CN112228160B - Supercritical carbon dioxide rotor sectional cooling and sealing structure - Google Patents
Supercritical carbon dioxide rotor sectional cooling and sealing structure Download PDFInfo
- Publication number
- CN112228160B CN112228160B CN202011127247.1A CN202011127247A CN112228160B CN 112228160 B CN112228160 B CN 112228160B CN 202011127247 A CN202011127247 A CN 202011127247A CN 112228160 B CN112228160 B CN 112228160B
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- rotor
- cooling
- shaft end
- sealing structure
- sealing
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- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F01—MACHINES OR ENGINES IN GENERAL; ENGINE PLANTS IN GENERAL; STEAM ENGINES
- F01D—NON-POSITIVE DISPLACEMENT MACHINES OR ENGINES, e.g. STEAM TURBINES
- F01D5/00—Blades; Blade-carrying members; Heating, heat-insulating, cooling or antivibration means on the blades or the members
- F01D5/02—Blade-carrying members, e.g. rotors
- F01D5/08—Heating, heat-insulating or cooling means
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- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F01—MACHINES OR ENGINES IN GENERAL; ENGINE PLANTS IN GENERAL; STEAM ENGINES
- F01D—NON-POSITIVE DISPLACEMENT MACHINES OR ENGINES, e.g. STEAM TURBINES
- F01D11/00—Preventing or minimising internal leakage of working-fluid, e.g. between stages
- F01D11/02—Preventing or minimising internal leakage of working-fluid, e.g. between stages by non-contact sealings, e.g. of labyrinth type
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- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F01—MACHINES OR ENGINES IN GENERAL; ENGINE PLANTS IN GENERAL; STEAM ENGINES
- F01D—NON-POSITIVE DISPLACEMENT MACHINES OR ENGINES, e.g. STEAM TURBINES
- F01D11/00—Preventing or minimising internal leakage of working-fluid, e.g. between stages
- F01D11/02—Preventing or minimising internal leakage of working-fluid, e.g. between stages by non-contact sealings, e.g. of labyrinth type
- F01D11/04—Preventing or minimising internal leakage of working-fluid, e.g. between stages by non-contact sealings, e.g. of labyrinth type using sealing fluid, e.g. steam
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- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F01—MACHINES OR ENGINES IN GENERAL; ENGINE PLANTS IN GENERAL; STEAM ENGINES
- F01D—NON-POSITIVE DISPLACEMENT MACHINES OR ENGINES, e.g. STEAM TURBINES
- F01D25/00—Component parts, details, or accessories, not provided for in, or of interest apart from, other groups
- F01D25/08—Cooling; Heating; Heat-insulation
- F01D25/12—Cooling
Abstract
The invention provides a sectional cooling and sealing structure of a supercritical carbon dioxide rotor, which comprises the following components: the cooling device comprises a cylinder body, a rotor and a segmented cooling sealing assembly; the rotor is connected with the cylinder body; the segmented cooling seal assembly is mounted between the rotor and the cylinder block. The invention realizes that the temperature of the rotor is gradually reduced to 100 ℃ from the exhaust temperature, greatly reduces the heat conduction and the heat radiation of the rotor along the axial direction, and ensures that the dry gas seal can operate at a safe temperature. In addition, the structure of the invention is safe and reliable, and can effectively solve the cooling and sealing problems of the supercritical carbon dioxide rotor.
Description
Technical Field
The invention relates to the technical field of cooling and sealing structures, in particular to a sectional cooling and sealing structure of a supercritical carbon dioxide rotor.
Background
The Brayton cycle of supercritical carbon dioxide has good application prospects in many fields due to the advantages of high efficiency, small system volume, low noise and the like, so that the research on the technology of the supercritical carbon dioxide turbine unit has great significance.
For supercritical carbon dioxide power plants, since the turbine exhaust pressure is relatively high, dry gas seal systems are often employed to reduce shaft end leakage. However, dry gas seals have certain temperature requirements, i.e. the temperature of the seal gas space cannot exceed 200 ℃, and the exhaust temperature of the turbine far exceeds this temperature. Therefore, in order to ensure the dry gas sealing system to operate safely and reliably, a reasonably designed sealing and rotor cooling structure becomes a key for solving the problem.
Disclosure of Invention
In order to solve the above technical problems, the present invention provides a cooling and sealing structure capable of making the temperature of a sealed air space lower than 200 ℃.
The invention provides a supercritical carbon dioxide rotor sectional cooling and sealing structure, which comprises: the cooling device comprises a cylinder body, a rotor and a segmented cooling sealing assembly; the rotor is connected with the cylinder body; the segmented cooling seal assembly is mounted between the rotor and the cylinder block; the cylinder block includes: an outer cylinder and an inner cylinder; a cavity is arranged between the outer cylinder and the inner cylinder; the outer cylinder and the inner cylinder are respectively connected with the rotor; the segment cooled seal assembly includes: a shaft end labyrinth cooling sealing structure and a dry gas sealing structure; the shaft end labyrinth cooling sealing structure and the dry gas sealing structure are arranged between the outer cylinder and the rotor; the shaft end labyrinth cooling and sealing structure comprises: the cooling air inlet is arranged between the two sections of shaft end labyrinth seal teeth; and the cold air inlets are communicated between the two adjacent sections of shaft end labyrinth seal teeth from the outer cylinder.
Preferably, the shaft end labyrinth seal tooth is provided with three sections, and the number of the cold air inlets is two, namely a first section cold air inlet and a second section cold air inlet.
Preferably, three sections of shaft end labyrinth seal teeth are arranged in a ladder manner, and two ends of a ladder shaft matched with the shaft end labyrinth seal teeth are arranged in sharp angles.
Preferably, the dry gas sealing structure includes: the dry gas sealing body, the sealing gas inlet, the first exhaust port and the second exhaust port; the dry gas seal body is disposed between the outer cylinder and the rotor; the dry gas sealing body is arranged adjacent to the shaft end labyrinth sealing teeth; the sealing air inlet is arranged between the shaft end labyrinth seal teeth and the dry air sealing body; the first exhaust port and the second exhaust port are arranged in parallel and are both led to the outside from the dry gas sealing body through the outer cylinder.
Preferably, the dry gas sealing structure further comprises an isolation gas inlet, and the isolation gas inlet is connected with the outer cylinder and the dry gas sealing body.
Compared with the prior art, the invention has the beneficial effects that: the sectional cooling sealing assembly arranged between the rotor and the cylinder body is used for cooling the shaft end of the rotor in a sectional manner, so that the thermal stress of the unit in operation can be reduced, and the service life of the rotor is prolonged; the axial heat conduction effect of the rotor is greatly reduced, so that the dry gas seal can operate at safe and reliable temperature and is not influenced by the temperature of the inlet gas.
Drawings
In order to more clearly illustrate the embodiments of the present invention or the technical solutions in the prior art, the drawings used in the description of the embodiments or the prior art will be briefly described below, and it is obvious that the drawings in the following description are some embodiments of the present invention, and other drawings can be obtained by those skilled in the art without creative efforts.
Fig. 1 is a schematic view of a sectional cooling and sealing structure of a supercritical carbon dioxide rotor according to an embodiment of the present invention.
Description of reference numerals:
1: an outer cylinder; 2: an inner cylinder; 3: a rotor; 4: shaft end labyrinth seal teeth; 5: a dry gas seal body; 6: a section of cold air inlet; 7: a second stage cold air inlet; 8: a seal gas inlet; 9: an insulating gas inlet; 10: a first exhaust port; 11: a second exhaust port.
Detailed Description
The technical solutions of the present invention will be described clearly and completely with reference to the following embodiments, and it should be understood that the described embodiments are some, but not all, embodiments of the present invention. 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.
In the description of the present invention, it is to be understood that the terms "center", "longitudinal", "lateral", "length", "width", "thickness", "upper", "lower", "front", "rear", "left", "right", "vertical", "horizontal", "top", "bottom", "inner", "outer", "clockwise", "counterclockwise", and the like, indicate orientations and positional relationships based on those shown in the drawings, and are used only for convenience of description and simplicity of description, and do not indicate or imply that the device or element being referred to must have a particular orientation, be constructed and operated in a particular orientation, and thus, should not be considered as limiting the present invention.
Furthermore, the terms "first", "second" and "first" are used for descriptive purposes only and are not to be construed as indicating or implying relative importance or implicitly indicating the number of technical features indicated. Thus, features defined as "first", "second", may explicitly or implicitly include one or more of the described features. In the description of the present invention, "a plurality" means two or more unless specifically defined otherwise. Furthermore, the terms "mounted," "connected," and "connected" are to be construed broadly and may, for example, be fixedly connected, detachably connected, or integrally connected; can be mechanically or electrically connected; they may be connected directly or indirectly through intervening media, or they may be interconnected between two elements. The specific meanings of the above terms in the present invention can be understood in specific cases to those skilled in the art.
As shown in fig. 1, the present invention provides a sectional cooling and sealing structure for a supercritical carbon dioxide rotor, comprising: the cylinder body, the rotor 3 and the sectional cooling sealing assembly; the rotor 3 is connected with the cylinder body; the sectional cooling seal assembly is installed between the rotor 3 and the cylinder body. The sectional cooling sealing assembly can reduce the thermal stress of the unit operation and prolong the service life of the rotor by cooling the shaft end of the rotor in sections.
In a more preferred embodiment, the cylinder block comprises: an outer cylinder 1 and an inner cylinder 2; a cavity is arranged between the outer cylinder 1 and the inner cylinder 2; the outer cylinder 1 and the inner cylinder 2 are connected to a rotor 3, respectively. The segment cooling seal assembly includes: a shaft end labyrinth cooling sealing structure and a dry gas sealing structure; the shaft end labyrinth cooling sealing structure and the dry gas sealing structure are arranged between the outer cylinder 1 and the rotor 3. The shaft end labyrinth cooling and sealing structure can greatly reduce the axial heat conduction effect of the rotor, so that the dry gas seal can operate at safe and reliable temperature and is not influenced by the inlet air temperature.
In a more preferred embodiment, the shaft end labyrinth cooling seal structure comprises: a plurality of sections of shaft end labyrinth seal teeth 4 and a plurality of cold air inlets arranged between two adjacent sections of shaft end labyrinth seal teeth 4; a plurality of cold air inlets are communicated between the labyrinth seal teeth 4 of the two adjacent sections of shaft ends from the outer cylinder 1. In the present embodiment, the shaft end labyrinth seal teeth 4 are preferably provided in three sections, and the number of the cold air inlets is preferably two, i.e., a first-section cold air inlet 6 and a second-section cold air inlet 7. Three sections of shaft end labyrinth seal teeth 4 are arranged by adopting a stepped shaft, and sharp corner structures are arranged on two sides of the stepped shaft, so that the leakage rate of each section can be greatly reduced, and the unit efficiency is improved. Through the segmented gas supply of the rotor shaft end, the supercritical carbon dioxide unit can realize quick response, the starting time of the unit is shortened, and the economic benefit is high.
In a more preferred embodiment, the dry gas seal structure comprises: a dry gas seal body 5, a seal gas inlet 8, a first exhaust port 10 and a second exhaust port 11; the dry gas seal body 5 is arranged between the outer cylinder 1 and the rotor 3; the dry gas sealing body 5 is arranged adjacent to the shaft end labyrinth seal teeth 4; the sealing gas inlet 8 is arranged between the shaft end labyrinth seal teeth 4 and the dry gas seal body 5; the first exhaust port 10 and the second exhaust port 11 are arranged in parallel and each lead from the dry gas seal body 5 to the outside through the outer cylinder 1. Through cooling the rotor shaft end in sections, the shaft end sealing and axle holding phenomenon caused by the fact that sealing gas in the dry gas sealing body 5 directly contacts with the extremely hot rotor can be effectively avoided, and the running stability of the unit is improved.
The dry gas sealing structure further comprises an isolation gas inlet 9, and the isolation gas inlet 9 is connected with the outer cylinder 1 and the dry gas sealing body 5. The isolating gas isolates outside air and oil stains, so that the dry gas sealing structure is prevented from being polluted, the dry gas sealing structure is safe and reliable to operate, and finally the sealing of the shaft end of the turbine is realized.
The first section cold air inlet 6, the second section cold air inlet 7 and the seal air inlet 8 are respectively filled with cold air with the temperature which is sequentially reduced along the axial direction so as to cool the rotor 3 in sections. The temperature of the gas is slightly lower than the exhaust temperature, the pressure is adjusted by a valve to enable the gas to slightly flow in the C direction through the shaft end labyrinth seal teeth 4, and the gas is gradually reduced in pressure and temperature, so that the rotor is cooled for the first time.
The second-stage cold air comes from a high-temperature heat regenerator, the temperature of the second-stage cold air is about 200 ℃, the second-stage cold air is pressurized by a plunger pump, the pressure of the second-stage cold air is slightly larger than that of the first-stage cold air, the second-stage cold air flows along the B direction through the shaft end labyrinth seal teeth 4, and the second-stage cold air is gradually reduced in pressure and temperature, so.
The sealing gas comes from the air extraction opening of the compressor, the pressure of the sealing gas is adjusted by a valve and is slightly larger than low-pressure cold air, the temperature is heated to about 100 ℃, the sealing gas flows to two sides, one side of the sealing gas is discharged from the first exhaust opening 10 through the dry gas sealing body 5, the other side of the sealing gas flows along the A direction through the shaft end labyrinth sealing teeth 4, the pressure is gradually reduced, the temperature is reduced, and the third cooling of the rotor is realized.
After three times of cooling, the temperature of the rotor is gradually reduced to 100 ℃ from the exhaust temperature, the axial thermal stress of the rotor is reduced, the axial heat conduction and radiation of the rotor are greatly reduced, and the dry gas seal can operate at a safe temperature.
Taking a 10MW supercritical carbon dioxide turbine rotor sectional cooling and sealing structure as an example, the turbine inlet pressure is 25MPa, the inlet temperature is 500 ℃, the exhaust pressure is 8.5MPa, and the exhaust temperature is 385 ℃.
The cold air at the outlet of the preheater is adjusted to 8.6MPa through a valve, the temperature is about 350 ℃, and the cold air enters the labyrinth seal of the first section of the shaft end through a section of cold air inlet 6 on the outer cylinder 1, so that the first section of the rotor is cooled.
Cold air at the cold end inlet of the low-temperature regenerator is pressurized to 8.7MPa by a plunger pump, the temperature is about 180 ℃, and the cold air enters the labyrinth seal at the second section of the shaft end through a second section of cold air inlet 7 on the outer cylinder 1, so that the second section of the rotor is cooled.
The sealing gas pressure of the dry gas sealing body 5 is 8.8Mpa, the temperature is about 100 ℃, and the dry gas enters the third section of sealing through the sealing gas inlet 8 on the outer cylinder 1, so that the third section of cooling of the rotor is realized. All paths of gas sources from the supercritical carbon dioxide system are connected with the pipe orifices on the outer cylinder 1 according to requirements.
Finally, it should be noted that: the above embodiments are only used to illustrate the technical solution of the present invention, and not to limit the same; while the invention has been described in detail and with reference to the foregoing embodiments, it will be understood by those skilled in the art that: the technical solutions described in the foregoing embodiments may still be modified, or some or all of the technical features may be equivalently replaced; and the modifications or the substitutions do not make the essence of the corresponding technical solutions depart from the scope of the technical solutions of the embodiments of the present invention.
Claims (5)
1. A supercritical carbon dioxide rotor segmented cooling and sealing structure is characterized by comprising: the cooling device comprises a cylinder body, a rotor (3) and a sectional cooling sealing assembly; the rotor (3) is connected with the cylinder body; the segmented cooling seal assembly is mounted between the rotor (3) and the cylinder block; the cylinder block includes: an outer cylinder (1) and an inner cylinder (2); a cavity is arranged between the outer cylinder (1) and the inner cylinder (2); the outer cylinder (1) and the inner cylinder (2) are respectively connected with the rotor (3); the segment cooled seal assembly includes: a shaft end labyrinth cooling sealing structure and a dry gas sealing structure; the shaft end labyrinth cooling sealing structure and the dry gas sealing structure are arranged between the outer cylinder (1) and the rotor (3); the shaft end labyrinth cooling and sealing structure comprises: a plurality of sections of shaft end labyrinth seal teeth (4) and a plurality of cold air inlets arranged between two adjacent sections of the shaft end labyrinth seal teeth (4); and a plurality of cold air inlets are communicated between two adjacent sections of shaft end labyrinth seal teeth (4) from the outer cylinder (1).
2. The supercritical carbon dioxide rotor sectional cooling and sealing structure according to claim 1 is characterized in that the shaft end labyrinth seal teeth (4) are provided with three sections, and the number of the cold air inlets is two, namely a first section cold air inlet (6) and a second section cold air inlet (7).
3. The sectional cooling and sealing structure of the supercritical carbon dioxide rotor according to claim 2, wherein three sections of the shaft end labyrinth seal teeth (4) are arranged in a ladder shape, and two ends of the ladder shaft matched with the shaft end labyrinth seal teeth are arranged in sharp corners.
4. The supercritical carbon dioxide rotor stage cooling and sealing structure according to claim 2 wherein the dry gas sealing structure comprises: a dry gas sealing body (5), a sealing gas inlet (8), a first exhaust port (10) and a second exhaust port (11); the dry gas seal body (5) is arranged between the outer cylinder (1) and the rotor (3); the dry gas sealing body (5) is arranged adjacent to the shaft end labyrinth sealing teeth (4); the sealing air inlet (8) is arranged between the shaft end labyrinth seal teeth (4) and the dry air seal body (5); the first exhaust port (10) and the second exhaust port (11) are arranged in parallel and both lead to the outside from the dry gas sealing body (5) through the outer cylinder (1).
5. The supercritical carbon dioxide rotor segment cooling and sealing structure according to claim 4 is characterized in that the dry gas sealing structure further comprises a shielding gas inlet (9), and the shielding gas inlet (9) connects the outer cylinder (1) and the dry gas sealing body (5).
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202011127247.1A CN112228160B (en) | 2020-10-20 | 2020-10-20 | Supercritical carbon dioxide rotor sectional cooling and sealing structure |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202011127247.1A CN112228160B (en) | 2020-10-20 | 2020-10-20 | Supercritical carbon dioxide rotor sectional cooling and sealing structure |
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| Publication Number | Publication Date |
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| CN112228160A CN112228160A (en) | 2021-01-15 |
| CN112228160B true CN112228160B (en) | 2021-06-18 |
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| Application Number | Title | Priority Date | Filing Date |
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| CN202011127247.1A Active CN112228160B (en) | 2020-10-20 | 2020-10-20 | Supercritical carbon dioxide rotor sectional cooling and sealing structure |
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Family Cites Families (5)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| AU2011372779B2 (en) * | 2011-10-27 | 2014-04-24 | Mitsubishi Heavy Industries, Ltd. | Dry gas seal structure |
| DE102014211690A1 (en) * | 2014-06-18 | 2015-12-24 | Siemens Aktiengesellschaft | Fluid energy machine, method of operation |
| CN205297656U (en) * | 2015-12-18 | 2016-06-08 | 赵忠波 | Combined type atmoseal device |
| US11441487B2 (en) * | 2018-04-27 | 2022-09-13 | Concepts Nrec, Llc | Turbomachine with internal bearing and rotor-spline interface cooling and systems incorporating the same |
| CN111577400A (en) * | 2020-04-29 | 2020-08-25 | 中国核动力研究设计院 | Supercritical carbon dioxide turbine shaft end sealing method and device adopting dry gas coupling labyrinth sealing |
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- 2020-10-20 CN CN202011127247.1A patent/CN112228160B/en active Active
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