Indirect cooling circulation gas turbine with bypass system

Abstract

The invention provides an intercooling cycle gas turbine with a bypass system. The bypass system is arranged between an intercooler inlet transition section and an intercooler outlet transition section. The bypass system comprises a low-pressure compressor outlet transition flow channel, a high-pressure compressor inlet transition flow channel, a control valve, an execution mechanism and a control cabinet. The low-pressure compressor outlet transition runner and the high-pressure compressor inlet transition runner are respectively connected with the intercooler inlet transition section and the intercooler outlet transition section; the control cabinet sends out a control instruction according to a set control program, and the control valve acts through the executing mechanism, so that the control valve is in an open state and a closed state. The bypass system can meet the technical requirement for rapid starting of the indirect cooling circulation gas turbine device and has the advantages of being compact in structure, reasonable in arrangement, simple in bypass system, convenient to operate, high in reliability and the like.

Description

Technical Field

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

[0002] Due to the superior performance of the simple cycle gas turbine device, it has the characteristics of small size, high power density, fast startup, and easy maintenance, and has been widely used in many energy fields. The gas turbine mainly includes three components: compressor, combustion chamber and gas turbine. Since the compressor consumes about 2 / 3 of the gas turbine expansion shaft work in the process of compressing air, the remaining net power output is used to drive the load. The lower the compressor inlet air temperature, the less power consumption of the compressor shaft. However, the temperature of the gas is always rising during the compression process, so the compression shaft power required is increasing. In order to increase the useful power of the gas turbine device and reduce the power consumption of the compressor, an intercooler assembly and a matching circulating cooling system are added between the high-pressure compressor and the low-pressure compressor, thereby obtaining an intercooled cycle gas turbine. Due to the large air flow, in order to cool the compressed air from the high-pressure compressor inlet to a predetermined temperature range, the heat carried by this part of the compressed air is very large, which makes the structural size of the intercooler assembly (including the intercooler, the intercooler inlet transition section and the outlet transition section) also very large. Therefore, the volume of the cavity of this part of the flow is quite large, which can be regarded as an energy accumulator and belongs to a volume inertia link, that is, the flow time of the air in the flow is closely related to the volume of the transition section, the air mass flow rate, the air density and other parameters, which makes the pressure loss of the air in the process of flowing through the intercooler assembly large. Due to the large time constant, the influence of the volume inertia link on the air flow 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 assembly as quickly as possible and enters the high-pressure compressor, so that the high-pressure rotor reaches the ignition speed value, and the air entering the combustion chamber reaches the minimum flow value, which is very unfavorable to the requirement of fast startup of the intercooled cycle gas turbine during the startup process. Summary of the invention

[0003] The object of the present invention is to provide an intercooled cycle gas turbine with a bypass system to solve the shortcomings of slow start-up time and large flow resistance of the intercooled cycle gas turbine device.

[0004] An intercooler cycle gas turbine with a bypass system comprises 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 provided between the low-pressure compressor and the intercooler, and an intercooler outlet transition section is provided between the intercooler and the high-pressure compressor; a bypass system is provided between the intercooler inlet transition section and the intercooler outlet transition section; the bypass system comprises a low-pressure compressor outlet transition flow channel, a high-pressure compressor inlet transition flow channel, a control valve, an actuator and a control cabinet; the low-pressure compressor outlet transition flow channel and the high-pressure compressor inlet transition flow channel are respectively connected to the intercooler inlet transition section and the intercooler outlet transition section; the control cabinet issues a control instruction according to a set control program, realizes the control valve action through the actuator, and puts the control valve in an "open" state and a "closed" state.

[0005] Furthermore, the flow capacity of the cross-sectional area of ​​the transition flow passage at the outlet of the low-pressure compressor is not less than the air flow value required for ignition of the combustion chamber.

[0006] Furthermore, the flow capacity of the cross-sectional area of ​​the high-pressure compressor inlet transition flow channel is not less than the air flow value required for combustion chamber ignition.

[0007] Furthermore, the actuator includes but is not limited to a mechanical transmission device that can transmit motion.

[0008] Furthermore, the bypass system includes but is not limited to operating during the startup process of the intercooled cycle gas turbine.

[0009] Furthermore, when the intercooler, the supporting circulating cooling system and other systems fail during the operation of the intercooled cycle gas turbine, the bypass system can convert the intercooled cycle gas turbine from the "fault" mode to the simple cycle gas turbine mode to continue operation.

[0010] The beneficial effects of the present invention are:

[0011] (1) Since the intercooled cycle gas turbine is equipped with a bypass system with a control valve, the requirement for faster startup of the intercooled cycle gas turbine can be met.

[0012] (2) Since the bypass system technology with a control valve is reasonably adopted on the intercooled cycle gas turbine body, not only can the intercooled cycle gas turbine be started faster, but also the structure is simple and the flow resistance is small. Even if the intercooler component and the circulating cooling system have "failures", the intercooled cycle gas turbine "failure" mode can be converted to the simple cycle gas turbine mode to continue operation.

[0013] (3) Compared with conventional intercooled cycle gas turbines, since the intercooler, the intercooler inlet transition section and the intercooler outlet transition section are a volume inertia link, due to the influence of the volume inertia effect, the intercooled cycle gas turbine device has the disadvantages of slow start-up time and large resistance in the transition section. The present invention adopts a bypass system technology in the intercooled cycle gas turbine to solve the disadvantages of slow start-up time and large flow resistance of the intercooled cycle gas turbine device.

[0014] (4) The present invention can meet the technical requirements for faster startup of an intercooled cycle gas turbine device, and has the characteristics of compact structure, reasonable layout, simple bypass system, convenient operation, and high reliability. BRIEF DESCRIPTION OF THE DRAWINGS

[0015] Figure 1 This is a simplified diagram of the working principle of a conventional intercooled cycle gas turbine;

[0016] Figure 2 The figure is a schematic diagram of the working principle of the present invention. DETAILED DESCRIPTION

[0017] The present invention is further described below in conjunction with the accompanying drawings.

[0018] Figure 1 This is a simplified diagram of the working principle of a conventional intercooled cycle gas turbine. The conventional intercooled cycle gas turbine 1 is composed of 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, an intercooler 8 and other components. An intercooler inlet transition section 9 is provided between the low-pressure compressor 2 and the intercooler 8, and an intercooler outlet transition section 10 is provided between the intercooler 8 and the high-pressure compressor 3.

[0019] Figure 2The schematic diagram of the working principle of the present invention is shown in FIG. 1. The novel intercooled cycle gas turbine 11 is based on the conventional intercooled cycle gas turbine 1. A bypass system 12 with a control valve is newly added to the intercooler inlet transition section 9 and the intercooler outlet transition section 10. The bypass system 12 is composed of a low-pressure compressor outlet transition passage 13, a high-pressure compressor inlet transition passage 14, a control valve 15, an actuator 16, and a control cabinet 17. When the intercooled cycle gas turbine is started, the bypass system 12 is put into operation, and the control cabinet 17 issues a control command to control the control valve through the actuator 16, so that the control valve is in a state of "Open" state; during the startup process, since a bypass system 12 is added between the intercooler inlet transition section 9 and the intercooler outlet transition section 10, and the flow resistance of the bypass system 12 is small, most of the air flowing out of the low-pressure compressor is directly sucked into the high-pressure compressor through the bypass system 12, so that the high-pressure rotor reaches the ignition speed faster, and the air flow entering the combustion chamber reaches the minimum value. At this time, the normal ignition and stable combustion of the combustion chamber can be guaranteed. After the high-pressure rotor speed reaches a certain speed value, the control valve 15 is gradually closed until the control valve is finally in the "closed" state.

[0020] Among them, the flow capacity of the cross-sectional area of ​​the transition flow channel 13 at the outlet of the low-pressure compressor should not be less than the air flow value required for the ignition of the combustion chamber, and the flow capacity of the cross-sectional area of ​​the transition flow channel 14 at the inlet of the high-pressure compressor should not be less than the air flow value required for the ignition of the combustion chamber.

[0021] The actuator 16 includes but is not limited to a mechanical transmission device capable of transmitting motion. The bypass system 12 can be operated not only during the startup process, but also during the operation of the intercooled cycle gas turbine 11, even if the intercooler 8, the supporting circulating cooling system, and other systems fail, the intercooled cycle gas turbine 11 can be converted from a "failure" mode to a simple cycle gas turbine mode to continue to operate.

[0022] The invention can meet the technical requirements for faster startup of an intercooled cycle gas turbine device and has the characteristics of compact structure, reasonable layout, simple bypass system, convenient operation, high reliability and the like.

[0023] 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. An intercooler cycle gas turbine with a bypass system, comprising 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), wherein an intercooler inlet transition section (9) is provided between the low-pressure compressor (2) and the intercooler (8), and an intercooler outlet transition section (10) is provided between the intercooler (8) and the high-pressure compressor (3); characterized in that: A bypass system (12) is provided between an intercooler inlet transition section (9) and an intercooler outlet transition section (10); the bypass system (12) comprises a low-pressure compressor outlet transition flow channel (13), a high-pressure compressor inlet transition flow channel (14), a control valve (15), an actuator (16) and a control cabinet (17); the low-pressure compressor outlet transition flow channel (13) and the high-pressure compressor inlet transition flow channel (14) are respectively connected to the intercooler inlet transition section (9) and the intercooler outlet transition section (10); the control cabinet (17) issues a control instruction according to a set control program, and realizes the action of the control valve (15) through the actuator (16), so that the control valve (15) is in an "open" state and a "closed" state.

2. The indirect cooling cycle gas turbine with a bypass system according to claim 1, characterized in that: The flow capacity of the cross-sectional area of ​​the low-pressure compressor outlet transition flow channel (13) is not less than the air flow value required for combustion chamber ignition.

3. The indirect cooling cycle gas turbine with a bypass system according to claim 1, characterized in that: The flow capacity of the flow channel cross-sectional area of ​​the high-pressure compressor inlet transition flow channel (14) is not less than the air flow value required for combustion chamber ignition.

4. The indirect cooling cycle gas turbine with a bypass system according to claim 1, characterized in that: The actuator (16) includes but is not limited to a mechanical transmission device capable of transmitting motion.

5. The indirect cooling cycle gas turbine with a bypass system according to claim 1, characterized in that: The bypass system (12) includes but is not limited to operating during the startup process of the intercooled cycle gas turbine.

6. The indirect cooling cycle gas turbine with a bypass system according to claim 1, characterized in that: When the intercooler (8) and the associated circulating cooling system and other systems fail during the operation of the intercooled cycle gas turbine, the bypass system (12) can convert the intercooled cycle gas turbine (11) from a "failure" mode to a simple cycle gas turbine mode to continue operation.

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