CN114856730B - Closed circulation cooling system of supercritical carbon dioxide turbine and adjusting method - Google Patents
Closed circulation cooling system of supercritical carbon dioxide turbine and adjusting method Download PDFInfo
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- CN114856730B CN114856730B CN202210467409.9A CN202210467409A CN114856730B CN 114856730 B CN114856730 B CN 114856730B CN 202210467409 A CN202210467409 A CN 202210467409A CN 114856730 B CN114856730 B CN 114856730B
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- main shaft
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- CURLTUGMZLYLDI-UHFFFAOYSA-N Carbon dioxide Chemical compound O=C=O CURLTUGMZLYLDI-UHFFFAOYSA-N 0.000 title claims abstract description 42
- 238000001816 cooling Methods 0.000 title claims abstract description 38
- 229910002092 carbon dioxide Inorganic materials 0.000 title claims abstract description 21
- 239000001569 carbon dioxide Substances 0.000 title claims abstract description 21
- 238000000034 method Methods 0.000 title claims abstract description 13
- 238000007789 sealing Methods 0.000 claims abstract description 61
- 230000001105 regulatory effect Effects 0.000 claims abstract description 35
- OKTJSMMVPCPJKN-UHFFFAOYSA-N Carbon Chemical group [C] OKTJSMMVPCPJKN-UHFFFAOYSA-N 0.000 claims abstract description 15
- 239000007789 gas Substances 0.000 claims description 95
- 239000000112 cooling gas Substances 0.000 claims description 41
- 238000001514 detection method Methods 0.000 claims description 10
- 238000012544 monitoring process Methods 0.000 claims description 3
- 238000004364 calculation method Methods 0.000 claims 1
- 230000000694 effects Effects 0.000 abstract description 2
- 230000003068 static effect Effects 0.000 description 5
- 239000012535 impurity Substances 0.000 description 2
- 238000010248 power generation Methods 0.000 description 2
- 239000003566 sealing material Substances 0.000 description 2
- 239000002826 coolant Substances 0.000 description 1
- 230000007547 defect Effects 0.000 description 1
- 238000010586 diagram Methods 0.000 description 1
- 238000004088 simulation Methods 0.000 description 1
- 239000007787 solid Substances 0.000 description 1
Classifications
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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
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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
- F01D11/003—Preventing or minimising internal leakage of working-fluid, e.g. between stages by packing rings; Mechanical seals
-
- 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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- Engineering & Computer Science (AREA)
- Mechanical Engineering (AREA)
- General Engineering & Computer Science (AREA)
- Turbine Rotor Nozzle Sealing (AREA)
Abstract
The invention discloses a closed circulation cooling system and an adjusting method of a supercritical carbon dioxide turbine, which ensure the cooling effect, prevent the medium inside the turbine from flowing backwards and prevent a main shaft from axially moving. When the dry gas sealing assembly operates normally, sealing gas of each dry gas sealing assembly is in a normal range value, the opening of the bypass valve is regulated, the opening of the regulating valve is smaller than 50%, the display value of the temperature sensor is observed, and when the temperature is 130-170 ℃, the opening of the regulating valve is kept unchanged; when the temperature is less than 130 ℃, the opening of the regulating valve is reduced, and at the moment, the pressure difference before and after the carbocycle seal is observed, and the pressure difference before and after the carbocycle seal is gradually reduced because the cooling air flow is reduced, so that the difference is always more than 0.1MPa; when the temperature of the dry gas sealing assembly shell is higher than 170 ℃, the opening of the regulating valve on the cooling air pipeline is required to be increased, and the pressure difference before and after carbon ring sealing is gradually increased due to the fact that the cooling air flow is increased, the opening of the regulating valve is slowly increased, and the pressure difference value is kept to be smaller than 0.8MPa all the time.
Description
Technical Field
The invention relates to the technical field of supercritical carbon dioxide turbines, in particular to a closed circulation cooling system of a supercritical carbon dioxide turbine and an adjusting method.
Background
The circulating power generation system taking supercritical carbon dioxide as a medium has high efficiency, can replace the traditional power generation circulating system, has small system volume, and has higher temperature (more than 550 ℃) and pressure (15-32 MPA) of the thermodynamic cycle of the system for improving the efficiency. For better sealing of the unit, the turbine typically selects a dry gas seal as the sealing component. Because the turbine temperature is higher, key parts such as the turbine seal and the like must be cooled in order to eliminate the influence of the temperature on the parts such as the turbine seal and the like.
Because the turbine seal is a dry gas seal, the dry gas seal needs proper sealing gas, if the sealing gas medium is selected improperly, the running cost of the unit can be increased, and meanwhile, if the sealing gas is directly emptied after being used, the loss of the unit can be increased, and the efficiency of the unit can be reduced; the reasonable use of the cooling air flow is one of the keys for realizing normal operation of the turbine unit, if the cooling air flow is improperly used, the sealing ring of the turbine dry gas sealing assembly is easily damaged, turbine media flow backwards, impurities enter the dry gas seal, and the dry gas seal dynamic and static rings are damaged; the unreasonable control of the cooling air flow also easily causes the axial force of the turbine main shaft to be overlarge, and the axial movement occurs to damage the turbine unit.
Disclosure of Invention
The invention aims to overcome the defects of the prior art and provide a closed circulation cooling system and an adjusting method of a supercritical carbon dioxide turbine, which reduce the medium loss of the system, ensure the cooling effect, prevent the medium inside the turbine from flowing backwards and prevent the spindle from moving axially.
The purpose of the invention is realized in the following way:
the closed circulation cooling system of the supercritical carbon dioxide turbine comprises a turbine body, wherein the turbine body is provided with an air inlet cavity and an air outlet cavity, an inner cylinder body is fixed in the turbine body, the inner cylinder body is communicated with the air inlet cavity and the air outlet cavity, a main shaft is arranged in the turbine body, turbine blades are arranged between the main shaft and the inner cylinder body and between the air inlet cavity and the air outlet cavity, turbine end covers are fixed at two ends of the turbine body, a carbocycle seal, a first sparse tooth seal and a first dry gas seal assembly are sequentially arranged between a first end of the main shaft and the corresponding turbine end cover from inside to outside, a gap is reserved between the carbocycle seal and the inner cylinder body, a second sparse tooth seal and a second dry gas seal assembly are sequentially arranged between a second end of the main shaft and the corresponding turbine end cover from inside to outside, a sealing piece is arranged between the second end of the main shaft and the turbine body,
the first end of the main shaft is provided with a first step surface, the second end of the main shaft is provided with a second step surface, the first step surface is axially positioned in cooperation with the inner cylinder body, a containing cavity is formed between the second step surface and the second sparse tooth seal, a dry gas seal air inlet cavity is reserved between the first dry gas seal assembly and the first sparse tooth seal and between the second sparse tooth seal assembly and between the second dry gas seal assembly, a cooling gas cavity is reserved between the first sparse tooth seal and the carbon ring seal and is used for introducing cooling gas, the cooling gas cavity is communicated with the containing cavity through a balance pipe, so that the pressure of the cooling gas cavity and the containing cavity is equal, the front pressure of the carbon ring seal is equal to the pressure of the second step surface, a gap between the inner cylinder body and the main shaft is equal to the pressure of the carbon ring seal and the gap between the inner cylinder body, so that the pressure of the first step surface and the back pressure of the carbon ring seal are equal, a front pressure detection channel and a back pressure detection channel are arranged on the turbine end cover, the front pressure detection channel is communicated with the cooling gas cavity, the front pressure detection channel is communicated with the cooling gas sensor cavity, the front pressure detection channel is communicated with the back pressure sensor, and the back pressure sensor is arranged;
the dry gas seal gas enters the dry gas seal gas inlet chamber, the cooling gas enters the cooling gas chamber, the pressure of the dry gas seal gas is larger than that of the cooling gas chamber, the pressure of the cooling gas chamber is larger than that of medium inside the turbine, part of the dry gas seal gas is mixed with the cooling gas in the cooling gas chamber through the first sparse tooth seal, part of the cooling gas after mixing enters the turbine through the carbocycle seal and a gap between the inner cylinder body and the main shaft, the other part of the cooling gas after mixing enters the accommodating chamber through the balance pipe, the cooling gas enters the turbine through the gap between the seal piece and the main shaft, and the part where the mixed gas passes is cooled.
Preferably, the exhaust cavity of the turbine body is connected with the air inlet end of the compressor through a pipeline, the air outlet end of the compressor is connected with the air inlet end of the high-pressure air storage tank through a pipeline, the air outlet end of the high-pressure air storage tank is respectively connected with a first branch pipeline and a second branch pipeline, the first branch pipeline is connected with a regulating valve and a bypass valve in parallel, the first branch pipeline is connected with a cooling air cavity and is used for inputting cooling air, the second branch pipeline is provided with a heater, and the second branch pipeline is connected with a dry air sealing air inlet cavity and is used for providing sealing air for the first dry air sealing assembly;
the back pressure sensor and the front pressure sensor monitor the front pressure and the back pressure of the carbocycle seal respectively, and the pressure difference between the first step surface and the second step surface is regulated by cooling air, so that the axial stress of the main shaft is balanced.
Preferably, the first dry gas sealing assembly and the second dry gas sealing assembly are provided with temperature sensors on the surfaces of the shells for monitoring the temperatures of the surfaces of the shells.
A method for adjusting a closed circulation cooling system of a supercritical carbon dioxide turbine,
when the dry gas sealing assembly operates normally, sealing gas of each dry gas sealing assembly is in a normal range value, the opening of the bypass valve is regulated, the opening of the regulating valve is smaller than 50%, the display value of the temperature sensor is observed, and when the temperature is 130-170 ℃, the opening of the regulating valve is kept unchanged;
when the temperature is less than 130 ℃, the opening of the regulating valve is reduced, and at the moment, the pressure difference before and after the carbocycle seal is observed, and the pressure difference before and after the carbocycle seal is gradually reduced because the cooling air flow is reduced, so that the difference is always more than 0.1MPa;
when the temperature of the dry gas sealing assembly shell is higher than 170 ℃, the opening of the regulating valve on the cooling air pipeline is required to be increased, and the pressure difference before and after carbon ring sealing is gradually increased due to the fact that the cooling air flow is increased, the opening of the regulating valve is slowly increased, and the pressure difference value is kept to be smaller than 0.8MPa all the time.
Preferably, if the differential pressure value before and after the carbocycle seal is less than 0.1MPa and the dry gas seal housing temperature is still less than 130 ℃, this indicates that the designed fit clearance between the inner cylinder, seal and spindle is large, and the design value is reduced.
Preferably, if the pressure difference between the front and rear of the carbocycle seal is greater than 0.8MPa, and the surface temperature of the dry gas seal housing is still greater than 170 ℃, the designed fit clearance between the inner cylinder body and the sealing element and the main shaft is smaller, and the designed value is increased.
Preferably, the initial design fit clearance values of the inner cylinder body, the sealing element and the main shaft are calculated by fluid software simulation.
By adopting the technical scheme, the invention can reduce the medium loss of the system, reduce the power loss of the dry gas seal heater, improve the system efficiency, prevent the parts of the dry gas seal body from being damaged due to overhigh temperature due to overhigh cooling gas flow, and prevent the cooling gas flow from being overhigh, the axial movement of a main shaft of the turbine and the damage to a unit.
Drawings
FIG. 1 is a schematic diagram of a closed cycle cooling gas system according to the present invention;
FIG. 2 is a schematic view of the internal structure of the turbine of the present invention.
Reference numerals
In the drawing, a first dry gas seal assembly 1, a rear pressure sensor 2, a front pressure sensor 3, a turbine end cover 4, a first sparse tooth seal 5, a carbon ring seal 6, an inner cylinder 7, a first-stage static blade 8 (other static blades and moving blades are arranged between a main shaft 9 and the inner cylinder 7, the moving blades are positioned on the main shaft, the static blades are positioned on the inner cylinder), the main shaft 9, a seal member 10, a turbine end cover 11, a second sparse tooth seal 12 and a second dry gas seal assembly 13.
Detailed Description
Embodiments of a closed cycle cooling system for a supercritical carbon dioxide turbine:
referring to fig. 1, because the main pipeline of the system is carbon dioxide, the cold air used in the invention also adopts carbon dioxide from the system (directly taking the exhaust medium of the compressor, the temperature of the outlet medium of the compressor is less than 120 ℃ and can be directly used as cooling air relative to the temperature of the medium inside the turbine above 550 ℃), so as to reduce the cost and the use convenience. During normal operation, the compressor main gas exhaust pipeline is provided with a bypass, a cooling medium (carbon dioxide) is buffered from the compressor exhaust bypass through the high-pressure gas storage tank, the buffered gas is divided into two parts, one part is taken as cold gas to directly enter the turbine (the pipeline is provided with a cooling gas regulating valve and a bypass valve), the other part is taken as dry gas sealing gas (the dry gas sealing is small in clearance of a dynamic and static ring due to working conditions and structural reasons, and under the high-pressure condition, a higher temperature is needed to prevent the sealing gas from changing into a solid state after interception or expansion in the dry gas sealing, so that the dry gas sealing is damaged). The dry gas sealing gas and the cooling gas are converged in the turbine, discharged through a turbine exhaust pipeline, and discharged medium is cooled and enters the compressor again for circulation, and the cooling gas participates in the system circulation, so that the medium loss is reduced, and the system efficiency is improved.
Referring to fig. 2, dry gas seal gas enters a dry gas seal gas inlet chamber, cooling gas enters a cooling gas chamber, after the dry gas seal gas and the cooling gas are mixed, one part of gas enters a turbine through a gap between an inner cylinder 7 and a main shaft 9, the other part of gas enters the turbine through a gap between the main shaft 9 and a sealing piece 10, and the part through which the mixed gas passes can be cooled. The back pressure sensor 2 and the front pressure sensor 3 monitor the front and back pressure of the carbocycle seal 6 respectively, wherein the front pressure of the carbocycle seal 6 (the pressure of the front pressure sensor 3) is equal to the pressure of the step surface II (the front pressure sensor 3 and the carbocycle seal are communicated through a balance pipe), and the back pressure of the carbocycle seal 6 (the pressure of the back pressure sensor 2) is equal to the pressure of the step surface I (the gap between the inner cylinder 7 and the main shaft 9 is larger). Therefore, in normal operation, the pressure difference between the first step surface and the second step surface must be kept small (regulated by cooling gas), otherwise, the spindle is easy to axially shift to damage the unit, and temperature sensors are installed on the surfaces of the first dry gas seal assembly 1 and the second dry gas seal assembly 13 and used for monitoring the surface temperature of the dry gas seal housing.
Embodiments of a method of adjusting a closed cycle cooling system of a supercritical carbon dioxide turbine:
when the unit operates normally, sealing gas of the dry gas sealing assembly is in a normal range value (the value is given by a sealing manufacturer, the flow required by different units is different), the opening of a bypass valve of a cooling gas pipeline in the figure 1 is regulated to be smaller than 50 percent (when the opening of the regulating valve is smaller, the regulating reaction rate is faster), the display value of a temperature sensor of a shell of the dry gas sealing assembly is observed, and when the temperature is 130-170 ℃, the opening is kept unchanged; when the temperature of the dry gas sealing assembly shell is lower than 130 ℃, the opening of the regulating valve is reduced, and at the same time, attention is paid to observing the front-rear pressure difference (the difference between the pressure value of the front pressure sensor 3 and the pressure value of the rear pressure sensor 2) of the carbocycle seal 6, because the cooling air flow is reduced, the pressure difference between the front and rear of the carbocycle seal is gradually reduced, and the difference is always higher than 0.1MPa (if the difference is too small, the medium of the turbine unit is easy to flow back to the first dry gas sealing assembly 1 and the second dry gas sealing assembly 13 through the inner cylinder 7 and the sealing element 10, and the dry gas sealing assembly 13, and the dry gas sealing damage is easy to be caused because the medium possibly contains impurities, and meanwhile, if the medium flows back, the matching section of the inner cylinder 7, the sealing element 10 and the main shaft 9 cannot be cooled because the medium temperature is higher than 550 ℃, and the matching section of the main shaft and the sealing element 9 are different, the matching clearance between the main shaft and the sealing material is easy to change greatly when the main shaft and the sealing material are at high temperature, and the matching clearance between the main shaft and the main shaft is influenced to normally run at the time, if the difference is lower than 0.1MPa and the temperature of the dry gas sealing assembly shell temperature is still lower than 130 ℃, the proper design clearance between the main shaft 7 and the main shaft and the sealing element and the main shaft 9 should be designed to be greatly reduced; when the temperature of the dry gas seal assembly shell is higher than 170 ℃, the opening of the regulating valve on the cooling air pipeline is required to be increased, and the differential pressure between the front and rear of the carbocycle seal 6 is gradually increased due to the fact that the cooling air flow is increased, the opening of the regulating valve is slowly increased, the differential pressure value is kept to be always smaller than 0.8MPa (if the differential pressure is large, the axial force between the step surface II of the main shaft 9 and the step surface is easily increased, the axial movement of the shaft is easily caused, a machine set is damaged), and if the differential pressure between the front and rear of the carbocycle seal 6 is close to 0.8MPa, the design fit clearance between the inner cylinder 7, the sealing element 10 and the main shaft 9 is indicated to be smaller, and the design value of the inner cylinder 7, the sealing element 10 and the main shaft 9 is properly increased. The design fit clearance values of the inner cylinder 7, the sealing element 10 and the main shaft 9 are calculated by simulation of corresponding fluid software.
Finally, it is noted that the above-mentioned preferred embodiments are only intended to illustrate rather than limit the invention, and that, although the invention has been described in detail by means of the above-mentioned preferred embodiments, it will be understood by those skilled in the art that various changes in form and details may be made therein without departing from the scope of the invention as defined by the appended claims.
Claims (6)
1. A method for adjusting a closed circulation cooling system of a supercritical carbon dioxide turbine is characterized by comprising the following steps of:
the utility model provides a closed circulation cooling system of supercritical carbon dioxide turbine, includes the turbine body, the turbine body has air inlet cavity, exhaust cavity, this internal interior cylinder body that is fixed with of turbine, interior cylinder body and air inlet cavity, exhaust cavity intercommunication are equipped with the main shaft in the turbine body, set up turbine blade between main shaft and the interior cylinder body, turbine blade is located between air inlet cavity, the exhaust cavity, the both ends of turbine body are fixed with the turbine end cover, be equipped with carbocycle seal, first sparse tooth seal, first dry gas seal assembly in proper order between the first end of main shaft and the turbine end cover that corresponds from inside to outside, carbocycle seal is adjacent with interior cylinder body, has the clearance between corresponding turbine end cover, carbocycle seal and the interior cylinder body, is equipped with second sparse tooth seal, second dry gas seal assembly in proper order between the second end of main shaft and the turbine end cover that corresponds from inside to outside, is equipped with sealing member between the second end of main shaft and the turbine body, its characterized in that:
the first end of the main shaft is provided with a first step surface, the second end of the main shaft is provided with a second step surface, the first step surface is axially positioned in cooperation with the inner cylinder body, a containing cavity is formed between the second step surface and the second sparse tooth seal, a dry gas seal air inlet cavity is reserved between the first dry gas seal assembly and the first sparse tooth seal and between the second sparse tooth seal assembly and between the second dry gas seal assembly, a cooling gas cavity is reserved between the first sparse tooth seal and the carbon ring seal and is used for introducing cooling gas, the cooling gas cavity is communicated with the containing cavity through a balance pipe, so that the pressure of the cooling gas cavity and the containing cavity is equal, the front pressure of the carbon ring seal is equal to the pressure of the second step surface, a gap between the inner cylinder body and the main shaft is equal to the pressure of the carbon ring seal and the gap between the inner cylinder body, so that the pressure of the first step surface and the back pressure of the carbon ring seal are equal, a front pressure detection channel and a back pressure detection channel are arranged on the turbine end cover, the front pressure detection channel is communicated with the cooling gas cavity, the front pressure detection channel is communicated with the cooling gas sensor cavity, the front pressure detection channel is communicated with the back pressure sensor, and the back pressure sensor is arranged;
the dry gas seal gas enters a dry gas seal gas inlet chamber, the cooling gas enters a cooling gas chamber, the pressure of the dry gas seal gas is larger than that of the cooling gas chamber, the pressure of the cooling gas chamber is larger than that of medium in a turbine, part of the dry gas seal gas is mixed with the cooling gas in the cooling gas chamber through a first sparse tooth seal, part of the cooling gas after mixing enters the turbine through a carbon ring seal and a gap between an inner cylinder body and a main shaft, the other part of the cooling gas after mixing enters a containing cavity through a balance pipe, and then enters the turbine through a gap between a seal piece and the main shaft, and the part where the mixed gas passes is cooled;
when the dry gas sealing assembly operates normally, sealing gas of each dry gas sealing assembly is in a normal range value, the opening of the bypass valve is regulated, the opening of the regulating valve is smaller than 50%, the display value of the temperature sensor is observed, and when the temperature is 130-170 ℃, the opening of the regulating valve is kept unchanged;
when the temperature is less than 130 ℃, the opening of the regulating valve is reduced, and at the moment, the pressure difference before and after the carbocycle seal is observed, and the pressure difference before and after the carbocycle seal is gradually reduced because the cooling air flow is reduced, so that the pressure difference value is kept to be always more than 0.1MPa;
when the temperature of the dry gas sealing assembly shell is higher than 170 ℃, the opening of the regulating valve on the cooling air pipeline is required to be increased, and the pressure difference before and after carbon ring sealing is gradually increased due to the fact that the cooling air flow is increased, the opening of the regulating valve is gradually increased, and the pressure difference value is kept to be smaller than 0.8MPa all the time.
2. The method of regulating a closed cycle cooling system of a supercritical carbon dioxide turbine according to claim 1, wherein: the turbine comprises a turbine body, a high-pressure gas storage tank, a first branch pipeline, a second branch pipeline, a regulating valve, a bypass valve, a cooling gas cavity, a heater, a dry gas sealing air inlet cavity, a first dry gas sealing assembly and a second dry gas sealing assembly, wherein an exhaust cavity of the turbine body is connected with the compressor air inlet end through a pipeline;
the back pressure sensor and the front pressure sensor monitor the front pressure and the back pressure of the carbocycle seal respectively, and the pressure difference between the first step surface and the second step surface is regulated by cooling air, so that the axial stress of the main shaft is balanced.
3. The method of regulating a closed cycle cooling system of a supercritical carbon dioxide turbine according to claim 1, wherein: and the shell surfaces of the first dry gas sealing assembly and the second dry gas sealing assembly are provided with temperature sensors for monitoring the temperature of the shell surfaces.
4. The method of regulating a closed cycle cooling system of a supercritical carbon dioxide turbine according to claim 1, wherein: when the front-back pressure difference value of the carbon ring seal is smaller than 0.1MPa and the temperature of the dry gas seal shell is still smaller than 130 ℃, the design fit clearance between the inner cylinder body and the main shaft is excessively large, and the design fit clearance value of the inner cylinder body and the main shaft is required to be reduced.
5. The method of regulating a closed cycle cooling system of a supercritical carbon dioxide turbine according to claim 1, wherein: when the front-back pressure difference value of the carbon ring seal is larger than 0.8MPa and the surface temperature of the dry gas seal shell is still larger than 170 ℃, the designed fit clearance between the inner cylinder body and the main shaft is too small, and the designed fit clearance value of the inner cylinder body and the main shaft are required to be increased.
6. A method of regulating a closed cycle cooling system for a supercritical carbon dioxide turbine according to claim 4 or 5, wherein: the initial design fit clearance values of the inner cylinder body, the sealing element and the main shaft are obtained through fluid software simulation calculation.
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| CN114087038A (en) * | 2021-11-11 | 2022-02-25 | 重庆江增船舶重工有限公司 | Cooling structure and method for cylinder body during shutdown of supercritical carbon dioxide turbine |
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