CN215718976U - Gas turbine hollow rotor structure supported by magnetic bearing - Google Patents
Gas turbine hollow rotor structure supported by magnetic bearing Download PDFInfo
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- CN215718976U CN215718976U CN202121081931.0U CN202121081931U CN215718976U CN 215718976 U CN215718976 U CN 215718976U CN 202121081931 U CN202121081931 U CN 202121081931U CN 215718976 U CN215718976 U CN 215718976U
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- turbine
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- magnetic bearing
- rotor
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- 238000010168 coupling process Methods 0.000 claims description 11
- 238000005859 coupling reaction Methods 0.000 claims description 11
- 238000005096 rolling process Methods 0.000 claims description 11
- 238000001816 cooling Methods 0.000 claims description 7
- 239000000725 suspension Substances 0.000 abstract description 9
- 238000005452 bending Methods 0.000 abstract description 8
- 238000002485 combustion reaction Methods 0.000 abstract description 7
- 238000005299 abrasion Methods 0.000 abstract description 3
- 239000010687 lubricating oil Substances 0.000 abstract description 3
- 230000008878 coupling Effects 0.000 description 7
- 230000009471 action Effects 0.000 description 6
- 238000000034 method Methods 0.000 description 6
- 230000008901 benefit Effects 0.000 description 5
- 239000002184 metal Substances 0.000 description 5
- 239000011248 coating agent Substances 0.000 description 3
- 238000000576 coating method Methods 0.000 description 3
- 230000008569 process Effects 0.000 description 3
- 239000007787 solid Substances 0.000 description 3
- 239000000919 ceramic Substances 0.000 description 2
- 239000000306 component Substances 0.000 description 2
- 230000007797 corrosion Effects 0.000 description 2
- 238000005260 corrosion Methods 0.000 description 2
- 239000000463 material Substances 0.000 description 2
- 230000004075 alteration Effects 0.000 description 1
- 229910010293 ceramic material Inorganic materials 0.000 description 1
- 239000008358 core component Substances 0.000 description 1
- 230000007547 defect Effects 0.000 description 1
- 238000001514 detection method Methods 0.000 description 1
- 238000010586 diagram Methods 0.000 description 1
- 230000000694 effects Effects 0.000 description 1
- 239000012530 fluid Substances 0.000 description 1
- 238000012986 modification Methods 0.000 description 1
- 230000004048 modification Effects 0.000 description 1
- 230000002035 prolonged effect Effects 0.000 description 1
- 238000006467 substitution reaction Methods 0.000 description 1
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- Turbine Rotor Nozzle Sealing (AREA)
- Structures Of Non-Positive Displacement Pumps (AREA)
- Rolling Contact Bearings (AREA)
Abstract
The utility model discloses a gas turbine hollow rotor structure supported by a magnetic bearing. The magnetic suspension type turbine blade assembly mainly comprises a magnetic suspension bearing (comprising a ball protection bearing), a hollow main shaft, a turbine blade assembly and a compressor blade assembly. The bearings are respectively arranged on the outer side of the gas compressor and the inner side of the turbine, the arrangement mode reduces the bearing span and improves the integral rigidity of the rotor system. The basic mechanical characteristics in the structural design are as follows: the rigid rotor is adopted, and the bending critical rotating speed is out of the working rotating speed range. Compared with a lubricating oil bearing, the magnetic bearing support can obviously reduce the number of matched equipment, reduce the occupied space, and most importantly, can reduce the abrasion of the shaft diameter and prolong the fatigue life. The main shaft adopts a hollow structure, so that the weight of the rotor is greatly reduced, and the output power of the combustion engine can be increased under the same conditions, namely the efficiency of the combustion engine is improved.
Description
Technical Field
The utility model relates to the technical field of fluid rotating machinery such as a gas turbine and the like, in particular to a gas turbine hollow rotor structure supported by a magnetic bearing.
Background
As a core component of a gas turbine, the structural and bearing design of the rotor of the combustion engine is particularly important. In general, a rotor of a rotating machine such as a gas turbine or a compressor is often supported by a sliding bearing, and this structure requires a large lubricating oil system, which results in a large system occupation space. In addition, the shaft bushing is easy to damage and wear when the combustion engine is started and stopped, and finally, the vibration stability of the rotor is reduced and the service life of the rotor is prolonged. When the unit operates, the supporting rigidity of the sliding bearing can not be adjusted manually, so that the critical rotating speed of the rotor is relatively single.
The conventional civil gas turbine rotor is of a solid shaft structure, the weight of the rotor is very high, the inertia of the gyroscope is greatly increased, in addition, under the condition that the power generated by the turbine is not changed, the power consumed by the rotor is very large, the rotational inertia of the solid rotor is also very large, and the bending critical rotating speed of the rotor is reduced.
SUMMERY OF THE UTILITY MODEL
Aiming at the defects of the prior art, the utility model provides a gas turbine hollow rotor structure supported by a magnetic bearing, so as to reduce the occupied space of the bearing, expand the frequency tuning margin of a rotor, improve the critical rotating speed of the rotor and finally prolong the service life of the rotor.
In order to achieve the purpose, the utility model is realized by the following technical scheme: a gas turbine hollow rotor structure supported by a magnetic bearing comprises a half coupling, wherein a main shaft is inserted into the right side of the half coupling, a front magnetic bearing is installed on the ring surface of the left side of the main shaft, a compressor shaft is installed outside the main shaft and on the right side of the front magnetic bearing, a plurality of compressor blades are installed on the outer ring surface of the compressor shaft, a turbine shaft is installed on the right side of the main shaft, a plurality of special stud bolts with the same structure are installed between the turbine shaft and the main shaft, a rear magnetic bearing is installed outside the turbine shaft, and a turbine assembly is installed on the right end surface of the turbine shaft.
Preferably, the front magnetic bearing comprises a rolling protection bearing, the rolling protection bearing is connected with the main shaft, a thrust bearing and a radial bearing are respectively installed on the left side and the right side in the rolling protection bearing, and the thrust bearing and the radial bearing are respectively connected with the main shaft.
Preferably, the rear magnetic bearing is provided with an air cooling hole.
Preferably, the turbine assembly comprises a first-stage turbine disc, the first-stage turbine disc is connected with the turbine shaft, first-stage turbine blades are installed on the outer annular surface of the first-stage turbine disc, a second-stage turbine disc is installed on the right side of the first-stage turbine disc, second-stage turbine blades are installed on the outer side of the second-stage turbine disc, a plurality of balancing weights A with the same structure are inserted in the first-stage turbine disc and the second-stage turbine disc, the first-stage turbine disc is connected with the turbine shaft through pull rod bolt groups A which are uniformly distributed on the circumference, and the first-stage turbine disc is connected with the second-stage turbine disc through pull rod bolt groups B which are uniformly distributed on the circumference.
Preferably, a plurality of balancing weights B with the same structure are embedded on the end faces of the left side and the right side of the compressor shaft, the main shaft is of a hollow structure, and balancing weight screw holes which are uniformly distributed in the radial direction are spirally arranged on the outer annular face of the compressor shaft and positioned on the left side and the right side.
Preferably, the balancing weight A is in a dovetail shape.
Preferably, the outermost circumferential surface of the half coupling is provided with a plurality of rectangular grooves which are uniformly distributed on the circumference.
Advantageous effects
The utility model provides a gas turbine hollow rotor structure supported by magnetic bearings. The hollow rotor structure of the gas turbine supported by the magnetic bearing adopts a rigid rotor design, the whole rotor has higher bending rigidity, and the rigidity and the mass are distributed along the axial direction more harmoniously, so that the rotor system is ensured to have no bending street rotating speed in the working rotating speed range.
The bearing adopts a group of (two) magnetic suspension bearings. The bearing is used for the first time in the domestic small and medium-sized gas turbine industry, wherein a rear end bearing of a gas compressor is defined as a front bearing, and a front end bearing of a turbine is defined as a rear bearing.
The magnetic bearing can adjust the magnetic force action through an automatic control system, namely, the supporting rigidity of the bearing is adjusted, so that the critical rotating speed range of the rotor is adjusted and controlled, the vibration value of the rotor is greatly reduced, and the rotor runs more stably.
The rotor journal keeps a suspension state separated from the magnetic bearing during operation, and the non-contact state ensures that the rotor journal has almost no abrasion, thereby greatly prolonging the service life of the rotor.
The rolling protection bearing is made of metal ceramic, and compared with pure metal, the material has higher hardness and has the advantages of obvious wear resistance, corrosion resistance and high temperature resistance.
A two-stage turbine structure is adopted, and a first-stage turbine is a hollow cavity structure and is used for through-flowing air for cooling the blades. Both stages of turbine blades are coated with a high temperature resistant coating. To increase blade fatigue creep strength.
Drawings
FIG. 1 is a schematic structural diagram of the present invention.
Fig. 2 is a schematic cross-sectional structure of the present invention.
Fig. 3 is a schematic partial cross-sectional structure of the present invention.
Fig. 4 is a schematic sectional structure view of the coupling half according to the present invention.
In the figure: 1. a half coupling; 2. a front magnetic bearing; 3. compressor blades; 4. a compressor shaft; 5. a rear magnetic bearing; 6. a first stage turbine blade; 7. a secondary turbine blade; 8. a counterweight screw; 9. an air cooling hole; 10. a main shaft; 20. a special stud; 21. a pull rod bolt group A; 22. a draw bar bolt group B; 23. A balancing weight A; 24. a first stage turbine disk; 25. a second stage turbine disk; 26. a turbine shaft; 27. a balancing weight B; 31. a thrust bearing; 32. a rolling protection bearing; 33. a radial bearing.
Detailed Description
The technical solutions in the embodiments of the present invention will be clearly and completely described below with reference to the drawings in the embodiments of the present invention, and it is obvious that the described embodiments are only a part of the embodiments of the present invention, and not all of the embodiments. All other embodiments, which can be derived by a person skilled in the art from the embodiments given herein without making any creative effort, shall fall within the protection scope of the present invention.
Referring to fig. 1-4, the present invention provides a technical solution: a gas turbine hollow rotor structure supported by magnetic bearings mainly comprises a half coupling 1, a compressor shaft 4, a turbine shaft 26, a front magnetic bearing 2, a rear magnetic bearing 5, a primary turbine disc 24 and a secondary turbine disc 25.
Preferably, the half coupling 1 and the main shaft 10 are connected and torque-transmitted by adopting a sleeve gear structure. Compared with the conventional coupler in the form of the rectangular key, the coupler has long fatigue life and larger strength margin. In addition, 60 rectangular grooves which are uniformly distributed on the circumference are processed on the outermost circumference surface of the half-coupling connecting flange, so that the working rotating speed of the rotor can be conveniently measured. And (4) the function of detection and protection on the operation start of the rotor.
The T-shaped tenons of the compressor blades 3 are uniformly distributed on the circumference and are arranged in a T-shaped groove of the compressor shaft 4; the compressor shaft 4 and the turbine shaft 26 are both hollow structures and are connected and fastened through special stud bolts, and compared with a conventional solid shaft, the hollow structure has the advantages of light weight and difficulty in deformation; because of its light weight, under the prerequisite that the turbine sends out the work the same, and then increase combustion engine output.
The turbine shaft 26 and the first-stage turbine disk 24 are connected and fastened through a high-strength tie-rod bolt group A, and the first-stage turbine disk 24 and the second-stage turbine disk 25 are connected and fastened through a high-strength tie-rod bolt group B. The first stage turbine blades 6 are hollow cavity structures for circulating air for cooling the blades. Both stages of turbine blades are coated with a high temperature resistant coating. To increase blade fatigue life and creep strength.
The compressor shaft 4, the turbine shaft 26, the first-stage turbine disc 24 and the second-stage turbine disc 25 are all provided with grooves for mounting dovetail-shaped balancing weights A23, in addition, threaded holes which are uniformly distributed in the circumference are set on the outer circular surface of the compressor shaft 4, and the screws 8 are additionally mounted during dynamic balance calibration of the rotor.
Preferably, the rotor of the gas turbine adopts a magnetic suspension bearing supporting mode, and the rotor is firstly used in the domestic small and medium-sized gas turbine industry. The rear end of the compressor is provided with a front magnetic bearing 2, the front end of the turbine is provided with a rear magnetic bearing 5, and the rear magnetic bearing 5 is provided with
The arrangement of the air cooling holes 9 is compared withThe structure that the support was arranged at the rotor outer end entirely has the span that reduces, improves the advantage of flexural rigidity. Finally, the bending critical speed of the rotor is increased.
When the combustion engine is not running, the rotor is supported and supported by the rolling protection bearing 32 made of metal ceramic material. During operation, the rotor of the engine floats under the electromagnetic action and is separated from the radial bearing 33 and the thrust bearing 31. Compared with a sliding bearing, the sliding bearing has the advantages that the occupied space of the combustion engine is greatly saved as no lubricating oil system equipment is arranged; the radial bearing 33 of the magnetic suspension bearing is not contacted with the rotor, and only the rolling protection bearing 32 is contacted with the rotor, so that the structure greatly reduces the service life of the rotor of the gas turbine; more importantly, the supporting rigidity of the magnetic suspension bearing can be adjusted through a control system, so that the bending vibration amplitude of the rotor can be reduced, the critical rotating speed range of the rotor is improved, namely the vibration characteristic of the rotor is greatly improved, and the rotor can run more stably.
All the electrical components in the present application are connected with the power supply adapted to the electrical components through the wires, and an appropriate controller should be selected according to actual conditions to meet the control requirements, and specific connection and control sequences should be obtained.
Example (b): this patent adopts the design of rigidity rotor, and whole rotor has higher bending rigidity, and rigidity and quality are more harmonious along axial distribution moreover to guarantee that rotor system does not have the bending rotational speed of just walking in the operating speed within range.
The bearing adopts a group of (two) magnetic suspension bearings. The bearing is used for the first time in the domestic small and medium-sized gas turbine industry, wherein a rear end bearing of a gas compressor is defined as a front bearing, and a front end bearing of a turbine is defined as a rear bearing.
The magnetic bearing can adjust the magnetic force action through an automatic control system, namely, the supporting rigidity of the bearing is adjusted, so that the critical rotating speed range of the rotor is adjusted and controlled, the vibration value of the rotor is greatly reduced, and the rotor runs more stably.
The rotor journal keeps a suspension state separated from the magnetic bearing during operation, and the non-contact state ensures that the rotor journal has almost no abrasion, thereby greatly prolonging the service life of the rotor.
The rolling protection bearing is made of metal ceramic, and compared with pure metal, the material has higher hardness and has the advantages of obvious wear resistance, corrosion resistance and high temperature resistance.
A two-stage turbine structure is adopted, and a first-stage turbine is a hollow cavity structure and is used for through-flowing air for cooling the blades. Both stages of turbine blades are coated with a high temperature resistant coating. To increase blade fatigue creep strength.
It is noted that, herein, relational terms such as first and second, and the like may be used solely to distinguish one entity or action from another entity or action without necessarily requiring or implying any actual such relationship or order between such entities or actions. Also, the terms "comprises," "comprising," or any other variation thereof, are intended to cover a non-exclusive inclusion, such that a process, method, article, or apparatus that comprises a list of elements does not include only those elements but may include other elements not expressly listed or inherent to such process, method, article, or apparatus. Without further limitation. The use of the phrase "comprising one of the elements does not exclude the presence of other like elements in the process, method, article, or apparatus that comprises the element.
Although embodiments of the present invention have been shown and described, it will be appreciated by those skilled in the art that changes, modifications, substitutions and alterations can be made in these embodiments without departing from the principles and spirit of the utility model, the scope of which is defined in the appended claims and their equivalents.
Claims (7)
1. The utility model provides a gas turbine hollow rotor structure of magnetic bearing support, includes half-coupling (1), its characterized in that, main shaft (10) have been inserted to the right side of half-coupling (1), install preceding magnetic bearing (2) on the left side ring face of main shaft (10), compressor shaft (4) are installed to the outside just right side that is located preceding magnetic bearing (2) of main shaft (10), install a plurality of compressor blades (3) on the outer annular surface of compressor shaft (4), turbine shaft (26) are installed to the right side of main shaft (10), turbine shaft (26) with install the same special stud (20) of a plurality of structures between main shaft (10), magnetic bearing (5) are installed after the externally mounted of turbine shaft (26), install the turbine subassembly on the right-hand member face of turbine shaft (26).
2. The magnetic bearing supported gas turbine hollow rotor structure of claim 1, characterized in that said front magnetic bearing (2) comprises a rolling protection bearing (32), said rolling protection bearing (32) is connected with said main shaft (10), a thrust bearing (31) and a radial bearing (33) are respectively installed at the left and right sides in said rolling protection bearing (32), said thrust bearing (31) and said radial bearing (33) are respectively connected with said main shaft (10).
3. The magnetic bearing supported gas turbine hollow rotor structure of claim 1, characterized in that said rear magnetic bearing (5) is provided with air cooling holes (9).
4. The magnetic bearing supported gas turbine hollow rotor structure of claim 1, characterized in that the turbine assembly comprises a first-stage turbine disc (24), the first-stage turbine disc (24) is connected with the turbine shaft (26), a first-stage turbine blade (6) is arranged on the outer ring surface of the first-stage turbine disc (24), a second-stage turbine disc (25) is arranged on the right side of the first-stage turbine disc (24), second-stage turbine blades (7) are arranged on the outer side of the second-stage turbine disc (25), a plurality of balancing weights A (23) with the same structure are inserted on the first-stage turbine disk (24) and the second-stage turbine disk (25), the first-stage turbine disc (24) is connected with the turbine shaft (26) through pull rod bolt groups A (21) which are uniformly distributed on the circumference, the first-stage turbine disc (24) is connected with the second-stage turbine disc (25) through tie rod bolt groups B (22) which are uniformly distributed on the circumference.
5. The hollow rotor structure of a magnetic bearing supported gas turbine according to claim 1, wherein a plurality of balancing weights B (27) having the same structure are embedded on both left and right end surfaces of the compressor shaft (4), the main shaft (10) has a hollow structure, and holes of balancing weights (8) are spirally installed on the left and right sides of the outer annular surface of the compressor shaft (4) and are circumferentially and radially distributed.
6. A magnetic bearing supported gas turbine hollow rotor structure according to claim 4, characterized in that said counterweight A (23) is dovetail-shaped.
7. The hollow rotor structure of a gas turbine supported by magnetic bearings according to claim 1, characterized in that the outermost circumferential surface of the half-coupling (1) is provided with a plurality of rectangular grooves uniformly distributed circumferentially.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202121081931.0U CN215718976U (en) | 2021-05-20 | 2021-05-20 | Gas turbine hollow rotor structure supported by magnetic bearing |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202121081931.0U CN215718976U (en) | 2021-05-20 | 2021-05-20 | Gas turbine hollow rotor structure supported by magnetic bearing |
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| Publication Number | Publication Date |
|---|---|
| CN215718976U true CN215718976U (en) | 2022-02-01 |
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| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN202121081931.0U Expired - Fee Related CN215718976U (en) | 2021-05-20 | 2021-05-20 | Gas turbine hollow rotor structure supported by magnetic bearing |
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Cited By (1)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN114876580A (en) * | 2022-07-12 | 2022-08-09 | 陕西联信材料科技有限公司 | Aircraft engine turbine blade assembly for aircraft manufacturing and preparation method thereof |
-
2021
- 2021-05-20 CN CN202121081931.0U patent/CN215718976U/en not_active Expired - Fee Related
Cited By (1)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN114876580A (en) * | 2022-07-12 | 2022-08-09 | 陕西联信材料科技有限公司 | Aircraft engine turbine blade assembly for aircraft manufacturing and preparation method thereof |
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| CF01 | Termination of patent right due to non-payment of annual fee |
Granted publication date: 20220201 |
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| CF01 | Termination of patent right due to non-payment of annual fee |