slot has a width greater than that of the sealing tongue housed in each radial slot.
- slot depth is meant the machining depth of the slot in the material of the segment concerned.
- tongue width is meant the distance of the tongue between its two side edges by which the tongue is positioned in the slots.
- FIG. 2 represents a spacer segment 18.
- the axial slot 36 has a depth P1 greater than the depth P2 of the radial slot 38 which opens into the axial slot 36
- this characteristic also applies to the junction B 'of the spacer segment 18, as well as to the junctions A and A' of the ring segment 16 ( figure 1 ).
- FIG. 3 On the figure 3 , two adjacent spacer segments 18, 18 'joined end to end are shown, as well as the junction B between the axial and radial slots 36.
- An axial sealing tab 42 is housed in the axial slot 36 and a tab d radial seal 44 is housed in the radial slot 38.
- the axial sealing tongue 42 has a width L1 greater than the width L2 of the radial sealing tongue 44.
- this characteristic relating to the width of the sealing tongues also applies to the junction B 'of the spacer segment 18, as well as to the junctions A and A' of the ring segment 16 ( figure 1 ).
- the fixed ring assembly as described constitutes an element of a high-pressure turbomachine turbine.
- the present invention applies to any other type of segmented ring which it is necessary to provide a seal between the adjacent segments, such as a high-pressure turbomachine distributor.
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- Engineering & Computer Science (AREA)
- Mechanical Engineering (AREA)
- General Engineering & Computer Science (AREA)
- Turbine Rotor Nozzle Sealing (AREA)
- Gasket Seals (AREA)
Description
La présente invention se rapporte au domaine général des ensembles à anneau fixe d'une turbine à gaz. Elle vise plus particulièrement des ensembles à anneau fixe d'une turbine haute-pression de turbomachine constitués d'une pluralité de segments réunis bout à bout avec interposition de languettes d'étanchéité.The present invention relates to the general field of stationary ring assemblies of a gas turbine. It is more particularly fixed ring assemblies of a high-pressure turbomachine turbine consisting of a plurality of segments joined end to end with the interposition of sealing tabs.
Dans une turbine à gaz, par exemple une turbine haute-pression de turbomachine, les aubes mobiles formant rotor sont entourées par un ensemble à anneau fixe formant enveloppe. L'ensemble à anneau fixe définit ainsi l'une des parois de la veine d'écoulement des gaz chauds provenant de la chambre de combustion de la turbomachine et traversant la turbine.In a gas turbine, for example a turbomachine high-pressure turbine, the rotor blades are surrounded by a fixed ring assembly forming an envelope. The fixed ring assembly thus defines one of the walls of the flow passage of hot gases from the combustion chamber of the turbomachine and passing through the turbine.
L'ensemble à anneau fixe se compose d'un anneau de turbine fixé sur le carter de la turbine par l'intermédiaire d'une entretoise. Généralement, l'anneau et l'entretoise d'un tel ensemble à anneau fixe sont sectorisés, c'est à dire qu'ils se composent chacun d'une pluralité de segments réunis bout à bout.The fixed ring assembly consists of a turbine ring attached to the turbine casing via a spacer. Generally, the ring and the spacer of such a fixed ring assembly are sectored, that is to say that they each consist of a plurality of segments joined end to end.
L'ensemble à anneau fixe ainsi défini étant directement en contact avec les gaz chauds issus de la chambre de combustion, il est nécessaire de refroidir les différents segments qui le composent. A cet effet, de l'air prélevé en fond de chambre circule dans un circuit de refroidissement aménagé dans chaque segment de l'ensemble à anneau fixe et est évacué dans la veine d'écoulement des gaz en amont des aubes mobiles de la turbine.The fixed ring assembly thus defined being directly in contact with the hot gases from the combustion chamber, it is necessary to cool the various segments that compose it. For this purpose, air taken from the chamber bottom circulates in a cooling circuit arranged in each segment of the fixed ring assembly and is discharged into the gas flow line upstream of the turbine blades.
Il est par ailleurs nécessaire d'assurer une étanchéité entre les segments adjacents de l'ensemble à anneau fixe afin d'éviter des fuites d'air particulièrement préjudiciables au bon refroidissement de ces segments. Dans ce but, il est connu (voir notamment les documents
Les fentes radiales et axiales dans lesquelles sont logées les languettes d'étanchéité sont généralement usinées de telle sorte qu'elles sont jointives, c'est à dire qu'elles communiquent entre elles. Cet arrangement est rendu nécessaire par le fait que les languettes d'étanchéité doivent recouvrir une surface maximum des faces latérales des segments afin d'obtenir une étanchéité optimale.The radial and axial slots in which the sealing tabs are housed are generally machined so that they are contiguous, ie they communicate with each other. This arrangement is necessitated by the fact that the sealing tabs must cover a maximum surface of the lateral faces of the segments in order to obtain an optimum seal.
Dans la pratique, on constate toutefois qu'un tel arrangement des fentes génère des fuites d'air importantes au niveau de la jonction entre les fentes axiales et radiales. Ces fuites sont illustrées sur la
Du fait de la répartition de pression dans le circuit de refroidissement des segments 100, 100', des fuites d'air apparaissent au niveau de la jonction des fentes axiales 102, 102' et radiales 104, 104' (ces fuites sont représentées en traits hachurés sur la figure). De telles fuites sont particulièrement pénalisantes pour le refroidissement des segments et pour le rendement de la turbine.Due to the pressure distribution in the cooling circuit of the
La présente invention vise donc à pallier de tels inconvénients en proposant un ensemble à anneau fixe de turbine à gaz dont les segments qui le constitue présentent une géométrie particulière des fentes et des languettes d'étanchéité permettant de réduire les fuites entre deux segments adjacents.The present invention therefore aims to overcome such drawbacks by proposing a gas turbine fixed ring assembly whose segments which constitute it have a particular geometry of the slots and sealing tabs to reduce leakage between two adjacent segments.
A cet effet, il est prévu un ensemble à anneau fixe formant enveloppe de rotor d'une turbine à gaz, l'ensemble à anneau fixe comportant une pluralité de segments dont des faces latérales adjacentes sont mises bout à bout avec interposition de moyens d'étanchéité, les moyens d'étanchéité comportant au moins une languette d'étanchéité axiale et au moins une languette d'étanchéité radiale logées respectivement dans au moins une fente axiale et au moins une fente radiale pratiquées en vis-à-vis dans les faces latérales adjacentes des segments, la fente radiale débouchant au moins à l'une de ses extrémités dans la fente axiale, caractérisé en ce que la fente axiale des faces latérales de chaque segment présente une profondeur supérieure à celle de la fente radiale et en ce que la languette d'étanchéité axiale présente une largeur supérieure à celle de la languette radiale.For this purpose, there is provided a fixed ring assembly forming a rotor envelope of a gas turbine, the fixed ring assembly having a plurality of segments including adjacent side faces are placed end to end with the interposition of sealing means, the sealing means comprising at least one axial sealing tongue and at least one radial sealing tongue housed respectively in at least one axial slot and at least one radial slot; formed opposite the adjacent side faces of the segments, the radial slot opening at least at one of its ends in the axial slot, characterized in that the axial slot of the lateral faces of each segment has a greater depth to that of the radial slot and in that the axial sealing tongue has a width greater than that of the radial tongue.
La languette d'étanchéité axiale logée dans une fente plus profonde permet de recouvrir les sections de fuite observées dans l'art antérieur. De la sorte, il est possible de diminuer les fuites d'air entre deux segments adjacents ce qui permet d'améliorer leur refroidissement. A refroidissement identique, il est par ailleurs possible de diminuer le débit d'air nécessaire au refroidissement, et donc d'augmenter le rendement de la turbine.The axial sealing tab housed in a deeper slot makes it possible to cover the leakage sections observed in the prior art. In this way, it is possible to reduce air leakage between two adjacent segments which improves their cooling. With identical cooling, it is also possible to reduce the air flow required for cooling, and therefore to increase the efficiency of the turbine.
Un autre avantage de l'invention réside dans le fait que cette suppression de ces fuites d'air s'effectue sans l'ajout de pièces annexes (de type cornières) préjudiciables à la masse de l'ensemble, ne nécessite pas de modifications importantes des fentes et des languettes d'étanchéité et n'implique pas de problèmes de maintenance.Another advantage of the invention resides in the fact that this suppression of these air leaks is carried out without the addition of ancillary parts (angle-type) detrimental to the mass of the assembly, does not require significant modifications. slots and sealing tabs and does not involve maintenance problems.
L'ensemble à anneau fixe peut constituer un anneau de turbine haute-pression d'une turbomachine. Dans ce cas, chaque segment d'anneau peut comporter, au niveau de ses faces latérales, deux fentes axiales disposées du côté de parois interne et externe et dans lesquelles sont logées des languettes axiales, et deux fentes radiales disposées du côté de parois amont et aval et dans lesquelles sont logées des languettes radiales.The fixed ring assembly may constitute a high-pressure turbine ring of a turbomachine. In this case, each ring segment may comprise, at its lateral faces, two axial slots disposed on the inner and outer wall side and in which axial tongues are housed, and two radial slots arranged on the upstream side of walls and downstream and in which are housed radial tongues.
L'ensemble à anneau fixe peut également constituer une entretoise sur lequel est fixé l'anneau de turbine haute-pression de la turbomachine. Dans ce cas, chaque segment d'entretoise peut comporter, au niveau de ses faces latérales, une fente axiale dans laquelle est logée une languette axiale, et au moins trois fentes radiales dont deux sont logées du côté de ses parois amont et aval et dans lesquelles sont logées des languettes radiales.The fixed ring assembly may also constitute a spacer on which is fixed the high-pressure turbine ring of the turbomachine. In this case, each spacer segment may comprise, at its lateral faces, an axial slot in which is housed an axial tongue, and at least three radial slots, two of which are housed on the side of its upstream and downstream walls and in which are accommodated radial tongues.
D'autres caractéristiques et avantages de la présente invention ressortiront de la description faite ci-dessous, en référence aux dessins annexés qui en illustrent un exemple de réalisation dépourvu de tout caractère limitatif. Sur les figures :
- la
figure 1 est une vue en coupe longitudinale d'un ensemble à anneau fixe de turbine haute-pression de turbomachine selon l'invention ; - la
figure 2 représente en perspective un segment d'entretoise de l'ensemble à anneau fixe de lafigure 1 ; - la
figure 3 illustre en perspective et partiellement en écorché deux segments d'entretoise de lafigure 2 réunis bout à bout ; - la
figure 4 est une vue en coupe selon IV-IV de lafigure 3 ; et - la
figure 5 , décrite précédemment, illustre les problèmes de fuites rencontrés dans un ensemble à anneau fixe de l'art antérieur.
- the
figure 1 is a longitudinal sectional view of a stationary ring assembly of turbomachine high-pressure turbine according to the invention; - the
figure 2 represents in perspective a spacer segment of the fixed ring assembly of thefigure 1 ; - the
figure 3 illustrates in perspective and partially cut off two spacer segments of thefigure 2 gathered end to end; - the
figure 4 is a sectional view along IV-IV of thefigure 3 ; and - the
figure 5 , described above, illustrates the leakage problems encountered in a fixed ring assembly of the prior art.
En liaison avec la
Les aubes mobiles 4 sont entourées par un ensemble à anneau fixe 12 formant enveloppe. Cet ensemble à anneau fixe se compose d'un anneau de turbine fixé sur un carter 14 de la turbine par l'intermédiaire d'une pluralité de segments d'entretoise 18. Plus particulièrement, l'anneau de turbine se compose d'une pluralité de segments d'anneau 16 réunis bout à bout. A titre d'exemple, il peut y avoir deux segments d'anneau 16 montés sur un seul segment d'entretoise 18.The
L'ensemble à anneau fixe 12 ainsi défini comporte un circuit de circulation d'air permettant de refroidir les segments d'anneau 16 et d'entretoise 18 qui sont exposés aux gaz chauds issus de la chambre de combustion.The
Pour ce faire, l'ensemble à anneau fixe 12 est muni d'un circuit de refroidissement. Un trou 20 est percé dans la paroi radiale amont 22a de chaque segment d'entretoise 18 et débouche dans une cavité 24 formée entre le carter 14 et le segment d'entretoise 18. L'air distribué dans cette cavité 24 provient d'un prélèvement réalisé en fond de chambre et alimente ensuite un circuit de refroidissement du segment d'entretoise 18 et du ou des segments d'anneau 16 montés sur celui-ci. L'air est finalement évacué dans la veine d'écoulement 6 des gaz chauds, en amont des aubes mobiles 4 de la turbine.To do this, the
Par ailleurs, comme l'anneau et l'entretoise de l'ensemble à anneau fixe 12 sont sectorisés, il convient de limiter les fuites d'air entre deux segments 16, 18 adjacents.Furthermore, since the ring and the spacer of the
A cet effet, des barrières d'étanchéité sont interposées entre deux segments adjacents d'anneau 16 et d'entretoise 18. Ces barrières sont constituées de languettes d'étanchéité logées dans des fentes axiales et radiales pratiquées en vis-à-vis dans les faces latérales adjacentes des segments 16, 18.For this purpose, sealing barriers are interposed between two
Par fentes axiales, on entend que ces fentes s'étendent sensiblement axialement, c'est à dire selon l'axe longitudinal X-X de la turbine haute-pression 2. De même, par fentes radiales, on entend que ces fentes s'étendent sensiblement radialement, c'est à dire selon une direction perpendiculaire à l'axe longitudinal X-X.By axial slots, it is meant that these slots extend substantially axially, that is to say along the longitudinal axis XX of the high-
Ainsi, chaque segment d'anneau 16 est muni d'au moins une fente axiale 26 et d'au moins une fente radiale 28 pratiquées sur ses faces latérales 30.Thus, each
Sur la
Une telle répartition des fentes axiales 26 et radiales 28 permet ainsi aux languettes d'étanchéité de recouvrir une grande surface des faces latérales 30 du segment d'anneau 16 afin d'assurer une étanchéité optimale entre deux segments d'anneau adjacents.Such a distribution of the axial and
Par ailleurs, il découle de cette répartition optimale que les deux fentes radiales 28 débouchent à leurs deux extrémités dans les fentes axiales 26. On peut aussi imaginer que les fentes radiales 28 ne débouchent dans les fentes axiales qu'à une seule de leurs extrémités.Moreover, it follows from this optimal distribution that the two
De même, chaque segment d'entretoise 18 est muni d'au moins une fente axiale 36 et d'au moins une fente radiale 38 pratiquées sur ses faces latérales 40.Similarly, each
Sur les
Du fait de la nécessité de réaliser une répartition optimale des fentes axiales 36 et radiales 38 sur toute la surface des faces latérales 40 du segment d'entretoise 18, deux des fentes radiales 38 débouchent à l'une de leurs extrémités dans la fente axiale 36.Due to the need to achieve optimal distribution of the
Dans les fentes axiales 26, 36 et radiales 28, 38 des segments d'anneau 16 et d'entretoise 18, sont logées des languettes d'étanchéité qui permettent d'obstruer partiellement le jeu existant entre deux segments adjacents afin de limiter les fuites d'air.In the
Or, des fuites d'air apparaissent au niveau de la jonction entre certaines de ces fentes axiales et radiales. Notamment, des fuites se développent pour les segments d'anneau 16, au niveau des jonctions A et A' (
Pour limiter de telles fuites, il est prévu, conformément à l'invention, que la ou les fentes axiales 26, 36 des faces latérales 30, 40 de chaque segment d'anneau 16 et d'entretoise 18 présente une profondeur supérieure à celle de la ou des fentes radiales 28, 38 et que la languette d'étanchéité logée dans chaque fente axiale présente une largeur supérieure à celle de la languette d'étanchéité logée dans chaque fente radiale.To limit such leaks, it is provided, in accordance with the invention, that the axial slot (s) 26, 36 of the lateral faces 30, 40 of each
Par profondeur de fente, on entend la profondeur d'usinage de la fente dans le matériau du segment concerné. Par largeur de languette, on entend la distance de la languette comprise entre ses deux bords latéraux par lesquels la languette est positionnée dans les fentes.By slot depth is meant the machining depth of the slot in the material of the segment concerned. By tongue width is meant the distance of the tongue between its two side edges by which the tongue is positioned in the slots.
Cette caractéristique est notamment illustrée sur la
Sur la
Sur les
Ainsi, les fuites d'air au niveau des jonctions entre fentes axiales 26, 36 et radiales 28, 38 des segments d'anneau 16 et d'entretoise 18 peuvent être évitées. Notamment, concernant les segments d'entretoise 18, on remarquera que la pression de l'air alimentant leur circuit de refroidissement est plus importante du côté des cavités 24 (
Bien entendu, cette particularité s'applique également aux segments d'anneau 16 pour lesquels la pression de l'air alimentant leur circuit de refroidissement est plus importante du côté de leur paroi externe 32b que du côté de leur paroi interne 32a (
En se référant à la
L'ensemble à anneau fixe tel que décrit constitue un élément d'une turbine haute-pression de turbomachine. Bien entendu, la présente invention s'applique à tout autre type d'anneau segmenté dont il est nécessaire d'assurer une étanchéité entre les segments adjacents, comme par exemple un distributeur haute-pression de turbomachine.The fixed ring assembly as described constitutes an element of a high-pressure turbomachine turbine. Of course, the present invention applies to any other type of segmented ring which it is necessary to provide a seal between the adjacent segments, such as a high-pressure turbomachine distributor.
Claims (6)
- A stationary ring assembly forming a rotor shroud for a gas turbine, the stationary ring assembly comprising a plurality of segments (16, 18) having adjacent side faces (30, 40) that are placed end to end with sealing means interposed therebetween, the sealing means comprising at least one axial sealing strip (42) and at least one radial sealing strip (44) respectively received in at least one axial slot (26, 36) and in at least one radial slots (28, 38) formed facing one another in the adjacent side faces of the segments, at least one end of each radial slot (28, 38) opening out into the corresponding axial slot (26, 36), the assembly being characterised in that each axial slot (26, 36) of a segment (16, 18) presents a depth (P1) that is greater than the depth (P2) of the corresponding radial slot (28, 38), and in that the axial sealing strip (42) presents a width (L1) that is greater than the width (L2) of the radial strip (44).
- An assembly according to claim 1, characterised in that it constitutes a high-pressure turbine ring for a turbomachine.
- An assembly according to claim 2, characterised in that each ring segment (16) includes, in each side face (30), two axial slots (26) disposed towards its inner and its outer walls (32a, 32b), and in which axial strips are received, and two radial slots (28) disposed towards its upstream and its downstream walls (34a, 34b), and in which radial strips are received.
- An assembly according to claim 1, characterised in that it constitutes a high-pressure turbine spacer for a turbomachine.
- An assembly according to claim 4, characterised in that each spacer segment (18) includes, in each side face (40), one axial slot (36) in which an axial strip (42) is received, and at least three radial slots (38), two of which are disposed towards its upstream and its downstream walls (22a, 22b), and in which radial strips (44) are received.
- A turbomachine including at least one assembly according to any one of claims 1 to 5.
Applications Claiming Priority (2)
Application Number | Priority Date | Filing Date | Title |
---|---|---|---|
FR0404737A FR2869943B1 (en) | 2004-05-04 | 2004-05-04 | FIXED RING ASSEMBLY OF A GAS TURBINE |
FR0404737 | 2004-05-04 |
Publications (2)
Publication Number | Publication Date |
---|---|
EP1593814A1 EP1593814A1 (en) | 2005-11-09 |
EP1593814B1 true EP1593814B1 (en) | 2008-07-30 |
Family
ID=34942095
Family Applications (1)
Application Number | Title | Priority Date | Filing Date |
---|---|---|---|
EP05290784A Active EP1593814B1 (en) | 2004-05-04 | 2005-04-08 | Feather seal configuration for a gas turbine shroud |
Country Status (9)
Country | Link |
---|---|
US (1) | US7201559B2 (en) |
EP (1) | EP1593814B1 (en) |
JP (1) | JP4516473B2 (en) |
CA (1) | CA2504171C (en) |
DE (1) | DE602005008503D1 (en) |
ES (1) | ES2311201T3 (en) |
FR (1) | FR2869943B1 (en) |
RU (1) | RU2373401C2 (en) |
UA (1) | UA87971C2 (en) |
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US8240985B2 (en) * | 2008-04-29 | 2012-08-14 | Pratt & Whitney Canada Corp. | Shroud segment arrangement for gas turbine engines |
US20110044803A1 (en) * | 2009-08-18 | 2011-02-24 | Pratt & Whitney Canada Corp. | Blade outer air seal anti-rotation |
US8556575B2 (en) * | 2010-03-26 | 2013-10-15 | United Technologies Corporation | Blade outer seal for a gas turbine engine |
US8753073B2 (en) | 2010-06-23 | 2014-06-17 | General Electric Company | Turbine shroud sealing apparatus |
US20120128472A1 (en) * | 2010-11-23 | 2012-05-24 | General Electric Company | Turbomachine nozzle segment having an integrated diaphragm |
FR2968350B1 (en) * | 2010-12-06 | 2016-01-29 | Snecma | SECTORIZED TURBINE RING FOR TURBOMACHINE, AND TURBOMACHINE EQUIPPED WITH SUCH A RING |
US8444152B2 (en) * | 2011-05-04 | 2013-05-21 | General Electric Company | Spring seal assembly and method of sealing a gap |
US20120292856A1 (en) * | 2011-05-16 | 2012-11-22 | United Technologies Corporation | Blade outer seal for a gas turbine engine having non-parallel segment confronting faces |
GB201117084D0 (en) * | 2011-10-05 | 2011-11-16 | Rolls Royce Plc | Strip seals |
US9810086B2 (en) * | 2011-11-06 | 2017-11-07 | General Electric Company | Asymmetric radial spline seal for a gas turbine engine |
US9587746B2 (en) | 2012-07-31 | 2017-03-07 | General Electric Company | Film riding seals for rotary machines |
US9416671B2 (en) | 2012-10-04 | 2016-08-16 | General Electric Company | Bimetallic turbine shroud and method of fabricating |
US10161259B2 (en) * | 2014-10-28 | 2018-12-25 | General Electric Company | Flexible film-riding seal |
FR3041993B1 (en) * | 2015-10-05 | 2019-06-21 | Safran Aircraft Engines | TURBINE RING ASSEMBLY WITH AXIAL RETENTION |
US10822988B2 (en) * | 2015-12-21 | 2020-11-03 | Pratt & Whitney Canada Corp. | Method of sizing a cavity in a part |
US10655495B2 (en) * | 2017-02-24 | 2020-05-19 | General Electric Company | Spline for a turbine engine |
US10662794B2 (en) * | 2017-10-19 | 2020-05-26 | Rolls-Royce Corporation | Strip seal axial assembly groove |
GB2571802A (en) * | 2018-03-06 | 2019-09-11 | Rolls Royce Plc | A Gas Turbine Engine Combustion Arrangement and a Gas Turbine Engine |
RU190280U1 (en) * | 2019-01-09 | 2019-06-25 | Публичное Акционерное Общество "Одк-Сатурн" | DEVICE FOR FIXING SEGMENT OF SEGPLATES IN THE FORCE CASE OF A TURBINE STATOR |
US11111802B2 (en) * | 2019-05-01 | 2021-09-07 | Raytheon Technologies Corporation | Seal for a gas turbine engine |
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US4524980A (en) * | 1983-12-05 | 1985-06-25 | United Technologies Corporation | Intersecting feather seals for interlocking gas turbine vanes |
US5154577A (en) * | 1991-01-17 | 1992-10-13 | General Electric Company | Flexible three-piece seal assembly |
US5188507A (en) * | 1991-11-27 | 1993-02-23 | General Electric Company | Low-pressure turbine shroud |
US5709530A (en) * | 1996-09-04 | 1998-01-20 | United Technologies Corporation | Gas turbine vane seal |
US5868398A (en) * | 1997-05-20 | 1999-02-09 | United Technologies Corporation | Gas turbine stator vane seal |
JP3462732B2 (en) * | 1997-10-21 | 2003-11-05 | 三菱重工業株式会社 | Double cross seal device for gas turbine vane |
US6814538B2 (en) * | 2003-01-22 | 2004-11-09 | General Electric Company | Turbine stage one shroud configuration and method for service enhancement |
US7063503B2 (en) * | 2004-04-15 | 2006-06-20 | Pratt & Whitney Canada Corp. | Turbine shroud cooling system |
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2004
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- 2005-04-08 DE DE602005008503T patent/DE602005008503D1/en active Active
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CA2504171A1 (en) | 2005-11-04 |
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ES2311201T3 (en) | 2009-02-01 |
JP4516473B2 (en) | 2010-08-04 |
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CA2504171C (en) | 2012-10-23 |
FR2869943A1 (en) | 2005-11-11 |
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US7201559B2 (en) | 2007-04-10 |
FR2869943B1 (en) | 2006-07-28 |
UA87971C2 (en) | 2009-09-10 |
EP1593814A1 (en) | 2005-11-09 |
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