CN113653539B - Turbine rotor arrangement system - Google Patents

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

A turbine rotor arrangement system

Technical field

The present invention relates to the technical field of turbine rotating machinery, and in particular, to a turbine rotor arrangement system.

Background technique

The supercritical carbon dioxide turbine rotor is a rotor suitable for power generation equipment. Most of the current balance pistons are arranged in the high-temperature section of the turbine. Due to the large air leakage radius, in order to control the amount of air leakage, the length of the balance piston is longer, resulting in The high temperature section is too long, resulting in lower safety performance of the unit. There are also a few balance pistons arranged in the low-temperature section. However, the existing steam cycle rotor layout scheme has a larger balance plate length and diameter, resulting in a larger overall span of the rotor, which is not conducive to the overall structural design of the unit, making it Safety performance and economic performance are low.

Contents of the invention

Based on the above, the purpose of the present invention is to provide a turbine rotor arrangement system that does not require a balance plate, has higher overall operating efficiency of the unit, smaller overall span of the rotor, and has better safety performance and economic performance of the unit.

In order to achieve the above objects, the present invention adopts the following technical solutions:

A turbine rotor arrangement system, including:

turbine cylinder;

A rotating shaft is arranged in the turbine cylinder, and the rotating shaft is sequentially provided with a first low temperature zone, a high temperature zone and a second low temperature zone along the axial direction of the rotating shaft;

A boss is provided in the first low temperature zone of the rotating shaft, and a first dry gas seal is provided on the outer periphery of the boss;

A first air inlet is provided on a side of the boss close to the high temperature zone, and the first air inlet is used to communicate with a cooling air source.

As a preferred solution for the turbine rotor arrangement system, it also includes:

A turbine rotor is provided in the high-temperature area of the rotating shaft, and blades are provided on the outer periphery of the turbine rotor;

A second air inlet is provided in the high-temperature area of the rotating shaft. The second air inlet is used to communicate with a high-temperature air source to drive the blades to drive the rotating shaft to rotate.

As a preferred solution for the turbine rotor arrangement system, it also includes:

A first exhaust port is provided in the high-temperature area of the rotating shaft and is located between the first air inlet and the second air inlet. The first air inlet and the first row A first seal is provided between the air ports. The first seal is sleeved on the rotating shaft. The first exhaust port and the first air inlet can pass between the first seal and the rotating shaft. gaps are connected.

As a preferred solution of the turbine rotor arrangement system, a second seal is provided between the second air inlet and the first exhaust port, and the second seal is sleeved on the rotating shaft. The second air inlet and the first exhaust port can communicate through a gap between the second seal and the rotating shaft.

As a preferred solution for the turbine rotor arrangement system, it also includes:

A second exhaust port is provided in the high-temperature area of the rotating shaft. The second exhaust port is connected with the first exhaust port. The second air inlet and the second exhaust port are respectively Disposed on both sides of the turbine rotor, the second exhaust port is farther away from the boss than the second air inlet, and the second exhaust port is used to collect high-temperature gas passing through the blades. .

As a preferred solution 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 third An exhaust port and the second exhaust port are connected through a gap between the inner cylinder and the outer cylinder.

As a preferred solution 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 connected through a communication pipe or a gap in the cylinder.

As a preferred solution for the turbine rotor arrangement system, it also includes:

A third air inlet is provided in the second low temperature zone of the rotating shaft. The third air inlet is connected to the first air inlet. The second exhaust port and the third air inlet are A third seal is provided between the ports, and the third seal is sleeved on the rotating shaft. The third air inlet and the second exhaust port can pass through the gap between the third seal and the rotating shaft. Gap connectivity.

As a preferred solution of the turbine rotor arrangement system, bearings are provided at both ends of the rotating shaft for supporting the rotating shaft, and bearings are provided on both sides of the rotating shaft on one side of the first low temperature zone. A bearing thrust plate.

As a preferred solution for the turbine rotor arrangement system, it also includes:

A second dry gas seal is sleeved on the rotating shaft and located in the second low temperature zone. The inner diameter of the first dry gas seal is larger than the inner diameter of the second dry gas seal, and the inner diameter of the first dry gas seal is The inner diameter is larger than the outer diameter of the bearing thrust plate.

The beneficial effects of the present invention are:

The invention provides a turbine rotor arrangement system. The turbine rotor arrangement system includes a turbine cylinder, a rotating shaft, a boss and a first air inlet. The rotating shaft is sequentially provided with a first low temperature zone, a high temperature zone and a third air inlet along the axial direction. In the second low-temperature zone, a boss with a first dry gas seal is set around the first low-temperature zone, and a first air inlet is set on the side of the boss close to the high-temperature zone. The first air inlet is connected to the cold air source to To cool down the rotor, 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 is the air pressure of the first air inlet, and the other side is atmospheric pressure. Through the first dry gas The pressure difference on both sides of the seal balances the axial thrust of the rotor, that is, without setting a balance plate, the balance force can be adjusted by adjusting the air pressure of the cooling air introduced through the first air inlet; and through the above arrangement, It is conducive to shortening the overall span of the rotor, conducive to the overall structural design of the rotor, and improving the safety and economic performance of the unit.

Description of the drawings

In order to more clearly illustrate the technical solutions in the embodiments of the present invention, a brief introduction will be made below to the drawings needed to describe the embodiments of the present invention. Obviously, the drawings in the following description are only some embodiments of the present invention. , For those of ordinary skill in the art, other drawings can also be obtained based on the content of the embodiments of the present invention and these drawings without exerting creative efforts.

Figure 1 is a half-section schematic diagram of a turbine rotor arrangement system provided by an embodiment of the present invention.

In the picture:

1. Rotating shaft; 2. Bearing; 3. Bearing thrust plate; 10. First low temperature zone; 20. High temperature zone; 30. Second low temperature zone; 101. Boss; 102. First dry gas seal; 103. First Air inlet; 104, first seal; 201, turbine rotor; 202, blade; 203, second air inlet; 204, first exhaust port; 205, second seal; 206, second exhaust port; 301. The third air inlet; 302. The third seal; 303. The second dry gas seal.

Detailed ways

The present invention will be further described in detail below in conjunction with the accompanying drawings and examples. It can be understood that the specific embodiments described here are only used to explain the present invention, but not to limit the present invention. In addition, it should be noted that, for convenience of description, only some but not all structures related to the present invention are shown in the drawings.

In the description of the present invention, unless otherwise clearly stated and limited, the terms "connected", "connected" and "fixed" should be understood in a broad sense. For example, it can be a fixed connection, a detachable connection, or an integral body. ; It can be a mechanical connection or an electrical connection; it can be a direct connection or an indirect connection through an intermediate medium; it can be an internal connection between two elements or an interaction between two elements. For those of ordinary skill in the art, the specific meanings of the above terms in the present invention can be understood on a case-by-case basis.

In the present invention, unless otherwise expressly provided and limited, the term "above" or "below" a first feature of a second feature may include direct contact between the first and second features, or may also include the first and second features. Not in direct contact but through additional characteristic contact between them. Furthermore, the terms "above", "above" and "above" a first feature on a second feature include the first feature being directly above and diagonally above the second feature, or simply mean that the first feature is higher in level than the second feature. “Below”, “under” and “under” the first feature is the second feature includes the first feature being directly below and diagonally below the second feature, or simply means that the first feature is less horizontally than the second feature.

In the description of this embodiment, the terms "upper", "lower", "left", "right" and other orientations or positional relationships are based on the orientations or positional relationships shown in the drawings, and are only for convenience of description and simplified operation. It is not intended to indicate or imply that the device or element referred to must have a specific orientation, be constructed and operate in a specific orientation, and therefore is not to be construed as a limitation of the invention. In addition, the terms "first" and "second" are only used for descriptive purposes and have no special meaning.

As shown in Figure 1, this 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 arranged in the turbine cylinder. Inside, the rotating shaft 1 is provided with a first low temperature zone 10, a high temperature zone 20 and a second low temperature zone 30 in sequence along the axial direction of the rotating shaft 1. The boss 101 is provided in the first low temperature zone 10 of the rotating shaft 1, and the outer peripheral sleeve of the boss 101 A first dry gas seal 102 is provided, and a first air inlet 103 is provided on the side of the boss 101 close to the high temperature zone 20, and the first air inlet 103 is used to communicate with the cooling air source. The inlet pressure of the cooling air is P ₀ and the temperature is T ₀ . P ₀ and T ₀ are the air inlet parameters of the turbine shaft sealing gas. The cooling gas source extracts cooling gas from the circulation system, and the temperature of the extracted cooling gas is lower than the temperature that the first dry gas seal 102 can withstand. The inlet pressure P ₀ of the cooling air entering the first air inlet 103 can be adjusted through the regulating valve, and the inlet air temperature T ₀ of the cooling air entering the first air inlet 103 can be adjusted through the electric heater, so that the cooling air can be controlled by The intake air pressure and intake air temperature of the source control the pressure P ₀ and temperature T ₀ of the cooling air entering the first air inlet 103 . The cold air connected to the first air inlet 103 is used to cool the rotor, and the temperature of the cooling air can be adjusted to reduce the thermal stress of the rotor; under the above structure, one side of the first dry gas seal 102 is the first air inlet 103 The air pressure on the other side is atmospheric pressure. The pressure difference on both sides of the first dry gas seal 102 balances the axial thrust of the rotor. That is, there is no need to set up a balance plate, and the balance force can be adjusted by adjusting the size of P ₀ . Moreover, the turbine rotor arrangement system provided by this embodiment solves the problem in the prior art: when the balance piston is arranged in the high-temperature section of the turbine, due to the large air leakage radius, the length of the balance piston must be lengthened in order to control the air leakage amount. This will cause the high-temperature section of the turbine to be too long, which can easily affect the safety performance of the unit.

Specifically, bearings 2 are provided at both ends of the rotating shaft 1. The bearings 2 are used to support the rotating shaft 1, and a bearing thrust plate 3 is provided on both sides of the rotating shaft 1 located in the first low temperature zone 10. More specifically, the inner diameter of the first dry gas seal 102 is larger than the outer diameter of the bearing thrust plate 3 . Since the bearing thrust plate 3 is integrated 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 plate 3 so that the first dry gas seal 102 can be smoothly sleeved on the rotating shaft 1 from one end. The outer periphery of the boss 101 makes the first dry gas seal 102 easy to install and disassemble, and can effectively avoid the limitations of the shaft seal leakage system, cooling air system, dry gas seal and carbon ring seal arrangement.

Further, the turbine rotor arrangement system also includes a turbine rotor 201, a second air inlet 203, a first exhaust port 204 and a second exhaust port 206. The turbine rotor 201 is arranged in the high temperature zone 20 of the rotating shaft 1, Blades 202 are provided on the outer periphery of the turbine rotor 201. The second air inlet 203 is provided in the high-temperature zone 20 of the rotating shaft 1. The second air inlet 203 is used to communicate with the high-temperature air source to drive the blades 202 to drive the rotating shaft 1 to rotate. The first The exhaust port 204 is provided in the high temperature zone 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 provided in the high temperature zone 20 of the rotating shaft 1 . The second exhaust port 206 is connected with the first exhaust port 204 . The second air inlet 203 and the second exhaust port 206 are respectively provided in the turbine rotor 201 On both sides of the blade, the second exhaust port 206 is far away from the boss 101 relative to the second air inlet 203 . The second exhaust port 206 is used to collect high-temperature gas passing through the blade 202 . The pressure of the high-temperature gas at the second air inlet 203 is P ₁ and the temperature is T ₁ . P ₁ and T ₁ are turbine air inlet parameters. The exhaust pressures of the first exhaust port 204 and the second exhaust port 206 are is P ₂ , the temperature is T ₂ , P ₂ and T ₂ are turbine exhaust parameters, the values of P ₁ , T ₁ , P ₂ and T ₂ are determined by the system, and the cooling gas source is extracted from the circulation system. The pressure is greater than the exhaust pressure P ₂ . The cooling air entering from the first air inlet 103 cools the rotating shaft 1 and is discharged from the first exhaust port 204. The high-temperature air entering from the second air inlet 203 enters the blades 202 to drive the blades 202 to rotate, and then is discharged from the second row of The air outlet 206 is discharged, and at the same time, a small amount of high-temperature gas leaked from the second air inlet 203 is discharged from the first exhaust port 204, and by connecting the second exhaust port 206 to the first exhaust port 204, the flow to the third exhaust port 204 can be The high-temperature air from the exhaust port 204 and the high-temperature air driven by the blades 202 to complete the work of the rotating shaft 1 are discharged together to ensure the normal and orderly operation of the rotating shaft 1.

In this embodiment, the turbine cylinder includes an outer cylinder and an inner cylinder. The inner cylinder is arranged in the outer cylinder. The rotating shaft 1 is arranged in the inner cylinder. The first exhaust port 204 and the second exhaust port 206 pass between the inner cylinder and the outer cylinder. The gaps between them are connected. 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 through a communication pipe or an intra-cylinder gap, which is not limited in this embodiment. Under the above structure, the axial force exerted by the high-temperature gas on the rotating shaft 1 can be offset to a minimum by the cooling air pressure at the first air inlet 103 , thereby minimizing the axial force on the rotating shaft 1 without arranging a balance plate.

Preferably, a first seal 104 is provided between the first air inlet 103 and the first exhaust port 204. The first seal 104 is sleeved on the rotating shaft 1, and the first exhaust port 204 and the first air inlet 103 can pass through. The gap between the first seal 104 and the rotating shaft 1 is connected. When the cooling air enters from the first air inlet 103 and is discharged from the first exhaust port 204, the cooling air cools the first seal 104, and the cooling air leaks from the gap between the first seal 104 and the rotating shaft 1 The air can further cool the first seal 104 to ensure the effective sealing of the first seal 104, thereby reducing the amount of air leakage, shortening the span of the rotating shaft 1, and improving the safety of the unit; at the same time, the air is flushed from the first air inlet 103 The incoming cooling air 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 provided between the second air inlet 203 and the first exhaust port 204. The second seal 205 is sleeved on the rotating shaft 1, and the second air inlet 203 and the first exhaust port 204 can pass through. The gap between the second seal 205 and the rotating shaft 1 is connected. By providing the second seal 205, leakage of high-temperature gas flowing into the second air inlet 203 can be prevented. Even if the high-temperature gas flowing to the second air inlet 203 leaks, the leaked high-temperature gas can be discharged through the first exhaust port 204 . Alternatively, the second seal 205 may adopt a tooth seal, a labyrinth seal or a honeycomb seal, preferably a tooth seal.

Furthermore, the second low temperature zone 30 of the rotating shaft 1 is provided with a third air inlet 301. The third air inlet 301 is connected to the first air inlet 103. The second exhaust port 206 and the third air inlet 301 are connected. A third seal 302 is provided between them. The third seal 302 is sleeved on the rotating shaft 1 . The third air inlet 301 and the second exhaust port 206 can be connected through the gap between the third seal 302 and the rotating shaft 1 . The cooling air flows from the first air inlet 103 to the third air inlet 301. The cooling air flowing into the third air inlet 301 can reduce the temperature of the second low temperature zone 30 of the rotating shaft 1, thereby reducing the temperature of the third seal 302. , the cooling air leaking from 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 exhaust port 206 to The third seal 302 flows to ensure 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 can also be blocked according to the actual working conditions, and different temperatures can be introduced into the third air inlet 301 and the first air inlet 103 respectively. and cooling air of different pressures to adapt to actual working conditions. In other embodiments, only the shaft segments corresponding to the first low temperature zone 10 and the high temperature zone 20 of the rotating shaft 1 may be retained according to the actual working conditions to shorten the span of the rotating shaft 1 distance to improve the safety of the unit.

Preferably, the first seal 104 and the third seal 302 are carbon ring seals. Since the first seal 104 and the third seal 302 are located in the first low temperature zone 10 and the second low temperature zone 30 respectively, the temperatures are relatively low, so that they can be arranged there. Compared with the gap of ordinary seals of 0.5mm, carbon ring seals can achieve a gap of 0.1mm. However, carbon ring seals have certain requirements for ambient temperature and cannot be arranged in high temperature areas. This arrangement can greatly reduce the boss. 101 in length, and reduces the length of the high-temperature section of the rotor when the turbine is running, improving the safety performance of the unit, and can reduce the leakage of mainstream gas to improve the overall operating efficiency. The length of the high-temperature zone 20 is reduced by about 32%.

In this embodiment, the second low temperature zone 30 is also 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 the third air inlet. On both sides of the port 301, the second dry gas seal 303 is farther away from the second exhaust port 206 than the third seal 302, and is used to seal 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 . By arranging the rotating shaft 1 in the inner cylinder and controlling the temperature and pressure of the cooling air, it can be ensured that the temperature and pressure of the cooling air entering from the first air inlet 103 and the third air inlet 301 are in the first dry gas seal 102 and The second dry gas seal 303 is within the allowable temperature and allowable pressure ranges, thereby ensuring that the first dry gas seal 102 and the second dry gas seal 303 respectively sleeved on the boss 101 and the rotating shaft 1 can effectively seal, thereby achieving Effective sealing between the rear rotating shaft and the inner cylinder, while achieving axial force balance of the rotating shaft 1. This solves the technical problems existing in the prior art: when dry gas seals are arranged on both sides of the turbine, such as using a conventional air leakage system, the lowest ambient pressure of the dry gas seal is the exhaust pressure of the turbine, and the supercritical state The dry gas sealing system below is prone to failure due to frictional heat.

The turbine rotor arrangement system provided by this embodiment has independent cooling air intake and exhaust, and a stable air source. The cooling air intake pressure can be adjusted as needed, so that balanced thrust can be achieved without arranging a balance plate. Moreover, the improvement of the turbine rotor layout system is conducive to greatly shortening the overall span of the rotor, which is beneficial to the overall structural design of the rotor, improving the safety performance of the overall rotor, and on this basis, the shaft diameter of the rotor can be appropriately reduced, further improving the Economic performance of the unit.

Note that the above are only the preferred embodiments of the present invention and the technical principles used. Those skilled in the art will understand that the present invention is not limited to the specific embodiments described herein, and that various obvious changes, readjustments and substitutions can be made to those skilled in the art without departing from the scope of the invention. Therefore, although the present invention has been described in detail through the above embodiments, the present invention is not limited to the above embodiments. Without departing from the concept of the present invention, it can also include more other equivalent embodiments, and the present invention The scope is determined by the scope of the appended 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).