EP3990753B1 - Support de palier de sortie de turbomachine - Google Patents

Support de palier de sortie de turbomachine Download PDF

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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.)
Active
Application number
EP20742352.6A
Other languages
German (de)
English (en)
French (fr)
Other versions
EP3990753A1 (fr
Inventor
Nicolas OVAERE
Fabien Stéphane GARNIER
Arnaud Lasantha GENILIER
Pierre Jean-Baptiste METGE
Current Assignee (The listed assignees may be inaccurate. Google has not performed a legal analysis and makes no representation or warranty as to the accuracy of the list.)
Safran Aircraft Engines SAS
Original Assignee
Safran Aircraft Engines SAS
Priority date (The priority date is an assumption and is not a legal conclusion. Google has not performed a legal analysis and makes no representation as to the accuracy of the date listed.)
Filing date
Publication date
Application filed by Safran Aircraft Engines SAS filed Critical Safran Aircraft Engines SAS
Publication of EP3990753A1 publication Critical patent/EP3990753A1/fr
Application granted granted Critical
Publication of EP3990753B1 publication Critical patent/EP3990753B1/fr
Active legal-status Critical Current
Anticipated expiration legal-status Critical

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Classifications

    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F01—MACHINES OR ENGINES IN GENERAL; ENGINE PLANTS IN GENERAL; STEAM ENGINES
    • F01D—NON-POSITIVE DISPLACEMENT MACHINES OR ENGINES, e.g. STEAM TURBINES
    • F01D25/00—Component parts, details, or accessories, not provided for in, or of interest apart from, other groups
    • F01D25/16—Arrangement of bearings; Supporting or mounting bearings in casings
    • F01D25/162—Bearing supports
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F01—MACHINES OR ENGINES IN GENERAL; ENGINE PLANTS IN GENERAL; STEAM ENGINES
    • F01D—NON-POSITIVE DISPLACEMENT MACHINES OR ENGINES, e.g. STEAM TURBINES
    • F01D25/00—Component parts, details, or accessories, not provided for in, or of interest apart from, other groups
    • F01D25/18—Lubricating arrangements
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F01—MACHINES OR ENGINES IN GENERAL; ENGINE PLANTS IN GENERAL; STEAM ENGINES
    • F01D—NON-POSITIVE DISPLACEMENT MACHINES OR ENGINES, e.g. STEAM TURBINES
    • F01D25/00—Component parts, details, or accessories, not provided for in, or of interest apart from, other groups
    • F01D25/24—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
    • 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
    • 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
    • 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
    • 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
    • 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.

Landscapes

  • 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)
EP20742352.6A 2019-06-26 2020-06-16 Support de palier de sortie de turbomachine Active EP3990753B1 (fr)

Applications Claiming Priority (2)

Application Number Priority Date Filing Date Title
FR1906933A FR3097900B1 (fr) 2019-06-26 2019-06-26 Support de palier de sortie de turbomachine
PCT/FR2020/051040 WO2020260796A1 (fr) 2019-06-26 2020-06-16 Support de palier de sortie de turbomachine

Publications (2)

Publication Number Publication Date
EP3990753A1 EP3990753A1 (fr) 2022-05-04
EP3990753B1 true EP3990753B1 (fr) 2023-04-05

Family

ID=68654606

Family Applications (1)

Application Number Title Priority Date Filing Date
EP20742352.6A Active EP3990753B1 (fr) 2019-06-26 2020-06-16 Support de palier de sortie de turbomachine

Country Status (5)

Country Link
US (1) US11686216B2 (zh)
EP (1) EP3990753B1 (zh)
CN (1) CN114080491B (zh)
FR (1) FR3097900B1 (zh)
WO (1) WO2020260796A1 (zh)

Families Citing this family (1)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US20240151271A1 (en) * 2022-11-07 2024-05-09 Rtx Corporation Annular oil distributor for bearing chamber

Family Cites Families (10)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
FR2524064A1 (fr) * 1982-03-26 1983-09-30 Snecma Dispositif de graissage et de refroidissement pour palier inter-arbres d'une turbomachine
FR2903151B1 (fr) * 2006-06-29 2011-10-28 Snecma Dispositif de ventilation d'un carter d'echappement dans une turbomachine
US7935164B2 (en) * 2007-11-28 2011-05-03 General Electric Company Vortex air-oil separator system
FR2985766B1 (fr) * 2012-01-16 2016-07-22 Snecma Agencement pour le guidage de l'ecoulement d'un liquide par rapport au rotor d'une turbomachine
FR2997444B1 (fr) * 2012-10-31 2018-07-13 Snecma Moyeu de carter pour une turbomachine
FR3013380B1 (fr) * 2013-11-20 2015-11-20 Snecma Support de palier a vrille d'etancheite axisymetrique
FR3027625B1 (fr) * 2014-10-27 2016-12-30 Snecma Turbomachine comprenant un generateur de courant electrique permettant l'injection d'huile depuis l'interieur d'un arbre de turbine
FR3079265B1 (fr) * 2018-03-23 2020-04-17 Safran Aircraft Engines Support de palier de turboreacteur obtenu par fabrication additive
CN109441567A (zh) * 2019-01-02 2019-03-08 广西玉柴机器股份有限公司 动力涡轮机的输出轴系
US11629648B2 (en) * 2020-12-17 2023-04-18 Hamilton Sundstrand Corporation Quick access engine rotator pad

Also Published As

Publication number Publication date
FR3097900B1 (fr) 2021-06-04
WO2020260796A1 (fr) 2020-12-30
FR3097900A1 (fr) 2021-01-01
EP3990753A1 (fr) 2022-05-04
CN114080491A (zh) 2022-02-22
US20220235672A1 (en) 2022-07-28
CN114080491B (zh) 2023-07-18
US11686216B2 (en) 2023-06-27

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