CN104005797B - Gas turbine rotor supporting mechanism and the gas turbine with this supporting mechanism - Google Patents
Gas turbine rotor supporting mechanism and the gas turbine with this supporting mechanism Download PDFInfo
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- CN104005797B CN104005797B CN201410244256.7A CN201410244256A CN104005797B CN 104005797 B CN104005797 B CN 104005797B CN 201410244256 A CN201410244256 A CN 201410244256A CN 104005797 B CN104005797 B CN 104005797B
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- 230000007246 mechanism Effects 0.000 title claims abstract description 42
- 230000036316 preload Effects 0.000 claims description 33
- 238000000034 method Methods 0.000 claims description 18
- 238000012856 packing Methods 0.000 claims description 12
- 238000005096 rolling process Methods 0.000 claims description 4
- 239000002131 composite material Substances 0.000 claims description 3
- 229920001971 elastomer Polymers 0.000 claims description 3
- 239000000806 elastomer Substances 0.000 claims description 3
- 239000012634 fragment Substances 0.000 claims description 3
- 230000002093 peripheral effect Effects 0.000 claims description 3
- 230000008901 benefit Effects 0.000 description 2
- 230000008859 change Effects 0.000 description 2
- 230000009286 beneficial effect Effects 0.000 description 1
- 230000005540 biological transmission Effects 0.000 description 1
- 238000013461 design Methods 0.000 description 1
- 238000011161 development Methods 0.000 description 1
- 230000000694 effects Effects 0.000 description 1
- 230000006872 improvement Effects 0.000 description 1
- 238000012986 modification Methods 0.000 description 1
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Abstract
The invention discloses a kind of gas turbine rotor supporting mechanism and the gas turbine with this supporting mechanism.Gas turbine rotor supporting mechanism, comprise and be located at gas turbine rotor wheel disc both sides for supporting the ball bearing of gas turbine rotor, ball bearing comprises the first ball bearing be located on the rotor shaft of gas turbine rotor wheel disc first side and the second ball bearing be located on the rotor shaft of rotor disk second side, first ball bearing comprises the first outer shroud, and the first outer shroud is provided with in order to apply axial force to gas turbine rotor and to cushion the elastic mechanism of gas turbine rotor axial force; Second ball bearing is set to the thrust bearing bearing gas turbine rotor axial force.Gas turbine axial carrying capacity can be improved, eliminate the problem of light load slipping; The structure stability of whole supporting mechanism under the state of running up is good.
Description
Technical field
The present invention relates to gas turbine structure field, especially, relate to a kind of gas turbine rotor supporting mechanism.In addition, the invention still further relates to a kind of gas turbine comprising above-mentioned supporting mechanism.
Background technique
Gas turbine is rotating machinery at a high speed, and the working speed of microminiature gas turbine, usually at more than 40000r/min, has striden across rotor second order even three rank critical speed of rotation.The sharply change of rotating speed brings the pressure in cross section before and after gas compressor and turbine, the surge of temperature or swashs and subtracts, and the axial force Rapid Variable Design causing rotor is even reverse, can cause gas turbine bearing light load slipping or bearing capacity inadequate.
In order to the shafting stability of gas turbine, the normal mode support rotor adopting ball bearing and stick roller bearing to coordinate both at home and abroad, the axial force of rotor is delivered on stator casing by ball bearing.But although ball bearing coordinates supporting way to be easy to assemble with stick roller bearing, because the axial force of rotor can only be passed by a ball bearing, so the whole rotor axial force of bearing is limited and affect life-span of bearing.
Summary of the invention
The object of the invention is to provide a kind of gas turbine rotor supporting mechanism and the gas turbine with this supporting mechanism, and the supporting way coordinated with stick roller bearing to solve existing ball bearing causes that gas turbine axial carrying capacity is low, the technical problem of easy light load slipping etc.
For achieving the above object, the technical solution used in the present invention is as follows:
A kind of gas turbine rotor supporting mechanism, comprise and be located at gas turbine rotor wheel disc both sides for supporting the ball bearing of gas turbine rotor, ball bearing comprises the first ball bearing be located on the rotor shaft of gas turbine rotor wheel disc first side and the second ball bearing be located on the rotor shaft of rotor disk second side, first ball bearing comprises the first outer shroud, and the first outer shroud of the first ball bearing is provided with in order to apply axial force to gas turbine rotor and to cushion the elastic mechanism of gas turbine rotor axial force; Second ball bearing is set to the thrust bearing bearing gas turbine rotor axial force.
Further, elastic mechanism comprises along the axial arranged of gas turbine rotor and one end is fixed on the elasticity preload piece on the first outer shroud and the fixed charge method end plate in order to fixing elasticity preload piece free end; The first end of elasticity preload piece is fixed on the axle side end face of the first outer shroud, second end of elasticity preload piece is fixed on fixed charge method end plate, fixed charge method end plate is fixed on gas turbine stator, compresses the first outer shroud apply axial force to gas turbine rotor by elasticity preload piece; Elasticity preload piece is preloading spring or pretension shell fragment.Also can cancel fixed charge method end plate, the free end of elasticity preload piece is directly fixed on gas turbine stator.
Further, elasticity preload piece is set to multiple, and multiple elasticity preload piece is equidistantly arranged along the circumference of gas turbine rotor; Multiple elasticity preload piece is fixed on same fixed charge method end plate, or each elasticity preload piece is connected to one piece of fixed charge method end plate.
Further, ball bearing all adopts half inner ring three-point contact ball bearing.
Further, the second ball bearing comprises the second outer shroud, is arranged with the expansion controlling ring-shaped insert preventing the second outer shroud from circumferentially rolling outside the second outer shroud; Second outer shroud is connected by interference fit with expansion controlling ring-shaped insert.
Further, expansion controlling ring-shaped insert peripheral hardware has the flexible strutting piece reducing support stiffness and adjustment gas turbine rotor critical speed of rotation, expansion controlling ring-shaped insert is arranged in gas turbine stator by flexible strutting piece, and flexible strutting piece is at least one in elastic ring, spring sheet, elastomer block, elastic strip.
Further, the axle side upper cover that the gas turbine stator of the second ball bearing is housed has taper cover plate, taper back-up ring is sealed in gas turbine stator by taper cover plate, the conical surface direction of taper cover plate is contrary with the conical surface setting direction of taper back-up ring, carries out self-alignment between taper cover plate and taper back-up ring by cone match to the second outer shroud.
Further, the axle side end face of the composite structure of the second outer shroud, expansion controlling ring-shaped insert and flexible strutting piece three is fitted with the adjustment packing ring in order to buffer shaft side external force; The gap compensating the second outer shroud thermal expansion is left between adjustment packing ring and taper back-up ring.
Further, the gap≤0.1mm between taper back-up ring and adjustment packing ring.
According to a further aspect in the invention, additionally provide a kind of gas turbine, comprise gas turbine rotor and gas turbine stator, supported by above-mentioned gas turbine rotor supporting mechanism between gas turbine rotor and gas turbine stator.
The present invention has following beneficial effect:
Gas turbine rotor supporting mechanism of the present invention, by laying ball bearing in order to support gas turbine rotor in the both sides of gas turbine rotor wheel disc; By arranging elastic mechanism in order to apply axial force to gas turbine rotor and to cushion gas turbine rotor axial force on the first ball bearing; Second ball bearing is set to thrust bearing in order to bear gas turbine rotor axial force; Improve gas turbine axial carrying capacity by cooperatively interacting between the first ball bearing and the second ball bearing, eliminate the problem of light load slipping; The structure stability of whole supporting mechanism under the state of running up is good.The axial force of whole rotor can be shared with two ball bearings, expand the excursion of the axial force that bearing can bear, extend bearing life.
Except object described above, feature and advantage, the present invention also has other object, feature and advantage.Below with reference to figure, the present invention is further detailed explanation.
Accompanying drawing explanation
The accompanying drawing forming a application's part is used to provide a further understanding of the present invention, and schematic description and description of the present invention, for explaining the present invention, does not form inappropriate limitation of the present invention.In the accompanying drawings:
Fig. 1 is the structural representation of the gas turbine rotor supporting mechanism of the preferred embodiment of the present invention;
Fig. 2 is the partial enlargement structural representation at A position in Fig. 1.
Marginal data:
1, gas turbine rotor wheel disc; 2, gas turbine rotor; 3, ball bearing; 301, the first ball bearing; 3011, the first outer shroud; 302, the second ball bearing; 3021, the second outer shroud; 4, elastic mechanism; 401, elasticity preload piece; 402, fixed charge method end plate; 5, gas turbine stator; 6, expansion controlling ring-shaped insert; 7, flexible strutting piece; 8, taper cover plate; 9, taper back-up ring; 10, packing ring is adjusted.
Embodiment
Below in conjunction with accompanying drawing, embodiments of the invention are described in detail, but the present invention can by the multitude of different ways that limits and cover implement.
Fig. 1 is the structural representation of the gas turbine rotor supporting mechanism of the preferred embodiment of the present invention; Fig. 2 is the partial enlargement structural representation at A position in Fig. 1.As depicted in figs. 1 and 2, the gas turbine rotor supporting mechanism of the present embodiment, comprise and be located at gas turbine rotor wheel disc 1 both sides for supporting the ball bearing 3 of gas turbine rotor 2, ball bearing 3 comprises the first ball bearing 301 be located on gas turbine rotor wheel disc 1 first side rotor shaft and the second ball bearing 302 be located on the rotor shaft of rotor disk second side, first ball bearing 301 comprises the first outer shroud 3011, first outer shroud 3011 and is provided with in order to apply axial force to gas turbine rotor 2 and to cushion the elastic mechanism 4 of gas turbine rotor 2 axial force; Second ball bearing 302 is set to the thrust bearing bearing gas turbine rotor 2 axial force.Gas turbine rotor supporting mechanism of the present invention, by laying ball bearing 3 in order to support gas turbine rotor 2 in the both sides of gas turbine rotor wheel disc 1; By arranging elastic mechanism 4 in order to apply axial force to gas turbine rotor 2 and to cushion gas turbine rotor 2 axial force on the first ball bearing 301; Second ball bearing 302 is set to thrust bearing in order to bear gas turbine rotor 2 axial force; Improve gas turbine axial carrying capacity by cooperatively interacting between the first ball bearing 301 and the second ball bearing 302, eliminate the problem of light load slipping; The structure stability of whole supporting mechanism under the state of running up is good.The axial force of whole rotor can be shared with two ball bearings, expand the excursion of the axial force that bearing can bear, extend bearing life.Preferably, leave gap when ball bearing is installed, the thermal distortion of bearing can be compensated, prevent outer shroud from rotating by expansion controlling ring-shaped insert simultaneously.
In the present embodiment, elastic mechanism 4 comprises along the axial arranged of gas turbine rotor 2 and one end is fixed on the elasticity preload piece 401 on the first outer shroud 3011 and the fixed charge method end plate 402 in order to fixing elasticity preload piece 401 free end; The first end of elasticity preload piece 401 is fixed on the axle side end face of the first outer shroud 3011, second end of elasticity preload piece 401 is fixed on fixed charge method end plate 402, fixed charge method end plate 402 is fixed on gas turbine stator 5, compresses the first outer shroud 3011 pairs of gas turbine rotors 2 apply axial force by elasticity preload piece 401; Elasticity preload piece 401 is preloading spring or pretension shell fragment.
In the present embodiment, elasticity preload piece 401 is set to multiple, and multiple elasticity preload piece 401 is equidistantly arranged along the circumference of gas turbine rotor 2; Multiple elasticity preload piece 401 is fixed on same fixed charge method end plate 402, or each elasticity preload piece 401 is connected to one piece of fixed charge method end plate 402.
In the present embodiment, ball bearing 3 all adopts half inner ring three-point contact ball bearing.Be convenient to bearing install.Bearing adopts three point contact, and the stability of structure is better, load, power transmission better effects if.
In the present embodiment, the second ball bearing 302 comprises the expansion controlling ring-shaped insert 6 being arranged with outside the second outer shroud 3021, second outer shroud 3021 to prevent the second outer shroud 3021 from circumferentially rolling; Second outer shroud 3021 is connected by interference fit with expansion controlling ring-shaped insert 6.
In the present embodiment, expansion controlling ring-shaped insert 6 peripheral hardware has the flexible strutting piece 7 reducing support stiffness and adjustment gas turbine rotor 2 critical speed of rotation, expansion controlling ring-shaped insert 6 is arranged in gas turbine stator 5 by flexible strutting piece 7, and flexible strutting piece 7 is at least one in elastic ring, spring sheet, elastomer block, elastic strip.
In the present embodiment, the axle side upper cover that the gas turbine stator 5 of the second ball bearing 302 is housed has taper cover plate 8, taper back-up ring 9 is sealed in gas turbine stator 5 by taper cover plate 8, the conical surface direction of taper cover plate 8 is contrary with the conical surface setting direction of taper back-up ring 9, carries out self-alignment between taper cover plate 8 and taper back-up ring 9 by cone match to the second outer shroud 3021.
In the present embodiment, the axle side end face of the composite structure of the second outer shroud 3021, expansion controlling ring-shaped insert 6 and flexible strutting piece 7 three is fitted with the adjustment packing ring 10 in order to buffer shaft side external force; The gap compensating the second outer shroud 3021 thermal expansion is left between adjustment packing ring 10 and taper back-up ring 9.
In the present embodiment, the gap≤0.1mm between taper back-up ring 9 and adjustment packing ring 10.
The gas turbine of the present embodiment, comprises gas turbine rotor 2 and gas turbine stator 5, is supported between gas turbine rotor 2 and gas turbine stator 5 by above-mentioned gas turbine rotor supporting mechanism.
During enforcement, gas turbine rotor 2 is arranged on two two half inner ring three-point contact ball bearings (ball bearing 3), one of them two half inner ring three-point contact ball bearing compresses the outer shroud of two half inner ring three-point contact ball bearing by preloading spring (elasticity preload piece 401), apply axial force to gas turbine rotor 2, the size of axial force is in the 1/4-3/4 of axial force when equaling gas turbine rated operation.Preferably, the size of axial force is in 1/2 of axial force when equaling gas turbine rated operation.Another half inner ring three point contact ball axle is thrust bearing, the outer shroud of this half inner ring three point contact ball axle and expansion controlling ring-shaped insert 6 interference fit, prevents outer shroud circumference from rolling.Elastic ring or spring sheet (flexible strutting piece 7) can be installed outside expansion controlling ring-shaped insert 6, reduce support stiffness, the critical speed of rotation that adjustment gas turbine rotor 2 is pacified, make the working speed of gas turbine avoid critical speed of rotation.
The axial force that gas turbine work produces offsets a part by preloading spring, and another part is delivered on casing by thrust bearing, and the axial force of rotor shared by two bearings, improves the life-span of bearing.
The outer shroud of thrust bearing is fixed on gas turbine stator 5 by taper cover plate 8, taper back-up ring 9 and adjustment packing ring 10, controls preset clearance within 0.1 by adjustment packing ring 10.During gas turbine running, temperature rises, by the thermal expansion of this backlash compensation outer race.Taper cover plate 8 and taper back-up ring 9 cooperatively interact, and ensure that outer shroud fixes self-alignment.
Gas turbine uses two ball bearing to add the rotor supporting structure form of spring pre-tightening.Spring applies the mode of axial force to bearing: preloading spring compresses outer shroud, and the number of spring can be multiple, and the direction of applying can change (can from the left side of axis also can from the right of axis), and the bearing simultaneously acted on can be any one.
When the size of initial tension of spring approximates gas turbine rated operation axial force 1/2; Thrust bearing outer shroud and fixing preset clearance control within 0.1; The means of fixation of thrust bearing adopts cone match self-alignment; Outer race adopts expansion controlling ring-shaped insert interference fit anti-rotation.The axial force of whole rotor can be shared with two ball bearings, expand the excursion of the axial force that bearing can bear, extend bearing life; Positioning bearing leaves gap when installing, and can compensate the thermal distortion of bearing, prevent outer shroud from rotating simultaneously by expansion controlling ring-shaped insert.Certain type gas turbine of this gas turbine rotor supporting mechanism is used to be successfully completed principle prototype development.Use the gas turbine stable working of this supporting structure, vibrate little.
The foregoing is only the preferred embodiments of the present invention, be not limited to the present invention, for a person skilled in the art, the present invention can have various modifications and variations.Within the spirit and principles in the present invention all, any amendment done, equivalent replacement, improvement etc., all should be included within protection scope of the present invention.
Claims (9)
1. a gas turbine rotor supporting mechanism, comprises and is located at gas turbine rotor wheel disc (1) both sides for supporting the ball bearing (3) of gas turbine rotor (2),
Described ball bearing (3) comprises the first ball bearing (301) be located on described gas turbine rotor wheel disc (1) first side rotor shaft and the second ball bearing (302) be located on the rotor shaft of rotor disk second side
It is characterized in that,
Described first ball bearing (301) comprises the first outer shroud (3011),
Described first outer shroud (3011) is provided with in order to apply axial force to described gas turbine rotor (2) and to cushion the elastic mechanism (4) of described gas turbine rotor (2) axial force;
Described second ball bearing (302) is set to the thrust bearing bearing described gas turbine rotor (2) axial force;
Described elastic mechanism (4) comprises along the axial arranged of described gas turbine rotor (2) and one end is fixed on the elasticity preload piece (401) on described first outer shroud (3011) and the fixed charge method end plate (402) in order to fixing described elasticity preload piece (401) free end;
The first end of described elasticity preload piece (401) is fixed on the axle side end face of described first outer shroud (3011),
Second end of described elasticity preload piece (401) is fixed on described fixed charge method end plate (402),
Described fixed charge method end plate (402) is fixed on gas turbine stator (5),
Compress described first outer shroud (3011) by described elasticity preload piece (401) and axial force is applied to described gas turbine rotor (2);
Described elasticity preload piece (401) is preloading spring or pretension shell fragment.
2. gas turbine rotor supporting mechanism according to claim 1, is characterized in that,
Described elasticity preload piece (401) is set to multiple,
Multiple described elasticity preload piece (401) is equidistantly arranged along the circumference of described gas turbine rotor (2);
Multiple described elasticity preload piece (401) is fixed on fixed charge method end plate described in same (402),
Or elasticity preload piece (401) described in each is connected to one piece of described fixed charge method end plate (402).
3. gas turbine rotor supporting mechanism according to claim 1, is characterized in that, described ball bearing (3) all adopts half inner ring three-point contact ball bearing.
4. gas turbine rotor supporting mechanism according to claim 1, is characterized in that,
Described second ball bearing (302) comprises the second outer shroud (3021),
The expansion controlling ring-shaped insert (6) preventing described second outer shroud (3021) from circumferentially rolling is arranged with outside described second outer shroud (3021);
Described second outer shroud (3021) is connected by interference fit with described expansion controlling ring-shaped insert (6).
5. gas turbine rotor supporting mechanism according to claim 4, is characterized in that,
Described expansion controlling ring-shaped insert (6) peripheral hardware has the flexible strutting piece (7) reducing support stiffness and adjustment described gas turbine rotor (2) critical speed of rotation,
Described expansion controlling ring-shaped insert (6) is arranged in described gas turbine stator (5) by flexible strutting piece (7),
Described flexible strutting piece (7) is elastic ring, at least one in spring sheet, elastomer block, elastic strip.
6. gas turbine rotor supporting mechanism according to claim 5, is characterized in that,
The axle side upper cover that the described gas turbine stator (5) of described second ball bearing (302) is housed has taper cover plate (8),
Taper back-up ring (9) is sealed in described gas turbine stator (5) by described taper cover plate (8),
The conical surface direction of described taper cover plate (8) is contrary with the conical surface setting direction of described taper back-up ring (9),
By cone match, self-alignment is carried out to described second outer shroud (3021) between described taper cover plate (8) and described taper back-up ring (9).
7. gas turbine rotor supporting mechanism according to claim 6, is characterized in that,
The axle side end face of the composite structure of described second outer shroud (3021), described expansion controlling ring-shaped insert (6) and described flexible strutting piece (7) three is fitted with the adjustment packing ring (10) in order to buffer shaft side external force;
The gap compensating the thermal expansion of described second outer shroud (3021) is left between described adjustment packing ring (10) and described taper back-up ring (9).
8. gas turbine rotor supporting mechanism according to claim 7, is characterized in that, the described gap≤0.1mm between described taper back-up ring (9) and described adjustment packing ring (10).
9. a gas turbine, comprise gas turbine rotor (2) and gas turbine stator (5), it is characterized in that, supported by the gas turbine rotor supporting mechanism such as according to any one of claim 1 to 8 between gas turbine rotor (2) and gas turbine stator (5).
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201410244256.7A CN104005797B (en) | 2014-06-04 | 2014-06-04 | Gas turbine rotor supporting mechanism and the gas turbine with this supporting mechanism |
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| Application Number | Priority Date | Filing Date | Title |
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| CN201410244256.7A CN104005797B (en) | 2014-06-04 | 2014-06-04 | Gas turbine rotor supporting mechanism and the gas turbine with this supporting mechanism |
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| Publication Number | Publication Date |
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| CN104005797A CN104005797A (en) | 2014-08-27 |
| CN104005797B true CN104005797B (en) | 2015-12-30 |
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| Application Number | Title | Priority Date | Filing Date |
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| CN201410244256.7A Active CN104005797B (en) | 2014-06-04 | 2014-06-04 | Gas turbine rotor supporting mechanism and the gas turbine with this supporting mechanism |
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Families Citing this family (4)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN105822366B (en) * | 2016-04-20 | 2017-07-21 | 中国科学院工程热物理研究所 | A kind of engine low pressure rotor supporting structure that there is fusing to design |
| CN106351965A (en) * | 2016-08-31 | 2017-01-25 | 中国南方航空工业(集团)有限公司 | Support connection structure and gas turbine with same |
| CN111188686B (en) * | 2020-01-19 | 2021-03-30 | 中国科学院工程热物理研究所 | Double-ball bearing supporting structure for preventing light load from slipping |
| CN115949670B (en) * | 2023-03-09 | 2023-06-30 | 中国航发四川燃气涡轮研究院 | Elastic structure for axial compression of bearing |
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| US4676667A (en) * | 1985-03-13 | 1987-06-30 | Nissan Motor Co., Ltd. | Variable preload shaft bearing for turbocharger |
| US5051061A (en) * | 1988-12-23 | 1991-09-24 | Asea Brown Boveri Ltd. | Multi-cylinder steam turbine set |
| CN103261716A (en) * | 2010-12-17 | 2013-08-21 | 谢夫勒科技股份两合公司 | Bearing arrangement for a turbocharger, and turbocharger |
Family Cites Families (3)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| JP2514546Y2 (en) * | 1987-12-24 | 1996-10-23 | 富士電機株式会社 | Turbine rotor jack-up device |
| JP4481523B2 (en) * | 2001-04-09 | 2010-06-16 | 株式会社東芝 | Combined cycle power generation facility and installation method thereof |
| JP5743914B2 (en) * | 2012-01-23 | 2015-07-01 | 株式会社東芝 | Steam turbine bearing support structure and steam turbine |
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2014
- 2014-06-04 CN CN201410244256.7A patent/CN104005797B/en active Active
Patent Citations (3)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| US4676667A (en) * | 1985-03-13 | 1987-06-30 | Nissan Motor Co., Ltd. | Variable preload shaft bearing for turbocharger |
| US5051061A (en) * | 1988-12-23 | 1991-09-24 | Asea Brown Boveri Ltd. | Multi-cylinder steam turbine set |
| CN103261716A (en) * | 2010-12-17 | 2013-08-21 | 谢夫勒科技股份两合公司 | Bearing arrangement for a turbocharger, and turbocharger |
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| CN104005797A (en) | 2014-08-27 |
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Address after: Dong Jiaduan 412002 in Hunan province Zhuzhou city Lusong District Patentee after: AECC HUNAN AVIATION POWERPLANT Research Institute Country or region after: China Address before: Dong Jiaduan 412002 in Hunan province Zhuzhou city Lusong District Patentee before: CHINA AVIATION POWER MACHINERY INSTITUTE Country or region before: China |