CN110966096A - A high temperature magnetic bearing cooling system for gas turbine - Google Patents
A high temperature magnetic bearing cooling system for gas turbine Download PDFInfo
- Publication number
- CN110966096A CN110966096A CN201911225830.3A CN201911225830A CN110966096A CN 110966096 A CN110966096 A CN 110966096A CN 201911225830 A CN201911225830 A CN 201911225830A CN 110966096 A CN110966096 A CN 110966096A
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- Prior art keywords
- magnetic suspension
- suspension bearing
- gas turbine
- radial magnetic
- rotating shaft
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- 238000001816 cooling Methods 0.000 title claims abstract description 20
- 239000000725 suspension Substances 0.000 claims abstract description 80
- 238000005057 refrigeration Methods 0.000 claims abstract description 31
- 230000017525 heat dissipation Effects 0.000 claims abstract description 6
- 238000001035 drying Methods 0.000 claims abstract description 5
- 238000009413 insulation Methods 0.000 claims description 12
- 238000010276 construction Methods 0.000 claims 1
- 239000011810 insulating material Substances 0.000 claims 1
- 230000000149 penetrating effect Effects 0.000 abstract 1
- 239000003507 refrigerant Substances 0.000 description 9
- 230000000694 effects Effects 0.000 description 8
- 238000005096 rolling process Methods 0.000 description 4
- 230000005284 excitation Effects 0.000 description 3
- 239000012530 fluid Substances 0.000 description 3
- 239000007788 liquid Substances 0.000 description 3
- 238000005461 lubrication Methods 0.000 description 3
- 230000035945 sensitivity Effects 0.000 description 3
- 238000002485 combustion reaction Methods 0.000 description 2
- 238000010586 diagram Methods 0.000 description 2
- 238000006073 displacement reaction Methods 0.000 description 2
- 239000012774 insulation material Substances 0.000 description 2
- 238000010521 absorption reaction Methods 0.000 description 1
- 230000002860 competitive effect Effects 0.000 description 1
- 238000001704 evaporation Methods 0.000 description 1
- 230000008020 evaporation Effects 0.000 description 1
- 239000000446 fuel Substances 0.000 description 1
- 238000002309 gasification Methods 0.000 description 1
Images
Classifications
-
- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F02—COMBUSTION ENGINES; HOT-GAS OR COMBUSTION-PRODUCT ENGINE PLANTS
- F02C—GAS-TURBINE PLANTS; AIR INTAKES FOR JET-PROPULSION PLANTS; CONTROLLING FUEL SUPPLY IN AIR-BREATHING JET-PROPULSION PLANTS
- F02C7/00—Features, components parts, details or accessories, not provided for in, or of interest apart form groups F02C1/00 - F02C6/00; Air intakes for jet-propulsion plants
- F02C7/06—Arrangements of bearings; Lubricating
-
- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F02—COMBUSTION ENGINES; HOT-GAS OR COMBUSTION-PRODUCT ENGINE PLANTS
- F02C—GAS-TURBINE PLANTS; AIR INTAKES FOR JET-PROPULSION PLANTS; CONTROLLING FUEL SUPPLY IN AIR-BREATHING JET-PROPULSION PLANTS
- F02C7/00—Features, components parts, details or accessories, not provided for in, or of interest apart form groups F02C1/00 - F02C6/00; Air intakes for jet-propulsion plants
- F02C7/12—Cooling of plants
- F02C7/16—Cooling of plants characterised by cooling medium
- F02C7/18—Cooling of plants characterised by cooling medium the medium being gaseous, e.g. air
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- Engineering & Computer Science (AREA)
- Chemical & Material Sciences (AREA)
- Combustion & Propulsion (AREA)
- Mechanical Engineering (AREA)
- General Engineering & Computer Science (AREA)
- Magnetic Bearings And Hydrostatic Bearings (AREA)
Abstract
The invention discloses a high-temperature magnetic suspension bearing cooling system for a gas turbine, which comprises a refrigerating system, a heat shield, a gas turbine rotating shaft, a first radial magnetic suspension bearing and an axial magnetic suspension bearing which are arranged at one end of the gas turbine rotating shaft, and a second radial magnetic suspension bearing which is arranged at the other end of the rotating shaft, wherein the second radial magnetic suspension bearing is close to the side of a gas turbine rotor; the first radial magnetic suspension bearing, the axial magnetic suspension bearing and the second radial magnetic suspension bearing are all fixed with the outer shell of the gas turbine; a heat shield is arranged outside the second radial magnetic suspension bearing and is fixed with the outer shell of the gas turbine; the refrigerating system comprises a compressor, a heat dissipation condenser, a capillary tube, a drying filter and a refrigerating pipeline which are connected in a circulating manner; the inside of the rotating shaft of the gas turbine is of a hollow structure; a hollow shaft is arranged in the rotating shaft; two ends of the hollow shaft are supported in the rotating shaft through bearings; the refrigeration pipeline penetrates through the hollow shaft and then is opposite to the second radial magnetic suspension bearing after penetrating out of the hollow shaft; the system has high cooling efficiency and reliable operation.
Description
Technical Field
The invention belongs to the technical field of gas turbines, and particularly relates to a high-temperature magnetic suspension bearing cooling system for a gas turbine.
Background
The high-temperature magnetic suspension bearing replaces the traditional rolling bearing, so that the bearing is close to the high-temperature end, the axial size of the engine is greatly shortened, the structure of the engine is more compact, in addition, the magnetic suspension bearing has the advantages of small friction and wear, no need of lubrication and the like, the running rotating speed of equipment can be effectively improved, the weight is reduced, the efficiency is improved, and the high-temperature magnetic suspension bearing becomes a hot point of competitive development of industrially developed countries;
however, at high temperatures, the sensitivity of the sensor changes significantly due to the large changes in parameters such as the resistance of the coil. But also can generate great temperature drift; the insulating layer of the excitation coil for the magnetic suspension bearing is easy to crack and fall off at high temperature, so that short-circuit accidents are caused. Therefore, the design of the high-temperature magnetic bearing refrigeration system 22 is crucial to magnetic bearings; the invention patent 201811094843.7 discloses a cooling mechanism for storing cryogenic fluid, which cools the magnetic bearing by releasing the cryogenic fluid, but such a solution requires constant filling of cryogenic fluid, thereby maintaining the normal use of the cooling mechanism, resulting in cumbersome use and additional labor cost. The utility model discloses a 201621153914.2 provides a magnetic suspension refrigerant compressor's direct current permanent magnet motor refrigerating system 22, this system refrigeration efficiency is higher, and the circulation evaporation through the refrigerant absorbs the heat, but as the gas turbine that power was equipped, its combustion position must produce high temperature, can't be similar to the processing of cooling down comprehensively in the cavity of motor.
Disclosure of Invention
The invention aims to provide a high-temperature magnetic suspension bearing cooling system for a gas turbine, which adopts a magnetic suspension bearing to replace a traditional rolling bearing, reduces friction and wear, shortens the axial size of an engine and ensures the reliable operation of equipment.
The technical solution for realizing the purpose of the invention is as follows:
a cooling system of a high-temperature magnetic suspension bearing for a gas turbine comprises a refrigerating system, a heat shield, a gas turbine rotating shaft, a first radial magnetic suspension bearing and an axial magnetic suspension bearing which are arranged at one end of the gas turbine rotating shaft, and a second radial magnetic suspension shaft which is arranged at the other end of the rotating shaft, wherein the second radial magnetic suspension bearing is close to the side of a gas turbine rotor; the first radial magnetic suspension bearing, the axial magnetic suspension bearing and the second radial magnetic suspension bearing are all fixed with the outer shell of the gas turbine; a heat insulation cover is arranged outside the second radial magnetic suspension bearing and is fixed with the outer shell of the gas turbine; the refrigerating system comprises a compressor, a heat dissipation condenser, a capillary tube, a drying filter and a refrigerating pipeline which are connected in a circulating manner; the rotating shaft is internally provided with a hollow structure; a hollow shaft is arranged in the rotating shaft; two ends of the hollow shaft are supported in the rotating shaft through bearings; the refrigeration pipeline penetrates through the hollow shaft and then penetrates out of the hollow shaft to be opposite to the second radial magnetic suspension bearing.
Compared with the prior art, the invention has the following remarkable advantages:
(1) the magnetic suspension bearing replaces the traditional rolling bearing, so that the bearing is close to the high-temperature end, the axial size of the engine is greatly shortened, the structure of the engine is more compact, the running rotating speed of equipment can be effectively improved, the weight is reduced, and the efficiency is improved.
(2) According to the invention, through the refrigeration system, the phenomenon that the sensitivity of the sensor can be greatly changed and great temperature drift can be generated due to great change of parameters such as resistance of the coil at high temperature is avoided; meanwhile, the phenomenon that an insulating layer of the excitation coil for the magnetic suspension bearing is easy to crack and fall off at high temperature to cause short-circuit accidents is avoided, and the reliability of the system is improved.
(3) The refrigeration pipeline is arranged in a rotating shaft cavity where the second radial magnetic suspension bearing is located, meanwhile, a heat insulation cover made of heat insulation materials is arranged to wrap the second radial magnetic suspension bearing to form a heat insulation space, the refrigeration pipeline conveys cold energy to the second radial magnetic suspension bearing through heat conduction, the temperature of the second radial magnetic suspension bearing is reduced, the heat insulation cover limits the loss of the cold energy, and the refrigeration effect is improved.
(4) And a plurality of air guide holes are formed in the rotating shaft section corresponding to the second radial magnetic suspension bearing, and cold air in the hollow rotating shaft cavity can enter the heat insulation space where the second radial magnetic suspension bearing is positioned through the air guide holes, so that the cooling effect of the second radial magnetic suspension bearing is further improved.
Drawings
Fig. 1 is a general structural schematic diagram of the system of the invention arranged on a gas engine rotating shaft.
Fig. 2 is a schematic diagram of the overall configuration of the refrigeration system.
FIG. 3 is a partially enlarged view of the shaft with air holes.
Fig. 4 is a schematic view of the connection of the refrigeration circuit to the hollow shaft.
Detailed Description
The invention is further described with reference to the following figures and embodiments.
With reference to fig. 1, the high-temperature magnetic suspension bearing refrigerant refrigeration system for the gas turbine of the present invention includes a refrigeration system 22, a heat shield 12, a gas engine rotating shaft 10, a first radial magnetic suspension bearing 9 and an axial magnetic suspension bearing 7 disposed at one end of the gas engine rotating shaft 10, and a second radial magnetic suspension shaft 21 disposed at the other end of the rotating shaft 10, and the second radial magnetic suspension bearing 21 is close to the gas turbine rotor 1 side (high-temperature side); the first radial magnetic suspension bearing 9, the axial magnetic suspension bearing 7 and the second radial magnetic suspension bearing 21 are all fixed with the outer shell of the gas engine; the axial displacement and the radial displacement of the rotating shaft 10 are respectively controlled through an axial magnetic suspension bearing and two radial magnetic suspension bearings, so that the fixing of the rotating shaft of the gas turbine is ensured. Compared with a common bearing, the magnetic suspension bearing has the advantages of small friction and wear, no need of lubrication, low vibration, low noise, low power consumption and the like. The outside of second radial magnetic suspension bearing 21 is equipped with separates heat exchanger 12, it is fixed with the gas turbine shell body to separate heat exchanger 12, through separating heat exchanger 12, seals the second radial magnetic suspension bearing 21 of countershaft 10 afterbody and handles, avoids high temperature gas and second radial magnetic suspension bearing 21's direct contact, can effectively reduce the temperature of second radial magnetic suspension bearing 21, reduces the influence of afterbody high temperature gas to second radial magnetic suspension bearing 21.
The refrigerating system 22 comprises a compressor 16, a heat dissipation condenser 18, a capillary tube 17, a drying filter 15 and a refrigerating pipeline 14 which are connected in a circulating manner; the principle of the refrigeration system 22 is that the compressor 16 compresses low-pressure vapor of the refrigerant in the refrigeration system 22 into high-pressure vapor, and at this time, the entire refrigerant vapor is in a high-temperature state, and then is discharged into the heat-dissipating condenser 18, and the compressor 16 liquefies and condenses the high-pressure refrigerant vapor into high-pressure liquid. The high-pressure liquid passes through the drying filter 15 and the intercepting capillary tube 17 and then is sprayed into the refrigerating pipeline 11 (the refrigerating pipeline 11 is used as a heat absorption evaporator), the high-pressure liquid is gasified under corresponding low pressure, a large amount of heat can be absorbed by the gasification, meanwhile, the low-pressure refrigerant circulates to the compressor 16, and the circulation work is carried out, so that the refrigerating effect is realized. The rotating shaft 10 is internally of a hollow structure; a hollow shaft 13 is arranged in the rotating shaft 10; the two ends of the hollow shaft 13 are supported in the rotating shaft 10 through a pair of bearings 20; the refrigeration pipeline 11 penetrates into the hollow shaft 13 and penetrates out of the hollow shaft 13, and then is opposite to the second radial magnetic suspension bearing 21. Referring to fig. 4, in order to make the second radial magnetic suspension bearing 21 at the tail of the rotating shaft 10 have a better heat dissipation effect, the tail of the refrigeration pipeline 11 is bent and rotated, so that the refrigeration pipeline 11 has a denser structure at the tail of the rotating shaft, and the refrigeration effect of the refrigerant refrigeration system is improved. When the gas turbine is operated to rotate at a high speed, the hollow shaft 13 prevents the refrigerating pipeline 11 from rotating along with the rotating shaft 10, and the operation of the refrigerating pipeline 11 is not affected.
Furthermore, the other end of the rotating shaft 10 corresponds to the position of the second radial magnetic suspension bearing 21, and a plurality of air guide holes 19 are radially arranged, the air guide holes 19 can enable cold air of the refrigeration pipeline 11 to directly enter a closed space formed by the second radial magnetic suspension bearing 21 and the heat insulation cover 12, the refrigeration effect can be further improved by increasing the air guide holes 19 under the condition of meeting the strength requirement of the rotating shaft 10 than by not increasing the air guide holes 19, the cooling efficiency is higher than that of a cooling mode of conducting the cold air to the second radial magnetic suspension bearing 21 through the inner wall of the rotating shaft 10, and the number and the arrangement mode of the air guide holes 19 can be adjusted according to the strength requirement of the rotating shaft 10.
The invention discloses a gas turbine, which belongs to the prior art, is not described in detail, and only accepts the working principle: the air is continuously sucked from the atmosphere on the rotating shaft 10 through the primary axial flow compressor rotor 6 and the secondary axial flow compressor rotor 5 and is compressed, the compressed air enters the combustion chamber to be mixed with the injected fuel and then is combusted to form high-temperature gas, the high-temperature gas immediately flows into the gas turbine to expand and do work, the gas turbine rotor 1 is pushed to drive the compressor rotor and the centrifugal impeller 3 to rotate together, and finally the high-temperature gas is discharged through an exhaust port on the gas turbine shell. The magnetic suspension bearing replaces the traditional rolling bearing, so that the bearing is close to the high-temperature end, the axial size of the engine is greatly shortened, the structure of the engine is more compact, in addition, the magnetic suspension bearing has the advantages of small friction and wear, no need of lubrication and the like, the running rotating speed of equipment can be effectively improved, the weight is reduced, and the efficiency is improved. The refrigeration pipeline 11 is arranged in a cavity of the rotating shaft 10 where the second radial magnetic suspension bearing 21 is located, meanwhile, a heat insulation cover 12 made of heat insulation materials is arranged to wrap the second radial magnetic suspension bearing 21 to form a heat insulation space, the refrigeration pipeline 11 transmits cold energy to the second radial magnetic suspension bearing 21 through heat conduction, the temperature of the second radial magnetic suspension bearing 21 is reduced, and the heat insulation cover 12 limits the loss of the cold energy; under the condition that the strength of the rotating shaft 10 allows, a plurality of air guide holes 19 are distributed in the section of the rotating shaft 10 corresponding to the second radial magnetic suspension bearing 21, and cold air in the cavity of the hollow rotating shaft 10 can enter the heat insulation space where the second radial magnetic suspension bearing 21 is located through the air guide holes 19, so that the cooling effect of the second radial magnetic suspension bearing 21 is improved. The refrigeration pipeline 11 of the refrigeration system is placed in the hollow rotating shaft 13, and other parts of the refrigeration system are placed outside the hollow rotating shaft 13. Not only can increase the heat dissipation efficiency, but also can reduce the volume of the whole device. Aiming at the high-temperature characteristic of the gas turbine, the refrigerant refrigerating system 22 designed by the invention has the advantages of high cooling efficiency and good effect. By the refrigerating system 22, the problem that the sensitivity of a sensor used by the magnetic suspension bearing can be greatly changed and great temperature drift can be generated due to large parameter change of the coil such as resistance and the like at high temperature is avoided; meanwhile, the phenomenon that the insulating layer of the excitation coil for the magnetic suspension bearing is easy to crack and fall off at high temperature to cause short-circuit accidents is avoided.
Claims (5)
1. The cooling system for the high-temperature magnetic suspension bearing for the gas turbine is characterized by comprising a refrigerating system (22), a heat shield (12), a gas turbine rotating shaft (10), a first radial magnetic suspension bearing (9) and an axial magnetic suspension bearing (7) which are arranged at one end of the gas turbine rotating shaft (10), and a second radial magnetic suspension shaft (21) which is arranged at the other end of the rotating shaft (10), wherein the second radial magnetic suspension bearing (21) is close to the side of a gas turbine rotor (1); the first radial magnetic suspension bearing (9), the axial magnetic suspension bearing (7) and the second radial magnetic suspension bearing (21) are all fixed with the outer shell of the gas turbine; a heat insulation cover (12) is arranged outside the second radial magnetic suspension bearing (21), and the heat insulation cover (12) is fixed with the outer shell of the gas turbine; the refrigeration system (22) comprises a compressor (16), a heat dissipation condenser (18), a capillary tube (17), a drying filter (15) and a refrigeration pipeline (14) which are connected in a circulating manner; the rotating shaft (10) is internally of a hollow structure; a hollow shaft (13) is arranged in the rotating shaft (10); two ends of the hollow shaft (13) are supported in the rotating shaft (10) through bearings (20); the refrigeration pipeline (11) penetrates through the hollow shaft (13) and penetrates out of the hollow shaft (13) to be opposite to the second radial magnetic suspension bearing (21).
2. Cooling system according to claim 1, characterized in that the tail of the refrigeration circuit (11) is of a dense arrangement.
3. Cooling system according to claim 1, characterized in that the tail of the refrigeration line (11) is of a curved rotary construction.
4. Cooling system according to claim 1, characterized in that the other end of the shaft (10) is provided with a plurality of air-guiding holes (19) in correspondence of the second radial magnetic bearing (21).
5. Cooling system according to claim 1, characterized in that the heat shield (12) is made of a heat insulating material.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201911225830.3A CN110966096B (en) | 2019-12-04 | 2019-12-04 | High-temperature magnetic suspension bearing cooling system for gas turbine |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201911225830.3A CN110966096B (en) | 2019-12-04 | 2019-12-04 | High-temperature magnetic suspension bearing cooling system for gas turbine |
Publications (2)
| Publication Number | Publication Date |
|---|---|
| CN110966096A true CN110966096A (en) | 2020-04-07 |
| CN110966096B CN110966096B (en) | 2024-09-03 |
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| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN201911225830.3A Active CN110966096B (en) | 2019-12-04 | 2019-12-04 | High-temperature magnetic suspension bearing cooling system for gas turbine |
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| Country | Link |
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| CN (1) | CN110966096B (en) |
Cited By (1)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN114483303A (en) * | 2021-12-30 | 2022-05-13 | 中车永济电机有限公司 | High-speed permanent magnet motor applied to micro gas turbine |
Citations (6)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| RU2323344C1 (en) * | 2006-07-26 | 2008-04-27 | Николай Борисович Болотин | Turbogenerator |
| CN104358597A (en) * | 2014-11-13 | 2015-02-18 | 叶金辉 | Magnetic suspension power generation device for absorbing low-grade residual heat |
| JP2018068021A (en) * | 2016-10-19 | 2018-04-26 | パナソニックＩｐマネジメント株式会社 | Turbomachine and refrigeration cycle device using the same |
| CN108131868A (en) * | 2017-12-25 | 2018-06-08 | 湖南同能机电科技有限公司 | A kind of heat power water-cooling device and heat power water-cooling device control method |
| CN109026998A (en) * | 2018-09-19 | 2018-12-18 | 中国科学院理化技术研究所 | High-temperature superconducting magnetic suspension bearing system |
| CN211573643U (en) * | 2019-12-04 | 2020-09-25 | 扬州大学 | High-temperature magnetic suspension bearing cooling system for gas turbine |
-
2019
- 2019-12-04 CN CN201911225830.3A patent/CN110966096B/en active Active
Patent Citations (6)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| RU2323344C1 (en) * | 2006-07-26 | 2008-04-27 | Николай Борисович Болотин | Turbogenerator |
| CN104358597A (en) * | 2014-11-13 | 2015-02-18 | 叶金辉 | Magnetic suspension power generation device for absorbing low-grade residual heat |
| JP2018068021A (en) * | 2016-10-19 | 2018-04-26 | パナソニックＩｐマネジメント株式会社 | Turbomachine and refrigeration cycle device using the same |
| CN108131868A (en) * | 2017-12-25 | 2018-06-08 | 湖南同能机电科技有限公司 | A kind of heat power water-cooling device and heat power water-cooling device control method |
| CN109026998A (en) * | 2018-09-19 | 2018-12-18 | 中国科学院理化技术研究所 | High-temperature superconducting magnetic suspension bearing system |
| CN211573643U (en) * | 2019-12-04 | 2020-09-25 | 扬州大学 | High-temperature magnetic suspension bearing cooling system for gas turbine |
Cited By (1)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN114483303A (en) * | 2021-12-30 | 2022-05-13 | 中车永济电机有限公司 | High-speed permanent magnet motor applied to micro gas turbine |
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| Publication number | Publication date |
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| CN110966096B (en) | 2024-09-03 |
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