WO2015002228A1 - Structure de partie en spirale et compresseur de suralimentation - Google Patents

Structure de partie en spirale et compresseur de suralimentation Download PDF

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Publication number
WO2015002228A1
WO2015002228A1 PCT/JP2014/067643 JP2014067643W WO2015002228A1 WO 2015002228 A1 WO2015002228 A1 WO 2015002228A1 JP 2014067643 W JP2014067643 W JP 2014067643W WO 2015002228 A1 WO2015002228 A1 WO 2015002228A1
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WO
WIPO (PCT)
Prior art keywords
turbine
scroll
flow path
aspect ratio
supercharger
Prior art date
Application number
PCT/JP2014/067643
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English (en)
Japanese (ja)
Inventor
章弘 山方
Original Assignee
株式会社Ihi
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 株式会社Ihi filed Critical 株式会社Ihi
Priority to DE112014003154.2T priority Critical patent/DE112014003154T5/de
Priority to CN201480031419.1A priority patent/CN105392975B/zh
Priority to JP2015525254A priority patent/JP5954494B2/ja
Publication of WO2015002228A1 publication Critical patent/WO2015002228A1/fr

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    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F02—COMBUSTION ENGINES; HOT-GAS OR COMBUSTION-PRODUCT ENGINE PLANTS
    • F02C—GAS-TURBINE PLANTS; AIR INTAKES FOR JET-PROPULSION PLANTS; CONTROLLING FUEL SUPPLY IN AIR-BREATHING JET-PROPULSION PLANTS
    • F02C6/00—Plural gas-turbine plants; Combinations of gas-turbine plants with other apparatus; Adaptations of gas-turbine plants for special use
    • F02C6/04—Gas-turbine plants providing heated or pressurised working fluid for other apparatus, e.g. without mechanical power output
    • F02C6/10—Gas-turbine plants providing heated or pressurised working fluid for other apparatus, e.g. without mechanical power output supplying working fluid to a user, e.g. a chemical process, which returns working fluid to a turbine of the plant
    • F02C6/12—Turbochargers, i.e. plants for augmenting mechanical power output of internal-combustion piston engines by increase of charge pressure
    • 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
    • F01D9/00—Stators
    • F01D9/02—Nozzles; Nozzle boxes; Stator blades; Guide conduits, e.g. individual nozzles
    • F01D9/026—Scrolls for radial machines or engines
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F02—COMBUSTION ENGINES; HOT-GAS OR COMBUSTION-PRODUCT ENGINE PLANTS
    • F02B—INTERNAL-COMBUSTION PISTON ENGINES; COMBUSTION ENGINES IN GENERAL
    • F02B39/00—Component parts, details, or accessories relating to, driven charging or scavenging pumps, not provided for in groups F02B33/00 - F02B37/00
    • 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
    • F05D2220/40—Application in turbochargers

Definitions

  • the present invention relates to a scroll part structure having a spiral flow path for supplying a fluid to a moving blade and a supercharger having the scroll part structure, and more particularly, to a scroll part structure and an overload capable of reducing pressure loss. Regarding the feeder.
  • a rotary prime mover that obtains power by supplying fluid to a moving blade and converting the kinetic energy of the fluid into rotational motion is generally called a turbine.
  • One of the apparatuses using such a turbine is a supercharger.
  • a supercharger (turbocharger) for a vehicle includes a turbine including a turbine rotor blade that rotates by supply of exhaust gas, and an impeller that is coaxially connected to the turbine rotor blade, and the rotation of the impeller And a compressor for sucking air.
  • the air taken in by the compressor is compressed and supplied to the engine, mixed with fuel and burned.
  • the exhaust gas after combustion is sent to the turbine for work, and finally discharged into the atmosphere.
  • the flow path for supplying the exhaust gas to the turbine rotor blade has a scroll portion for accelerating the exhaust gas.
  • the scroll portion is formed in a spiral shape around the rotating shaft of the turbine blade, and is configured as a flow path for supplying the exhaust gas toward the rotating shaft of the turbine blade.
  • variable capacity supercharger In such a supercharger, a variable capacity supercharger has been developed in order to obtain an appropriate turbine output in accordance with the rotational speed of the vehicle engine (see Patent Documents 1 and 2).
  • the variable capacity supercharger includes a plurality of rotatable vanes (blades) arranged in a flow path between the scroll portion and the turbine rotor blade.
  • the flow rate can be suppressed when the flow rate is the same, so that the flow rate can be suppressed. Therefore, the pressure loss can be reduced.
  • the scroll portion cannot be designed to be larger than a certain size in the design of the supercharger or the turbine because of the relationship with the in-vehicle conditions.
  • variable capacity supercharger described in Patent Document 2
  • a part of the variable nozzle mechanism protruding into the scroll portion obstructs the flow of the exhaust gas, and the pressure loss due to the increased flow passage cross-sectional area. The reduction effect will be reduced.
  • the present invention was devised in view of the above-described problems, and even when a part of the variable nozzle mechanism protrudes from the scroll portion, the scroll portion structure can reduce the pressure loss of the fluid supplied to the moving blade. And to provide a supercharger.
  • the present invention provides a scroll portion structure and a supercharger that have little influence on the reduction of fluid pressure loss due to a part of the protruding variable nozzle mechanism even when the variable nozzle mechanism is provided in the scroll portion.
  • the purpose is to provide a machine.
  • 1st aspect of this invention is a scroll part structure, Comprising: Around the rotating shaft of the said moving blade of the turbine which supplies motive power by supplying a fluid to a moving blade, an inlet part, an outlet part, and the said inlet part and the said outlet A flow path formed in a spiral shape composed of an intermediate part of the part, the aspect ratio of the cross-sectional shape of the flow path of the intermediate part is higher than the aspect ratio of the inlet part and the outlet part, the aspect ratio is ( The axial length of the turbine having the flow path cross-sectional shape) / (the radial length of the turbine having the flow path cross-sectional shape), and the intermediate portion is a portion having at least the aspect ratio of 1.8 or more. It is summarized as having.
  • a second aspect of the present invention includes a turbine including a turbine rotor blade that rotates by supplying exhaust gas, and an impeller that is coaxially connected to the turbine rotor blade, and sucks air by the rotation of the impeller. And a supercharger having the scroll part structure according to the first aspect.
  • the scroll portion may have a peak value of the aspect ratio within a range of 30 ° to 120 ° from the starting point.
  • the peak value may be set within a range of 2.0 to 3.0.
  • the turbine includes a variable nozzle mechanism in which a plurality of rotatable vanes are arranged in an introduction path for supplying fluid from the scroll portion to the rotor blade, and a part of the variable nozzle mechanism protrudes from the scroll portion. May be arranged.
  • the flow path cross-section while securing the flow cross-sectional area of the scroll part by increasing the aspect ratio of the cross-sectional shape of the flow path at the middle part of the scroll part.
  • the shape can be formed into a flat shape. Therefore, even if the turbine is arranged such that a part of the variable nozzle mechanism protrudes from the scroll part or the supercharger having the turbine, the flow path of the scroll part can be formed so as to avoid the protruding part. It is possible to reduce the pressure loss of the fluid supplied to the rotor blade.
  • FIG. 1 is a cross-sectional view showing a supercharger according to an embodiment of the present invention.
  • FIG. 2A is a plan view showing a scroll part structure according to this embodiment
  • FIG. 2B is a plan view showing a scroll part structure according to the prior art.
  • FIG. 3A is a tomogram in which the flow path cross-sectional shapes of the scroll portion shown in FIG. 2A are stacked and displayed
  • FIG. 3B is a flow diagram of the scroll portion shown in FIG. It is the tomogram which displayed the road cross-sectional shape in a laminated manner.
  • FIG. 4A is a diagram showing the aspect ratio of the scroll part (flow path) according to the present embodiment
  • FIG. 4B is the aspect ratio of the scroll part (flow path) according to the modification of the present embodiment.
  • FIG. FIG. 5A and FIG. 5B are diagrams showing an example of the analysis result of the total pressure distribution in the scroll portion using CFD
  • FIG. 5A is the analysis result for the scroll portion according to this embodiment
  • FIG. 5B shows an analysis result for the scroll unit according to the conventional technique.
  • 6 (a) and 6 (b) are diagrams showing the result of turbine element tests
  • FIG. 6 (a) shows the turbine efficiency
  • FIG. 6 (b) shows the turbine flow rate ratio.
  • FIG. 1 is a cross-sectional view showing the supercharger according to the present embodiment.
  • FIG. 2A is a plan view showing a scroll part structure according to this embodiment.
  • FIG. 2B is a plan view showing a scroll part structure according to the prior art.
  • FIG. 3A is a tomogram in which the flow path cross-sectional shapes of the scroll portion shown in FIG.
  • FIG. 3B is a tomogram in which the flow path cross-sectional shapes of the scroll portion shown in FIG.
  • the supercharger 1 includes a turbine 2 including a turbine rotor blade 21 that rotates by supply of exhaust gas, and an impeller 31 that is coaxially connected to the turbine rotor blade 21. And a compressor 3 for sucking air.
  • the turbine 2 has a scroll portion 4 as a flow path formed in a spiral shape around the rotation axis of the turbine rotor blade 21.
  • the scroll part (flow path) 4 includes an inlet part 41, an outlet part 42, and an intermediate part 43 between the inlet part 41 and the outlet part 42.
  • the aspect ratio of the channel cross-sectional shape of the intermediate portion 43 is higher than the aspect ratio of the inlet portion 41 and the outlet portion 42.
  • the aspect ratio is defined by (the axial length La of the turbine 2 having the flow path cross-sectional shape) / (the radial length Lr of the turbine 2 having the flow path cross-sectional shape).
  • the intermediate portion 43 has at least a portion having an aspect ratio of 1.8 or more.
  • the external shape of the supercharger 1 supports a turbine housing 22 that constitutes the casing of the turbine 2, a compressor housing 32 that constitutes the casing of the compressor 3, and the rotating shaft 5 that connects the turbine disk 23 and the impeller 31. And a center housing 51.
  • the scroll part 4 constitutes a part of the turbine housing 22.
  • the supercharger 1 is a so-called vehicle supercharger.
  • the supercharger 1 is also a variable capacity supercharger provided with a variable nozzle mechanism 6.
  • the variable nozzle mechanism 6 has a plurality of pivotable members arranged in a flow path between the scroll portion 4 and the turbine rotor blade 21 in order to obtain an appropriate output of the turbine 2 in accordance with the rotational speed of the engine of the vehicle.
  • a vane 61 is provided.
  • the variable nozzle mechanism 6 includes an annular shroud 62 fixed to the turbine housing 22, an annular support ring 63 supported between the turbine housing 22 and the center housing 51, and rotation between the shroud 62 and the support ring 63.
  • a plurality of vanes 61 supported in a possible manner, a drive mechanism 64 that rotates the vanes 61, and a pin 65 that maintains a distance between the shroud 62 and the support ring 63 are configured. Therefore, the portion surrounded by the shroud 62 and the support ring 63 constitutes the introduction path 7 for supplying the exhaust gas flowing through the scroll portion 4 to the turbine rotor blade 21, and a part of the shroud 62 is shown in FIG. This corresponds to the protrusion 8 shown.
  • the drive mechanism 64 is comprised by the link mechanism, for example.
  • the drive mechanism 64 is powered by an actuator (not shown) arranged outside the supercharger 1. With this power, the drive mechanism 64 can change the angle while synchronizing the plurality of vanes 61.
  • the scroll portion (flow channel) 4 is formed in a spiral shape from an inlet portion 41 having a large flow passage cross-sectional area toward an outlet portion 42 having a small flow passage cross-sectional area.
  • the curve inside the scroll part 4 is called an inner edge
  • the curve outside the scroll part 4 is called an outer edge.
  • the phase is set to 0 ° with the point where the flow direction of the exhaust gas G supplied from the inlet portion 41 coincides with the tangential direction of the outer edge constituting the scroll portion 4 as the starting point P1. It is assumed that the portion upstream of the starting point P1 forms the inlet 41, and the phase increases toward the downstream side (counterclockwise in the figure). Therefore, the inlet portion 41 corresponds to a range of about ⁇ 60 ° to 0 °, the outlet portion 42 corresponds to a range of 270 ° to about 300 °, and the intermediate portion 43 has a phase of 0 °. This corresponds to a range of ⁇ 270 °.
  • a circle C1 having a radius R is a frame size that defines the maximum outer shape given when the scroll unit 4 is designed.
  • a circle C2 having a radius r is a frame size that defines a shroud given when the scroll unit 4 is designed. Note that the sizes of the radii R and r vary depending on the type and output of the applied turbine or supercharger.
  • the outer edge of the scroll portion 4 is formed along the circle C1 from the start point P1 to the intermediate point P2 in the intermediate portion 43, for example, and extends from the intermediate point P2 to the end point P3. And formed so as to gradually decrease from the circle C1.
  • the intermediate point P2 is set, for example, within a range of 180 ° to 270 ° in phase.
  • the inner edge of the scroll portion 4 is formed along the circle C2 from the starting point Q1 toward the circle C2 and extending from the intermediate point Q2 in the intermediate portion 43 to the end point P3, for example.
  • This intermediate point Q2 is set, for example, within a range of 45 ° to 135 ° in phase.
  • the conventional scroll part 40 is generally formed so that the circle C ⁇ b> 2 is the center line of the scroll part 40. Therefore, the outer edge of the scroll part 40 is gradually reduced from the start point P1 toward the end point P3, and the inner edge of the scroll part 40 is formed so as to be gradually increased from the start point Q1 toward the end point P3.
  • the scroll portion 4 in the present embodiment has a frame outer shape, that is, a shape brought close to the circle C1. Moreover, the distance from the center of the scroll part 4 to an inner edge is larger than the scroll part 40 of a prior art. As a result, as will be described later, the protruding amount of the protruding portion 8 to the scroll portion 4 can be reduced as compared with the conventional case.
  • the scroll portions 4 and 40 are cut every phase of 30 °, and the cross section of the flow path at phase ⁇ 60 ° (ie, the plane perpendicular to the main flow).
  • the cross section S12 and the flow path cross section S13 having a phase of 300 ° are stacked and displayed.
  • the value of each phase is given as an index for a position on a reference line (for example, the central axis) along the flow path.
  • the rectangular part in a figure has shown the protrusion part 8.
  • the scroll portion 4 in the present embodiment has the axial length La of the turbine 2 having the flow path cross-sectional shape, and the axial length of the turbine 2 having the flow path cross-sectional shape of the scroll portion 40 in the prior art. It is formed longer than the length La ′. Moreover, the scroll part 4 in this embodiment is approaching the upper end part of the protrusion part 8 in the flow-path cross section S6 whose radial direction length Lr of the turbine 2 of flow-path cross-sectional shape is a phase of 90 degrees.
  • the scroll part 40 in the prior art approaches the upper end part of the protrusion part 8 in the flow path cross section S9 in which the radial length Lr of the turbine 2 having the flow path cross-sectional shape is 180 ° in phase.
  • the radial length Lr at the flow path cross section (that is, each flow path cross section at the inlet 41) of 0 ° or less is the length in the direction perpendicular to the axial length La in the flow path cross section. means.
  • the projection amount of the projection 8 is small within the range of 90 ° to 300 °, and in particular, within the range of 90 ° to 180 °, the scroll unit 40 according to the related art. This means that the protruding amount of the protruding portion 8 is smaller than that.
  • the radial length Lr of the turbine 2 having the cross-sectional shape of the flow path is made to be the radial length Lr ′ of the prior art by bringing the scroll portion 4 close to the outer shape of the frame within the phase range of 90 ° to 180 °. It can be said that the cross-sectional shape of the flow channel is extended to the axial length La in order to make the cross-sectional area shorter and to secure the cross-sectional area of the flow channel.
  • the intermediate portion 43 of the scroll portion 4 has an aspect ratio by increasing the axial length La of the turbine 2 having a channel cross-sectional shape and shortening the radial length Lr of the turbine 2 having a channel cross-sectional shape. Is configured to be high.
  • the scroll portion 4 in the present embodiment is defined by (the axial length La of the turbine 2 having the flow passage cross-sectional shape) / (the radial length Lr of the turbine 2 having the flow passage cross-sectional shape) in the intermediate portion 43.
  • the aspect ratio is higher than that of the scroll portion 40 of the prior art.
  • FIG. 4A is a diagram illustrating an aspect ratio of the scroll unit 4 according to the present embodiment.
  • FIG. 4B is a diagram illustrating the aspect ratio of the scroll unit according to the modification of the present embodiment.
  • the horizontal axis indicates the phase (°)
  • the vertical axis indicates the aspect ratio.
  • a square ( ⁇ ) indicates a numerical value of the scroll unit 4 in the present embodiment
  • a circle ( ⁇ ) indicates a numerical value of the scroll unit 40 in the prior art.
  • the aspect ratio of the scroll unit 4 in this embodiment is 1.0 (circular) at a phase of ⁇ 60 °.
  • the aspect ratio increases smoothly as the phase increases, reaches a peak value of 2.6 at a phase of 90 °, and then decreases smoothly to about 1.3 at a phase of 270 °.
  • the pressure loss of the exhaust gas flowing through the scroll part 4 can be reduced by configuring the aspect ratio with a smooth curve.
  • the aspect ratio of the scroll unit 40 in the prior art is 1.0 (circular shape) at a phase of ⁇ 60 °.
  • the aspect ratio increases as the phase increases, reaches a substantially constant value 1.7 in the phase range of 90 ° to 180 °, then decreases, and reaches about 1.1 at the phase 270 °.
  • the scroll portion 40 in the prior art has an aspect ratio of less than 1.8
  • the scroll portion 4 in the present embodiment has a portion having an aspect ratio of 1.8 or more in the intermediate portion 43.
  • the scroll portion 4 in the present embodiment is not limited to the illustrated shape, and may have a peak value of the aspect ratio within the range of the phase of 30 ° to 120 ° from the start point P1, for example.
  • the value may be set within a range of 2.0 to 3.0.
  • FIG. 4B as a modified example, a first modified example ( ⁇ ) having an aspect ratio peak value 3.0 at a phase of 60 ° and a first modified example ( ⁇ ) having an aspect ratio peak value of 2.0 at a phase of 90 °. Two modified examples ( ⁇ ) are shown.
  • the amount of protrusion of the protrusion 8 can be reduced at an early stage, and the pressure by the protrusion 8 can be reduced. Loss can be further reduced.
  • the second modification by setting the peak value of the aspect ratio downstream of the phase of 90 °, the flow path cross-sectional shape can be more smoothly deformed, and the flow path cross-sectional shape It is possible to easily reduce the pressure loss due to the change of the.
  • the scroll portion 4 in order to increase the aspect ratio, it is preferable to increase the axial length La of the turbine 2 having a channel cross-sectional shape.
  • the scroll portion 4 generally has a flange portion 44 that constitutes an engagement portion with another pipe at the inlet portion 41. If the scroll portion 4 protrudes outside the axial end line W of the flange portion 44, it may interfere with other in-vehicle components. Therefore, it is preferable that the outer shape of the scroll portion 4 is configured not to protrude from the flange portion 44.
  • the flow path cross-sectional area of the scroll part 4 is ensured by increasing the aspect ratio of the flow path cross-sectional shape at the intermediate portion 43 of the scroll part 4.
  • the flow path cross-sectional shape can be formed into a flat shape, and even if the turbine 2 is arranged so that a part of the variable nozzle mechanism 6 protrudes to the scroll portion 4, the protrusion 8 is avoided.
  • the flow path of the scroll part 4 can be formed, and the pressure loss of the fluid supplied to the turbine rotor blade 21 can be reduced.
  • FIG. 5A and FIG. 5B are diagrams illustrating an example of an analysis result of the total pressure distribution in the scroll portion using CFD (Computational Fluid Dynamics).
  • FIG. 5A shows an analysis result for the scroll unit 4 according to the present embodiment.
  • FIG. 5B shows an analysis result for the scroll unit according to the conventional technique.
  • the pressure distribution diagram exemplarily shows the case of the channel cross section S6 having a phase of 90 °.
  • the high-pressure area ⁇ is widely distributed from the central portion to the outer edge portion of the flow path cross section of the scroll portion 4 in the present embodiment, and the low-pressure area is located on the inner edge side portion. ⁇ is slightly distributed.
  • the high-pressure area ⁇ ′ is widely distributed from the central portion to the outer edge portion of the flow path cross section of the scroll portion 40 in the prior art, and the inner edge side portion.
  • the low pressure area ⁇ ′ is widely distributed.
  • the pressure distribution diagram is displayed in gray scale, but in the pressure distribution diagram of the actual CFD analysis result, the pressure distribution is displayed in color, and the red (level 1) ⁇ orange color in order from the highest pressure (Level 2) ⁇ yellow (level 3) ⁇ green (level 4) ⁇ blue (level 5) is displayed.
  • Level 1 ⁇ orange color in order from the highest pressure
  • Level 2 ⁇ yellow
  • level 3 ⁇ green
  • level 5 blue
  • the area ⁇ and the area ⁇ ′ stays in green (level 4)
  • the area ⁇ ′ reaches blue (level 5)
  • the scroll according to the present embodiment It can be visually understood that the pressure loss can be reduced in the partial structure.
  • FIGS. 6 (a) and 6 (b) are diagrams showing the result of turbine element tests.
  • FIG. 6A shows the turbine efficiency.
  • FIG. 6B shows the turbine flow rate ratio.
  • the data of the scroll part structure according to the present embodiment shown in FIGS. 2 (a) and 3 (a) is shown by squares ( ⁇ ) and solid lines, and FIGS. 2 (b) and 3 (b).
  • the turbine shaft is rotated by supplying high-pressure and high-temperature combustion gas to the turbine in a unit test facility of the turbocharger, and the pressure ratio of the turbine inlet / outlet (outlet pressure / inlet pressure) passes through the turbine.
  • the turbine efficiency is calculated by measuring the flow rate to be measured and measuring the power consumption of the coaxial compressor.
  • the horizontal axis indicates the pressure ratio
  • the vertical axis indicates the turbine efficiency (%).
  • the turbine efficiency at a high rotational speed no significant difference was found between the turbine having the scroll part structure according to the conventional technique and the turbine having the scroll part structure according to the present embodiment.
  • the turbine efficiency at a low rotational speed it can be understood that the turbine having the scroll portion structure according to this embodiment is superior to the turbine having the scroll portion structure according to the prior art by about 2 to 3 pts.
  • the low rotation speed region is a region that is always used (or passed) during operation of the supercharger (turbine), and it is very meaningful to improve the turbine efficiency in the low rotation speed region even slightly.
  • the horizontal axis indicates the pressure ratio
  • the vertical axis indicates the turbine flow rate ratio (the turbine flow rate having the scroll portion structure according to the present embodiment / the turbine flow rate having the scroll portion structure according to the prior art).
  • the turbine flow rate ratio of the turbine having the scroll portion structure according to the present embodiment is higher than that of the turbine having the scroll portion structure according to the prior art, both in the case of high speed and low speed. It can be seen that this is about 2-3% better.
  • the supercharger having the scroll part structure according to the present embodiment has the scroll part structure according to the prior art by reducing the pressure loss of the fluid supplied to the moving blade. Compared with the supercharger, the turbine efficiency can be improved and the flow rate can be increased.
  • the supercharger 1 shown in FIG. 1 is not limited to the structure shown in the figure, and is a supercharger having a different configuration of the variable nozzle mechanism 6 or a supercharger having no variable nozzle mechanism 6. Alternatively, it may be a supercharger other than those for vehicles, or may have a turbine 2 driven by a gas other than exhaust gas or a liquid such as water.

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  • Engineering & Computer Science (AREA)
  • Chemical & Material Sciences (AREA)
  • Mechanical Engineering (AREA)
  • General Engineering & Computer Science (AREA)
  • Combustion & Propulsion (AREA)
  • Chemical Kinetics & Catalysis (AREA)
  • General Chemical & Material Sciences (AREA)
  • Supercharger (AREA)

Abstract

La présente invention concerne un compresseur de suralimentation (1) équipé d'une turbine (2) et d'un compresseur (3). La turbine (2) est pourvue d'une partie en spirale (canal d'écoulement) (4) formée en forme de spirale autour de l'axe de rotation d'aubes (21) de turbine. La partie en spirale (4) présente une structure telle que le facteur de forme de la forme de section transversale du canal d'écoulement au niveau d'une partie intermédiaire (43) entre une partie admission (41) et une partie sortie (42) soit supérieur aux facteurs de forme de la partie admission (41) et de la partie sortie (42).
PCT/JP2014/067643 2013-07-05 2014-07-02 Structure de partie en spirale et compresseur de suralimentation WO2015002228A1 (fr)

Priority Applications (3)

Application Number Priority Date Filing Date Title
DE112014003154.2T DE112014003154T5 (de) 2013-07-05 2014-07-02 Spiralstruktur und Lader
CN201480031419.1A CN105392975B (zh) 2013-07-05 2014-07-02 涡旋部构造及增压器
JP2015525254A JP5954494B2 (ja) 2013-07-05 2014-07-02 スクロール部構造及び過給機

Applications Claiming Priority (2)

Application Number Priority Date Filing Date Title
JP2013141550 2013-07-05
JP2013-141550 2013-07-05

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WO2015002228A1 true WO2015002228A1 (fr) 2015-01-08

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CN (1) CN105392975B (fr)
DE (1) DE112014003154T5 (fr)
WO (1) WO2015002228A1 (fr)

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JPWO2017168629A1 (ja) * 2016-03-30 2018-12-20 三菱重工エンジン＆ターボチャージャ株式会社 ターボチャージャー
US20230020581A1 (en) * 2020-01-07 2023-01-19 Mitsubishi Heavy Industries Engine & Turbocharger, Ltd. Turbine housing and turbocharger

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EP3473832B1 (fr) * 2016-12-28 2021-09-01 Mitsubishi Heavy Industries Engine & Turbocharger, Ltd. Turbine et turbocompresseur

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JP5954494B2 (ja) 2016-07-20

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