CN104005797A - Gas turbine rotor supporting mechanism and gas turbine with same - Google Patents
Gas turbine rotor supporting mechanism and gas turbine with same Download PDFInfo
- Publication number
- CN104005797A CN104005797A CN201410244256.7A CN201410244256A CN104005797A CN 104005797 A CN104005797 A CN 104005797A CN 201410244256 A CN201410244256 A CN 201410244256A CN 104005797 A CN104005797 A CN 104005797A
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- gas turbine
- turbine rotor
- ball bearing
- ring
- outer shroud
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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
- 230000003139 buffering effect Effects 0.000 abstract 1
- 230000008901 benefit Effects 0.000 description 2
- 238000010586 diagram Methods 0.000 description 2
- 230000000694 effects Effects 0.000 description 2
- 238000009434 installation Methods 0.000 description 2
- 230000009286 beneficial effect Effects 0.000 description 1
- 230000005540 biological transmission Effects 0.000 description 1
- 230000008859 change Effects 0.000 description 1
- 230000006872 improvement Effects 0.000 description 1
- 238000012986 modification Methods 0.000 description 1
- 230000004048 modification Effects 0.000 description 1
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- Support Of The Bearing (AREA)
Abstract
The invention discloses a gas turbine rotor supporting mechanism and a gas turbine with the same. The gas turbine rotor supporting mechanism comprises ball bearings arranged on two sides of a gas turbine rotor wheel disc to be used for supporting a gas turbine rotor, the ball bearings comprise a first ball bearing arranged on a rotor shaft on a first side of the gas turbine rotor wheel disc and a second ball bearing arranged on a rotor shaft on a second side of the rotor wheel disc, the first ball bearing comprises a first outer ring, the first outer ring is provided with an elastic mechanism used for exerting axial force on the gas turbine rotor and buffering the gas turbine rotor axial force, and the second ball bearing is arranged into a thrust bearing for bearing the axial force of the gas turbine rotor. The gas turbine rotor supporting mechanism can improve axial bearing capability of the gas turbine, the problem of light load slippage is solved, and structural stability of the whole supporting mechanism in a high-speed running state 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 that comprises above-mentioned supporting mechanism.
Background technique
Gas turbine is rotating machinery at a high speed, and the working speed of microminiature gas turbine more than 40000r/min, has striden across even three rank critical speed of rotation of rotor second order conventionally.Sharply changing of rotating speed brought the pressure in gas compressor and cross section, turbine front and back, surge or sharp the subtracting of temperature, causes that the quick variation of axial force of rotor is even reverse, can cause gas turbine bearing light load slipping or bearing capacity inadequate.
For the shafting stability of gas turbine, the normal mode support rotor that adopts 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 assembling with stick roller bearing, because the axial force of rotor can only pass by a ball bearing, so the axial force that whole rotor bears 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, causes that gas turbine axial carrying capacity is low, the technical problem of easy light load slipping etc. to solve supporting way that existing ball bearing coordinates with stick roller bearing.
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 to be located at the first ball bearing on gas turbine rotor wheel disc the first side rotor shaft and to be located at the second ball bearing on rotor disk the second side rotor shaft, the 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; The second ball bearing is set to bear the thrust bearing of gas turbine rotor axial force.
Further, elastic mechanism comprises the elasticity preload piece that is fixed on along axial arranged and one end of gas turbine rotor on the first outer shroud and in order to the fixing free-ended fixed charge method end plate of elasticity preload piece; The first end of elasticity preload piece is fixed on the axle side end face of the first outer shroud, the 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 gas turbine rotor is applied to axial force 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 pieces are circumferentially equidistantly arranged along gas turbine rotor; Multiple elasticity preload pieces are fixed on same fixed charge method end plate, or each elasticity preload piece is connected with respectively a fixed charge method end plate.
Further, ball bearing all adopts ring three-point contact ball bearing in half.
Further, the second ball bearing comprises the second outer shroud, and the second outer shroud is arranged with to prevent that the second outer shroud is along the expansion controlling ring-shaped insert circumferentially rolling outward; The second outer shroud is connected by interference fit with expansion controlling ring-shaped insert.
Further, the flexible strutting piece that expansion controlling ring-shaped insert peripheral hardware has to reduce support stiffness and adjusts 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 cover plate is sealed on taper back-up ring in gas turbine stator, the conical surface direction of taper cover plate and the conical surface of taper back-up ring arrange opposite direction, between taper cover plate and taper back-up ring, by cone match, the second outer shroud are carried out to self-alignment.
Further, on the axle side end face of the second outer shroud, expansion controlling ring-shaped insert and flexible strutting piece three's composite structure, be fitted with the adjustment packing ring in order to buffer shaft side external force; Adjust the gap of leaving to compensate the second outer shroud thermal expansion between 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, also provide a kind of gas turbine, comprised gas turbine rotor and gas turbine stator, between gas turbine rotor and gas turbine stator, supported by above-mentioned gas turbine rotor supporting mechanism.
The present invention has following beneficial effect:
Gas turbine rotor supporting mechanism of the present invention, lays ball bearing in order to support gas turbine rotor by the both sides at gas turbine rotor wheel disc; By elastic mechanism being set on the first ball bearing in order to apply axial force to gas turbine rotor and to cushion gas turbine rotor axial force; The 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.Can share with two ball bearings the axial force of whole rotor, 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.
Brief description of the drawings
The accompanying drawing that forms the application's a part is used to provide a further understanding of the present invention, and schematic description and description of the present invention is used 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 local structure for amplifying schematic diagram 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, adjust packing ring.
Embodiment
Below in conjunction with accompanying drawing, embodiments of the invention are elaborated, 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 local structure for amplifying schematic diagram 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 to be located at the first ball bearing 301 on gas turbine rotor wheel disc 1 first side rotor shaft and to be located at the second ball bearing 302 on rotor disk the second side rotor shaft, the first ball bearing 301 comprises that the first outer shroud 3011, the first outer shrouds 3011 are 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 forces; The second ball bearing 302 is set to bear the thrust bearing of gas turbine rotor 2 axial forces.Gas turbine rotor supporting mechanism of the present invention, lays ball bearing 3 in order to support gas turbine rotor 2 by the both sides at gas turbine rotor wheel disc 1; By elastic mechanism 4 being set on the first ball bearing 301 in order to apply axial force to gas turbine rotor 2 and to cushion gas turbine rotor 2 axial forces; The second ball bearing 302 is set to thrust bearing in order to bear gas turbine rotor 2 axial forces; 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.Can share with two ball bearings the axial force of whole rotor, expand the excursion of the axial force that bearing can bear, extend bearing life.Preferably, ball bearing leaves gap while installation, can compensate the thermal distortion of bearing, prevents that outer shroud from rotating by expansion controlling ring-shaped insert simultaneously.
In the present embodiment, elastic mechanism 4 comprises the elasticity preload piece 401 that is fixed on along axial arranged and one end of gas turbine rotor 2 on the first outer shroud 3011 and in order to the fixing free-ended fixed charge method end plate 402 of elasticity preload piece 401; The first end of elasticity preload piece 401 is fixed on the axle side end face of the first outer shroud 3011, the 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 gas turbine rotor 2 is applied to 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 pieces 401 are circumferentially equidistantly arranged along gas turbine rotor 2; Multiple elasticity preload pieces 401 are fixed on same fixed charge method end plate 402, or each elasticity preload piece 401 is connected with respectively a fixed charge method end plate 402.
In the present embodiment, ball bearing 3 all adopts ring three-point contact ball bearing in half.Being convenient to bearing installs.Bearing adopts 3 contacts, and the stability of structure is better, load, power transmission better effects if.
In the present embodiment, the second ball bearing 302 comprises the outer expansion controlling ring-shaped inserts 6 that are arranged with to prevent the second outer shroud 3021 circumferential rollings in edge of the second outer shroud 3021, the second outer shrouds 3021; The second outer shroud 3021 is connected by interference fit with expansion controlling ring-shaped insert 6.
In the present embodiment, the flexible strutting piece 7 that expansion controlling ring-shaped insert 6 peripheral hardwares have to reduce support stiffness and adjust 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 cover plate 8 is sealed on taper back-up ring 9 in gas turbine stator 5, the conical surface direction of taper cover plate 8 and the conical surface of taper back-up ring 9 arrange opposite direction, between taper cover plate 8 and taper back-up ring 9, by cone match, the second outer shroud 3021 are carried out to self-alignment.
In the present embodiment, on the axle side end face of the second outer shroud 3021, expansion controlling ring-shaped insert 6 and flexible strutting piece 7 threes' composite structure, be fitted with the adjustment packing ring 10 in order to buffer shaft side external force; Adjust the gap of leaving to compensate the second outer shroud 3021 thermal expansions between 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, between gas turbine rotor 2 and gas turbine stator 5, supports by above-mentioned gas turbine rotor supporting mechanism.
When enforcement, gas turbine rotor 2 is arranged in two two half and encircles on three-point contact ball bearing (ball bearing 3), one of them two half interior three-point contact ball bearing that encircle compresses two partly outer shrouds of interior ring three-point contact ball bearings by preloading spring (elasticity preload piece 401), gas turbine rotor 2 is applied to axial force, the 1/4-3/4 of the size of axial force axial force in the time equaling gas turbine nominal operation state.Preferably, the size of axial force in the time equaling gas turbine nominal operation state axial force 1/2.Another half interior ring, three point contact ball axles are thrust bearings, are somebody's turn to do outer shroud and expansion controlling ring-shaped insert 6 interference fit of in half, encircling three point contact ball axles, prevent that outer shroud from circumferentially rolling.Expansion controlling ring-shaped insert 6 is outer can install elastic ring or spring sheet (flexible strutting piece 7), reduces support stiffness, adjusts the critical speed of rotation that gas turbine rotor 2 is pacified, and makes the working speed of gas turbine avoid critical speed of rotation.
The axial force that gas turbine work produces is offset a part by preloading spring, and another part is delivered on casing by thrust bearing, and two bearings have been shared the axial force of rotor, have improved 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 in 0.1 by adjusting packing ring 10.When gas turbine running, temperature rise, by the thermal expansion of this backlash compensation outer race.Taper cover plate 8 cooperatively interacts with taper back-up ring 9, ensures the fixing self-alignment of outer shroud.
Gas turbine uses two ball bearings 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 applying can change (can from the axial left side also can from axial the right), and the bearing of effect can be any one simultaneously.
When the size of initial tension of spring approximates gas turbine nominal operation state 1/2 of axial force; Thrust bearing outer shroud and fixing preset clearance are controlled in 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.Can share with two ball bearings the axial force of whole rotor, expand the excursion of the axial force that bearing can bear, extend bearing life; Positioning bearing leaves gap while installation, can compensate the thermal distortion of bearing, prevents that outer shroud from rotating by expansion controlling ring-shaped insert simultaneously.Use certain type gas turbine of this gas turbine rotor supporting mechanism 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 of doing, be equal to replacement, improvement etc., within all should being included in protection scope of the present invention.
Claims (10)
1. a gas turbine rotor supporting mechanism, comprises and is located at the ball bearing (3) that gas turbine rotor wheel disc (1) both sides are used for supporting gas turbine rotor (2),
Described ball bearing (3) comprises to be located at the first ball bearing (301) on described gas turbine rotor wheel disc (1) first side rotor shaft and to be located at the second ball bearing (302) on rotor disk the second side rotor shaft
It is characterized in that,
Described the first ball bearing (301) comprises the first outer shroud (3011),
Described the 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 the second ball bearing (302) is set to bear the thrust bearing of described gas turbine rotor (2) axial force.
2. gas turbine rotor supporting mechanism according to claim 1, is characterized in that,
Described elastic mechanism (4) comprises the elasticity preload piece (401) that is fixed on along axial arranged and one end of described gas turbine rotor (2) on described the first outer shroud (3011) and in order to the fixing free-ended fixed charge method end plate of described elasticity preload piece (401) (402);
The first end of described elasticity preload piece (401) is fixed on the axle side end face of described the first outer shroud (3011),
It is upper that the second end of described elasticity preload piece (401) is fixed in described fixed charge method end plate (402),
It is upper that described fixed charge method end plate (402) is fixed in gas turbine stator (5),
Compress described the first outer shroud (3011) by described elasticity preload piece (401) described gas turbine rotor (2) is applied to axial force;
Described elasticity preload piece (401) is preloading spring or pretension shell fragment.
3. gas turbine rotor supporting mechanism according to claim 2, is characterized in that,
Described elasticity preload piece (401) is set to multiple,
Multiple described elasticity preload pieces (401) are circumferentially equidistantly arranged along described gas turbine rotor (2);
It is upper that multiple described elasticity preload pieces (401) are fixed on described in same fixed charge method end plate (402),
Or described in each, elasticity preload piece (401) is connected with respectively a described fixed charge method end plate (402).
4. gas turbine rotor supporting mechanism according to claim 2, is characterized in that, described ball bearing (3) all adopts ring three-point contact ball bearing in half.
5. gas turbine rotor supporting mechanism according to claim 2, is characterized in that,
Described the second ball bearing (302) comprises the second outer shroud (3021),
Described the second outer shroud (3021) is outer is arranged with to prevent that described the second outer shroud (3021) is along the expansion controlling ring-shaped insert (6) circumferentially rolling;
Described the second outer shroud (3021) is connected by interference fit with described expansion controlling ring-shaped insert (6).
6. gas turbine rotor supporting mechanism according to claim 5, is characterized in that,
The flexible strutting piece (7) that described expansion controlling ring-shaped insert (6) peripheral hardware has to reduce support stiffness and adjusts 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 at least one in elastic ring, spring sheet, elastomer block, elastic strip.
7. gas turbine rotor supporting mechanism according to claim 6, is characterized in that,
The axle side upper cover that the described gas turbine stator (5) of described the second ball bearing (302) is housed has taper cover plate (8),
Described taper cover plate (8) is sealed on taper back-up ring (9) in described gas turbine stator (5),
The conical surface of the conical surface direction of described taper cover plate (8) and described taper back-up ring (9) arranges opposite direction,
Between described taper cover plate (8) and described taper back-up ring (9), by cone match, described the second outer shroud (3021) is carried out to self-alignment.
8. gas turbine rotor supporting mechanism according to claim 7, is characterized in that,
On the axle side end face of described the second outer shroud (3021), described expansion controlling ring-shaped insert (6) and described flexible strutting piece (7) three's composite structure, be fitted with the adjustment packing ring (10) in order to buffer shaft side external force;
Between described adjustment packing ring (10) and described taper back-up ring (9), leave to compensate the gap of described the second outer shroud (3021) thermal expansion.
9. gas turbine rotor supporting mechanism according to claim 8, is characterized in that, the described gap≤0.1mm between described taper back-up ring (9) and described adjustment packing ring (10).
10. a gas turbine, comprise gas turbine rotor (2) and gas turbine stator (5), it is characterized in that, between gas turbine rotor (2) and gas turbine stator (5), support by gas turbine rotor supporting mechanism as claimed in any one of claims 1-9 wherein.
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 |
Applications Claiming Priority (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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| Publication Number | Publication Date |
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| CN104005797A true CN104005797A (en) | 2014-08-27 |
| CN104005797B 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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Cited By (4)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN105822366A (en) * | 2016-04-20 | 2016-08-03 | 中国科学院工程热物理研究所 | Low-pressure rotor supporting structure of engine with fusing 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 |
| CN111188686A (en) * | 2020-01-19 | 2020-05-22 | 中国科学院工程热物理研究所 | Double-ball bearing supporting structure for preventing light load from slipping |
| CN115949670A (en) * | 2023-03-09 | 2023-04-11 | 中国航发四川燃气涡轮研究院 | Elastic structure for axial compression of bearing |
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Cited By (6)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN105822366A (en) * | 2016-04-20 | 2016-08-03 | 中国科学院工程热物理研究所 | Low-pressure rotor supporting structure of engine with fusing 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 |
| CN111188686A (en) * | 2020-01-19 | 2020-05-22 | 中国科学院工程热物理研究所 | Double-ball bearing supporting structure for preventing light load from slipping |
| 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 |
| CN115949670A (en) * | 2023-03-09 | 2023-04-11 | 中国航发四川燃气涡轮研究院 | Elastic structure for axial compression of bearing |
| 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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| Publication number | Publication date |
|---|---|
| CN104005797B (en) | 2015-12-30 |
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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 |
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