WO2002064959A1 - Procede d'accouplement pour tige de turbine de turbocompresseur - Google Patents
Procede d'accouplement pour tige de turbine de turbocompresseur Download PDFInfo
- Publication number
- WO2002064959A1 WO2002064959A1 PCT/JP2002/001091 JP0201091W WO02064959A1 WO 2002064959 A1 WO2002064959 A1 WO 2002064959A1 JP 0201091 W JP0201091 W JP 0201091W WO 02064959 A1 WO02064959 A1 WO 02064959A1
- Authority
- WO
- WIPO (PCT)
- Prior art keywords
- shaft
- wheel
- turbine shaft
- fitting hole
- turbine
- Prior art date
Links
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
- 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
- F01D5/025—Fixing blade carrying members on shafts
-
- 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
-
- 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
- F05D2230/00—Manufacture
- F05D2230/20—Manufacture essentially without removing material
- F05D2230/23—Manufacture essentially without removing material by permanently joining parts together
- F05D2230/232—Manufacture essentially without removing material by permanently joining parts together by welding
- F05D2230/233—Electron beam welding
-
- 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
- F05D2230/00—Manufacture
- F05D2230/60—Assembly methods
- F05D2230/64—Assembly methods using positioning or alignment devices for aligning or centring, e.g. pins
-
- 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
- F05D2250/20—Three-dimensional
- F05D2250/23—Three-dimensional prismatic
- F05D2250/232—Three-dimensional prismatic conical
-
- 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
- Y10—TECHNICAL SUBJECTS COVERED BY FORMER USPC
- Y10T—TECHNICAL SUBJECTS COVERED BY FORMER US CLASSIFICATION
- Y10T29/00—Metal working
- Y10T29/49—Method of mechanical manufacture
- Y10T29/49316—Impeller making
- Y10T29/4932—Turbomachine making
Definitions
- the present invention relates to a method of joining a wheel (twin wheel and compressor wheel) used for a supercharger (turbocharger) of an internal combustion engine to a turbine shaft.
- the turbocharger connects the evening bin housing provided in the middle of the exhaust passage and the compressor housing provided in the middle of the intake passage via a center housing, and a turbine wheel rotatably supported in the turbine housing.
- the compressor and the compressor wheel rotatably supported in the compressor housing are coaxially connected via an evening bin shaft rotatably supported in the center housing.
- the exhaust gas discharged from the internal combustion engine flows into the turbine housing from the exhaust gas inlet, and flows in a spiral shape along the scroll passage. And spin the bin wheel in the evening.
- the bin wheel rotates in this way, the torque of the turbine wheel is transmitted to the compressor wheel via the turbine shaft, and the compressor wheel rotates in synchronization with the turbine wheel.
- the compressor wheel rotates in synchronism with the turbine wheel, the intake air near the intake port is drawn into the compressor housing by the suction force generated by the rotation of the compressor wheel, and sent to the compressor housing.
- the pressure is fed to the intake / exhaust port through the outlet passage and the scroll passage.
- the intake air compressed in the compressor housing is forcibly supplied to the combustion chamber, so that the charging efficiency of the intake air is improved.
- the fuel injection amount in accordance with the increase in the intake air amount it is possible to obtain greater combustion power and explosive power, and it is possible to increase the engine output.
- the turpentine wheel must rotate at a high speed of 100,000 to 160,000 Z ⁇ . While being exposed to a high-temperature exhaust gas of up to 900 ° C. Therefore, in the production of the Yuichi Pochija, the Yubin bin wheel, compressor wheel, and Yubin bin shaft must be arranged with high precision on the same rotating shaft. In particular, manufacturing errors (wheel and turbine It is very important not to cause the displacement of the shaft rotation axis).
- the wheel and turbine shaft as described above are often joined by electron beam welding.
- the accuracy of the pre-welding determines the product accuracy. I do.
- a fitting hole 51 is formed in the turpentine wheel 50, and a protrusion 61 is formed in one of the evening bin shafts 60 at one end on the side joined to the turbine wheel 50. I do.
- the protrusion 61 is fitted into the fitting hole 51 so as to form the gap 52, and one end of the bin shaft 60 is brought into contact with the turbine wheel 50 at the contact portion 53, Positioning was being performed.
- the turbine shaft 60 contracts in the axial direction, there is a problem that the dimensional accuracy in the axial direction is easily lost.
- the positioning of the turbine wheel 50 and the turbine shaft 60 depends on the accuracy of the jig to be used, and it is difficult to secure stable coaxiality. In addition, it becomes difficult to maintain accurate coaxiality due to jig variations and aging.
- the present invention has been made in view of the above problems, and has as its technical object to provide a joining method capable of improving the joining accuracy between a wheel and a bin shaft. Disclosure of the invention
- the present invention employs the following means in order to solve the above-described problems. That is, when a wheel provided with a fitting hole for inserting and fixing one end of a turbine shaft and a turbine shaft to be concentrically located at the center of the rotation shaft of the wheel are joined, a fitting hole of the wheel is provided. At least a portion of the inner peripheral wall of the fitting is formed in a tapered shape so that the diameter decreases inward from the opening side of the fitting hole,
- a tapered axial contact portion that can be in close contact with the tapered inner peripheral wall is provided, and is inserted into the fitting hole.
- An inlet with a constant diameter is provided at one end of the turbine shaft joined to a wheel.
- the wheel and the evening bin shaft are joined and fixed so as to be concentric on a rotation axis.
- An insertion portion having a constant diameter is formed at one end of the turbine shaft, and a taper portion that gradually increases in diameter is provided continuously from the insertion portion, and the insertion portion and the large-diameter portion are arranged on a concentric axis. You can do so.
- the wheels include a turbine wheel and a compressor wheel, and are connected to each other on the same axis via a rotatably supported turbine shaft. Further, it is possible to weld the wheel and the turbine shaft by melting a portion other than the axial contact portion of the turbine shaft and the tapered inner peripheral wall of the wheel.
- At least a part of the inner peripheral wall of the fitting hole into which one end of the turbine shaft is inserted is tapered so that the diameter decreases inward from the opening side of the fitting hole.
- Those formed in a shape are preferred.
- the turbine shaft has a tapered axial contact portion that can be tightly attached to an inner peripheral wall of a fitting hole provided in the turbine wheel at one end, and has a constant diameter inserted into the fitting hole. It is possible to employ a configuration having an inlet. In this case, an insertion portion having a constant diameter is formed at one end, and a taper portion that gradually increases in diameter is provided while continuing from the insertion portion, and is arranged so that the insertion portion and the large-diameter portion are coaxial. can do.
- turbocharger can be applied to the manufacture of any turbocharger such as a variable turbo, a combustible nozzle turbo, a linear shard turbo, a sequential turbo, and the like, as long as the turbo charger has a wheel and a single bin shaft.
- a variable turbo such as a variable turbo, a combustible nozzle turbo, a linear shard turbo, a sequential turbo, and the like.
- the axial contact portion is provided at a portion other than the welded portion in the turbine shaft, the dimensional change in the axial direction at the time of fusion shrinkage of the turbine shaft can be prevented.
- the axial contact portion is formed in a tapered shape, and at least a part of the inner peripheral wall of the fitting hole which is in contact with the axially contacted portion is also formed in a tapered shape.
- both are guided so as to be located on the same axis, coaxial accuracy is easily secured.
- the movement in the direction orthogonal to the axial direction of the turbine shaft is restricted by the tapered axial contact portion, so that the turbine shaft is prevented from being bent due to heat during welding.
- the tarpin shaft has an abutting portion that abuts against a surface formed in the fitting hole and restricts movement of the tarpin shaft in the axial direction during welding. It can be provided at a site other than the above. As a result, the movement of the tarpin shaft is reliably prevented.
- an insertion portion having a constant diameter to be inserted into the fitting hole is provided at one end of the turbine shaft to be joined to the wheel. Avoid dimensional changes in the axial direction when the turbine shaft melts and shrinks, even if the abutment that restricts the turbine shaft from moving in the axial direction by contacting the surface formed in the fitting hole in the previous period. Can be.
- the present invention when joining the wheel and the turbine shaft by means such as welding, it is possible to prevent a dimensional change due to shrinkage of the turbine shaft 4 in the axial direction, thereby improving the product accuracy. be able to.
- the inner peripheral wall of the fitting hole of the wheel is required. At least a portion is formed in a tapered shape so that the diameter becomes smaller inward from the opening side of the fitting hole, while one end of the turbine shaft joined to the wheel can be in close contact with the inner peripheral wall.
- FIG. 1 is a cross-sectional view of the turbine wheel of the present invention.
- FIG. 2 is a side view of the turpin shaft of the present invention.
- FIG. 3 is a view showing a state where the evening bin wheel and the turbine shaft are joined.
- FIG. 4 is an enlarged view of a portion A in FIG. 3, and is a diagram showing a joint portion between a turbine wheel and a turbine shaft.
- FIG. 5 is a diagram showing a joint between a turbine wheel and a evening bin shaft according to another embodiment.
- FIG. 6 is a view showing a joint between a turbine wheel and a turpin shaft according to still another embodiment.
- FIG. 7 is a partially broken perspective view showing the structure of the turbocharger.
- FIG. 8 is a flowchart showing a joining process of the turbine wheel and the turbine shaft.
- FIG. 9 is a diagram showing an example of a state in which a conventional turpin wheel and an evening bin shaft are joined.
- FIG. 10 is a diagram showing a processing state of a conventional tarpin shaft.
- the turbocharger 12 is configured by connecting a compressor housing 13 and a turbine housing 14 via a center housing 15.
- the bin shaft 4 is rotatably supported about its axis L.
- One end of the turpin shaft 4 projects into the compressor housing, and a turbine wheel 1 having a plurality of blades 2 is attached to the projecting portion.
- the turbine wheel 1 is rotated by the flow force of exhaust gas.
- a blade (blade) 2 is formed around a cylindrical main body.
- a cylindrical fitting hole 3 into which the turbine shaft 4 is inserted and fixed is provided on the axis L of the rotation.
- the inner peripheral wall 3a of the fitting hole 3 has a stepped portion 3b, and the entire circumference of the inner peripheral wall from the stepped portion 3b toward the opening side of the fitting hole 3 is smaller than the tip of the fitting hole 3.
- Large diameter 3c I'm wearing The entire circumference of the inner peripheral wall on the opening side further than the large diameter portion 3c is formed in a tapered shape so as to increase in diameter toward the opening of the fitting hole 3, and this portion is tapered edge 3d It has become.
- the evening bin shaft 4 is a cylindrical shaft, and one end thereof is provided with a head 5 that is inserted into and fixed to the fitting hole 3.
- the head 5 has a larger diameter than the central portion of the turbine shaft 4 and has a thrust bearing 5a and the like.
- the distal end of the head 5 has a constant diameter, that is, an insertion portion 6 whose diameter does not change, and a tapered axial contact portion 7 having a diameter gradually increasing while being continuous from the insertion portion 6. And the axial contact portion 7 are arranged on a concentric axis.
- Such a turbine shaft 4 is subjected to a heat treatment to improve its degree of hardening after its outer shape is substantially adjusted, and is further finished by polishing.
- the tapered axial contact portion 7 of the turbine shaft 4 abuts on the tapered portion 3 d of the inner peripheral portion of the fitting hole 3, but these tapered portions are joined together. Because of the close contact, the positioning of the evening bin shaft 4 in the direction of the axis L is naturally performed, and both are positioned on the same axis. Therefore, the turbine wheel 1 and the turbine shaft 4 adhere to each other in a stable state without rattling.
- the insertion portion 6 reaches a deep portion where the diameter of the fitting hole 3 is small. Since the side surface 9 and the small-diameter inner peripheral wall 3a are in contact with each other, the close contact between the axial contact portion 7 and the tapered edge 3d is extremely stable.
- the positional relationship between the insertion portion 6 and the axial contact portion 7 is not necessarily limited to the case of this embodiment.
- a tapered part is provided in the deep part of the fitting hole 3 and this is used as the axial contact part, and the insertion part for stabilizing the close contact is changed to be located on the opening side of the fitting hole 3. You may.
- the tapered axial contact portion 7 as close as possible to the opening of the fitting hole 3, it is possible to easily reduce the joining error in the axial direction, and the turbine wheel 1 and the evening bin shaft 4 The joining accuracy is improved.
- the fusion portion 11 is located at a position separate from the axial contact portion 7 as shown in the figure, and the fusion shortens the turbine shaft 4 so that the axial length does not change.
- the axial accuracy of the turbine shaft 4 is maintained by the axial contact portion 7.
- step 1 the groove processing of the turbine wheel 1 is performed.
- a fitting hole 3 including an axial contact portion 7 is provided, and a plurality of blades 2 are formed on the outer periphery.
- the blade 2 is finished so as to have a form substantially like a turbine wheel.
- the turbine shaft 4 is formed by shaping steel into a shaft shape, adjusting the shapes of the shaft and the head, then imparting hardness to the whole by induction hardening, and finishing by polishing.
- step 3 the evening bin wheel 1 and the turbine shaft 4 are washed. After cleaning, in step 4, the turbine wheel 1 and the turbine shaft 4 are joined to each other by electronic beam welding.
- step 5 the shroud portion of the turbine wheel 1 is finished.
- step 6 the overall balance is adjusted in step 6, and after cleaning it in step 7, it is completed.
- the axial contact portion 7 is provided at a portion other than the melting portion that is melted by welding, a change in the axial dimension of the turbine shaft 4 can be prevented.
- the contact between the axial contact portion 7 and the tapered peripheral portion 3 d is made to adhere to each other, in other words, the turbine wheel 1 and the turbine shaft 4 are simply inserted by inserting the insertion portion 6 into the fitting hole 3 and bringing the two together. Therefore, since the turbine wheel 1 and the turbine shaft 4 are guided so as to be arranged on the same axis, coaxial accuracy is easily ensured.
- the provision of the insertion portion 6 having a constant diameter together with the axial contact portion 7 makes the contact between the axial contact portion 7 and the tapered peripheral portion 3d extremely stable, and the turbine shaft 4 Axial displacement is less likely to occur.
- the movement of the turbine shaft 4 is also restricted by the axial contact portion 7 in a direction orthogonal to the axial direction, so that the bending of the evening bin shaft 4 due to heat during welding can be effectively prevented.
- the present embodiment has described the joining of the turbine shaft and the turbine wheel, it is needless to say that the same can be applied to the joining of the turbine shaft and the compressor wheel. It is a theory.
- the joining may be performed by any means other than the electron beam welding or other joining means.
- a step 31 is formed on the inner peripheral wall 30 of the fitting hole 3, and the step 31 is a surface 3 orthogonal to the rotation axis of the evening bin shaft 4. 2 are formed.
- the tip (leftward in the drawing) of the step 31 is a small diameter portion 33.
- a projection 34 is inserted to be inserted into the small-diameter portion 33, and the projection 34 and the outer periphery 35 of the evening bin shaft 4 are formed.
- a step 36 is formed between them.
- the corner of the stepped portion 36 is chamfered to form a flat portion 37.
- the stepped portion 31 on the side of the fitting hole 3 and the stepped portion 36 on the turbine shaft 4 side abut against each other when the turbine wheel 1 and the evening bin shaft 4 are joined.
- the welded part 39 located at a place other than the contact part 38, here, behind the contact part 38 (to the right in FIG. 5) should be melted.
- the contact portion 38 does not melt, and in combination with the tapered axial contact portion 7, the dimensional change due to shrinkage of the turbine shaft 4 in the axial direction can be more reliably prevented.
- the insertion portion 6 is inserted into the fitting hole 3 without providing a tapered axial contact portion. Things.
- a step 31 is formed in the inner peripheral wall 30 of the fitting hole 3, and the step 31 has a surface 32 orthogonal to the turbine shaft 4.
- the tip (leftward in the drawing) of the step 31 is a small diameter portion 33.
- a projection 34 is inserted to be inserted into the small-diameter portion 33, and between the projection 34 and the outer peripheral portion 35 of the turbine shaft 4.
- a step portion 36 is formed. The corner of the step portion 36 is chamfered to form a flat portion 37.
- the gap S between the inner peripheral wall 30 of the fitting hole 3 and the outer peripheral surface 35 of the turbine shaft 4 is made as small as possible. If 4 is press-fitted into the fitting hole 3, they can be coaxially arranged with almost no error.
- the present invention can be used in the manufacture of a turbocharger device for an internal combustion engine, and provides a high-quality turbocharger device with improved joining accuracy between a turbine wheel and a tarpin shaft.
Landscapes
- Engineering & Computer Science (AREA)
- Mechanical Engineering (AREA)
- General Engineering & Computer Science (AREA)
- Chemical & Material Sciences (AREA)
- Combustion & Propulsion (AREA)
- Supercharger (AREA)
- Turbine Rotor Nozzle Sealing (AREA)
Description
Claims
Priority Applications (2)
Application Number | Priority Date | Filing Date | Title |
---|---|---|---|
EP02711417A EP1359297A1 (en) | 2001-02-09 | 2002-02-08 | Connection method for turbo charger turbine shaft |
US10/470,696 US6848180B2 (en) | 2001-02-09 | 2002-02-08 | Turbocharger turbine shaft joining method |
Applications Claiming Priority (2)
Application Number | Priority Date | Filing Date | Title |
---|---|---|---|
JP2001034439A JP2002235547A (ja) | 2001-02-09 | 2001-02-09 | ターボチャージャ用タービン軸の接合方法 |
JP2001-34439 | 2001-02-09 |
Publications (1)
Publication Number | Publication Date |
---|---|
WO2002064959A1 true WO2002064959A1 (fr) | 2002-08-22 |
Family
ID=18898048
Family Applications (1)
Application Number | Title | Priority Date | Filing Date |
---|---|---|---|
PCT/JP2002/001091 WO2002064959A1 (fr) | 2001-02-09 | 2002-02-08 | Procede d'accouplement pour tige de turbine de turbocompresseur |
Country Status (4)
Country | Link |
---|---|
US (1) | US6848180B2 (ja) |
EP (1) | EP1359297A1 (ja) |
JP (1) | JP2002235547A (ja) |
WO (1) | WO2002064959A1 (ja) |
Families Citing this family (34)
Publication number | Priority date | Publication date | Assignee | Title |
---|---|---|---|---|
JP2001254627A (ja) * | 2000-03-13 | 2001-09-21 | Ishikawajima Hanyou Kikai Kk | 過給機のタービンロータ軸の加工方法 |
AT6677U1 (de) * | 2003-03-31 | 2004-02-25 | Magna Steyr Fahrzeugtechnik Ag | Verfahren zum verschweissen eines rotationssymmetrischen teiles mit einem nabenteil |
US6994526B2 (en) * | 2003-08-28 | 2006-02-07 | General Electric Company | Turbocharger compressor wheel having a counterbore treated for enhanced endurance to stress-induced fatigue and configurable to provide a compact axial length |
US7040867B2 (en) * | 2003-11-25 | 2006-05-09 | Honeywell International, Inc. | Compressor wheel joint |
GB0425088D0 (en) * | 2004-11-13 | 2004-12-15 | Holset Engineering Co | Compressor wheel |
DE102005007404B3 (de) * | 2005-02-18 | 2006-03-30 | Daimlerchrysler Ag | Verbindung einer Welle mit einem Turbinenrad eines Abgasturboladers |
JPWO2006117847A1 (ja) * | 2005-04-27 | 2008-12-18 | 株式会社日立製作所 | マイクロガスタービン |
CN100413636C (zh) * | 2005-09-29 | 2008-08-27 | 哈尔滨工业大学 | TiAl基合金增压涡轮与钢轴的高强度连接方法 |
JP4727532B2 (ja) * | 2006-08-18 | 2011-07-20 | 三菱重工業株式会社 | タービンロータの製造方法および排気ターボ過給機用タービンロータの製造方法 |
EP2092174B1 (de) * | 2006-12-11 | 2015-09-09 | BorgWarner, Inc. | Turbolader |
DE102007009779B4 (de) * | 2007-02-27 | 2019-08-01 | Wittenstein Se | Drehverbindung zwischen Welle und Ritzel und Verfahren zu deren Herstellung |
DE102007012641A1 (de) * | 2007-03-16 | 2008-09-18 | Daimler Ag | Laufzeug für einen Abgasturbolader |
DE102008038007A1 (de) * | 2008-08-16 | 2010-02-18 | Bosch Mahle Turbo Systems Gmbh & Co. Kg | Abgasturbolader |
JP5578839B2 (ja) * | 2009-11-30 | 2014-08-27 | 三菱重工業株式会社 | タービンロータ及びタービンロータの製造方法 |
US8684696B2 (en) | 2009-12-31 | 2014-04-01 | Rolls-Royce North American Technologies, Inc. | Gas turbine engine and main engine rotor assembly and disassembly |
US20120076639A1 (en) * | 2010-09-27 | 2012-03-29 | Nicolas Vazeille | Shaft and Turbine Wheel Assembly |
US8784065B2 (en) * | 2011-05-24 | 2014-07-22 | Caterpillar Inc. | Friction welding of titanium aluminide turbine to titanium alloy shaft |
JP5912659B2 (ja) * | 2012-02-28 | 2016-04-27 | 三菱重工業株式会社 | タービンロータ |
CN104145101B (zh) * | 2012-03-15 | 2018-04-10 | 博格华纳公司 | 排气涡轮增压器 |
JP5408283B2 (ja) * | 2012-04-20 | 2014-02-05 | トヨタ自動車株式会社 | ターボ過給機 |
JP2015535323A (ja) * | 2012-11-02 | 2015-12-10 | ボーグワーナー インコーポレーテッド | タービンロータを製造するための方法 |
JP6018964B2 (ja) | 2013-04-08 | 2016-11-02 | 株式会社オティックス | ターボチャージャ |
WO2015023432A1 (en) * | 2013-08-14 | 2015-02-19 | Borgwarner Inc. | Adjusting shaft arrangement of an exhaust-gas turbocharger |
DE112015000410T5 (de) * | 2014-01-15 | 2016-10-13 | Ihi Corporation | Verfahren zum Schweissen von Welle und Laufrad in Turbinenwelle, Turbinenwelle und Schweissvorrichtung |
DE102014213641A1 (de) * | 2014-01-17 | 2015-08-06 | Borgwarner Inc. | Verfahren zur Verbindung eines Verdichterrades mit einer Welle einer Aufladeeinrichtung |
US10024166B2 (en) | 2014-09-16 | 2018-07-17 | Honeywell International Inc. | Turbocharger shaft and wheel assembly |
US9827631B2 (en) | 2014-09-16 | 2017-11-28 | Honeywell International Inc. | Turbocharger shaft and wheel assembly |
US10041351B2 (en) | 2014-09-16 | 2018-08-07 | Honeywell International Inc. | Turbocharger shaft and wheel assembly |
US9821410B2 (en) | 2014-09-16 | 2017-11-21 | Honeywell International Inc. | Turbocharger shaft and wheel assembly |
US10603740B2 (en) * | 2015-02-09 | 2020-03-31 | Borgwarner Inc. | Method of joining by electron beam or laser welding a turbocharger turbine wheel to a shaft; corresponding turbocharger turbine wheel |
US9850857B2 (en) | 2015-08-17 | 2017-12-26 | Electro-Motive Diesel, Inc. | Turbocharger blisk/shaft joint with heat isolation |
CN110382839B (zh) * | 2017-03-22 | 2021-05-28 | 株式会社Ihi | 旋转体以及增压器 |
US11603880B2 (en) * | 2018-05-08 | 2023-03-14 | Cummins Inc. | Turbocharger shaft with cladding |
WO2021152742A1 (ja) * | 2020-01-29 | 2021-08-05 | 三菱重工エンジン&ターボチャージャ株式会社 | コンプレッサ装置及びターボチャージャ |
Citations (3)
Publication number | Priority date | Publication date | Assignee | Title |
---|---|---|---|---|
JPS6441633U (ja) * | 1987-09-07 | 1989-03-13 | ||
JPH02173322A (ja) * | 1988-12-23 | 1990-07-04 | Toyota Motor Corp | ターボチャージャ用タービンホイール |
JP2001254627A (ja) * | 2000-03-13 | 2001-09-21 | Ishikawajima Hanyou Kikai Kk | 過給機のタービンロータ軸の加工方法 |
Family Cites Families (2)
Publication number | Priority date | Publication date | Assignee | Title |
---|---|---|---|---|
DE3545135A1 (de) * | 1984-12-19 | 1986-06-26 | Honda Giken Kogyo K.K., Tokio/Tokyo | Fittingeinheit |
JPH02167867A (ja) * | 1988-12-21 | 1990-06-28 | Ngk Insulators Ltd | セラミックス接合体 |
-
2001
- 2001-02-09 JP JP2001034439A patent/JP2002235547A/ja active Pending
-
2002
- 2002-02-08 EP EP02711417A patent/EP1359297A1/en not_active Withdrawn
- 2002-02-08 WO PCT/JP2002/001091 patent/WO2002064959A1/ja not_active Application Discontinuation
- 2002-02-08 US US10/470,696 patent/US6848180B2/en not_active Expired - Fee Related
Patent Citations (3)
Publication number | Priority date | Publication date | Assignee | Title |
---|---|---|---|---|
JPS6441633U (ja) * | 1987-09-07 | 1989-03-13 | ||
JPH02173322A (ja) * | 1988-12-23 | 1990-07-04 | Toyota Motor Corp | ターボチャージャ用タービンホイール |
JP2001254627A (ja) * | 2000-03-13 | 2001-09-21 | Ishikawajima Hanyou Kikai Kk | 過給機のタービンロータ軸の加工方法 |
Also Published As
Publication number | Publication date |
---|---|
EP1359297A1 (en) | 2003-11-05 |
US20040057834A1 (en) | 2004-03-25 |
JP2002235547A (ja) | 2002-08-23 |
US6848180B2 (en) | 2005-02-01 |
Similar Documents
Publication | Publication Date | Title |
---|---|---|
WO2002064959A1 (fr) | Procede d'accouplement pour tige de turbine de turbocompresseur | |
US7875823B1 (en) | Process for assembling a high speed hollow rotor shaft | |
US8128865B2 (en) | Process of making a shrouded impeller | |
JP2006207526A (ja) | 可変容量型排気ターボ過給機及び可変ノズル機構構成部材の製造方法 | |
JPH0567763B2 (ja) | ||
US8763248B2 (en) | Method for manufacturing aircraft engine cases with bosses | |
EP2118450B1 (en) | Method for manufacturing a variable-vane mechanism for a turbocharger | |
JPH05504804A (ja) | 埋込みナットのコンプレッサホイール | |
EP1134358A3 (en) | Method of machining the turbine rotor shaft of a supercharger | |
EP2233719A1 (en) | Housing fastening method | |
WO2014130707A1 (en) | Electric rotor fit onto a turbomachine shaft | |
JPH0357281B2 (ja) | ||
JP3473562B2 (ja) | 可変ノズルベーン付きターボチャージャ | |
WO2010137610A1 (ja) | 過給機に適用されるインペラおよびその製造方法 | |
JPWO2003021083A1 (ja) | ハイブリッドロータ及びその製造方法並びにガスタービン | |
KR20030094643A (ko) | 터보 과급기용 터빈 축 접합방법 | |
WO2021038737A1 (ja) | コンプレッサハウジング、過給機およびコンプレッサハウジングの製造方法 | |
CN206092075U (zh) | 一种涡轮增压器的涡轮与轴总成 | |
JP7034260B2 (ja) | ウェストゲートバルブ | |
CN106996309A (zh) | 一种陶瓷增压器涡轮转轴及其成型工艺 | |
WO2010137609A1 (ja) | 過給機に適用されるインペラおよびその製造方法 | |
JP4490050B2 (ja) | ロータシャフトを製造する方法及び装置 | |
CN1461892A (zh) | 涡轮增压器的涡轮轴的连接方法 | |
EP0514040B1 (en) | Rotors for mechanically-driven superchargers | |
JP4646737B2 (ja) | 静圧気体軸受スピンドル装置 |
Legal Events
Date | Code | Title | Description |
---|---|---|---|
AK | Designated states |
Kind code of ref document: A1 Designated state(s): US |
|
AL | Designated countries for regional patents |
Kind code of ref document: A1 Designated state(s): AT BE CH CY DE DK ES FI FR GB GR IE IT LU MC NL PT SE TR |
|
121 | Ep: the epo has been informed by wipo that ep was designated in this application | ||
WWE | Wipo information: entry into national phase |
Ref document number: 10470696 Country of ref document: US |
|
WWE | Wipo information: entry into national phase |
Ref document number: 2002711417 Country of ref document: EP |
|
WWP | Wipo information: published in national office |
Ref document number: 2002711417 Country of ref document: EP |
|
WWW | Wipo information: withdrawn in national office |
Ref document number: 2002711417 Country of ref document: EP |