WO2023242950A1 - Ventilateur à hélice et soufflante axiale - Google Patents

Ventilateur à hélice et soufflante axiale Download PDF

Info

Publication number
WO2023242950A1
WO2023242950A1 PCT/JP2022/023795 JP2022023795W WO2023242950A1 WO 2023242950 A1 WO2023242950 A1 WO 2023242950A1 JP 2022023795 W JP2022023795 W JP 2022023795W WO 2023242950 A1 WO2023242950 A1 WO 2023242950A1
Authority
WO
WIPO (PCT)
Prior art keywords
blade
protrusion
propeller fan
trailing edge
point
Prior art date
Application number
PCT/JP2022/023795
Other languages
English (en)
Japanese (ja)
Inventor
俊勝 新井
一樹 蓮池
Original Assignee
三菱電機株式会社
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 三菱電機株式会社 filed Critical 三菱電機株式会社
Priority to PCT/JP2022/023795 priority Critical patent/WO2023242950A1/fr
Priority to JP2024527952A priority patent/JPWO2023242950A1/ja
Publication of WO2023242950A1 publication Critical patent/WO2023242950A1/fr

Links

Images

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
    • F04D29/26—Rotors specially for elastic fluids
    • F04D29/32—Rotors specially for elastic fluids for axial flow pumps
    • F04D29/38—Blades

Definitions

  • a separated vortex is formed near the leading edge of the blade, and airflow in a turbulent boundary layer is generated on the suction surface side of the rotor blade.
  • the larger the separation vortex generated near the leading edge of the blade the larger the trailing vortex generated behind the trailing edge of the blade as the airflow on the suction surface side flows toward the trailing edge of the blade while being turbulent.
  • noise is generated due to interference between blade tip vortices, separation vortices, and blade trailing vortices with adjacent rotary blades, bell mouths, and the like. The noise characteristics deteriorate as the blade tip vortices, separation vortices, and trailing vortices become larger, and as the airflow turbulence generated on the suction surface increases.
  • Patent Document 1 a substantially triangular protrusion is provided on the rear edge of the rotational direction of the suction side of the blade, which extends approximately in the direction in which the blade extends, to reduce noise caused by airflow on the suction side. It's suppressed.
  • the approximately triangular protrusion has a larger inclination angle on the leading edge side of the blade than on the trailing edge side of the blade. For this reason, the blade trailing vortex generated behind the blade trailing edge cannot be efficiently reduced, and the noise reduction effect is small.
  • the present disclosure has been made in view of the above, and aims to provide a propeller fan that further reduces noise generated by a trailing vortex of the blade generated behind the trailing edge of the blade.
  • the protrusion includes a first inclined portion whose height gradually increases from the leading edge of the wing toward the apex of the protrusion, and a first slope whose height gradually decreases from the apex of the protrusion toward the trailing edge of the wing. a second slope, and the first angle, which is the angle of the first slope, is steeper than the second angle, which is the angle of the second slope.
  • the propeller fan of the present disclosure it is possible to further reduce the noise generated by the trailing vortex of the blade generated behind the trailing edge of the blade.
  • a cross-sectional developed view of the inner peripheral edge of a blade in a propeller fan according to an embodiment A cross-sectional developed view of the outer peripheral edge of a blade in a propeller fan according to an embodiment
  • FIG. 1 is a perspective view showing the configuration of an axial blower 100 according to an embodiment.
  • the axial blower 100 includes a propeller fan 10, a main body 21, a bell mouth 30 as a wind tunnel, a motor (not shown), and a motor fixing member (not shown).
  • a propeller fan 10 and a motor are arranged inside the bell mouth 30.
  • the propeller fan 10 has a cylindrical boss portion 2 and a plurality of rotary blades 1 having the same three-dimensional shape.
  • the boss portion 2 is rotationally driven by a motor, and rotates in the direction of arrow W around a rotating shaft 3.
  • Each rotor blade 1 is attached radially to the outer periphery of the boss portion 2.
  • the bell mouth 30 has a diameter that is gradually reduced from the large-diameter suction port side toward the blowout port side.
  • the rotary blade 1 has a leading edge 1a, which is the front end in the rotational direction indicated by arrow W, a trailing blade edge 1b, which is the rear end in the rotational direction indicated by arrow W, and an inner circumference (
  • the blade has an inner peripheral edge portion 1c which is an end portion on the boss portion 2 side) and an outer peripheral blade portion 1d which is an end portion on the outer peripheral portion side.
  • five rotary blades 1 are shown, and in FIG. 2, three rotary blades 1 are shown. As the number of rotary blades 1, other numbers may be adopted.
  • the Z-axis corresponding to the rotation axis 3 the X-axis and Y-axis that are two axes perpendicular to the Z-axis, and the coordinate center O of the X-axis, Y-axis, and Z-axis are shown. There is.
  • the propeller fan 10 has a shape in which the outer circumferential portion is bent toward the upstream side of the airflow as indicated by arrow A in terms of the shape in the direction connecting the inner circumferential portion and the outer circumferential portion. This reduces the interference caused by the blade tip vortex 5 mentioned above.
  • the inner periphery side is convex with respect to the airflow, and the outer periphery side is concave with respect to the airflow.
  • the S-shape is not limited to this, the shape is not limited to this, and the outer periphery is bent toward the upstream side of the airflow. It is sufficient if it has the following.
  • FIG. 6 is a perspective view showing the rotor blade 1 of the propeller fan 10 according to the embodiment.
  • FIG. 7 is a cross-sectional development view of the blade inner circumferential edge portion 1c of the propeller fan 10 according to the embodiment.
  • FIG. 7 is a cross-sectional developed view of the propeller fan 10 cut along a cylindrical surface having a radius D1-D1' in FIG. 4 and expanded into a two-dimensional plane.
  • FIG. 8 is a developed cross-sectional view of the blade outer peripheral edge portion 1d of the propeller fan 10 according to the embodiment.
  • FIG. 8 is a cross-sectional developed view of the propeller fan 10 cut along a cylindrical surface having a radius D2-D2' in FIG. 4 and expanded into a two-dimensional plane.
  • FIG. 9 is a cross-sectional developed view of an intermediate portion between the inner blade edge 1c and the outer blade edge 1d in the propeller fan 10 according to the embodiment.
  • FIG. 9 is a cross-sectional exploded view of the propeller fan 10 cut along a cylindrical surface having a radius D3-D3' in FIG. 4 and expanded into a two-dimensional plane.
  • FIG. 10 is a partially sectional exploded view showing the protrusion 20 of the rotor blade 1 of the propeller fan 10 according to the embodiment.
  • FIG. 11 is an enlarged cross-sectional developed view showing the protrusion 20 of the rotor blade 1 of the propeller fan 10 according to the embodiment.
  • FIG. 12 is a diagram showing a change in the slope of the tangent to the suction surface 1f of the rotor blade 1 of the propeller fan 10 according to the embodiment.
  • FIG. 13 is a cross-sectional developed view showing the blade trailing vortex 14 and the like generated in a comparative example without the protrusion 20.
  • FIG. 14 is a cross-sectional development view showing the blade trailing vortex 14 and the like generated in the rotor blade 1 of the propeller fan 10 according to the embodiment in which the protrusion 20 is provided.
  • the blade trailing edge portion 1b also has a rounded shape to prevent separation of airflow.
  • the curvature of the R shape on the side of the suction surface 1f is larger than the curvature of the R shape on the side of the pressure surface 1g.
  • the blade trailing vortex 14 shown in FIG. A protrusion 20 is provided for suppression.
  • the protrusion 20 extends parallel to the wing trailing edge 1b. It is desirable that the protrusion 20 is continuously provided over one-third or more of the length of the blade trailing edge 1b.
  • the protrusion 20 is preferably provided continuously from a radial position Rrib near the inner blade edge 1c to a radial position Rrib' near the outer blade edge 1d.
  • the projection 20 increases in height from the end of the projection on the wing leading edge 1a side (point PB in FIG. 11) toward the apex of the projection 20 (point PD in FIG. 11).
  • the first inclined portion 20a gradually increases in height, and the height increases from the apex of the protrusion 20 (point PD in FIG. 11) to the end of the protrusion on the wing trailing edge 1b side (point PF in FIG. 11). It has a second slope portion 20b that gradually becomes lower.
  • the first angle which is the angle of the first inclined portion 20a, is steeper than the second angle, which is the angle of the second inclined portion 20b.
  • the projection 20 has a shape in which the inclination ⁇ 2 with respect to the blade surface on the downstream side (the blade trailing edge 1b side) is larger than the inclination ⁇ 1 with respect to the blade surface on the upstream side (the blade leading edge 1a side). has. Note that it is preferable that the protrusions 20 have the same cross-sectional shape in the direction along the blade trailing edge 1b.
  • the chord length L is the longest distance between the straight line LW1 and the straight line LW2 when the blade is sandwiched between two parallel straight lines LW1 and LW2 in the cylindrical cross section of the rotary blade 1. It is defined as the length.
  • the direction parallel to the blade chord length L and going from the blade leading edge 1a to the blade trailing edge 1b is defined as the XL direction, which is perpendicular to the blade chord length L, parallel to the straight line LW1 and the straight line LW2, and runs from the downstream side to the upstream side.
  • the heading direction is defined as the ZL direction.
  • the curved surface connecting point PA and point PB is the curved surface on the wing leading edge 1a side of the wing surface adjacent to the protrusion 20.
  • the arc connecting portion connecting point PB and point PC is a portion connecting the portion of the projection portion 20 on the blade leading edge portion 1a side and the blade surface.
  • the curved surface connecting the point PC and the apex point PD is the curved surface of the protrusion 20 on the wing leading edge portion 1a side.
  • the curved surface connecting point PD and point PE is the curved surface of the protrusion 20 on the wing trailing edge 1b side.
  • the arc connecting portion connecting point PE and point PF is a portion connecting the portion of the projection portion 20 on the blade trailing edge portion 1b side and the blade surface.
  • the curved surface connecting point PF and point PG is a curved surface on the blade trailing edge 1b side of the blade surface adjacent to the protrusion 20.
  • Point PG is a point included in the trailing edge portion 1b
  • the curved surface connecting points PA and PB and the curved surface connecting points PF and PG are part of the suction surface 1f, which is the upstream surface of the rotor blade 1.
  • the protrusion 20 is formed by a curved surface connecting points PC and PD and a curved surface connecting points PD and PE.
  • the curved surface connecting points PA and PB and the curved surface connecting points PF and PG are curved surfaces that are convex toward the upstream side.
  • the curved surface connecting point PC and point PD and the curved surface connecting point PD and point PE are curved surfaces convex to the upstream side, and the curved surface connecting point PA and point PB and the curved surface connecting point PF and point PG.
  • the curvature is greater than the curved surface. That is, the protrusion 20 is a curved surface with a larger curvature than the suction surface 1f of the rotor blade 1.
  • the negative pressure surface 1f and the protrusion 20 are smoothly connected in an arc shape by an arc connection part connecting points PB and PC and an arc connection part connecting points PE and PF.
  • the curved surface that connects points PA and PB and the curved surface that connects points PC and PD are continuous and smooth so that the slopes at the connection points are equal due to the arc connection section that connects point PB and point PC. connected to.
  • the arc connecting portion connecting point PB and point PC is convex toward the downstream side.
  • the curved surface that connects points PD and PE and the curved surface that connects points PF and PG are continuously smoothed by the arc connection connecting points PE and PF so that the slopes at the connection are equal. connected to.
  • FIG. 12 shows a change in the slope dZL/dXL of the tangent to the suction surface 1f of the rotor blade 1 of the propeller fan 10 in the XL direction.
  • the curved surface connecting point PA and point PB is a curved surface that is convex toward the upstream side
  • the arc connecting portion connecting point PB and point PC is a curved surface that is convex toward the downstream side.
  • the slope dZL/dXL of the tangent line becomes maximum at point PB between point PA and point PC.
  • Straight line LPB is a straight line that touches the blade surface at point PB.
  • the curved surface connecting point PD and point PE that constitutes the protrusion 20 is a curved surface that is convex toward the upstream side, and has a shape that protrudes toward the upstream side as it approaches the blade leading edge portion 1a side. Since the arcuate connection connecting point PE and point PF is a curved surface convex toward the downstream side, the slope of the tangent of the protrusion 20 on the blade trailing edge 1b side with respect to the XL axis becomes maximum at point PE.
  • Straight line LPE is a straight line that touches the blade surface at point PE.
  • the slope of the protrusion 20 on the blade trailing edge 1b side is defined by a straight line LPE.
  • the inclination of the protrusion 20 on the blade trailing edge 1b side is at a point PE near the connection between the protrusion 20 and the blade trailing edge 1b, where the inclination of the tangent line is maximum downstream. This is the slope at .
  • a straight line passing through point PE and parallel to straight line LPB is defined as straight line LPB2.
  • the inclination ⁇ 1 of the protrusion 20 on the wing leading edge 1a side is defined by the angle between the straight line LPB and the straight line LPC.
  • the inclination ⁇ 2 of the projection 20 on the blade trailing edge 1b side is defined by the angle between the straight line LPB2 and the straight line LPE.
  • the height tr of the protrusion 20 and the plate thickness tk of the rotor blade 1 are defined as follows.
  • the apex of the protrusion 20 in the ZL direction is defined as a point PD.
  • the height tr of the protrusion 20 and the plate thickness tk of the wing portion are defined by the height in the ZL direction at the position of this point PD.
  • Let the straight line LPB be the virtual wing surface.
  • Point Pt is a point on a straight line that passes through the vertex indicated by point PD of protrusion 20 and extends in the ZL direction, and intersects with straight line LPB.
  • the height from point Pt to point PD, which is the apex of protrusion 20, is defined as height tr of protrusion 20.
  • Point Pk is a point that passes through the apex of the protrusion 20 indicated by point PD and intersects with the blade surface of the pressure surface 1g on a straight line extending in the ZL direction.
  • the width tw of the protrusion 20 and the distance B of the protrusion 20 from the wing trailing edge 1b are defined as follows.
  • the width tw of the protrusion 20 is defined as the distance from point PC, which is the front edge of the protrusion 20, to point PE, which is the rear edge of the protrusion 20, in the XL direction.
  • the distance from point PE, which is the trailing edge of the projection 20, to point PG on the blade trailing edge 1b of the rotor 1 is defined as distance B of the projection 20 from the blade trailing edge 1b.
  • a wake vortex 14 is generated.
  • the rotor blade 1 when the rotor blade 1 is provided with the protrusion 20, it is possible to prevent the air flow 32 from flowing toward the blade trailing edge 1b, and airflow occurs behind the blade trailing edge 1b.
  • the blade trailing vortex 14 can be made smaller.
  • the slope ⁇ 2 of the protrusion 20 on the blade trailing edge 1b side is larger than the slope ⁇ 1 of the protrusion 20 on the blade leading edge 1a side.
  • the first angle which is the angle of the first inclined portion 20a
  • the second angle which is the angle of the second inclined portion 20b.
  • Patent Document 1 when the flow point changes and the angle of the flow flowing into the rotor blade 1 changes, separation may become excessive due to the protruding shape and noise may worsen.
  • dust and the like tend to accumulate on the apex of the protrusion, and when dust accumulates, the shape of the protrusion changes, which may change the flow, resulting in excessive separation and worsening of noise.
  • the protrusion 20 of the embodiment has a shape that is curved on the upstream side of the flow and sharply pointed on the downstream side, and the thicker apex portion is closer to the upstream side of the flow. This prevents the flow from separating excessively and stabilizes the flow.
  • ⁇ 1 be larger than 90°.
  • the turbulence caused by the blade trailing vortex 14 can be weakened. That is, it is desirable that the angle of the protrusion 20 satisfies the relationship 90° ⁇ 1 ⁇ 2.
  • K T SPL A -10Log (Q P T 2.5 ) Q is the air volume [m 3 /min], P T is the total pressure [Pa], and SPL A is the noise characteristic [dB] after A-characteristic correction.
  • the width tw of the protrusion 20 preferably satisfies a range from one time the height tr of the protrusion 20 to four times the height tr of the protrusion 20, as shown by the following formula. 1 ⁇ tr ⁇ tw ⁇ 4 ⁇ tr
  • the shape of the protrusion 20 is a smooth curved shape that is high at the center and low at the periphery.
  • a parabola or a quadratic curve may be used as the curve shape.
  • FIG. 16 is a diagram showing the relationship between the distance of the protrusion 20 with respect to the blade trailing edge 1b of the propeller fan 10 and the specific noise reduction rate ⁇ K T according to the embodiment.
  • the horizontal axis represents the ratio of the distance B of the protrusion 20 from the blade trailing edge 1b to the blade chord length L
  • the vertical axis represents the specific noise reduction ratio ⁇ K T.
  • the noise reduction effect will be small. It is desirable to provide the protrusion 20 in the range of ⁇ B/L ⁇ 0.08.
  • FIG. 17 is a plan view showing a modification of the propeller fan 10 according to the embodiment.
  • FIG. 18 is a plan view showing another modification of the propeller fan 10 according to the embodiment.
  • the protrusion 20 is provided from the center position in the radial direction to the outer peripheral side.
  • the protrusion 20 is provided from the center position in the radial direction to the inner peripheral side.
  • the propeller fan 10 it is possible to achieve low noise with any pattern of the projections 20, and experiments have shown that an effect of -1.8 (db) in specific noise can be obtained. I was able to confirm that. Even when the protrusion 20 could not be arranged over the entire blade trailing edge 1b due to manufacturing reasons, certain effects were obtained.
  • These series of evaluation results are the results of evaluating the rotor blade 1 having a diameter of 220 mm at a constant rotation speed of 1400/min.
  • the length of the protrusion 20 is preferably parallel to the blade trailing edge 1b and is 1/3 or more of the length of the blade trailing edge 1b.
  • FIG. 19 is a plan view showing the propeller fan 10 according to the embodiment.
  • the plurality of rotary blades 1 are arranged so that they do not overlap. , are evenly arranged in the circumferential direction around the rotating shaft 3.
  • resin molding the propeller fan 10 it is possible to form the propeller fan 10 using a mold that is divided into two parts vertically in the Z-axis direction.
  • the protrusion 20 is also shaped to be compatible with two-part molding.
  • FIG. 20 is an enlarged sectional developed view of the propeller fan 10 according to the embodiment shown in FIG. 11, which is rotated so that the Z-axis direction is in the vertical direction. It is assumed that resin molding is performed using a mold that is divided into two parts in the vertical direction of FIG. 20, that is, in the positive direction and the negative direction of the Z axis.
  • the cross section of the protrusion 20 on a cylindrical surface centered on the rotating shaft 3 extending in the Z-axis direction should have a shape that becomes wider from the upstream side to the downstream side. good.
  • the slope of the straight line LPC advances from the downstream side (Z-axis negative side) to the upstream side (Z-axis positive side), it increases from the blade leading edge 1a side to the blade trailing edge 1b side.
  • the slope of the straight line LPE advances from the downstream side (Z-axis negative side) to the upstream side (Z-axis positive side), it slopes upward from the blade trailing edge 1b side to the blade leading edge 1a side. It may be a shape.
  • this shape By adopting this shape, it becomes a shape that prevents undercuts during molding, and it becomes possible to use a mold consisting of a simple upper and lower mold configuration, and there is no large increase in cost for introduction. Moreover, by adopting this shape, there are no corners, which prevents dust from adhering, and even when there is no cleaning work, the noise reduction effect can be exerted for a long period of time.

Landscapes

  • Engineering & Computer Science (AREA)
  • Mechanical Engineering (AREA)
  • General Engineering & Computer Science (AREA)
  • Structures Of Non-Positive Displacement Pumps (AREA)

Abstract

La partie périphérique externe d'une pale rotative (1) a une forme qui est courbée vers le côté amont d'un flux d'air. Une saillie (20) s'étendant parallèlement à un bord de fuite de pale (1b) de la pale rotative (1) est disposée sur un côté surface de pression négative (1f) du bord de fuite de pale (1b). La saillie (20) comporte une première partie inclinée (20a) dont la hauteur augmente progressivement à partir d'un côté bord d'attaque de pale vers le sommet de la saillie (20), et une seconde partie inclinée (20b) qui dont la hauteur diminue progressivement à partir du sommet de la saillie (20) vers le bord de fuite de pale (1b). Un premier angle, qui est l'angle de la première partie inclinée (20a), est plus raide qu'un second angle, qui est l'angle de la seconde partie inclinée (20b).
PCT/JP2022/023795 2022-06-14 2022-06-14 Ventilateur à hélice et soufflante axiale WO2023242950A1 (fr)

Priority Applications (2)

Application Number Priority Date Filing Date Title
PCT/JP2022/023795 WO2023242950A1 (fr) 2022-06-14 2022-06-14 Ventilateur à hélice et soufflante axiale
JP2024527952A JPWO2023242950A1 (fr) 2022-06-14 2022-06-14

Applications Claiming Priority (1)

Application Number Priority Date Filing Date Title
PCT/JP2022/023795 WO2023242950A1 (fr) 2022-06-14 2022-06-14 Ventilateur à hélice et soufflante axiale

Publications (1)

Publication Number Publication Date
WO2023242950A1 true WO2023242950A1 (fr) 2023-12-21

Family

ID=89192672

Family Applications (1)

Application Number Title Priority Date Filing Date
PCT/JP2022/023795 WO2023242950A1 (fr) 2022-06-14 2022-06-14 Ventilateur à hélice et soufflante axiale

Country Status (2)

Country Link
JP (1) JPWO2023242950A1 (fr)
WO (1) WO2023242950A1 (fr)

Citations (4)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
JP2011179330A (ja) * 2010-02-26 2011-09-15 Panasonic Corp 羽根車と送風機及びそれを用いた空気調和機
JP2012041821A (ja) * 2010-08-12 2012-03-01 Mitsubishi Heavy Ind Ltd 翼体
JP2013019335A (ja) * 2011-07-12 2013-01-31 Mitsuba Corp 冷却ファン
KR20140124892A (ko) * 2012-08-07 2014-10-28 엘지전자 주식회사 팬

Patent Citations (4)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
JP2011179330A (ja) * 2010-02-26 2011-09-15 Panasonic Corp 羽根車と送風機及びそれを用いた空気調和機
JP2012041821A (ja) * 2010-08-12 2012-03-01 Mitsubishi Heavy Ind Ltd 翼体
JP2013019335A (ja) * 2011-07-12 2013-01-31 Mitsuba Corp 冷却ファン
KR20140124892A (ko) * 2012-08-07 2014-10-28 엘지전자 주식회사 팬

Also Published As

Publication number Publication date
JPWO2023242950A1 (fr) 2023-12-21

Similar Documents

Publication Publication Date Title
JP4396775B2 (ja) 遠心ファン
JP6914371B2 (ja) 軸流送風機
JP6218862B2 (ja) 軸流送風機
US20200240430A1 (en) Propeller fan and axial flow blower
WO2003072948A1 (fr) Ventilateur
JP4818310B2 (ja) 軸流送風機
JP5127854B2 (ja) 送風機及びヒートポンプ装置
CN205876751U (zh) 离心式送风机及具有该离心式送风机的空调机
JP2003184792A (ja) 送風機
JP5682751B2 (ja) 多翼送風機
CN115443382B (zh) 送风机
WO2023242950A1 (fr) Ventilateur à hélice et soufflante axiale
TWI529308B (zh) Impeller and the use of impeller shaft flow blower
WO2019035153A1 (fr) Hélice, ventilateur et dispositif de climatisation
JPH08240197A (ja) 軸流ファン
KR20170102097A (ko) 누류 및 와류 억제용 축류팬
CN110566500A (zh) 一种离心通风机的叶轮
WO2022137388A1 (fr) Soufflante
JPH01247797A (ja) ファン
JP2000009083A (ja) 羽根車
CN114829784A (zh) 离心送风机
JP6625291B1 (ja) 羽根車、送風機及び空気調和機
JP7487854B1 (ja) 送風機
WO2020110167A1 (fr) Impulseur et ventilateur à flux axial
KR20040043623A (ko) 축류팬

Legal Events

Date Code Title Description
121 Ep: the epo has been informed by wipo that ep was designated in this application

Ref document number: 22946770

Country of ref document: EP

Kind code of ref document: A1

ENP Entry into the national phase

Ref document number: 2024527952

Country of ref document: JP

Kind code of ref document: A