Bypass system of indirect cooling cycle gas turbine

Abstract

The invention provides a bypass system of an intercooling cycle gas turbine, which comprises a three-shaft intercooling cycle gas turbine, a low-pressure compressor, a high-pressure compressor, a combustion chamber, a high-pressure turbine, a low-pressure turbine, a power turbine and an intercooler, wherein an intercooler inlet transition section is arranged between the low-pressure compressor and the intercooler; a bypass system with a control valve is additionally arranged on the intercooler inlet transition section and the intercooler outlet transition section of the three-shaft intercooling cycle gas turbine, before the intercooling cycle gas turbine is started, the control valve is firstly opened by an electric actuating mechanism, and then the intercooler inlet transition section and the intercooler outlet transition section of the three-shaft intercooling cycle gas turbine are started. The control valve on the bypass flow channel is located at the opening position, after ignition in the combustion chamber is successful and combustion is stable and the rotating speed of the high-pressure rotor reaches a certain rotating speed value, the control valve can be gradually closed and finally located at the closing position, and after the technology is adopted, the requirement for rapid starting of the three-shaft intercooling cycle gas turbine can be met.

Description

Technical Field

[0001] The invention belongs to the technical field of gas turbines, and in particular relates to a bypass system of an intercooled cycle gas turbine. Background Art

[0002] The simple cycle three-shaft gas turbine device mainly includes large components such as a low-pressure compressor, a high-pressure compressor, a combustion chamber, a high-pressure turbine, a low-pressure turbine, and a power turbine. In order to increase the useful work of the gas turbine device, one of the methods to reduce the power consumption of the compressor is to add an intercooler assembly and its supporting circulating cooling system between the high-pressure compressor and the low-pressure compressor, thereby obtaining an intercooled cycle gas turbine.

[0003] At present, when gas turbines are in use, due to the large air flow rate, in order to reduce the high-pressure compressor inlet air temperature to a lower temperature range, the heat carried by this part of compressed air is very large, which makes the structural size of the intercooler component also very large. When the time constant is large, the influence of the volume inertia link on the air flow and resistance loss cannot be ignored during the startup transition process. Therefore, it is necessary to ensure that the air at the outlet of the low-pressure compressor flows through the intercooler component as quickly as possible and enters the high-pressure compressor, so that the high-pressure rotor reaches the ignition speed value, and ensure that the air entering the combustion chamber reaches the minimum flow value. This is very unfavorable to the requirement of fast startup during the startup process of the intercooled cycle gas turbine. Summary of the invention

[0004] The object of the present invention is to provide a bypass system for an intercooled cycle gas turbine, aiming to solve the problem that the bypass system does not have compact structure, simple system, convenient system operation and high reliability.

[0005] The present invention is implemented as follows: a bypass system for an intercooled cycle gas turbine comprises a three-shaft intercooled cycle gas turbine, a low-pressure compressor, a high-pressure compressor, a combustion chamber, a high-pressure turbine, a low-pressure turbine, a power turbine and an intercooler: an intercooler inlet transition section is arranged between the low-pressure compressor and the intercooler, an intercooler outlet transition section is arranged between the intercooler and the high-pressure compressor, a bypass system is arranged between the intercooler inlet transition section and the intercooler outlet transition section, the bypass system comprises a valve inlet transition flow channel, a valve outlet transition flow channel, a control valve, a control box and an electric actuator, the control valve comprises an annular valve disc, a gear transmission shaft and a sealing gasket, a support plate is arranged on the outer wall of the intercooler inlet transition section, the gear transmission shaft is respectively provided with a bevel gear, a shaft sleeve, a sleeve, a nut and a spline, and a bearing, an end cover and a rubber gasket are respectively arranged on the mounting seat supporting the gear transmission shaft in the inner hole of the support plate.

[0006] Furthermore, the intercooler inlet transition section and the intercooler outlet transition section are designed as two independent components, and the intercooler inlet transition section and the intercooler outlet transition section are assembled by bolt connection.

[0007] Furthermore, the end surface of the annular valve disc is provided with gear teeth, and the gear teeth are meshed with the bevel gear of the gear transmission shaft to transmit motion.

[0008] Furthermore, the annular valve disc and the sealing gasket are installed between the valve inlet transition flow channel and the valve outlet transition flow channel, and the annular valve disc can rotate freely around the axis of the gas turbine.

[0009] Furthermore, the gear transmission shaft is meshedly connected with gear teeth on the end surface of the annular valve disc via a bevel gear.

[0010] Furthermore, the number of the support plates is two, and the two support plates are arranged on the inner wall of the intercooler inlet transition section along the circumferential direction.

[0011] Furthermore, there are four sealing pads, and all four sealing pads are made of round rubber material.

[0012] The beneficial effects of the present invention are as follows: a bypass system with a control valve is added to the intercooler inlet transition section and the intercooler outlet transition section of the three-axis intercooled cycle gas turbine. Before the three-axis intercooled cycle gas turbine is started, the control valve is first opened by the electric actuator to put the control valve on the bypass flow channel in the open position. After the ignition in the combustion chamber is successfully and stably burned, the control valve can be gradually closed and finally in the closed position after the high-pressure rotor speed reaches a certain speed value. By adopting this technology, the requirement for rapid start-up of the three-axis intercooled cycle gas turbine can be achieved. BRIEF DESCRIPTION OF THE DRAWINGS

[0013] Figure 1 This is a schematic diagram of the principle of a three-shaft intercooled cycle gas turbine of the present invention;

[0014] Figure 2 It is a schematic diagram of the structure of the intercooler assembly and the bypass system of the present invention;

[0015] Figure 3 The present invention Figure 1 Middle BB cross-section, Figure 3 -a indicates that the annular valve disc is in the open position, Figure 3 -b is a schematic diagram showing the structure of the annular valve disc in the closed position;

[0016] Figure 4 The present invention Figure 1 Middle AA section view, Figure 4 -a means the annular valve disc is in the closed position before rotation. Figure 4 -b represents the open position of the annular valve disc after rotation.

[0017] In the figure: 1. three-shaft intercooled cycle gas turbine; 2. low-pressure compressor; 3. high-pressure compressor; 4. combustion chamber; 5. high-pressure turbine; 6. low-pressure turbine; 7. power turbine; 8. intercooler; 9. intercooler inlet transition section; 10. intercooler outlet transition section; 11. bypass system; 12. valve inlet transition flow channel; 13. valve outlet transition flow channel; 14. control valve; 15. control box; 16. electric actuator; 17. annular valve disc; 18. gear transmission shaft; 19. sealing gasket; 20. bevel gear; 21. bushing; 22. sleeve; 23. nut; 24. spline; 25. bearing; 26. end cover; 27. rubber pad; 28. gear teeth; 29. ​​support plate. DETAILED DESCRIPTION

[0018] The present invention will be further described below in conjunction with the accompanying drawings.

[0019] The embodiment of the present invention provides a bypass system for an intercooled cycle gas turbine, such as Figure 1-4 As shown, the three-shaft intercooled cycle gas turbine 1, a low-pressure compressor 2, a high-pressure compressor 3, a combustion chamber 4, a high-pressure turbine 5, a low-pressure turbine 6, a power turbine 7 and an intercooler 8: an intercooler inlet transition section 9 is arranged between the low-pressure compressor 2 and the intercooler 8, an intercooler outlet transition section 10 is arranged between the intercooler 8 and the high-pressure compressor 3, a bypass system 11 is arranged between the intercooler inlet transition section 9 and the intercooler outlet transition section 10, and the bypass system 11 includes a valve inlet transition flow The intercooler comprises a control valve 14, a control box 15 and an electric actuator 16. The control valve 14 comprises an annular valve disc 17, a gear transmission shaft 18 and a sealing gasket 19. A support plate 29 is arranged on the outer wall of the intercooler inlet transition section 9. The gear transmission shaft 18 is respectively provided with a bevel gear 20, a sleeve 21, a sleeve 22, a nut 23 and a spline 24. The mounting seat supporting the gear transmission shaft 18 in the inner hole of the support plate 29 is respectively provided with a bearing 25, an end cover 26 and a rubber pad 27.

[0020] It should be noted that, when the existing gas turbine is in use, due to the large air flow, in order to reduce the inlet air temperature of the high-pressure compressor 3 to a lower temperature range, the heat carried by this part of the compressed air is very large, which makes the structural size of the intercooler component also very large. When the time constant is large, the influence of the volume inertia link on the air flow and resistance loss cannot be ignored during the startup transition process. Therefore, it is necessary to ensure that the air at the outlet of the low-pressure compressor 2 flows through the intercooler component as quickly as possible and enters the high-pressure compressor 3, so that the high-pressure rotor reaches the ignition speed value, and ensure that the air entering the combustion chamber 4 reaches the minimum flow value. This is very unfavorable to the requirement of fast startup during the startup of the intercooled cycle gas turbine, so In order to solve the problem that the existing bypass system does not have compact structure, simple system, convenient system operation and high reliability, the present solution adds a bypass system 11 with a control valve 14 on the intercooler inlet transition section 9 and the intercooler outlet transition section 10 of the three-shaft intercooled cycle gas turbine 1. Before the three-shaft intercooled cycle gas turbine 1 is started, the control valve 14 is first opened by the electric actuator 16 to put the control valve 14 on the bypass flow channel in the open position. After the ignition in the combustion chamber 4 is successfully and stably burned, the control valve 14 can be gradually closed after the high-pressure rotor speed reaches a certain speed value, and finally in the closed position. By adopting this technology, the requirement of rapid start-up of the three-shaft intercooled cycle gas turbine 1 can be achieved.

[0021] Specifically, in this embodiment, the solution mainly includes that the intercooler inlet transition section 9 and the intercooler outlet transition section 10 are designed as two independent components, and the intercooler inlet transition section 9 and the intercooler outlet transition section 10 are assembled by bolt connection.

[0022] In a further preferred embodiment of the present invention, Figure 2-4 As shown, the end face of the annular valve disc 17 is provided with gear teeth 28, which mesh with the bevel gear 20 of the gear transmission shaft 18 to transmit motion. The end face of the annular valve disc 17 is provided with bevel teeth, and the gear teeth 28 on the gear transmission shaft 18 mesh with the bevel teeth on the annular valve disc 17, so that the gear transmission shaft 18 drives the annular valve disc 17 to rotate.

[0023] In this embodiment, when the three-shaft intercooled cycle gas turbine 1 is started, the bypass system 11 is put into operation, and the electric actuator 16 is controlled by the control box 15 to put the control valve 14 in the open position. During the startup of the three-shaft intercooled cycle gas turbine 1, since the pressure loss of the bypass system 11 added to the transition section is relatively small, most of the compressed air discharged from the low-pressure compressor 2 is directly sucked into the high-pressure compressor 3 through the bypass system 11, so that the high-pressure rotor reaches the ignition speed as soon as possible, and the corresponding air flow entering the combustion chamber 4 reaches the minimum flow value. At this time, the normal ignition and stable combustion of the combustion chamber 4 can be guaranteed. After the high-pressure rotor speed reaches a certain speed value, the annular valve disc 17 of the control valve 14 can be gradually closed, and finally the annular valve disc 17 is in the closed position.

[0024] In a further preferred embodiment of the present invention, Figure 2-4 As shown, the annular valve disc 17 and the sealing gasket 19 are installed between the valve inlet transition flow channel 12 and the valve outlet transition flow channel 13, and the annular valve disc 17 can rotate freely around the axis of the gas turbine.

[0025] In this embodiment, it is possible to prevent the air in the outlet transition flow channel 13 from leaking into the inlet transition flow channel 12, thereby improving the sealing performance.

[0026] In a further preferred embodiment of the present invention, Figure 2-4 As shown, the gear transmission shaft 18 is meshedly connected with the gear teeth 28 on the end surface of the annular valve disk 17 via the bevel gear 20 .

[0027] In this embodiment, by providing bevel teeth on the end surface of the annular valve disc 17 , the gear teeth 28 on the gear transmission shaft 18 mesh with the bevel teeth on the annular valve disc 17 , so that the gear transmission shaft 18 drives the annular valve disc 17 to rotate.

[0028] In a further preferred embodiment of the present invention, Figure 2 As shown, there are two support plates 29 , and the two support plates 29 are arranged on the inner wall of the intercooler inlet transition section 9 along the circumferential direction.

[0029] In this embodiment, it is convenient to install and connect the mounting seat of the gear transmission shaft 18 of the control valve 14 .

[0030] In a further preferred embodiment of the present invention, Figure 2-4 As shown, there are four sealing pads 19 , and all of the four sealing pads 19 are made of round rubber material.

[0031] In this embodiment, four circular sealing gaskets 19 are respectively arranged between the annular valve disc 17 and the intercooler inlet transition section 9 and the intercooler outlet transition section 10 to prevent the air in the valve outlet transition channel 13 from leaking into the valve inlet transition channel 12.

[0032] The above description is only a preferred embodiment of the present invention and is not intended to limit the present invention. For those skilled in the art, the present invention may have various modifications and variations. Any modification, equivalent replacement, improvement, etc. made within the spirit and principle of the present invention shall be included in the protection scope of the present invention.

Claims

1. A bypass system for an indirect cooling cycle gas turbine, characterized in that: The invention comprises a three-shaft intercooled cycle gas turbine (1), a low-pressure compressor (2), a high-pressure compressor (3), a combustion chamber (4), a high-pressure turbine (5), a low-pressure turbine (6), a power turbine (7) and an intercooler (8); an intercooler inlet transition section (9) is arranged between the low-pressure compressor (2) and the intercooler (8); an intercooler outlet transition section (10) is arranged between the intercooler (8) and the high-pressure compressor (3); a bypass system (11) is arranged between the intercooler inlet transition section (9) and the intercooler outlet transition section (10); the bypass system (11) comprises a valve inlet transition channel (12), A valve outlet transition flow channel (13), a control valve (14), a control box (15) and an electric actuator (16); the control valve (14) comprises an annular valve disc (17), a gear transmission shaft (18) and a sealing gasket (19); a support plate (29) is arranged on the outer wall of the intercooler inlet transition section (9); the gear transmission shaft (18) is respectively provided with a bevel gear (20), a shaft sleeve (21), a sleeve (22), a nut (23) and a spline (24); and a mounting seat in the inner hole of the support plate (29) supporting the gear transmission shaft (18) is respectively provided with a bearing (25), an end cover (26) and a rubber gasket (27).

2. The bypass system of an indirect cooling cycle gas turbine according to claim 1, characterized in that: The intercooler inlet transition section (9) and the intercooler outlet transition section (10) are designed as two independent components, and the intercooler inlet transition section (9) and the intercooler outlet transition section (10) are assembled by bolt connection.

3. The bypass system of an indirect cooling cycle gas turbine according to claim 1, characterized in that: The end surface of the annular valve disc (17) is provided with gear teeth (28), and the gear teeth (28) mesh with the bevel gear (20) of the gear transmission shaft (18) to transmit motion.

4. The bypass system of an indirect cooling cycle gas turbine according to claim 1, characterized in that: The annular valve disc (17) and the sealing gasket (19) are installed between the valve inlet transition flow channel (12) and the valve outlet transition flow channel (13), and the annular valve disc (17) can rotate freely around the axis of the gas turbine.

5. The bypass system of the indirect cooling cycle gas turbine according to claim 1, characterized in that: The gear transmission shaft (18) is meshedly connected with the gear teeth (28) on the end surface of the annular valve disc (17) via a bevel gear (20).

6. The bypass system of an indirect cooling cycle gas turbine according to claim 1, characterized in that: The number of the support plates (29) is two, and the two support plates (29) are arranged on the inner wall of the intercooler inlet transition section (9) along the circumferential direction.

7. The bypass system of an indirect cooling cycle gas turbine according to claim 1, characterized in that: The number of the sealing pads (19) is four, and the four sealing pads (19) are all made of round rubber material.

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