EP3990753B1 - Turbomachine end bearing support - Google Patents
Turbomachine end bearing support Download PDFInfo
- Publication number
- EP3990753B1 EP3990753B1 EP20742352.6A EP20742352A EP3990753B1 EP 3990753 B1 EP3990753 B1 EP 3990753B1 EP 20742352 A EP20742352 A EP 20742352A EP 3990753 B1 EP3990753 B1 EP 3990753B1
- Authority
- EP
- European Patent Office
- Prior art keywords
- wall
- support
- bearing support
- turbomachine
- axial direction
- 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.)
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- 238000004519 manufacturing process Methods 0.000 claims description 12
- 239000000654 additive Substances 0.000 claims description 6
- 230000000996 additive effect Effects 0.000 claims description 6
- 239000003921 oil Substances 0.000 description 20
- 238000010079 rubber tapping Methods 0.000 description 8
- 239000007789 gas Substances 0.000 description 7
- 239000012530 fluid Substances 0.000 description 4
- 230000005484 gravity Effects 0.000 description 3
- 238000003754 machining Methods 0.000 description 3
- 238000000034 method Methods 0.000 description 3
- 239000000843 powder Substances 0.000 description 2
- 238000011084 recovery Methods 0.000 description 2
- 238000011144 upstream manufacturing Methods 0.000 description 2
- 230000015572 biosynthetic process Effects 0.000 description 1
- 238000006243 chemical reaction Methods 0.000 description 1
- 238000002485 combustion reaction Methods 0.000 description 1
- 238000004891 communication Methods 0.000 description 1
- 230000001788 irregular Effects 0.000 description 1
- 239000010687 lubricating oil Substances 0.000 description 1
- 239000000463 material Substances 0.000 description 1
- 238000012986 modification Methods 0.000 description 1
- 230000004048 modification Effects 0.000 description 1
- 238000005245 sintering Methods 0.000 description 1
Images
Classifications
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- 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
- F01D25/162—Bearing supports
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- 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
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- 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
- F01D25/24—Casings; Casing parts, e.g. diaphragms, casing fastenings
-
- 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
- F01D25/24—Casings; Casing parts, e.g. diaphragms, casing fastenings
- F01D25/243—Flange connections; Bolting arrangements
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- 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
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- 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
- F05D2230/30—Manufacture with deposition of material
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- 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
- F05D2230/30—Manufacture with deposition of material
- F05D2230/31—Layer deposition
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- 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
- F05D2230/50—Building or constructing in particular ways
- F05D2230/53—Building or constructing in particular ways by integrally manufacturing a component, e.g. by milling from a billet or one piece construction
-
- 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
- F05D2240/50—Bearings
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- 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
- F05D2260/98—Lubrication
Definitions
- the invention relates to a turbomachine output bearing support.
- turbomachine designates all the gas turbine devices producing motive power, among which a distinction is made in particular between turbojet engines providing the thrust necessary for propulsion by reaction to the high-speed ejection of hot gases, and turboshaft engines in which the motive power is provided by the rotation of a motor shaft.
- turbine engines are used as an engine for helicopters, ships, trains, or even as an industrial engine.
- Turboprops are also turboshaft engines used as an aircraft engine.
- the turbomachine output bearing is the last bearing of the turbomachine considered in the direction of gas flow within the turbomachine, from upstream to downstream, carrying one or more rotor shafts of the turbomachine.
- Known turbomachine output bearing supports are generally complex parts comprising several parts machined separately and then assembled together, in particular by bolting. Such a manufacturing process is complex and expensive. Moreover, assembly by bolting makes these known bearing supports relatively heavy parts. So there is a need for that.
- the invention relates to a turbomachine output bearing support according to claim 1.
- support means “turbomachine output bearing support”.
- a swirl is an element known moreover by those skilled in the art which makes it possible to prevent oil leaks from a bearing.
- the axial direction is defined by a geometric axis of the support, for example an axis of symmetry of revolution.
- a radial direction is a direction perpendicular to the axial direction.
- the azimuthal or circumferential direction corresponds to the direction describing a ring around the axial direction.
- the three directions axial, radial and azimuthal correspond respectively to the directions defined by the coast, the radius and the angle in a cylindrical coordinate system.
- the adjectives "inner/internal” and "outer/external” are used in reference to a radial direction so that the inner part (i.e. radially inner) of an element is closer to the axis defining the axial direction than the outer part (i.e. radially outer) of the same element.
- outer and inner walls are annular and that the outer wall is arranged on the outer side of the inner wall.
- the support By forming the support in one and the same piece, for example by additive manufacturing, it is possible to eliminate the assembly elements of the supports known from the state of the art. Moreover, by forming the support in one and the same piece, it is possible to dispense with certain parts of the supports known from the state of the art, and to integrate them altogether or to start with the internal wall and/or the wall external and/or the auger support. This also makes it possible to avoid certain complex machining operations necessary in the supports known from the state of the art.
- the inner wall comprises a first portion having a first substantially frustoconical shape (ie diverging annular shape) extending in the axial direction and having the inner side and the outer side, the first portion having a first axial end provided with a first flange fixing and a second axial end, opposite in the axial direction to the first axial end, provided with a bearing support portion, the first portion bearing on the internal side an internal portion forming a second fixing flange.
- a first substantially frustoconical shape ie diverging annular shape
- substantially frustoconical or “divergent annular shape” is meant a regular frustoconical shape (i.e. of constant angle with respect to the axial direction), an irregular frustoconical shape (i.e. of constant angle in portions along the axial direction, different from one portion to another), a concave (for example in the shape of a bell) or convex (for example in the shape of a trumpet bell), a combination of the aforementioned shapes, or more generally any annular geometry connecting a first axial end having a first diameter to a second axial end having a second diameter larger than the first diameter.
- the auger support is carried by the inner wall on the outer side.
- the auger support extends from the outer side of the inner wall.
- the auger support is disposed between the inner wall and the outer wall.
- the outer wall has a second substantially frustoconical shape (i.e. divergent annular shape) extending in the axial direction and having a third axial end connected to the inner wall on the outer side of the inner wall, and a fourth axial end, opposite the second axial end in the axial direction, forming a collector ring.
- a second substantially frustoconical shape i.e. divergent annular shape
- the outer wall extends from the outer side of the inner wall.
- the inner wall and the outer wall are coaxial.
- the auger support may be coaxial with the inner wall and the outer wall.
- the collector ring can be an annular portion configured to collect/exhaust a pressurized fluid, for example gas, from the interior side of the external wall.
- a cavity is formed between the outer wall and the auger support, the collector ring being configured to evacuate a pressurized fluid into this cavity.
- the collector ring may form an annular chamber having one or more radial openings in fluid communication with the interior of the support.
- the turbomachine output bearing support comprises at least one air evacuation channel extending from the outer side of the outer wall and fluidly connecting the inner side of the inner wall and the collector ring.
- the air evacuation channel makes it possible to evacuate gases collected in the collector ring towards the interior side of the internal wall.
- the evacuation channel can also extend on the outer side of the inner wall.
- the outer wall and/or the inner wall form at least a portion of the walls forming the air evacuation channel.
- such a channel makes it possible in particular to do away with additional walls that are much more cumbersome and heavy, and therefore to significantly reduce the mass of the support.
- the turbomachine output bearing support comprises three air evacuation channels regularly distributed around the axial direction.
- Such a configuration makes it possible to ensure a homogeneous evacuation of air and to distribute the mass evenly over the circumference of the support.
- the at least one air evacuation channel has an air outlet opening formed in the internal wall.
- the turbomachine output bearing support includes an oil drain channel.
- Such a drainage channel makes it possible to collect lubricating oil from the bearing which escapes from the oil circuit of the bearing.
- a drainage channel is distinct from an oil recovery channel of the oil circuit of the bearing.
- the oil drain channel can be configured to drain oil by gravity.
- the bearing support may have a top and a bottom, the drainage channel being placed on the side of the bottom of the support.
- the drainage channel can define the low side of the support.
- the oil drain channel extends from the exterior side of the outer wall and has a first inlet in the collector ring, a second inlet in the outer wall and opening into a space formed between the auger support and the outer wall, and an outlet emerging from the inner side of the inner wall.
- the drainage channel can also extend on the outer side of the inner wall.
- the outer wall and/or the inner wall form at least a portion of the walls forming the drainage channel.
- One embodiment also relates to a method of manufacturing a turbomachine output bearing support according to any one of the embodiments described in the present disclosure, comprising at least one additive manufacturing step.
- additive manufacturing is a manufacturing process by adding material, by stacking successive layers.
- the successive layers are formed by powder, the powder being selectively sintered by laser.
- Such a manufacturing method is particularly well suited for manufacturing complex parts, such as the turbomachine output bearing support which is the subject of the present presentation. This makes it possible in particular to avoid certain complex machining steps which are necessary in the supports of the state of the art.
- FIG. 1 represents a schematic view of a turbomachine 100, in this example a two-spool turbojet, comprising a turbomachine output bearing support 10.
- the turbomachine 100 comprises a casing 110 housing a low pressure body 120, a high body pressure 140 and a combustion chamber 160.
- the low pressure body 120 comprises a low pressure compressor 120A and a low pressure turbine 120B coupled in rotation by a shaft 120C.
- the high pressure body 140 comprises a high pressure compressor 140A and a high pressure turbine 140B coupled in rotation by a shaft 140C.
- Shaft 120C is coaxial with shaft 140C, and extends through shaft 140C.
- the shafts 120C and 140C are rotatable around the axis X of the turbomachine.
- the turbomachine output bearing support 10 extends along the axial direction X, and is coaxial with the shafts 120C and 140C.
- the support 10 supports the bearing of the shaft 120C arranged on the side of the outlet S of the turbine engine 100, the gases flowing within the turbine engine 100 from upstream to downstream from the inlet E to exit S according to the arrow in bold.
- the turbomachine output bearing support 10 is described in more detail with reference to the figure 2 , 3 , 4 And 5 . Note that only the support 10 is shown in these figures. In particular, the bearing and the swirl which are carried by this support 10 are not represented.
- the support 10 extends along the axial direction X, along a radial direction R and a circumferential direction C.
- the support 10 is formed in one and the same piece by additive manufacturing and comprises an internal wall 12, an external wall 14 and an auger support 16.
- the internal wall 12 has an internal side Cl and an external side CE
- the inner wall 12 comprises a first portion 12A having a first substantially frustoconical shape extending in the axial direction X and having the inner side CI and the outer side CE, the first portion 12A having a first axial end 12A1 provided with a first fixing flange 18 and a second axial end 12A2, opposite in the axial direction X to the first axial end 12A1, provided with a bearing support portion 20, the first portion 12A bearing on the internal side Cl an internal portion 22 forming a second clamp.
- the internal portion 22 comprises a web 22A extending in the axial direction X and connected to the first portion 12A, on the internal side Cl.
- the web 22A carries a portion 22B forming a fastening flange.
- the diameter of the second flange 22 is smaller than the diameter of the first flange 18.
- the second flange 22 is set back in the axial direction X with respect to the first flange 18, inside the internal wall 12.
- the veil 22A has a third substantially frustoconical shape with axis X (the second substantially frustoconical shape being formed by the second wall described in more detail below) and of opposite inclination with respect to the inclination of the first portion 12A.
- the first portion 12A has on the internal side Cl a cylindrical portion 24 of axis X and of transverse section in the circular axial direction.
- the cylindrical portion 24 is disposed radially between the internal portion 22 and the first flange 18.
- the distal end of the portion 24 is set back in the axial direction X of the flange-forming portion 22B, inside the internal wall 12.
- the portion 24 is configured to attach an oil inlet cover thereto, for example by sintering. A seal may also be placed between said cover and portion 24.
- the first portion 12A has through holes 23A arranged radially between the bearing support portion 20 and the internal portion 22 and through holes 23B arranged radially between the internal portion 22 and the cylindrical portion 24. These holes 23A and 23B are regularly distributed along the circumferential direction C. These holes 23A and 23B form passages for the flow of oil from the bearing, not shown, carried by the bearing support 10.
- the auger support 16 is carried by the inner wall 12, on the outer side CE.
- the auger support 16 has a veil 16A extending along the axial direction X and connected to the first portion 12A, on the external side CE.
- the veil 16A carries a portion forming a twist support 16B.
- the diameter of the auger support portion 16B is smaller than the diameter of the bearing support portion 20.
- the auger support portion 16B is disposed beyond the bearing support portion 20 in the direction axial X, on the outer side of the inner wall 12.
- the veil 16A has a fourth substantially frustoconical shape with axis X inclined on the same side with respect to the axial direction as the first portion 12A.
- the outer wall 14 has a second substantially frustoconical shape extending in the axial direction X and having a third axial end 14A connected to the inner wall 12 on the outer side CE of the inner wall 12, and a fourth axial end 14B, opposite the second axial end 14A in the axial direction X, forming a collector ring 26.
- the substantially frustoconical shape of the outer wall 14 is inclined on the same side relative to the axial direction X as the first portion 12A.
- first, second, third and fourth substantially frustoconical shapes are all different. According to a variant, some of these shapes, or even all of these shapes, could be identical (for example all regular truncated cones, but of different sizes).
- the collector ring 26 is an annular portion forming an annular chamber having several radial openings 26A facing the inside of the bearing support 10 and regularly distributed along the circumferential direction C.
- a cavity 30 is formed between the outer wall 14 and the auger support 16, the collector ring 26 being configured to evacuate a pressurized fluid, in this example gas, from this cavity 30.
- the collector ring 26 is fluidically connected to the inner side C1 of the inner wall 12 via air evacuation channels 32.
- air evacuation channels 32 there are three air evacuation channels 32 regularly distributed around the direction axial X (ie the channels 32 are spaced apart by 120° in the direction circumferential C).
- Each channel 32 has an air outlet opening 32A made in the internal wall 12.
- the outer wall 14 forms a portion of the walls of each air exhaust channel 32.
- the support 10 has in this example three tappings 34, 36 and 38 for a fluidic connection of the support 10 to an oil supply circuit of the bearing.
- the taps 34, 36 and 38 are arranged on the internal side CI of the internal wall 12.
- the tapping 34 is an oil supply tapping connected to an oil supply pipe 33 partly visible on the figure 2 , and opening into the bearing support portion 20 via the orifice 33A.
- the pipe 33 is formed in the thickness of the internal wall 12, and more particularly in this example of the first portion 12A.
- the support 10 being formed from a single piece by additive manufacturing, the formation of this conduit 33 is facilitated and makes it possible to avoid the complex machining operations necessary in the supports known from the state of the art.
- the tapping 36 is an oil recovery tapping connected to a manifold 37 arranged between the external wall 14, the internal wall 12 and the auger support 16.
- the manifold 37 has a wall 37A extending radially between the auger support 16, in this example the veil 16A, the external wall 14, and the internal wall 12.
- the collector 37 has an opening 37B made in the auger support 16, in this example the veil 16A.
- a through hole 23A is arranged plumb, considered along the radial direction R, of the opening 37B.
- the tapping 38 is an oil drainage tapping connected to an oil drainage channel 40.
- the oil drainage channel 40 extends from the exterior side of the outer wall 14 and has a first inlet 42 provided in the collector ring 26, a second inlet 44 made in the outer wall 14 and opening into the space 30 formed between the auger support 16 and the outer wall 14.
- the tapping 38 forms the outlet of the pipe 40 which emerges from the inner side Cl of the inner wall 12.
- Wall external 14 and internal wall 12 each form a portion of the wall of the drainage channel 40.
- the second inlet 44 comprises two through holes 44A made in the outer wall 14, on either side in the circumferential direction C of the collector 37, and adjacent to the collector 37 (see figure 5 ).
- the drainage channel 40 defines the bottom B of the support 10, the top H being diametrically opposed.
- the support 10 is configured to be mounted within the turbomachine 100, with the top H and the bottom B considered as such (i.e. the top above the bottom and vice versa) according to the direction of gravity G, in normal operation of the turbomachine 100.
- the drainage of the oil is thus carried out by gravity.
- the drainage channel 40 is arranged diametrically opposite an air exhaust channel 32, and equidistant in the circumferential direction C from the other two air exhaust channels 32.
- the air circulating via the holes 23B possibly containing oil, this oil is drained by the drainage channel 40 via the second inlet 44.
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- Engineering & Computer Science (AREA)
- Mechanical Engineering (AREA)
- General Engineering & Computer Science (AREA)
- Structures Of Non-Positive Displacement Pumps (AREA)
- Sliding-Contact Bearings (AREA)
- Support Of The Bearing (AREA)
Description
L'invention concerne un support de palier de sortie de turbomachine.The invention relates to a turbomachine output bearing support.
Le terme « turbomachine » désigne l'ensemble des appareils à turbine à gaz produisant une énergie motrice, parmi lesquels on distingue notamment les turboréacteurs fournissant une poussée nécessaire à la propulsion par réaction à l'éjection à grande vitesse de gaz chauds, et les turbomoteurs dans lesquels l'énergie motrice est fournie par la rotation d'un arbre moteur. Par exemple, des turbomoteurs sont utilisés comme moteur pour des hélicoptères, des navires, des trains, ou encore comme moteur industriel. Les turbopropulseurs (turbomoteur entrainant une hélice) sont également des turbomoteurs utilisés comme moteur d'avion.The term "turbomachine" designates all the gas turbine devices producing motive power, among which a distinction is made in particular between turbojet engines providing the thrust necessary for propulsion by reaction to the high-speed ejection of hot gases, and turboshaft engines in which the motive power is provided by the rotation of a motor shaft. For example, turbine engines are used as an engine for helicopters, ships, trains, or even as an industrial engine. Turboprops (turbomotor driving a propeller) are also turboshaft engines used as an aircraft engine.
Le palier de sortie de turbomachine est le dernier palier de la turbomachine considéré dans le sens de l'écoulement des gaz au sein de la turbomachine, de l'amont vers l'aval, portant un ou plusieurs arbres de rotor de la turbomachine.The turbomachine output bearing is the last bearing of the turbomachine considered in the direction of gas flow within the turbomachine, from upstream to downstream, carrying one or more rotor shafts of the turbomachine.
Le document
Les supports de palier de sortie de turbomachine connus sont des pièces généralement complexes comprenant plusieurs parties usinées séparément et assemblées ensuite entre elles, notamment par boulonnage. Un tel procédé de fabrication est complexe et couteux. Par ailleurs, l'assemblage par boulonnage fait de ces supports de paliers connus des pièces relativement lourdes. Il existe donc un besoin en ce sens.Known turbomachine output bearing supports are generally complex parts comprising several parts machined separately and then assembled together, in particular by bolting. Such a manufacturing process is complex and expensive. Moreover, assembly by bolting makes these known bearing supports relatively heavy parts. So there is a need for that.
L'invention concerne un support de palier de sortie de turbomachine selon la revendication 1.The invention relates to a turbomachine output bearing support according to claim 1.
Par la suite et sauf indication contraire, par « support », on entend « support de palier de sortie de turbomachine ». Une vrille est un élément connu par ailleurs par l'homme du métier qui permet d'éviter des fuites d'huile d'un palier.Hereafter and unless otherwise indicated, the term “support” means “turbomachine output bearing support”. A swirl is an element known moreover by those skilled in the art which makes it possible to prevent oil leaks from a bearing.
La direction axiale est définie par un axe géométrique du support, par exemple un axe de symétrie de révolution. Une direction radiale est une direction perpendiculaire à la direction axiale. La direction azimutale ou circonférentielle correspond à la direction décrivant un anneau autour de la direction axiale. Les trois directions axiale, radiale et azimutale correspondent respectivement aux directions définies par la côte, le rayon et l'angle dans un système de coordonnées cylindrique. Par ailleurs, sauf précision contraire, les adjectifs « intérieur/interne » et « extérieur/externe » sont utilisés en référence à une direction radiale de sorte que la partie intérieure (i.e. radialement intérieure) d'un élément est plus proche de l'axe définissant la direction axiale que la partie extérieure (i.e. radialement extérieure) du même élément.The axial direction is defined by a geometric axis of the support, for example an axis of symmetry of revolution. A radial direction is a direction perpendicular to the axial direction. The azimuthal or circumferential direction corresponds to the direction describing a ring around the axial direction. The three directions axial, radial and azimuthal correspond respectively to the directions defined by the coast, the radius and the angle in a cylindrical coordinate system. Furthermore, unless otherwise specified, the adjectives "inner/internal" and "outer/external" are used in reference to a radial direction so that the inner part (i.e. radially inner) of an element is closer to the axis defining the axial direction than the outer part (i.e. radially outer) of the same element.
On comprend que les parois externe et interne sont annulaires et que la paroi externe est disposée du côté externe de la paroi interne.It is understood that the outer and inner walls are annular and that the outer wall is arranged on the outer side of the inner wall.
En formant le support d'une seule et même pièce, par exemple par fabrication additive, on peut supprimer les éléments d'assemblages des supports connus de l'état de la technique. Par ailleurs, en formant le support d'une seule et même pièce, on peut s'affranchir de certaines parties des supports connus de l'état de la technique, et les intégrer en tout ou partir avec la paroi interne et/ou la paroi externe et/ou le support de vrille. Ceci permet également d'éviter certains usinages complexes nécessaires dans les supports connus de l'état de la technique.By forming the support in one and the same piece, for example by additive manufacturing, it is possible to eliminate the assembly elements of the supports known from the state of the art. Moreover, by forming the support in one and the same piece, it is possible to dispense with certain parts of the supports known from the state of the art, and to integrate them altogether or to start with the internal wall and/or the wall external and/or the auger support. This also makes it possible to avoid certain complex machining operations necessary in the supports known from the state of the art.
La paroi interne comprend une première portion présentant une première forme sensiblement tronconique (i.e. forme annulaire divergente) s'étendant selon la direction axiale et présentant le côté interne et le côté externe, la première portion présentant une première extrémité axiale pourvue d'une première bride de fixation et une deuxième extrémité axiale, opposée selon la direction axiale à la première extrémité axiale, pourvue d'une portion de support de palier, la première portion portant du côté interne une portion interne formant une seconde bride de fixation.The inner wall comprises a first portion having a first substantially frustoconical shape (ie diverging annular shape) extending in the axial direction and having the inner side and the outer side, the first portion having a first axial end provided with a first flange fixing and a second axial end, opposite in the axial direction to the first axial end, provided with a bearing support portion, the first portion bearing on the internal side an internal portion forming a second fixing flange.
Par « sensiblement tronconique » ou « forme annulaire divergente » on entend une forme tronconique régulière (i.e. d'angle constant par rapport à la direction axiale), une forme tronconique irrégulière (i.e. d'angle constant par portions le long de la direction axiale, différent d'une portion à l'autre), une forme courbe concave (par exemple en forme de cloche) ou convexe (par exemple en forme de pavillon de trompette), une combinaison des formes précitées, ou plus généralement toute géométrie annulaire reliant une première extrémité axiale ayant un premier diamètre à une deuxième extrémité axiale ayant un deuxième diamètre plus grand que le premier diamètre.By “substantially frustoconical” or “divergent annular shape” is meant a regular frustoconical shape (i.e. of constant angle with respect to the axial direction), an irregular frustoconical shape (i.e. of constant angle in portions along the axial direction, different from one portion to another), a concave (for example in the shape of a bell) or convex (for example in the shape of a trumpet bell), a combination of the aforementioned shapes, or more generally any annular geometry connecting a first axial end having a first diameter to a second axial end having a second diameter larger than the first diameter.
Le support de vrille est porté par la paroi interne du côté externe.The auger support is carried by the inner wall on the outer side.
En d'autres termes, le support de vrille s'étend depuis le côté extérieur de la paroi interne. Par exemple, le support de vrille est disposé entre la paroi interne et la paroi externe.In other words, the auger support extends from the outer side of the inner wall. For example, the auger support is disposed between the inner wall and the outer wall.
Dans certains modes de réalisation, la paroi externe présente une deuxième forme sensiblement tronconique (i.e. forme annulaire divergente) s'étendant selon la direction axiale et présentant une troisième extrémité axiale raccordée à la paroi interne du côté externe de la paroi interne, et une quatrième extrémité axiale, opposé à la deuxième extrémité axiale selon la direction axiale, formant un anneau collecteur.In some embodiments, the outer wall has a second substantially frustoconical shape (i.e. divergent annular shape) extending in the axial direction and having a third axial end connected to the inner wall on the outer side of the inner wall, and a fourth axial end, opposite the second axial end in the axial direction, forming a collector ring.
En d'autres termes, la paroi externe s'étend depuis le côté extérieur de la paroi interne. La paroi interne et la paroi externe sont coaxiales. Le support de vrille peut être coaxial avec la paroi interne et la paroi externe.In other words, the outer wall extends from the outer side of the inner wall. The inner wall and the outer wall are coaxial. The auger support may be coaxial with the inner wall and the outer wall.
L'anneau collecteur peut être une portion annulaire configurée pour collecter/évacuer un fluide sous pression, par exemple du gaz, depuis le côté intérieur de la paroi externe. Par exemple, une cavité est formée entre la paroi extérieure et le support de vrille, l'anneau collecteur étant configuré pour évacuer un fluide sous pression dans cette cavité. Par exemple, l'anneau collecteur peut former une chambre annulaire présentant une ou plusieurs ouvertures radiales en communication fluidique avec l'intérieur du support.The collector ring can be an annular portion configured to collect/exhaust a pressurized fluid, for example gas, from the interior side of the external wall. For example, a cavity is formed between the outer wall and the auger support, the collector ring being configured to evacuate a pressurized fluid into this cavity. For example, the collector ring may form an annular chamber having one or more radial openings in fluid communication with the interior of the support.
Dans certains modes de réalisation, le support de palier de sortie de turbomachine comprend aux moins un canal d'évacuation d'air s'étendant du côté extérieur de la paroi externe et reliant fluidiquement le côté intérieur de la paroi interne et l'anneau collecteur.In certain embodiments, the turbomachine output bearing support comprises at least one air evacuation channel extending from the outer side of the outer wall and fluidly connecting the inner side of the inner wall and the collector ring.
Le canal d'évacuation d'air permet d'évacuer des gaz collectés dans l'anneau collecteur vers le côté intérieure de la paroi interne. Par exemple, le canal d'évacuation peut s'étendre aussi sur le côté extérieur de la paroi interne. Par exemple, la paroi externe et/ou la paroi interne forment au moins une portion des parois formant le canal d'évacuation d'air.The air evacuation channel makes it possible to evacuate gases collected in the collector ring towards the interior side of the internal wall. For example, the evacuation channel can also extend on the outer side of the inner wall. For example, the outer wall and/or the inner wall form at least a portion of the walls forming the air evacuation channel.
Comparativement aux supports de l'état de la technique, un tel canal permet notamment de s'affranchir de parois additionnelles bien plus encombrantes et lourdes, et donc de réduire significativement la masse du support.Compared to the supports of the state of the art, such a channel makes it possible in particular to do away with additional walls that are much more cumbersome and heavy, and therefore to significantly reduce the mass of the support.
Dans certains modes de réalisation, le support de palier de sortie de turbomachine comprend trois canaux d'évacuation d'air régulièrement répartis autour de la direction axiale.In certain embodiments, the turbomachine output bearing support comprises three air evacuation channels regularly distributed around the axial direction.
Une telle configuration permet d'assurer une évacuation d'air homogène et de répartir la masse régulièrement sur la circonférence du support.Such a configuration makes it possible to ensure a homogeneous evacuation of air and to distribute the mass evenly over the circumference of the support.
Dans certains modes de réalisation, le au moins un canal d'évacuation d'air présente une ouverture de sortie d'air ménagée dans la paroi interne.In certain embodiments, the at least one air evacuation channel has an air outlet opening formed in the internal wall.
Dans certains modes de réalisation, le support de palier de sortie de turbomachine comprend un canal de drainage d'huile.In some embodiments, the turbomachine output bearing support includes an oil drain channel.
Un tel canal de drainage permet de collecter de l'huile de lubrification du palier qui s'échappe du circuit d'huile du palier. Un tel canal de drainage est distinct d'un canal de récupération d'huile du circuit d'huile du palier. Par exemple, le canal de drainage d'huile peut être configuré pour drainer l'huile par gravité. Par exemple, le support de palier peut présenter un haut et un bas, le canal de drainage étant disposé du côté du bas du support. Par exemple, le canal de drainage peut définir le côté bas du support.Such a drainage channel makes it possible to collect lubricating oil from the bearing which escapes from the oil circuit of the bearing. Such a drainage channel is distinct from an oil recovery channel of the oil circuit of the bearing. For example, the oil drain channel can be configured to drain oil by gravity. For example, the bearing support may have a top and a bottom, the drainage channel being placed on the side of the bottom of the support. For example, the drainage channel can define the low side of the support.
Dans certains modes de réalisation, le canal de drainage d'huile s'étend du côté extérieur de la paroi externe et présente une première entrée ménagée dans l'anneau collecteur, une deuxième entrée ménagée dans la paroi externe et s'ouvrant dans espace formée entre le support de vrille et la paroi externe, et une sortie débouchant du côté intérieur de la paroi interne.In some embodiments, the oil drain channel extends from the exterior side of the outer wall and has a first inlet in the collector ring, a second inlet in the outer wall and opening into a space formed between the auger support and the outer wall, and an outlet emerging from the inner side of the inner wall.
Par exemple, le canal de drainage peut s'étendre aussi sur le côté extérieur de la paroi interne. Par exemple, la paroi externe et/ou la paroi interne forment au moins une portion des parois formant le canal de drainage. Comparativement aux supports de l'état de la technique, un tel canal permet notamment de s'affranchir de parois additionnelles lourdes et encombrantes, et donc de réduire significativement la masse du support.For example, the drainage channel can also extend on the outer side of the inner wall. For example, the outer wall and/or the inner wall form at least a portion of the walls forming the drainage channel. Compared to the supports of the state of the art, such a channel makes it possible in particular to dispense with heavy and cumbersome additional walls, and therefore to significantly reduce the mass of the support.
Un mode de réalisation concerne également un procédé de fabrication d'un support de palier de sortie de turbomachine selon l'un quelconque des modes de réalisation décrits dans le présent exposé, comprenant au moins une étape de fabrication additive.One embodiment also relates to a method of manufacturing a turbomachine output bearing support according to any one of the embodiments described in the present disclosure, comprising at least one additive manufacturing step.
Pour rappel, une fabrication additive est un procédé de fabrication par ajout de matière, par empilement de couches successives. Par exemple, les couches successives sont formées par de la poudre, la poudre étant frittée sélectivement par laser.As a reminder, additive manufacturing is a manufacturing process by adding material, by stacking successive layers. For example, the successive layers are formed by powder, the powder being selectively sintered by laser.
Un tel procédé de fabrication est particulièrement bien adapté pour fabriquer des pièces complexes, telles que le support de palier de sortie de turbomachine objet du présent exposé. Ceci permet notamment d'éviter certaines étapes d'usinage complexes qui sont nécessaires dans les supports de l'état de la technique.Such a manufacturing method is particularly well suited for manufacturing complex parts, such as the turbomachine output bearing support which is the subject of the present presentation. This makes it possible in particular to avoid certain complex machining steps which are necessary in the supports of the state of the art.
L'objet du présent exposé et ses avantages seront mieux compris à la lecture de la description détaillée faite ci-après de différents modes de réalisation donnés à titre d'exemples non limitatifs. Cette description fait référence aux pages de figures annexées, sur lesquelles :
- [
Fig. 1 ] Lafigure 1 représente une turbomachine, - [
Fig. 2 ] Lafigure 2 représente le support de palier de sortie de la turbomachine de lafigure 1 , en perspective, - [
Fig. 3 ] Lafigure 3 représente le support de palier de sortie de la turbomachine de lafigure 1 , selon une autre vue en perspective, - [
Fig. 4 ] Lafigure 4 représente le support de palier de sortie de la turbomachine vu selon le plan de coupe IV de lafigure 3 , et - [
Fig.5 ] Lafigure 5 représente le support de palier de sortie de la turbomachine vu selon le plan V de lafigure 4 .
- [
Fig. 1 ] Therefigure 1 represents a turbomachine, - [
Fig. 2 ] Therefigure 2 represents the turbine engine output bearing support of thefigure 1 , in perspective, - [
Fig. 3 ] Therepicture 3figure 1 , according to another perspective view, - [
Fig. 4 ] Therefigure 4 represents the turbomachine output bearing support seen according to section plan IV of thepicture 3 - [
Fig.5 ] Therefigure 5 represents the turbine engine output bearing support seen along plane V of thefigure 4 .
La
Le support de palier de sortie de turbomachine 10 s'étend selon la direction axiale X, et est coaxial avec les arbres 120C et 140C. Dans cet exemple, le support 10 supporte le palier de l'arbre 120C disposé du côté de la sortie S de la turbomachine 100, les gaz s'écoulant au sein de la turbomachine 100 de l'amont vers l'aval depuis l'entrée E vers la sortie S selon la flèche en gras.The turbomachine
Le support de palier de sortie de turbomachine 10 est décrit plus en détail en référence aux
Le support 10 est formé d'une seule et même pièce par fabrication additive et comprend une paroi interne 12, une paroi externe 14 et un support de vrille 16. La paroi interne 12 présente un côté interne Cl et un côté externe CEThe
La paroi interne 12 comprend une première portion 12A présentant une première forme sensiblement tronconique s'étendant selon la direction axiale X et présentant le côté interne CI et le côté externe CE, la première portion 12A présentant une première extrémité axiale 12A1 pourvue d'une première bride de fixation 18 et une deuxième extrémité axiale 12A2, opposée selon la direction axiale X à la première extrémité axiale 12A1, pourvue d'une portion de support de palier 20, la première portion 12A portant du côté interne Cl une portion interne 22 formant une seconde bride de fixation. Dans cet exemple, la portion interne 22 comprend un voile 22A s'étendant selon la direction axiale X et raccordé à la première portion 12A, du côté interne Cl. Le voile 22A porte une portion formant bride de fixation 22B. Dans cet exemple, le diamètre de la seconde bride 22 est inférieur au diamètre de la première bride 18. La seconde bride 22 est disposée en retrait selon la direction axiale X par rapport à la première bride 18, à l'intérieur de la paroi interne 12. Dans cet exemple, le voile 22A présente une troisième forme sensiblement tronconique d'axe X (la deuxième forme sensiblement tronconique étant formée par la deuxième paroi décrite plus en détail ci-après) et d'inclinaison opposée par rapport à l'inclinaison de la première portion 12A.The
Dans cet exemple, la première portion 12A présente du côté interne Cl une portion cylindrique 24 d'axe X et de section transverse à la direction axiale circulaire. La portion cylindrique 24 est disposée radialement entre la portion interne 22 et la première bride 18. L'extrémité distale de la portion 24 est disposée en retrait selon la direction axiale X de la portion formant bride 22B, à l'intérieur de la paroi interne 12. La portion 24 est configurée pour y fixer un couvercle d'arrivée d'huile, par exemple par frittage. Un joint d'étanchéité peut également être disposé entre ledit couvercle et la portion 24.In this example, the
On note que la première portion 12A présente des trous traversants 23A disposés radialement entre la portion de support de palier 20 et la portion interne 22 et des trous traversants 23B disposés radialement entre la portion interne 22 et la portion cylindrique 24. Ces trous 23A et 23B sont régulièrement répartis selon la direction circonférentielle C. Ces trous 23A et 23B forment des passages pour l'écoulement de l'huile du palier non représenté porté par le support de palier 10.It is noted that the
Le support de vrille 16 est porté par la paroi interne 12, du côté externe CE. Dans cet exemple, le support de vrille 16 présente un voile 16A s'étendant selon la direction axiale X et raccordé à la première portion 12A, du côté externe CE. Le voile 16A porte une portion formant support de vrille 16B. Dans cet exemple, le diamètre de la portion de support de vrille 16B est inférieur au diamètre de la portion de support de palier 20. La portion de support de vrille 16B est disposée au-delà de la portion de support de palier 20 selon la direction axiale X, du côté extérieur de la paroi interne 12. Dans cet exemple, le voile 16A présente une quatrième forme sensiblement tronconique d'axe X inclinée du même côté par rapport à la direction axiale que la première portion 12A.The
La paroi externe 14 présente une deuxième forme sensiblement tronconique s'étendant selon la direction axiale X et présentant une troisième extrémité axiale 14A raccordée à la paroi interne 12 du côté externe CE de la paroi interne 12, et une quatrième extrémité axiale14B, opposé à la deuxième extrémité axiale 14A selon la direction axiale X, formant un anneau collecteur 26. La forme sensiblement tronconique de la paroi externe 14 est inclinée du même côté par rapport à la direction axiale X que la première portion 12A.The
Dans cet exemple, les première, deuxième, troisième et quatrième formes sensiblement tronconiques sont toutes différentes. Selon une variante, certaines de ces formes, voire toutes ces formes, pourraient être identiques (par exemple toutes tronconiques régulières, mais de tailles différentes).In this example, the first, second, third and fourth substantially frustoconical shapes are all different. According to a variant, some of these shapes, or even all of these shapes, could be identical (for example all regular truncated cones, but of different sizes).
Dans cet exemple, l'anneau collecteur 26 est une portion annulaire formant une chambre annulaire présentant plusieurs ouvertures radiales 26A orientées vers l'intérieur du support de palier 10 et régulièrement réparties selon la direction circonférentielle C. Dans cet exemple, une cavité 30 est formée entre la paroi extérieure 14 et le support de vrille 16, l'anneau collecteur 26 étant configuré pour évacuer un fluide sous pression, dans cet exemple du gaz, depuis cette cavité 30.In this example, the
L'anneau collecteur 26 est relié fluidiquement au côté intérieur Cl de la paroi interne 12 via des canaux d'évacuation d'air 32. Dans cet exemple, il y a trois canaux d'évacuation d'air 32 régulièrement répartis autour de la direction axiale X (i.e. les canaux 32 sont espacés de 120° selon la direction circonférentielle C). Chaque canal 32 présente une ouverture de sortie d'air 32A ménagée dans la paroi interne 12. Comme cela est visible sur la
Le support 10 présente dans cet exemple trois piquages 34, 36 et 38 pour un branchement fluidique du support 10 à un circuit d'alimentation d'huile du palier. Dans cet exemple, les piquages 34, 36 et 38 sont disposés sur le côté interne CI de la paroi interne 12.The
Le piquage 34 est un piquage d'alimentation d'huile relié à une conduite d'alimentation d'huile 33 en partie visible sur la
Le piquage 36 est un piquage de récupération d'huile reliée à un collecteur 37 ménagé entre la paroi externe 14, la paroi interne 12 et le support de vrille 16. Dans cet exemple, le collecteur 37 présente une paroi 37A s'étendant radialement entre le support de vrille 16, dans cet exemple le voile 16A, la paroi externe 14, et la paroi interne 12. Le collecteur 37 présente une ouverture 37B ménagée dans le support de vrille 16, dans cet exemple le voile 16A. Par ailleurs, un trou traversant 23A est disposé à l'aplomb, considéré selon la direction radiale R, de l'ouverture 37B.The tapping 36 is an oil recovery tapping connected to a manifold 37 arranged between the
Le piquage 38 est un piquage de drainage d'huile relié à un canal de drainage d'huile 40. Le canal de drainage d'huile 40 s'étend du côté extérieur de la paroi externe 14 et présente une première entrée 42 ménagée dans l'anneau collecteur 26, une deuxième entrée 44 ménagée dans la paroi externe 14 et s'ouvrant dans l'espace 30 formée entre le support de vrille 16 et la paroi externe 14. Le piquage 38 forme la sortie de la conduite 40 qui débouche du côté intérieur Cl de la paroi interne 12. Comme cela est visible sur la
Dans cet exemple, la deuxième entrée 44 comprend deux trous traversants 44A ménagés dans la paroi externe 14, de part et d'autre selon la direction circonférentielle C du collecteur 37, et adjacents au collecteur 37 (voir
Dans cet exemple, le canal de drainage 40 définit le bas B du support 10, le haut H étant diamétralement opposé. Ainsi, le support 10 est configuré pour être monté au sein de la turbomachine 100, avec le haut H et le bas B considérés ainsi (i.e. le haut au-dessus du bas et inversement) selon le sens de la gravité G, en fonctionnement normal de la turbomachine 100. Le drainage de l'huile est ainsi réalisé par gravité.In this example, the
Dans cet exemple, le canal de drainage 40 est disposé diamétralement à l'opposé d'un canal d'évacuation d'air 32, et équidistant selon la direction circonférentielle C des deux autres canaux d'évacuation d'air 32.In this example, the
Par exemple, l'air circulant via les trous 23B pouvant éventuellement contenir de l'huile, cette huile est drainée par le canal de drainage 40 via la deuxième entrée 44.For example, the air circulating via the
Bien que la présente invention ait été décrite en se référant à des modes de réalisation spécifiques, il est évident que des modifications et des changements peuvent être effectués sur ces exemples sans sortir de la portée générale de l'invention telle que définie par les revendications. En particulier, des caractéristiques individuelles des différents modes de réalisation illustrés/mentionnés peuvent être combinées dans des modes de réalisation additionnels. Par conséquent, la description et les dessins doivent être considérés dans un sens illustratif plutôt que restrictif.Although the present invention has been described with reference to specific embodiments, it is obvious that modifications and changes can be made to these examples without departing from the general scope of the invention as defined by the claims. In particular, individual features of the different illustrated/mentioned embodiments can be combined in additional embodiments. Accordingly, the description and the drawings should be considered in an illustrative rather than restrictive sense.
Il est également évident que toutes les caractéristiques décrites en référence à un procédé sont transposables, seules ou en combinaison, à un dispositif, et inversement, toutes les caractéristiques décrites en référence à un dispositif sont transposables, seules ou en combinaison, à un procédé.It is also obvious that all the characteristics described with reference to a method can be transposed, alone or in combination, to a device, and conversely, all the characteristics described with reference to a device can be transposed, alone or in combination, to a method.
Claims (8)
- A turbomachine output bearing support (10) extending according to an axial direction (X), said support (10) being formed by one and the same piece and comprising an annular inner wall (12) having an inner side (CI) and an outer side (CE), and a twist support (16), the inner wall (12) comprising a first section (12A) having a first substantially frustoconical form extending according to the axial direction (X) and having the inner side (CI) and the outer side (CE), the first section (12A) having a first axial end (12A1) provided with a first attachment flange (18) and a second axial end (12A2) opposite to the first axial end (12A1) according to the axial direction (X), provided with a bearing support section (20), the first section (12A) carrying on the inner side (CI) an inner section (22) forming a second attachment flange, the twist support (16) being carried by the inner wall (12A) on the outer side (CE), characterized in that said support (10) formed by one and the same piece comprises an annular outer wall (14) arranged to the outer side (CE) of the inner wall (12) .
- The turbomachine output bearing support (10) according to claim 1, wherein the outer wall (14) has a second substantially frustoconical form extending according to the axial direction (X) and having a third axial end (14A) attached to the inner wall (12) on the outer side (CE) of the inner wall (12), and a fourth axial end (14B), opposite the second axial end (14A) according to the axial direction (X), forming a collector ring (26).
- The turbomachine output bearing support (10) according to claim 2, comprising at least one air exhaust duct (32) extending on the external side of the outer wall (14) and fluidically connecting the internal side (CI) of the inner wall (12) and the collector ring (26).
- The turbomachine output bearing support (10) according to claim 3, comprising three air exhaust ducts (32) uniformly distributed around the axial direction (X).
- The turbomachine output bearing support (10) according to claim 3 or 4, wherein the at least one air exhaust duct (32) has an air outlet opening (32A) arranged in the inner wall (12).
- The turbomachine output bearing support (10) according to any one of claims 1 to 5, comprising an oil drainage duct (40).
- The turbomachine output bearing support (10) according to claim 6, wherein the oil drainage duct (40) extends on the external side of the outer wall (14) and has a first intake (42) arranged in the collector ring (16), a second intake (44) arranged in the outer wall (14) and opening into a space (30) formed between the twist support (16) and the outer wall (14), and an output (36) terminating to the internal side (CI) of the inner wall (12).
- A manufacturing process of a turbomachine output bearing support (10) according to any one of claims 1 to 7, comprising at least one additive manufacturing step.
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FR1906933A FR3097900B1 (en) | 2019-06-26 | 2019-06-26 | Turbomachine outlet bearing bracket |
PCT/FR2020/051040 WO2020260796A1 (en) | 2019-06-26 | 2020-06-16 | Turbomachine output bearing support |
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FR2524064A1 (en) * | 1982-03-26 | 1983-09-30 | Snecma | LUBRICATION AND COOLING DEVICE FOR INTER-SHAFT BEARING OF A TURBOMACHINE |
FR2903151B1 (en) * | 2006-06-29 | 2011-10-28 | Snecma | DEVICE FOR VENTILATION OF AN EXHAUST CASE IN A TURBOMACHINE |
US7935164B2 (en) * | 2007-11-28 | 2011-05-03 | General Electric Company | Vortex air-oil separator system |
FR2985766B1 (en) * | 2012-01-16 | 2016-07-22 | Snecma | ARRANGEMENT FOR GUIDING THE FLOW OF A LIQUID IN RELATION TO THE ROTOR OF A TURBOMACHINE |
FR2997444B1 (en) * | 2012-10-31 | 2018-07-13 | Snecma | HUB FOR A TURBOMACHINE |
FR3013380B1 (en) * | 2013-11-20 | 2015-11-20 | Snecma | AXISYMMETRIC SEAL BEARING SUPPORT SUPPORT |
FR3027625B1 (en) * | 2014-10-27 | 2016-12-30 | Snecma | TURBOMACHINE COMPRISING AN ELECTRIC CURRENT GENERATOR FOR THE INJECTION OF OIL FROM THE INTERIOR OF A TURBINE TREE |
FR3079265B1 (en) * | 2018-03-23 | 2020-04-17 | Safran Aircraft Engines | TURBO-BEARING BEARING SUPPORT OBTAINED BY ADDITIVE MANUFACTURING |
CN109441567A (en) * | 2019-01-02 | 2019-03-08 | 广西玉柴机器股份有限公司 | The output shafting of power turbine |
US11629648B2 (en) * | 2020-12-17 | 2023-04-18 | Hamilton Sundstrand Corporation | Quick access engine rotator pad |
-
2019
- 2019-06-26 FR FR1906933A patent/FR3097900B1/en active Active
-
2020
- 2020-06-16 US US17/597,065 patent/US11686216B2/en active Active
- 2020-06-16 EP EP20742352.6A patent/EP3990753B1/en active Active
- 2020-06-16 CN CN202080047171.3A patent/CN114080491B/en active Active
- 2020-06-16 WO PCT/FR2020/051040 patent/WO2020260796A1/en unknown
Also Published As
Publication number | Publication date |
---|---|
CN114080491A (en) | 2022-02-22 |
WO2020260796A1 (en) | 2020-12-30 |
FR3097900A1 (en) | 2021-01-01 |
US20220235672A1 (en) | 2022-07-28 |
EP3990753A1 (en) | 2022-05-04 |
US11686216B2 (en) | 2023-06-27 |
CN114080491B (en) | 2023-07-18 |
FR3097900B1 (en) | 2021-06-04 |
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