GB2058941A - Radial-flow turbine rotors - Google Patents
Radial-flow turbine rotors Download PDFInfo
- Publication number
- GB2058941A GB2058941A GB8024628A GB8024628A GB2058941A GB 2058941 A GB2058941 A GB 2058941A GB 8024628 A GB8024628 A GB 8024628A GB 8024628 A GB8024628 A GB 8024628A GB 2058941 A GB2058941 A GB 2058941A
- Authority
- GB
- United Kingdom
- Prior art keywords
- rotor
- radial
- flow turbine
- main portion
- end fitting
- 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.)
- Withdrawn
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
- 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
- F01D5/04—Blade-carrying members, e.g. rotors for radial-flow machines or engines
- F01D5/043—Blade-carrying members, e.g. rotors for radial-flow machines or engines of the axial inlet- radial outlet, or vice versa, type
- F01D5/048—Form or construction
-
- 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
Landscapes
- Engineering & Computer Science (AREA)
- Mechanical Engineering (AREA)
- General Engineering & Computer Science (AREA)
- Turbine Rotor Nozzle Sealing (AREA)
Abstract
The rotor 30 is hollow and has reinforcement ribs 38 for increasing the strength of the rotor against centrifugal forces. A port 39 connects the interior 33 and exterior of the rotor to prevent excessive pressures from developing inside the rotor. Back plate 35 may be omitted. The rotor may be of ceramic. <IMAGE>
Description
SPECIFICATION
Radial-flow turbine rotors
The invention relates to radial-flow turbine rotors for use in gas turbine engines, turbochargers, or the like. More especially, the invention relates to a radial-flow turbine rotor of hollow construction that provides the rotor with a high strength against centrifugal force and prevents internal air pressure within the rotor from growing excessively high.
Radial-flow turbines, as well as axial-flow turbines, have been used in gas turbine engines, turbo-chargers and the like. In comparison with the axial-flow turbine, the radial-flow turbine is advantageous in that it has a simple construction and can be manufactured easily at a relatively low cost. Moreover, in the radial-flow turbine, the expansion ratio per stage of the gas introduced into vanes of the rotor is higher than that of the axial-flow turbine and output power per unit flow-rate of the applied gas is larger than that of the axialflow turbine, and further a gap between the outer ends of the rotor vanes and the inner surface of a housing therefor hardly affects the hydrodynamic performance. Therefore, in a radial-flow turbine, the output efficiency per stage of the rotor is higher than that of an axial-flow turbine.
Although a radial-flow turbine rotor has advantages as stated above in comparison with the axial-flow turbine rotor, there still remain some problems to be solved. Some of the problems of conventional radial flow turbine rotors will be explained by means of examples with reference to Figs. 1 and 2 of the accompanying drawings.
Fig. 1 shows an example of a conventional radial flow turbine rotor with an axial-flow turbine rotor superimposed for the purpose of explanation. If a radial-flow turbine and an axial-flow turbine are designed based on the same specifications, the radial-flow turbine rotor R has a rotor wheel W of a larger outer diameter and bulk than the base portion B of the axial-flow turbine rotor A. Because of this the total weight of a conventional radial-flow turbine rotor which is not hollow in structure is appreciably larger than that of a corresponding axial-flow turbine rotor, and the moment of inertia of a conventional solid radialflow turbine rotor is relatively large and its accelerating performance may be inferior to that of an axial-flow turbine rotor.
To overcome the above-mentioned problem, there has already been proposed a radial-flow turbine rotor which has a hollow structure so as to reduce the total weight of the rotor and the moment of inertia in comparison with a rotor which is not hollow in structure.
That previously proposed structure is illustrated in Fig. 2 of the drawings. A rotor 10 comprises a plurality of curved vanes 11 and a bell-shaped wheel 1 2 having a hollow structure. A rear wall 1 3 of the wheel 1 2 projects outwards to provide a cylindrical projection 1 5 having an opening co-axial with the rotor 1 0. The rear end surface of the projection 1 5 is non-planar, being formed with a plurality of cogs 23 spaced apart at regular intervals to serve as a coupling with a driving shaft 1 7. A recess 21 is formed co-axially with the driving shaft 1 7 in the front end portion of the shaft.
On the front end surface of the driving shaft 1 7 are formed a plurality of cogs 24 spaced apart at regular intervals to engage with the cogs 23 of the projection 1 5 to constitute a coupling assembly for connecting the rotor 10 and the driving shaft 1 7.
The rotor 10 and the driving shaft 1 7 are cooperably joined at a coupling portion 1 8 in such a manner that a plurality of the cogs 23 and 24 provided on the rear end surface of the projection 1 5 and the front end surface of the driving shaft 1 7 so interengage as to permit relative displacement between the cogs 23 and 24 in the radial direction. By the use of that construction, excessive thermal stress in, or disintegration of, the rotor 10 resulting from substantial differences in thermal expansion between the rotor and the driving shaft 1 7 can be effectively prevented. Accordingly, it is possible to transmit driving power effectively and accurately to the driving shaft 1 7 from the rotor 10.Further, it is also possible to locate the rotor 10 and the driving shaft 1 7 in properly and accurately centred alignment and thus achieve normal and durable operation of the rotor.
A small opening 1 6 is formed co-axially with the rotor 10 in the front portion of the wheel 1 2. A threaded hole 1 9 and a nonthreaded hole 20 are formed in the centre of the driving shaft 1 7 along the axis thereof. A bolt 22 is inserted from the opening 1 6 through the inside of the hollow wheel 1 2 and the opening of the cylindrical projection 1 5 into the hole 20 and then screwed into the threaded hole 1 9 to hold the rotor 10 and the driving shaft 1 7 firmly together in the axial direction.
It should be noted that, although the rotor can be formed of any suitable material, it is preferably formed of a ceramic which has relatively high heat resistance. By forming the rotor of a ceramic, comparatively high heat resistance and durability can be achieved.
In the above construction, however, while high accelerating performance can be achieved by reducing the total weight of the rotor 10 to make the moment of inertia smaller than that of a solid rotor, the strength of the rotor against centrifugal force is lowered because the inside of the rotor is empty.
In more detail, in operation, if the rotor 10 is driven at a high rotational speed, causing a considerable centrifugal force to act on the rotor, an uneven centrifugal stress is applied to various parts of the rotor 10, since the centrifugal stress is concentrated in a central portion 14 of the rear wall 1 3. This may lead to the centrifugal stress exceeding the strength of the material, such as ceramic, forming the rotor 10, especially at the central portion 1 4 of the rear wall 13, causing fatigue or breakage of the central portion.
In addition to the above disadvantage, since the inside of the rotor 10 is substantially sealed once the rotor has been mounted on the shaft 1 7 and the rotor is subjected to introduced gas at high pressure and high temperature during operation, the internal gas pressure within the rotor is increased so that corresponding pressure stress may be generated in the portions around the inside of the rotor to cause fatigue or breakdown of the rotor.
It is an object of the present invention to provide a radial-flow turbine rotor which has a high strength against centrifugal force exerted on the rotor during operation thereof by preventing the centrifugal stress from being concentrated in a specific part of the rotor, while still having a hollow structure and a small moment of inertia.
Another object of the present invention is to provide a radial-flow turbine rotor the internal gas pressure within which is prevented from growing excessively high by arranging that the inside of the rotor is in communication with the outside of the rotor.
A further object of the present invention is to provide a radial-flow turbine rotor that has a simple construction and can be manufactured easily considering its high strength and high accelerating performance.
According to the present invention, there is provided a radial-flow turbine rotor of substantially hollow construction and which is provided with reinforcement means therein, and the inside of which is open to the outside.
Two forms of radial4low turbine constructed in accordance with the invention will now be described by way of example only with reference to Figs. 3 to 5 of the accompanying drawings, in which: Figure 1 is a partial longitudinal sectional view showing a conventional solid radial-flow turbine rotor together with an axial-flow turbine rotor for comparison;
Figure 2 is a longitudinal sectional view showing a previously proposed type of radialflow turbine;
Figure 3 is a longitudinal sectional view showing the first form of radial-flow turbine rotor according to the invention;
Figure 4 is a cross-sectional view taken along the line IV-IV of Fig. 3; and
Figure 5 is a longitudinal sectional view showing the second form of rotor according to the invention.
Referring to Fig. 3 of the drawings, a radialflow turbine rotor is generally designated by the reference numeral 30. The rotor 30 comprises a plurality of curved vanes 31 and a bell-shaped rotor wheel which is substantially hollow in structure, and is designated generally by the reference numeral 32. The rotor, wheel 32 comprises a shrouding wall 34, a hollow shaft 37, a plurality of ribs 38 and a rear wall 35.
The hollow shaft 37 is co-axial with the rotor 30 and extends along the centre axis of the rotor 30 from the axial front end of the wheel 32. The rear end of the shaft 37 extends outward through an opening provided in the centre of the rear wall 35. The rear end of the shaft 37 is provided with a plurality of cogs to form, together with cogs formed at the front end of a driving shaft 41, a coupling portion 42 where the rotor 30 and the driving shaft 41 are coupled together. The hollow shaft 37 is open at both axial ends thereof for receiving a bolt 45 therethrough.A threaded hole 43 and a non-threaded hole 44 are integrally formed in the centre of the driving shaft 41 along the centre axis thereof for receiving the bolt 45 and a recess 48 is formed co-axially with the driving shaft 41 at the axial front end thereof in the same manner as in the rotor described above with reference to Fig. 2.
A plurality of ribs 38 are integrally formed as a reinforcement means on the outer periphery of the shaft 37 and extend outwardly in the radial direction therefrom. The ribs are spaced apart to define a plurality of chambers
33. Thus equal numbers of ribs 38 and chambers 33 are formed, as may be seen from Fig. 4.
At least one hole 39 may be formed as a communication means in the rear wall 35 of each compartment 33, as seen in Fig. 4, so that each compartment communicates with the outside of the rotor. Communication means may also be provided by forming at least one hole (not shown) in each rib 38 so that all of the compartments 33 communicate with each other, and then at least one hole may be formed in the rear wall 35, so that all the compartments 33 communicate with the outside of the rotor 30.
The shrouding wall 34 has a planar radially extending portion at the axial rear end thereof, and at the inward end of the straight portion
is provided a recessed portion 40 into which the rear wall 35 is fitted. The axial depth of the recessed portion 40 should be substantially the same as the thickness of the rear wall 35.
The rear wall 35 is disc-shaped and is
provided with an opening for the hollow shaft
37 to pass through and at least one hole 39
as a communication means as described
above.
With the above component structure in
mind, the assembly process will now be de
scribed.
The rotor may be formed of two separate members, the first comprising the plurality of curved vanes 31, the shrouding wall 34, the hollow shaft 37 and the plurality of ribs 38, and the second comprising the rear wall 35 only. For example, the first member may be formed integrally as one die-casting, such as an injection moulding, slip cast forming, or hydrostatic pressure forming, and the second member, the rear wall 35, may be formed separately.
Next, the rear wall 35 is fitted to the integrally formed member at the recessed portion 40 and on the outer periphery of the hollow shaft 37. Thereafter, the two members are sintered so as to be completely fixed to each other. The particular sintering process will depend on the materials used for the two members. For example, if the material of both members is Silicon (Si), the two members may be first sub-assembled with Silicon slip in the unsintered or pre-sintered state, and then during the process of sintering by chemical reaction in the presence of nitrogen N2 in the atmosphere, the two members are converted to ceramic so as to be chemically and completely fixed together.On the other hand, if the two members are both formed of ceramic powders, such as silicon nitride (Si3 N4) or silicon carbide (SiC), the two members may be first sub-assembled with a slip of material similar to Si3N4 or SiC in the unsintered or pre-sintered state and then the two members may be sintered under normal pressure, or the two members may be first sub-assembled after being separately sintered under normal pressure and then the two members may be again sintered under normal pressure so that they are completely fixed together.
The driving shaft 41 and the rotor 30 meet at the coupling portion 42 and are connected by interengagement of the cogs in the same manner as in the rotor described above with reference to Fig. 2. Next the bolt 45 is inserted through the inside of the hollow shaft 37 into the non-threaded hole 44 and then screwed into the threaded hole 43 to fix the rotor 30 and the driving shaft 41 firmly together in the axial direction.
Although the rotor can be formed of any suitable material, it is preferable to use a ceramic which has a relatively high heat resistance.
With the above construction, the rotor 30 has a small moment of inertia in comparison with a conventional solid rotor so that the accelerating performance is greatly improved, and yet the ribs 38 prevent the centrifugal stress from being concentrated at a root portion 36 of the rear wall 35, so that the centrifugal stress is much less likely to exceed the allowable stress of the ceramic materials.
For example, in the case of hot pressing, the allowable stress is in the range of 60 to 70 kg/mm2, in the case of sintering under normal pressure, it is in the range of 20 to 30 kg/mm2, and in the case of sintering by chemical reaction, it is in the range of 1 2 to 30 kg/mm2. Therefore, the strength of the rotor 30 against centrifugal force is much larger than that of a conventional hollow rotor. Moreover, since the inside of the rotor 30 is in communication with the outside thereof, excessive increases of gas pressure within the rotor can be avoided.
In addition, in the manufacture of the rotor 30, while the rotor has high strength, no components of the rotor are excessively thick relative to the rotor vanes 31, and the total volume and weight of the shrouding wall 34, the hollow shaft 37 and ribs 38 is not very large relative to that of the rotor vanes 31, in comparison with a conventional solid rotor.
Therefore, even if only one moulding operation is used, whether injection moulding, hydrostatic forming, slip cast forming or similar technique, faults generated inside the components of the rotor, such as, for example, cracks, strain or unevenness caused by differences in density will be almost entirely avoided. Further, during degreasing of moulding agents, such as, for example, thermoplastic resin or starch employed at the time of forming the rotor, the present construction avoids the production of cracks and so on which are apt to be generated at relatively thick portions because of the gas pressure within the compartments of the rotor arising from the presence of volatile substances.
Referring to Fig. 5, the construction of the second form of rotor is the same as that of the first form of rotor except that the rear wall 35 is omitted, and, accordingly, no holes are required in the ribs 38 and the inner surface of the shrouding wall 34 is not provided with any shaped portion corresponding to the recessed portion 40 of the rotor shown in Fig.
3.
By this construction, in comparison with the embodiment shown in Fig. 3, the rotor 30 is provided with higher strength against centrifugal forces and the inside of the rotor is completely open to the outside, giving more efficient communication between the inside and the outside, and further, since there are no processes for forming the rear wall or for coupling the rear wall to the other integrally formed member, manufacturing costs can be considerably reduced. On the other hand, the accelerating performance of the rotor shown in Fig. 5 is a little lower than that of the rotor shown in Fig. 3 since windage losses are generated in operation of the rotor by the ribs 38 and adversely affect the accelerating performance.
It is to be understood that the invention is not limited to the embodiments described above and that various changes and modifications may be made without departing from the spirit and scope of the invention as defined in the appended claims. In particular, various materials may be used for the rotor 30 and various fixing means may be used for coupling the rear wall 35 with the other member of the rotor 30, and further the communication means between the inside and the outside of the rotor and the reinforcement means for the rotor may be widely varied in ways which will be clear to those skilled in the relevant art.
Claims (11)
1. A radial-flow turbine rotor which has a rotor wheel of substantially hollow construction and a cylindrical hollow shaft extending through the rotor wheel along the rotational axis of the wheel, and which includes: a radial reinforcement member provided within the interior of said rotor wheel for increasing the strength of the rotor and reinforcing the root portion of the rotor against the effects of centrifugal forces; the interior of the rotor wheel being in communication with the exterior of the rotor wheel to allow gas to flow between the said interior and the said exterior.
2. A radial-flow turbine rotor as claimed in claim 1, wherein the reinforcement member comprises a plurality of ribs extending radially between the hollow shaft and the internal surface of a circumferential sloped wall of the rotor wheel.
3. A radial-flow turbine rotor as claimed in claim 2, wherein the ribs partition the interior of the rotor wheel into a plurality of chambers each of which communicates with the exterior of the rotor wheel.
4. A radial-flow turbine rotor as claimed in claim 3, wherein the rotor wheel comprises a main portion and an end fitting formed separately from said main portion and closing the rear open end of the main portion, the end fitting is formed with a plurality of openings each of which corresponds to one of the chambers formed within the interior of said rotor wheel in order to establish communication between the inside and the outside of the rotor wheel.
5. A radial-flow turbine rotor as claimed in claim 2, wherein the rotor wheel comprises a main portion and an end fitting formed separately from the main portion and closing the rear open end of the main portion, the end fitting is formed with an opening corresponding to one of the chambers defined within the rotor wheel by the ribs and the ribs are formed with openings for communication between the adjacent chambers.
6. A radial-flow turbine rotor as claimed in any one of claims 1 to 5, wherein the hollow shaft has means for interengagement with a driving shaft at the rear end thereof.
7. A radial-flow turbine rotor as claimed in claim 6, wherein the means for interengagement between the hollow shaft and the driving shaft is a plurality of interengagible cogs formed on mating ends of the hollow shaft and the driving shaft.
8. A radial-flow turbine rotor as claimed in claim 6 or claim 7, wherein the hollow shaft and the driving shaft are held in interengaged position by a retaining screw passing through said hollow shaft and engaging with said driving shaft.
9. A radial-flow turbine rotor as set forth in claim 4 or claim 5, wherein the main portion and the end fitting of the rotor wheel are formed of silicon, and are fitted together by sub-assembling the main portion and the end fitting with silicon slip in an unsintered or pre-sintered state; and sintering the main portion and end fitting pre-assembly by chemical reaction in the presence of an atmosphere comprising nitrogen in order to convert to ceramic.
1 0. A radial-flow turbine rotor as claimed in claim 4 or claim 5, wherein the main portion and the end fitting of the rotor wheel are formed of ceramic powder and are fitted together by sub-assembling the main portion and the end fitting with the same material as forming the main portion and the end fitting in the unsintered or pre-sintered state; and sintering the sub-assembly under normal pressure.
11. A radial-flow turbine rotor as claimed in claim 4 or claim 5, wherein the main portion and the end fitting of the rotor wheel are formed from ceramic powder and are fitted together by sintering each of the main portion and the end fitting under normal pressure, independently; and sintering together under normal pressure.
1 2. A radial-flow turbine rotor substantially as hereinbefore described with reference to, and as shown in, Figs. 3 and 4, or Fig. 5, of the accompanying drawings.
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| JP9604879A JPS5925083B2 (en) | 1979-07-30 | 1979-07-30 | radial turbine rotor |
Publications (1)
| Publication Number | Publication Date |
|---|---|
| GB2058941A true GB2058941A (en) | 1981-04-15 |
Family
ID=14154576
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| GB8024628A Withdrawn GB2058941A (en) | 1979-07-30 | 1980-07-28 | Radial-flow turbine rotors |
Country Status (3)
| Country | Link |
|---|---|
| JP (1) | JPS5925083B2 (en) |
| DE (1) | DE3028558A1 (en) |
| GB (1) | GB2058941A (en) |
Cited By (16)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| EP0808989A1 (en) * | 1996-05-23 | 1997-11-26 | Alcatel | Impeller for a radial turbine |
| US7281901B2 (en) * | 2004-12-29 | 2007-10-16 | Caterpillar Inc. | Free-form welded power system component |
| EP1956189A1 (en) * | 2007-02-12 | 2008-08-13 | Daido Castings Co., Ltd. | Turbine wheel for a turbocharger |
| CN102996598A (en) * | 2011-09-09 | 2013-03-27 | 迪尔公司 | Disk gang bolt tensioning structure |
| US8424305B2 (en) | 2003-05-15 | 2013-04-23 | Volvo Lastvagnar Ab | Turbo compressor system for an internal combustion engine comprising a compressor of radial type and provided with an impeller with backswept blades |
| US20140072404A1 (en) * | 2012-09-07 | 2014-03-13 | Robert Bosch Gmbh | Blade wheel for a continuous-flow machine and method for producing a turbine wheel for a continuous-flow machine |
| WO2015062802A1 (en) * | 2013-10-29 | 2015-05-07 | Continental Automotive Gmbh | Compressor wheel composed of a plurality of components |
| US9260971B2 (en) | 2009-10-07 | 2016-02-16 | Mitsubishi Heavy Industries, Ltd. | Turbine rotor |
| WO2018106539A1 (en) * | 2016-12-05 | 2018-06-14 | Cummins Filtration Ip, Inc. | Separation assembly with a single-piece impulse turbine |
| WO2018153446A1 (en) * | 2017-02-22 | 2018-08-30 | Zollern Gmbh & Co. Kg | Turbine impeller, in particular for an exhaust gas turbocharger |
| WO2020136473A1 (en) * | 2018-12-27 | 2020-07-02 | Atlas Copco Airpower, Naamloze Vennootschap | Impeller and turbocompressor equipped with such impeller and method for manufacturing such an impeller |
| BE1026931B1 (en) * | 2018-12-27 | 2020-07-27 | Atlas Copco Airpower Nv | Impeller and turbocharger equipped with such impeller |
| JP2020115015A (en) * | 2015-10-02 | 2020-07-30 | 株式会社Ihi | Impeller and supercharger |
| US11352999B2 (en) | 2018-04-17 | 2022-06-07 | Cummins Filtration Ip, Inc | Separation assembly with a two-piece impulse turbine |
| US11471808B2 (en) | 2017-01-09 | 2022-10-18 | Cummins Filtration Ip, Inc. | Impulse turbine with non-wetting surface for improved hydraulic efficiency |
| US12030063B2 (en) | 2018-02-02 | 2024-07-09 | Cummins Filtration Ip, Inc. | Separation assembly with a single-piece impulse turbine |
Families Citing this family (4)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| JPS60101201A (en) * | 1983-11-08 | 1985-06-05 | Ngk Spark Plug Co Ltd | Joining structure in turbine shaft |
| JPH074792A (en) * | 1993-06-16 | 1995-01-10 | Matsushita Refrig Co Ltd | Refrigerator |
| DE102016213238A1 (en) * | 2016-07-20 | 2018-01-25 | Man Diesel & Turbo Se | Radial turbine rotor and method of making same |
| DE102016217349A1 (en) | 2016-09-12 | 2018-03-15 | Robert Bosch Gmbh | Impeller for a turbine and method of making an impeller |
-
1979
- 1979-07-30 JP JP9604879A patent/JPS5925083B2/en not_active Expired
-
1980
- 1980-07-28 GB GB8024628A patent/GB2058941A/en not_active Withdrawn
- 1980-07-28 DE DE19803028558 patent/DE3028558A1/en not_active Withdrawn
Cited By (27)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| FR2749038A1 (en) * | 1996-05-23 | 1997-11-28 | Alsthom Cge Alcatel | RADIAL TURBINE WHEEL |
| EP0808989A1 (en) * | 1996-05-23 | 1997-11-26 | Alcatel | Impeller for a radial turbine |
| US8424305B2 (en) | 2003-05-15 | 2013-04-23 | Volvo Lastvagnar Ab | Turbo compressor system for an internal combustion engine comprising a compressor of radial type and provided with an impeller with backswept blades |
| US7281901B2 (en) * | 2004-12-29 | 2007-10-16 | Caterpillar Inc. | Free-form welded power system component |
| CN1800587B (en) * | 2004-12-29 | 2011-11-23 | 卡特彼勒公司 | Free-form welded power system component |
| EP1956189A1 (en) * | 2007-02-12 | 2008-08-13 | Daido Castings Co., Ltd. | Turbine wheel for a turbocharger |
| US9260971B2 (en) | 2009-10-07 | 2016-02-16 | Mitsubishi Heavy Industries, Ltd. | Turbine rotor |
| CN102996598A (en) * | 2011-09-09 | 2013-03-27 | 迪尔公司 | Disk gang bolt tensioning structure |
| CN102996598B (en) * | 2011-09-09 | 2016-05-04 | 迪尔公司 | Disc harrow group bolt tightening structure and tension method thereof |
| US20140072404A1 (en) * | 2012-09-07 | 2014-03-13 | Robert Bosch Gmbh | Blade wheel for a continuous-flow machine and method for producing a turbine wheel for a continuous-flow machine |
| CN103670531A (en) * | 2012-09-07 | 2014-03-26 | 罗伯特·博世有限公司 | Impeller for a fluid machine and method for manufacturing a turbine for a fluid machine |
| WO2015062802A1 (en) * | 2013-10-29 | 2015-05-07 | Continental Automotive Gmbh | Compressor wheel composed of a plurality of components |
| JP2020115015A (en) * | 2015-10-02 | 2020-07-30 | 株式会社Ihi | Impeller and supercharger |
| US10781823B2 (en) | 2015-10-02 | 2020-09-22 | Ihi Corporation | Impeller and supercharger |
| WO2018106539A1 (en) * | 2016-12-05 | 2018-06-14 | Cummins Filtration Ip, Inc. | Separation assembly with a single-piece impulse turbine |
| CN110049820A (en) * | 2016-12-05 | 2019-07-23 | 康明斯过滤Ip公司 | Separation assembly with single-piece impulse turbine machine |
| CN110049820B (en) * | 2016-12-05 | 2021-07-20 | 康明斯过滤Ip公司 | Separation Assemblies with One-Piece Impulse Turbines |
| US11458484B2 (en) | 2016-12-05 | 2022-10-04 | Cummins Filtration Ip, Inc. | Separation assembly with a single-piece impulse turbine |
| US11471808B2 (en) | 2017-01-09 | 2022-10-18 | Cummins Filtration Ip, Inc. | Impulse turbine with non-wetting surface for improved hydraulic efficiency |
| WO2018153446A1 (en) * | 2017-02-22 | 2018-08-30 | Zollern Gmbh & Co. Kg | Turbine impeller, in particular for an exhaust gas turbocharger |
| US12030063B2 (en) | 2018-02-02 | 2024-07-09 | Cummins Filtration Ip, Inc. | Separation assembly with a single-piece impulse turbine |
| US11352999B2 (en) | 2018-04-17 | 2022-06-07 | Cummins Filtration Ip, Inc | Separation assembly with a two-piece impulse turbine |
| WO2020136473A1 (en) * | 2018-12-27 | 2020-07-02 | Atlas Copco Airpower, Naamloze Vennootschap | Impeller and turbocompressor equipped with such impeller and method for manufacturing such an impeller |
| CN111379738A (en) * | 2018-12-27 | 2020-07-07 | 阿特拉斯·科普柯空气动力股份有限公司 | Impeller, turbo compressor equipped with an impeller, and method for manufacturing an impeller |
| BE1026931B1 (en) * | 2018-12-27 | 2020-07-27 | Atlas Copco Airpower Nv | Impeller and turbocharger equipped with such impeller |
| BE1026932B1 (en) * | 2018-12-27 | 2020-07-28 | Atlas Copco Airpower Nv | Impeller and turbocharger equipped with such impeller and method of manufacturing impeller |
| US11878347B2 (en) | 2018-12-27 | 2024-01-23 | Atlas Copco Airpower, Naamloze Vennootschap | Impeller and turbocompressor equipped with such impeller and method for manufacturing such an impeller |
Also Published As
| Publication number | Publication date |
|---|---|
| JPS5925083B2 (en) | 1984-06-14 |
| DE3028558A1 (en) | 1981-02-19 |
| JPS5620705A (en) | 1981-02-26 |
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