WO2024095525A1 - タービン - Google Patents

タービン Download PDF

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Publication number
WO2024095525A1
WO2024095525A1 PCT/JP2023/022643 JP2023022643W WO2024095525A1 WO 2024095525 A1 WO2024095525 A1 WO 2024095525A1 JP 2023022643 W JP2023022643 W JP 2023022643W WO 2024095525 A1 WO2024095525 A1 WO 2024095525A1
Authority
WO
WIPO (PCT)
Prior art keywords
impeller
turbine
scroll passage
housing
central axis
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/JP2023/022643
Other languages
English (en)
French (fr)
Japanese (ja)
Inventor
拓郎 桐明
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.)
IHI Corp
Original Assignee
IHI 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
Application filed by IHI Corp filed Critical IHI Corp
Priority to DE112023003534.2T priority Critical patent/DE112023003534T5/de
Priority to CN202380064936.8A priority patent/CN119895129A/zh
Priority to JP2024554110A priority patent/JPWO2024095525A1/ja
Publication of WO2024095525A1 publication Critical patent/WO2024095525A1/ja
Priority to US19/071,859 priority patent/US20250198310A1/en
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
    • F01D25/00—Component parts, details, or accessories, not provided for in, or of interest apart from, other groups
    • F01D25/24—Casings; Casing parts, e.g. diaphragms, casing fastenings
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F01—MACHINES OR ENGINES IN GENERAL; ENGINE PLANTS IN GENERAL; STEAM ENGINES
    • F01D—NON-POSITIVE DISPLACEMENT MACHINES OR ENGINES, e.g. STEAM TURBINES
    • 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
    • F05D2240/00—Components
    • F05D2240/10—Stators
    • F05D2240/14—Casings or housings protecting or supporting assemblies within
    • 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
    • F05D2250/00—Geometry
    • F05D2250/50—Inlet or outlet
    • F05D2250/52—Outlet
    • 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
    • F05D2250/00—Geometry
    • F05D2250/70—Shape
    • F05D2250/75—Shape given by its similarity to a letter, e.g. T-shaped

Definitions

  • the turbine may have two scroll passages arranged along the central axial direction of the impeller.
  • Patent Document 1 discloses a twin-scroll turbocharger equipped with such a turbine.
  • the shape of the outlet portion of the front scroll is adjusted to improve supercharging efficiency.
  • the objective of this disclosure is to provide a turbine that can improve turbine efficiency.
  • a turbine includes an impeller, a housing that accommodates the impeller, and a housing outlet that is spaced apart from the impeller in the direction of the central axis of the impeller and that discharges fluid that has passed through the impeller, a first scroll passage located outside the impeller in the radial direction of the impeller and that guides fluid to the impeller, and a second scroll passage located outside the impeller in the radial direction and closer to the housing outlet relative to the first scroll passage in the direction of the central axis and that guides fluid to the impeller, the second scroll passage inclined with respect to the radial direction in a cross section that is parallel to the central axis of the impeller and includes the central axis so as to move away from the housing outlet in the central axis direction as it approaches the impeller in the radial direction, and in the cross section, a region that includes the outlet of the second scroll passage includes a first portion having a linear shape parallel to the radial direction and a
  • the first and second parts may have a cast surface.
  • the first scroll passage and the second scroll passage may be directly connected to the space that houses the impeller.
  • This disclosure makes it possible to improve turbine efficiency.
  • FIG. 1 is a schematic cross-sectional view of a turbocharger including a turbine according to an embodiment.
  • FIG. 2 is an enlarged cross-sectional view showing an area A in FIG.
  • FIG. 3 is an enlarged cross-sectional view showing a turbine according to a first comparative example.
  • FIG. 4 is an enlarged cross-sectional view showing a turbine according to a second comparative example.
  • FIG. 5 is an enlarged cross-sectional view showing the analysis results of entropy of the turbines according to the embodiment, the first comparative example, and the second comparative example.
  • FIG. 6 is a graph showing an analysis result of the turbine efficiency of the turbines according to the embodiment, the first comparative example, and the second comparative example.
  • FIG. 1 is a schematic cross-sectional view of a turbocharger TC equipped with a turbine T according to an embodiment.
  • FIG. 1 shows a cross section parallel to and including the central axes of a shaft 1, a turbine impeller 2, and a compressor impeller 3.
  • the turbine T is incorporated into the turbocharger TC.
  • the turbine T may be incorporated into a device other than the turbocharger TC, or may be a standalone unit.
  • the turbocharger TC comprises a shaft 1, a turbine impeller (impeller) 2, and a compressor impeller 3.
  • the shaft 1, the turbine impeller 2, and the compressor impeller 3 rotate integrally. Therefore, in this disclosure, the "central axial direction,” “radial direction,” and “circumferential direction” of the shaft 1, the turbine impeller 2, and the compressor impeller 3 may be referred to simply as the “central axial direction,” “radial direction,” and “circumferential direction,” respectively.
  • the turbocharger TC includes a bearing housing 4, a turbine housing (housing) 5, and a compressor housing 6.
  • the turbine housing 5 is connected to a first end face of the bearing housing 4 in the central axis direction, which is the left end face in FIG. 1.
  • the compressor housing 6 is connected to a second end face of the bearing housing 4 in the central axis direction, which is the right end face in FIG. 1.
  • the bearing housing 4 includes a bearing hole 4a.
  • the bearing hole 4a extends in the central axis direction within the bearing housing 4.
  • the bearing hole 4a accommodates the bearing 7.
  • two full-floating bearings spaced apart in the central axis direction are shown as an example of the bearing 7.
  • the bearing 7 may be a semi-floating bearing or another radial bearing such as a rolling bearing.
  • the bearing 7 rotatably supports the shaft 1.
  • the turbine impeller 2 is provided at a first end of the shaft 1 in the central axial direction, which is the left end in FIG. 1.
  • the turbine impeller 2 rotates integrally with the shaft 1.
  • the turbine impeller 2 is rotatably housed within the turbine housing 5.
  • the compressor impeller 3 is provided at a second end of the shaft 1 opposite the first end in the central axial direction, which is the right end in FIG. 1.
  • the compressor impeller 3 rotates integrally with the shaft 1.
  • the compressor impeller 3 is rotatably housed within the compressor housing 6.
  • the compressor housing 6 includes an air intake 6a on the end face opposite the bearing housing 4 in the central axis direction.
  • the air intake 6a is spaced apart from the compressor impeller 3 in the central axis direction.
  • the air intake 6a is connected to an air cleaner (not shown).
  • the bearing housing 4 and the compressor housing 6 define a diffuser passage 60 therebetween.
  • the diffuser passage 60 has an annular shape around the compressor impeller 3.
  • the diffuser passage 60 is in fluid communication with the intake port 6a via the compressor impeller 3.
  • the compressor housing 6 includes a scroll passage 61.
  • the scroll passage 61 is located radially outward of the diffuser passage 60.
  • the scroll passage 61 is in fluid communication with the diffuser passage 60.
  • the scroll passage 61 is also in fluid communication with an intake port of the engine (not shown).
  • the scroll passage 61 has a generally spiral shape.
  • the compressor housing 6 As described above, when the compressor impeller 3 rotates, air is drawn into the compressor housing 6 through the intake port 6a. As the air passes through the compressor impeller 3, it is accelerated and pressurized by centrifugal force. The air is further pressurized in the diffuser passage 60 and the scroll passage 61. The pressurized air flows out from an outlet (not shown) and is led to the intake port of the engine. In the turbocharger TC, the portion including the compressor impeller 3 and the compressor housing 6 functions as a centrifugal compressor C.
  • the turbine housing 5 includes an exhaust port (housing outlet) 5a on the end face opposite the bearing housing 4 in the central axis direction.
  • the exhaust port 5a is spaced apart from the turbine impeller 2 in the central axis direction.
  • the exhaust port 5a is connected to an exhaust gas purification device (not shown).
  • the turbine housing 5 includes a space S that houses the turbine impeller 2. Specifically, the turbine housing 5 includes a shroud 5b that faces the blades 21 of the turbine impeller 2. The shroud 5b faces radially inward and defines at least a portion of the space S. The space S is in fluid communication with the exhaust port 5a.
  • the turbine housing 5 includes a first scroll passage 51 and a second scroll passage 52 arranged along the central axis direction.
  • a turbine T may also be called a "twin scroll turbine.”
  • the first scroll passage 51 and the second scroll passage 52 are located radially outward relative to the turbine impeller 2 and the space S.
  • the second scroll passage 52 is located closer to the exhaust port 5a than the first scroll passage 51 in the central axis direction.
  • the first scroll passage 51 and the second scroll passage 52 have a roughly spiral shape.
  • the first scroll passage 51 and the second scroll passage 52 are connected to an inlet that is fluidly connected to the exhaust port of the engine (not shown).
  • the first scroll passage 51 and the second scroll passage 52 receive exhaust gas from the engine.
  • the first scroll passage 51 and the second scroll passage 52 are connected to the space S in parallel with each other.
  • first scroll passage 51 and the second scroll passage 52 there are no vanes between the first scroll passage 51 and the second scroll passage 52 and the turbine impeller 2 to adjust the flow of exhaust gas.
  • first scroll passage 51 and the second scroll passage 52 are directly connected to the space S. Therefore, in this embodiment, each of the first scroll passage 51 and the second scroll passage 52 directly faces the turbine impeller 2 in the radial direction.
  • first scroll passage 51 extends generally parallel to the radial direction in the cross section of FIG. 1.
  • the second scroll passage 52 inclines with respect to the radial direction so as to move away from the exhaust port 5a in the central axial direction as it approaches the turbine impeller 2 in the radial direction in the cross section of FIG. 1.
  • exhaust gas from the engine is received by the first scroll passage 51 and the second scroll passage 52.
  • the exhaust gas is guided by the first scroll passage 51 and the second scroll passage 52 to the turbine impeller 2 and further to the exhaust port 5a.
  • the exhaust gas rotates the turbine impeller 2 while passing through it.
  • the rotational force of the turbine impeller 2 is transmitted to the compressor impeller 3 via the shaft 1.
  • the compressor impeller 3 rotates, air is taken in from the intake port 6a and is accelerated and pressurized by the compressor impeller 3, as described above.
  • the portion including the turbine impeller 2 and the turbine housing 5 functions as the turbine T.
  • FIG. 2 is an enlarged cross-sectional view showing region A in FIG. 1, and shows the region including the outlet 54 of the second scroll passage 52.
  • the outlet 54 is the section of the second scroll passage 52 that is closest to the space S.
  • FIG. 2 shows a cross section that is parallel to and includes the central axis of the turbine impeller 2.
  • the second scroll passage 52 includes a surface 53 connected to the shroud 5b.
  • the surface 53 faces radially outward.
  • the region including the outlet 54 of the second scroll passage 52 includes a first portion P1 and a second portion P2. From another perspective, the first portion P1 and the second portion P2 are located between the surface 53 and the shroud 5b, and the surface 53 and the shroud 5b are connected to each other via the first portion P1 and the second portion P2.
  • the first portion P1 has a linear shape parallel to the radial direction in the cross section of FIG. 2.
  • the first portion P1 is located radially outward from the shroud 5b.
  • the first portion P1 is formed continuously with the shroud 5b.
  • the second portion P2 has an R-shape in the cross section of FIG. 2. Therefore, the second portion P2 has a rounded shape (arc shape).
  • the second portion P2 is located radially outward from the first portion P1.
  • the second portion P2 is formed continuously with the first portion P1.
  • the turbine housing 5 including the first portion P1 and the second portion P2 can be manufactured as follows. First, the turbine housing 5 is formed by casting. For example, the first scroll passage 51 and the second scroll passage 52 can be formed using a core. Then, the shroud 5b is finished by machining. During machining, the first portion P1 and the second portion P2 are not machined. Therefore, the first portion P1 and the second portion P2 of the turbine housing 5 as a finished product have a cast surface. For example, when the first portion P1 and the second portion P2 are machined, it is difficult to machine the boundary between the second portion P2 and the region in the second scroll passage 52 smoothly. Such difficult machining increases the manufacturing cost.
  • the first portion P1 and the second portion P2 are left as a cast surface, such machining is not necessary. Also, according to such a configuration, for example, the first portion P1 having a linear shape can be used as a reference for subsequent machining.
  • the flow direction of the exhaust gas flowing through the second scroll passage 52 is reversed in the central axis direction when it flows into the space S.
  • the second scroll passage 52 since the second scroll passage 52 is directly connected to the space S, the flow of the exhaust gas is abruptly bent when it flows into the space S. Therefore, the flow along the surface 53 is likely to separate in the region along the shroud 5b after the flow direction is reversed.
  • the region including the outlet 54 includes the second portion P2 having an R-shape and the first portion P1 having a straight shape along the flow of the exhaust gas.
  • FIG. 3 is an enlarged cross-sectional view showing a turbine T1 according to a first comparative example.
  • the turbine T1 differs from the turbine T according to the above embodiment in the shape of the region including the outlet 54. In other respects, the turbine T1 may be the same as the turbine T.
  • turbine housing 5 does not include first portion P1 and second portion P2 described above.
  • Surface 53 and shroud 5b are directly connected to each other by a sharp angle SC.
  • FIG. 4 is an enlarged cross-sectional view showing a turbine T2 according to a second comparative example.
  • the turbine T2 differs from the turbine T according to the above embodiment in the shape of the region including the outlet 54. In other respects, the turbine T2 may be the same as the turbine T.
  • turbine housing 5 includes third portion P3 instead of first portion P1 and second portion P2 described above.
  • Third portion P3 has an R-shape. That is, in turbine T2, only third portion P3 having an R-shape is located between surface 53 and shroud 5b.
  • the radius of the R-shape of third portion P3 is larger than the radius of the R-shape of second portion P2 described above.
  • FIG. 5 is an enlarged cross-sectional view showing the entropy analysis results of turbines T, T1, and T2 according to the embodiment, the first comparative example, and the second comparative example. The same conditions were used in the analysis, except for the shape of the area including the outlet 54.
  • the upper diagram in FIG. 5 shows the analysis results of turbine T1 according to the first comparative example
  • the middle diagram in FIG. 5 shows the analysis results of turbine T2 according to the second comparative example
  • the lower diagram in FIG. 5 shows the analysis results of turbine T according to the embodiment.
  • the region with high entropy (black region) Emax decreases in the region along the shroud 5b in the order of turbine T1, turbine T2, and turbine T. That is, in the turbine T according to the embodiment, separation is the least in the region along the shroud 5b.
  • FIG. 6 is a graph showing the analysis results of the turbine efficiency of turbines T, T1, and T2 according to the embodiment, the first comparative example, and the second comparative example.
  • FIG. 6 shows the turbine efficiency of each model in the analysis results of FIG. 5.
  • the turbine efficiency can be calculated by dividing the turbine output by the amount of heat given to the turbine.
  • the turbine efficiency increases in the order of turbine T1, turbine T2, and turbine T.
  • the turbine T according to the embodiment can improve the turbine efficiency.
  • the turbine T as described above includes a turbine impeller 2 and a turbine housing 5 that accommodates the turbine impeller 2.
  • the turbine housing 5 includes an exhaust port 5a that is spaced apart from the turbine impeller 2 in the central axis direction and discharges exhaust gas that has passed through the turbine impeller 2, a first scroll passage 51 that is located outside the turbine impeller 2 in the radial direction and guides the exhaust gas to the turbine impeller 2, and a second scroll passage 52 that is located outside the turbine impeller 2 in the radial direction and closer to the exhaust port 5a than the first scroll passage 51 in the central axis direction and guides fluid to the turbine impeller 2.
  • the second scroll passage 52 is inclined with respect to the radial direction so as to move away from the exhaust port 5a in the central axis direction as it approaches the turbine impeller 2 in the radial direction.
  • the region including the outlet 54 of the second scroll passage 52 includes a first portion P1 having a linear shape parallel to the radial direction, and a second portion P2 having an R-shape and formed continuously radially outward from the first portion P1.
  • the first portion P1 and the second portion P2 have a cast surface.
  • the first portion P1 which has a linear shape, can be used as a reference for subsequent processing.
  • difficult machining is not required.
  • the first scroll passage 51 and the second scroll passage 52 are directly connected to the space S that houses the turbine impeller 2.
  • the exhaust gas flowing through the second scroll passage 52 is suddenly bent when it flows into the space S. Therefore, the effect of suppressing separation is more easily achieved.
  • the turbine T does not include vanes for adjusting the flow of exhaust gas between the first scroll passage 51 and the second scroll passage 52 and the turbine impeller 2.
  • the turbine may include such vanes.
  • Turbine impeller (impeller) 5.

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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)
PCT/JP2023/022643 2022-11-02 2023-06-19 タービン Ceased WO2024095525A1 (ja)

Priority Applications (4)

Application Number Priority Date Filing Date Title
DE112023003534.2T DE112023003534T5 (de) 2022-11-02 2023-06-19 Turbine
CN202380064936.8A CN119895129A (zh) 2022-11-02 2023-06-19 涡轮机
JP2024554110A JPWO2024095525A1 (https=) 2022-11-02 2023-06-19
US19/071,859 US20250198310A1 (en) 2022-11-02 2025-03-06 Turbine

Applications Claiming Priority (2)

Application Number Priority Date Filing Date Title
JP2022-176675 2022-11-02
JP2022176675 2022-11-02

Related Child Applications (1)

Application Number Title Priority Date Filing Date
US19/071,859 Continuation US20250198310A1 (en) 2022-11-02 2025-03-06 Turbine

Publications (1)

Publication Number Publication Date
WO2024095525A1 true WO2024095525A1 (ja) 2024-05-10

Family

ID=90930099

Family Applications (1)

Application Number Title Priority Date Filing Date
PCT/JP2023/022643 Ceased WO2024095525A1 (ja) 2022-11-02 2023-06-19 タービン

Country Status (5)

Country Link
US (1) US20250198310A1 (https=)
JP (1) JPWO2024095525A1 (https=)
CN (1) CN119895129A (https=)
DE (1) DE112023003534T5 (https=)
WO (1) WO2024095525A1 (https=)

Citations (8)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
JPS5438431A (en) * 1977-09-02 1979-03-23 Hitachi Ltd Turbosupercharger
JPS63302134A (ja) * 1987-06-01 1988-12-09 Hitachi Ltd 排気タ−ビン過給機
JP2007192180A (ja) * 2006-01-20 2007-08-02 Toyota Motor Corp ターボチャージャのタービン
JP2012211572A (ja) * 2011-03-31 2012-11-01 Denso Corp ターボチャージャ
JP2013011260A (ja) * 2011-06-30 2013-01-17 Mitsubishi Heavy Ind Ltd 可変流量ラジアルタービン
JP2013136993A (ja) * 2011-12-28 2013-07-11 Mitsubishi Heavy Ind Ltd ツインスクロールターボチャージャ
JP2018091275A (ja) * 2016-12-06 2018-06-14 トヨタ自動車株式会社 過給機
US20180328280A1 (en) * 2017-05-09 2018-11-15 Honeywell International Inc. Turbocharger having a meridionally divided turbine housing and a variable turbine nozzle

Family Cites Families (6)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US8424304B2 (en) * 2009-11-03 2013-04-23 Honeywell International Inc. Turbine assembly for a turbocharger, having two asymmetric volutes that are sequentially activated, and associated method
KR20130047310A (ko) * 2011-10-31 2013-05-08 현대자동차주식회사 자동차용 터보차저의 터빈하우징
JP5964056B2 (ja) * 2012-01-11 2016-08-03 三菱重工業株式会社 タービンハウジングのスクロール構造
JP6413980B2 (ja) * 2014-09-04 2018-10-31 株式会社デンソー ターボチャージャの排気タービン
WO2016071959A1 (ja) * 2014-11-04 2016-05-12 三菱重工業株式会社 タービンハウジングおよびタービンハウジングの製造方法
DE102021108686A1 (de) * 2021-04-07 2022-10-13 Borgwarner Inc. Turbinenanordnung mit separater leiteinrichtung

Patent Citations (8)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
JPS5438431A (en) * 1977-09-02 1979-03-23 Hitachi Ltd Turbosupercharger
JPS63302134A (ja) * 1987-06-01 1988-12-09 Hitachi Ltd 排気タ−ビン過給機
JP2007192180A (ja) * 2006-01-20 2007-08-02 Toyota Motor Corp ターボチャージャのタービン
JP2012211572A (ja) * 2011-03-31 2012-11-01 Denso Corp ターボチャージャ
JP2013011260A (ja) * 2011-06-30 2013-01-17 Mitsubishi Heavy Ind Ltd 可変流量ラジアルタービン
JP2013136993A (ja) * 2011-12-28 2013-07-11 Mitsubishi Heavy Ind Ltd ツインスクロールターボチャージャ
JP2018091275A (ja) * 2016-12-06 2018-06-14 トヨタ自動車株式会社 過給機
US20180328280A1 (en) * 2017-05-09 2018-11-15 Honeywell International Inc. Turbocharger having a meridionally divided turbine housing and a variable turbine nozzle

Also Published As

Publication number Publication date
US20250198310A1 (en) 2025-06-19
CN119895129A (zh) 2025-04-25
JPWO2024095525A1 (https=) 2024-05-10
DE112023003534T5 (de) 2025-07-31

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