WO2014091804A1 - 圧縮機 - Google Patents

圧縮機 Download PDF

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Publication number
WO2014091804A1
WO2014091804A1 PCT/JP2013/074030 JP2013074030W WO2014091804A1 WO 2014091804 A1 WO2014091804 A1 WO 2014091804A1 JP 2013074030 W JP2013074030 W JP 2013074030W WO 2014091804 A1 WO2014091804 A1 WO 2014091804A1
Authority
WO
WIPO (PCT)
Prior art keywords
impeller
compressor
main wing
respect
wing
Prior art date
Application number
PCT/JP2013/074030
Other languages
English (en)
French (fr)
Japanese (ja)
Inventor
勲 冨田
杉本　浩一
Original Assignee
三菱重工業株式会社
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 三菱重工業株式会社 filed Critical 三菱重工業株式会社
Priority to KR1020157014099A priority Critical patent/KR101765405B1/ko
Priority to EP13862737.7A priority patent/EP2918849B1/en
Priority to CN201380063648.7A priority patent/CN104854350B/zh
Publication of WO2014091804A1 publication Critical patent/WO2014091804A1/ja

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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
    • F04D29/26—Rotors specially for elastic fluids
    • F04D29/28—Rotors specially for elastic fluids for centrifugal or helico-centrifugal pumps for radial-flow or helico-centrifugal pumps
    • F04D29/30—Vanes
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F04—POSITIVE - DISPLACEMENT MACHINES FOR LIQUIDS; PUMPS FOR LIQUIDS OR ELASTIC FLUIDS
    • F04D—NON-POSITIVE-DISPLACEMENT PUMPS
    • F04D21/00—Pump involving supersonic speed of pumped fluids
    • 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
    • F04D29/28—Rotors specially for elastic fluids for centrifugal or helico-centrifugal pumps for radial-flow or helico-centrifugal pumps
    • F04D29/284—Rotors specially for elastic fluids for centrifugal or helico-centrifugal pumps for radial-flow or helico-centrifugal pumps for compressors
    • 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
    • F05D2240/20—Rotors
    • F05D2240/30—Characteristics of rotor blades, i.e. of any element transforming dynamic fluid energy to or from rotational energy and being attached to a rotor
    • F05D2240/303—Characteristics of rotor blades, i.e. of any element transforming dynamic fluid energy to or from rotational energy and being attached to a rotor related to the leading edge of a rotor blade

Definitions

  • the present disclosure relates to a compressor such as a centrifugal compressor or a mixed flow compressor.
  • Patent Document 1 discloses a centrifugal compressor provided with a main wing curved in an arc shape in a direction opposite to the rotational direction in the axial direction of the impeller in order to improve the performance of the compressor. It is disclosed by people.
  • the present invention has been made in view of the above-described conventional problems, and the purpose of the present invention is to suppress the development of shock waves generated at high speed rotation by devising the shape of the leading edge of the main wing.
  • Another object of the present invention is to provide a compressor which is intended to improve performance in a high speed rotation range.
  • At least one embodiment of the present invention is In a compressor that compresses gas that has flowed in from the axial direction, and discharges the gas radially or obliquely with respect to the axial direction, With the rotation axis, An impeller rotating with the rotating shaft; And a compressor housing rotatably accommodating the impeller.
  • the impeller includes a hub fixed to the rotation shaft, and a plurality of main wings provided so as to protrude from the hub. The leading edge of the main wing is inclined in the radial direction with respect to the radial direction toward the radially outer side at a position of at least 50% of the wing length extending radially outward when the impeller is viewed in the axial direction doing.
  • the leading edge of the main wing is inclined in the rotational direction with respect to the radial direction toward the radially outer side at least at a position of 50% of the blade length when the impeller is viewed in the axial direction ing. For this reason, as described later, it is possible to suppress a shock wave generated at the time of high speed rotation of the impeller, and to improve the performance of the compressor in the high speed rotation range.
  • the leading edge of the main wing is rotationally inclined in the radial direction with respect to the radial direction in the range of at least 40% to 80% of the wing length.
  • the maximum inclination angle in the range of 40% to 80% of the blade length is in the range of 3 to 20 degrees with respect to the radial direction. According to such a configuration, it is possible to effectively suppress the shock wave generated at the time of high speed rotation of the impeller, and to improve the performance of the compressor in the high speed rotation range.
  • the radially inner side when the leading edge of the main wing is viewed in the axial direction of the impeller, at the radially inner end thereof, the radially inner side is rotated toward the radial direction with respect to the radial direction. It is inclined. According to such a configuration, it is possible to secure a long connection length between the main wing and the hub while improving the performance of the compressor in the high speed rotation range, and to alleviate the stress concentration at the root portion of the main wing.
  • the leading edge of the main wing when the leading edge of the main wing is viewed in the axial direction of the impeller, at the radially outer end thereof, the direction of rotation relative to the radial direction toward the radially outer side is It is inclined to the opposite side. According to such a configuration, the sharpness of the tip of the main wing can be made gentle while improving the performance of the compressor in the high speed rotation range, and the rigidity of the tip of the main wing can be enhanced. The generated vibration can be suppressed.
  • the leading edge of the main wing is directed to the shroud side at a position at least 50% of the wing height extending toward the shroud side of the compressor housing when the impeller is viewed from the meridional direction. Is inclined upstream with respect to the direction perpendicular to the axis. According to such a configuration, as described later, it is possible to suppress the development of a shock wave generated at the time of high speed rotation of the impeller, and to improve the performance of the compressor in the high speed rotation range.
  • the leading edge of the main wing is continuously inclined upstream with respect to the direction perpendicular to the axial direction toward the shroud in the range of 40% to 80% of the wing height.
  • the maximum inclination angle in the range of 40% to 80% of the wing height is in the range of 10 to 30 degrees with respect to the direction perpendicular to the axis. According to such a configuration, it is possible to effectively suppress the development of shock waves generated at the time of high speed rotation of the impeller, and to improve the performance of the compressor in the high speed rotation range.
  • the front edge of the main wing is upstream on the hub side toward the hub side at the end on the hub side when the impeller is viewed from the meridional direction. It is inclined. According to such a configuration, it is possible to secure a long connection length between the main wing and the hub while improving the performance of the compressor in the high speed rotation range, and to alleviate the stress concentration at the root portion of the main wing.
  • the leading edge of the main wing is downstream in a direction perpendicular to the axial direction toward the shroud side at an end on the shroud side when the impeller is viewed from the meridional direction. It is inclined. According to such a configuration, the sharpness of the tip of the main wing can be made gentle while improving the performance of the compressor in the high speed rotation range, and the rigidity of the tip of the main wing can be enhanced. The generated vibration can be suppressed.
  • the leading edge of the main wing visually recognizes the impeller from the axial direction, at least 50% of the wing length, radially outward in the radial direction It is inclined to the rotational direction side. For this reason, it is possible to provide a compressor capable of improving the performance in the high speed rotation region by suppressing the development of the shock wave generated at the high speed rotation.
  • FIG. 1 illustrates a compressor according to one embodiment. It is a perspective view showing the impeller of the compressor concerning one embodiment. It is the elements on larger scale which showed the impeller of the compressor concerning one Embodiment, Comprising: (a) is a meridional view visually recognized from the meridional direction, (b) is the top view visually recognized from the axial direction. It is explanatory drawing which shows the planar shape of the front edge of a main wing. It is explanatory drawing for demonstrating an effect
  • FIG. 1 is a diagram showing a compressor according to an embodiment.
  • FIG. 2 is a perspective view showing an impeller of a compressor according to one embodiment.
  • the compressor 1 is configured as a centrifugal compressor 1 that compresses gas flowing in the axial direction of the compressor and radially discharges the gas.
  • the centrifugal compressor 1 includes a rotating shaft 2, an impeller 3 provided at one end of the rotating shaft 2, and a compressor housing 6 rotatably accommodating the impeller 3.
  • the rotating shaft 2 is rotatably supported by bearings (not shown), and is configured to be rotatable around a center line CL.
  • the impeller 3 includes a conical hub 4 fixed to one end of the rotation shaft 2 and a plurality of main wings 5 provided to project from the surface of the hub 4.
  • the impeller 3 may also include an intermediate wing 7 axially shorter than the main wing 5 formed between the adjacent main wings 5 and 5 as shown in FIG. 2.
  • a flow passage portion 11 through which gas flows is formed between the main wing 5 and the middle wing 7 (in the absence of the middle wing 7 between the adjacent main wings 5 and 5).
  • the compressor housing 6 has an inlet flow passage 12 for flowing the gas in the axial direction, a diffuser flow passage 14 for flowing out the gas compressed by the impeller 3, and the compressed gas to the outside of the housing. And the scroll channel 16 which leads.
  • the above-described impeller 3 is formed so that the upper edge 5 a of the main wing 5 thereof conforms to the inner peripheral shape of the shroud portion 18, and is rotatably accommodated in the compressor housing 6. And when impeller 3 rotates at high speed, the gas which flowed in from front edge 5b flows through channel part 11, is accelerated, and flows out into diffuser channel 14 mentioned above from trailing edge 5c.
  • FIG. 3 is a partial enlarged view showing the impeller of the compressor according to one embodiment, wherein (a) is a meridional view visually recognized from the meridional direction, and (b) is a plan view visually recognized from the axial direction is there.
  • the front edge 5b of the main wing 5 extends in a direction orthogonal to the center line CL in the meridional view as shown in FIG. 3 (a).
  • FIG. 3B in a plan view, in the vicinity of the central portion of the front edge 5b, it is inclined radially outward with respect to the radial direction r toward the rotational direction R side.
  • the planar shape of the front edge 5b of the main wing 5 viewed in the axial direction will be described in detail with reference to FIG.
  • FIG. 4 is an explanatory view showing a planar shape of the leading edge of the main wing.
  • the most downstream point P1 of the planar shape of the leading edge 5b is 0.2L toward the radially outward position. It is formed.
  • the most upstream flow point P2 is formed at a position of 0.8 L toward the radially outer side.
  • a range of 20 to 80% (0.2 to 0.8 L) of the wing length L is inclined at the maximum inclination angle ⁇ 1 toward the radial direction r toward the rotational direction R with respect to the radial direction r. There is.
  • FIG. 5 is an explanatory view for explaining the operation in the case of inclining the leading edge of the main wing radially outward toward the rotational direction with respect to the radial direction, wherein (a) is the leading edge in the radial direction When parallel (reference example), (b) has shown the case (example) where the leading edge inclines with respect to the radial direction.
  • the arrow V in the drawing indicates the flow direction of the gas, and the length of the arrow V means the magnitude of the flow velocity.
  • the impeller 3 rotates at high speed, the relative flow velocity between the main wing 5 and the gas increases as it goes radially outward. For this reason, the arrow V becomes long as it goes to radial direction outer side.
  • the reduction of the compression efficiency due to the above-mentioned shock wave is performed radially outward at a position of at least 50% of the vane length L extending radially outward.
  • the effect can be expected by inclining toward the rotational direction R with respect to the radial direction.
  • the front edge 5b of the main wing 5 is inclined radially outward to the rotational direction R with respect to the radial direction.
  • the maximum inclination angle ⁇ 1 in the range of 40% to 80% of the blade length L is in the range of 3 to 20 degrees with respect to the radial direction, the shock wave generated at high speed rotation of the impeller 3 described above Can be effectively suppressed.
  • the radial inner end (for example, 0.0 as shown in FIG. 4) In the range of ⁇ 0.2 L), it is inclined to the rotational direction R side with respect to the radial direction toward the inside in the radial direction. According to such a configuration, a long connection length between the main wing 5 and the hub 4 is secured while improving the performance of the compressor 1 in the high speed rotation range. As a result, the overhang is alleviated, and the stress concentration at the root of the main wing 5 can be alleviated.
  • the radial outer end (0.8 L to 1.0 L) of the radial outer end It inclines to the opposite side to the rotation direction with respect to the radial direction toward the outside. According to such a configuration, while improving the performance of the compressor 1 in the high speed rotation range, it is possible to moderate the degree of sharpening at the tip of the main wing 5 and to improve the rigidity at the tip of the main wing 5. For this reason, the vibration which generate
  • FIG. 6 is a perspective view showing an impeller of a compressor according to one embodiment.
  • FIG. 7 is a partial enlarged view showing an impeller of a compressor according to an embodiment, wherein (a) is a meridional view visually recognized from the meridional direction and (b) is a plan view visually recognized from the axial direction is there.
  • FIG. 8 is an explanatory view showing the shape of the meridional plane of the leading edge of the main wing.
  • the impeller 3 concerning this embodiment is fundamentally the same as embodiment mentioned above, attaches
  • the impeller 3 of the present embodiment has a plan shape of the front edge 5 b of the main wing 5 in addition to the same shape as the embodiment described above. As shown in), in the vicinity of the central portion of the front edge 5b in meridional view, it inclines upstream with respect to the direction perpendicular to the axis p toward the shroud side. As shown in detail in FIG. 8, when the blade height of the leading edge 5b extending toward the shroud side is H, the most downstream point P1 of the meridional shape of the leading edge 5b is 0.2H toward the shroud side. It is formed. Further, the most upstream point P2 is formed at a position of 0.8 H toward the shroud side. The range of 20 to 80% (0.2 to 0.8H) of the blade height H is inclined at the maximum inclination angle ⁇ 2 on the upstream side with respect to the direction perpendicular to the axis p toward the shroud side.
  • FIG. 9 is an explanatory view for explaining the operation when the leading edge of the main wing is inclined upstream with respect to the axial orthogonal direction toward the shroud side, corresponding to FIG. 5 of the embodiment described above It is.
  • (A) of FIG. 9 shows the case where the front edge is parallel to the axial orthogonal direction
  • (b) shows the case where the front edge is inclined to the axial orthogonal direction.
  • the reduction of the compression efficiency due to the shock wave mentioned above is directed to the shroud side at a position of at least 50% of the wing height H extending toward the shroud side when the leading edge 5b of the main wing 5 is viewed from the meridional direction of the impeller 3.
  • the effect can be expected by inclining to the upstream side with respect to the axis orthogonal direction.
  • the leading edge 5b of the main wing 5 is inclined upstream with respect to the axial orthogonal direction toward the shroud side.
  • the maximum inclination angle ⁇ 2 in the range of 40% to 80% of the blade height H is in the range of 10 to 30 degrees with respect to the axis orthogonal direction, it occurs at high speed rotation of the impeller 3 described above Shock waves can be effectively suppressed.
  • the end portion on the hub side (for example, 0.0 as shown in FIG. 8) In the range of -0.2 H), it is inclined upstream with respect to the direction orthogonal to the axis toward the hub side.
  • a long connection length between the main wing 5 and the hub 4 is secured while improving the performance of the compressor 1 in the high speed rotation range.
  • the overhang is alleviated, and the stress concentration at the root of the main wing 5 can be alleviated.
  • the present invention is not limited thereto, and various improvements and modifications may be made without departing from the scope of the present invention.
  • the compressor 1 compresses the gas flowing in the axial direction and flows out in the oblique direction It may be configured as a mixed flow compressor.
  • the compressor according to at least one embodiment of the present invention is suitably used, for example, as a compressor of a supercharger used for an automobile or ship engine.

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  • Engineering & Computer Science (AREA)
  • Mechanical Engineering (AREA)
  • General Engineering & Computer Science (AREA)
  • Structures Of Non-Positive Displacement Pumps (AREA)
PCT/JP2013/074030 2012-12-13 2013-09-06 圧縮機 WO2014091804A1 (ja)

Priority Applications (3)

Application Number Priority Date Filing Date Title
KR1020157014099A KR101765405B1 (ko) 2012-12-13 2013-09-06 압축기
EP13862737.7A EP2918849B1 (en) 2012-12-13 2013-09-06 Compressor
CN201380063648.7A CN104854350B (zh) 2012-12-13 2013-09-06 压缩机

Applications Claiming Priority (2)

Application Number Priority Date Filing Date Title
JP2012-272526 2012-12-13
JP2012272526A JP5606515B2 (ja) 2012-12-13 2012-12-13 圧縮機

Publications (1)

Publication Number Publication Date
WO2014091804A1 true WO2014091804A1 (ja) 2014-06-19

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ID=50934103

Family Applications (1)

Application Number Title Priority Date Filing Date
PCT/JP2013/074030 WO2014091804A1 (ja) 2012-12-13 2013-09-06 圧縮機

Country Status (5)

Country Link
EP (1) EP2918849B1 (enrdf_load_stackoverflow)
JP (1) JP5606515B2 (enrdf_load_stackoverflow)
KR (1) KR101765405B1 (enrdf_load_stackoverflow)
CN (1) CN104854350B (enrdf_load_stackoverflow)
WO (1) WO2014091804A1 (enrdf_load_stackoverflow)

Families Citing this family (13)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
EP3434908B1 (en) * 2016-03-30 2020-10-07 Mitsubishi Heavy Industries Engine & Turbocharger, Ltd. Impeller, rotary machine, and turbocharger
ITUA20164221A1 (it) * 2016-06-09 2017-12-09 Fieni Giovanni S R L Gruppo di ventilazione per atomizzazione ed irrorazione
DE102016220133A1 (de) * 2016-10-14 2018-04-19 Bosch Mahle Turbo Systems Gmbh & Co. Kg Laufrad für einen Abgasturbolader und Abgasturbolader mit einem solchen Laufrad
FR3062431B1 (fr) * 2017-01-27 2021-01-01 Safran Helicopter Engines Pale de rouet pour turbomachine, comprenant une ailerette a son sommet et au bord d'attaque
WO2019073551A1 (ja) * 2017-10-11 2019-04-18 三菱重工エンジン＆ターボチャージャ株式会社 遠心式回転機械のインペラ及び遠心式回転機械
CN107989823B (zh) * 2017-12-26 2023-12-01 北京伯肯节能科技股份有限公司 叶轮、离心压缩机及燃料电池系统
JP6740271B2 (ja) * 2018-03-05 2020-08-12 三菱重工業株式会社 羽根車及びこの羽根車を備えた遠心圧縮機
CN109404334A (zh) * 2018-12-27 2019-03-01 泛仕达机电股份有限公司 一种斜流风轮及包括该斜流风轮的低噪声斜流风机
CN112032103B (zh) * 2019-06-03 2022-08-26 日本电产株式会社 叶轮、送风装置以及吸尘器
CN110939602B (zh) * 2019-12-30 2025-03-21 天津北方天力增压技术有限公司 一种具有进气前缘后掠弯曲特征的增压器压气机叶轮
CN113565793B (zh) * 2020-04-29 2024-09-13 青岛海尔空调电子有限公司 压缩机叶轮及压缩机
DE102022127147B4 (de) * 2022-10-17 2024-06-27 Man Energy Solutions Se Verdichter und Turbolader
JP2024158726A (ja) 2023-04-28 2024-11-08 三星電子株式会社 インペラ、送風機、及び掃除機

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JPS6360097U (enrdf_load_stackoverflow) * 1986-10-06 1988-04-21
JP2004044473A (ja) 2002-07-11 2004-02-12 Mitsubishi Heavy Ind Ltd 羽根車および遠心圧縮機
JP2004052754A (ja) * 2002-05-10 2004-02-19 Borgwarner Inc チタン圧縮機翼車のためのハイブリッド製造法
JP2009228549A (ja) * 2008-03-21 2009-10-08 Ihi Corp 遠心圧縮機
JP2012052534A (ja) * 2010-08-31 2012-03-15 General Electric Co <Ge> 超音速圧縮機ロータおよびそれを組み立てる方法
GB2486019A (en) * 2010-12-02 2012-06-06 Dyson Technology Ltd Fan impeller
JP2013508618A (ja) * 2009-10-27 2013-03-07 ゼネラル・エレクトリック・カンパニイ 遠心圧縮機のための小滴キャッチャ

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US20080229742A1 (en) * 2007-03-21 2008-09-25 Philippe Renaud Extended Leading-Edge Compressor Wheel
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JP2004052754A (ja) * 2002-05-10 2004-02-19 Borgwarner Inc チタン圧縮機翼車のためのハイブリッド製造法
JP2004044473A (ja) 2002-07-11 2004-02-12 Mitsubishi Heavy Ind Ltd 羽根車および遠心圧縮機
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JP2012052534A (ja) * 2010-08-31 2012-03-15 General Electric Co <Ge> 超音速圧縮機ロータおよびそれを組み立てる方法
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See also references of EP2918849A4

Also Published As

Publication number Publication date
KR20150079892A (ko) 2015-07-08
JP2014118833A (ja) 2014-06-30
EP2918849A4 (en) 2015-11-25
EP2918849A1 (en) 2015-09-16
CN104854350A (zh) 2015-08-19
JP5606515B2 (ja) 2014-10-15
CN104854350B (zh) 2019-10-01
EP2918849B1 (en) 2017-11-01
KR101765405B1 (ko) 2017-08-07

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