WO2013145078A1 - Turbocompresseur d'échappement - Google Patents

Turbocompresseur d'échappement Download PDF

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Publication number
WO2013145078A1
WO2013145078A1 PCT/JP2012/057734 JP2012057734W WO2013145078A1 WO 2013145078 A1 WO2013145078 A1 WO 2013145078A1 JP 2012057734 W JP2012057734 W JP 2012057734W WO 2013145078 A1 WO2013145078 A1 WO 2013145078A1
Authority
WO
WIPO (PCT)
Prior art keywords
edge
introduction hole
deflector
exhaust turbine
turbine supercharger
Prior art date
Application number
PCT/JP2012/057734
Other languages
English (en)
Japanese (ja)
Inventor
俊典 沖
貴幸 古田
Original Assignee
トヨタ自動車 株式会社
Priority date (The priority date is an assumption and is not a legal conclusion. Google has not performed a legal analysis and makes no representation as to the accuracy of the date listed.)
Filing date
Publication date
Application filed by トヨタ自動車 株式会社 filed Critical トヨタ自動車 株式会社
Priority to PCT/JP2012/057734 priority Critical patent/WO2013145078A1/fr
Publication of WO2013145078A1 publication Critical patent/WO2013145078A1/fr

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Classifications

    • 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
    • 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
    • F01D25/18—Lubricating arrangements
    • 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
    • F01D25/18—Lubricating arrangements
    • F01D25/183—Sealing means
    • 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
    • F02B39/14—Lubrication of pumps; Safety measures therefor
    • 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
    • F16—ENGINEERING ELEMENTS AND UNITS; GENERAL MEASURES FOR PRODUCING AND MAINTAINING EFFECTIVE FUNCTIONING OF MACHINES OR INSTALLATIONS; THERMAL INSULATION IN GENERAL
    • F16C—SHAFTS; FLEXIBLE SHAFTS; ELEMENTS OR CRANKSHAFT MECHANISMS; ROTARY BODIES OTHER THAN GEARING ELEMENTS; BEARINGS
    • F16C17/00—Sliding-contact bearings for exclusively rotary movement
    • F16C17/04—Sliding-contact bearings for exclusively rotary movement for axial load only
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F16—ENGINEERING ELEMENTS AND UNITS; GENERAL MEASURES FOR PRODUCING AND MAINTAINING EFFECTIVE FUNCTIONING OF MACHINES OR INSTALLATIONS; THERMAL INSULATION IN GENERAL
    • F16C—SHAFTS; FLEXIBLE SHAFTS; ELEMENTS OR CRANKSHAFT MECHANISMS; ROTARY BODIES OTHER THAN GEARING ELEMENTS; BEARINGS
    • F16C33/00—Parts of bearings; Special methods for making bearings or parts thereof
    • F16C33/02—Parts of sliding-contact bearings
    • F16C33/04—Brasses; Bushes; Linings
    • F16C33/06—Sliding surface mainly made of metal
    • F16C33/10—Construction relative to lubrication
    • F16C33/1025—Construction relative to lubrication with liquid, e.g. oil, as lubricant
    • F16C33/106—Details of distribution or circulation inside the bearings, e.g. details of the bearing surfaces to affect flow or pressure of the liquid
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F16—ENGINEERING ELEMENTS AND UNITS; GENERAL MEASURES FOR PRODUCING AND MAINTAINING EFFECTIVE FUNCTIONING OF MACHINES OR INSTALLATIONS; THERMAL INSULATION IN GENERAL
    • F16C—SHAFTS; FLEXIBLE SHAFTS; ELEMENTS OR CRANKSHAFT MECHANISMS; ROTARY BODIES OTHER THAN GEARING ELEMENTS; BEARINGS
    • F16C2360/00—Engines or pumps
    • F16C2360/23—Gas turbine engines
    • F16C2360/24—Turbochargers

Definitions

  • the present invention relates to an exhaust turbine supercharger mounted on an internal combustion engine.
  • FIG. 8 shows a cross-sectional structure of a conventional general exhaust turbine supercharger.
  • a thrust bearing 20 that receives the thrust force of the rotating shaft 2 of the compressor impeller 4 is provided inside the bearing housing 10.
  • the thrust bearing 20 includes a thrust collar 21 that rotates integrally with the rotary shaft 2, and a thrust disk 22 that is fitted in a groove 21 a formed on the outer peripheral surface of the thrust collar 21 and is fixed to the bearing housing 10. .
  • a seal ring collar 30 that rotates integrally with the rotary shaft 2 is provided between the thrust bearing 20 and the compressor impeller 4.
  • a seal retainer 40 is inserted into the bearing housing 10 from the outside of the thrust bearing 20.
  • the seal retainer 40 has a facing surface 41 that faces the outer peripheral surface of the seal ring collar 30, and a seal ring 39 is press-fitted into the facing surface 41.
  • the seal ring 39 is accommodated in a groove portion 31 formed on the outer peripheral surface of the seal ring collar 30.
  • the seal ring 39 and the groove portion 31 form a seal structure, and oil leakage to the compressor impeller 4 side is suppressed through the seal structure.
  • a substantially disc-shaped deflector 150 is provided in the recess 42 formed inside the seal retainer 40.
  • the rotating shaft 2 is inserted through the center hole 153 of the deflector 150.
  • the deflector 150 divides a space formed between the seal retainer 40 and the thrust bearing 20 into two chambers (first chamber C1 and second chamber C2). Further, a tongue piece 155 extends inward and downward from the vertical lower portion of the deflector 150.
  • oil is supplied to the groove portion 21a of the thrust collar 21 for lubrication through an oil passage formed inside the bearing housing 10.
  • the thrust collar 21 rotates integrally with the rotary shaft 2, the oil adhering to the thrust collar 21 scatters, and the scattered oil is collected by the deflector 150 and the tongue. It is discharged through the piece 155 to the drain passage. As a result, the inflow of oil into the second chamber C ⁇ b> 2 is suppressed, and oil leakage to the compressor impeller 4 side through the seal ring collar 30 and the seal retainer 40 is suppressed.
  • An object of the present invention is to reduce the amount of oil that stays in the second chamber, and to prevent the oil from leaking to the compressor impeller side through between the seal ring collar and the seal retainer opposed thereto. It is to provide a turbine supercharger.
  • the exhaust turbine supercharger rotationally drives the compressor impeller by the energy of the exhaust.
  • the exhaust turbine supercharger is positioned between the thrust bearing and the compressor impeller in the axial direction of the rotating shaft and is external to the rotating shaft in the axial direction of the rotating shaft.
  • a deflector that divides a space formed between the seal retainer and the thrust bearing into two chambers.
  • the flow direction of the air flow including the oil scattered by the centrifugal force generated with the rotation of the rotary shaft in the thrust bearing side chamber is defined as the air flow direction.
  • the deflector includes an introduction hole that penetrates the deflector, and a flange that extends from a first edge that is an upstream edge of the introduction hole in the airflow direction toward the thrust bearing.
  • the scissors are configured to be positioned closer to the thrust bearing toward the downstream side in the airflow direction, and the scissors together with the second edge that is the downstream edge in the airflow direction in the introduction hole. An opening that opens toward the downstream side is formed.
  • the chamber on the thrust bearing side is referred to as the first chamber and the chamber on the seal retainer side is referred to as the second chamber.
  • the soot of the above aspect is formed in the deflector, the flow cross-sectional area of the airflow including oil is reduced by the soot in the first chamber toward the downstream side in the airflow direction. .
  • the flow velocity increases and the pressure decreases.
  • a negative pressure is generated in the opening of the deflector in the first chamber.
  • the oil existing in the second chamber is sucked into the first chamber through the introduction hole and the opening due to the negative pressure generated in the first chamber. Accordingly, the amount of oil staying in the second chamber can be reduced, and oil can be prevented from leaking to the compressor impeller side between the seal ring collar and the seal retainer.
  • the first edge is an edge on the rear side in the rotation direction of the rotation shaft in the introduction hole
  • the second edge is an edge on the front side in the rotation direction of the rotation shaft in the introduction hole
  • the flange is positioned closer to the thrust bearing toward the front side in the rotation direction of the rotation shaft.
  • first edge is a radially inner edge of the introduction hole
  • second edge is a radially outer edge of the introduction hole
  • the flange is a radially outer edge of the introduction hole. A mode in which it is located closer to the thrust bearing is preferable.
  • a plurality of the introduction holes and the ridges are arranged in the circumferential direction of the deflector.
  • the introduction hole and the ridge are arranged above the lowest part in the vertical direction of the edge of the center hole.
  • the oil discharged from the second chamber or the first chamber to the drain passage may temporarily stay in the seal retainer. Further, the liquid level of the oil thus staying can reach the position immediately below the lowest part in the vertical direction of the edge of the central hole of the deflector. Therefore, even if the introduction hole and the ridge are arranged below the lowermost portion of the edge of the center hole in the vertical direction, the introduction hole and the ridge may not be able to generate the negative pressure as described above.
  • the arrangement positions of the introduction holes and the ridges can be accurately set, and unnecessary introduction holes and ridges need not be formed.
  • the deflector has a disc shape and an inner peripheral portion having the center hole, and an outer peripheral portion positioned closer to the seal retainer and radially outward than the inner peripheral portion. It is preferable that the ridge is formed on the inner periphery.
  • the arrangement positions of the introduction hole and the ridge are close to the rotation axis. For this reason, the airflow including oil reaches the soot before the flow velocity decreases, and an appropriate negative pressure can be generated at the opening. Therefore, the oil existing in the second chamber can be preferably sucked into the first chamber.
  • the introduction hole and the ridge are formed by pressing the deflector.
  • the deflector can be easily formed as compared with the aspect in which the member corresponding to the flange is formed on the main body by welding or the like. become.
  • Sectional drawing which shows the cross-sectional structure centering on a deflector about the exhaust turbine supercharger which concerns on one Embodiment of this invention.
  • Sectional drawing which shows the cross-section of the deflector in the embodiment.
  • the top view which shows the planar structure of the deflector seen from the arrow A direction of FIG.
  • FIG. 5 is a cross-sectional view showing a cross-sectional structure of the deflector along the line DD in FIG. 4.
  • the top view which shows the planar structure of the deflector corresponding to FIG. 4 about the modification of the embodiment.
  • the top view which shows the planar structure of the deflector corresponding to FIG. 4 about the other modification of the embodiment.
  • Sectional drawing which shows the cross-section of the conventional general exhaust turbine supercharger.
  • FIG. 1 shows a cross-sectional structure centered on a deflector for the exhaust turbine turbocharger of the present embodiment.
  • the upper part in the vertical direction is simply referred to as the upper part
  • the lower part in the vertical direction is simply referred to as the lower part.
  • the exhaust turbine supercharger includes a bearing housing 10 that surrounds a plurality of bearings that rotatably support the rotating shaft 2 of the compressor impeller 4.
  • a thrust bearing 20 that receives the thrust force of the rotating shaft 2 of the compressor impeller 4 is provided inside the bearing housing 10.
  • the thrust bearing 20 includes a thrust collar 21 that is externally fitted to the rotary shaft 2, and a thrust disk 22 that is fitted in a groove portion 21 a formed on the outer peripheral surface of the thrust collar 21.
  • the thrust collar 21 rotates integrally with the rotary shaft 2, while the thrust disk 22 is fixed to the bearing housing 10.
  • seal ring collar 30 that is externally fitted to the rotary shaft 2 and rotates integrally.
  • An annular groove 31 is formed on the outer peripheral surface of the seal ring collar 30.
  • An annular protrusion 32 is formed on the outer peripheral surface of the seal ring collar 30 closer to the thrust bearing 20 than the groove 31.
  • a seal retainer 40 is inserted into the bearing housing 10.
  • the seal retainer 40 is fixed to the bearing housing 10 with bolts.
  • the seal retainer 40 has a facing surface 41 that faces the outer peripheral surface of the seal ring collar 30, and a seal ring 39 is press-fitted into the facing surface 41.
  • the seal ring 39 is accommodated in the groove 31 of the seal ring collar 30.
  • the seal ring 39 and the groove portion 31 form a seal structure.
  • a substantially donut-shaped recess 42 is formed on the seal retainer 40 on the thrust bearing 20 side.
  • the end surface 43 of the seal retainer 40 on the thrust bearing 20 side (the end surface on the outer peripheral side of the recess 42) is in contact with the end surface of the thrust disk 22.
  • a substantially disc-shaped deflector 50 having a center hole 53 is provided in the recess 42 of the seal retainer 40, and the rotary shaft 2 is inserted through the center hole 53.
  • the central hole 53 of the deflector 50 is located closer to the thrust bearing 20 than the protrusion 32 of the seal ring collar 30.
  • the deflector 50 divides a space formed between the seal retainer 40 and the thrust bearing 20 into two chambers. Of the two chambers partitioned by the deflector 50, the chamber on the thrust bearing 20 side is referred to as a first chamber C1, and the chamber on the seal retainer 40 side is referred to as a second chamber C2.
  • oil is supplied for lubrication to the groove 21a of the thrust collar 21 through an oil passage formed inside the bearing housing 10.
  • FIG. 2 shows a cross-sectional structure of the deflector 50.
  • FIG. 3 shows a planar structure of the deflector 50 as viewed from the direction of arrow A in FIG.
  • FIG. 4 shows an enlarged view of part B of FIG.
  • FIG. 5 shows a cross-sectional structure of the deflector 50 along the line DD in FIG.
  • the deflector 50 is formed in a disc shape and has an inner peripheral portion 51 having the center hole 53, and is positioned on the seal retainer 40 side and radially outward from the inner peripheral portion 51.
  • the outer peripheral part 54 and the tongue piece 55 extended inclining from the lower part of the outer peripheral part 54 to the thrust bearing 20 side downward (lower right side in FIG. 2) are provided.
  • a plurality of penetrating the deflectors 50 are located above the lowermost part 52 a of the edge 52 of the center hole 53, that is, above the two-dot chain line L in FIGS. 2 and 3.
  • five) introduction holes 60 and flanges 70 are formed at equal intervals along the circumferential direction. The sizes of the introduction holes 60 and the flanges 70 and the distance between them and the center of the center hole 53 are the same.
  • the introduction hole 60 has an isosceles triangle shape. That is, the second edge 62 which is the edge of the introduction hole 60 on the front side in the rotation direction of the rotation shaft 2 extends along the radial direction Y and corresponds to the base of the isosceles triangle. Further, the first edge 61 that is the edge on the rear side in the rotation direction of the rotation shaft 2 in the introduction hole 60 corresponds to the vertex of the isosceles triangle.
  • ⁇ 70 extends from the first edge 61 toward the front side of the drawing, that is, toward the thrust bearing 20, and has a substantially triangular pyramid shape.
  • the surface including the second edge 62 in the triangular pyramid is an opening 80. That is, the flange 70 is positioned closer to the thrust bearing 20 toward the front side of the rotation shaft 2 in the rotation direction. Further, an opening 80 is formed by the second edge 62 and the flange 70.
  • the introduction hole 60 and the flange 70 are formed by pressing the deflector 50.
  • the deflector 50 is formed with the flange 70 of the above-described aspect, and therefore, in the first chamber C ⁇ b> 1, the front side in the rotation direction of the rotary shaft 2 by the same flange 70, The flow cross-sectional area of the air flow containing oil is reduced toward the downstream side in the air flow direction. For this reason, when the airflow containing oil passes the eaves 70, the flow velocity increases and the pressure decreases. Thereby, a negative pressure is generated in the opening 80 of the deflector 50 in the first chamber C1. As a result, as indicated by an arrow N in FIG.
  • the oil present in the second chamber C2 is sucked into the first chamber C1 through the introduction hole 60 due to the negative pressure generated in the first chamber C1.
  • the number of introduction holes 60 and the ridges 70, their arrangement positions, and their sizes are set through experiments and simulations so as to generate an appropriate magnitude of negative pressure in the opening 80.
  • the flange 70 is provided so that the opening 80 opens toward the front side in the rotation direction of the rotary shaft 2, that is, toward the downstream side in the airflow direction, the oil scattered by the centrifugal force is directly passed through the introduction hole 60. Outflow to the second chamber C2 is suppressed.
  • the oil discharged from the second chamber C2 or the first chamber C1 to the drain passage may temporarily stay in the recess 42 of the seal retainer 40.
  • the level of the oil remaining in this way can reach the position immediately below the lowermost part 52a in the edge 52 of the center hole 53 of the deflector 50, as shown by a one-dot chain line in FIG. Therefore, even if the introduction hole and the ridge are formed below the lowermost portion 52a in the vertical direction of the edge 52 of the center hole 53, the introduction hole and the ridge may not be able to generate the negative pressure as described above. There is.
  • the arrangement positions of the introduction hole 60 and the flange 70 can be accurately set, and unnecessary introduction holes and flanges need not be formed.
  • the arrangement positions of the introduction hole 60 and the flange 70 are close to the rotary shaft 2. It becomes. For this reason, before the flow velocity decreases, the airflow including oil reaches the ridge 70, and an appropriate amount of negative pressure can be generated in the opening 80. Therefore, the oil present in the second chamber C2 can be preferably sucked into the first chamber C1.
  • the deflector 50 of the exhaust turbine supercharger includes an introduction hole 60 penetrating the deflector 50 and an edge (first edge) 61 on the rear side in the rotation direction of the rotary shaft 2 in the introduction hole 60 from a thrust bearing. And a ridge 70 extending toward 20.
  • the flange 70 is located closer to the thrust bearing 20 toward the front side in the rotational direction of the rotary shaft 2.
  • an opening 80 is formed by the edge (second edge) 62 and the flange 70 on the front side in the rotation direction of the rotation shaft 2 in the introduction hole 60.
  • a plurality of introduction holes 60 and ridges 70 are arranged in the circumferential direction of the deflector 50. According to such a configuration, a negative pressure is generated in each of the openings 80 arranged at a plurality of positions in the circumferential direction of the deflector 50. As a result, oil present at different positions in the second chamber C2 is sucked into the first chamber C1 through the respective introduction holes 60. Therefore, the amount of oil staying in the second chamber C2 can be accurately reduced.
  • the introduction hole 60 and the flange 70 are disposed above the lowermost part 52 a in the vertical direction of the edge 52 of the center hole 53. According to such a configuration, the arrangement positions of the introduction hole 60 and the collar 70 can be set accurately, and unnecessary introduction holes and collars need not be formed.
  • the deflector 50 has a disc shape and has an inner peripheral portion 51 having a center hole 53, and is positioned closer to the seal retainer 40 and radially outward than the inner peripheral portion 51, and contacts the inner wall of the seal retainer 40. And an outer peripheral portion 54 in contact therewith.
  • the introduction hole 60 and the flange 70 are formed in the inner peripheral portion 51. According to such a configuration, an air stream containing oil can reach the ridge 70 before the flow velocity decreases, and a negative pressure of an appropriate magnitude can be generated in the opening 80. Therefore, the oil present in the second chamber C2 can be preferably sucked into the first chamber C1.
  • the introduction hole 60 and the flange 70 are formed by pressing the deflector 50. According to such a configuration, for example, after the introduction hole is formed in the main body of the deflector, the deflector 50 can be easily formed as compared with an aspect in which a member corresponding to the flange is formed on the main body by welding or the like. It becomes like this.
  • exhaust turbine supercharger is not limited to the configuration exemplified in the above-described embodiment, and may be implemented as, for example, the following form appropriately modified.
  • the shapes of the introduction hole 60, the flange 70, and the opening 80 are not limited to those illustrated in the above embodiment.
  • the introduction hole 260 may have a substantially cup shape
  • the flange 270 may have a curved surface shape
  • the opening 280 may have a substantially semi-elliptical shape. Also in this case, it is desirable to form the introduction hole 260 and the flange 270 by press working.
  • the introduction hole and the ridge 70 are formed by pressing, but the formation mode of the ridge according to the present invention is not limited to this.
  • a member corresponding to the flange may be formed on the main body by welding or the like.
  • the outer peripheral portion 54 of the deflector 50 is positioned closer to the seal retainer 40 than the inner peripheral portion 51.
  • the outer peripheral portion of the deflector is positioned closer to the thrust bearing 20 than the inner peripheral portion. It can also be adopted. Even in this case, it is desirable to form the introduction hole and the flange in the inner peripheral portion in the same manner as in the above-described embodiment in order to generate a negative pressure of an appropriate magnitude in the opening.
  • introduction holes and ridges are not limited to those illustrated in the above embodiment, but experiments such that an appropriate negative pressure is generated at the opening, etc. Can be changed as appropriate.
  • a plurality of introduction holes and ridges may be provided in the radial direction.
  • the introduction hole 60 and the flange 70 are arranged at a position where the airflow direction is along the rotation direction of the rotary shaft 2.
  • the airflow direction gradually follows the radial direction from the rotation direction of the rotation shaft 2 as the introduction position of the introduction hole and the flange approaches the axis of the rotation shaft 2. Therefore, for example, when the introduction hole and the ridge are arranged at a position where the airflow direction is along the radial direction of the rotary shaft 2, the introduction hole 360 and the ridge 370 are formed in the deflector 350 as shown in FIG. Is desirable. That is, as shown in FIG.
  • the flange 370 extends from the radially inner edge 361 of the introduction hole 360 toward the front side of the sheet, that is, toward the thrust bearing 20 and toward the radially outer side of the introduction hole 360 toward the thrust bearing 20. It is located near.
  • the opening 380 is formed by a radially outer edge 362 and a flange 370 in the introduction hole 360.
  • Tongue piece 60, 260, 360 ... Introduction hole, 61 ... Edge on the rear side in the rotational direction, 62 ... Edge on the front side in the rotational direction, 70, 270 ... ⁇ , 80, 280, 380... Opening, 361... Radially inner edge, 362.

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  • Engineering & Computer Science (AREA)
  • General Engineering & Computer Science (AREA)
  • Mechanical Engineering (AREA)
  • Chemical & Material Sciences (AREA)
  • Combustion & Propulsion (AREA)
  • Oil, Petroleum & Natural Gas (AREA)
  • Chemical Kinetics & Catalysis (AREA)
  • General Chemical & Material Sciences (AREA)
  • Supercharger (AREA)

Abstract

L'invention concerne un déflecteur (50) pour un turbocompresseur d'échappement pourvu d'un trou d'introduction (60) pénétrant le déflecteur (50) et de corniches (70) s'étendant vers un palier de butée (20) à partir d'un bord (61) du trou d'introduction (60) qui est situé derrière dans la direction rotationnelle d'un arbre rotatif (2). Les corniches (70) sont disposées de façon à se rapprocher plus étroitement du palier de butée (20) lorsque les corniches (70) s'étendent devant dans la direction rotationnelle de l'arbre rotatif (2). De même, une ouverture (80) est formée par les corniches (70) et le bord (62) du trou d'introduction (60) qui est situé devant dans la direction rotationnelle de l'arbre rotatif (2).
PCT/JP2012/057734 2012-03-26 2012-03-26 Turbocompresseur d'échappement WO2013145078A1 (fr)

Priority Applications (1)

Application Number Priority Date Filing Date Title
PCT/JP2012/057734 WO2013145078A1 (fr) 2012-03-26 2012-03-26 Turbocompresseur d'échappement

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Application Number Priority Date Filing Date Title
PCT/JP2012/057734 WO2013145078A1 (fr) 2012-03-26 2012-03-26 Turbocompresseur d'échappement

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WO2013145078A1 true WO2013145078A1 (fr) 2013-10-03

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Cited By (5)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
WO2016079781A1 (fr) * 2014-11-17 2016-05-26 三菱重工業株式会社 Turbomachine
WO2017080924A1 (fr) * 2015-11-13 2017-05-18 Abb Turbo Systems Ag Dispositif d'étanchéification d'un logement de palier et turbocompresseur à gaz d'échappement comprenant un tel dispositif
JPWO2017042925A1 (ja) * 2015-09-10 2017-10-12 三菱重工業株式会社 ターボチャージャの軸受装置、及びターボチャージャ
WO2019180428A1 (fr) * 2018-03-20 2019-09-26 Cummins Ltd Ensemble palier pour turbomachine, et élément déflecteur pour ladite turbomachine
US10641330B2 (en) 2016-03-01 2020-05-05 Mitsubishi Heavy Industries Engine & Turbocharger, Ltd. Bearing device and exhaust turbine supercharger

Citations (5)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
JPH03121275U (fr) * 1990-03-27 1991-12-12
JPH07217440A (ja) * 1994-02-02 1995-08-15 Taiho Kogyo Co Ltd ターボチャージャの非接触シール装置
JPH0941982A (ja) * 1995-07-28 1997-02-10 Taiho Kogyo Co Ltd ターボチャージャ用リングシール装置
JPH10339155A (ja) * 1997-06-10 1998-12-22 Nippon Soken Inc 過給機のオイル洩れ防止装置
JP2004132319A (ja) * 2002-10-11 2004-04-30 Nippon Soken Inc 過給機の潤滑装置

Patent Citations (5)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
JPH03121275U (fr) * 1990-03-27 1991-12-12
JPH07217440A (ja) * 1994-02-02 1995-08-15 Taiho Kogyo Co Ltd ターボチャージャの非接触シール装置
JPH0941982A (ja) * 1995-07-28 1997-02-10 Taiho Kogyo Co Ltd ターボチャージャ用リングシール装置
JPH10339155A (ja) * 1997-06-10 1998-12-22 Nippon Soken Inc 過給機のオイル洩れ防止装置
JP2004132319A (ja) * 2002-10-11 2004-04-30 Nippon Soken Inc 過給機の潤滑装置

Cited By (13)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
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CN106795808A (zh) * 2014-11-17 2017-05-31 三菱重工业株式会社 涡轮机械
JPWO2016079781A1 (ja) * 2014-11-17 2017-06-29 三菱重工業株式会社 ターボ機械
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WO2016079781A1 (fr) * 2014-11-17 2016-05-26 三菱重工業株式会社 Turbomachine
US10605160B2 (en) 2014-11-17 2020-03-31 Mitsubishi Heavy Industries Engine & Turbocharger, Ltd. Turbomachine
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