EP3274559A1 - Keramikkern für eine mehrkammerturbinenschaufel - Google Patents

Keramikkern für eine mehrkammerturbinenschaufel

Info

Publication number
EP3274559A1
EP3274559A1 EP16714492.2A EP16714492A EP3274559A1 EP 3274559 A1 EP3274559 A1 EP 3274559A1 EP 16714492 A EP16714492 A EP 16714492A EP 3274559 A1 EP3274559 A1 EP 3274559A1
Authority
EP
European Patent Office
Prior art keywords
core
blade
ceramic
cavities
central cavity
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.)
Pending
Application number
EP16714492.2A
Other languages
English (en)
French (fr)
Inventor
Sylvain Paquin
Charlotte Marie Dujol
Patrice Eneau
Hugues Denis JOUBERT
Adrien Bernard Vincent ROLLINGER
Current Assignee (The listed assignees may be inaccurate. Google has not performed a legal analysis and makes no representation or warranty as to the accuracy of the list.)
Safran Aircraft Engines SAS
Original Assignee
Safran Aircraft Engines SAS
SNECMA SAS
Priority date (The priority date 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 date listed.)
Filing date
Publication date
Application filed by Safran Aircraft Engines SAS, SNECMA SAS filed Critical Safran Aircraft Engines SAS
Publication of EP3274559A1 publication Critical patent/EP3274559A1/de
Pending legal-status Critical Current

Links

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
    • F01D5/00—Blades; Blade-carrying members; Heating, heat-insulating, cooling or antivibration means on the blades or the members
    • F01D5/12—Blades
    • F01D5/28—Selecting particular materials; Particular measures relating thereto; Measures against erosion or corrosion
    • F01D5/284—Selection of ceramic materials
    • B—PERFORMING OPERATIONS; TRANSPORTING
    • B22—CASTING; POWDER METALLURGY
    • B22C—FOUNDRY MOULDING
    • B22C9/00—Moulds or cores; Moulding processes
    • B22C9/02—Sand moulds or like moulds for shaped castings
    • B22C9/04—Use of lost patterns
    • B—PERFORMING OPERATIONS; TRANSPORTING
    • B22—CASTING; POWDER METALLURGY
    • B22C—FOUNDRY MOULDING
    • B22C9/00—Moulds or cores; Moulding processes
    • B22C9/10—Cores; Manufacture or installation of cores
    • 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
    • F01D5/00—Blades; Blade-carrying members; Heating, heat-insulating, cooling or antivibration means on the blades or the members
    • F01D5/12—Blades
    • F01D5/14—Form or construction
    • F01D5/18—Hollow blades, i.e. blades with cooling or heating channels or cavities; Heating, heat-insulating or cooling means on 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
    • F01D5/00—Blades; Blade-carrying members; Heating, heat-insulating, cooling or antivibration means on the blades or the members
    • F01D5/12—Blades
    • F01D5/14—Form or construction
    • F01D5/18—Hollow blades, i.e. blades with cooling or heating channels or cavities; Heating, heat-insulating or cooling means on blades
    • F01D5/187—Convection cooling
    • 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
    • F05D2230/00—Manufacture
    • F05D2230/20—Manufacture essentially without removing material
    • F05D2230/21—Manufacture essentially without removing material by casting
    • 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
    • F05D2230/00—Manufacture
    • F05D2230/20—Manufacture essentially without removing material
    • F05D2230/21—Manufacture essentially without removing material by casting
    • F05D2230/211—Manufacture essentially without removing material by casting by precision casting, e.g. microfusing or investment casting
    • 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
    • F05D2240/30—Characteristics of rotor blades, i.e. of any element transforming dynamic fluid energy to or from rotational energy and being attached to a rotor
    • F05D2240/305—Characteristics of rotor blades, i.e. of any element transforming dynamic fluid energy to or from rotational energy and being attached to a rotor related to the pressure side of a rotor blade
    • 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
    • F05D2300/00—Materials; Properties thereof
    • F05D2300/20—Oxide or non-oxide ceramics

Definitions

  • the present invention relates to the general field of turbomachine turbine blades, and more particularly to turbine blades provided with integrated cooling circuits produced by the lost-wax casting technique.
  • a turbomachine comprises a combustion chamber in which air and fuel are mixed before being burned.
  • the gases from this combustion flow downstream of the combustion chamber and then feed a high pressure turbine and a low pressure turbine.
  • Each turbine has one or more rows of stationary blades (called distributors) alternating with one or more rows of moving blades (called moving wheels), circumferentially spaced around the rotor of the turbine.
  • These turbine blades are subjected to very high temperatures of the combustion gases, which reach values much higher than those which can bear without damage these blades which are in direct contact with these gases, which has the effect of limiting their service life. .
  • trombone cavity circuits which have the advantage of maximizing the work of air through the circuit, lead to a significant heating of this air which results in a decrease in the thermal efficiency of the holes located in end of trombone.
  • configurations with leading-edge cavities and direct-feed trailing edge do not provide an effective response. at the high temperature levels usually seen at the top of the blade.
  • the different cavities are separated from the vein only by a wall of variable thickness depending on the areas of the blade. Given the constraints on the flow rate allocated to cooling the blades and the current trend of increasing the vein air temperatures, it is not possible to efficiently cool the dawn with a circuit of this type without significantly increasing the air flow and penalize engine performance.
  • FIG. 5 illustrates a gas turbine engine high-pressure turbine blade 10 having an aerodynamic surface or blade 12 which extends radially between a foot 14 and a blade tip 16.
  • the foot of the blade is shaped so that it allows the mounting of the blade on a rotor disc.
  • the top of the blade has a so-called tubular portion 18 consisting of a bottom transverse to the blade and a wall forming its edge in the extension of the wall of the blade 12.
  • the blade 12 comprises, in the example illustrated by way of principle, a plurality of cavities 20, 22, 24, 26, 28, 30, 32.
  • First and second central cavities 20, 22 extend from foot to the top of the blade and two other cavities 24, 26 are disposed on either side of these central cavities, along the wall of the extrados between these central cavities and the extrados wall of the blade and along the wall of the intrados between these central cavities and the intrados wall of the dawn.
  • a cavity 28 is located in the portion of the blade near the leading edge and two cavities 30, 32 follow one another in line in the portion of the blade near the trailing edge.
  • the high pressure turbine blades are conventionally made in lost-wax foundry, the geometry of the circuits being realized, according to its complexity, by the positioning in the mold of one or several ceramic cores whose outer surface forms the inner surface of the finished blade.
  • the cooling circuits comprising several cavities, like those of FIGS. 5 and 6, require the assembly of several separate ceramic cores (intended to produce the central cold cavities insulated from the hot gases and the fine external cavities having air supplies). distinct) to ensure the metal wall thickness before it can be cast. It is thus a complex operation whose assembly, which is done manually by the foot and the head of the ceramic cores, prevents the realization in foundry of the bath at the head of dawn, which obliges to a finishing operation expensive additional which may lead to a limitation of the mechanical strength of the blade in this zone (supply of the bath or brazing by for example).
  • the present invention therefore aims to overcome the disadvantages associated with the manual assembly of several separate cores by proposing a cooling circuit for a turbine blade that can be made in a single core in order to eliminate these assembly and finishing operations.
  • tub of the circuits of the prior art while ensuring the distance intercavities corresponding to the thickness of the metal partition after pouring of the molten metal, more reliably than in the current manual assemblies.
  • a ceramic core used for the manufacture of a turbomachine hollow turbine blade according to the lost wax foundry technique, the blade having at least one central cavity, a first lateral cavity disposed between said at least one central cavity and an extrados wall of the blade and a second lateral cavity disposed between said at least one central cavity and an intrados wall of the blade.
  • the core is shaped to form said cavities in a single member and comprises, to jointly feed the interior of said cooling air cavities, core portions for forming said first and second lateral cavities connected to a core portion for forming said at least one central cavity, on the one hand at the bottom of the core by at least two ceramic junctions and on the other hand at different heights of said core by a plurality of other ceramic junctions whose positioning defines the thickness of the internal partitions of the blade while providing additional cooling air to predetermined critical areas of said first and second lateral cavities.
  • a core portion for forming a bath and connected to said core portion for forming said at least one central cavity by ceramic junctions whose positioning defines the thickness of said bath while providing air evacuation cooling at the head of dawn.
  • the need for assembling fireworks at the head of the blade is removed, which makes it possible to obtain a foundry bath having the same mechanical properties as the body of the dawn.
  • the main feed of the lateral cavities by their foot makes it possible to better control the flow of air and the overall cooling of the external walls on the finished blade and, on the core, the feeds of the different cavities can be joined as soon as possible. injection, which further improves the mechanical strength of the cores.
  • said predetermined critical zones are chosen from the most thermomechanically stressed zones of said first and second lateral cavities and said ceramic junctions have a section dimensioned to ensure the mechanical strength of said internal partitions during the casting of the metal. molten.
  • the invention also relates to the method of manufacturing a turbomachine hollow turbine blade made by the lost-wax casting technique by means of a single-element core as explained above and any turbomachine turbine equipped with a plurality of cooled blades made from such a method.
  • a turbomachine hollow turbine blade made by the lost-wax casting technique by means of a single-element core as explained above and any turbomachine turbine equipped with a plurality of cooled blades made from such a method.
  • FIG. 1 is an intrados view of a turbine blade core according to the invention
  • FIG. 2 is an extrados view of a turbine blade core according to the invention
  • FIG. 3 is a view of the core of FIGS. 1 and 2 cut along the height of the blade to show its junction zones
  • FIG. 5 is a perspective view of a turbine blade of the prior art
  • FIG. 6 is a sectional view of the blade of Figure 5.
  • Figures 1 and 2 show a ceramic core 40 for the realization of a turbomachine turbine blade respectively seen extrados side and intrados side view of this blade.
  • the ceramic core in the illustrated example, comprises seven parts or columns forming a single element.
  • the first column 42 which is intended to be on the side of the arrival of the combustion gases, corresponds to the leading edge cavity 28 which will be created after casting, while the second column 44 corresponds to the central cavity 20 which is adjacent to it.
  • the latter receives a flow of cooling air through a pipe (not shown) resulting, after casting, the presence of a first column foot 46 of the core 40.
  • the other three columns 48, 50, 52 making a go- return correspond to the following cavities 22, 30, 32 which receive a second flow of cooling air supplied by another pipe resulting from the presence of a second column foot 54 connected to the first column foot 46 to form the foot of the core .
  • the first and second columns 42 and 44 are connected to each other by a series of bridges 56, to which will correspond, after casting, air supply ports (see reference 80 in Figure 4A) for cooling of the leading edge cavity 28.
  • At least two upper bridges 57, at the connection with the columns and a head 59 of the core 40 make it possible to obtain the desired thickness of the partition at the bottom of the bath during the casting and are also dimensioned to form air exhaust ports.
  • vertically inclined bridges 58 create core thinned regions to create stiffened blade regions.
  • the size of the various bridges is determined to prevent them from breaking when handling the core 40, which would render it unusable.
  • the bridges are, in the example considered, distributed spaced substantially regularly over the height of the core 40 in particular to the first column 42 of the core.
  • the core 40 further comprises sixth and seventh lateral columns 60 and 62 separated from each other of the second and third columns 44, 48 by a determined spacing thus leaving room for the creation of a solid inter-cavity wall during casting of the molten metal.
  • the lower end of the sixth column 60 is connected to the first column foot 46 and the lower end of the seventh column 62 is connected to the second foot column 54 and multiple ceramic junctions of small section (see for example the references 64, 66, 68 of Figure 3), however dimensioned to ensure the mechanical strength of the internal partitions formed during the casting of the molten metal in the mold of casting, are arranged on the functional portion of the blade between these two lateral columns and the second and third central columns.
  • Figures 4A, 4B and 4C show the orifices 72, 74, 76, 78 left by the junctions between the two central cavities 20, 22 and the lateral cavities 24, 26 at different heights of the blade (or core).
  • FIG. 4A it is possible to note the two orifices 72, 74 ensuring an air passage between the central cavity 22 and the lateral cavities 24, 26 respectively, the orifice 80 at the resulting leading edge cavity 28. of a bridge 56.
  • the orifice 76 ensures an air passage between the central cavity 20 and the lateral cavity 24
  • the orifice 78 ensures an air passage between the central cavity 20 and the lateral cavity 26.
  • the lost wax manufacturing process of the blade once the nucleus into a single element made is conventional and consists first of all in forming an injection mold in which is placed the core before injection of the wax.
  • the wax model thus created is then dipped in slips consisting of ceramic suspension to make a casting mold (also called shell mold). Finally, the wax is removed and the shell mold is baked into which the molten metal can then be cast.
  • junctions linking the central and lateral columns of the core Due to the ceramic junctions linking the central and lateral columns of the core, their relative spacing is controlled over the entire height of the blade. These junctions are further positioned to drive, on the finished blade, a supply of additional fresh air from the central cavities to the most thermomechanically stressed areas of the lateral cavities, which also improves the local thermal efficiency. and the life of dawn. These junctions are especially sized and arranged to ensure:

Landscapes

  • Engineering & Computer Science (AREA)
  • Mechanical Engineering (AREA)
  • General Engineering & Computer Science (AREA)
  • Chemical & Material Sciences (AREA)
  • Ceramic Engineering (AREA)
  • Materials Engineering (AREA)
  • Turbine Rotor Nozzle Sealing (AREA)
  • Molds, Cores, And Manufacturing Methods Thereof (AREA)
EP16714492.2A 2015-03-23 2016-03-22 Keramikkern für eine mehrkammerturbinenschaufel Pending EP3274559A1 (de)

Applications Claiming Priority (2)

Application Number Priority Date Filing Date Title
FR1552383A FR3034128B1 (fr) 2015-03-23 2015-03-23 Noyau ceramique pour aube de turbine multi-cavites
PCT/FR2016/050628 WO2016151234A1 (fr) 2015-03-23 2016-03-22 Noyau ceramique pour aube de turbine multi-cavites

Publications (1)

Publication Number Publication Date
EP3274559A1 true EP3274559A1 (de) 2018-01-31

Family

ID=53514313

Family Applications (1)

Application Number Title Priority Date Filing Date
EP16714492.2A Pending EP3274559A1 (de) 2015-03-23 2016-03-22 Keramikkern für eine mehrkammerturbinenschaufel

Country Status (9)

Country Link
US (1) US10961856B2 (de)
EP (1) EP3274559A1 (de)
JP (2) JP2018515343A (de)
CN (1) CN107407152A (de)
BR (1) BR112017020233A2 (de)
CA (1) CA2981994A1 (de)
FR (1) FR3034128B1 (de)
RU (1) RU2719410C2 (de)
WO (1) WO2016151234A1 (de)

Families Citing this family (17)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
PL3086893T3 (pl) * 2013-12-23 2020-01-31 United Technologies Corporation Rama konstrukcyjna z traconym rdzeniem
FR3037829B1 (fr) * 2015-06-29 2017-07-21 Snecma Noyau pour le moulage d'une aube ayant des cavites superposees et comprenant un trou de depoussierage traversant une cavite de part en part
FR3048718B1 (fr) * 2016-03-10 2020-01-24 Safran Aube de turbomachine a refroidissement optimise
FR3067390B1 (fr) 2017-04-10 2019-11-29 Safran Aube de turbine presentant une structure amelioree
US11098595B2 (en) * 2017-05-02 2021-08-24 Raytheon Technologies Corporation Airfoil for gas turbine engine
FR3067955B1 (fr) * 2017-06-23 2019-09-06 Safran Aircraft Engines Procede de positionnement d'une piece creuse
US10731474B2 (en) * 2018-03-02 2020-08-04 Raytheon Technologies Corporation Airfoil with varying wall thickness
FR3080051B1 (fr) * 2018-04-13 2022-04-08 Safran Noyau pour la fonderie d'une piece aeronautique
US11040915B2 (en) * 2018-09-11 2021-06-22 General Electric Company Method of forming CMC component cooling cavities
FR3094655B1 (fr) * 2019-04-08 2021-02-26 Safran Procédé de fabrication d’une pluralité de secteurs de distributeur par fonderie
FR3107920B1 (fr) 2020-03-03 2023-11-10 Safran Aircraft Engines Aube creuse de turbomachine et plateforme inter-aubes équipées de saillies perturbatrices de flux de refroidissement
CN111678563A (zh) * 2020-06-20 2020-09-18 贵阳航发精密铸造有限公司 测量多腔涡轮叶片内腔流量夹具
CN112916811B (zh) * 2021-01-22 2023-05-16 成都航宇超合金技术有限公司 带气膜孔的空心涡轮叶片的铸造方法
CN113414355B (zh) * 2021-06-10 2024-04-09 安徽海立精密铸造有限公司 一种复杂型腔汽车铸件全包芯式泥芯结构
CN114393177A (zh) * 2022-01-25 2022-04-26 烟台路通精密科技股份有限公司 一种大型薄壁铝合金增压叶轮的铸造工艺及装置
FR3137316A1 (fr) 2022-06-29 2024-01-05 Safran Aircraft Engines Noyau céramique pour aube de turbine creuse à perçages externes
CN115625286B (zh) * 2022-10-13 2023-06-30 中国航发北京航空材料研究院 单晶空心导向叶片的外型模具及其定位方法

Family Cites Families (32)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
GB860126A (en) * 1956-06-20 1961-02-01 Wiggin & Co Ltd Henry Improvements relating to the production of hollow metal articles
FR2569225A1 (fr) * 1977-06-11 1986-02-21 Rolls Royce Aube creuse refroidie, pour moteur a turbine a gaz
GB2121483B (en) * 1982-06-08 1985-02-13 Rolls Royce Cooled turbine blade for a gas turbine engine
US4596281A (en) * 1982-09-02 1986-06-24 Trw Inc. Mold core and method of forming internal passages in an airfoil
US4627480A (en) * 1983-11-07 1986-12-09 General Electric Company Angled turbulence promoter
US5720431A (en) 1988-08-24 1998-02-24 United Technologies Corporation Cooled blades for a gas turbine engine
US5667359A (en) 1988-08-24 1997-09-16 United Technologies Corp. Clearance control for the turbine of a gas turbine engine
US5296308A (en) * 1992-08-10 1994-03-22 Howmet Corporation Investment casting using core with integral wall thickness control means
US5599166A (en) * 1994-11-01 1997-02-04 United Technologies Corporation Core for fabrication of gas turbine engine airfoils
US5702232A (en) * 1994-12-13 1997-12-30 United Technologies Corporation Cooled airfoils for a gas turbine engine
US5947181A (en) * 1996-07-10 1999-09-07 General Electric Co. Composite, internal reinforced ceramic cores and related methods
US5820774A (en) * 1996-10-28 1998-10-13 United Technologies Corporation Ceramic core for casting a turbine blade
US6511293B2 (en) * 2001-05-29 2003-01-28 Siemens Westinghouse Power Corporation Closed loop steam cooled airfoil
GB0114503D0 (en) * 2001-06-14 2001-08-08 Rolls Royce Plc Air cooled aerofoil
US6637500B2 (en) * 2001-10-24 2003-10-28 United Technologies Corporation Cores for use in precision investment casting
US6915840B2 (en) * 2002-12-17 2005-07-12 General Electric Company Methods and apparatus for fabricating turbine engine airfoils
US6929054B2 (en) * 2003-12-19 2005-08-16 United Technologies Corporation Investment casting cores
US6966756B2 (en) * 2004-01-09 2005-11-22 General Electric Company Turbine bucket cooling passages and internal core for producing the passages
US20050258577A1 (en) * 2004-05-20 2005-11-24 Holowczak John E Method of producing unitary multi-element ceramic casting cores and integral core/shell system
FR2875425B1 (fr) * 2004-09-21 2007-03-30 Snecma Moteurs Sa Procede de fabrication d'une aube de turbomachine, assemblage de noyaux pour la mise en oeuvre du procede.
US7377746B2 (en) * 2005-02-21 2008-05-27 General Electric Company Airfoil cooling circuits and method
US7413403B2 (en) * 2005-12-22 2008-08-19 United Technologies Corporation Turbine blade tip cooling
US7625178B2 (en) * 2006-08-30 2009-12-01 Honeywell International Inc. High effectiveness cooled turbine blade
US7722324B2 (en) * 2006-09-05 2010-05-25 United Technologies Corporation Multi-peripheral serpentine microcircuits for high aspect ratio blades
US7674093B2 (en) 2006-12-19 2010-03-09 General Electric Company Cluster bridged casting core
US20100034662A1 (en) * 2006-12-26 2010-02-11 General Electric Company Cooled airfoil and method for making an airfoil having reduced trail edge slot flow
FR2914871B1 (fr) 2007-04-11 2009-07-10 Snecma Sa Outillage pour la fabrication de noyaux ceramiques de fonderie pour aubes de turbomachines
FR2961552B1 (fr) 2010-06-21 2014-01-31 Snecma Aube de turbine a cavite de bord d'attaque refroidie par impact
FR2986982B1 (fr) * 2012-02-22 2024-07-05 Snecma Ensemble de noyau de fonderie pour la fabrication d'une aube de turbomachine, procede de fabrication d'une aube et aube associes
US9765630B2 (en) 2013-01-09 2017-09-19 General Electric Company Interior cooling circuits in turbine blades
FR3021697B1 (fr) * 2014-05-28 2021-09-17 Snecma Aube de turbine a refroidissement optimise
FR3021698B1 (fr) * 2014-05-28 2021-07-02 Snecma Aube de turbine, comprenant un conduit central de refroidissement isole thermiquement de parois de l'aube par deux cavites laterales jointives en aval du conduit central

Also Published As

Publication number Publication date
RU2017134365A3 (de) 2019-09-12
FR3034128A1 (fr) 2016-09-30
FR3034128B1 (fr) 2017-04-14
CA2981994A1 (fr) 2016-09-29
JP2018515343A (ja) 2018-06-14
RU2719410C2 (ru) 2020-04-17
CN107407152A8 (zh) 2018-01-12
RU2017134365A (ru) 2019-04-03
US20180073373A1 (en) 2018-03-15
WO2016151234A1 (fr) 2016-09-29
JP7455074B2 (ja) 2024-03-25
BR112017020233A2 (pt) 2018-05-22
JP2021062408A (ja) 2021-04-22
US10961856B2 (en) 2021-03-30
CN107407152A (zh) 2017-11-28

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