EP1586743A1 - Anneau de turbine - Google Patents
Anneau de turbine Download PDFInfo
- Publication number
- EP1586743A1 EP1586743A1 EP05290821A EP05290821A EP1586743A1 EP 1586743 A1 EP1586743 A1 EP 1586743A1 EP 05290821 A EP05290821 A EP 05290821A EP 05290821 A EP05290821 A EP 05290821A EP 1586743 A1 EP1586743 A1 EP 1586743A1
- Authority
- EP
- European Patent Office
- Prior art keywords
- sectors
- ring according
- turbine ring
- slots
- radial
- 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.)
- Granted
Links
- 238000007789 sealing Methods 0.000 claims abstract description 19
- 210000002105 tongue Anatomy 0.000 claims description 34
- 238000001816 cooling Methods 0.000 claims description 8
- 239000007789 gas Substances 0.000 description 7
- 238000002485 combustion reaction Methods 0.000 description 6
- 230000006866 deterioration Effects 0.000 description 2
- 241001415961 Gaviidae Species 0.000 description 1
- 230000015572 biosynthetic process Effects 0.000 description 1
- 230000002349 favourable effect Effects 0.000 description 1
- 230000037406 food intake Effects 0.000 description 1
- 238000000034 method Methods 0.000 description 1
- 230000001459 mortal effect Effects 0.000 description 1
- 238000005192 partition Methods 0.000 description 1
- 238000005086 pumping Methods 0.000 description 1
- 230000000930 thermomechanical effect Effects 0.000 description 1
- 238000011144 upstream manufacturing Methods 0.000 description 1
- 210000003462 vein Anatomy 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
-
- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F05—INDEXING SCHEMES RELATING TO ENGINES OR PUMPS IN VARIOUS SUBCLASSES OF CLASSES F01-F04
- F05D—INDEXING SCHEME FOR ASPECTS RELATING TO NON-POSITIVE-DISPLACEMENT MACHINES OR ENGINES, GAS-TURBINES OR JET-PROPULSION PLANTS
- F05D2240/00—Components
- F05D2240/10—Stators
- F05D2240/11—Shroud seal segments
Definitions
- the invention relates to a turbine ring forming the envelope outer rotor of this turbine.
- the invention is particularly applicable to a high pressure turbine located immediately downstream of the chamber of combustion of an airplane turbojet. It concerns more particularly the connecting and cooling the sectors constituting said ring of turbine.
- a turbine of the type indicated above driven by very hot, the rotor rotates inside a stationary turbine ring constituted by a plurality of curved sectors joined end to end, circumferentially, to form the rotor casing.
- the temperature of the gases driving the wheel to blades is such that the thermomechanical stresses that are created in and between sectors, may cause deterioration reducing the duration of life of the rings.
- sealing systems are planned between these neighboring sectors, comprising tabs extending between these sectors and housed in slots facing each other in the adjacent radial faces of said sectors.
- a known sector 1, shown in FIG. sealing system comprising four tabs 2-5, housed in slots 6, 7, 8.
- the tongue 3 is folded and extends between two slots 6, 7 opening into one another and accommodating other straight tabs 2, 4. Slots are difficult to machine accurately, especially because of the difference in thickness needed to insert the folded tongue. The positioning of the latter is delicate.
- the tongue 2 is fully housed in a slot 6 parallel to the hot face 9 of the sector and to little distance from it.
- practicing slots creates zones of concentration of stresses which, when they are near the surface hot, weaken the room and accelerate its deterioration.
- the invention in particular to eliminate these disadvantages.
- the invention therefore relates to a turbine ring forming rotor casing, of the type constituted by a plurality of sectors, joined together with interposed sealing systems including tabs extending between adjacent sectors, said tongues being housed in slots provided opposite each other in adjacent radial faces of said sectors, characterized in that each sealing system consists of straight tabs engaged in respective straight slots of said radial faces.
- each sealing system comprises first and second tongues extending chevron on the side said radial faces, said tabs being engaged in straight slots of said radial faces defining their relative positions precisely.
- Another advantage of the invention lies in the fact that the arrangement of tongues in chevron on the side of the hot face allows both to distance the stress concentration zones of said hot face (since the slits deviate from it) and also to provide sufficient space between tabs and the hot face to open air ejection channels cooling supplied from a cavity in the sector itself.
- each sector includes a cavity of cooling air circulation, characterized in that it further comprises air ejection channels extending between said cavity and at least one face radial of the sector, these channels opening on said radial face between an edge interior thereof and said first and second tabs.
- FIGS. 2 to 4 there is shown represents turbine ring sectors 11 constituting the fixed envelope a rotor, not shown.
- This is the high pressure turbine of a turbojet.
- This turbine is placed downstream of the combustion chamber.
- such a ring consists of 32 ring sectors 11 curves such as those shown, end to end to form an envelope slightly conical surrounding said rotor.
- Each sector 11 is constituted a thick, slightly curved plate to reconstitute the ring.
- Each sector 11 further comprises two radial faces 20, 21 by which it is connects circumferentially to neighboring areas, by means of sealing 26 (see Figure 2) mentioned above.
- Each system sealing member 26 consists of a set of tongues engaged in corresponding slots defined in said radial faces 20, 21 facing.
- Each tab is engaged in two slots belonging to two sectors ring circumferentially adjacent.
- each sector 11 is hollow and comprises an air circulation cavity cooling unit 35 fed from the outside.
- FIG. 4 very schematically illustrates the position of the formed ring by all the sectors 11.
- a turbine casing 15 defines with this ring an annular cavity 17.
- the assembly extends radially outside the wheel with high pressure vanes 19 itself interposed axially between the high pressure distributor 21 and the low pressure distributor 23. Air from the compressor is taken upstream of the combustion chamber and penetrates (via bores) into the annular cavity 17. This cavity feeds so all ring sectors.
- Each ring sector ( Figure 3) comprises two separate cavities 39 and 40 in the shape of a trombone, separated by a partition 42 and fed respectively by orifices 37 and 38.
- the circulating air in the cavity 39 escapes through a series of objection channels 44 opening on the input edge 16 of the ring sector while the air flowing in the cavity 40 escapes through a series of ejection channels 46 opening onto the output edge 18 of the ring sector.
- the invention relates in particular to advantageous development of said sealing systems between sectors.
- each sealing system 26 here consists of three straight tabs engaged in slots respective rectilinear radial faces of the two adjacent sectors.
- each sealing system (FIG. 2) comprises a first tongue 27 and a second tongue 28, located on the inner side of said radial faces, that is to say on the side of the hot faces of the sectors.
- the tongues 27, 28 are arranged in chevron, that is to say engaged in slots 31, 32 of said radial faces which extend obliquely with respect to inner faces 12 and outer 14 sectors. These slots define the relative positions of the two tabs.
- each sealing system has a third tongue 29 extending substantially from one end to the other of the sectors adjacent, parallel to the axis of the ring, on the outer side of said faces radials.
- the tongue 29 is engaged in rectilinear slots 33 of the adjacent areas.
- the first tab 27 extends between point A located near the entrance edge of the two sectors, inward (near the hot faces) and a point B located near the third tongue 29.
- the second tongue 28 is positioned so that it extends between a point C located near the exit edge 18 of each of the two sectors, inward and a point D located near the first tongue, substantially between the middle and two thirds of it in from point A.
- the length of the first tongue 27 depends on the angle it makes with the third tongue 29. Once this angle determined (several possibilities are shown in Figure 5) the position and length of the second tab derive from it.
- the angle defined by the first and third tongue can be understood between 15 and 70 °, approximately.
- the slots can be machined precisely and are perfectly localized.
- the tabs can be inserted into these slots and their relative positions can be perfectly controlled. It follows that the leakage section between said first and second tongues (S 1 ) and the leakage section between the first and third tongues (S 2 ) are perfectly controlled.
- each sector includes ejection channels 50, extending between the cavity 40 and at least one radial face of the sector. These channels open on the radial face 20 between the inner edge thereof (hot side) and said first and second tongues 27, 28.
- the chevron arrangement of the two tabs makes it possible to practice these channels of air ejection.
- the channels are arranged in a row parallel to the axis of the ring. In the example of Figure 3, they all extend perpendicularly at the radial face.
- some channels 50 extend perpendicular to the radial face but others located at the ends of said row or at least one of them are practiced at an angle and diverging compared to the first, here in a direction from the cavity to the face radial.
- the angle between the diverging channels can be between 10 and 120 ° In some cases, channels could also be converging in the other direction.
- the channels, parallel make an angle to a direction perpendicular to the face radial. The angle is such that the air is ejected obliquely towards the rear of the ring.
- the parallel channels are at an angle to at a direction perpendicular to the radial face. The angle is such that the air is ejected obliquely towards the front of the ring.
- the channels 50 open on the radial face 20 which is the one that the vanes first reach given the direction of rotation indicated by the arrow F. This is favorable to avoid or limit reintroductions of hot gas in inter-sector spaces.
- the air that escapes from the channels 50 cools the wall in which they are practiced by convection (thermal pumping) while the wall opposite (face 21) is cooled by the impact of the air jets.
- air jets escaping from the ducts 50 establish a kind of fluidic system preventing ingestions of hot gases.
- the slots 31, 32, 33 are independent, that is, they do not communicate with each other others. This avoids the need to make mortal remains at the junction of two slots. Inter-sector leakage sections are also reduced.
- the invention also relates to any ring sector or any assembly of ring sectors having the characteristics described above.
Landscapes
- Engineering & Computer Science (AREA)
- Mechanical Engineering (AREA)
- General Engineering & Computer Science (AREA)
- Turbine Rotor Nozzle Sealing (AREA)
Abstract
Description
- la figure 1 représente une face radiale d'un secteur entrant dans la constitution d'un anneau de turbine conforme à l'état de la technique ;
- la figure 2 représente une face radiale d'un secteur entrant dans la constitution d'un anneau de turbine conforme à l'invention ;
- la figure 3 est une vue schématique de deux secteurs consécutifs représentés selon la flèche 3 de la figure 2 ;
- la figure 4 est une vue schématique du carter associé à de tels secteurs d'anneau ;
- la figure 5 est une vue schématique illustrant diverses orientations possibles desdites première et deuxième languettes ; et
- les figures 6 à 8 sont des vues partielles de variantes d'un secteur de la figure 3.
Claims (12)
- Anneau de turbine formant enveloppe de rotor, du type constitué par une pluralité de secteurs (11), réunis bout à bout avec interposition de systèmes d'étanchéité comprenant des languettes (27, 28, 29) s'étendant entre secteurs voisins, lesdites languettes étant logées dans des fentes pratiquées en vis-à-vis dans des faces radiales adjacentes desdits secteurs, caractérisé en ce que chaque système d'étanchéité est constituée de languettes rectilignes engagées dans des fentes rectilignes (31, 32, 33) respectives desdites faces radiales et en ce que les fentes pratiquées sur chaque face radiale sont indépendantes.
- Anneau de turbine selon la revendication 1, caractérisé en ce que chaque système d'étanchéité entre deux secteurs comporte une première et une deuxième languettes (27, 28) s'étendant en chevron du côté intérieur desdites faces radiales, lesdites languettes étant engagées dans des fentes (31, 32) desdites faces radiales définissant leurs positions relatives.
- Anneau de turbine selon la revendication 2, caractérisé en ce que chaque système d'étanchéité comporte une troisième languette (29) s'étendant sensiblement d'une extrémité à l'autre des secteurs adjacents, parallèlement à l'axe de l'anneau, du côté extérieur desdites faces radiales.
- Anneau de turbine selon la revendication 3, caractérisé en ce que ladite première languette (27) s'étend entre un point (A) situé à proximité d'un bord d'entrée de chaque secteur, vers l'intérieur, et un point (B) situé à proximité de ladite troisième languette.
- Anneau de turbine selon la revendication 4, caractérisé en ce que l'angle défini par les directions desdites première et troisième languettes est compris entre 15 et 70 degrés.
- Anneau de turbine selon l'une des revendications 4 ou 5, caractérisé en ce que ladite deuxième languette (28) s'étend entre un point (C) situé à proximité d'un bord de sortie de chaque secteur, vers l'intérieur et un point (D) situé à proximité de ladite première languette, sensiblement entre le milieu et les deux tiers de celle-ci.
- Anneau de turbine selon l'une des revendications 4 ou 5, dans lequel chaque secteur comprend une cavité de circulation d'air de refroidissement (40), caractérisé en ce que chaque secteur comprend des canaux d'éjection d'air (50), s'étendant entre ladite cavité et au moins une face radiale 20 dudit secteur, ces canaux débouchant sur ladite face radiale entre un bord intérieur de celle-ci et lesdites première et deuxième languettes.
- Anneau de turbine selon la revendication 7, caractérisé en ce qu'au moins certains canaux s'étendent sensiblement perpendiculairement à ladite face radiale.
- Anneau de turbine selon la revendication 7, caractérisé en ce que les orifices desdits canaux sont disposés selon une rangée parallèle à l'axe de l'anneau.
- Anneau de turbine selon la revendication 9, caractérisé en ce que des canaux situés aux extrémités de ladite rangée sont pratiqués en biais et divergent par rapport aux autres dans le sens allant de la cavité vers la face radiale.
- Anneau de turbine selon l'une des revendications précédentes, caractérisé en ce que les fentes en regard de deux faces radiales adjacentes desdits secteurs abritent une seule languette (27, 28, 29).
- Turbine caractérisée en ce qu'elle comporte un anneau selon l'une des revendications précédentes.
Applications Claiming Priority (2)
Application Number | Priority Date | Filing Date | Title |
---|---|---|---|
FR0403925A FR2869070B1 (fr) | 2004-04-15 | 2004-04-15 | Anneau de turbine |
FR0403925 | 2004-04-15 |
Publications (2)
Publication Number | Publication Date |
---|---|
EP1586743A1 true EP1586743A1 (fr) | 2005-10-19 |
EP1586743B1 EP1586743B1 (fr) | 2012-05-30 |
Family
ID=34942125
Family Applications (1)
Application Number | Title | Priority Date | Filing Date |
---|---|---|---|
EP05290821A Active EP1586743B1 (fr) | 2004-04-15 | 2005-04-14 | Anneau de turbine |
Country Status (9)
Country | Link |
---|---|
US (1) | US7513740B1 (fr) |
EP (1) | EP1586743B1 (fr) |
JP (1) | JP4679215B2 (fr) |
CN (1) | CN1683772B (fr) |
CA (1) | CA2503066C (fr) |
ES (1) | ES2386146T3 (fr) |
FR (1) | FR2869070B1 (fr) |
RU (1) | RU2377419C2 (fr) |
UA (1) | UA91958C2 (fr) |
Cited By (5)
Publication number | Priority date | Publication date | Assignee | Title |
---|---|---|---|---|
FR2919345A1 (fr) * | 2007-07-26 | 2009-01-30 | Snecma Sa | Anneau pour une roue de turbine de turbomachine. |
EP2045445A2 (fr) | 2007-10-01 | 2009-04-08 | United Technologies Corporation | Secteur de virole, noyau de coulée correspondant, et procédé de refroidissement d'un tel secteur |
CN101852136A (zh) * | 2009-03-31 | 2010-10-06 | 通用电气公司 | 减小燃气轮机中密封件之间的间隙的装置 |
WO2013074165A3 (fr) * | 2011-11-06 | 2013-08-15 | General Electric Company | Joint cannelé radial asymétrique pour un moteur à turbine à gaz |
FR3070718A1 (fr) * | 2017-09-06 | 2019-03-08 | Safran Aircraft Engines | Ensemble de turbine a secteurs d'anneau |
Families Citing this family (10)
Publication number | Priority date | Publication date | Assignee | Title |
---|---|---|---|---|
MX2008011352A (es) * | 2006-03-06 | 2008-09-23 | Alstom Technology Ltd | Turbina de gas con un escudo termico anular y bandas de sellado anguladas. |
US20130134678A1 (en) * | 2011-11-29 | 2013-05-30 | General Electric Company | Shim seal assemblies and assembly methods for stationary components of rotary machines |
US9863323B2 (en) | 2015-02-17 | 2018-01-09 | General Electric Company | Tapered gas turbine segment seals |
US10689994B2 (en) * | 2016-03-31 | 2020-06-23 | General Electric Company | Seal assembly to seal corner leaks in gas turbine |
US20180340437A1 (en) * | 2017-02-24 | 2018-11-29 | General Electric Company | Spline for a turbine engine |
US20180355754A1 (en) * | 2017-02-24 | 2018-12-13 | General Electric Company | Spline for a turbine engine |
US10655495B2 (en) * | 2017-02-24 | 2020-05-19 | General Electric Company | Spline for a turbine engine |
US20180355741A1 (en) * | 2017-02-24 | 2018-12-13 | General Electric Company | Spline for a turbine engine |
US10648362B2 (en) * | 2017-02-24 | 2020-05-12 | General Electric Company | Spline for a turbine engine |
US10982559B2 (en) * | 2018-08-24 | 2021-04-20 | General Electric Company | Spline seal with cooling features for turbine engines |
Citations (3)
Publication number | Priority date | Publication date | Assignee | Title |
---|---|---|---|---|
US5997247A (en) | 1997-01-30 | 1999-12-07 | Societe Nationale Detude Et De Construction De Mothers D'aviation "Snecma" | Seal of stacked thin slabs that slide within reception slots |
EP1162346A2 (fr) * | 2000-06-08 | 2001-12-12 | General Electric Company | Refroidissement des segments des viroles de turbine |
US6575697B1 (en) * | 1999-11-10 | 2003-06-10 | Snecma Moteurs | Device for fixing a turbine ferrule |
Family Cites Families (4)
Publication number | Priority date | Publication date | Assignee | Title |
---|---|---|---|---|
FR2597921A1 (fr) * | 1986-04-24 | 1987-10-30 | Snecma | Anneau de turbine sectorise |
US5127793A (en) * | 1990-05-31 | 1992-07-07 | General Electric Company | Turbine shroud clearance control assembly |
US5088888A (en) * | 1990-12-03 | 1992-02-18 | General Electric Company | Shroud seal |
US6814538B2 (en) * | 2003-01-22 | 2004-11-09 | General Electric Company | Turbine stage one shroud configuration and method for service enhancement |
-
2004
- 2004-04-15 FR FR0403925A patent/FR2869070B1/fr not_active Expired - Fee Related
-
2005
- 2005-04-12 JP JP2005114431A patent/JP4679215B2/ja active Active
- 2005-04-12 US US11/103,539 patent/US7513740B1/en active Active
- 2005-04-12 CA CA2503066A patent/CA2503066C/fr active Active
- 2005-04-14 EP EP05290821A patent/EP1586743B1/fr active Active
- 2005-04-14 ES ES05290821T patent/ES2386146T3/es active Active
- 2005-04-14 UA UAA200503531A patent/UA91958C2/uk unknown
- 2005-04-14 RU RU2005110997/06A patent/RU2377419C2/ru active
- 2005-04-15 CN CN200510065259.5A patent/CN1683772B/zh active Active
Patent Citations (3)
Publication number | Priority date | Publication date | Assignee | Title |
---|---|---|---|---|
US5997247A (en) | 1997-01-30 | 1999-12-07 | Societe Nationale Detude Et De Construction De Mothers D'aviation "Snecma" | Seal of stacked thin slabs that slide within reception slots |
US6575697B1 (en) * | 1999-11-10 | 2003-06-10 | Snecma Moteurs | Device for fixing a turbine ferrule |
EP1162346A2 (fr) * | 2000-06-08 | 2001-12-12 | General Electric Company | Refroidissement des segments des viroles de turbine |
Cited By (12)
Publication number | Priority date | Publication date | Assignee | Title |
---|---|---|---|---|
FR2919345A1 (fr) * | 2007-07-26 | 2009-01-30 | Snecma Sa | Anneau pour une roue de turbine de turbomachine. |
EP2045445A2 (fr) | 2007-10-01 | 2009-04-08 | United Technologies Corporation | Secteur de virole, noyau de coulée correspondant, et procédé de refroidissement d'un tel secteur |
EP2045445A3 (fr) * | 2007-10-01 | 2012-04-04 | United Technologies Corporation | Secteur de virole, noyau de coulée correspondant, et procédé de refroidissement d'un tel secteur |
CN101852136A (zh) * | 2009-03-31 | 2010-10-06 | 通用电气公司 | 减小燃气轮机中密封件之间的间隙的装置 |
CN101852136B (zh) * | 2009-03-31 | 2013-10-23 | 通用电气公司 | 减小燃气轮机中密封件之间的间隙的装置 |
WO2013074165A3 (fr) * | 2011-11-06 | 2013-08-15 | General Electric Company | Joint cannelé radial asymétrique pour un moteur à turbine à gaz |
US9810086B2 (en) | 2011-11-06 | 2017-11-07 | General Electric Company | Asymmetric radial spline seal for a gas turbine engine |
FR3070718A1 (fr) * | 2017-09-06 | 2019-03-08 | Safran Aircraft Engines | Ensemble de turbine a secteurs d'anneau |
WO2019048766A1 (fr) * | 2017-09-06 | 2019-03-14 | Safran Aircraft Engines | Ensemble de turbine à secteurs d'anneau |
CN111051649A (zh) * | 2017-09-06 | 2020-04-21 | 赛峰飞机发动机公司 | 具有环部段的涡轮组件 |
US11149574B2 (en) | 2017-09-06 | 2021-10-19 | Safran Aircraft Engines | Turbine assembly with ring segments |
CN111051649B (zh) * | 2017-09-06 | 2022-04-01 | 赛峰飞机发动机公司 | 具有环部段的涡轮组件 |
Also Published As
Publication number | Publication date |
---|---|
FR2869070B1 (fr) | 2008-10-17 |
CN1683772A (zh) | 2005-10-19 |
JP2005299663A (ja) | 2005-10-27 |
US7513740B1 (en) | 2009-04-07 |
FR2869070A1 (fr) | 2005-10-21 |
ES2386146T3 (es) | 2012-08-10 |
US20090074579A1 (en) | 2009-03-19 |
EP1586743B1 (fr) | 2012-05-30 |
RU2005110997A (ru) | 2006-10-20 |
CN1683772B (zh) | 2011-07-06 |
RU2377419C2 (ru) | 2009-12-27 |
CA2503066A1 (fr) | 2005-10-15 |
CA2503066C (fr) | 2013-01-15 |
JP4679215B2 (ja) | 2011-04-27 |
UA91958C2 (uk) | 2010-09-27 |
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