EP3613993B1 - Turbocompresseur doté d'un agencement de refroidissement de palier axial - Google Patents

Turbocompresseur doté d'un agencement de refroidissement de palier axial Download PDF

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Publication number
EP3613993B1
EP3613993B1 EP19192850.6A EP19192850A EP3613993B1 EP 3613993 B1 EP3613993 B1 EP 3613993B1 EP 19192850 A EP19192850 A EP 19192850A EP 3613993 B1 EP3613993 B1 EP 3613993B1
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EP
European Patent Office
Prior art keywords
axial
axial bearing
inlet
drive shaft
turbo compressor
Prior art date
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Application number
EP19192850.6A
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German (de)
English (en)
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EP3613993A1 (fr
Inventor
Julien COTE
Stan VANDESTEENE
Jonathan VLASTUIN
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Danfoss AS
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Danfoss AS
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Publication of EP3613993A1 publication Critical patent/EP3613993A1/fr
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Classifications

    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F04—POSITIVE - DISPLACEMENT MACHINES FOR LIQUIDS; PUMPS FOR LIQUIDS OR ELASTIC FLUIDS
    • F04D—NON-POSITIVE-DISPLACEMENT PUMPS
    • F04D29/00—Details, component parts, or accessories
    • F04D29/58—Cooling; Heating; Diminishing heat transfer
    • F04D29/582—Cooling; Heating; Diminishing heat transfer specially adapted for elastic fluid pumps
    • F04D29/584—Cooling; Heating; Diminishing heat transfer specially adapted for elastic fluid pumps cooling or heating the machine
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F04—POSITIVE - DISPLACEMENT MACHINES FOR LIQUIDS; PUMPS FOR LIQUIDS OR ELASTIC FLUIDS
    • F04D—NON-POSITIVE-DISPLACEMENT PUMPS
    • F04D17/00—Radial-flow pumps, e.g. centrifugal pumps; Helico-centrifugal pumps
    • F04D17/08—Centrifugal pumps
    • F04D17/10—Centrifugal pumps for compressing or evacuating
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F04—POSITIVE - DISPLACEMENT MACHINES FOR LIQUIDS; PUMPS FOR LIQUIDS OR ELASTIC FLUIDS
    • F04D—NON-POSITIVE-DISPLACEMENT PUMPS
    • F04D29/00—Details, component parts, or accessories
    • F04D29/05—Shafts or bearings, or assemblies thereof, specially adapted for elastic fluid pumps
    • F04D29/051—Axial thrust balancing
    • F04D29/0513—Axial thrust balancing hydrostatic; hydrodynamic thrust bearings
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F04—POSITIVE - DISPLACEMENT MACHINES FOR LIQUIDS; PUMPS FOR LIQUIDS OR ELASTIC FLUIDS
    • F04D—NON-POSITIVE-DISPLACEMENT PUMPS
    • F04D29/00—Details, component parts, or accessories
    • F04D29/40—Casings; Connections of working fluid
    • F04D29/42—Casings; Connections of working fluid for radial or helico-centrifugal pumps
    • F04D29/44—Fluid-guiding means, e.g. diffusers
    • F04D29/441—Fluid-guiding means, e.g. diffusers especially adapted for elastic fluid pumps
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F04—POSITIVE - DISPLACEMENT MACHINES FOR LIQUIDS; PUMPS FOR LIQUIDS OR ELASTIC FLUIDS
    • F04D—NON-POSITIVE-DISPLACEMENT PUMPS
    • F04D25/00—Pumping installations or systems
    • F04D25/02—Units comprising pumps and their driving means
    • F04D25/06—Units comprising pumps and their driving means the pump being electrically driven
    • F04D25/0606—Units comprising pumps and their driving means the pump being electrically driven the electric motor being specially adapted for integration in the pump
    • 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
    • F05D2250/00—Geometry
    • F05D2250/50—Inlet or outlet
    • F05D2250/51—Inlet

Definitions

  • the present invention relates to a turbo compressor, and particularly to a refrigeration turbo compressor.
  • a refrigeration turbo compressor may include:
  • the axial bearing plate facing towards the inlet distributor reaches a high temperature which leads to an important deformation of said axial bearing plate, and thus induce deformations of the gas films in the axial bearing arrangement when such an axial bearing arrangement is a gas axial bearing arrangement.
  • Such deformations of the axial bearing plate may lead to seizure of the axial bearing arrangement and to shortened lifetime of the turbo compressor.
  • deformations of the axial bearing plate may also lead to an instability of the axial bearing arrangement, which causes the generation of vibrations of the drive shaft and thus causes contacts of the latter with static parts of the turbo compressor leading to scratches or breaking of the drive shaft.
  • WO2018/041938 discloses a turbo compressor according to the preamble of the claim 1.
  • US 2003/059315 Al discloses another turbo compressor of the prior art.
  • Another object of the present invention is to provide a turbo compressor which is reliable, and which is particularly not subjected to the above-mentioned deformations.
  • the present invention relates to a turbo compressor according to claim 1.
  • Such a configuration of the axial bearing cooling arrangement, and particularly of the bypass openings, allows cooling the axial bearing plate with a derived part of the inlet refrigerant flow, and thus avoids or at least strongly reduces, even at the most critical running conditions of the turbo compressor, the thermal deformations of the axial bearing plate and thus of the axial bearing arrangement.
  • the configuration of the turbo compressor according to the present invention avoids a seizure of the axial bearing arrangement and improves the stability of said axial bearing arrangement, and thus improves the reliability of the turbo compressor and increases the lifetime of the turbo compressor.
  • turbo compressor may also include one or more of the following features, taken alone or in combination.
  • a turbo compressor according to the invention is solely defined by the appended claims.
  • the bypass refrigerant flow path extends in parallel to the inlet refrigerant flow path.
  • the axial bearing arrangement is located adjacent the impeller.
  • the inlet distributor has an annular disc shape.
  • the bypass openings are circumferentially aligned around the longitudinal axis of the drive shaft.
  • the bypass refrigerant flow path is defined by the inlet distributor and the axial bearing plate.
  • the inlet distributor has a first axial surface facing toward the impeller and a second axial surface facing towards the axial bearing arrangement, each bypass opening extending through the inlet distributor thickness and emerging respectively in the first axial surface and in the second axial surface.
  • the bypass openings are angularly distributed around the longitudinal axis of the drive shaft.
  • the inlet distributor includes inlet flow guide members facing towards the impeller, the inlet flow guide members being angularly distributed around the longitudinal axis of the drive shaft and partially defining the inlet refrigerant flow path.
  • each of the inlet flow guide members extends radially towards the drive shaft.
  • each bypass opening is located between two respective adjacent inlet flow guide members.
  • each bypass opening emerges into the first axial surface of the inlet distributor between two respective adjacent inlet flow guide members.
  • the inlet flow guide members are provided on the first axial surface of the inlet distributor.
  • the inlet flow guide members are arranged such that each pair of adjacent inlet flow guide members is configured to radially guide a respective part of the inlet refrigerant flow towards a center area of the inlet distributor.
  • each of the inlet flow guide members has a triangular shape and has an apex oriented towards the drive shaft.
  • each of the inlet flow guide members has an arcuate cross sectional profile.
  • each inlet flow guide member radially converges towards the drive shaft.
  • the axial bearing cooling arrangement includes bypass flow guide members provided on the inlet distributor and facing towards the axial bearing arrangement, the bypass flow guide members being angularly distributed around the longitudinal axis of the drive shaft and partially defining the bypass refrigerant flow path.
  • each of the bypass flow guide members extends radially towards the drive shaft.
  • each bypass flow guide member radially converges towards the drive shaft.
  • each bypass flow guide member has a wing-shaped cross sectional profile.
  • each bypass flow guide member partially defines a bypass flow guide channel extending radially towards the drive shaft.
  • each bypass opening emerges into a respective bypass flow guide channel.
  • the turbo compressor includes a refrigerant inlet fluidly connected to inlet distributor and configured to supply the inlet distributor with refrigerant.
  • the axial bearing arrangement is an axial gas bearing arrangement.
  • the turbo compressor further includes a bearing sleeve located between the electrical motor and the axial bearing arrangement, the bearing sleeve having a longitudinal axis and surrounding the drive shaft, the bearing sleeve including:
  • the radial bearing part and the outer sleeve part are concentrically arranged.
  • the axial end face is planar and oriented perpendicularly with respect to the longitudinal axis of the bearing sleeve.
  • the bearing sleeve further includes an annular gap formed between the radial bearing part and the outer sleeve part and extending around the longitudinal axis of the bearing sleeve.
  • the bearing sleeve further includes a cooling area formed in an outer circumferential surface of the outer sleeve part and intended for the passage of a refrigerant so as to dissipate heat from the bearing sleeve.
  • the cooling area includes at least one annular cooling channel formed in the outer circumferential surface of the outer sleeve part and extending around the longitudinal axis of the bearing sleeve.
  • the axial bearing plate and the additional axial bearing plate extend parallel to each other.
  • the additional axial bearing plate abuts against the contact surface of the bearing sleeve.
  • the electrical motor includes a motor stator and a motor rotor, the motor rotor being connected to the second axial end portion of the drive shaft.
  • the radial bearing part includes a radial bearing surface configured to cooperate with the drive shaft.
  • the radial bearing part includes an additional radial bearing surface configured to cooperate with the drive shaft, the radial bearing surface and the additional radial bearing surface being axially offset with respect to each other.
  • the outer sleeve part and the radial bearing part are made in one piece.
  • the outer sleeve part and the radial bearing part are distinct from each other and are assembled together.
  • the inlet distributor includes an abutment surface against which abuts the bearing sleeve, and for example the contact surface of the sleeve part.
  • the bearing sleeve is axially immobilized with respect to the inlet distributor.
  • the inlet distributor may include a tubular part defining an inner housing in which are received the axial bearing plate, the additional axial bearing plate and the spacer ring.
  • the turbo compressor includes several compression stages configured to compress a refrigerant, each compression stage including an impeller connected to the first axial end portion of the drive shaft.
  • Figures 1 to 6 represent a refrigeration turbo compressor 1 according to the invention, which may be for example a two-stage refrigeration turbo compressor.
  • the turbo compressor 1 includes an hermetic casing 2 and a drive shaft 3 which is rotatably arranged within the hermetic casing 2 and which extends along a longitudinal axis A.
  • the drive shaft 3 includes a first axial end portion 4, a second axial end portion 5 opposite to the first axial end portion 4, and an intermediate portion 6 located between the first and second axial end portions 4, 5.
  • the turbo compressor 1 further includes one or several impeller(s) connected to the first axial end portion 4 of the drive shaft 3, and configured to compress a refrigerant.
  • the turbo compressor 1 includes two impellers 7.1, 7.2 arranged in a back-to-back configuration.
  • the turbo compressor 1 further includes a refrigerant inlet 8 and a refrigerant outlet 9 respectively located upstream and downstream of the impeller 7.1 which belongs to a first compression stage, and an additional refrigerant inlet 10 and an additional refrigerant outlet 11 respectively located upstream and downstream of the impeller 7.2 which belongs to a second compression stage, the refrigerant outlet 9 being fluidly connected to the additional refrigerant inlet 10.
  • the turbo compressor 1 also includes an electrical motor 12 configured to drive in rotation the drive shaft 3 about the longitudinal axis A.
  • the electrical motor 12 includes a motor stator 13 and a motor rotor 14 connected to the second axial end portion 5 of the drive shaft 3.
  • the second axial end portion 5 may include an axial bore 15 within which is arranged the motor rotor 14.
  • the motor rotor 14 may for example be firmly fitted, such as press-fitted or shrink fitted, within the axial bore 15. Further the motor rotor 14 may be a permanent magnet motor rotor.
  • the turbo compressor 1 further includes an axial bearing arrangement, also named thrust bearing arrangement, arranged between the impellers 7.1, 7.2 and the electrical motor 12 and configured to limit an axial movement of the drive shaft 3 during operation.
  • the axial bearing arrangement is advantageously a gas axial bearing arrangement.
  • the axial bearing arrangement includes an axial bearing member 17 arranged on an outer surface of the intermediate portion 6 of the drive shaft 3 and extending radially outwardly with respect to the drive shaft 3.
  • the axial bearing arrangement also includes an axial bearing plate 18 and an additional axial bearing plate 19 each having an annular ring shape, and being arranged in parallel.
  • the axial bearing plate 18 faces towards the impellers 7.1, 7.2, while the additional axial bearing plate 19 faces towards the electrical motor 12.
  • the axial bearing arrangement further includes a spacer ring 20 surrounding the axial bearing member 17, and being clamped between the axial bearing plate 18 and the additional axial bearing plate 19 at radial outer portions of the axial bearing plate 18 and the additional axial bearing plate 19.
  • the spacer ring 20, the axial bearing plate 18 and the additional axial bearing plate 19 define a space in which extends the axial bearing member 17.
  • the spacer ring 20 particularly defines an axial distance between the axial bearing plate 18 and the additional axial bearing plate 19, said axial distance being slightly greater than the width of the axial bearing member 17.
  • the turbo compressor 1 is configured so that gas refrigerant is introduced between the axial bearing member 17, the axial bearing plate 18 and the additional axial bearing plate 19 to form a gas axial bearing.
  • the turbo compressor 1 also includes a bearing sleeve 21, also named bearing housing, which extends along the intermediate portion 6 of the drive shaft 3 and which is located between the axial bearing arrangement and the electrical motor 12.
  • the bearing sleeve 21 may be a one-piece bearing sleeve, or may be made from separated parts assembled together.
  • the bearing sleeve 21 particularly includes:
  • the radial bearing part 22 and the outer sleeve part 23 are concentrically arranged, and the outer sleeve part 23 is connected to the radial bearing part 22 through a connecting part 26 which is away from the axial end face 24, and which is for example positioned substantially at a center of the axial length of the radial bearing part 22.
  • the outer sleeve part 23 may be shorter than the radial bearing part 22 along the longitudinal axis of the bearing sleeve 21.
  • the bearing sleeve 21 further includes an additional annular gap 27 formed between the radial bearing part 22 and the outer sleeve part 23 and extending around the longitudinal axis of the bearing sleeve 21.
  • the additional annular gap 27 faces towards the electrical motor 12, and the annular gap 25 and the additional annular gap 27 are separated by the connecting part 26.
  • the radial bearing part 22 includes a radial bearing surface 22.1 and an additional radial bearing surface 22.2 located on each side of the connecting part 26 and configured to respectively cooperate with a bearing portion 6.1 and an additional bearing portion 6.2 provided on the intermediate portion 6 of the drive shaft 3.
  • the radial bearing surface 22.1 and the bearing portion 6.1 form a radial bearing 28, and particularly a radial gas bearing, while the additional radial bearing surface 22.2 and the additional bearing portion 6.2 define an additional radial bearing 29, and particularly an additional radial gas bearing.
  • the bearing sleeve 21 further includes a contact surface 30 located at the axial end face 24 of outer sleeve part 23, the additional axial bearing plate 19 abutting against the contact surface 30.
  • the bearing sleeve 21 further includes a cooling area 31 formed in an outer circumferential surface of the outer sleeve part 23.
  • the cooling area 31 may for example include an annular cooling channel 32 formed in the outer circumferential surface of the outer sleeve part 23 and extending around the longitudinal axis of the bearing sleeve 21, the annular cooling channel 32 being intended for the passage of a refrigerant so as to dissipate heat from the bearing sleeve 21.
  • the turbo compressor 1 further includes an inlet distributor 33 fluidly connected to the refrigerant inlet 8, and at least partially defining an inlet refrigerant flow path P configured to supply, and for example to axially supply, the first compression stage with an inlet refrigerant flow.
  • the inlet distributor 33 may have an annular disc shape and is located adjacent the axial bearing plate 18.
  • the inlet distributor 33 has a first axial surface 33.1 facing toward the impellers 7.1, 7.2 and a second axial surface 33.2 facing towards the axial bearing arrangement, and particularly facing towards the axial bearing plate 18.
  • the inlet distributor 33 includes inlet flow guide members 34 provided on and protruding from the first axial surface 33.1 of the inlet distributor 33 and facing towards the impellers 7.1, 7.2.
  • the inlet flow guide members 34 partially define the inlet refrigerant flow path P and are particularly arranged such that each pair of adjacent inlet flow guide members 34 is configured to radially guide a respective part of the inlet refrigerant flow towards a center area of the inlet distributor 33.
  • the inlet flow guide members 34 are regularly angularly distributed around the longitudinal axis A of the drive shaft 3, and each inlet flow guide member 34 extends radially towards the drive shaft 3 and converges towards the drive shaft 3.
  • Each inlet flow guide member 34 may have a triangular shape and have an apex oriented towards the drive shaft 3.
  • the bearing sleeve 21 is axially immobilized with respect to the inlet distributor 33.
  • the turbo compressor 1 may therefore include a securing member 35 axially tightening the bearing sleeve 21 against the inlet distributor 33, and more particularly against an abutment surface 36 provided on the inlet distributor 33.
  • the securing member 35 may be secured, for example by screwing, to the hermetic casing 2 or to the inlet distributor 33.
  • the contact surface 30 of the bearing sleeve 21 abuts against the abutment surface 36.
  • the inlet distributor 33 may for example include a tubular part 37 defining an inner housing 38 in which are received the axial bearing plate 18, the additional axial bearing plate 19 and the spacer ring 20.
  • the turbo compressor 1 further includes an elastic element 39 arranged between the axial bearing plate 18 and the inlet distributor 33.
  • the elastic element 39 axially biases the axial bearing plate 18, the additional axial bearing plate 19 and the spacer ring 20 with a predetermined force, for example in the range of 1000 to 2000 N, against the contact surface 30 of the bearing sleeve 21.
  • the elastic element 39 is an annular spring washer, preferably of the Belleville type, coaxially arranged with the bearing sleeve 21 and the drive shaft 3.
  • the elastic element 39 is advantageously arranged in an annular recess formed in the second axial surface 33.2 of the inlet distributor 33, and is in contact with a radial outer portion of the axial bearing plate 18.
  • the elastic element 39 allows, notably when a thermal expansion occurs in the turbo compressor 1, an axial sliding of the axial bearing plate 18, of the additional axial bearing plate 19 and of the spacer ring 20 with respect to the inlet distributor 33, and thus avoids deformations of said parts which could lead to a shortened lifetime of the turbo compressor 1.
  • the turbo compressor 1 also includes an axial bearing cooling arrangement configured to cool at least partially the axial bearing plate 18.
  • the axial bearing cooling arrangement includes bypass openings 40 formed in the inlet distributor 33.
  • the bypass openings are regularly angularly distributed around the longitudinal axis A of the drive shaft 3, and are advantageously circumferentially aligned around the longitudinal axis A of the drive shaft 3.
  • each bypass opening 40 extends through the inlet distributor thickness and emerges respectively in the first axial surface 33.1 and in the second axial surface 33.2.
  • each bypass opening 40 emerges in the first axial surface 33.1 of the inlet distributor 33 between two respective adjacent inlet flow guide members 34.
  • each bypass opening 40 has a generally rectangular shape, but may have any other shape.
  • the axial bearing cooling arrangement further includes bypass flow guide members 41 provided on or recessed from the second axial surface 33.2 of the inlet distributor 33 and facing towards the axial bearing arrangement, and particularly towards the axial bearing plate 18.
  • the bypass flow guide members 41 are angularly distributed around the longitudinal axis A of the drive shaft 3 and extend radially towards the drive shaft 3.
  • each bypass flow guide member 41 partially defines a bypass flow guide channel 42 extending radially towards the drive shaft 3 and converging towards the drive shaft 3, and each bypass opening 40 emerges into a respective bypass flow guide channel 42.
  • the axial bearing cooling arrangement therefore includes a bypass refrigerant flow path 43 which is defined by the bypass flow guide channels 42 and the axial bearing plate 18, and which extends at least partially along the surface of the axial bearing plate 18 facing towards the inlet distributor 33 and the impellers 7.1, 7.2.
  • the bypass refrigerant flow path 43 extends in parallel to the inlet refrigerant flow path P.
  • the bypass openings 40 are particularly configured to derive a part of the inlet refrigerant flow, flowing into the inlet refrigerant flow path P, into the bypass refrigerant flow path 43 such that said derived part of the inlet refrigerant flow flows into the bypass flow guide channels 42 and along the surface of the axial bearing plate 18 facing towards the impellers 7.1, 7.2 and thus at least partially cools the axial bearing plate 18.
  • bypass refrigerant flow path 43 is advantageously fluidly connected to the inlet refrigerant flow path P downstream of the bypass openings 40 through an annular gap 44 defined by the drive shaft 3 and an inner circumferential surface of the inlet distributor 33, such that the derived part of the inlet refrigerant flow returns to the inlet refrigerant flow after having at least partially cooled the axial bearing plate 18.
  • Such a configuration of the axial bearing cooling arrangement, and particularly of the bypass openings 40 and the bypass flow guide channels 42, allows cooling the axial bearing plate 18 with a derived part of the inlet refrigerant flow, and thus avoids or at least strongly reduces, even at the most critical running conditions of the turbo compressor, thermal deformations of the axial bearing plate 18 and thus of the axial bearing arrangement.
  • the configuration of the turbo compressor 1 according to the present invention avoids a seizure of the axial bearing arrangement and improves the stability of said axial bearing arrangement, and thus improves the reliability of the turbo compressor 1 and increases the lifetime of the turbo compressor 1.

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  • Engineering & Computer Science (AREA)
  • Mechanical Engineering (AREA)
  • General Engineering & Computer Science (AREA)
  • Physics & Mathematics (AREA)
  • Fluid Mechanics (AREA)
  • Thermal Sciences (AREA)
  • Structures Of Non-Positive Displacement Pumps (AREA)
  • Mounting Of Bearings Or Others (AREA)
  • Supercharger (AREA)

Claims (11)

  1. Turbocompresseur (1) comprenant :
    un arbre d'entraînement (3) ayant un axe longitudinal (A) et comprenant une première partie d'extrémité axiale (4) et une seconde partie d'extrémité axiale (5) opposée à la première partie d'extrémité axiale (4),
    un étage de compression conçu pour comprimer un réfrigérant, l'étage de compression comprenant une turbine (7.1) reliée à la première partie d'extrémité axiale (4) de l'arbre d'entraînement (3),
    un moteur électrique (12) relié à la seconde partie d'extrémité axiale (5) de l'arbre d'entraînement (3) et conçu pour entraîner en rotation l'arbre d'entraînement (3) autour d'un axe de rotation,
    un agencement de palier axial conçu pour limiter un déplacement axial de l'arbre d'entraînement (3) pendant le fonctionnement, l'agencement de palier axial comprenant :
    une plaque de palier axial (18) ayant une forme annulaire et faisant face à la turbine (7.1),
    une plaque de palier axial supplémentaire (19) ayant une forme annulaire,
    une bague d'écartement (20) serrée entre la plaque de palier axial (18) et la plaque de palier axial supplémentaire (19) au niveau de parties externes radiales de la plaque de palier axial (18) et de la plaque de palier axial supplémentaire (19), la bague d'écartement (20) définissant une distance axiale entre la plaque de palier axial (18) et la plaque de palier axial supplémentaire (19),
    un élément de palier axial (17) disposé sur la surface externe de l'arbre d'entraînement (3), l'élément de palier axial (17) s'étendant sensiblement radialement vers l'extérieur par rapport à l'arbre d'entraînement (3) et s'étendant dans un espace entre des parties internes radiales de la plaque de palier axial (18) et de la plaque de palier axial supplémentaire (19),
    un distributeur d'entrée (33) définissant au moins partiellement un trajet de flux de réfrigérant d'entrée (P) conçu pour alimenter l'étage de compression en un flux de réfrigérant d'entrée, le distributeur d'entrée (33) étant situé adjacent à la plaque de palier axial (18),
    caractérisé en ce que le turbocompresseur (1) comprend en outre un agencement de refroidissement de palier axial conçu pour refroidir au moins partiellement la plaque de palier axial (18), l'agencement de refroidissement de palier axial comprenant des ouvertures de dérivation (40) formées dans le distributeur d'entrée (33) et un trajet de flux de réfrigérant de dérivation (43) défini par le distributeur d'entrée (33) et la plaque de palier axial (18), le trajet de flux de réfrigérant de dérivation (43) s'étendant au moins partiellement le long d'une surface de la plaque de palier axial (18) faisant face au distributeur d'entrée (33), les ouvertures de dérivation (40) étant conçues pour dériver une partie du flux de réfrigérant d'entrée dans le trajet de flux de réfrigérant de dérivation (43) de sorte que ladite partie dérivée du flux de réfrigérant d'entrée refroidit au moins partiellement la plaque de palier axial (18), le trajet de flux de réfrigérant de dérivation (43) étant en communication fluidique avec le trajet de flux de réfrigérant d'entrée (P) en aval des ouvertures de dérivation (40) de sorte que la partie dérivée du flux de réfrigérant d'entrée retourne vers le flux de réfrigérant d'entrée après avoir au moins partiellement refroidi la plaque de palier axial (18).
  2. Turbocompresseur (1) selon la revendication 1, dans lequel le distributeur d'entrée (33) a une première surface axiale (33.1) faisant face à la turbine (7.1) et une seconde surface axiale (33.2) faisant face à l'agencement de palier axial, chaque ouverture de dérivation (40) s'étendant à travers une épaisseur de distributeur d'entrée et émergeant respectivement dans la première surface axiale (33.1) et dans la seconde surface axiale (33.2).
  3. Turbocompresseur (1) selon la revendication 1 ou 2, dans lequel le distributeur d'entrée (33) comprend des éléments de guidage de flux d'entrée (34) faisant face à la turbine (7.1), les éléments de guidage de flux d'entrée (34) étant distribués de façon angulaire autour de l'axe longitudinal (A) de l'arbre d'entraînement (3) et définissant partiellement le trajet de flux de réfrigérant d'entrée (P).
  4. Turbocompresseur (1) selon la revendication 3, dans lequel chaque ouverture de dérivation (40) est située entre deux éléments de guidage de flux d'entrée adjacents respectifs (34).
  5. Turbocompresseur (1) selon l'une quelconque des revendications 1 à 4, dans lequel l'agencement de refroidissement de palier axial comprend des éléments de guidage de flux de dérivation (41) placés sur le distributeur d'entrée (33) et faisant face à l'agencement de palier axial, les éléments de guidage de flux de dérivation (41) étant distribués de façon angulaire autour de l'axe longitudinal (A) de l'arbre d'entraînement (3) et définissant partiellement le trajet de flux de réfrigérant de dérivation (43).
  6. Turbocompresseur (1) selon la revendication 5, dans lequel chaque élément de guidage de flux de dérivation (41) converge radialement vers l'arbre d'entraînement (3)
  7. Turbocompresseur (1) selon la revendication 5 ou 6, dans lequel chaque élément de guidage de flux de dérivation (41) définit partiellement un canal de guidage de flux de dérivation (42) s'étendant radialement vers l'arbre d'entraînement (3).
  8. Turbocompresseur (1) selon l'une quelconque des revendications 1 à 7, dans lequel l'agencement de palier axial est un agencement de palier de gaz axial.
  9. Turbocompresseur (1) selon l'une quelconque des revendications 1 à 8, comprenant en outre une douille de palier (21) située entre le moteur électrique (12) et l'agencement de palier axial, la douille de palier (21) ayant un axe longitudinal et entourant l'arbre d'entraînement (3), la douille de palier (21) comprenant :
    une partie de palier radial (22) qui est tubulaire et qui est conçue pour supporter en rotation l'arbre d'entraînement (3),
    une partie de douille externe (23) entourant la partie de palier radial (22) et comprenant une face d'extrémité axiale (24) qui fait face à l'agencement de palier axial et une surface de contact (30) qui est située sur la face d'extrémité axiale (24) et qui est conçue pour coopérer avec l'agencement de palier axial.
  10. Turbocompresseur (1) selon la revendication 9, dans lequel la douille de palier (21) comprend en outre une zone de refroidissement (31) formée dans une surface circonférentielle externe de la partie de douille externe (23) et est destinée au passage d'un réfrigérant de façon à dissiper la chaleur de la douille de palier.
  11. Turbocompresseur (1) selon la revendication 10, dans lequel la zone de refroidissement (31) comprend au moins un canal de refroidissement annulaire (32) formé dans la surface circonférentielle externe de la partie de douille externe (23) et s'étendant autour de l'axe longitudinal de la douille de palier (21).
EP19192850.6A 2018-08-22 2019-08-21 Turbocompresseur doté d'un agencement de refroidissement de palier axial Active EP3613993B1 (fr)

Applications Claiming Priority (1)

Application Number Priority Date Filing Date Title
FR1857593A FR3085188B1 (fr) 2018-08-22 2018-08-22 Un turbocompresseur pourvu d'un agencement de refroidissement de palier axial

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EP3613993A1 EP3613993A1 (fr) 2020-02-26
EP3613993B1 true EP3613993B1 (fr) 2023-07-19

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JP6881645B1 (ja) * 2020-03-31 2021-06-02 ダイキン工業株式会社 スラスト気体軸受、それを備える遠心型圧縮機、およびそれを備える冷凍装置
CN217107202U (zh) 2020-09-23 2022-08-02 博格华纳公司 压缩机组件和用于车辆的涡轮增压器

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Publication number Priority date Publication date Assignee Title
KR100414110B1 (ko) * 2001-09-25 2004-01-07 엘지전자 주식회사 터보 압축기의 베어링 냉각구조
US8556516B2 (en) * 2010-08-26 2013-10-15 Hamilton Sundstrand Corporation Compressor bearing cooling inlet plate
JP2015183568A (ja) * 2014-03-24 2015-10-22 株式会社豊田自動織機 流体機械
FR3038665B1 (fr) * 2015-07-07 2017-07-21 Danfoss Commercial Compressors Compresseur centrifuge ayant un agencement d'etancheite inter-etages
FR3055678B1 (fr) * 2016-09-02 2020-09-18 Danfoss Silicon Power Gmbh Agencement de palier axial pour un arbre d'entrainement d'un compresseur centrifuge
FR3055677B1 (fr) * 2016-09-02 2020-05-29 Danfoss A/S Arbre de turbocompresseur modulaire

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FR3085188A1 (fr) 2020-02-28
EP3613993A1 (fr) 2020-02-26

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