CN113653539B - Turbine rotor arrangement system - Google Patents
Turbine rotor arrangement system Download PDFInfo
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- CN113653539B CN113653539B CN202110990710.3A CN202110990710A CN113653539B CN 113653539 B CN113653539 B CN 113653539B CN 202110990710 A CN202110990710 A CN 202110990710A CN 113653539 B CN113653539 B CN 113653539B
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- rotating shaft
- air inlet
- seal
- turbine rotor
- exhaust port
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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
- 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
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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
- F01D25/16—Arrangement of bearings; Supporting or mounting bearings in casings
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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
- F01D25/24—Casings; Casing parts, e.g. diaphragms, casing fastenings
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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
- F01D25/24—Casings; Casing parts, e.g. diaphragms, casing fastenings
- F01D25/26—Double casings; Measures against temperature strain in casings
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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
- F01D25/30—Exhaust heads, chambers, or the like
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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
- F01D5/06—Rotors for more than one axial stage, e.g. of drum or multiple disc type; Details thereof, e.g. shafts, shaft connections
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- Engineering & Computer Science (AREA)
- Mechanical Engineering (AREA)
- General Engineering & Computer Science (AREA)
- Turbine Rotor Nozzle Sealing (AREA)
Abstract
The invention relates to the technical field of turbine rotary machinery, and discloses a turbine rotor arrangement system. The turbine rotor arrangement system comprises a turbine cylinder, a rotating shaft, a boss and a first air inlet, wherein the rotating shaft is arranged in the turbine cylinder, and a first low-temperature region, a high-temperature region and a second low-temperature region are sequentially arranged on the rotating shaft along the axial direction of the rotating shaft; the boss is arranged in the first low-temperature area of the rotating shaft, and a first dry gas seal is sleeved on the periphery of the boss; the first air inlet is arranged on one side, close to the high-temperature area, of the boss, and the first air inlet is used for communicating a cooling air source. The turbine rotor arrangement system does not need to arrange a balance disc, and thrust generated by pressure difference before and after a boss sealed by dry gas is arranged to balance through flow and axial thrust generated by sealing teeth, so that the whole operation efficiency of the unit is higher, the whole span of the rotor is smaller, and the safety performance and the economic performance of the unit are better.
Description
Technical Field
The invention relates to the technical field of turbine rotary machinery, in particular to a turbine rotor arrangement system.
Background
The supercritical carbon dioxide turbine rotor is suitable for power generation equipment, and the existing balance piston is mostly arranged at the high temperature section of the turbine, and because the air leakage radius is large, the length of the balance piston is long to control the air leakage, so that the high temperature section of the turbine is overlong, and the safety performance of a unit is low. There are also few balance pistons arranged in the low temperature section, but the existing rotor arrangement scheme of steam cycle has larger balance disc length and diameter, resulting in larger overall span of the rotor, which is unfavorable for the overall structural design of the unit, and makes the safety and economical performance lower.
Disclosure of Invention
Based on the above, the invention aims to provide a turbine rotor arrangement system which does not need to arrange a balance disc, has higher overall operation efficiency of a unit, smaller overall span of a rotor and better safety performance and economic performance of the unit.
In order to achieve the above purpose, the invention adopts the following technical scheme:
a turbine rotor arrangement system comprising:
a turbine cylinder;
the rotating shaft is arranged in the turbine cylinder, and a first low-temperature region, a high-temperature region and a second low-temperature region are sequentially arranged along the axial direction of the rotating shaft;
the boss is arranged in the first low-temperature area of the rotating shaft, and a first dry gas seal is sleeved on the periphery of the boss;
the first air inlet is arranged on one side, close to the high-temperature area, of the boss, and the first air inlet is used for communicating a cooling air source.
As a preferred embodiment of the turbine rotor arrangement system, further comprising:
the turbine rotor is arranged in the high-temperature area of the rotating shaft, and blades are arranged on the periphery of the turbine rotor;
the second air inlet is arranged in the high temperature area of the rotating shaft and is used for being communicated with the high Wen Qiyuan so as to drive the blades to drive the rotating shaft to rotate.
As a preferred embodiment of the turbine rotor arrangement system, further comprising:
the first exhaust port is arranged in the high temperature area of the rotating shaft and is positioned between the first air inlet and the second air inlet, a first seal is arranged between the first air inlet and the first exhaust port, the first seal is arranged on the rotating shaft in a sealing manner, and the first exhaust port and the first air inlet can be communicated through a gap between the first seal and the rotating shaft.
As a preferred scheme of the turbine rotor arrangement system, a second seal is arranged between the second air inlet and the first air outlet, the second seal is arranged on the rotating shaft in a sealing mode, and the second air inlet and the first air outlet can be communicated through a gap between the second seal and the rotating shaft.
As a preferred embodiment of the turbine rotor arrangement system, further comprising:
the second exhaust port is arranged in the high temperature area of the rotating shaft, the second exhaust port is communicated with the first exhaust port, the second air inlet and the second exhaust port are respectively arranged on two sides of the turbine rotor, the second exhaust port is far away from the boss relative to the second air inlet, and the second exhaust port is used for collecting high temperature gas passing through the blades.
As a preferable mode of the turbine rotor arrangement system, the turbine cylinder includes an outer cylinder and an inner cylinder, the inner cylinder is provided in the outer cylinder, the rotation shaft is provided in the inner cylinder, and the first exhaust port and the second exhaust port are communicated through a gap between the inner cylinder and the outer cylinder.
As a preferable mode of the turbine rotor arrangement system, the turbine cylinder is a single-layer cylinder, and the first exhaust port and the second exhaust port are communicated through a communicating pipe or an in-cylinder gap.
As a preferred embodiment of the turbine rotor arrangement system, further comprising:
the third air inlet is arranged in the second low-temperature area of the rotating shaft, the third air inlet is communicated with the first air inlet, a third seal is arranged between the second air outlet and the third air inlet, the third seal is arranged on the rotating shaft in a sealing manner, and the third air inlet and the second air outlet can be communicated with a gap between the rotating shaft through the third seal.
As a preferable scheme of the turbine rotor arrangement system, bearings are respectively arranged at two ends of the rotating shaft and used for supporting the rotating shaft, and a bearing thrust disc is respectively arranged at two sides of the rotating shaft positioned at one side of the first low-temperature region.
As a preferred embodiment of the turbine rotor arrangement system, further comprising:
the second dry gas seal is sleeved on the rotating shaft and located in the second low-temperature area, the inner diameter of the first dry gas seal is larger than that of the second dry gas seal, and the inner diameter of the first dry gas seal is larger than the outer diameter of the bearing thrust disc.
The beneficial effects of the invention are as follows:
the invention provides a turbine rotor arrangement system, which comprises a turbine cylinder, a rotating shaft, a boss and a first air inlet, wherein the rotating shaft is sequentially provided with a first low-temperature region, a high-temperature region and a second low-temperature region along the axial direction; under the structure, one side of the first dry gas seal is the air pressure of the first air inlet, the other side is the atmospheric pressure, and the axial thrust of the rotor is balanced through the pressure difference at the two sides of the first dry gas seal, namely, the balance disc is not required to be arranged, and the balance force can be adjusted by adjusting the air pressure of the cooling air introduced by the first air inlet; through the arrangement, the whole span of the rotor is shortened, the whole structural design of the rotor is facilitated, and the safety and the economic performance of the unit are improved.
Drawings
In order to more clearly illustrate the technical solutions of the embodiments of the present invention, the following description will briefly explain the drawings needed in the description of the embodiments of the present invention, and it is obvious that the drawings in the following description are only some embodiments of the present invention, and other drawings may be obtained according to the contents of the embodiments of the present invention and these drawings without inventive effort for those skilled in the art.
FIG. 1 is a schematic semi-sectional view of a turbine rotor arrangement system provided in an embodiment of the present invention.
In the figure:
1. a rotating shaft; 2. a bearing; 3. a bearing thrust disc; 10. a first low temperature zone; 20. a high temperature zone; 30. a second low temperature zone; 101. a boss; 102. a first dry gas seal; 103. a first air inlet; 104. a first seal; 201. a turbine rotor; 202. a blade; 203. a second air inlet; 204. a first exhaust port; 205. a second seal; 206. a second exhaust port; 301. a third air inlet; 302. a third seal; 303. and (5) sealing the second dry gas.
Detailed Description
The invention is described in further detail below with reference to the drawings and examples. It is to be understood that the specific embodiments described herein are merely illustrative of the invention and are not limiting thereof. It should be further noted that, for convenience of description, only some, but not all of the structures related to the present invention are shown in the drawings.
In the description of the present invention, unless explicitly stated and limited otherwise, the terms "connected," "connected," and "fixed" are to be construed broadly, and may be, for example, fixedly connected, detachably connected, or integrally formed; can be mechanically or electrically connected; can be directly connected or indirectly connected through an intermediate medium, and can be communicated with the inside of two elements or the interaction relationship of the two elements. The specific meaning of the above terms in the present invention will be understood in specific cases by those of ordinary skill in the art.
In the present invention, unless expressly stated or limited otherwise, a first feature "above" or "below" a second feature may include both the first and second features being in direct contact, as well as the first and second features not being in direct contact but being in contact with each other through additional features therebetween. Moreover, a first feature being "above," "over" and "on" a second feature includes the first feature being directly above and obliquely above the second feature, or simply indicating that the first feature is higher in level than the second feature. The first feature being "under", "below" and "beneath" the second feature includes the first feature being directly under and obliquely below the second feature, or simply means that the first feature is less level than the second feature.
In the description of the present embodiment, the terms "upper", "lower", "left", "right", and the like are orientation or positional relationships based on those shown in the drawings, merely for convenience of description and simplicity of operation, and do not indicate or imply that the apparatus or elements referred to must have a specific orientation, be constructed and operated in a specific orientation, and thus should not be construed as limiting the invention. Furthermore, the terms "first," "second," and the like, are used merely for distinguishing between descriptions and not for distinguishing between them.
As shown in fig. 1, the present embodiment provides a turbine rotor arrangement system, which includes a turbine cylinder, a rotating shaft 1, a boss 101 and a first air inlet 103, the rotating shaft 1 is disposed in the turbine cylinder, the rotating shaft 1 is sequentially provided with a first low temperature region 10, a high temperature region 20 and a second low temperature region 30 along the axial direction of the rotating shaft 1, the boss 101 is disposed in the first low temperature region 10 of the rotating shaft 1, a first dry gas seal 102 is sleeved on the periphery of the boss 101, the first air inlet 103 is disposed on one side of the boss 101 close to the high temperature region 20, and the first air inlet 103 is used for communicating with a cooling air source. The inlet pressure of the cooling gas is P 0 At a temperature T 0 ，P 0 And T 0 Is an air inlet parameter of turbine shaft seal air. Wherein the cooling gas source extracts cooling gas from the circulation system, the extracted cooling gas having a temperature less than a temperature that can be tolerated by the first dry gas seal 102. The intake pressure P of the cooling gas into the first intake port 103 can be adjusted by the adjusting valve 0 The temperature T of the cooling air entering the first air inlet 103 can be adjusted by an electric heater 0 Thereby realizing control of the pressure P of the cooling air entering through the first air inlet 103 by controlling the air inlet pressure and air inlet temperature of the cooling air source 0 And temperature T 0 . The cold air communicated with the first air inlet 103 is used for cooling the rotor, and the thermal stress of the rotor can be reduced by adjusting the temperature of the cooling air; under the above structure, one side of the first dry gas seal 102 is the air pressure of the first air inlet 103, the other side is the atmospheric pressure, and the axial thrust of the rotor is balanced by the pressure difference on both sides of the first dry gas seal 102, that is, the ventilation can be realized without arranging a balance discOverregulation P 0 To adjust the magnitude of the balancing force. And the turbine rotor arrangement system provided by the embodiment solves the problems in the prior art: the balance piston is arranged at the height Wen Duanshi of the turbine, and the length of the balance piston is necessarily lengthened for controlling the air leakage because of the larger radius of the air leakage, so that the high temperature section of the turbine is too long, and the safety performance of the unit is easily influenced by the too long high temperature section.
Specifically, the two ends of the rotating shaft 1 are respectively provided with a bearing 2, the bearings 2 are used for supporting the rotating shaft 1, and two sides of the rotating shaft 1 located in the first low temperature area 10 are respectively provided with a bearing thrust disc 3. More specifically, the inner diameter of the first dry gas seal 102 is greater than the outer diameter of the bearing thrust disc 3. Because the bearing thrust disk 3 is integral with the rotor and cannot be disassembled, the inner diameter of the first dry gas seal 102 is larger than the outer diameter of the bearing thrust disk 3, so that the first dry gas seal 102 can be smoothly sleeved on the periphery of the boss 101 from one end of the rotating shaft 1, namely, the first dry gas seal 102 is convenient to install and disassemble, and the limitation of a shaft seal leakage system, a cooling gas system, a dry gas seal and a carbocycle seal arrangement can be effectively avoided.
Further, the turbine rotor arrangement system further comprises a turbine rotor 201, a second air inlet 203, a first air outlet 204 and a second air outlet 206, wherein the turbine rotor 201 is arranged in the high temperature region 20 of the rotating shaft 1, the periphery of the turbine rotor 201 is provided with blades 202, the second air inlet 203 is arranged in the high temperature region 20 of the rotating shaft 1, the second air inlet 203 is used for communicating with a high temperature air source so as to drive the blades 202 to drive the rotating shaft 1 to rotate, and the first air outlet 204 is arranged in the high temperature region 20 of the rotating shaft 1 and is positioned between the first air inlet 103 and the second air inlet 203. The second exhaust port 206 is disposed in the high temperature region 20 of the rotating shaft 1, the second exhaust port 206 is communicated with the first exhaust port 204, the second air inlet 203 and the second exhaust port 206 are respectively disposed at two sides of the turbine rotor 201, the second exhaust port 206 is far away from the boss 101 relative to the second air inlet 203, and the second exhaust port 206 is used for collecting the high temperature gas passing through the blades 202. The pressure of the high temperature gas at the second inlet 203 is P 1 At a temperature T 1 ，P 1 And T 1 The exhaust pressures of the first and second exhaust ports 204, 206 are P for turbine intake parameters 2 At a temperature T 2 ，P 2 And T 2 For turbine exhaust parameters, P 1 、T 1 、P 2 And T 2 The value of (2) is determined by the system, and the pressure of the cooling gas extracted from the circulation system by the cooling gas source is greater than the exhaust pressure P 2 . The cooling gas entering from the first air inlet 103 cools the rotating shaft 1 and then is discharged from the first air outlet 204, the high-temperature gas entering from the second air inlet 203 enters into the blades 202 to drive the blades 202 to rotate, then is discharged from the second air outlet 206, meanwhile, a small amount of high-temperature gas leaking from the second air inlet 203 is discharged from the first air outlet 204, and the high-temperature gas flowing to the first air outlet 204 and the high-temperature gas which drives the rotating shaft 1 to complete work by the blades 202 can be discharged together by communicating the second air outlet 206 with the first air outlet 204, so that the normal and orderly work of the rotating shaft 1 is ensured.
In this embodiment, the turbine cylinder includes an outer cylinder and an inner cylinder, the inner cylinder is disposed in the outer cylinder, the rotary shaft 1 is disposed in the inner cylinder, and the first exhaust port 204 and the second exhaust port 206 communicate through a gap between the inner cylinder and the outer cylinder. Of course, in other embodiments, the turbine cylinder may be a single-layer cylinder, and the first exhaust port 204 and the second exhaust port 206 may communicate through a communication pipe or an in-cylinder gap, which is not limited in this embodiment. With the above structure, the axial force generated by the high-temperature air to the rotating shaft 1 can be counteracted to the minimum by the cooling air pressure at the first air inlet 103, so that the axial force applied to the rotating shaft 1 is reduced to the maximum extent, and a balance disc is not required to be arranged.
Preferably, a first seal 104 is arranged between the first air inlet 103 and the first air outlet 204, the first seal 104 is sleeved on the rotating shaft 1, and the first air outlet 204 and the first air inlet 103 can be communicated through a gap between the first seal 104 and the rotating shaft 1. In the process that cooling gas enters from the first air inlet 103 and then is discharged from the first air outlet 204, the cooling gas cools the first seal 104, and the cooling gas leaked from a gap between the first seal 104 and the rotating shaft 1 can further cool the first seal 104, so that the effective sealing of the first seal 104 is ensured, the reduction of air leakage is realized, the span of the rotating shaft 1 is shortened, and the safety of a unit is improved; while the cooling gas rushing in from the first air inlet 103 also prevents the high temperature gas flowing out from the second air inlet 203 from flowing toward the first seal 104.
Preferably, a second seal 205 is arranged between the second air inlet 203 and the first air outlet 204, the second seal 205 is sleeved on the rotating shaft 1, and the second air inlet 203 and the first air outlet 204 can be communicated through a gap between the second seal 205 and the rotating shaft 1. By providing the second seal 205, leakage of the high-temperature gas flowing into the second intake port 203 can be prevented. Even if leakage occurs in the high-temperature gas flowing to the second gas inlet 203, the leaked high-temperature gas can be discharged through the first gas outlet 204. Alternatively, the second seal 205 may be a tooth seal, a labyrinth seal, or a honeycomb seal, preferably a tooth seal.
Further, the second low temperature region 30 of the rotating shaft 1 is provided with a third air inlet 301, the third air inlet 301 is communicated with the first air inlet 103, a third seal 302 is arranged between the second air outlet 206 and the third air inlet 301, the third seal 302 is sleeved on the rotating shaft 1, and the third air inlet 301 and the second air outlet 206 can be communicated with the rotating shaft 1 through a gap between the third seal 302. The cooling gas flows into the third air inlet 301 from the first air inlet 103, the cooling gas flowing into the third air inlet 301 can reduce the temperature of the second low temperature region 30 of the rotating shaft 1, thereby reducing the temperature of the third seal 302, the cooling gas leaked from between the rotating shaft 1 and the third seal 302 can further reduce the temperature of the third seal 302, and the cooling gas entering through the third air inlet 301 can prevent the high temperature gas discharged from the second air outlet 206 from flowing to the third seal 302, thereby ensuring the effective sealing of the third seal 302. In other embodiments, the communication between the third air inlet 301 and the first air inlet 103 may be blocked according to the actual working condition, and cooling air with different temperatures and different pressures may be respectively introduced into the third air inlet 301 and the first air inlet 103 to adapt to the actual working condition, in other embodiments, only the shaft sections corresponding to the first low temperature region 10 and the high temperature region 20 of the rotating shaft 1 may be reserved according to the actual working condition, so as to shorten the span of the rotating shaft 1 and improve the safety of the unit.
Preferably, the first seal 104 and the third seal 302 are carbocycle seals, and because the first seal 104 and the third seal 302 are respectively located in the first low temperature area 10 and the second low temperature area 30, the temperature is lower, so that the carbocycle seals can be arranged therein, and compared with the clearance of 0.5mm of a common seal, the carbocycle seals can enable the clearance to be 0.1mm, but the carbocycle seals have certain requirements on the ambient temperature, and cannot be arranged in the high temperature area 20, so that the arrangement can greatly reduce the length of the boss 101, reduce the length of a high temperature section of a rotor during turbine operation, improve the safety performance of a unit, reduce the air leakage amount of main flow gas to improve the overall operation efficiency, and reduce the length of the high temperature area 20 by about 32%.
In this embodiment, the second low temperature area 30 is further provided with a second dry gas seal 303, the second dry gas seal 303 is sleeved on the rotating shaft 1, the second dry gas seal 303 and the third seal 302 are respectively located at two sides of the third air inlet 301, and the second dry gas seal 303 is far away from the second air outlet 206 relative to the third seal 302 for sealing the inner cylinder. In this embodiment, the inner diameter of the first dry gas seal 102 is greater than the inner diameter of the second dry gas seal 303. Through setting up pivot 1 in the inner cylinder, control cooling gas's temperature and pressure, can guarantee that the temperature and the pressure of the cooling gas that gets into from first air inlet 103 and third air inlet 301 are in the allowable temperature and the allowable pressure range of first dry gas seal 102 and second dry gas seal 303 to guarantee to overlap respectively and locate first dry gas seal 102 and the second dry gas seal 303 of boss 101 and pivot 1 can effectively seal, and then realize the effective seal of post-rotation and inner cylinder, realize the axial force balance of pivot 1 simultaneously. The technical problems in the prior art are solved: when dry gas seals are disposed on both sides of the turbine, such as in a conventional blow-by system, the ambient pressure of the dry gas seals is at a minimum the turbine exhaust pressure, and the dry gas seal system in the supercritical state is susceptible to failure due to frictional heat generation.
The turbine rotor arrangement system provided by the embodiment has the advantages that the air inlet and the air outlet of the cooling air are independent, the air source is stable, the pressure of the air inlet of the cooling air can be adjusted according to the requirement, and therefore the balance thrust can be achieved without arranging a balance disc. The improvement of the turbine rotor arrangement system is beneficial to greatly shortening the whole span of the rotor, is beneficial to the whole structural design of the rotor, improves the safety performance of the whole rotor, and can properly reduce the shaft diameter of the rotor on the basis, thereby further improving the economic performance of the unit.
Note that the above is only a preferred embodiment of the present invention and the technical principle applied. It will be understood by those skilled in the art that the present invention is not limited to the particular embodiments described herein, but is capable of various obvious changes, rearrangements and substitutions as will now become apparent to those skilled in the art without departing from the scope of the invention. Therefore, while the invention has been described in connection with the above embodiments, the invention is not limited to the embodiments, but may be embodied in many other equivalent forms without departing from the spirit or scope of the invention, which is set forth in the following claims.
Claims (8)
1. A turbine rotor arrangement system, comprising:
a turbine cylinder;
the rotating shaft (1) is arranged in the turbine cylinder, a first low-temperature area (10), a high-temperature area (20) and a second low-temperature area (30) are sequentially arranged on the rotating shaft (1) along the axial direction of the rotating shaft (1), bearings (2) are respectively arranged at two ends of the rotating shaft (1) and used for supporting the rotating shaft (1), and a bearing thrust disc (3) is respectively arranged at two sides of the rotating shaft (1) positioned at one side of the first low-temperature area (10);
the boss (101) is arranged in the first low-temperature area (10) of the rotating shaft (1), and a first dry gas seal (102) is sleeved on the periphery of the boss (101);
the first air inlet (103) is arranged on one side, close to the high-temperature area (20), of the boss (101), and the first air inlet (103) is used for communicating a cooling air source;
the second dry gas seal (303) is sleeved on the rotating shaft (1) and located in the second low-temperature area (30), the inner diameter of the first dry gas seal (102) is larger than that of the second dry gas seal (303), and the inner diameter of the first dry gas seal (102) is larger than that of the bearing thrust disc (3).
2. The turbine rotor arrangement system of claim 1, further comprising:
a turbine rotor (201) arranged in the high temperature region (20) of the rotating shaft (1), wherein blades (202) are arranged on the periphery of the turbine rotor (201);
the second air inlet (203) is arranged in the high temperature area (20) of the rotating shaft (1), and the second air inlet (203) is used for communicating with the high Wen Qiyuan so as to drive the blades (202) to drive the rotating shaft (1) to rotate.
3. The turbine rotor arrangement system of claim 2, further comprising:
the first exhaust port (204) is arranged in the high temperature area (20) of the rotating shaft (1), and is positioned between the first air inlet (103) and the second air inlet (203), a first seal (104) is arranged between the first air inlet (103) and the first exhaust port (204), the rotating shaft (1) is sleeved with the first seal (104), and the first exhaust port (204) and the first air inlet (103) can be communicated through a gap between the first seal (104) and the rotating shaft (1).
4. The turbine rotor arrangement system of claim 3, characterized in that a second seal (205) is provided between the second air inlet (203) and the first air outlet (204), the second seal (205) is sleeved on the rotating shaft (1), and the second air inlet (203) and the first air outlet (204) can be communicated through a gap between the second seal (205) and the rotating shaft (1).
5. The turbine rotor arrangement system of claim 3, further comprising:
the second exhaust port (206) is arranged in the high temperature area (20) of the rotating shaft (1), the second exhaust port (206) is communicated with the first exhaust port (204), the second air inlet (203) and the second exhaust port (206) are respectively arranged on two sides of the turbine rotor (201), the second exhaust port (206) is far away from the boss (101) relative to the second air inlet (203), and the second exhaust port (206) is used for collecting high-temperature gas passing through the blades (202).
6. The turbine rotor arrangement system of claim 5, wherein the turbine cylinder comprises an outer cylinder and an inner cylinder, the inner cylinder being disposed within the outer cylinder, the shaft (1) being disposed within the inner cylinder, the first exhaust port (204) and the second exhaust port (206) being in communication through a gap between the inner cylinder and the outer cylinder.
7. The turbine rotor arrangement system of claim 5, wherein the turbine cylinder is a single-layer cylinder, and the first exhaust port (204) and the second exhaust port (206) are in communication via a communication pipe or an in-cylinder gap.
8. The turbine rotor arrangement system of claim 5, further comprising:
the third air inlet (301) is arranged in the second low-temperature area (30) of the rotating shaft (1), the third air inlet (301) is communicated with the first air inlet (103), a third seal (302) is arranged between the second air outlet (206) and the third air inlet (301), the third seal (302) is sleeved on the rotating shaft (1), and the third air inlet (301) and the second air outlet (206) can be communicated with a gap between the rotating shaft (1) through the third seal (302).
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202110990710.3A CN113653539B (en) | 2021-08-26 | 2021-08-26 | Turbine rotor arrangement system |
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| Application Number | Priority Date | Filing Date | Title |
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| CN202110990710.3A CN113653539B (en) | 2021-08-26 | 2021-08-26 | Turbine rotor arrangement system |
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| CN113653539A CN113653539A (en) | 2021-11-16 |
| CN113653539B true CN113653539B (en) | 2023-10-20 |
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| CN112253259A (en) * | 2020-09-16 | 2021-01-22 | 上海发电设备成套设计研究院有限责任公司 | Turbine rotor system |
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| WO2018109810A1 (en) * | 2016-12-12 | 2018-06-21 | 株式会社 東芝 | Turbine and turbine system |
| CN111706405A (en) * | 2020-05-12 | 2020-09-25 | 中国核动力研究设计院 | Dry gas sealing self-cooling structure and method |
| CN112253259A (en) * | 2020-09-16 | 2021-01-22 | 上海发电设备成套设计研究院有限责任公司 | Turbine rotor system |
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