CN112253259A - Turbine rotor system - Google Patents
Turbine rotor system Download PDFInfo
- Publication number
- CN112253259A CN112253259A CN202010974430.9A CN202010974430A CN112253259A CN 112253259 A CN112253259 A CN 112253259A CN 202010974430 A CN202010974430 A CN 202010974430A CN 112253259 A CN112253259 A CN 112253259A
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- Prior art keywords
- rotating shaft
- seal
- air inlet
- exhaust port
- turbine rotor
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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
- 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
- F01D5/027—Arrangements for balancing
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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
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- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F01—MACHINES OR ENGINES IN GENERAL; ENGINE PLANTS IN GENERAL; STEAM ENGINES
- F01D—NON-POSITIVE DISPLACEMENT MACHINES OR ENGINES, e.g. STEAM TURBINES
- F01D5/00—Blades; Blade-carrying members; Heating, heat-insulating, cooling or antivibration means on the blades or the members
- F01D5/02—Blade-carrying members, e.g. rotors
- F01D5/08—Heating, heat-insulating or cooling means
Abstract
The invention belongs to the technical field of turbine rotating machinery, and discloses a turbine rotor system which comprises a rotating shaft, wherein 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 balance disc is arranged in a first low-temperature area of the rotating shaft, and a first seal is sleeved on the balance disc; the first air inlet is arranged in a first low-temperature region of the rotating shaft and is used for being communicated with a cooling air source for cooling so as to realize first sealing; the turbine rotor is arranged in a 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 a high-temperature area of the rotating shaft and used for providing high-temperature gas to drive the blades to drive the rotating shaft to rotate. The turbine rotor system can reduce the air leakage of the balance disc, shorten the length of the balance disc, further shorten the span of the rotating shaft and improve the safety of a unit.
Description
Technical Field
The invention relates to the technical field of turbine rotating machinery, in particular to a turbine rotor system.
Background
Supercritical carbon dioxide turbine rotor is the rotor that is applicable to power generation facility, the high temperature section of pivot is all located to the balance disk and the turbine rotor of present pivot, the pivot is at the during operation, along with operating temperature's increase, the air leakage volume of balance disk can increase by a wide margin, can lead to the efficiency of system to reduce by a wide margin, the reducible air leakage volume of length of increase balance disk, but can make rotor high temperature section too long, lead to the structural design difficulty of rotor, can influence rotor unit's security performance simultaneously.
Disclosure of Invention
The invention aims to provide a turbine rotor system, which aims to solve the problems of large air leakage of a balance disc, long length of the balance disc and poor unit safety of the conventional turbine rotor system.
In order to achieve the purpose, the invention adopts the following technical scheme:
a turbine rotor system comprising:
the rotating shaft is provided with a first low-temperature zone, a high-temperature zone and a second low-temperature zone in sequence along the axial direction of the rotating shaft;
the balance disc is arranged in the first low-temperature area of the rotating shaft, and a first seal is sleeved on the balance disc;
the first air inlet is arranged in the first low-temperature region of the rotating shaft and is used for being communicated with a cooling air source to cool the first seal;
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 on the rotating shaft and used for providing high-temperature gas for driving the blades to drive the rotating shaft to rotate.
Preferably, the first low temperature region of the rotating shaft further has a first exhaust port, the first air inlet and the first exhaust port are respectively located at both sides of the first seal, the first exhaust port is far away from the turbine rotor relative to the first air inlet, and the first exhaust port and the first air inlet may communicate through a gap between the rotating shaft and the first seal.
Preferably, the high-temperature region of the rotating shaft is provided with a second exhaust port, the second air inlet and the second exhaust port are respectively located on two sides of the turbine rotor, the second exhaust port is far away from the balance disc relative to the second air inlet, and the second exhaust port is used for collecting high-temperature gas passing through the blades.
Preferably, the second low-temperature zone of the rotating shaft is provided with a third air inlet, a third air outlet and a second seal, the second seal is sleeved on the rotating shaft and is located between the third air inlet and the third air outlet, the third air inlet is close to the second air outlet relative to the third air outlet, the third air inlet is communicated with the first air inlet, the third air outlet is communicated with the first air outlet, and the third air outlet and the third air inlet can be communicated through a gap between the rotating shaft and the second seal.
Preferably, the rotating shaft is further provided with a fourth exhaust port, the fourth exhaust port is arranged between the first air inlet and the second air inlet, a third seal is arranged between the fourth exhaust port and the second air inlet, the third seal is sleeved on the rotating shaft, and the fourth exhaust port and the second air inlet can be communicated through a gap between the rotating shaft and the third seal.
Preferably, a fourth seal is arranged between the fourth exhaust port and the first air inlet, the rotating shaft is sleeved with the fourth seal, and the fourth exhaust port and the first air inlet can be communicated through a gap between the rotating shaft and the fourth seal.
Preferably, a fifth seal is arranged between the third air inlet and the second air outlet, the fifth seal is sleeved on the rotating shaft, and the third air inlet and the second air outlet can be communicated through a gap between the rotating shaft and the fifth seal.
Preferably, the turbine rotor system further comprises a bearing cylinder, the rotating shaft is arranged in the bearing cylinder, the rotating shaft is provided with a first dry gas seal in the first low-temperature area, the rotating shaft is provided with a second dry gas seal in the second low-temperature area, the first dry gas seal and the second dry gas seal are all sleeved on the rotating shaft and used for sealing the bearing cylinder, the first dry gas seal is close to the first exhaust port relative to the first air inlet, and the second dry gas seal is close to the third exhaust port relative to the third air inlet.
Preferably, the intake pressure of the first intake port is smaller than the intake pressure of the second intake port.
Preferably, the first seal and the second seal are both carbon ring seals.
The invention has the beneficial effects that:
the invention relates to a turbine rotor system, which comprises a rotating shaft, wherein 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 balance disc is arranged in a first low-temperature area of the rotating shaft, and a first seal is sleeved on the balance disc; the first air inlet is arranged in a first low-temperature region of the rotating shaft and is used for communicating a cooling air source to cool the first seal; the turbine rotor is arranged in a 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 a high-temperature area of the rotating shaft and used for providing high-temperature gas to drive the blades to drive the rotating shaft to rotate. In the prior art, the balance disc is arranged in a high-temperature area, the air leakage of the balance disc is increased along with the continuous increase of the operating temperature of high-temperature gas, and the air leakage needs to be reduced by increasing the length of the balance disc. According to the turbine rotor system, the balance disc is arranged in the first low-temperature region, the first seal is sleeved on the balance disc, and the temperature of the first seal is reduced by controlling the temperature of cooling air flowing into the first air inlet from the cooling air source, so that the first seal is ensured to be effectively sealed, the air leakage of the balance disc is reduced, the length of the balance disc is shortened, the span of a rotating shaft is further shortened, and the safety of a unit is improved.
Drawings
FIG. 1 is a schematic half-section view of a turbine rotor system of the present invention.
In the figure:
1-a rotating shaft;
11-a first low temperature zone; 111-a balance disc; 1111-a first seal; 112-a first air inlet; 113-a first exhaust port; 114-first dry gas seal; 115-fourth seal;
12-high temperature zone; 121-a turbine rotor; 122-blades; 123-a second air inlet; 124-a second exhaust port; 125-a fourth vent; 126-third seal;
13-a second low temperature zone; 131-a third air inlet; 132-a third exhaust port; 133-a second seal; 134-second dry gas seal; 135-fifth seal.
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", "right", etc. are used in an orientation or positional relationship based on that shown in the drawings only for convenience of description and simplicity of operation, and do not indicate or imply that the device or element referred to must have a particular orientation, be constructed and operated in a particular 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.
The invention provides a turbine rotor system, as shown in fig. 1, the turbine rotor system comprises a rotating shaft 1, a first low-temperature zone 11, a high-temperature zone 12 and a second low-temperature zone 13 are sequentially arranged along the axial direction of the rotating shaft 1; the balance disc 111 is arranged in the first low-temperature zone 11 of the rotating shaft 1, and a first seal 1111 is sleeved on the balance disc 111; the first air inlet 112 is arranged in the first low-temperature region 11 of the rotating shaft 1, and the first air inlet 112 is used for communicating with a cooling air source to cool the first seal 1111; the turbine rotor 121 is arranged in the high-temperature region 12 of the rotating shaft 1, and blades 122 are arranged on the periphery of the turbine rotor 121; the second gas inlet 123 is disposed in the high temperature region 12 of the rotating shaft 1, and the second gas inlet 123 is used for providing high temperature gas to drive the blades 122 to drive the rotating shaft 1 to rotate. According to the turbine rotor system, the balance disc 111 is arranged in the first low-temperature region 11, the first seal 1111 is sleeved on the balance disc 111, the temperature of the first seal 1111 is reduced by controlling the temperature of cooling air flowing into the first air inlet 112 from a cooling air source, so that the first seal 1111 is effectively sealed, the air leakage amount of the balance disc 111 is reduced, the length of the balance disc 111 is shortened, the span of the rotating shaft 1 is further shortened, and the safety of a unit is improved.
Alternatively, as shown in fig. 1, the first low-temperature region 11 of the rotating shaft 1 further has a first exhaust port 113, the first intake port 112 and the first exhaust port 113 are respectively located on both sides of the first seal 1111, the first exhaust port 113 is located away from the turbine rotor 121 with respect to the first intake port 112, and the first exhaust port 113 and the first intake port 112 may communicate through a gap between the rotating shaft 1 and the first seal 1111. The first air inlet 112 and the first air outlet 113 are respectively positioned at both sides of the first seal 1111, the cooling air flowing in from the first air inlet 112 can reduce the temperature of the first low temperature zone 11 of the rotating shaft 1, and further reduce the temperature of the first seal 1111, and the cooling air leaking from between the rotating shaft 1 and the first seal 1111 can further reduce the temperature of the first seal 1111; meanwhile, the cooling air charged through the first air inlet 112 can prevent the high-temperature air flowing out of the second air inlet 123 from flowing toward the first seal 1111. The cooling air is provided by a cooling air source, the cooling air source is an outlet of a compressor or a pump, the air inlet pressure of the cooling air entering the first air inlet 112 can be adjusted through a regulating valve, the air inlet temperature of the cooling air entering the first air inlet 112 can be adjusted through an electric heater, and therefore the temperature and the pressure of the cooling air entering the first air inlet 112 can be controlled by controlling the air inlet pressure and the air inlet temperature of the cooling air source.
Alternatively, as shown in fig. 1, the high temperature region 12 of the rotating shaft 1 is further provided with a second exhaust port 124, the second inlet port 123 and the second exhaust port 124 are respectively located at two sides of the turbine rotor 121, the second exhaust port 124 is far away from the balance disk 111 relative to the second inlet port 123, and the second exhaust port 124 is used for collecting high temperature gas passing through the blades 122. Through the second exhaust port 124, the high-temperature gas flowing in from the second gas inlet 123 can drive the blades 122 to drive the rotating shaft 1 to rotate, and finally can be exhausted through the second exhaust port 124, and the rotating shaft 1 can be ensured to be in a working state all the time by the process of circulation; the second exhaust port 124 is far from the balance disk 111 relative to the second intake port 123, the first exhaust port 113 is far from the turbine rotor 121 relative to the first intake port 112, so that the force exerted by the cooling gas on the balance disk 111 is leftward (in the OB direction in fig. 1), the force exerted by the high-temperature gas on the turbine rotor 121 is rightward (in the OA direction in fig. 1), and the leftward force exerted by the balance disk 111 on the rotating shaft 1 can counteract the rightward force exerted by the turbine rotor 121 on the rotating shaft 1 to the minimum, so that the axial force exerted on the rotating shaft 1 is minimized.
Optionally, as shown in fig. 1, the second low temperature zone 13 of the rotating shaft 1 is provided with a third air inlet 131, a third air outlet 132 and a second seal 133, the second seal 133 is sleeved on the rotating shaft 1 and located between the third air inlet 131 and the third air outlet 132, the third air inlet 131 is close to the second air outlet 124 relative to the third air outlet 132, the third air inlet 131 is communicated with the first air inlet 112, the third air outlet 132 is communicated with the first air outlet 113, and the third air outlet 132 and the third air inlet 131 can be communicated through a gap between the rotating shaft 1 and the second seal 133. The third air inlet 131 is communicated with the first air inlet 112, the cooling air of the cooling air source can flow into the third air inlet 131 from the first air inlet 112, the cooling air flowing into the third air inlet 131 can reduce the temperature of the second low-temperature region 13 of the rotating shaft 1, and further reduce the temperature of the second seal 133, the cooling air leaking between the rotating shaft 1 and the second seal 133 can further reduce the temperature of the second seal 133, and the cooling air filled through the third air inlet 131 can prevent the high-temperature air discharged from the second air outlet 124 from flowing to the second seal 133. In other embodiments, the communication between the third air inlet 131 and the first air inlet 112 may also be blocked according to actual conditions, and cooling air with different temperatures and different pressures may be respectively introduced into the third air inlet 131 and the first air inlet 112 to adapt to the actual conditions. In other embodiments, only the shaft sections corresponding to the first low-temperature zone 11 and the high-temperature zone 12 of the rotating shaft 1 may be reserved according to actual conditions to shorten the span of the rotating shaft 1, thereby improving the safety of the unit.
Optionally, as shown in fig. 1, the first seal 1111 and the second seal 133 are both carbon ring seals. Compared with other seals, the carbon ring seal has the advantages that the sealing gap can be reduced to 0.01mm, but the carbon seal has requirements on the ambient temperature, if the balance disc 111 is arranged in the high-temperature area 12, the working temperature of the high-temperature area 12 does not meet the allowable temperature for the balance disc 111 to adopt the carbon ring seal, the air leakage amount of the balance disc 111 is large, and therefore the balance disc 111 is arranged in the first low-temperature area 11, the sealing performance can be guaranteed, the use requirements can be met, the length of the balance disc 111 can be shortened, and the span of the rotating shaft 1 can be shortened.
Optionally, as shown in fig. 1, the high temperature region 12 of the rotating shaft 1 is further provided with a fourth exhaust port 125, the fourth exhaust port 125 is disposed between the first air inlet 112 and the second air inlet 123, a third seal 126 is disposed between the fourth exhaust port 125 and the second air inlet 123, the third seal 126 is sleeved on the rotating shaft 1, and the fourth exhaust port 125 and the second air inlet 123 may be communicated through a gap between the rotating shaft 1 and the third seal 126. By providing the third seal 126 between the fourth exhaust port 125 and the second inlet port 123, the leakage of the high-temperature gas flowing into the second inlet port 123 can be prevented, and even if the leakage of the high-temperature gas flowing into the second inlet port 123 occurs, the leaked high-temperature gas can be discharged through the fourth exhaust port 125; the fourth exhaust port 125 is connected to the second exhaust port 124, so that high-temperature gas leaked from the gap between the rotating shaft 1 and the third seal 126 and high-temperature gas generated by the blade 122 driving the rotating shaft 1 to complete work can be exhausted together, thereby ensuring normal and orderly work of the rotating shaft 1.
Alternatively, as shown in fig. 1, a fourth seal 115 is disposed between the fourth exhaust port 125 and the first inlet port 112, the rotating shaft 1 is sleeved with the fourth seal 115, and the fourth exhaust port 125 and the second inlet port 123 may be communicated through a gap between the rotating shaft 1 and the fourth seal 115. By providing the fourth seal 115 between the fourth exhaust port 125 and the first inlet port 112, efficient exhaust of high-temperature gas leaking from the second inlet port 123 from the fourth exhaust port 125 can be ensured.
Alternatively, as shown in fig. 1, a fifth seal 135 is disposed between the third air inlet 131 and the second air outlet 124, the fifth seal 135 is sleeved on the rotating shaft 1, and the third air inlet 131 and the second air outlet 124 can be communicated through a gap between the rotating shaft 1 and the fifth seal 135. By providing the fifth seal 135 between the third air inlet 131 and the second air outlet 124, leakage of the cooling air flowing in from the third air inlet 131 can be prevented by the fifth seal 135. Third seal 126, fourth seal 115, and fifth seal 135 may be tooth seals, labyrinth seals, or honeycomb seals, with tooth seals being preferred.
Optionally, as shown in fig. 1, the turbine rotor system further includes a bearing cylinder, the rotating shaft 1 is disposed in the bearing cylinder, the first low-temperature region 11 of the rotating shaft 1 is provided with a first dry gas seal 114, the second low-temperature region 13 of the rotating shaft 1 is provided with a second dry gas seal 134, both the first dry gas seal 114 and the second dry gas seal 134 are sleeved on the rotating shaft 1 and are used for sealing the bearing cylinder, the first dry gas seal 114 is close to the first exhaust port 113 relative to the first air inlet 112, and the second dry gas seal 134 is close to the third exhaust port 132 relative to the third air inlet 131. Through locating pivot 1 in holding the jar, control the temperature and the pressure of cooling air supply, can guarantee to follow the temperature and the pressure of the cooling gas that first gas vent 113 and third gas vent 132 discharged into the jar of holding within the allowable temperature and the allowable pressure range of first dry gas seal 114 and second dry gas seal 134 to guarantee that the first dry gas seal 114 and the second dry gas seal 134 of cover dress pivot 1 can effectively seal, and then realize pivot 1 and the effective seal of holding the jar.
Alternatively, the intake pressure of the first intake port 112 is smaller than the intake pressure of the second intake port 123. The intake pressure of the first intake port 112 is controlled by controlling the intake pressure of the cooling air source, the first intake port 112 and the first exhaust port 113 communicate through the gap between the rotary shaft 1 and the first seal 1111, the third intake port 131 and the third exhaust port 132 communicate through the gap between the rotary shaft 1 and the second seal 133, the cooling air leaked from the first intake port 112 can be discharged from the first exhaust port 113 to the socket, the cooling air leaked from the third intake port 131 can be discharged from the third exhaust port 132 to the socket, by controlling the intake air pressure of the first intake port 112 to be smaller than the intake air pressure of the second intake port 123, it is ensured that the pressure of the cooling gas from the first and third exhaust ports 113 and 132 is less than the allowable pressure of the first and second dry gas seals 114 and 134, thereby ensuring effective sealing of the first dry gas seal 114 and the second dry gas seal 134, and further realizing effective sealing of the rotating shaft 1 and the bearing cylinder.
It should be understood that the above-described embodiments of the present invention are merely examples for clearly illustrating the present invention, and are not intended to limit the embodiments of the present invention. Numerous obvious variations, adaptations and substitutions will occur to those skilled in the art without departing from the scope of the invention. And are neither required nor exhaustive of all embodiments. Any modification, equivalent replacement, and improvement made within the spirit and principle of the present invention should be included in the protection scope of the claims of the present invention.
Claims (10)
1. A rotor system for a turbine, comprising:
the rotating shaft (1) is sequentially provided with a first low-temperature area (11), a high-temperature area (12) and a second low-temperature area (13) along the axial direction of the rotating shaft (1);
the balance disc (111), the balance disc (111) is arranged in the first low-temperature area (11) of the rotating shaft (1), and a first seal (1111) is sleeved on the balance disc (111);
a first air inlet (112), wherein the first air inlet (112) is arranged in the first low-temperature region (11) of the rotating shaft (1), and the first air inlet (112) is used for being communicated with a cooling air source to cool the first seal (1111);
the turbine rotor (121), the turbine rotor (121) is arranged in the high-temperature area (12) of the rotating shaft (1), and blades (122) are arranged on the periphery of the turbine rotor (121);
the second air inlet (123), second air inlet (123) are located pivot (1) high temperature region (12), second air inlet (123) are used for providing the high temperature gas drive blade (122) drive pivot (1) rotates.
2. The turbine rotor system according to claim 1, characterized in that the first low temperature zone (11) of the rotating shaft (1) further has a first exhaust port (113), the first intake port (112) and the first exhaust port (113) being located on both sides of the first seal (1111), respectively, the first exhaust port (113) being remote from the turbine rotor (121) with respect to the first intake port (112), the first exhaust port (113) and the first intake port (112) being communicable through a gap between the rotating shaft (1) and the first seal (1111).
3. The turbine rotor system according to claim 2, characterized in that the high temperature region (12) of the rotating shaft (1) is provided with a second exhaust port (124), the second inlet port (123) and the second exhaust port (124) are respectively located on both sides of the turbine rotor (121), the second exhaust port (124) is far away from the balance disk (111) relative to the second inlet port (123), and the second exhaust port (124) is used for collecting high temperature gas passing through the blades (122).
4. The turbine rotor system according to claim 3, wherein the second low temperature region (13) of the rotating shaft (1) is provided with a third air inlet (131), a third air outlet (132) and a second seal (133), the second seal (133) is sleeved on the rotating shaft (1) and is located between the third air inlet (131) and the third air outlet (132), the third air inlet (131) is close to the second air outlet (124) relative to the third air outlet (132), the third air inlet (131) is communicated with the first air inlet (112), the third air outlet (132) is communicated with the first air outlet (113), and the third air outlet (132) and the third air inlet (131) can be communicated through a gap between the rotating shaft (1) and the second seal (133).
5. The turbine rotor system according to claim 1, wherein the high temperature region (12) of the rotating shaft (1) is further provided with a fourth exhaust port (125), the fourth exhaust port (125) is arranged between the first air inlet (112) and the second air inlet (123), a third seal (126) is arranged between the fourth exhaust port (125) and the second air inlet (123), the third seal (126) is sleeved on the rotating shaft (1), and the fourth exhaust port (125) and the second air inlet (123) can be communicated through a gap between the rotating shaft (1) and the third seal (126).
6. The turbine rotor system according to claim 5, wherein a fourth seal (115) is disposed between the fourth exhaust port (125) and the first air inlet port (112), the fourth seal (115) is sleeved on the rotating shaft (1), and the fourth exhaust port (125) and the first air inlet port (112) can be communicated through a gap between the rotating shaft (1) and the fourth seal (115).
7. The turbine rotor system according to claim 4, wherein a fifth seal (135) is arranged between the third air inlet (131) and the second air outlet (124), the fifth seal (135) is sleeved on the rotating shaft (1), and the third air inlet (131) and the second air outlet (124) can be communicated through a gap between the rotating shaft (1) and the fifth seal (135).
8. The turbine rotor system according to claim 4, further comprising a bearing cylinder, wherein the rotating shaft (1) is disposed in the bearing cylinder, the first low-temperature region (11) of the rotating shaft (1) is provided with a first dry gas seal (114), the second low-temperature region (13) of the rotating shaft (1) is provided with a second dry gas seal (134), the first dry gas seal (114) and the second dry gas seal (134) are both sleeved on the rotating shaft (1) and used for sealing the bearing cylinder, the first dry gas seal (114) is close to the first exhaust port (113) relative to the first air inlet (112), and the second dry gas seal (134) is close to the third exhaust port (132) relative to the third air inlet (131).
9. The turbine rotor system of claim 1, wherein an intake pressure of the first intake port (112) is less than an intake pressure of the second intake port (123).
10. The turbine rotor system of claim 4, wherein the first seal (1111) and the second seal (133) are both carbon ring seals.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202010974430.9A CN112253259A (en) | 2020-09-16 | 2020-09-16 | Turbine rotor system |
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| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202010974430.9A CN112253259A (en) | 2020-09-16 | 2020-09-16 | Turbine rotor system |
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| CN112253259A true CN112253259A (en) | 2021-01-22 |
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| Application Number | Title | Priority Date | Filing Date |
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| CN202010974430.9A Pending CN112253259A (en) | 2020-09-16 | 2020-09-16 | Turbine rotor system |
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Cited By (4)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN113653539A (en) * | 2021-08-26 | 2021-11-16 | 上海发电设备成套设计研究院有限责任公司 | Turbine rotor arrangement system |
| CN113931705A (en) * | 2021-11-02 | 2022-01-14 | 上海发电设备成套设计研究院有限责任公司 | Turbine rotor device and operation method thereof |
| CN115559788A (en) * | 2022-12-01 | 2023-01-03 | 中国核动力研究设计院 | Supercritical carbon dioxide turbine |
| CN113931705B (en) * | 2021-11-02 | 2024-04-23 | 上海发电设备成套设计研究院有限责任公司 | Turbine rotor device and operation method thereof |
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| JP2010019190A (en) * | 2008-07-11 | 2010-01-28 | Toshiba Corp | Steam turbine and method of cooling steam turbine |
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| EP0623735A1 (en) * | 1993-05-03 | 1994-11-09 | Ormat Industries, Ltd. | Method of and apparatus for cooling a seal for machinery |
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Cited By (6)
| Publication number | Priority date | Publication date | Assignee | Title |
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| CN113653539A (en) * | 2021-08-26 | 2021-11-16 | 上海发电设备成套设计研究院有限责任公司 | Turbine rotor arrangement system |
| CN113653539B (en) * | 2021-08-26 | 2023-10-20 | 上海发电设备成套设计研究院有限责任公司 | Turbine rotor arrangement system |
| CN113931705A (en) * | 2021-11-02 | 2022-01-14 | 上海发电设备成套设计研究院有限责任公司 | Turbine rotor device and operation method thereof |
| CN113931705B (en) * | 2021-11-02 | 2024-04-23 | 上海发电设备成套设计研究院有限责任公司 | Turbine rotor device and operation method thereof |
| CN115559788A (en) * | 2022-12-01 | 2023-01-03 | 中国核动力研究设计院 | Supercritical carbon dioxide turbine |
| CN115559788B (en) * | 2022-12-01 | 2023-03-14 | 中国核动力研究设计院 | Supercritical carbon dioxide turbine |
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