WO2014004238A1 - Exhaust-gas turbocharger - Google Patents

Exhaust-gas turbocharger Download PDF

Info

Publication number
WO2014004238A1
WO2014004238A1 PCT/US2013/046726 US2013046726W WO2014004238A1 WO 2014004238 A1 WO2014004238 A1 WO 2014004238A1 US 2013046726 W US2013046726 W US 2013046726W WO 2014004238 A1 WO2014004238 A1 WO 2014004238A1
Authority
WO
WIPO (PCT)
Prior art keywords
blade
exhaust
groove
projection
housing
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/US2013/046726
Other languages
French (fr)
Inventor
Aleksandra DIMOVA
Thomas Lischer
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.)
BorgWarner Inc
Original Assignee
BorgWarner Inc
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 BorgWarner Inc filed Critical BorgWarner Inc
Priority to JP2015518569A priority Critical patent/JP6159798B2/en
Priority to US14/406,644 priority patent/US10119411B2/en
Priority to IN342DEN2015 priority patent/IN2015DN00342A/en
Priority to KR1020157000552A priority patent/KR102033019B1/en
Priority to CN201380028878.XA priority patent/CN104364493B/en
Priority to DE112013002451.9T priority patent/DE112013002451T5/en
Publication of WO2014004238A1 publication Critical patent/WO2014004238A1/en
Anticipated expiration legal-status Critical
Ceased legal-status Critical Current

Links

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
    • F01D11/00—Preventing or minimising internal leakage of working-fluid, e.g. between stages
    • F01D11/02—Preventing or minimising internal leakage of working-fluid, e.g. between stages by non-contact sealings, e.g. of labyrinth type
    • 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
    • F04D29/08—Sealings
    • F04D29/16—Sealings between pressure and suction sides
    • F04D29/161—Sealings between pressure and suction sides especially adapted for elastic fluid pumps
    • F04D29/162—Sealings between pressure and suction sides especially adapted for elastic fluid pumps of a centrifugal flow wheel
    • 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
    • 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
    • F04—POSITIVE - DISPLACEMENT MACHINES FOR LIQUIDS; PUMPS FOR LIQUIDS OR ELASTIC FLUIDS
    • F04D—NON-POSITIVE-DISPLACEMENT PUMPS
    • F04D17/00—Radial-flow pumps, e.g. centrifugal pumps; Helico-centrifugal pumps
    • F04D17/08—Centrifugal pumps
    • F04D17/10—Centrifugal pumps for compressing or evacuating
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F04—POSITIVE - DISPLACEMENT MACHINES FOR LIQUIDS; PUMPS FOR LIQUIDS OR ELASTIC FLUIDS
    • F04D—NON-POSITIVE-DISPLACEMENT PUMPS
    • F04D25/00—Pumping installations or systems
    • F04D25/02—Units comprising pumps and their driving means
    • F04D25/024—Units comprising pumps and their driving means the driving means being assisted by a power recovery turbine
    • 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
    • F04D29/08—Sealings
    • F04D29/10—Shaft sealings
    • F04D29/102—Shaft sealings especially adapted for elastic fluid pumps
    • 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 invention relates to an exhaust-gas turbocharger according to the preamble of claim 1.
  • Turbochargers which are already known generally have a housing in which a shaft is mounted The shaft connects a turbine wheel and a compressor wheel.
  • the turbine wheel and the compressor wheel have in each case multiple blades. Between the blade tips and the housing there is formed a small gap such that the blades can move without making contact with the housing.
  • Each blade has a suction side and a pressure side. A loss flow from the pressure side to the suction side of the blade is generated by the gap between the blade and the housing.
  • the labyrinth seal comprises at least one combination of a groove and a projection which projects into the groove. Either the groove or the projection is formed on the blade. The other element in each case is formed on the inner side of the housing.
  • a projection and a groove it is preferably also possible for multiple combinations of a projection and a groove to be used. It is thus the case, for example, that multiple projections are formed on each blade, and accordingly also multiple grooves are formed in the housing. Furthermore, it is also possible for both projections and also grooves to be formed on the blades, and for grooves and projections to be formed correspondingly on the housing.
  • the labyrinth seal is used on the blades of the compressor wheel.
  • the greatest pressures at the compressor wheel arise in the region of the compressor outlet. Therefore, the labyrinth seal is preferably implemented in the region of the compressor outlet.
  • Both the groove and also the projection may have any desired geometry. It is preferably provided that the projection is trapezoidal. As a result of the trapezoidal design, the contour of the blade tip merges into the projection not with edges of 90° but rather with a smaller angle.
  • the labyrinth seal according to the invention impedes the loss flow via the gap between the blade and housing, and in so doing simultaneously reduces the undesired backflow from the compressor outlet.
  • Figure 1 shows a schematically simplified sectional view of an exhaust- gas turbocharger according to the invention as per an exemplary embodiment
  • Figure 2 shows a detail of the exhaust-gas turbocharger according to the invention as per the exemplary embodiment
  • Figure 3 shows a compressor wheel of the exhaust-gas turbocharger according to the invention as per the exemplary embodiment.
  • FIG. 1 is a highly simplified illustration of an exhaust-gas turbocharger 1.
  • the exhaust-gas turbocharger 1 comprises a housing 2 in which a shaft 3 is rotatably mounted.
  • a compressor wheel 4 and a turbine wheel 5 are seated in a rotationally conjoint manner on the shaft 3.
  • Both the turbine wheel 5 and also the compressor wheel 4 have in each case multiple blades 6.
  • the compressor wheel 4 compresses inducted charge air in the direction of a compressor outlet 9.
  • exhaust gas flows to the turbine wheel 5 and thus drives the turbine wheel 5, the shaft 3 and the compressor wheel 4.
  • a gap 7 is formed between the blades 6 and the housing 2.
  • Figure 2 shows a detail of the compressor wheel 4 and of the housing 2.
  • the housing 2 may be of multi-part construction. It can be seen that the housing 2 is assembled from a compressor housing 11 and a bearing housing 12.
  • the labyrinth seal 8 shown in Figure 2 is used.
  • the labyrinth seal 8 is composed of a combination of a groove 13 and a projection 14 on each blade 6.
  • the groove 13 is formed over the full circumference and in a continuous fashion on the inner side of the housing 2, in particular of the compressor housing 11.
  • the projection 14 on the blade 6 is an integral constituent part of the blade 6.
  • the projection 14 projects into the groove 13.
  • the contactless labyrinth seal 8 is thus formed along the gap 7.
  • the labyrinth seal 8 is formed in that half of the blade 6 which faces toward the compressor outlet 9, because it is here that the greatest pressures or pressure differences, and thus also losses, are to be expected.
  • Figure 3 shows the compressor wheel 4 with multiple blades 6 in detail.
  • Figure 3 shows that the projection 14 is formed in each case at a blade tip 15 of the blades 6.
  • the projection 14 is trapezoidal.
  • a projection 14 is formed on each blade 6 of the compressor wheel 4.
  • the labyrinth seal 8 may also have multiple projections 14 and/or combinations of projections 14 and grooves 13 along a blade tip 15 of a blade 6. Corresponding, complementary grooves 13 and projections 14 are then formed in the housing, such that in each case one projection 14 project into a groove 13.

Landscapes

  • Engineering & Computer Science (AREA)
  • Mechanical Engineering (AREA)
  • General Engineering & Computer Science (AREA)
  • Chemical & Material Sciences (AREA)
  • Combustion & Propulsion (AREA)
  • Chemical Kinetics & Catalysis (AREA)
  • General Chemical & Material Sciences (AREA)
  • Supercharger (AREA)
  • Turbine Rotor Nozzle Sealing (AREA)
  • Structures Of Non-Positive Displacement Pumps (AREA)
  • Sealing Using Fluids, Sealing Without Contact, And Removal Of Oil (AREA)

Description

EXHAUST-GAS TURBOCHARGER DESCRIPTION The invention relates to an exhaust-gas turbocharger according to the preamble of claim 1.
Turbochargers which are already known generally have a housing in which a shaft is mounted The shaft connects a turbine wheel and a compressor wheel. The turbine wheel and the compressor wheel have in each case multiple blades. Between the blade tips and the housing there is formed a small gap such that the blades can move without making contact with the housing. Each blade has a suction side and a pressure side. A loss flow from the pressure side to the suction side of the blade is generated by the gap between the blade and the housing.
It is an object of the present invention to specify an exhaust-gas turbocharger which, while being inexpensive to produce and assemble, can be operated with the greatest possible efficiency.
This object is achieved by the features of claim 1. The dependent claims relate to preferred refinements of the invention.
It has been recognized according to the invention that the flow through the gap between blades and housing can be improved by means of a contactless labyrinth seal in the region of the blade tips. The labyrinth seal according to the invention comprises at least one combination of a groove and a projection which projects into the groove. Either the groove or the projection is formed on the blade. The other element in each case is formed on the inner side of the housing.
It is preferably also possible for multiple combinations of a projection and a groove to be used. It is thus the case, for example, that multiple projections are formed on each blade, and accordingly also multiple grooves are formed in the housing. Furthermore, it is also possible for both projections and also grooves to be formed on the blades, and for grooves and projections to be formed correspondingly on the housing.
In a particularly preferred embodiment, the labyrinth seal is used on the blades of the compressor wheel. The greatest pressures at the compressor wheel arise in the region of the compressor outlet. Therefore, the labyrinth seal is preferably implemented in the region of the compressor outlet.
Both the groove and also the projection may have any desired geometry. It is preferably provided that the projection is trapezoidal. As a result of the trapezoidal design, the contour of the blade tip merges into the projection not with edges of 90° but rather with a smaller angle. The labyrinth seal according to the invention impedes the loss flow via the gap between the blade and housing, and in so doing simultaneously reduces the undesired backflow from the compressor outlet.
Further details, advantages and features of the invention become apparent from the following description of an exemplary embodiment with reference to the drawing, in which:
Figure 1 shows a schematically simplified sectional view of an exhaust- gas turbocharger according to the invention as per an exemplary embodiment,
Figure 2 shows a detail of the exhaust-gas turbocharger according to the invention as per the exemplary embodiment, and
Figure 3 shows a compressor wheel of the exhaust-gas turbocharger according to the invention as per the exemplary embodiment.
An exemplary embodiment will be explained below on the basis of Figures 1 to
3.
Figure 1 is a highly simplified illustration of an exhaust-gas turbocharger 1. The exhaust-gas turbocharger 1 comprises a housing 2 in which a shaft 3 is rotatably mounted. A compressor wheel 4 and a turbine wheel 5 are seated in a rotationally conjoint manner on the shaft 3. Both the turbine wheel 5 and also the compressor wheel 4 have in each case multiple blades 6.
The compressor wheel 4 compresses inducted charge air in the direction of a compressor outlet 9. At a turbine inlet 10, exhaust gas flows to the turbine wheel 5 and thus drives the turbine wheel 5, the shaft 3 and the compressor wheel 4.
A gap 7 is formed between the blades 6 and the housing 2.
Figure 2 shows a detail of the compressor wheel 4 and of the housing 2. According to Figure 2, the housing 2 may be of multi-part construction. It can be seen that the housing 2 is assembled from a compressor housing 11 and a bearing housing 12.
According to the invention, to prevent loss flows in the gap 7, the labyrinth seal 8 shown in Figure 2 is used. The labyrinth seal 8 is composed of a combination of a groove 13 and a projection 14 on each blade 6. In the example shown, the groove 13 is formed over the full circumference and in a continuous fashion on the inner side of the housing 2, in particular of the compressor housing 11.
The projection 14 on the blade 6 is an integral constituent part of the blade 6. The projection 14 projects into the groove 13. The contactless labyrinth seal 8 is thus formed along the gap 7.
As shown in Figure 2, the labyrinth seal 8 is formed in that half of the blade 6 which faces toward the compressor outlet 9, because it is here that the greatest pressures or pressure differences, and thus also losses, are to be expected. Figure 3 shows the compressor wheel 4 with multiple blades 6 in detail. Figure 3 shows that the projection 14 is formed in each case at a blade tip 15 of the blades 6. In the exemplary embodiment shown, the projection 14 is trapezoidal. As is also shown in Figure 3, a projection 14 is formed on each blade 6 of the compressor wheel 4.
As an alternative to the exemplary embodiment shown, the labyrinth seal 8 may also have multiple projections 14 and/or combinations of projections 14 and grooves 13 along a blade tip 15 of a blade 6. Corresponding, complementary grooves 13 and projections 14 are then formed in the housing, such that in each case one projection 14 project into a groove 13.
It is also possible for the labyrinth seal shown to be implemented on the blades 16 of the turbine wheel 5.
In addition to the above written description of the invention, reference is hereby explicitly made to the diagrammatic illustration of the invention in Figures 1 to 3 for additional disclosure thereof.
LIST OF REFERENCE SIGNS
1 Exhaust-gas turbocharger
2 Housing
3 Shaft
4 Compressor wheel
5 Turbine wheel
6 Blades
7 Gap
8 Labyrinth seal
9 Compressor outlet
10 Turbine inlet
11 Compressor housing
12 Bearing housing
13 Groove
14 Projection
15 Blade tip

Claims

1. An exhaust-gas turbocharger (1) comprising:
a housing (2),
- a turbine wheel (5) with blades (6),
a compressor wheel (4) with blades (6), and
- a shaft (3) which is mounted in the housing (2) and which connects the turbine wheel (5) and compressor wheel (4),
wherein,
- in a gap (7) between the housing (2) and at least one blade (6), a contactless labyrinth seal (8) is formed on the blade (6) and on the housing (2), wherein the labyrinth seal (8) comprises at least one combination of a groove (13) and a projection (14).
2. The exhaust-gas turbocharger as claimed in claim 1, wherein the labyrinth seal (8) comprises at least one groove (13) in the housing (2) and one projection (14), which projects into the groove (13), on the blade (6), and/or at least one groove (13) in the blade (6) and one projection (14), which projects into the groove (13), on the housing (2).
3. The exhaust-gas turbocharger as claimed in one of the preceding claims, wherein the labyrinth seal (8) comprises multiple combinations of a groove (13) and a projection (14) on a blade (6).
4. The exhaust-gas turbocharger as claimed in one of the preceding claims, wherein the groove (13) and/or the projection (14) is arranged at a blade tip (15) of the blade (6).
5. The exhaust-gas turbocharger as claimed in one of the preceding claims, wherein the groove (13) and/or the projection (14) is arranged on each blade (6) of the compressor wheel (4) or turbine wheel (5).
6. The exhaust-gas turbocharger as claimed in one of the preceding claims, wherein the groove (13) and/or the projection (14) is arranged in that half of the blade
7. The exhaust-gas turbocharger as claimed in one of the preceding claims, wherein the groove (13) and/or the projection (14) is arranged in that half of the blade (6) of the turbine wheel (5) which faces toward a turbine inlet (10).
8. The exhaust-gas turbocharger as claimed in one of the preceding claims, wherein the groove (13) and/or the projection (14) is trapezoidal.
PCT/US2013/046726 2012-06-25 2013-06-20 Exhaust-gas turbocharger Ceased WO2014004238A1 (en)

Priority Applications (6)

Application Number Priority Date Filing Date Title
JP2015518569A JP6159798B2 (en) 2012-06-25 2013-06-20 Exhaust gas turbocharger
US14/406,644 US10119411B2 (en) 2012-06-25 2013-06-20 Exhaust-gas turbocharger
IN342DEN2015 IN2015DN00342A (en) 2012-06-25 2013-06-20
KR1020157000552A KR102033019B1 (en) 2012-06-25 2013-06-20 Exhaust-gas turbocharger
CN201380028878.XA CN104364493B (en) 2012-06-25 2013-06-20 exhaust turbocharger
DE112013002451.9T DE112013002451T5 (en) 2012-06-25 2013-06-20 turbocharger

Applications Claiming Priority (2)

Application Number Priority Date Filing Date Title
DE102012012558 2012-06-25
DE102012012558.5 2012-06-25

Publications (1)

Publication Number Publication Date
WO2014004238A1 true WO2014004238A1 (en) 2014-01-03

Family

ID=49783757

Family Applications (1)

Application Number Title Priority Date Filing Date
PCT/US2013/046726 Ceased WO2014004238A1 (en) 2012-06-25 2013-06-20 Exhaust-gas turbocharger

Country Status (7)

Country Link
US (1) US10119411B2 (en)
JP (1) JP6159798B2 (en)
KR (1) KR102033019B1 (en)
CN (1) CN104364493B (en)
DE (1) DE112013002451T5 (en)
IN (1) IN2015DN00342A (en)
WO (1) WO2014004238A1 (en)

Cited By (2)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
WO2015131988A1 (en) * 2014-03-03 2015-09-11 Mtu Friedrichshafen Gmbh Compressor with sealing device at the blade tips of the rotor blades
WO2020126413A1 (en) * 2018-12-19 2020-06-25 Ebm-Papst Mulfingen Gmbh & Co. Kg Turbocompressor with adapted meridian contour of the blades and compressor wall

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DE102016001484A1 (en) * 2016-02-11 2017-08-17 Ebm-Papst St. Georgen Gmbh & Co. Kg fan unit
WO2017150254A1 (en) * 2016-03-03 2017-09-08 株式会社Ihi Rotary machine
JP6662451B2 (en) * 2016-05-09 2020-03-11 株式会社Ihi Centrifugal compressor impeller
KR20210132505A (en) * 2020-04-27 2021-11-04 삼성전자주식회사 Motor assembly and a cleaner comprising the same
CN113062882A (en) * 2021-04-13 2021-07-02 德耐尔能源装备有限公司 Structure for reducing pneumatic noise of centrifugal gas compressor
US12385701B2 (en) 2022-04-28 2025-08-12 Hamilton Sundstrand Corporation Additively manufactured turbomachinery components with designed atmosphere of an inner voided core for heat transfer control
US12228034B2 (en) 2022-04-28 2025-02-18 Hamilton Sundstrand Corporation Additively manufactures multi-metallic adaptive or abradable rotor tip seals
CN115507061A (en) * 2022-11-09 2022-12-23 湖南天雁机械有限责任公司 Volute and compressor
CN115507056A (en) * 2022-11-09 2022-12-23 湖南天雁机械有限责任公司 A kind of impeller and compressor
CN116044805A (en) * 2022-12-23 2023-05-02 湖南天雁机械有限责任公司 Turbocharger with anti-drop bearing locating pin structure
CN116146503A (en) * 2023-02-23 2023-05-23 安徽美芝精密制造有限公司 Compressors, air conditioners, fuel cell modules and vehicles

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JP2003343486A (en) * 2002-05-28 2003-12-03 Ishikawajima Harima Heavy Ind Co Ltd Centrifugal compressor with long and short impeller
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Cited By (3)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
WO2015131988A1 (en) * 2014-03-03 2015-09-11 Mtu Friedrichshafen Gmbh Compressor with sealing device at the blade tips of the rotor blades
WO2020126413A1 (en) * 2018-12-19 2020-06-25 Ebm-Papst Mulfingen Gmbh & Co. Kg Turbocompressor with adapted meridian contour of the blades and compressor wall
US11555507B2 (en) 2018-12-19 2023-01-17 Ebm-Papst Mulfingen Gmbh & Co. Kg Turbocompressor with adapted meridian contour of the blades and compressor wall

Also Published As

Publication number Publication date
DE112013002451T5 (en) 2015-01-22
US10119411B2 (en) 2018-11-06
CN104364493A (en) 2015-02-18
KR102033019B1 (en) 2019-10-16
IN2015DN00342A (en) 2015-06-12
JP6159798B2 (en) 2017-07-05
KR20150032285A (en) 2015-03-25
CN104364493B (en) 2018-05-15
US20150176422A1 (en) 2015-06-25
JP2015521709A (en) 2015-07-30

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