WO2015007980A1 - Dispositif de protection contre des fuites d'huile vers les rotors d'une turbine de turbomachine - Google Patents
Dispositif de protection contre des fuites d'huile vers les rotors d'une turbine de turbomachine Download PDFInfo
- Publication number
- WO2015007980A1 WO2015007980A1 PCT/FR2014/051782 FR2014051782W WO2015007980A1 WO 2015007980 A1 WO2015007980 A1 WO 2015007980A1 FR 2014051782 W FR2014051782 W FR 2014051782W WO 2015007980 A1 WO2015007980 A1 WO 2015007980A1
- Authority
- WO
- WIPO (PCT)
- Prior art keywords
- upstream
- trunnion
- baffle
- downstream
- turbine
- Prior art date
Links
- 238000011144 upstream manufacturing Methods 0.000 claims abstract description 89
- 238000007789 sealing Methods 0.000 claims abstract description 34
- 238000009423 ventilation Methods 0.000 claims abstract description 33
- 239000000203 mixture Substances 0.000 claims abstract description 17
- 239000003351 stiffener Substances 0.000 claims description 4
- 230000000694 effects Effects 0.000 description 8
- 241000842962 Apoda limacodes Species 0.000 description 3
- 238000005461 lubrication Methods 0.000 description 2
- 230000000873 masking effect Effects 0.000 description 2
- 230000001681 protective effect Effects 0.000 description 2
- 238000000926 separation method Methods 0.000 description 2
- 238000005119 centrifugation Methods 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
- F01D25/00—Component parts, details, or accessories, not provided for in, or of interest apart from, other groups
- F01D25/18—Lubricating arrangements
- F01D25/183—Sealing means
-
- 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
- F01D25/18—Lubricating arrangements
-
- 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
- F01D25/16—Arrangement of bearings; Supporting or mounting bearings in casings
-
- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F02—COMBUSTION ENGINES; HOT-GAS OR COMBUSTION-PRODUCT ENGINE PLANTS
- F02C—GAS-TURBINE PLANTS; AIR INTAKES FOR JET-PROPULSION PLANTS; CONTROLLING FUEL SUPPLY IN AIR-BREATHING JET-PROPULSION PLANTS
- F02C7/00—Features, components parts, details or accessories, not provided for in, or of interest apart form groups F02C1/00 - F02C6/00; Air intakes for jet-propulsion plants
- F02C7/28—Arrangement of 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
- F05D2220/00—Application
- F05D2220/30—Application in turbines
-
- 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
- F05D2240/20—Rotors
- F05D2240/24—Rotors for turbines
-
- 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
- F05D2240/60—Shafts
-
- 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
- F05D2260/60—Fluid transfer
- F05D2260/609—Deoiling or demisting
Definitions
- the present invention relates to the general field of turbines of a turbomachine, and in particular of the low-pressure turbine.
- the low-pressure shaft of a turbomachine rotates the various stages of the low-pressure turbine by means of a pin fixed to the low-pressure shaft.
- This trunnion delimits an upstream upstream cavity in which air travels in order to ventilate the various disks of the low-pressure turbine disposed downstream of this trunnion.
- the trunnion of the low-pressure shaft has ventilation holes allowing the ventilation air taken upstream in the engine to feed an external downstream cavity by passing through an inner upstream cavity. This ventilation air is then guided to the disks of the different stages of the low-pressure turbine downstream of the journal to cool them.
- oil from leaks in the lubrication circuit and oil chambers of the turbomachine is also present in the upstream cavity of the low-pressure turbine. This oil has a tendency to mix with the ventilation air and to follow the same path as this one and end up in the downstream cavity of the low-pressure turbine.
- the present invention therefore has the main purpose of overcoming such disadvantages by providing a device for protecting the rotors of the turbine against the risk of oil fire.
- a protection device against oil leakage to the rotors of a turbomachine turbine comprising an upstream cavity in which an air / oil mixture can circulate, said upstream cavity being delimited downstream.
- upstream deflector makes it possible to minimize the amount of oil passing from the upstream cavity to the downstream cavity. Indeed, this upstream deflector comes in particular to impede the direct path of the air / oil mixture coming through the ventilation holes in the trunnion.
- the positioning of the upstream deflector makes it possible to ensure separation between the air path and the oil path.
- the air of the air / oil mixture will tend to pass under the upstream deflector and to walk to the downstream cavity through the ventilation holes.
- the oil of the air / oil mixture under the effect of the centrifugal force of rotation of the pin, it will have a tendency, once past the upstream deflector, to be pressed against the inner wall of the sealing flange. of the trunnion and to go upstream along it.
- the presence of oil passage holes at the end of the upstream deflector which is fixed on the trunnion sealing flange then allows the oil to be discharged upstream of the upstream cavity, without meet airflow counter-clockwise.
- the device according to the invention makes it possible to obtain a deoiling of the air / oil mixture present in the upstream cavity with the oil which is discharged upstream to be recovered and the air which feeds the downstream cavity for ventilate the rotors of the turbine.
- the upstream baffle extends radially inwardly so as to mask the ventilation holes in the trunnion.
- the upstream baffle comprises a fixing flange which is fixed on the trunnion sealing flange by means of fastening systems of the trunnion sealing flange on the trunnion.
- the oil passage holes are advantageously made in the fastening flange of the upstream baffle and angularly positioned between the fastening systems of the trunnion sealing flange on the trunnion.
- the device further comprises a downstream annular baffle fixed on the trunnion and extending radially outwards in the direction of the ventilation holes so as to delimit with the upstream baffle a baffle for the air / oil mixture flowing in the upstream cavity.
- a downstream annular baffle fixed on the trunnion and extending radially outwards in the direction of the ventilation holes so as to delimit with the upstream baffle a baffle for the air / oil mixture flowing in the upstream cavity.
- downstream baffle advantageously extends radially outwardly so as to mask the ventilation holes. This masking favors the capture on the upstream deflector of any direct projections of oil.
- downstream deflector is advantageously interposed axially between the upstream baffle and the ventilation holes made in the trunnion.
- the device may further comprise stiffeners providing a connection between free ends of the upstream and downstream deflectors.
- the downstream baffle may include a mounting flange that is secured to the journal by means of journal attachment systems on a turbine shaft.
- the invention also relates to a turbomachine turbine comprising a protection device against oil leakage as defined above.
- the invention also relates to a turbomachine comprising such a turbine.
- FIG. 1 is a schematic view of a device for protection against oil leakage according to the invention
- FIG. 2 is a perspective view of the upstream deflector of the protection device of FIG. 1;
- FIG. 3 and 4 are schematic views of protection against oil leakage according to alternative embodiments of the invention.
- FIG. 1 schematically and partially shows a turbomachine low-pressure turbine 2 equipped with an oil leakage protection device according to the invention.
- the invention applies to any turbomachine turbine.
- the low-pressure turbine 2 comprises a low-pressure shaft 4 centered on a longitudinal axis 6 of the turbomachine.
- upstream and downstream will be used with respect to the direction of flow of the gas stream passing through the turbomachine.
- downstream and downstream will be used relative to the longitudinal axis 6 of the turbomachine.
- the journal 8 is connected to a rotor disc 12 of a stage of the low-pressure turbine which rotates about the longitudinal axis 6. As shown in FIG. this rotor disc 12 is connected to the rotor discs 12 of the other stages of the low pressure turbine.
- the journal 8 of the low-pressure turbine also comprises a sealing flange 14 which extends axially upstream.
- This sealing flange 14 carries a sealing device (for example a seal labyrinth, not shown in the figures).
- This sealing flange can be fixed to the trunnion by means of a plurality of fastening systems 16, for example of the screw / nut type.
- the journal 8 of the low-pressure turbine delimits two cavities, namely an upstream cavity 18 and a downstream cavity 20.
- the upstream cavity 18 is formed on the inner side and is delimited, on the one hand radially on the outside by the sealing flange 14 of the trunnion, and on the other hand axially downstream by the trunnion itself.
- the downstream cavity 20 it is formed on the outer side and is delimited, on the one hand axially upstream by the journal, and on the other hand radially outwardly by the rotor discs 12.
- the upstream and downstream cavities 20 communicate with each other via a plurality of ventilation holes 22 made in the trunnion 8 and regularly distributed around the longitudinal axis 6 of the turbomachine.
- the downstream cavity 20 opens to ventilation circuits of the rotor discs of the different stages of the low-pressure turbine (not shown in the figures).
- Air taken upstream in the turbomachine feeds the upstream cavity 18 and then passes into the downstream cavity 20 (by restoring a pressure differential between the two cavities) where it is used to supply the ventilation circuits of the disks. rotor.
- oil from leaks in the lubrication circuit and oil chambers of the turbomachine (not shown in the figures) is also present in the upstream cavity 18.
- this oil must not end up in the downstream cavity 20 to avoid any risk of triggering a fire.
- an upstream annular baffle 24 which is fixed on the sealing flange 14 of the journal.
- This upstream deflector 24 is for example formed from a sheet and extends radially inwardly towards the ventilation holes 22 made in the trunnion so as to mask them.
- the upstream baffle 24 has oil passage holes 26 which are formed at its end fixed on the sealing flange 14 of the journal. More specifically, the upstream baffle 24 comprises a fastening flange 24a which can be fastened to the sealing flange 14 of the trunnion by means of the fastening systems 16 of the sealing flange on the trunnion.
- the sealing flange 14 of the trunnion and the trunnion 8 have festoons, respectively 14a and 8a, which are fixed together by the fastening systems 16.
- the oil passage holes 26 are formed in the fastening flange 24a of the upstream baffle 24 and are angularly positioned between the respective festoons 14a, 8a of the sealing flange 14 of the journal and the journal 8.
- These oil passage holes 26 may be regularly distributed around the longitudinal axis 6 of the turbomachine and their number and their dimensions are adapted in particular according to the amount of oil to be evacuated.
- the fastening flange 24a of the upstream deflector 24 also makes it possible to mask the zones situated angularly between the respective festoons 8a, 14a of the journal and its sealing flange, so as to force the passage of air to pass through the air. inside the upstream deflector.
- the size of the oil passage holes 26 is relatively small so that they can quickly be "stuffed” with oil and thus avoid any air passage.
- the air passage at the end of the upstream deflector which is fixed on the sealing flange of the journal is also prohibited by the presence of the fastening flange 24a of the deflector which forms an obstacle to such a passage.
- the upstream deflector 24 masks the ventilation holes 22 made in the trunnion 8, preventing the air / oil mixture flowing in the upstream cavity 18 from passing through these ventilation holes to reach the downstream cavity 20.
- the air / oil mixture (whose path is shown schematically by a solid line in Figure 1) bypasses the upstream deflector.
- this air / oil mixture separates into an oil path (schematized by the mixed lines) which is pressed against the inner wall of the sealing flange 14 of the pin 8 and upstream upstream along it, in particular by borrowing the oil passage holes 26 made in the fastening flange 24a of the upstream deflector, and in one air path (schematized by the dotted lines) which borrows the ventilation holes 22 made in the trunnion under the effect of the differential pressure existing between the upstream and downstream cavities.
- the air thus deoiled enters the downstream cavity and can then feed the ventilation circuits of the rotor disks of the different stages of the low-pressure turbine.
- the oil recovered against the inner wall of the trunnion sealing flange it travels upstream along this wall under the effect of the centrifugal force and can be recovered further upstream, for example by means of scoops (not shown in the figures).
- FIG. 3 represents an alternative embodiment of the device for protecting against oil leaks according to the invention.
- This protection device is identical to that described in connection with Figures 1 and 2 and further comprises a downstream annular baffle 28 which is fixed on the pin 8.
- the downstream deflector 28 is for example formed from a sheet and s extends radially outwards towards the ventilation holes 22 made in the trunnion 8 so as to mask them.
- this downstream deflector 28 is interposed axially between the upstream baffle 24 and the ventilation holes 22 and forms with the upstream baffle a baffle for the air / oil mixture circulating in the upstream cavity 18 (whose path is shown schematically by a line full).
- the downstream deflector 28 comprises a fastening flange 28a which can be fixed on the trunnion 8 by means of the fastening systems 10 of the trunnion 8 on the low-pressure shaft 4.
- the upstream 24 and downstream deflectors 28 prevent the air / oil mixture flowing in the upstream cavity 18 from passing directly through these ventilation holes to reach the downstream cavity 20.
- the air / oil mixture separates into an oil path (schematized by the dashed lines) which comes press against the inner wall of the sealing flange 14 of the pin and go upstream along it, and in an air path (schematized by the dotted lines) which borrows the holes of ventilation 22 under the effect of the differential pressure existing between the upstream and downstream cavities.
- the air thus deoiled enters the downstream cavity and can then feed the ventilation circuits of the rotor disks of the different stages of the low-pressure turbine.
- the oil recovered against the inner wall of the trunnion sealing flange it travels upstream along this wall under the effect of centrifugal force and can be recovered further upstream.
- FIG. 4 represents another alternative embodiment of the device for protecting against oil leaks according to the invention.
- the device according to this variant is identical with that described in connection with Figure 3 and further comprises stiffeners 30 providing a connection between the free ends of the upstream baffle 24 and downstream 28 (that is to say their ends opposite to the clamp).
- stiffeners 30 may be simple sheets fixed to the free ends of the baffles 24, 28 and angularly spaced from each other to allow passage of the air / oil mixture. They make it possible to confer a certain mechanical strength on the protective device thus constituted.
Landscapes
- Engineering & Computer Science (AREA)
- Mechanical Engineering (AREA)
- General Engineering & Computer Science (AREA)
- Chemical & Material Sciences (AREA)
- Combustion & Propulsion (AREA)
- Turbine Rotor Nozzle Sealing (AREA)
- Sealing Using Fluids, Sealing Without Contact, And Removal Of Oil (AREA)
Abstract
Description
Claims
Priority Applications (6)
Application Number | Priority Date | Filing Date | Title |
---|---|---|---|
CN201480040681.2A CN105392968B (zh) | 2013-07-16 | 2014-07-10 | 用于防止向涡轮机的涡轮的转子漏油的装置 |
US14/904,557 US10294820B2 (en) | 2013-07-16 | 2014-07-10 | Device for protecting against oil leaks towards the rotors of a turbomachine turbine |
RU2016104974A RU2665607C2 (ru) | 2013-07-16 | 2014-07-10 | Устройство защиты от утечек масла в сторону роторов турбины газотурбинного двигателя |
EP14755859.7A EP3022403B1 (fr) | 2013-07-16 | 2014-07-10 | Dispositif de protection contre des fuites d'huile vers les rotors d'une turbine de turbomachine |
BR112016000969-0A BR112016000969B1 (pt) | 2013-07-16 | 2014-07-10 | Dispositivo de proteção contra vazamentos de óleo na direção dos rotores de uma turbina de turbomáquina, turbina de turbomáquina, e, turbomáquina |
CA2917946A CA2917946C (fr) | 2013-07-16 | 2014-07-10 | Dispositif de protection contre des fuites d'huile vers les rotors d'une turbine de turbomachine |
Applications Claiming Priority (2)
Application Number | Priority Date | Filing Date | Title |
---|---|---|---|
FR1357001 | 2013-07-16 | ||
FR1357001A FR3008738B1 (fr) | 2013-07-16 | 2013-07-16 | Dispositif de protection contre les fuites d'huile vers les rotors d'une turbine de turbomachine |
Publications (1)
Publication Number | Publication Date |
---|---|
WO2015007980A1 true WO2015007980A1 (fr) | 2015-01-22 |
Family
ID=49378459
Family Applications (1)
Application Number | Title | Priority Date | Filing Date |
---|---|---|---|
PCT/FR2014/051782 WO2015007980A1 (fr) | 2013-07-16 | 2014-07-10 | Dispositif de protection contre des fuites d'huile vers les rotors d'une turbine de turbomachine |
Country Status (8)
Country | Link |
---|---|
US (1) | US10294820B2 (fr) |
EP (1) | EP3022403B1 (fr) |
CN (1) | CN105392968B (fr) |
BR (1) | BR112016000969B1 (fr) |
CA (1) | CA2917946C (fr) |
FR (1) | FR3008738B1 (fr) |
RU (1) | RU2665607C2 (fr) |
WO (1) | WO2015007980A1 (fr) |
Cited By (2)
Publication number | Priority date | Publication date | Assignee | Title |
---|---|---|---|---|
WO2021064330A1 (fr) * | 2019-10-03 | 2021-04-08 | Safran Aircraft Engines | Agencement de turbine intégrant une rigole circonférentielle de récupération d'huile |
FR3139357A1 (fr) * | 2022-09-07 | 2024-03-08 | Safran Helicopter Engines | Turbomachine avec canalisation d’air secondaire comportant un systeme de deshuilage |
Families Citing this family (2)
Publication number | Priority date | Publication date | Assignee | Title |
---|---|---|---|---|
EP3239481A1 (fr) * | 2016-04-27 | 2017-11-01 | Rolls-Royce plc | Paroi de chambre d'huile avec trous traversants |
IT201800006394A1 (it) * | 2018-06-18 | 2019-12-18 | Sistema di spurgo per cassa cuscino |
Citations (2)
Publication number | Priority date | Publication date | Assignee | Title |
---|---|---|---|---|
EP2090764A1 (fr) * | 2008-02-13 | 2009-08-19 | Snecma | Dispositif de récupération d'huile |
WO2012069772A1 (fr) * | 2010-11-26 | 2012-05-31 | Snecma | Dispositif d'evacuation d'huile et turbomachine comprenant un tel dispositif |
Family Cites Families (10)
Publication number | Priority date | Publication date | Assignee | Title |
---|---|---|---|---|
GB876862A (en) * | 1959-03-11 | 1961-09-06 | Rolls Royce | Improvements in or relating to bearing lubrication |
US3844110A (en) * | 1973-02-26 | 1974-10-29 | Gen Electric | Gas turbine engine internal lubricant sump venting and pressurization system |
US4084861A (en) * | 1976-11-11 | 1978-04-18 | United Technologies Corporation | Thrust bearing damping means |
FR2518650B1 (fr) * | 1981-12-22 | 1986-05-30 | Snecma | Dispositif de pilotage des jeux d'un palier inter-arbres de turbomachine multi-corps |
GB9009588D0 (en) * | 1990-04-28 | 1990-06-20 | Rolls Royce Plc | A hydraulic seal and method of assembly |
US6705349B2 (en) * | 2001-10-22 | 2004-03-16 | General Electric Company | Weep plug |
US7836675B2 (en) * | 2006-02-21 | 2010-11-23 | General Electric Company | Supercore sump vent pressure control |
US7935164B2 (en) * | 2007-11-28 | 2011-05-03 | General Electric Company | Vortex air-oil separator system |
CN201953484U (zh) * | 2010-12-23 | 2011-08-31 | 中国航空工业集团公司沈阳发动机设计研究所 | 一种避免篦齿封严结构滑油泄漏的装置 |
FR2992679A1 (fr) * | 2012-06-28 | 2014-01-03 | Snecma | Tourillon de turbomachine comportant une couronne de recuperation d'un flux d'huile de lubrification avec une pluralite d'orifices d'evacuation d'huile de lubrification |
-
2013
- 2013-07-16 FR FR1357001A patent/FR3008738B1/fr not_active Expired - Fee Related
-
2014
- 2014-07-10 BR BR112016000969-0A patent/BR112016000969B1/pt active IP Right Grant
- 2014-07-10 CN CN201480040681.2A patent/CN105392968B/zh active Active
- 2014-07-10 CA CA2917946A patent/CA2917946C/fr active Active
- 2014-07-10 EP EP14755859.7A patent/EP3022403B1/fr active Active
- 2014-07-10 US US14/904,557 patent/US10294820B2/en active Active
- 2014-07-10 WO PCT/FR2014/051782 patent/WO2015007980A1/fr active Application Filing
- 2014-07-10 RU RU2016104974A patent/RU2665607C2/ru active
Patent Citations (2)
Publication number | Priority date | Publication date | Assignee | Title |
---|---|---|---|---|
EP2090764A1 (fr) * | 2008-02-13 | 2009-08-19 | Snecma | Dispositif de récupération d'huile |
WO2012069772A1 (fr) * | 2010-11-26 | 2012-05-31 | Snecma | Dispositif d'evacuation d'huile et turbomachine comprenant un tel dispositif |
Cited By (5)
Publication number | Priority date | Publication date | Assignee | Title |
---|---|---|---|---|
WO2021064330A1 (fr) * | 2019-10-03 | 2021-04-08 | Safran Aircraft Engines | Agencement de turbine intégrant une rigole circonférentielle de récupération d'huile |
FR3101662A1 (fr) * | 2019-10-03 | 2021-04-09 | Safran Aircraft Engines | Agencement de turbine intégrant une rigole circonférentielle de récupération d’huile |
CN114502820A (zh) * | 2019-10-03 | 2022-05-13 | 赛峰飞机发动机公司 | 带有油回收圆周槽的涡轮布置 |
CN114502820B (zh) * | 2019-10-03 | 2024-05-24 | 赛峰飞机发动机公司 | 带有油回收圆周槽的涡轮布置 |
FR3139357A1 (fr) * | 2022-09-07 | 2024-03-08 | Safran Helicopter Engines | Turbomachine avec canalisation d’air secondaire comportant un systeme de deshuilage |
Also Published As
Publication number | Publication date |
---|---|
US10294820B2 (en) | 2019-05-21 |
CA2917946A1 (fr) | 2015-01-22 |
CA2917946C (fr) | 2021-05-04 |
RU2016104974A3 (fr) | 2018-06-01 |
BR112016000969A2 (fr) | 2017-08-29 |
EP3022403A1 (fr) | 2016-05-25 |
CN105392968B (zh) | 2018-04-10 |
CN105392968A (zh) | 2016-03-09 |
BR112016000969B1 (pt) | 2022-02-08 |
FR3008738A1 (fr) | 2015-01-23 |
RU2016104974A (ru) | 2017-08-21 |
EP3022403B1 (fr) | 2021-08-25 |
US20160169041A1 (en) | 2016-06-16 |
FR3008738B1 (fr) | 2015-08-28 |
RU2665607C2 (ru) | 2018-08-31 |
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