WO2014072626A2 - Support de tube d'évacuation d'air dans une turbomachine - Google Patents
Support de tube d'évacuation d'air dans une turbomachine Download PDFInfo
- Publication number
- WO2014072626A2 WO2014072626A2 PCT/FR2013/052625 FR2013052625W WO2014072626A2 WO 2014072626 A2 WO2014072626 A2 WO 2014072626A2 FR 2013052625 W FR2013052625 W FR 2013052625W WO 2014072626 A2 WO2014072626 A2 WO 2014072626A2
- Authority
- WO
- WIPO (PCT)
- Prior art keywords
- support
- turbomachine
- fins
- tube
- annular portion
- Prior art date
Links
- 239000003351 stiffener Substances 0.000 claims description 9
- PXHVJJICTQNCMI-UHFFFAOYSA-N Nickel Chemical compound [Ni] PXHVJJICTQNCMI-UHFFFAOYSA-N 0.000 claims description 6
- 238000011144 upstream manufacturing Methods 0.000 claims description 6
- 229910001119 inconels 625 Inorganic materials 0.000 claims description 3
- 229910000816 inconels 718 Inorganic materials 0.000 claims description 3
- 229910052759 nickel Inorganic materials 0.000 claims description 3
- 229910000601 superalloy Inorganic materials 0.000 claims description 3
- 238000007599 discharging Methods 0.000 claims 2
- 238000001816 cooling Methods 0.000 description 3
- 230000000295 complement effect Effects 0.000 description 2
- 230000000694 effects Effects 0.000 description 2
- 239000007789 gas Substances 0.000 description 2
- 238000002485 combustion reaction Methods 0.000 description 1
- 238000006073 displacement reaction Methods 0.000 description 1
- 238000005476 soldering Methods 0.000 description 1
- 230000035882 stress Effects 0.000 description 1
- 230000008646 thermal stress Effects 0.000 description 1
- 238000003466 welding 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
- F01M—LUBRICATING OF MACHINES OR ENGINES IN GENERAL; LUBRICATING INTERNAL COMBUSTION ENGINES; CRANKCASE VENTILATING
- F01M13/00—Crankcase ventilating or breathing
-
- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F16—ENGINEERING ELEMENTS AND UNITS; GENERAL MEASURES FOR PRODUCING AND MAINTAINING EFFECTIVE FUNCTIONING OF MACHINES OR INSTALLATIONS; THERMAL INSULATION IN GENERAL
- F16B—DEVICES FOR FASTENING OR SECURING CONSTRUCTIONAL ELEMENTS OR MACHINE PARTS TOGETHER, e.g. NAILS, BOLTS, CIRCLIPS, CLAMPS, CLIPS OR WEDGES; JOINTS OR JOINTING
- F16B2/00—Friction-grip releasable fastenings
- F16B2/20—Clips, i.e. with gripping action effected solely by the inherent resistance to deformation of the material of the fastening
- F16B2/22—Clips, i.e. with gripping action effected solely by the inherent resistance to deformation of the material of the fastening of resilient material, e.g. rubbery material
- F16B2/24—Clips, i.e. with gripping action effected solely by the inherent resistance to deformation of the material of the fastening of resilient material, e.g. rubbery material of metal
- F16B2/241—Clips, i.e. with gripping action effected solely by the inherent resistance to deformation of the material of the fastening of resilient material, e.g. rubbery material of metal of sheet metal
- F16B2/243—Clips, i.e. with gripping action effected solely by the inherent resistance to deformation of the material of the fastening of resilient material, e.g. rubbery material of metal of sheet metal internal, i.e. with spreading action
-
- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F16—ENGINEERING ELEMENTS AND UNITS; GENERAL MEASURES FOR PRODUCING AND MAINTAINING EFFECTIVE FUNCTIONING OF MACHINES OR INSTALLATIONS; THERMAL INSULATION IN GENERAL
- F16L—PIPES; JOINTS OR FITTINGS FOR PIPES; SUPPORTS FOR PIPES, CABLES OR PROTECTIVE TUBING; MEANS FOR THERMAL INSULATION IN GENERAL
- F16L3/00—Supports for pipes, cables or protective tubing, e.g. hangers, holders, clamps, cleats, clips, brackets
- F16L3/08—Supports for pipes, cables or protective tubing, e.g. hangers, holders, clamps, cleats, clips, brackets substantially surrounding the pipe, cable or protective tubing
- F16L3/12—Supports for pipes, cables or protective tubing, e.g. hangers, holders, clamps, cleats, clips, brackets substantially surrounding the pipe, cable or protective tubing comprising a member substantially surrounding the pipe, cable or protective tubing
- F16L3/1222—Supports for pipes, cables or protective tubing, e.g. hangers, holders, clamps, cleats, clips, brackets substantially surrounding the pipe, cable or protective tubing comprising a member substantially surrounding the pipe, cable or protective tubing the member having the form of a closed ring, e.g. used for the function of two adjacent pipe sections
-
- 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
- F01D25/28—Supporting or mounting arrangements, e.g. for turbine casing
-
- 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
- F01D25/30—Exhaust heads, chambers, or the like
-
- 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
Definitions
- the present invention relates to an air discharge tube support loaded with oil of a turbomachine.
- a turbomachine such as a turbojet engine or a turboprop engine, conventionally comprises, from upstream to downstream in the direction of flow of the gases, a fan, a low pressure compressor, a high pressure compressor, a combustion chamber, a high turbine pressure, a low pressure turbine, and a gas exhaust nozzle.
- Each compressor stage has a turbine stage, both of which are connected by a shaft so as to form a body, in particular a low pressure body and a high pressure body.
- the low pressure body shaft may be hollow and contain a tube, commonly referred to as "Center Vent Tube” or “CVT”.
- This tube comprises an upstream portion rotatable, extended by a fixed downstream portion and allows the discharge of oil-laden air from certain enclosures of the turbomachine.
- the downstream portion of this tube passes through an ejection cone to which it is connected by a support comprising an inner annular portion of general Omega section, surrounding the tube, and a conical portion fixed to the ejection cone and to the inner annular portion. .
- the conical portion has holes for passing a flow of cooling air through the ejection cone.
- the conical portion of the support is attached to the inner annular portion by means of screws.
- the ejection cone is subjected to temperatures between 650 ° C and 680 ° C, while the tube may be at a temperature between 450 ° C and 480 ° C.
- This large temperature difference (240 ° C) generates thermal expansion phenomena, stresses and displacements that the support must be able to absorb while retaining its qualities of rigidity.
- the current support is relatively heavy, which increases the total mass of the turbomachine, in addition to being expensive.
- the invention aims in particular to provide a simple, effective and economical solution to this problem.
- a support intended to carry a tube of air discharge loaded with oil of a turbomachine, comprising a radially inner annular part, intended to be mounted around said tube, characterized in that it comprises fins extending outwardly from the annular portion, said fins being inclined with respect to the axial direction of the annular portion and with respect to the radial plane, the radially outer periphery of the fins being intended to be fixed to a cone of ejection of the turbomachine.
- Such a support has a relatively low weight, is inexpensive, allows the passage of air through the ejection cone, and adequately supports the effects of thermal expansion that may occur in operation, while ensuring its support function. tube.
- such a medium is about five to six times lighter than the current medium.
- the inner annular portion comprises a cylindrical inner ring from which a frustoconical annular cup extends radially outwards, each fin extending outwardly in the extension of said cup.
- the length of the cylindrical inner ring is less than or equal to 0.4 times its internal diameter.
- the cylindrical inner ring is a short guide forming, to a certain extent, a ball joint connection between the tube and the support.
- each fin has an inner periphery connected to the annular portion and a outer periphery comprising an attachment zone to the ejection cone, forming an angle with the rest of the fin.
- each attachment zone has the shape of a cone portion, complementary to the ejection cone.
- the fins and the inner annular portion may be made of nickel-based superalloy, for example INCONEL 625 or INCONEL 718.
- the number of fins is between 3 and 14.
- the invention also relates to an assembly for a turbomachine comprising an air discharge tube loaded with oil from a turbomachine, said tube comprising an upstream portion rotatable and a fixed downstream portion, said downstream portion passing through a cone of ejection and extending along the axis of said ejection cone, said downstream portion being surrounded by the inner annular portion of a support of the aforementioned type, so that said downstream portion is mounted axially free in rotation and in translation in said inner annular portion, the fins of the support being further attached to the ejection cone by their outer periphery.
- the ejection cone comprises at least one annular stiffener, the outer periphery of each fin being fixed to the stiffener.
- the invention finally relates to a turbomachine, characterized in that it comprises an assembly described above.
- FIG. 1 is a perspective view in axial section of part of a current turbine engine
- FIG. 2 is a view in axial section illustrating the mounting of a current support between an ejection cone and an air discharge tube loaded with oil
- FIG. 3 is a perspective view of the assembly of FIG. 2
- FIG. 4 is a perspective view of a support according to a first embodiment of the invention.
- FIG. 5 is a side view of the support of FIG. 4,
- FIG. 6 is a perspective view of the frustoconical cup and fins of the support of FIG. 4;
- FIG. 7 is a perspective view of the cylindrical ring of the support of FIG. 4,
- FIG. 8 is a perspective view, partly broken away, of part of a turbomachine comprising the support of FIG. 4;
- FIG. 9 is a perspective view and part broken away, of a portion of a turbomachine comprising a support according to a second embodiment of the invention.
- FIG. 10 is a detailed view of part of FIG. 9.
- a downstream portion of a current turbine engine is shown in Figure 1 and comprises an ejection cone 1 attached downstream of an exhaust casing 2, itself located downstream of a low-pressure turbine (not shown ).
- the ejection cone 1 has an axial opening 3 at its downstream end.
- the turbomachine also comprises a tube 4 commonly called “Center Vent Tube” or “CVT” which comprises an upstream portion rotatable (not visible), extended by a fixed downstream portion 4a and which allows the discharge of air loaded with oil , from some speakers of the turbomachine.
- CVT Center Vent Tube
- the downstream portion 4a of this tube 4 passes through the ejection cone 1 and opens downstream thereof through the opening 3.
- Said downstream portion 4a is connected to the ejection cone 1 by a support 5.
- the latter is visible in Figure 2 and comprises an inner annular portion 6 of general Omega section, surrounding the tube 4, and a conical portion 7 fixed to the ejection cone 1 and the inner annular portion 6.
- the conical portion 7 comprises holes 8 allowing the passage of a cooling air flow crossing the ejection cone 1.
- the conical portion 7 of the support 5 is fixed to the inner annular portion 6 by means of screws (not shown).
- the invention proposes to connect the downstream part 4a of the tube 4 to the ejection cone 1 by the support 5 illustrated in FIGS. 4 to 8.
- This support 5 is made by assembling a ring cylindrical 9, intended to be mounted around said tube 4, and a frustoconical cup 10 from which fins 1 1 extend.
- the length of the cylindrical ring 9 is less than or equal to 0.4 times its internal diameter.
- the cylindrical ring 9 is a short guide forming, to a certain extent, a ball joint connection between the tube 4 and the support 5.
- the frustoconical cup 10 is fixed in the central zone of the cylindrical ring 9.
- the tube 4 is also mounted free in rotation and in axial translation in the ring 9. These different degrees of freedom can in particular compensate for any deformations in operation, due for example to mechanical and thermal stresses.
- the ring 9 may also comprise chamfers turned radially inwards, at its ends, so as not to damage the tube 4 during assembly of the support 5.
- the assembly represented in FIG. 6, forming the frustoconical cup 10 as well as the fins 1 1, can be obtained by cutting and folding a sheet, before being fixed, for example by soldering, to the cylindrical inner ring 9 shown in Figure 7.
- Each fin 1 1 extends in the extension of the cup 10, outside thereof, and has an inner periphery connected to the cup 10 and an outer periphery comprising a fastening zone 12 to the cone of ejection 1 forming an angle ⁇ with the rest of the fin 1 1.
- Each fixing zone 12 preferably has the shape of a cone portion and is complementary to the inner surface of the ejection cone 1.
- the number of fins 1 1 is for example between 3 and 14.
- the angle a of the cup 10 and fins 1 1 with respect to the axis A of the support 5 is not straight.
- the inclination angle of the fins 1 1 makes it possible to adequately withstand the effects of thermal expansions that may occur during operation, while ensuring the support function of the tube 4.
- the fins 1 1, the frustoconical cup 10 and the cylindrical ring 9 are made of nickel-based superalloy, for example INCONEL 625 (NiCr22Mo9Nb) or INCONEL 718.
- Such a support 5 is relatively light, allows the passage of cooling air between the different fins 1 1 and is inexpensive. By way of comparison, such a support 5 is approximately five to six times lighter than the current support illustrated in FIG.
- Figures 9 and 10 illustrate an alternative embodiment of the invention, wherein the inner wall of the ejection cone 1 comprises annular stiffeners extending radially inwards.
- Each stiffener has an L-shaped section, a branch 13a is fixed for example by welding to the inner wall of the cone 1 and another branch 13b has holes 14 ( Figure 10).
- the support 5 is made by assembling a cylindrical ring 9, intended to be mounted around said tube 4, and a frustoconical cup 10 from which fins 1 1 extend.
- the support 5 of FIGS. 9 and 10 differs from that shown in FIGS. 4 to 8 in that the radially outer periphery of each fin comprises a fastening zone 12 parallel to the flange 13b of the stiffener situated furthest downstream and pressed against the upstream wall of this wing 13b.
- Each attachment zone 12 has a hole 15 disposed opposite a corresponding hole 14.
- holes 14, 15 allow the passage of screws for fixing the support 5 to the stiffener 13, intended to cooperate for example with nuts riveted in the holes 15 of the fins 1 1 of the support 5, or in the holes 14 of the stiffener 13.
Landscapes
- Engineering & Computer Science (AREA)
- General Engineering & Computer Science (AREA)
- Mechanical Engineering (AREA)
- Structures Of Non-Positive Displacement Pumps (AREA)
- Supercharger (AREA)
- Turbine Rotor Nozzle Sealing (AREA)
Abstract
Description
Claims
Priority Applications (7)
Application Number | Priority Date | Filing Date | Title |
---|---|---|---|
BR112015010702-8A BR112015010702B1 (pt) | 2012-11-12 | 2013-11-04 | Suporte destinado a portar um tubo de evacuação de ar, conjunto para uma turbomáquina e turbomáquina |
RU2015122125A RU2646167C2 (ru) | 2012-11-12 | 2013-11-04 | Держатель трубы для отвода воздуха в турбогенераторе |
CA2891072A CA2891072C (fr) | 2012-11-12 | 2013-11-04 | Support de tube d'evacuation d'air dans une turbomachine |
CN201380062481.2A CN104822912B (zh) | 2012-11-12 | 2013-11-04 | 涡轮机中的排气管支架 |
US14/441,964 US9863278B2 (en) | 2012-11-12 | 2013-11-04 | Air exhaust tube holder in a turbomachine |
JP2015541211A JP6251752B2 (ja) | 2012-11-12 | 2013-11-04 | ターボ機械内の排気管用ホルダ |
EP13803104.2A EP2917519B1 (fr) | 2012-11-12 | 2013-11-04 | Support de tube d'évacuation d'air dans une turbomachine |
Applications Claiming Priority (2)
Application Number | Priority Date | Filing Date | Title |
---|---|---|---|
FR1260750A FR2997997B1 (fr) | 2012-11-12 | 2012-11-12 | Support de tube d'evacuation d'air dans une turbomachine |
FR1260750 | 2012-11-12 |
Publications (2)
Publication Number | Publication Date |
---|---|
WO2014072626A2 true WO2014072626A2 (fr) | 2014-05-15 |
WO2014072626A3 WO2014072626A3 (fr) | 2014-07-03 |
Family
ID=47505153
Family Applications (1)
Application Number | Title | Priority Date | Filing Date |
---|---|---|---|
PCT/FR2013/052625 WO2014072626A2 (fr) | 2012-11-12 | 2013-11-04 | Support de tube d'évacuation d'air dans une turbomachine |
Country Status (9)
Country | Link |
---|---|
US (1) | US9863278B2 (fr) |
EP (1) | EP2917519B1 (fr) |
JP (1) | JP6251752B2 (fr) |
CN (1) | CN104822912B (fr) |
BR (1) | BR112015010702B1 (fr) |
CA (1) | CA2891072C (fr) |
FR (1) | FR2997997B1 (fr) |
RU (1) | RU2646167C2 (fr) |
WO (1) | WO2014072626A2 (fr) |
Cited By (2)
Publication number | Priority date | Publication date | Assignee | Title |
---|---|---|---|---|
FR3043138A1 (fr) * | 2015-11-04 | 2017-05-05 | Snecma | Tube de degazage et cone d'ejection pour une turbomachine, ainsi que leur outillage de montage |
EP3196424A4 (fr) * | 2015-01-26 | 2018-05-23 | IHI Corporation | Mécanisme d'alignement de tube de ventilation central et dispositif de support de tube de ventilation central |
Families Citing this family (10)
Publication number | Priority date | Publication date | Assignee | Title |
---|---|---|---|---|
USD777021S1 (en) * | 2014-03-25 | 2017-01-24 | Airbus Defence And Space Limited | Clamp |
EP3017874B2 (fr) | 2014-11-06 | 2022-02-09 | Raytheon Technologies Corporation | Buses de pulvérisation à froid |
US10203114B2 (en) | 2016-03-04 | 2019-02-12 | General Electric Company | Sleeve assemblies and methods of fabricating same |
US10228141B2 (en) | 2016-03-04 | 2019-03-12 | General Electric Company | Fuel supply conduit assemblies |
US20170254540A1 (en) * | 2016-03-04 | 2017-09-07 | General Electric Company | Spacers and conduit assemblies having the same |
FR3064302B1 (fr) * | 2017-03-23 | 2019-06-07 | Safran Aircraft Engines | Appuis centraux de tubes servitude a retour elastique |
US11473431B2 (en) * | 2019-03-12 | 2022-10-18 | Raytheon Technologies Corporation | Energy dissipating damper |
US11028728B2 (en) | 2019-03-22 | 2021-06-08 | Raytheon Technologies Corporation | Strut dampening assembly and method of making same |
FR3121181B1 (fr) * | 2021-03-26 | 2023-09-29 | Safran Aircraft Engines | Tube d’ejection comportant des pattes circonferentielles |
FR3135754A1 (fr) * | 2022-05-18 | 2023-11-24 | Safran Aircraft Engines | Supportage d’un stator d’une machine électrique en aval d’une turbine |
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US20040088989A1 (en) * | 2002-11-07 | 2004-05-13 | Siemens Westinghouse Power Corporation | Variable exhaust struts shields |
EP2085574A1 (fr) * | 2008-01-23 | 2009-08-05 | Snecma | Centrage d'une pièce à l'intérieur d'un arbre |
CH702182A1 (de) * | 2009-11-02 | 2011-05-13 | Alstom Technology Ltd | Gasturbine mit abgasgehäuse sowie verfahren zum herstellen einer solchen gasturbine. |
EP2395214A1 (fr) * | 2010-06-10 | 2011-12-14 | Alstom Technology Ltd | Collecteur de gaz d'échappement pour turbomachine et procédé de production dudit collecteur |
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DE19852603A1 (de) * | 1998-11-14 | 2000-05-18 | Asea Brown Boveri | Verfahren zur Montage eines Abgasgehäuses für eine Wärmekraftmaschine, vorzugsweise eine Gasturbinenanlage |
US7384199B2 (en) * | 2004-08-27 | 2008-06-10 | General Electric Company | Apparatus for centering rotor assembly bearings |
US7464536B2 (en) * | 2005-07-07 | 2008-12-16 | General Electric Company | Methods and apparatus for assembling gas turbine engines |
FR2920194B1 (fr) * | 2007-08-23 | 2014-02-21 | Airbus France | Cone d'ejection des gaz pour turboreacteur d'aeronef equipe d'un dispositif de generation de turbulences de flux primaire limitant le bruit de jet |
US8061983B1 (en) * | 2008-06-20 | 2011-11-22 | Florida Turbine Technoligies, Inc. | Exhaust diffuser strut with stepped trailing edge |
FR2933130B1 (fr) * | 2008-06-25 | 2012-02-24 | Snecma | Carter structural pour turbomachine |
US20110016881A1 (en) * | 2009-07-21 | 2011-01-27 | Jose Luis Ruiz | Gas turbine with exhaust gas casing and method for producing a gas turbine |
DE102011008921A1 (de) * | 2011-01-19 | 2012-07-19 | Rolls-Royce Deutschland Ltd & Co Kg | Gasturbinenabgaskonus |
PL221113B1 (pl) * | 2012-01-25 | 2016-02-29 | Gen Electric | Układy dyfuzora wydechowego turbiny |
FR3042812B1 (fr) * | 2015-10-23 | 2019-06-14 | Safran Aircraft Engines | Tube central de ventilation pre-charge |
-
2012
- 2012-11-12 FR FR1260750A patent/FR2997997B1/fr active Active
-
2013
- 2013-11-04 EP EP13803104.2A patent/EP2917519B1/fr active Active
- 2013-11-04 CA CA2891072A patent/CA2891072C/fr active Active
- 2013-11-04 BR BR112015010702-8A patent/BR112015010702B1/pt active IP Right Grant
- 2013-11-04 CN CN201380062481.2A patent/CN104822912B/zh active Active
- 2013-11-04 JP JP2015541211A patent/JP6251752B2/ja active Active
- 2013-11-04 WO PCT/FR2013/052625 patent/WO2014072626A2/fr active Application Filing
- 2013-11-04 RU RU2015122125A patent/RU2646167C2/ru active
- 2013-11-04 US US14/441,964 patent/US9863278B2/en active Active
Patent Citations (4)
Publication number | Priority date | Publication date | Assignee | Title |
---|---|---|---|---|
US20040088989A1 (en) * | 2002-11-07 | 2004-05-13 | Siemens Westinghouse Power Corporation | Variable exhaust struts shields |
EP2085574A1 (fr) * | 2008-01-23 | 2009-08-05 | Snecma | Centrage d'une pièce à l'intérieur d'un arbre |
CH702182A1 (de) * | 2009-11-02 | 2011-05-13 | Alstom Technology Ltd | Gasturbine mit abgasgehäuse sowie verfahren zum herstellen einer solchen gasturbine. |
EP2395214A1 (fr) * | 2010-06-10 | 2011-12-14 | Alstom Technology Ltd | Collecteur de gaz d'échappement pour turbomachine et procédé de production dudit collecteur |
Cited By (5)
Publication number | Priority date | Publication date | Assignee | Title |
---|---|---|---|---|
EP3196424A4 (fr) * | 2015-01-26 | 2018-05-23 | IHI Corporation | Mécanisme d'alignement de tube de ventilation central et dispositif de support de tube de ventilation central |
US10557351B2 (en) | 2015-01-26 | 2020-02-11 | Ihi Corporation | Center vent tube aligning mechanism and center vent tube support device |
FR3043138A1 (fr) * | 2015-11-04 | 2017-05-05 | Snecma | Tube de degazage et cone d'ejection pour une turbomachine, ainsi que leur outillage de montage |
WO2017077219A1 (fr) * | 2015-11-04 | 2017-05-11 | Safran Aircraft Engines | Tube de degazage et cone d'ejection pour une turbomachine, ainsi que leur outillage de montage |
US11306679B2 (en) | 2015-11-04 | 2022-04-19 | Safran Aircraft Engines | Degassing tube and ejection cone for a turbine engine, as well as tool for assembly thereof |
Also Published As
Publication number | Publication date |
---|---|
JP6251752B2 (ja) | 2017-12-20 |
US9863278B2 (en) | 2018-01-09 |
US20150300206A1 (en) | 2015-10-22 |
EP2917519B1 (fr) | 2018-08-15 |
BR112015010702A2 (pt) | 2017-07-11 |
FR2997997B1 (fr) | 2014-12-26 |
CN104822912A (zh) | 2015-08-05 |
EP2917519A2 (fr) | 2015-09-16 |
CA2891072A1 (fr) | 2014-05-15 |
FR2997997A1 (fr) | 2014-05-16 |
CA2891072C (fr) | 2020-12-01 |
CN104822912B (zh) | 2018-07-27 |
RU2015122125A (ru) | 2017-01-10 |
JP2015535048A (ja) | 2015-12-07 |
WO2014072626A3 (fr) | 2014-07-03 |
BR112015010702B1 (pt) | 2021-08-03 |
RU2646167C2 (ru) | 2018-03-01 |
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