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WO2016035329A1 - Turbine d'échappement pour turbocompresseur - Google Patents

Turbine d'échappement pour turbocompresseur Download PDF

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Publication number
WO2016035329A1
WO2016035329A1 PCT/JP2015/004442 JP2015004442W WO2016035329A1 WO 2016035329 A1 WO2016035329 A1 WO 2016035329A1 JP 2015004442 W JP2015004442 W JP 2015004442W WO 2016035329 A1 WO2016035329 A1 WO 2016035329A1
Authority
WO
WIPO (PCT)
Prior art keywords
turbine
angle
exhaust gas
attack
scroll
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.)
Ceased
Application number
PCT/JP2015/004442
Other languages
English (en)
Japanese (ja)
Inventor
石井　幹人
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.)
Denso Corp
Original Assignee
Denso Corp
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
Priority claimed from JP2015168824A external-priority patent/JP6413980B2/ja
Application filed by Denso Corp filed Critical Denso Corp
Priority to CN201580045368.2A priority Critical patent/CN106795807B/zh
Priority to DE112015004058.7T priority patent/DE112015004058T5/de
Priority to US15/508,645 priority patent/US20170292381A1/en
Publication of WO2016035329A1 publication Critical patent/WO2016035329A1/fr
Anticipated expiration legal-status Critical
Ceased legal-status Critical Current

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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
    • F01D5/00—Blades; Blade-carrying members; Heating, heat-insulating, cooling or antivibration means on the blades or the members
    • F01D5/02—Blade-carrying members, e.g. rotors
    • F01D5/04—Blade-carrying members, e.g. rotors for radial-flow machines or engines
    • 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
    • F01D17/00—Regulating or controlling by varying flow
    • F01D17/10—Final actuators
    • F01D17/12—Final actuators arranged in stator parts
    • F01D17/14—Final actuators arranged in stator parts varying effective cross-sectional area of nozzles or guide conduits
    • 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
    • F02—COMBUSTION ENGINES; HOT-GAS OR COMBUSTION-PRODUCT ENGINE PLANTS
    • F02B—INTERNAL-COMBUSTION PISTON ENGINES; COMBUSTION ENGINES IN GENERAL
    • F02B37/00—Engines characterised by provision of pumps driven at least for part of the time by exhaust
    • F02B37/12—Control of the pumps
    • F02B37/22—Control of the pumps by varying cross-section of exhaust passages or air passages, e.g. by throttling turbine inlets or outlets or by varying effective number of guide conduits
    • 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
    • Y—GENERAL TAGGING OF NEW TECHNOLOGICAL DEVELOPMENTS; GENERAL TAGGING OF CROSS-SECTIONAL TECHNOLOGIES SPANNING OVER SEVERAL SECTIONS OF THE IPC; TECHNICAL SUBJECTS COVERED BY FORMER USPC CROSS-REFERENCE ART COLLECTIONS [XRACs] AND DIGESTS
    • Y02—TECHNOLOGIES OR APPLICATIONS FOR MITIGATION OR ADAPTATION AGAINST CLIMATE CHANGE
    • Y02T—CLIMATE CHANGE MITIGATION TECHNOLOGIES RELATED TO TRANSPORTATION
    • Y02T10/00—Road transport of goods or passengers
    • Y02T10/10—Internal combustion engine [ICE] based vehicles
    • Y02T10/12—Improving ICE efficiencies

Definitions

  • the present disclosure relates to an exhaust turbine of a turbocharger having two scroll passages with different capacities.
  • Patent Document 1 is known as a prior art related to an exhaust turbine of a turbocharger.
  • the exhaust turbine disclosed in the same document 1 divides the inside of the turbine housing in the axial direction by a partition wall to form a first scroll channel having a small channel area and a second scroll channel having a large channel area,
  • a variable capacity valve that can open and close the inlet of the second scroll flow path is provided.
  • variable displacement valve In this exhaust turbine, for example, the variable displacement valve is closed in a low speed rotation region of the engine (for example, when the exhaust gas flow rate is small), and exhaust gas is intensively introduced only into the first scroll flow path. In many high-speed rotation regions, the turbine output corresponding to the exhaust gas flow rate can be obtained by opening the variable displacement valve and introducing the exhaust gas into the second scroll flow path.
  • the flow area of the first scroll flow path is different from that of the second scroll flow path. Specifically, the flow area of the first scroll flow path is 1/3 or less of the entire area. It is. In this configuration, two different flow and velocity vectors are generated in the axial direction at the inlet of the turbine blade, and the angle of the exhaust gas flow flowing into the turbine blade is also different.
  • the turbine blades are designed for the case where exhaust gas is introduced into both the first scroll passage and the second scroll passage, the exhaust gas is introduced only into the first scroll passage. In this case, turbulent flow or choke is generated, and the pressure loss is increased, so that the problem that turbine efficiency is lowered has been found.
  • the inventor has a problem in that the first scroll flow path with a small flow path area increases the friction loss on the flow path surface as compared with the second scroll flow path with a large flow path area, so that the turbine efficiency decreases. Was also found.
  • An object of the present disclosure is to provide an exhaust turbine of a turbocharger that can suppress a decrease in turbine efficiency.
  • an exhaust turbine of a turbocharger includes a turbine wheel having a plurality of turbine blades around a hub fixed to a shaft, and a turbine housing that forms a scroll passage on an outer periphery of the turbine wheel, As the exhaust gas discharged from the internal combustion engine is blown to the turbine blades through the scroll passage, the turbine wheel rotates, and the turbine housing divides the scroll passage into one side and the other side in the axial direction.
  • the first scroll flow path is formed on the side
  • the second scroll flow path is formed on the other side
  • the exhaust gas flow rate blown to the turbine blades through the first scroll flow path passes through the second scroll flow path to the turbine.
  • the angle of attack of the turbine blade set on one side of the direction is called the first angle of attack
  • the angle of attack of the turbine blade set on the other side in the axial direction corresponding to the second scroll flow path is the second angle of attack.
  • the first angle of attack is It is set according to the relative inflow angle of the exhaust gas blown to the turbine blade through the scroll flow path
  • the second angle of attack is the relative inflow angle of the exhaust gas blown to the turbine blade through the second scroll flow path.
  • the flow rate of the exhaust gas blown to the turbine blade through the first scroll flow path is set smaller than the flow rate of the exhaust gas blown to the turbine blade through the second scroll flow path. For this reason, the relative inflow angle of the exhaust gas differs between one axial side corresponding to the first scroll passage and the other axial side corresponding to the second scroll passage at the inlet of the turbine blade.
  • FIG. 1 is a perspective view of a turbine wheel according to a first embodiment of the present disclosure
  • FIG. 2 is a cross-sectional view showing a first angle of attack and a second angle of attack set on the turbine blade
  • FIG. 3 is a cross-sectional view of the exhaust turbine according to the first embodiment.
  • FIG. 4 is an overall configuration diagram showing an intake / exhaust system of an engine including a turbocharger
  • FIG. 5 is an explanatory view showing a speed triangle of exhaust gas
  • FIG. 6 is an explanatory diagram showing the relationship between the first angle of attack and the second angle of attack
  • FIG. 4 is an overall configuration diagram showing an intake / exhaust system of an engine including a turbocharger
  • FIG. 5 is an explanatory view showing a speed triangle of exhaust gas
  • FIG. 6 is an explanatory diagram showing the relationship between the first angle of attack and the second angle of attack
  • FIG. 7 is a perspective view of a turbine blade according to a second embodiment of the present disclosure
  • FIG. 8 is a cross-sectional view of an exhaust turbine according to a third embodiment of the present disclosure
  • FIG. 9 is a cross-sectional view of an exhaust turbine according to Example 4 of the present disclosure
  • FIG. 10 is a cross-sectional view of the exhaust turbine according to the fifth embodiment of the present disclosure.
  • the turbocharger 1 As shown in FIG. 4, the turbocharger 1 according to the first embodiment includes an exhaust turbine 4 disposed on the downstream side of the exhaust manifold 3 in the exhaust path of the engine 2, and an upstream side of the intake manifold 5 in the intake path of the engine 2. And an intake air compressor 6 disposed in the.
  • the exhaust turbine 4 includes a turbine housing 7 that introduces exhaust gas through the exhaust manifold 3 and a turbine wheel 8 that is housed inside the turbine housing 7 and converts the kinetic energy of the exhaust gas into rotational force.
  • the turbine wheel 8 is a radial turbine that discharges exhaust gas flowing in from the outer periphery in the radial direction in the axial direction.
  • an exhaust purification device 9 that removes harmful substances contained in the exhaust gas, a muffler 10 that is a silencer, and the like are disposed.
  • the exhaust turbine 4 is provided with a waste gate mechanism that can adjust the flow rate of exhaust gas flowing into the turbine wheel 8.
  • the waste gate mechanism includes, for example, an exhaust bypass passage 11 that connects the exhaust upstream side and the exhaust downstream side of the turbine housing 7 to bypass the turbine wheel 8, and a waste gate valve 12 that can open and close the exhaust bypass passage 11.
  • the waste gate valve 12 opens when the pressure of the air sent to the engine 2 (supercharging pressure) exceeds a certain value.
  • the waste gate mechanism may be a built-in type in which an exhaust bypass passage 11 is formed in the turbine housing 7 and a waste gate valve 12 is incorporated, or an external type configured independently of the exhaust turbine 4.
  • the intake compressor 6 includes a compressor wheel 14 connected to the turbine wheel 8 via the turbine shaft 13 and a compressor housing 15 that houses the compressor wheel 14 therein. When the compressor wheel 14 is rotated by the rotation of the turbine wheel 8, the intake compressor 6 compresses the air introduced into the compressor housing 15 and forcibly feeds it into the engine 2.
  • An air cleaner 16 that filters air taken in by the engine 2 is provided in the intake path upstream of the intake compressor 6.
  • an intercooler 17 that cools the air compressed by the intake compressor 6 is disposed in the intake path downstream of the intake compressor 6, and an electronic throttle device 18 that adjusts the intake air amount downstream of the intercooler 17 and the like. Is disposed.
  • the turbine housing 7 has a spiral scroll passage 19 formed on the outer periphery of the turbine wheel 8, and as shown in FIG. 3, the scroll passage 19 is separated by a partition wall 7a on one side and the other side in the axial direction (left-right direction in the drawing). It is divided into and.
  • the first scroll channel 19a is more than the second scroll channel 19b.
  • the capacity is small.
  • the side opposite to the direction in which the exhaust gas flows out from the turbine wheel 8 (the left side in the figure) is defined as one side in the axial direction, and the same side as the direction in which the exhaust gas flows out (the right side in the figure) is the axial direction. It is defined as the other side.
  • a variable capacity valve 20 (see FIG. 4) that varies the capacity of the exhaust turbine 4 by adjusting the flow rate of the exhaust gas introduced into the second scroll flow path 19b is disposed at the inlet of the second scroll flow path 19b.
  • the variable displacement valve 20 is controlled in valve opening according to the operating state of the engine 2. For example, the valve opening is controlled to be small during low speed and low load operation, and the valve opening is controlled to be large during high speed and high load operation.
  • the variable displacement valve 20 is closed and the inlet of the second scroll passage 19b is closed, the exhaust gas discharged from the engine 2 is introduced only into the first scroll passage 19a, and the variable displacement valve 20 is opened.
  • the variable capacity valve 20 is a flow rate adjusting unit.
  • the turbine wheel 8 includes a hub 21 fixed to the turbine shaft 13 (see FIG. 4) and a plurality of turbine blades 22 provided around the hub 21.
  • the hub 21 is provided such that the hub radius, which is a height in the radial direction perpendicular to the axial center of the turbine wheel 8, decreases in a quadratic curve from the inlet side to the outlet side of the exhaust gas with respect to the turbine wheel 8. .
  • the turbine blades 22 have different angles of attack on one side in the axial direction corresponding to the first scroll flow path 19a and on the other side in the axial direction corresponding to the second scroll flow path 19b.
  • the angle of attack is an angle formed by the front edge direction and the reference line. 2 shows a cross-sectional shape along the longitudinal direction of the turbine blade 22 and corresponds to the IIa-IIa cross section and the IIb-IIb cross section of FIG.
  • the leading edge direction is a direction in which a curve of a blade thickness center line (a line indicated by a one-dot chain line in FIG. 2) in a cross section along the longitudinal direction of the turbine blade 22 extends in the outer diameter direction at the blade tip.
  • the leading edge direction is the direction of the tangent to the center line at the blade tip.
  • the blade end on the inlet side of the turbine blade 22 is referred to as a leading edge 22a.
  • the reference line is a line extending in the radial direction of the turbine wheel 8 through the leading edge 22a.
  • the angle of attack set on one side in the axial direction is referred to as a first angle of attack ⁇ 1
  • the angle of attack set on the other side in the axial direction is referred to as a second angle of attack ⁇ 2.
  • the angle of attack of the turbine blade 22 is set corresponding to the relative inflow angle of the exhaust gas blown to the turbine blade 22. That is, the first angle of attack ⁇ 1 is set according to the relative inflow angle of the exhaust gas blown to the turbine blades 22 from the first scroll channel 19a, and the second angle of attack ⁇ 2 is determined from the second scroll channel 19b. It is set according to the relative inflow angle of the exhaust gas blown to the turbine blade 22.
  • the relative exhaust gas inflow angle is an inflow angle of exhaust gas flowing into the inlet of the turbine blade 22 when the radial direction is set to 0 ° in the rotating coordinate system of the turbine wheel 8. That is, the angle ⁇ formed by the relative velocity vector and the reference line in the velocity triangle shown in FIG. Further, c represents the absolute speed of the exhaust gas, u represents the peripheral speed of the turbine blade 22, and w represents the relative speed of the exhaust gas.
  • the angle of attack of the turbine blade 22 with respect to the relative inflow angle ⁇ (see FIG. 5A) when the relative speed w has a vector in the rotational direction of the turbine wheel 8 with respect to the reference line (the arrow direction in the figure). Expressed as a positive angle.
  • the angle of attack of the turbine blade 22 with respect to the relative inflow angle ⁇ (see FIG. 5B) when the relative speed w has a vector in the counter-rotating direction of the turbine wheel 8 with respect to the reference line is expressed as a negative angle.
  • a positive angle and a negative angle when compared, it is defined that the angle of attack having a positive angle is larger than the angle of attack having a negative angle, not the size of the angle itself. For example, at +10 degrees and -30 degrees, +10 degrees is greater.
  • the turbine blade 22 of the present disclosure is formed such that the average value of the first angle of attack ⁇ 1 is larger than the average value of the second angle of attack ⁇ 2.
  • (A) of the figure shows the case where the average value of the first angle of attack ⁇ 1 and the average value of the second angle of attack ⁇ 2 are both positive.
  • FIG. 5B shows a case where the average value of the first angle of attack ⁇ 1 and the average value of the second angle of attack ⁇ 2 both have negative angles, and the average value of the first angle of attack ⁇ 1 is the first value.
  • the negative angle is smaller than the average value of the two angle of attack ⁇ 2, that is, the average value of the first angle of attack ⁇ 1 is larger than the average value of the second angle of attack ⁇ 2.
  • FIG. 5C shows the case where the average value of the first angle of attack ⁇ 1 has a positive angle and the average value of the second angle of attack ⁇ 2 is zero.
  • FIG. 4D shows the case where the average value of the first angle of attack ⁇ 1 is zero and the average value of the second angle of attack ⁇ 2 is a negative angle.
  • FIGS. 4E to 4G show the case where the average value of the first angle of attack ⁇ 1 has a positive angle and the average value of the second angle of attack ⁇ 2 has a negative angle.
  • the average value of the first angle of attack ⁇ 1 that is an angle of the second angle is larger than the average value of the second angle of attack ⁇ 2 that is a negative angle.
  • the average value of the first angle of attack ⁇ 1 is the first angle of attack ⁇ 1 in the magnitude relationship between the average value of the first angle of attack ⁇ 1 and the average value of the second angle of attack ⁇ 2.
  • the second angle of attack has a negative angle. It is larger than the average value of the angle ⁇ 2.
  • FIG. 1 An example corresponding to the above figure (e) is shown in FIG. 1 and FIG.
  • the leading edge 22a is formed in a substantially straight line on one side (the lower side in the drawing) and the other side in the axial direction, and as shown in FIG.
  • the first angle of attack ⁇ 1 having a larger angle is formed larger than the second angle of attack ⁇ 2 having a negative angle.
  • subjected to FIG. 1, FIG. 2 has shown the rotation direction of the turbine wheel 8.
  • the first angle of attack ⁇ 1 and the second angle of attack ⁇ 2 do not change clearly between one side and the other side in the axial direction, but change smoothly. That is, there is an angle of attack of zero angle between the one side and the other side in the axial direction, and the first angle of attack ⁇ 1 is on the one side in the axial direction from the angle of attack of zero angle to the hub side of the leading edge 22a.
  • the second angle of attack ⁇ 2 is gradually decreased toward the opposite hub side of the leading edge 22a (negative angle is gradually increased) on the other side in the axial direction. Accordingly, it can be said that the turbine blade 22 shown in FIG. 1 is formed such that the average value of the first angle of attack ⁇ 1 having a positive angle is larger than the average value of the second angle of attack ⁇ 2 having a negative angle.
  • the first scroll passage 19a is formed to have a smaller capacity than the second scroll passage 19b.
  • the relative inflow angle of the exhaust gas is different at the inlet of the turbine blade 22 between the one axial side corresponding to the first scroll passage 19a and the other axial side corresponding to the second scroll passage 19b.
  • the turbine blade 22 has different angles of attack depending on the relative inflow angles on one side and the other side in the axial direction. Specifically, the first angle of attack ⁇ 1 is set on one side in the axial direction, the second angle of attack ⁇ 2 is set on the other side in the axial direction, and the average value of the first angle of attack ⁇ 1 is the second angle of attack.
  • the turbine blade 22 has a leading edge 22a formed substantially linearly on one side and the other side in the axial direction, and the second scroll channel on one side in the axial direction corresponding to the first scroll channel 19a.
  • the angle of attack is larger than the other side in the axial direction corresponding to 19b. That is, since the average value of the first angle of attack ⁇ 1 is larger than the average value of the second angle of attack ⁇ 2, the average value of the first angle of attack ⁇ 1 is smaller than the average value of the second angle of attack ⁇ 2. Compared with the case, the manufacture of the turbine blade 22 is easier.
  • the turbine blade 22 has an angle of attack of zero angle between one side and the other side in the axial direction, and the first angle of attack ⁇ 1 gradually increases on one side in the axial direction across the angle of attack of zero angle.
  • the second angle of attack ⁇ 2 is gradually reduced on the other side in the axial direction. That is, since the first angle of attack ⁇ 1 and the second angle of attack ⁇ 2 are smoothly changed across the angle of attack of zero angle, it is possible to provide a turbine blade 22 that is less stress concentrated and easy to manufacture. . Moreover, since the angle of attack changes smoothly, the flow of exhaust gas also becomes smooth, which contributes to the improvement of turbine efficiency.
  • the second embodiment is an example in which the leading edge 22a of the turbine blade 22 is shifted in the circumferential direction between one axial side (the lower side in the drawing) and the other side.
  • the circumferential position of the leading edge 22a is formed on the counter-rotation direction side on one side in the axial direction having the first angle of attack ⁇ 1 and on the other side in the axial direction having the second angle of attack ⁇ 2.
  • the average value of the first angle of attack ⁇ 1 is set larger than the average value of the second angle of attack ⁇ 2, as in the first embodiment.
  • the average of the first angle of attack ⁇ 1 The angle difference between the value and the average value of the second angle of attack ⁇ 2 can be made larger.
  • Example 3 The third embodiment is an example in which a partition plate 23 is provided on the turbine blade 22 as shown in FIG.
  • the partition plate 23 has an exhaust gas on one side blown to the turbine blades 22 through the first scroll flow path 19a and an exhaust gas on the other side blown to the turbine blades 22 through the second scroll flow path 19b.
  • the trailing edge 22b refers to the blade end portion on the outlet side of the turbine blade 22.
  • the effect of the reinforcement rib with respect to the turbine blade 22 can also be expected by providing the partition plate 23.
  • Example 4 As shown in FIG. 9, the fourth embodiment is an example in which fixed nozzles are arranged at the outlets of the first scroll flow path 19a and the second scroll flow path 19b. Example 2 can be applied.
  • the fixed nozzle includes a first fixed nozzle 24 disposed at the outlet of the first scroll passage 19a and a second fixed nozzle 25 disposed at the outlet of the second scroll passage 19b.
  • a nozzle plate 26 is disposed between the fixed nozzle 24 and the second fixed nozzle 25. That is, the first fixed nozzle 24 is disposed on one side in the axial direction with the nozzle plate 26 interposed therebetween, and the second fixed nozzle 25 is disposed on the other side in the axial direction.
  • the nozzle plate 26 is arranged so that the exhaust gas passing through the first fixed nozzle 24 and the exhaust gas passing through the second fixed nozzle 25 flow independently of each other.
  • a space with the fixed nozzle 25 is partitioned in the axial direction.
  • first fixed nozzle 24 and the second fixed nozzle 25 a plurality of nozzle vanes are arranged in the circumferential direction with a predetermined interval, and the throat area of the first fixed nozzle 24 is the second fixed nozzle.
  • the throat area is smaller than 25.
  • the throat area is a minimum flow path area formed between nozzle vanes adjacent in the circumferential direction.
  • the first fixed nozzle 24 has more nozzle vanes than the second fixed nozzle 25, or The throat area can be reduced by increasing the inclination of the nozzle vane with respect to the radial direction. As a result, the exhaust gas flow rate passing through the first fixed nozzle 24 is less than the exhaust gas flow rate passing through the second fixed nozzle 25.
  • the capacity of the first scroll channel 19a is made smaller than the capacity of the second scroll channel 19b. do not have to.
  • the first scroll channel 19a and the second scroll channel 19b can be formed to have the same capacity.
  • the nozzle plate 26 is disposed between the first fixed nozzle 24 and the second fixed nozzle 25, the exhaust gas that passes through the first fixed nozzle 24 and the second fixed nozzle 25 pass through.
  • the first fixed nozzle 24 and the second fixed nozzle 25 can form independent flows without interfering with the exhaust gas.
  • Example 5 The fifth embodiment is an example in which the turbine radius differs between a portion corresponding to the first scroll passage 19a and a portion corresponding to the second scroll passage 19b of the turbine blade 22.
  • the turbine radius refers to the distance from the axial center of the turbine wheel 8 to the leading edge 22a of the turbine blade 22 indicated by a one-dot chain line in FIG.
  • the turbine blade 22 has a large turbine radius on one side in the axial direction corresponding to the first scroll flow path 19a, and a small turbine radius on the other side in the axial direction corresponding to the second scroll flow path 19b. That is, when the turbine radius of the part corresponding to the first scroll flow path 19a is the first radius r1, and the turbine radius of the part corresponding to the second scroll flow path 19b is the second radius r2, as shown in FIG. The relationship that one radius r1 is larger than the second radius r2 is established.
  • the relative inflow angle can be made closer.
  • generation of turbulent flow or choke can be further suppressed than in the above-described embodiments, and separation loss in the turbine wheel 8 can be suppressed, so that turbine efficiency can be improved.
  • the first scroll channel 19a is formed on one side in the axial direction and the second scroll channel 19b is formed on the other side in the axial direction.
  • the first scroll channel 19a and the second scroll are formed.
  • the turbine blade 22 has a second angle of attack ⁇ 2 set on one side in the axial direction and a first angle of attack ⁇ 1 set on the other side in the axial direction, but the average of the first angle of attack ⁇ 1 The value is set larger than the average value of the second angle of attack ⁇ 2 as in the first embodiment.
  • the present disclosure can be applied even if the first scroll channel 19a and the second scroll channel 19b have the same size and positional relationship. In this case, it is possible to correct the difference in inflow angle due to manufacturing variations.
  • the throat area of the first fixed nozzle 24 arranged on one side in the axial direction is smaller than that of the second fixed nozzle 25 arranged on the other side in the axial direction.
  • the present disclosure can be applied to a configuration in which the throat area of the second fixed nozzle 25 is smaller than that of the fixed nozzle 24.
  • the turbine blade 22 has a first angle of attack ⁇ 1 set on the other axial side corresponding to the second fixed nozzle 25 having a small throat area, and corresponds to the first fixed nozzle 24 having a large throat area.
  • a second angle of attack ⁇ 2 is set on one side in the axial direction.
  • the average value of the first angle of attack ⁇ 1 is set larger than the average value of the second angle of attack ⁇ 2, as in the first embodiment.

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

Abstract

Dans la présente invention, différents angles d'attaque sont définis pour des aubes (22) de turbine sur un côté et sur l'autre côté dans une direction axiale selon un angle d'entrée relative de gaz d'échappement. En d'autres termes, un premier angle d'attaque (θ1) est défini sur un côté dans la direction axiale conformément à l'angle d'entrée relative du gaz d'échappement dirigé vers les aubes de turbine à travers un premier passage en volute (19a), et un second angle d'attaque (θ2) est défini sur l'autre côté dans la direction axiale conformément à l'angle d'entrée relative du gaz d'échappement dirigé vers la turbine à travers un second passage en volute (19b).
PCT/JP2015/004442 2014-09-04 2015-09-01 Turbine d'échappement pour turbocompresseur Ceased WO2016035329A1 (fr)

Priority Applications (3)

Application Number Priority Date Filing Date Title
CN201580045368.2A CN106795807B (zh) 2014-09-04 2015-09-01 涡轮增压机的排气涡轮
DE112015004058.7T DE112015004058T5 (de) 2014-09-04 2015-09-01 Abgasturbine für Turbolader
US15/508,645 US20170292381A1 (en) 2014-09-04 2015-09-01 Exhaust turbine for turbocharger

Applications Claiming Priority (4)

Application Number Priority Date Filing Date Title
JP2014180610 2014-09-04
JP2014-180610 2014-09-04
JP2015168824A JP6413980B2 (ja) 2014-09-04 2015-08-28 ターボチャージャの排気タービン
JP2015-168824 2015-08-28

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WO2016035329A1 true WO2016035329A1 (fr) 2016-03-10

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PCT/JP2015/004442 Ceased WO2016035329A1 (fr) 2014-09-04 2015-09-01 Turbine d'échappement pour turbocompresseur

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Cited By (10)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
WO2017189291A1 (fr) * 2016-04-25 2017-11-02 Borgwarner Inc. Roue de turbine pour turbine
EP3412892A4 (fr) * 2016-03-31 2019-01-23 Mitsubishi Heavy Industries Engine & Turbocharger, Ltd. Aube de machine rotative, compresseur d'alimentation et procédé de formation de champ d'écoulement de celle-ci
WO2020003649A1 (fr) * 2018-06-29 2020-01-02 株式会社Ihi Turbine et compresseur de suralimentation
US10662904B2 (en) 2018-03-30 2020-05-26 Deere & Company Exhaust manifold
JP2020200836A (ja) * 2017-02-22 2020-12-17 株式会社Ihi 過給機
US11073076B2 (en) 2018-03-30 2021-07-27 Deere & Company Exhaust manifold
CN113614344A (zh) * 2019-04-01 2021-11-05 株式会社Ihi 可变容量型增压器
CN116753035A (zh) * 2023-07-17 2023-09-15 广东信稳能控技术研究有限公司 绿环空调低压涡轮机构
CN116964306A (zh) * 2021-04-20 2023-10-27 株式会社Ihi 可变容量型增压器
WO2025062122A1 (fr) * 2023-09-18 2025-03-27 Cummins Ltd Turbocompresseur et système de pile à combustible

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US11041505B2 (en) 2016-03-31 2021-06-22 Mitsubishi Heavy Industries Engine & Turbocharger, Ltd. Rotary machine blade, supercharger, and method for forming flow field of same
EP3412892A4 (fr) * 2016-03-31 2019-01-23 Mitsubishi Heavy Industries Engine & Turbocharger, Ltd. Aube de machine rotative, compresseur d'alimentation et procédé de formation de champ d'écoulement de celle-ci
CN109072698A (zh) * 2016-04-25 2018-12-21 博格华纳公司 用于涡轮机的涡轮机叶轮
CN109072698B (zh) * 2016-04-25 2022-02-18 博格华纳公司 用于涡轮机的涡轮机叶轮
US11220908B2 (en) 2016-04-25 2022-01-11 Borgwarner Inc. Turbine wheel for a turbine
WO2017189291A1 (fr) * 2016-04-25 2017-11-02 Borgwarner Inc. Roue de turbine pour turbine
JP2020200836A (ja) * 2017-02-22 2020-12-17 株式会社Ihi 過給機
JP7036173B2 (ja) 2017-02-22 2022-03-15 株式会社Ihi 過給機
US10662904B2 (en) 2018-03-30 2020-05-26 Deere & Company Exhaust manifold
US11073076B2 (en) 2018-03-30 2021-07-27 Deere & Company Exhaust manifold
US11384716B2 (en) 2018-03-30 2022-07-12 Deere & Company Exhaust manifold
US11486297B2 (en) 2018-03-30 2022-11-01 Deere & Company Exhaust manifold
JPWO2020003649A1 (ja) * 2018-06-29 2021-06-03 株式会社Ihi タービンおよび過給機
WO2020003649A1 (fr) * 2018-06-29 2020-01-02 株式会社Ihi Turbine et compresseur de suralimentation
US11261746B2 (en) 2018-06-29 2022-03-01 Ihi Corporation Turbine and turbocharger
CN113614344A (zh) * 2019-04-01 2021-11-05 株式会社Ihi 可变容量型增压器
CN113614344B (zh) * 2019-04-01 2023-06-06 株式会社Ihi 可变容量型增压器
US11686244B2 (en) 2019-04-01 2023-06-27 Ihi Corporation Variable-capacity turbocharger
CN116964306A (zh) * 2021-04-20 2023-10-27 株式会社Ihi 可变容量型增压器
CN116753035A (zh) * 2023-07-17 2023-09-15 广东信稳能控技术研究有限公司 绿环空调低压涡轮机构
WO2025062122A1 (fr) * 2023-09-18 2025-03-27 Cummins Ltd Turbocompresseur et système de pile à combustible

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