CN1499083A - Compressor impeller assembly - Google Patents
Compressor impeller assembly Download PDFInfo
- Publication number
- CN1499083A CN1499083A CNA2003101198134A CN200310119813A CN1499083A CN 1499083 A CN1499083 A CN 1499083A CN A2003101198134 A CNA2003101198134 A CN A2003101198134A CN 200310119813 A CN200310119813 A CN 200310119813A CN 1499083 A CN1499083 A CN 1499083A
- Authority
- CN
- China
- Prior art keywords
- hole
- diameter
- axle
- impeller
- shaft
- 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.)
- Pending
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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
- F04—POSITIVE - DISPLACEMENT MACHINES FOR LIQUIDS; PUMPS FOR LIQUIDS OR ELASTIC FLUIDS
- F04D—NON-POSITIVE-DISPLACEMENT PUMPS
- F04D29/00—Details, component parts, or accessories
- F04D29/26—Rotors specially for elastic fluids
- F04D29/266—Rotors specially for elastic fluids mounting compressor rotors on shafts
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- Engineering & Computer Science (AREA)
- Mechanical Engineering (AREA)
- General Engineering & Computer Science (AREA)
- Chemical & Material Sciences (AREA)
- Combustion & Propulsion (AREA)
- Structures Of Non-Positive Displacement Pumps (AREA)
- Supercharger (AREA)
- Compressor (AREA)
- Turbine Rotor Nozzle Sealing (AREA)
Abstract
This compressor wheel assembly has the compressor wheel 7 installed on a rotary shaft 8. This shaft 8 extends by penetrating through the hole arranged along the rotary shaft of the wheel. The hole has a first shaft directional part 21 having a diameter coincident with a diameter of the shaft and a second shaft directional part 22 having an expanded diameter. An inside surface of the second part of the hole is arranged at an interval in the radial direction from the shaft 8.
Description
Technical field
The present invention relates to a kind of gas compressor blade wheel assembly of rotating shaft.Be particularly related to the gas compressor blade wheel assembly of turbosupercharger.
Background technique
Turbosupercharger is a kind of known devices, is the suction port supply air of internal-combustion engine being higher than under the barometric pressure (air inlet pressure).Conventional turbosupercharger comprises substantially: one is installed in the exhaust gas drive turbine in the rotating shaft in turbine cylinder.The rotating drive of turbine is installed in the compressor impeller of a other end in compressor housing.Compressor impeller is delivered to the suction tude of internal-combustion engine with pressurized air, thereby improves compressor power.Rotating shaft is supported on the axle journal, and thrust bearing places in the intermediate support shell that is connected between turbine and the compressor impeller housing.
Conventional compressor impeller comprises one group of blade that stretches out from central shaft, has on the central shaft in order to accept the through hole of turbo-charger shaft one end.Compressor impeller is fixed on the axle by the nut that screws in axle head, passes the impeller bore place at axle, and is supported on the impeller front end, and impeller is fixed on (or other radially-protruding contact that rotates with axle) on the shaft shoulder.
Latest requirement to turbocharger performance is to improve the air-flow of the turbosupercharger of given size, thereby improve rotating speed, such as surpassing 100,000rpm.Be the so high rotating speed requirement of adaptation, the bearing of turbosupercharger, thus the diameter of axle of turbosupercharger must reduce.But, using the axle of relative minor diameter is debatable for conventional compressor impeller mounting unit assembly, that is to say, the enough narrow through hole that passes compressor impeller that processing reaches required precision is inconvenient (if the rotation of axle is talked about stably, through hole must be coaxial with the rotation of axis and impeller).Along with reducing of through-hole diameter, and reduce corresponding with intensity of size of processing the required instrument of through hole.Even reach required machining accuracy, the process time of prolongation and tool wear problem have suppressed this processing feasibility economically.
Above problem is aggravated along with the development of turbosupercharger, requires to use more high performance material, as the titanium of hardness greater than aluminum alloy commonly used.
One of way of avoiding the problems referred to above is to use so-called as U.S. Pat 4,705,463 disclosed atresia compressor impellers.The turbo-charger shaft that this kind gas compressor blade wheel assembly only needs a short relatively tapped hole to accept to shorten on compressor impeller.But also may there be equilibrium problem in this assembly, because being threaded between compressor impeller and the axle, and the gap of existence in this connections is difficult to the coaxality that keeps required.
Summary of the invention
One of purpose of the present invention is exactly to eliminate or weaken the problems referred to above.
According to the present invention, a kind of gas compressor blade wheel assembly is provided, comprise that one is installed in the compressor impeller on the running shaft, axle passes along the through hole of impeller rotating shaft line, through hole has the corresponding the first axle part branch of diameter of diameter and axle, with the second axle part branch of increased diameter, thereby make the internal surface of through hole second portion and axle that spaced radial be arranged.
Impeller only is supported on the axle by the first axle part branch of through hole.This part of through hole can be machined to desired diameter along the impeller shaft line length, and keeps desired precision.The remaining part that only adds large through-hole, thus the alignment of impeller on axle do not influenced.
The present invention also provides a kind of turbosupercharger that comprises above-mentioned gas compressor blade wheel assembly.
Other best features of the present invention is just clear by following introduction.
Description of drawings
Referring now to accompanying drawing, only specific embodiments of the invention are described in the mode that exemplifies.Wherein:
Fig. 1 is the axial, cross-sectional view of conventional turbosupercharger, and the main member and the conventional gas compressor blade wheel assembly of turbosupercharger is shown;
Fig. 2 is the sectional view according to gas compressor blade wheel assembly of the present invention.
Embodiment
The basic building block of conventional centripetal turbine pressurized machine is shown at first as shown in Figure 1.This turbosupercharger comprises through a case of center bearing 3 and is connected a turbine 1 on the gas compressor 2.Turbine 1 comprises a volute 4, a built-in turbine 5.Equally, gas compressor 2 comprises the shell 6 of calming the anger, a built-in compressor impeller 7.Turbine 5 and compressor impeller 7 are installed in the opposite end of common shaft 8, and common shaft 8 is supported on the bearing assembly 9 in cartridge housing 3.
Exhaust entrance 10 and exhaust outlet 11 are arranged on the volute 4.Inlet 10 imports the annular chamber 12 that surrounds turbine 5 with the exhaust that enters.Blast air is through turbine, by entering outlet 11 with the coaxial circle of turbine 5 opening of giving vent to anger.The rotating band dynamic pressure mechanism of qi impeller 7 of turbine 5 rotates, and sucks air by axial entrance 13, and pressurized air is delivered to internal-combustion engine by the annular spiral 14 of giving vent to anger.
With reference to more detailed gas compressor blade wheel assembly, compressor impeller comprises a plurality of blades 15 that stretch out from central shaft 16, and the through hole of accepting axle 8 one ends is arranged on the central shaft.Axle 8 stretches out from the front end of compressor impeller 7 slightly, passes nut 17, is supported on the front end of compressor impeller, and compressor impeller 7 is fixed on thrust bearing and the oil seal assembly 18.The details of thrust bearing/oil seal assembly may be different, and this is unimportant to the installation configuration of understanding compressor impeller.Importantly, the clamping force that provides by nut 17 of compressor impeller 7 is avoided getting loose from axle 8.
The problem that above-mentioned conventional gas compressor blade wheel assembly exists is discussed by this detailed description.
Fig. 2 illustrates the gas compressor blade wheel assembly according to the present invention.The details of axle 8, thrust bearing and oil seal assembly 18 and clamping nut 17 can be conventional fully, such as according to shown in Figure 1.
The obvious difference of the present invention and existing assembly is: the through hole of compressor impeller radially is being step, thereby has the shaft portion 21 and 22 of two different-diameters.The first axle part divides 21 outer diameters with respect to axle 8, and diameter is less relatively.But the second axle part divides 22 enlarged diameter, thereby its internal surface has spaced radial with axle 8.Therefore compressor impeller only is supported on the axle 8 by first portion 21.The enlarged portion of through hole 22 is formed at the lower front end area of impeller pressure, therefore the operation of impeller is not had ill-effect.
Thereby, the through hole of relative minor diameter according to the present invention, the diameter that need be complementary with axle 8, processing on compressor impeller to maximum length, and on axis less than the axial length of impeller, but be easy to be worked into required precision.By second portion, thereby finish through hole at the front end area of impeller processing increased diameter.Therefore overcome the problem that runs in the prior art, promptly attempted the through hole of the relative minor diameter of processing on the whole width of compressor impeller.
It should be understood that through hole increased diameter part 22 can process before or after small diameter portion 21.Equally, the penetrable Impeller Machining of minor diameter through hole strengthens on a part of length afterwards.
It should be understood that and to improve the details of the above-mentioned embodiment of the invention shown in Figure 2.Such as, the relative length of through hole first and second parts can be with described different.Equally, through hole not be used in and is mutated into step on the diameter, but the zone that between first and second parts, increases gradually with a diameter.
Further distortion can be installed in a cylindrical sleeve the large diameter relatively part of through hole, and the diameter of sleeve cooperates with the diameter of impeller, supports for impeller provides further on axle.
Other possible replacement is conspicuous to the corresponding techniques personnel.
Claims (8)
1. gas compressor blade wheel assembly, comprise: one is installed in the compressor impeller on the running shaft, axle passes along the through hole of impeller rotating shaft line, through hole has on diameter the first axle part branch with respect to shaft diameter, with the second axle part branch of increased diameter, thereby make the internal surface of through hole second portion and axle that spaced radial be arranged.
2. gas compressor blade wheel assembly as claimed in claim 1 is characterized in that: the shaft shoulder is limited between described first and second shaft portions of through hole in one.
3. gas compressor blade wheel assembly as claimed in claim 1 is characterized in that: through-hole diameter increases between described first and second shaft portions of through hole gradually.
4. as the described gas compressor blade wheel assembly of above-mentioned arbitrary claim, it is characterized in that: the first axle part branch of described through hole stretches out from an axial end of compressor impeller.
5. as the described gas compressor blade wheel assembly of above-mentioned arbitrary claim, it is characterized in that: a cylindrical sleeve is installed in described through hole, radially expands between the outer surface of the internal surface of through hole second portion and axle.
6. the compressor impeller in the rotating shaft that is installed in predetermined diameter, compressor impeller band one axial hole, accepting an end of described axle, through hole has on diameter with respect to the first axle part branch of described predetermined shaft diameter and the diameter the second axle part branch greater than described predetermined shaft diameter.
7. compressor impeller as claimed in claim 6 is characterized in that: a cylindrical sleeve is installed in the second portion of through hole, and the internal diameter of sleeve is corresponding to the diameter of sleeve first portion.
8. a turbocharger, the compressor impeller that the other end of the axle that comprises the turbine that is installed in running shaft one end in the volute and rotate in being installed on volute is provided with, compressor impeller has axially through the through hole between impeller first axial plane and impeller second axial plane, described second axial plane is away from described turbine, wherein through hole has internal diameter corresponding to the first axle part branch of shaft diameter and the second axle part branch of increased diameter, thereby the internal surface of increased diameter part has spaced radial with axle, and the described the first axle part of through hole divides described first axial end extension from the compressor impeller part, to described second axial end of impeller.
Applications Claiming Priority (2)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| GB0224726.0 | 2002-10-24 | ||
| GBGB0224726.0A GB0224726D0 (en) | 2002-10-24 | 2002-10-24 | Compressor wheel assembly |
Publications (1)
| Publication Number | Publication Date |
|---|---|
| CN1499083A true CN1499083A (en) | 2004-05-26 |
Family
ID=9946478
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CNA2003101198134A Pending CN1499083A (en) | 2002-10-24 | 2003-10-24 | Compressor impeller assembly |
Country Status (6)
| Country | Link |
|---|---|
| US (1) | US20040126251A1 (en) |
| EP (1) | EP1413764A3 (en) |
| JP (1) | JP2004144096A (en) |
| KR (1) | KR20040036657A (en) |
| CN (1) | CN1499083A (en) |
| GB (1) | GB0224726D0 (en) |
Cited By (4)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN100465457C (en) * | 2005-12-01 | 2009-03-04 | 发那科株式会社 | Fluid machine |
| CN101057078B (en) * | 2004-11-13 | 2012-02-22 | 奥尔塞特工程有限公司 | Compressor wheel, its manufacture method, compressor wheel assembly and turbocharger |
| CN101315083B (en) * | 2007-05-30 | 2013-09-18 | 诺沃皮尼奥内有限公司 | Anchorage system for the rotors of a rotating fluid machine |
| CN109612863A (en) * | 2018-12-12 | 2019-04-12 | 中国北方发动机研究所(天津) | A kind of pressure booster blower impeller wear test verifying device |
Families Citing this family (10)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| GB0224727D0 (en) * | 2002-10-24 | 2002-12-04 | Holset Engineering Co | Compressor wheel assembly |
| GB0224723D0 (en) * | 2002-10-24 | 2002-12-04 | Holset Engineering Co | Compressor wheel assembly |
| GB0224721D0 (en) * | 2002-10-24 | 2002-12-04 | Holset Engineering Co | Compressor wheel assembly |
| US20070059188A1 (en) * | 2005-09-09 | 2007-03-15 | Borgwarner Inc. | Aerodynamically enhanced bearing housing pocket geometry |
| JP4826417B2 (en) * | 2006-09-29 | 2011-11-30 | 株式会社ジェイテクト | Supercharger |
| DE102010020213A1 (en) * | 2010-05-12 | 2011-11-17 | Bosch Mahle Turbo Systems Gmbh & Co. Kg | Charging device, in particular exhaust gas turbocharger for a motor vehicle |
| DE102010041981A1 (en) * | 2010-10-05 | 2012-04-05 | Bosch Mahle Turbo Systems Gmbh & Co. Kg | loader |
| KR101102567B1 (en) * | 2010-10-20 | 2012-01-04 | 케이넷(주) | Block for preventing influx of gas and water along microtube |
| WO2018174103A1 (en) * | 2017-03-22 | 2018-09-27 | 株式会社Ihi | Rotating body, supercharger, and rotating body manufacturing method |
| KR102419842B1 (en) | 2021-09-24 | 2022-07-12 | 주식회사 제이더블유테크 | Compressor wheel for turbocharger and manufacturing method thereof |
Family Cites Families (15)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| US2377740A (en) * | 1944-03-31 | 1945-06-05 | Gen Electric | Centrifugal compressor |
| US2860827A (en) * | 1953-06-08 | 1958-11-18 | Garrett Corp | Turbosupercharger |
| US3200753A (en) * | 1963-02-07 | 1965-08-17 | Martin Marietta Corp | Turbo-boost pump |
| US3601501A (en) * | 1970-02-26 | 1971-08-24 | John G Johnson | Gas compressor impeller and shaft assembly |
| BE787539A (en) * | 1971-08-27 | 1973-02-14 | Alsthom Cgee | COMPONENTS OF A WELDED ROTOR |
| DE2829150A1 (en) * | 1978-07-03 | 1980-01-24 | Barmag Barmer Maschf | EXHAUST TURBOCHARGER |
| DE3268013D1 (en) * | 1981-08-18 | 1986-01-30 | Bbc Brown Boveri & Cie | Exhaust-gas turbocharger with bearings between turbine and compressor |
| US5163816A (en) * | 1991-07-12 | 1992-11-17 | General Motors Corporation | Wheel lock, centering and drive means and turbocharger impeller combination |
| JP3777648B2 (en) * | 1996-04-03 | 2006-05-24 | 石川島播磨重工業株式会社 | Impeller fastening structure |
| US5895204A (en) * | 1997-08-06 | 1999-04-20 | Carrier Corporation | Drive positioning mechanism for a variable pipe diffuser |
| US6017184A (en) * | 1997-08-06 | 2000-01-25 | Allied Signal Inc. | Turbocharger integrated bearing system |
| DE19736333C1 (en) * | 1997-08-21 | 1999-03-04 | Man B & W Diesel Ag | Mounting for turbine wheel for fluid pump |
| GB0224723D0 (en) * | 2002-10-24 | 2002-12-04 | Holset Engineering Co | Compressor wheel assembly |
| GB0224721D0 (en) * | 2002-10-24 | 2002-12-04 | Holset Engineering Co | Compressor wheel assembly |
| GB0224727D0 (en) * | 2002-10-24 | 2002-12-04 | Holset Engineering Co | Compressor wheel assembly |
-
2002
- 2002-10-24 GB GBGB0224726.0A patent/GB0224726D0/en not_active Ceased
-
2003
- 2003-10-20 EP EP03256586A patent/EP1413764A3/en not_active Withdrawn
- 2003-10-22 US US10/691,093 patent/US20040126251A1/en not_active Abandoned
- 2003-10-24 JP JP2003364667A patent/JP2004144096A/en active Pending
- 2003-10-24 CN CNA2003101198134A patent/CN1499083A/en active Pending
- 2003-10-24 KR KR1020030074547A patent/KR20040036657A/en not_active Application Discontinuation
Cited By (5)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN101057078B (en) * | 2004-11-13 | 2012-02-22 | 奥尔塞特工程有限公司 | Compressor wheel, its manufacture method, compressor wheel assembly and turbocharger |
| US8641380B2 (en) | 2004-11-13 | 2014-02-04 | Cummins Turbo Technologies Limited | Compressor wheel |
| CN100465457C (en) * | 2005-12-01 | 2009-03-04 | 发那科株式会社 | Fluid machine |
| CN101315083B (en) * | 2007-05-30 | 2013-09-18 | 诺沃皮尼奥内有限公司 | Anchorage system for the rotors of a rotating fluid machine |
| CN109612863A (en) * | 2018-12-12 | 2019-04-12 | 中国北方发动机研究所(天津) | A kind of pressure booster blower impeller wear test verifying device |
Also Published As
| Publication number | Publication date |
|---|---|
| GB0224726D0 (en) | 2002-12-04 |
| EP1413764A2 (en) | 2004-04-28 |
| EP1413764A3 (en) | 2005-04-13 |
| KR20040036657A (en) | 2004-04-30 |
| JP2004144096A (en) | 2004-05-20 |
| US20040126251A1 (en) | 2004-07-01 |
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Legal Events
| Date | Code | Title | Description |
|---|---|---|---|
| C06 | Publication | ||
| PB01 | Publication | ||
| C02 | Deemed withdrawal of patent application after publication (patent law 2001) | ||
| WD01 | Invention patent application deemed withdrawn after publication |