CN113653539A - Turbine rotor arrangement system - Google Patents
Turbine rotor arrangement system Download PDFInfo
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- CN113653539A CN113653539A CN202110990710.3A CN202110990710A CN113653539A CN 113653539 A CN113653539 A CN 113653539A CN 202110990710 A CN202110990710 A CN 202110990710A CN 113653539 A CN113653539 A CN 113653539A
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- air inlet
- rotating shaft
- seal
- turbine rotor
- turbine
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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
Abstract
The invention relates to the technical field of turbine rotating 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 region 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 is used for being communicated with a cooling air source. The turbine rotor arrangement system does not need to arrange a balance disc, through the thrust generated by the front-back pressure difference of the boss provided with the dry gas seal, the thrust balance through-flow and the axial thrust generated by the seal teeth are balanced, the whole operation efficiency of the unit is high, the whole span of the rotor is small, and the safety performance and the economic performance of the unit are good.
Description
Technical Field
The invention relates to the technical field of turbine rotating machinery, in particular to a turbine rotor arrangement system.
Background
The supercritical carbon dioxide turbine rotor is a rotor suitable for power generation equipment, most of the existing balance pistons are arranged at a high-temperature section of a turbine, and the length of the balance piston is long to control air leakage because the air leakage radius is large, so that the high-temperature section of the turbine is too long, and the safety performance of a unit is low. And a few balance pistons are arranged at the low-temperature section, but the existing rotor arrangement scheme of the steam cycle has larger length and diameter of a balance disc, so that the whole span of the rotor is larger, the whole structural design of a unit is not facilitated, and the safety performance and the economic performance of the unit are 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 purpose, the invention adopts the following technical scheme:
a turbine rotor arrangement 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 on the rotating shaft along the axial direction of the rotating shaft;
the boss is arranged in the first low-temperature region 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 used for being communicated with a cooling air source.
As a preferable embodiment of the turbine rotor arrangement system, the turbine rotor arrangement system further includes:
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 used for being communicated with a high-temperature air source so as to drive the blades to drive the rotating shaft to rotate.
As a preferable embodiment of the turbine rotor arrangement system, the turbine rotor arrangement system further includes:
first exhaust port, set up in the pivot the high temperature region, and be located first air inlet with between the second air inlet, first air inlet with be provided with first sealed between the first exhaust port, first sealed cover is located the pivot, first exhaust port with first air inlet can pass through first sealed with clearance intercommunication between the pivot.
As a preferred scheme of the turbine rotor arrangement system, a second seal is arranged between the second air inlet and the first exhaust port, the second seal is sleeved on the rotating shaft, and the second air inlet and the first exhaust port can be communicated through a gap between the second seal and the rotating shaft.
As a preferable embodiment of the turbine rotor arrangement system, the turbine rotor arrangement system further includes:
the second gas vent, set up in the pivot the high temperature area, the second gas vent with first gas vent intercommunication, the second air inlet with the second gas vent set up respectively in turbine rotor's both sides, the second gas vent for the second air inlet is kept away from the boss, the second gas vent is used for collecting the process the high-temperature gas of blade.
As a preferable aspect of the turbine rotor arrangement system, the turbine cylinder includes an outer cylinder and an inner cylinder, the inner cylinder is disposed in the outer cylinder, the rotating shaft is disposed 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 scheme 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 a gap in the cylinder.
As a preferable embodiment of the turbine rotor arrangement system, the turbine rotor arrangement system further includes:
the third air inlet, set up in the pivot the second low temperature zone, the third air inlet communicate in first air inlet, the second gas vent with it is sealed to be provided with the third between the third air inlet, the sealed cover of third is located the pivot, the third air inlet with the second gas vent can pass through the third seal with clearance intercommunication between the pivot.
As a preferred scheme of the turbine rotor arrangement system, two ends of the rotating shaft are respectively provided with a bearing for supporting the rotating shaft, and two sides of the rotating shaft, which are located on one side of the first low-temperature region, are respectively provided with a bearing thrust disc.
As a preferable embodiment of the turbine rotor arrangement system, the turbine rotor arrangement system further includes:
and the second dry gas seal is sleeved on the rotating shaft and positioned in the second low-temperature region, 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 invention has the beneficial effects that:
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, the boss with a first dry air seal is sleeved on the periphery of the first low-temperature region, the first air inlet is arranged on one side of the boss close to the high-temperature region, the first air inlet is communicated with a cold air source to cool a rotor, and the thermal stress of the rotor can be reduced by adjusting the temperature of the cold air; under the structure, one side of the first dry gas seal is the air pressure of the first air inlet, the other side of the first dry gas seal is the atmospheric pressure, the axial thrust of the rotor is balanced through the pressure difference of the two sides of the first dry gas seal, namely, a balance disc is not needed to be arranged, and the balance force can be adjusted by adjusting the air pressure of the cooling air introduced into the first air inlet; and through the arrangement, the whole span of the rotor is favorably shortened, the whole structure design of the rotor is favorably realized, and the safety and the economic performance of the unit are improved.
Drawings
In order to more clearly illustrate the technical solutions in the embodiments of the present invention, the drawings used in the description of the embodiments of the present invention will be briefly described below, and it is obvious that the drawings in the following description are only some embodiments of the present invention, and for those skilled in the art, other drawings can be obtained according to the contents of the embodiments of the present invention and the drawings without creative efforts.
FIG. 1 is a schematic half-section view of a turbine rotor layout system according to 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. sealing the first dry gas; 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. third sealing; 303. and sealing the second dry gas.
Detailed Description
The present invention will be described in further detail with reference to the accompanying drawings and examples. It is to be understood that the specific embodiments described herein are merely illustrative of the invention and are not limiting of the invention. It should be further noted that, for the convenience of description, only some of the structures related to the present invention are shown in the drawings, not all of the structures.
In the description of the present invention, unless expressly stated or limited otherwise, the terms "connected," "connected," and "fixed" are to be construed broadly, e.g., as meaning permanently connected, removably connected, or integral to one another; can be mechanically or electrically connected; either directly or indirectly through intervening media, either internally or in any other relationship. The specific meanings of the above terms in the present invention can be understood in specific cases to those skilled in the art.
In the present invention, unless otherwise expressly stated or limited, "above" or "below" a first feature means that the first and second features are in direct contact, or that the first and second features are not in direct contact but are in contact with each other via another feature therebetween. Also, the first feature being "on," "above" and "over" the second feature includes the first feature being directly on and obliquely above the second feature, or merely indicating that the first feature is at a higher level than the second feature. A first feature being "under," "below," and "beneath" a second feature includes the first feature being directly under and obliquely below the second feature, or simply meaning that the first feature is at a lesser elevation than the second feature.
In the description of the present embodiment, the terms "upper", "lower", "left", "right", and the like are used based on the orientations and positional relationships shown in the drawings only for convenience of description and simplification of operation, and do not indicate or imply that the referred device or element must have a specific orientation, be configured and operated in a specific orientation, and thus, should not be construed as limiting the present invention. Furthermore, the terms "first" and "second" are used only for descriptive purposes and are not intended to have a special meaning.
As shown in fig. 1, the present embodiment provides a turbine rotor arrangement system, the turbine rotor arrangement system 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 an 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 air seal 102 is sleeved on an outer periphery of the boss 101, the first air inlet 103 is disposed on a side of the boss 101 close to the high-temperature region 20, and the first air inlet 103 is used for communicating with a cold air sourceBut the gas source. The inlet pressure of the cooling gas is P0At a temperature of T0，P0And T0And the air inlet parameters of the turbine shaft seal gas are obtained. Wherein the cooling gas source extracts cooling gas from the circulation system, the temperature of the extracted cooling gas being less than the temperature that the first dry gas seal 102 can withstand. The inlet pressure P of the cooling air entering the first inlet 103 can be adjusted by adjusting the valve0The temperature T of the cooling air entering the first air inlet 103 can be adjusted by the electric heater0Thereby realizing the control of the pressure P of the cooling air entering the first air inlet 103 by controlling the air inlet pressure and the air inlet temperature of the cooling air source0And temperature T0. 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 cold air; under the 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, the axial thrust of the rotor is balanced through the pressure difference on the two sides of the first dry gas seal 102, namely, a balance disc is not needed to be arranged, and the adjustment of P can be realized0The magnitude of the balance force is adjusted. And the turbine rotor arrangement system that this embodiment provided has solved the problem among the prior art: when the balance piston is arranged at the high-temperature section of the turbine, the length of the balance piston is inevitably lengthened for controlling the air leakage because of the larger radius of the air leakage, which causes the high-temperature section of the turbine to be too long, and the safety performance of the unit is easily affected by the too long high-temperature section.
Specifically, 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 region 10 are respectively provided with a bearing thrust disc 3. More specifically, the inner diameter of the first dry gas seal 102 is larger than the outer diameter of the bearing thrust disk 3. Because bearing thrust dish 3 is integrative with the rotor, unable dismantlement, consequently, the internal diameter of first dry gas seal 102 is greater than the external diameter of bearing thrust dish 3 for first dry gas seal 102 can be established smoothly in boss 101 periphery from the one end of pivot 1, even make first dry gas seal 102 be convenient for install and dismantle, can effectively avoid bearing seal gas leakage system, cooling gas system, dry gas seal and the sealed limitation of arranging of carbocycle.
Further, theThe 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 area 20 of the rotating shaft 1, 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, the second air inlet 203 is used for communicating a high-temperature air source 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 area 20 of the rotating shaft 1 and is located 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 disposed on two sides of the turbine rotor 201, respectively, 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 vane 202. The pressure of the high temperature gas at the second inlet 203 is P1At a temperature of T1，P1And T1The exhaust pressure at the first exhaust port 204 and the second exhaust port 206 is P for turbine inlet parameters2At a temperature of T2，P2And T2For turbine exhaust parameters, P1、T1、P2And T2Is determined by the system, the pressure of the cooling gas extracted by the cooling gas source from the circulation system being greater than the discharge pressure P2. The cooling air that gets into from first air inlet 103 is discharged from first exhaust port 204 after cooling to pivot 1, the high temperature gas that gets into from second air inlet 203 gets into in blade 202 drive blade 202 and rotates, then discharge from second exhaust port 206, a little high temperature gas that leaks from second air inlet 203 simultaneously is discharged by first exhaust port 204, and through communicating second exhaust port 206 in first exhaust port 204, can discharge the high temperature gas that flows to first exhaust port 204 and the high temperature gas that blade 202 drove pivot 1 and accomplish work together, guarantee pivot 1 normal orderly work.
In this embodiment, the turbine cylinder includes an outer cylinder and an inner cylinder, the inner cylinder is disposed in the outer cylinder, the rotating shaft 1 is disposed in the inner cylinder, and the first exhaust port 204 and the second exhaust port 206 are communicated 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 be connected by a connection pipe or an inter-cylinder gap, which is not limited in this embodiment. Under the above structure, the axial force generated by the high-temperature gas on the rotating shaft 1 can be offset to the minimum by the pressure of the cooling gas at the first air inlet 103, so that the axial force applied to the rotating shaft 1 is reduced to the maximum, and a balance disc does not need to be arranged.
Preferably, 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. In the process that cooling gas enters from the first air inlet 103 and is then discharged from the first exhaust port 204, the cooling gas cools the first seal 104, and the cooling gas leaking from the 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; meanwhile, the cooling air rushing in from the first air inlet 103 can also prevent the high-temperature air flowing out from the second air inlet 203 from flowing to 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, the high-temperature gas flowing into the second inlet port 203 can be prevented from leaking. Even if the high-temperature gas flowing to the second gas inlet 203 leaks, the leaked high-temperature gas can be discharged through the first gas outlet 204. Alternatively, the second seal 205 may employ a tooth seal, a labyrinth seal or a honeycomb seal, preferably a tooth seal.
Furthermore, 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 rotating shaft 1 is sleeved with the third seal 302, and the third air inlet 301 and the second air outlet 206 can be communicated through a gap between the third seal 302 and the rotating shaft 1. The cooling air flows into the third air inlet 301 from the first air inlet 103, the cooling air flowing into the third air inlet 301 can reduce the temperature of the second low-temperature region 30 of the rotating shaft 1, so that the temperature of the third seal 302 is reduced, the cooling air leaking between the rotating shaft 1 and the third seal 302 can further reduce the temperature of the third seal 302, and the cooling air 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, so that the effective sealing of the third seal 302 is ensured. In other embodiments, the communication between the third air inlet 301 and the first air inlet 103 may be blocked according to actual conditions, 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 conditions, or 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 conditions, 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 carbon ring seals, and since the first seal 104 and the third seal 302 are respectively located in the first low-temperature region 10 and the second low-temperature region 30, the temperature is low, so that the carbon ring seals can be arranged therein, and compared with the gap of a common seal, which is 0.5mm, the carbon ring seals can make the gap 0.1mm, but the carbon ring seals have certain requirements on the ambient temperature and cannot be arranged in the high-temperature region 20, so that the arrangement can greatly reduce the length of the boss 101, reduce the length of the high-temperature region of the rotor during the operation of the turbine, improve the safety performance of the unit, and reduce the air leakage amount of the main stream gas to improve the overall operation efficiency, and reduce the length of the high-temperature region 20 by about 32%.
In this embodiment, the second low temperature region 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 away from the second air outlet 206 relative to the third seal 302 and is used for sealing the inner cylinder. In this embodiment, the inner diameter of the first dry gas seal 102 is larger than the inner diameter of the second dry gas seal 303. Through setting up pivot 1 in the inner casing, control the temperature and the pressure of cooling gas, 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 within the temperature and the pressure range of allowability of first dry gas seal 102 and second dry gas seal 303 to guarantee to overlap respectively and locate boss 101 and pivot 1 first dry gas seal 102 and second dry gas seal 303 and can effectively seal, and then realize changeing the back and effectively seal of inner casing, realize the axial force balance of pivot 1 simultaneously. The technical problems in the prior art are solved as follows: when dry gas seals are arranged on two sides of a turbine, if a conventional leakage system is adopted, the lowest environmental pressure of the dry gas seals is the exhaust pressure of the turbine, and the dry gas seal system in a supercritical state is easy to fail due to frictional heat.
The turbine rotor arrangement system that this embodiment provided's cooling gas's admit air and exhaust independently, and the air supply is stable, can adjust the pressure that the cooling gas admitted air as required to need not to arrange the balance disk and can realize balanced thrust. And the improvement of the turbine rotor arrangement system is favorable for greatly shortening the overall span of the rotor, the overall structural design of the rotor is favorable for improving the safety performance of the overall rotor, the shaft diameter of the rotor can be properly reduced on the basis, and the economic performance of the unit is further improved.
It is to be noted that the foregoing is only illustrative of the preferred embodiments of the present invention and the technical principles employed. 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, although the present invention has been described in greater detail by the above embodiments, the present invention is not limited to the above embodiments, and may include other equivalent embodiments without departing from the spirit of the present invention, and the scope of the present invention is determined by the scope of the appended claims.
Claims (10)
1. A turbine rotor arrangement, comprising:
a turbine cylinder;
the turbine cylinder is characterized by comprising a rotating shaft (1), wherein the rotating shaft (1) is arranged in the turbine cylinder, and 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);
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 formed in one side, close to the high-temperature area (20), of the boss (101), and the first air inlet (103) is used for being communicated with a cooling air source.
2. The turbine rotor arrangement of claim 1, further comprising:
the turbine rotor (201) is arranged in the high-temperature area (20) of the rotating shaft (1), and 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 being communicated with a high-temperature air source to drive the blade (202) to drive the rotating shaft (1) to rotate.
3. The turbine rotor arrangement of claim 2, further comprising:
first exhaust port (204), set up in pivot (1) high temperature zone (20), and be located first air inlet (103) with between second air inlet (203), first air inlet (103) with be provided with first sealed (104) between first exhaust port (204), first sealed (104) cover is located pivot (1), first exhaust port (204) with first air inlet (103) can pass through first sealed (104) with clearance intercommunication between pivot (1).
4. The turbine rotor arrangement of claim 3, characterized in that a second seal (205) is provided between the second inlet (203) and the first outlet (204), the second seal (205) being sleeved to the shaft (1), the second inlet (203) and the first outlet (204) being communicable through a gap between the second seal (205) and the shaft (1).
5. The turbine rotor arrangement of claim 3, further comprising:
second gas vent (206), set up in pivot (1) high temperature zone (20), second gas vent (206) with first gas vent (204) intercommunication, second air inlet (203) with second gas vent (206) set up respectively in the both sides of turbine rotor (201), second gas vent (206) for second air inlet (203) are kept away from boss (101), second gas vent (206) are used for collecting the process the high-temperature gas of blade (202).
6. The turbine rotor arrangement according to claim 5, wherein the turbine cylinder comprises an outer cylinder and an inner cylinder, the inner cylinder being disposed within the outer cylinder, the rotary shaft (1) being disposed within the inner cylinder, the first exhaust port (204) and the second exhaust port (206) communicating through a gap between the inner cylinder and the outer cylinder.
7. The turbine rotor arrangement according to claim 5, wherein the turbine cylinder is a single cylinder, and the first exhaust port (204) and the second exhaust port (206) are communicated by a communicating pipe or an in-cylinder gap.
8. The turbine rotor arrangement of claim 5, further comprising:
third air inlet (301), set up in pivot (1) second low temperature zone (30), third air inlet (301) communicate in first air inlet (103), second gas vent (206) with be provided with the third between third air inlet (301) and seal (302), the third seals (302) cover and locates pivot (1), third air inlet (301) with second gas vent (206) can pass through the third seal (302) with clearance intercommunication between pivot (1).
9. The turbine rotor arrangement system according to claim 1, characterized in that bearings (2) are provided at both ends of the rotating shaft (1) for supporting the rotating shaft (1), and a bearing thrust disk (3) is provided at both sides of the rotating shaft (1) at one side of the first low temperature zone (10).
10. The turbine rotor arrangement of claim 9, further comprising:
and the second dry gas seal (303) is sleeved on the rotating shaft (1) and is positioned in the second low-temperature region (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).
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| CN202110990710.3A CN113653539B (en) | 2021-08-26 | 2021-08-26 | Turbine rotor arrangement system |
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| CN202110990710.3A CN113653539B (en) | 2021-08-26 | 2021-08-26 | Turbine rotor arrangement system |
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| CN113653539A true CN113653539A (en) | 2021-11-16 |
| CN113653539B CN113653539B (en) | 2023-10-20 |
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| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN114508393A (en) * | 2021-12-27 | 2022-05-17 | 东方电气集团东方汽轮机有限公司 | Cylinder with zero axial thrust during load shedding, and primary and secondary reheating steam turbine |
| CN115539160A (en) * | 2022-12-01 | 2022-12-30 | 中国核动力研究设计院 | Turbine system under supercritical carbon dioxide environment |
Citations (3)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| 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 |
-
2021
- 2021-08-26 CN CN202110990710.3A patent/CN113653539B/en active Active
Patent Citations (3)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| 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 |
Cited By (4)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN114508393A (en) * | 2021-12-27 | 2022-05-17 | 东方电气集团东方汽轮机有限公司 | Cylinder with zero axial thrust during load shedding, and primary and secondary reheating steam turbine |
| CN114508393B (en) * | 2021-12-27 | 2023-07-18 | 东方电气集团东方汽轮机有限公司 | Cylinder with zero axial thrust during load shedding, primary and secondary reheat steam turbine |
| CN115539160A (en) * | 2022-12-01 | 2022-12-30 | 中国核动力研究设计院 | Turbine system under supercritical carbon dioxide environment |
| CN115539160B (en) * | 2022-12-01 | 2023-03-10 | 中国核动力研究设计院 | Turbine system under supercritical carbon dioxide environment |
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| CN113653539B (en) | 2023-10-20 |
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