EP3906357A1 - Distributeur pour turbine, turbine de turbomachine équipée de ce distributeur et turbomachine équipée de cette turbine - Google Patents
Distributeur pour turbine, turbine de turbomachine équipée de ce distributeur et turbomachine équipée de cette turbineInfo
- Publication number
- EP3906357A1 EP3906357A1 EP19848997.3A EP19848997A EP3906357A1 EP 3906357 A1 EP3906357 A1 EP 3906357A1 EP 19848997 A EP19848997 A EP 19848997A EP 3906357 A1 EP3906357 A1 EP 3906357A1
- Authority
- EP
- European Patent Office
- Prior art keywords
- distributor
- sector
- angular
- tongue
- turbine
- 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
- 239000000463 material Substances 0.000 claims abstract description 18
- 238000007789 sealing Methods 0.000 claims description 15
- 230000008878 coupling Effects 0.000 abstract description 2
- 238000010168 coupling process Methods 0.000 abstract description 2
- 238000005859 coupling reaction Methods 0.000 abstract description 2
- 210000002105 tongue Anatomy 0.000 description 28
- 238000004519 manufacturing process Methods 0.000 description 10
- 230000001681 protective effect Effects 0.000 description 9
- 238000012423 maintenance Methods 0.000 description 4
- 238000003466 welding Methods 0.000 description 4
- 238000006073 displacement reaction Methods 0.000 description 3
- 238000003754 machining Methods 0.000 description 3
- 239000000654 additive Substances 0.000 description 2
- 230000000996 additive effect Effects 0.000 description 2
- 238000005219 brazing Methods 0.000 description 2
- 238000009760 electrical discharge machining Methods 0.000 description 2
- 238000000034 method Methods 0.000 description 2
- 241000842962 Apoda limacodes Species 0.000 description 1
- 241000237503 Pectinidae Species 0.000 description 1
- 230000009286 beneficial effect Effects 0.000 description 1
- 238000002485 combustion reaction Methods 0.000 description 1
- 230000000295 complement effect Effects 0.000 description 1
- 230000003247 decreasing effect Effects 0.000 description 1
- 230000000694 effects Effects 0.000 description 1
- 239000000446 fuel Substances 0.000 description 1
- 239000002184 metal Substances 0.000 description 1
- 230000009467 reduction Effects 0.000 description 1
- 230000008439 repair process Effects 0.000 description 1
- 235000020637 scallop Nutrition 0.000 description 1
- 229910000679 solder Inorganic materials 0.000 description 1
- 238000005476 soldering Methods 0.000 description 1
- 238000011144 upstream manufacturing Methods 0.000 description 1
- 210000003462 vein Anatomy 0.000 description 1
- 230000004584 weight gain Effects 0.000 description 1
- 235000019786 weight gain Nutrition 0.000 description 1
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
- F01D9/00—Stators
- F01D9/02—Nozzles; Nozzle boxes; Stator blades; Guide conduits, e.g. individual nozzles
- F01D9/04—Nozzles; Nozzle boxes; Stator blades; Guide conduits, e.g. individual nozzles forming ring or sector
- F01D9/041—Nozzles; Nozzle boxes; Stator blades; Guide conduits, e.g. individual nozzles forming ring or sector using blades
-
- 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
- F01D9/00—Stators
- F01D9/02—Nozzles; Nozzle boxes; Stator blades; Guide conduits, e.g. individual nozzles
- F01D9/04—Nozzles; Nozzle boxes; Stator blades; Guide conduits, e.g. individual nozzles forming ring or sector
-
- 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
- F01D11/08—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
- F01D11/125—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 with a reinforcing structure
-
- 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
- F05D2220/00—Application
- F05D2220/30—Application in turbines
- F05D2220/32—Application in turbines in gas turbines
- F05D2220/323—Application in turbines in gas turbines for aircraft propulsion, e.g. jet engines
-
- 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
- F05D2240/12—Fluid guiding means, e.g. vanes
- F05D2240/128—Nozzles
-
- 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
- F05D2240/55—Seals
-
- 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
- F05D2260/00—Function
- F05D2260/30—Retaining components in desired mutual position
- F05D2260/33—Retaining components in desired mutual position with a bayonet coupling
Definitions
- TITLE Turbine distributor, turbomachine turbine equipped with this distributor and turbomachine equipped with this turbine /
- the present invention relates to a distributor for a low or high pressure turbine, a low or high pressure turbine comprising this distributor and a turbomachine, such as an airplane turbojet or turboprop, comprising the aforementioned turbine.
- Certain turbomachinery comprise a low pressure turbine and a high pressure turbine, which recover part of the energy released by the combustion of fuel to drive respectively, a low pressure compressor and a high pressure compressor, located at the inlet of turbomachine air.
- the low pressure turbine 1 has a longitudinal axis XX ′.
- Each distributor 2 is sectorized, that is to say formed by several angular sectors 20 of distributor, arranged circumferentially end to end and assembled.
- Each angular sector of the distributor 20 comprises two platforms in a portion of an arc of a circle, arranged coaxially one inside the other and connected together by radial or substantially radial blades 201. These platforms delimit between them the annular gas flow stream in the turbine 1.
- the external platform 202 comprises means for hooking onto an external casing 100 of the turbine 1.
- the internal platform 203 is extended towards the inside of the turbine by a radial foot 204 which ends in a base 205.
- This base 205 carries on its radially internal face, elements of abradable material 206.
- This abradable material is in the form of a honeycomb structure.
- the elements of abradable material 206 cooperate with annular wipers 30 carried by the neighboring rotor 3, to form seals of the "labyrinth seal" type. Indeed, in operation and under the effect of heat, the wipers 30 and the internal platform 203 expand and approach, the wipers 30 dig furrows in the abradable material 206. There thus exists between the furrows and the wipers, a weak game which constitutes this joint to labyrinth. This play induces the performance of the flow of the hot air stream flowing in the turbine.
- the honeycomb 206 is brazed on the base 205 of each angular sector 20 of the distributor, then is resumed in machining.
- this material is machined by electroerosion (known by the acronym EDM for "Electrical Discharge Machining"), which is an expensive technique and requires specific and costly controls as well.
- each sector 20 has sealing slots 207, which open on each of the end faces of a sector 20 intended to come into contact with the end faces of the neighboring distributor sector 20.
- An inter-sector sealing tongue (not shown in the figures) is engaged in each sealing slot 207, so as to overlap the space existing between two neighboring distributor sectors 20 and thus to stop or limit the leakage d cross-sector air.
- the production and manufacture of the sealing slots 207 and the mounting of the inter-sector sealing tabs are very expensive and take a long time.
- the slots 207 are also difficult to size and there is a significant risk that the sealing tabs are dislodged from the sealing slots 207 and get lost in the air stream, resulting in air and leakage. possible impacts on other parts of the turbine.
- the invention aims to provide a turbomachine distributor which overcomes the aforementioned drawbacks of the prior art. More specifically, the object of the invention is to provide a turbomachine distributor which is simple and less expensive to produce and assemble, while reducing air leaks in the stream.
- the invention relates to a distributor for a turbine, comprising several angular sectors of distributors, each angular sector comprising two sectors of internal and external platforms, respectively, in the shape of an arc of a circle, coaxial, connected together by several radial or substantially radial blades, each internal platform sector being integral with a radially internal foot, this distributor comprising an annular ferrule on which said angular distributor sectors are fixed circumferentially end to end, this ferrule comprising a cylindrical ring of which the radially internal face carries an abradable material.
- the radially internal foot of each internal platform sector comprises a tongue, which extends radially inwards from said foot, and which extends circumferentially over part of the length of said foot
- the radially outer face of said cylindrical ring carries an outer radial wing, provided with a plurality of L-shaped legs, one of the branches of which is said to be “fixing”, is integral with the outer radial wing and extends perpendicularly to a radius of the ring and parallel to the longitudinal axis C1 -C ⁇ of said ring and the other branch of which, called “retaining”, extends opposite this external radial wing and at a short distance from it, so to provide with it a slot for receiving said tongue from each angular sector of the dispenser and this slot is open at one of its longitudinal ends to allow engagement of said tongue, so as to secure the dog-collar fixing of said ferrule sure each angular distributor sector.
- said tongue extends circumferentially to the center of the radially internal foot of each sector of internal platform;
- the end of the retaining branch is provided with a lug protruding in the direction of the outer radial wing, so as to circumferentially retain said tongue when the latter is engaged in the slot for receiving the tongue;
- the dispenser comprises at least one sealing plate, in at least one segment, with an L-shaped cross section or substantially L-shaped, fixed to the radially internal foot of an angular sector of the dispenser (ô), so as to be extend at least opposite the intersection between two neighboring angular distributor sectors;
- the dispenser comprises at least one thermal protection sheet, in at least one segment, with an L-shaped or substantially L-shaped cross section, fixed to the cylindrical ring of the ferrule.
- the invention also relates to a turbomachine turbine comprising the aforementioned distributor and a turbomachine, such as a turbojet or an airplane turboprop, which comprises the aforementioned turbine.
- FIG. 1 is a view in longitudinal section of a low pressure turbine of the state of the art
- FIG. 2 is a perspective view of the dispenser shell according to the invention.
- FIG. 3 is a detail view of FIG. 2,
- FIG. 4 is a detailed view of FIG. 3,
- FIG. 5 is a perspective view of an angular sector of a dispenser according to the invention
- FIG. 6 is a perspective view of a portion of a ferrule and an angular sector of a dispenser assembled in accordance with the invention
- FIG. 7 is a schematic view in axial section of the shell, of the interior part of an angular sector of the distributor and of a protective sheet assembled, the sheet being produced according to a first embodiment
- FIG. 8 is a schematic view in axial section of the shell, of the interior part of an angular sector of the distributor and of a protective sheet assembled, the sheet being produced according to a second embodiment
- FIG. 9 is a perspective view of an angular sector of a distributor, of two protective sheets and of a part of the assembled shell, which constitute a part of a distributor according to the invention.
- FIG. 10 is a detailed and perspective view of two different protective sheets assembled respectively on the shell and on an angular sector of the distributor,
- FIG. 11 is a detailed and perspective view of an alternative embodiment of a protective sheet assembled on an angular sector of the dispenser.
- FIG. 12 is a detailed and perspective view of a method of fixing an angular sector of the distributor on the shell.
- the distributor according to the invention is referenced 4 and comprises an annular ring 5, on which are fixed several angular sectors of distributor 6. Only part of the distributor 4 is visible in FIG. 9.
- the annular shell 5 will now be described in more detail in conjunction with Figures 2 to 4. It extends over 360 ° and has a longitudinal axis C1 -C ⁇ .
- the annular shell 5 comprises a cylindrical ring 50 (or tube) of small width compared to its diameter, of small thickness and of longitudinal axis X1 -C ⁇ .
- This ring 50 has a radially internal face 51 and a radially external face 52.
- the inner face 51 carries an abradable material 53 in one or more elements.
- This abradable material 53 is preferably a honeycomb structure. He is brazed on the ring 50 and resumed in machining as described above for the abradable material 206.
- This abradable material 53 is also cylindrical.
- the external face 52 of the ring 50 comprises several first mechanical fixing members, distributed around its periphery and intended to cooperate with second complementary mechanical fixing members, carried by each of the angular sectors 6.
- these mechanical fixing members are of the dog clutch type, and allow coupling of the ferrule 5 and the distributor sectors 6 by the engagement of tongues in slots for receiving these tongues.
- the ferrule 5 is provided with a radial wing 54, which extends radially outwards, from the external face 52 of the ring 50.
- This wing 54 is annular and extends over the entire periphery of the ring 50. It has a rear face 541 and an opposite front face 542.
- the rear face 541 is preferably oriented towards the downstream of the turbine.
- a plurality of L-shaped legs 55 are integral with the wing 54 and are distributed uniformly over the entire circumference thereof.
- Each tab 55 is also curved and has a general shape in an arc, the circle of which is coaxial with the ring 50 but with a radius greater than the radius of the ring 50.
- the tab 55 follows the shape of the ring 50.
- Each L-shaped tab 55 has a short branch 551, called the fixing branch and a long branch 552, called the retaining branch.
- the fixing branch 551 extends perpendicularly to a radius of the ring 50 and parallel to the longitudinal axis C1 -C ⁇ of said ring.
- the retaining branch 552 extends circumferentially and at a short distance from the rear face 541 of the wing 54, so as to define therewith a slot 553.
- the long branch 552 has a front face 554 which extends opposite and parallel to the rear face 541 of the wing 54.
- Part of the branch 551 constitutes the bottom 555 of the slot 553.
- the slot 553 is open opposite the bottom 555, between the free end of the long branch 552 and the wing 54.
- the long branch 552 has at its free end, a lug 556 (see FIG. A), which projects from the front face 554, in the direction of the rear face 541 of the wing 54, so as to seal only partially the slot 555.
- the branch 552 is advantageously slightly flexible.
- the ring 50 can possibly be split, (see the longitudinal slot 500). This gives it a certain flexibility and facilitates the mounting of the distributor 4.
- the different parts 50, 54 and 55 of the ferrule 5 are preferably monobloc (coming from material).
- the ferrule 5 can be manufactured, for example, by machining or by additive manufacturing.
- the ferrule 5 is preferably made of metal.
- This sector 6 comprises, in a conventional manner, two angular sectors of platforms in an arc of a circle, coaxial, namely a sector of external platform 61 and a sector of internal platform 62, interconnected by several blades 63 radial or substantially radial.
- the different angular sectors 6 are assembled around the ferrule 5, end to end circumferentially, so that the different angular sectors of external platform 61 together form the external platform of the distributor 4 and that the different angular sectors of platform internal shape 62 together form the internal platform of the distributor 4.
- the angular sector of internal platform 62 is integral with a foot 621, called “internal radial foot", because it extends radially from the internal face of said sector of internal platform, in the direction from inside the dispenser 4.
- the internal radial foot 621 is curved, seen from the front. It is extended radially inwards by an internal radial tongue 622, also curved in front view.
- the tongue 622 is centered in length relative to the internal radial leg 621, so as to avoid the overhang.
- the length of the tongue 622 is preferably reduced to what is necessary for it to absorb the forces.
- the tongue 622 has a tangential length L1, equal to approximately one third of the tangential length L2 of the leg 621.
- the foot 621 supports a single tongue 622.
- the tongue 622 is thinner than the foot 621, so that it can form with this foot 621, a shoulder 623 which opens onto the front face 6211 of the foot 621 (see FIG. 7), that is to say a shoulder 624 which opens onto the rear face 6212 of the foot 621 (see FIG. 8).
- one or more sealing sheets 7 can be fixed to the different angular sectors of the dispenser 6.
- the sheet 7 is formed of a slightly curved profile in an arc, in a circle whose radius is coaxial with the circle of the internal platform 62 in an arc, so as to match the shape of this platform.
- the sheet 7 has a substantially L-shaped cross-section, with a fixing flank 71 and a protective flank 72.
- the fixing flank 71 is intended to be fixed to the foot 621, for example by brazing or welding, this brazing or this welding being able to be carried out punctually or over the entire length of the sheet.
- Each flank 71, 72 may possibly have folds, which define different sides, so as to adapt to the different shapes of feet 621, as seen for example in FIGS. 7 and 8.
- the sheet 7 provides both a sealing role by limiting inter-sector distributor leaks 6 and a thermal protection role with respect to the shell 5, the abradable material 53 and the other elements of the low pressure turbine which are located below this sheet.
- the sheet 8 is arched as is the protective sheet 7. It also has a substantially L-shaped cross section with a fixing flank (not visible in the figure) intended to be fixed by welding or soldering on the external face 52 of the ferrule 50 and a protective flank 81 which extends substantially parallel to the feet 621.
- the sheet 8 can be sectored or extend over 360 ° and may or may not have festoons 810. Its role is to protect the shell 5 and direct the flow of hot air towards the blades 63.
- Each angular sector 6 is mounted on the ferrule 5 so that its tongue 622 is introduced laterally by the open end of the slot 553 and then moved counterclockwise, that is to say to the left in the figure 3.
- the bottom 555 of the slot 553 acts as an anti-rotation stop.
- the rear faces 541 and front 554 constitute bearing faces for the tongue 622 and limit its axial displacement and therefore the axial displacement of the corresponding angular sector 6.
- the tongues 622 are preferably inserted into the slots 553, so that the shoulders 623 or 624 do not come into contact respectively with the wing 54 or the branch 552, which allows a slight radial clearance j1, respectively j2, between the two, and allows the different components to expand.
- FIG. 6 represents an angular sector of a distributor 6, the tongue of which is inserted into the slot of the dog clutch carried by the ferrule 5.
- the lug 556 makes it possible to prevent the disengagement of the tongue 622, the elasticity of the branch 552 being sufficient to allow the introduction of the tongue into the slot.
- the ferrule 5 is mounted in the turbine so that its axis X1 -C ⁇ coincides with the axis X, X ’of the turbine.
- the ferrule 5 is cylindrical in shape and with a simple dog clutch fixing system. Its manufacture is therefore inexpensive, in particular with the new manufacturing processes, for example additive manufacturing.
- the abradable material fixed 53 to the shell 5 is now dissociated from the sectors 6 of the dispenser.
- the repairs to the shell 5 or to the distributor sectors 6 are therefore independent of each other, which can simplify maintenance operations.
- the invention also allows an overall weight gain over the whole of the distributor 4, because the shell 5 has a thickness less than that of the base of an internal platform on a conventional angular sector.
- the manufacturing cost in particular the foundry cost for manufacturing the dispenser, is also reduced, since there is less material and areas to be checked. It is no longer necessary to solder and machine the abradable material on each distributor sector. In addition, it is no longer necessary to make slots on the internal platform 62, which leads to a reduction in costs and simplifies manufacturing.
Abstract
Description
Claims
Applications Claiming Priority (2)
Application Number | Priority Date | Filing Date | Title |
---|---|---|---|
FR1874402A FR3091311B1 (fr) | 2018-12-31 | 2018-12-31 | Distributeur pour turbine, turbine de turbomachine équipée de ce distributeur et turbomachine équipée de cette turbine. |
PCT/FR2019/053317 WO2020141284A1 (fr) | 2018-12-31 | 2019-12-30 | Distributeur pour turbine, turbine de turbomachine équipée de ce distributeur et turbomachine équipée de cette turbine |
Publications (2)
Publication Number | Publication Date |
---|---|
EP3906357A1 true EP3906357A1 (fr) | 2021-11-10 |
EP3906357B1 EP3906357B1 (fr) | 2023-03-29 |
Family
ID=66690613
Family Applications (1)
Application Number | Title | Priority Date | Filing Date |
---|---|---|---|
EP19848997.3A Active EP3906357B1 (fr) | 2018-12-31 | 2019-12-30 | Distributeur pour turbine, turbine de turbomachine équipée de ce distributeur et turbomachine équipée de cette turbine |
Country Status (5)
Country | Link |
---|---|
US (1) | US11408295B2 (fr) |
EP (1) | EP3906357B1 (fr) |
CN (1) | CN113366191B (fr) |
FR (1) | FR3091311B1 (fr) |
WO (1) | WO2020141284A1 (fr) |
Family Cites Families (13)
Publication number | Priority date | Publication date | Assignee | Title |
---|---|---|---|---|
FR2427469A1 (fr) * | 1978-06-01 | 1979-12-28 | Snecma | Dispositif de fixation d'une garniture d'etancheite sur un distributeur de turbomachine |
FR2452590A1 (fr) * | 1979-03-27 | 1980-10-24 | Snecma | Garniture d'etancheite amovible pour segment de distributeur de turbomachine |
JP3697705B2 (ja) * | 1995-06-22 | 2005-09-21 | 石川島播磨重工業株式会社 | ガスタービン高圧タービン静翼の固定装置 |
US6220815B1 (en) * | 1999-12-17 | 2001-04-24 | General Electric Company | Inter-stage seal retainer and assembly |
GB0224962D0 (en) * | 2002-10-26 | 2002-12-04 | Rolls Royce Plc | Seal apparatus |
FR2928961B1 (fr) * | 2008-03-19 | 2015-11-13 | Snecma | Distributeur sectorise pour une turbomachine. |
FR2930592B1 (fr) * | 2008-04-24 | 2010-04-30 | Snecma | Distributeur de turbine pour une turbomachine |
FR2979662B1 (fr) * | 2011-09-07 | 2013-09-27 | Snecma | Procede de fabrication d'un secteur de distributeur de turbine ou redresseur de compresseur en materiau composite pour turbomachine et turbine ou compresseur incorporant un distributeur ou un redresseur forme de tels secteurs |
US9416673B2 (en) * | 2012-01-17 | 2016-08-16 | United Technologies Corporation | Hybrid inner air seal for gas turbine engines |
FR3003599B1 (fr) * | 2013-03-25 | 2017-11-17 | Snecma | Aubage fixe de distribution de flux ameliore |
DE102013212465B4 (de) * | 2013-06-27 | 2015-03-12 | MTU Aero Engines AG | Dichtanordnung für eine Strömungsmaschine, eine Leitschaufelanordnung und eine Strömungsmaschine mit einer derartigen Dichtanordnung |
DE102016222608A1 (de) * | 2016-11-17 | 2018-05-17 | MTU Aero Engines AG | Dichtungsanordnung für eine Leitschaufelanordnung einer Gasturbine |
ES2765852T3 (es) * | 2017-05-29 | 2020-06-11 | MTU Aero Engines AG | Dispositivo de sellado para una turbina, método para fabricar un dispositivo de sellado y una turbina |
-
2018
- 2018-12-31 FR FR1874402A patent/FR3091311B1/fr active Active
-
2019
- 2019-12-30 WO PCT/FR2019/053317 patent/WO2020141284A1/fr unknown
- 2019-12-30 EP EP19848997.3A patent/EP3906357B1/fr active Active
- 2019-12-30 US US17/419,404 patent/US11408295B2/en active Active
- 2019-12-30 CN CN201980090369.7A patent/CN113366191B/zh active Active
Also Published As
Publication number | Publication date |
---|---|
CN113366191A (zh) | 2021-09-07 |
FR3091311B1 (fr) | 2021-04-09 |
US11408295B2 (en) | 2022-08-09 |
WO2020141284A1 (fr) | 2020-07-09 |
US20220074312A1 (en) | 2022-03-10 |
EP3906357B1 (fr) | 2023-03-29 |
CN113366191B (zh) | 2023-03-28 |
FR3091311A1 (fr) | 2020-07-03 |
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