Gas turbine and thermal power generation system

Abstract

This disclosure relates to a gas turbine and a thermal power generation system. The gas turbine includes a main compressor assembly, an auxiliary compressor, a cooling assembly, and a turbine assembly. The main compressor assembly includes a primary compression unit, a final compression unit, and multiple intermediate compression units located between the primary and final compression units. Each intermediate compression unit has an exhaust port communicating with its internal cavity. The intake port of the auxiliary compressor is connected to the exhaust port of one of the intermediate compression units via the cooling assembly. The exhaust port of the auxiliary compressor is connected to the internal chamber of the turbine assembly. The cooling assembly is disposed between the intermediate compression unit connected to the intake port of the auxiliary compressor and the turbine assembly, and is used to cool the gas before it enters the internal chamber of the turbine assembly.

Description

Technical Field

[0001] This disclosure relates to the field of thermal power generation system technology, and more specifically, to a gas turbine and a thermal power generation system. Background Technology

[0002] Gas turbines, as core equipment in modern power generation and aero-engines, are widely used in power, aerospace, and industrial fields. In related technologies, water or steam is generally used as the cooling medium to cool the turbine blade surface. This mixture is sprayed directly onto the turbine blade surface after mixing with the gas. While this method can achieve a certain cooling effect, it also causes problems such as corrosion and overload, which affect the service life of the turbine blades. Utility Model Content

[0003] The purpose of this disclosure is to provide a gas turbine and a thermal power generation system to solve the technical problems existing in the related art.

[0004] To achieve the above objectives, the first aspect of this disclosure provides a gas turbine, including a main compressor assembly, a secondary compressor, a cooling assembly, and a turbine assembly. The main compressor assembly includes a primary compression unit, a final compression unit, and a plurality of intermediate compression units located between the primary compression unit and the final compression unit. Each intermediate compression unit has an extraction port communicating with its internal cavity.

[0005] The air inlet of the auxiliary compressor is connected to the air extraction port of one of the intermediate compression units via the cooling assembly, and the exhaust port of the auxiliary compressor is connected to the internal chamber of the turbine assembly.

[0006] The cooling assembly is disposed between the intermediate compression unit, which is connected to the air inlet of the auxiliary compressor, and the turbine assembly, and is used to cool the gas before it enters the internal chamber of the turbine assembly.

[0007] Optionally, the cooling assembly includes a heat exchanger having a heat exchange chamber, a hot fluid inlet and a hot fluid outlet formed on the heat exchanger, a gas passage communicating with the hot fluid inlet and the hot fluid outlet in the heat exchange chamber, the hot fluid inlet communicating with the extraction port of the intermediate compression unit, and the hot fluid outlet communicating with the inlet of the auxiliary compressor.

[0008] Optionally, the heat exchanger also has a cooling medium inlet and a cooling medium outlet, as well as a cooling medium pipe located inside the heat exchanger and communicating with the cooling medium inlet and the cooling medium outlet respectively. The inner wall of the heat exchanger and the outer wall of the cooling medium pipe together restrict the gas passage.

[0009] Optionally, the cooling medium pipe is arranged in a curved shape within the heat exchange chamber.

[0010] Optionally, the gas pressure at the exhaust port of the auxiliary compressor is 1.1 to 1.2 times the gas pressure at the inlet of the auxiliary compressor.

[0011] Optionally, the gas turbine further includes a combustion chamber, the exhaust port of the final stage compression unit is connected to the inlet of the combustion chamber, and the outlet of the combustion chamber is connected to the internal chamber of the turbine assembly.

[0012] Optionally, the gas turbine further includes a flow divider, the flow divider having a flow divider cavity, an intake passage communicating with the flow divider cavity, and multiple exhaust passages. The intake passage is connected to the exhaust port of the auxiliary compressor, and the multiple exhaust passages are respectively connected to the internal chambers of the turbine assembly.

[0013] Optionally, the turbine assembly has multiple airflow inlets, each airflow inlet communicating with a different region of the internal chamber of the turbine assembly, and each exhaust channel communicating with each airflow inlet in a one-to-one correspondence.

[0014] A second aspect of this disclosure provides a thermal power generation system including a gas turbine as described above.

[0015] Optionally, the cooling assembly includes a heat exchanger, which also has a cooling medium inlet and a cooling medium outlet. The thermal power generation system includes a boiler and a cooling system. The cooling medium inlet of the heat exchanger is connected to the cooling system, and the cooling medium outlet of the heat exchanger is connected to the water inlet of the boiler.

[0016] Through the above technical solution, when cooling the turbine blades of the turbine assembly, the gas is compressed by the primary and intermediate compression units of the main compressor assembly, becoming high-temperature and high-pressure gas. It then enters the cooling assembly through the extraction port, and after being cooled by the cooling assembly, it becomes low-temperature and high-pressure gas, which then enters the inlet of the auxiliary compressor. After being compressed again by the auxiliary compressor, it enters the internal chamber of the turbine assembly from the exhaust port of the auxiliary compressor. In the above process, on the one hand, the setting of the cooling assembly can significantly reduce the temperature of the compressed gas, which is beneficial to the cooling of the turbine blades. On the other hand, the compressed gas flowing through the cooling assembly has a lower temperature, which can reduce the thermal expansion and heat loss of the gas during the compression process, thereby reducing the energy consumption during the compression process. Under the same input power, the auxiliary compressor can output more compressed gas with appropriate pressure and flow rate, thereby improving the compression efficiency.

[0017] On the other hand, since each intermediate compression unit is equipped with an extraction port, the gas pressure, temperature and other parameters of different intermediate compression units are different. In this way, compressed gas can be flexibly selected from different intermediate compression units according to the actual working conditions and cooling requirements. By selecting the appropriate extraction port, the gas most suitable for cooling requirements can be obtained, thereby improving the cooling efficiency of turbine blades while minimizing energy consumption.

[0018] Furthermore, compared to related technologies that use water or steam as a cooling medium and mix it with gas before directly spraying it onto the turbine blade surface to cool the turbine blades, this solution utilizes gas extracted from the intermediate compression unit of the main compressor assembly, which is then pressurized by the auxiliary compressor before entering the turbine assembly. Using gas as a cooling medium avoids corrosion problems caused by water or steam and can effectively extend the service life of the turbine blades.

[0019] Other features and advantages of this disclosure will be described in detail in the following detailed description section. Attached Figure Description

[0020] The accompanying drawings are provided to further illustrate the present disclosure and form part of the specification. They are used together with the following detailed description to explain the present disclosure, but do not constitute a limitation thereof. In the drawings:

[0021] Figure 1 This is a schematic diagram of the structural connection of a gas turbine provided in an exemplary embodiment of the present disclosure;

[0022] Figure 2 This is a partial cross-sectional view of the main compressor assembly of a gas turbine provided in an exemplary embodiment of this disclosure.

[0023] Explanation of reference numerals in the attached figures

[0024] 1-Gas turbine; 10-Main compressor assembly; 11-Primary compression unit; 12-Final compression unit; 13-Intermediate compression unit; 100-Extraction port; 20-Secondary compressor; 30-Cooling assembly; 31-Heat exchanger; 32-Hot fluid inlet; 33-Hot fluid outlet; 34-Cooling medium inlet; 35-Cooling medium outlet; 36-Gas passage; 37-Cooling medium pipeline; 40-Turbine assembly; 50-Combustion chamber; 60-Branch component. Detailed Implementation

[0025] The specific embodiments of this disclosure will be described in detail below with reference to the accompanying drawings. It should be understood that the specific embodiments described herein are for illustration and explanation only and are not intended to limit this disclosure.

[0026] In this disclosure, unless otherwise stated, directional terms such as "up," "down," "left," and "right" are used to indicate orientation or positional relationships only for the convenience of describing this disclosure and simplifying the description, and are not intended to indicate or imply that the device or element referred to must have a specific orientation, or a specific orientation structure and operation, and therefore should not be construed as a limitation of this disclosure. The terms "inner" and "outer" refer to the inner and outer contours of the corresponding structures.

[0027] Additionally, it should be noted that the terms used, such as "first" and "second," are used to distinguish one element from another and do not indicate sequence or importance. Furthermore, in the description referring to the accompanying drawings, the same reference numerals in different drawings denote the same element.

[0028] In the description of this disclosure, it should also be noted that, unless otherwise expressly specified and limited, the terms "set up," "connect," "link," and "install" should be interpreted broadly. For example, they can refer to a fixed connection, a detachable connection, or an integral connection; they can refer to a direct connection or an indirect connection through an intermediate medium. Those skilled in the art can understand the specific meaning of the above terms in this disclosure according to the specific circumstances.

[0029] refer to Figures 1 to 2 As shown, the first aspect of this disclosure provides a gas turbine 1, including a main compressor assembly 10, an auxiliary compressor 20, a cooling assembly 30, and a turbine assembly 40. The main compressor assembly 10 includes a primary compression unit 11, a final compression unit 12, and a plurality of intermediate compression units 13 located between the primary compression unit 11 and the final compression unit 12. Each intermediate compression unit 13 has an exhaust port 100 communicating with its internal cavity. The intake port of the auxiliary compressor 20 is connected to the exhaust port 100 of one of the intermediate compression units 13 via the cooling assembly 30. The exhaust port of the auxiliary compressor 20 is connected to the internal chamber of the turbine assembly 40. The cooling assembly 30 is disposed between the intermediate compression unit 13 connected to the intake port of the auxiliary compressor 20 and the turbine assembly 40, and is used to cool the gas before it enters the internal chamber of the turbine assembly 40.

[0030] Through the above technical solution, when cooling the turbine blades of the turbine assembly 40, the gas is compressed by the primary compression unit 11 and the intermediate compression unit 13 of the main compressor assembly 10, and becomes high-temperature and high-pressure gas. It enters the cooling assembly 30 through the exhaust port 100. After being cooled by the cooling assembly 30, it becomes low-temperature and high-pressure gas and then enters the inlet of the auxiliary compressor 20. After being compressed again by the auxiliary compressor 20, it enters the internal chamber of the turbine assembly 40 from the exhaust port of the auxiliary compressor 20. In the above process, on the one hand, the setting of the cooling assembly 30 can significantly reduce the temperature of the compressed gas, which is beneficial to the cooling of the turbine blades. On the other hand, the compressed gas flowing through the cooling assembly 30 has a lower temperature, which can reduce the thermal expansion and heat loss of the gas during the compression process, thereby reducing the energy consumption during the compression process. Under the same input power, the auxiliary compressor 20 can output more compressed gas with appropriate pressure and flow rate, thereby improving the compression efficiency.

[0031] On the other hand, since each intermediate compression unit 13 is equipped with an extraction port 100, the gas pressure, temperature and other parameters of different intermediate compression units 13 are different. In this way, compressed gas can be flexibly extracted from different intermediate compression units 13 according to the actual working conditions and cooling requirements. By selecting the appropriate extraction port 100, the gas most suitable for cooling requirements can be obtained, thereby improving the cooling efficiency of the turbine blades while minimizing energy consumption.

[0032] Furthermore, compared to related technologies that use water or steam as a cooling medium and mix it with gas before directly spraying it onto the turbine blade surface to cool the turbine blades, this solution utilizes gas extracted from the intermediate compression unit 13 of the main compressor assembly 10, which is then pressurized by the auxiliary compressor 20 before entering the turbine assembly 40. By using gas as a cooling medium, the corrosion problems caused by water or steam are avoided, and the service life of the turbine blades can be effectively extended.

[0033] It should be noted that the pressure in different compression units gradually increases along the direction from the primary compression unit 11 to the final compression unit 12. Thus, in actual operation, the intermediate compression unit 13 corresponding to its pressure can be selected according to the usage conditions. In addition, the intermediate compression unit 13 mentioned above can be any compression unit other than the primary compression unit 11 and the final compression unit 12. This disclosure does not impose any restrictions on this. Specifically, it can be selected according to the actual required pressure. For example, if the pressure in the internal chamber of the turbine assembly 40 is high, the air extraction port 100 of the intermediate compression unit 13, which is relatively close to the final compression unit 12, can be selected as the air supply port. If the pressure in the internal chamber of the turbine assembly 40 is low, the air extraction port 100 of the intermediate compression unit 13, which is relatively close to the primary compression unit 11, can be selected as the air supply port.

[0034] In one exemplary embodiment provided in this disclosure, the main compressor assembly 10 includes a total of twenty compression units, and the air extraction port 100 of the tenth or eleventh intermediate compression unit 13 can be selected as the air supply port.

[0035] This disclosure does not limit the specific type of the cooling assembly 30 described above. For example, in one embodiment provided by this disclosure, the cooling assembly 30 may include a heat exchanger 31, which has a heat exchange chamber, a hot fluid inlet 32 ​​and a hot fluid outlet 33 formed on the heat exchanger 31, and a gas passage 36 communicating with the hot fluid inlet 32 ​​and the hot fluid outlet 33 in the heat exchange chamber. The hot fluid inlet 32 ​​is connected to the exhaust port 100 of the intermediate compression unit 13, and the hot fluid outlet 33 is connected to the air inlet of the auxiliary compressor 20. In this way, as the compressed gas flows into and out of the gas passage 36 and the hot fluid outlet 33 through the hot fluid inlet 32 ​​and the hot fluid outlet 33 formed on the heat exchanger 31, the heat in the compressed gas can be dissipated through the gas passage 36, thereby achieving cooling of the compressed gas.

[0036] Alternatively, in other embodiments provided in this disclosure, the cooling component 30 may also be a spray device or an intercooler.

[0037] To further enhance the cooling effect on the compressed gas, the heat exchanger 31 may also have a cooling medium inlet 34 and a cooling medium outlet 35, as well as a cooling medium pipe 37 located inside the heat exchanger 31 and connected to the cooling medium inlet 34 and the cooling medium outlet 35 respectively. The inner wall of the heat exchanger 31 and the outer wall of the cooling medium pipe 37 together define the gas passage 36. The cooling medium pipe 37 is distributed inside the heat exchanger 31, and its outer wall and the inner wall of the heat exchanger 31 together define the gas passage 36. This increases the contact area between the gas and the cooling medium pipe 37 and the inner wall of the heat exchanger 31 during the flow of the gas in the gas passage 36. In this way, the compressed gas can transfer heat to the inner wall of the heat exchanger 31 and the outer wall of the cooling medium pipe 37 during the flow of the compressed gas in the gas passage 36. At the same time, the cooling medium flowing in the cooling medium pipe 37 can carry away the heat, thereby achieving cyclic cooling of the compressed gas.

[0038] It should be noted that the cooling medium mentioned above can circulate within the cooling medium pipeline 37, thereby achieving continuous cooling of the compressed gas.

[0039] This disclosure does not limit the specific type of the heat dissipation medium. For example, in one exemplary embodiment provided in this disclosure, the cooling medium may be water.

[0040] Alternatively, in other embodiments provided in this disclosure, the cooling medium may also be a refrigerant, such as propane (R290), isobutane (R600a), or a non-azeotropic refrigerant mixture (R407C).

[0041] To further increase the heat exchange area with the compressed gas, in one exemplary embodiment provided in this disclosure, the cooling medium pipe 37 is arranged in a curved shape within the heat exchange chamber. Within the limited space inside the heat exchanger 31, the curved cooling medium pipe 37 allows the gas passage 36 it restricts to have a longer flow path, thereby increasing the residence time of the compressed air in the gas passage 36, and thus achieving the purpose of improving the heat exchange effect.

[0042] Alternatively, in another embodiment provided in this disclosure, the space of the heat exchange chamber can be divided into an outer ring chamber and an inner ring chamber, wherein the inner ring chamber is located inside the outer ring chamber, the cooling medium pipe 37 is disposed in the outer ring chamber (or the cooling medium is filled in the outer ring chamber), and the gas passage 36 is disposed in the inner ring chamber. In this way, when the compressed gas flows through the gas passage 36, it can exchange heat with the outer ring chamber located on its periphery and the cooling medium disposed in the outer ring chamber.

[0043] In other embodiments provided in this disclosure, the cooling medium pipe 37 may also be arranged in the heat exchange cavity in a coiled or spiral manner.

[0044] The appropriate pressurization of the auxiliary compressor 20 helps maintain the pressure balance of the entire gas turbine 1 system. In one embodiment provided in this disclosure, the gas pressure at the exhaust port of the auxiliary compressor 20 can be 1.1 to 1.2 times the gas pressure flowing out of the inlet of the auxiliary compressor 20. That is, the auxiliary compressor 20 can further compress the compressed gas discharged from the extraction port 100 of the intermediate compression unit 13. After the gas pressure extracted from the intermediate compression unit 13 of the main compressor is increased by 1.1 to 1.2 times by the auxiliary compressor 20, it can better match the working pressure requirements of the turbine assembly 40, avoiding the risk of insufficient cooling gas entering the turbine or insufficient work due to excessively low pressure, as well as the risk of increased system energy consumption and component damage due to excessively high pressure.

[0045] Optionally, the gas turbine 1 may also include a combustion chamber 50, with the exhaust port 100 of the final stage compression unit 12 connected to the inlet of the combustion chamber 50, and the outlet of the combustion chamber 50 connected to the internal chamber of the turbine assembly 40.

[0046] Optionally, the gas turbine 1 also includes a flow divider 60. The flow divider 60 has a flow divider cavity, an intake passage communicating with the flow divider cavity, and multiple exhaust passages. The intake passage communicates with the exhaust port of the auxiliary compressor 20, and the multiple exhaust passages communicate with the internal chambers of the turbine assembly 40. The multiple exhaust passages can guide gas to different parts of the turbine assembly 40, ensuring that each part of the turbine assembly 40 receives sufficient and uniform cooling and power gases. This guarantees a more uniform temperature distribution in different areas of the turbine assembly 40, preventing localized overheating or overcooling, thereby improving the reliability and stability of the turbine assembly 40 and reducing the risk of blade damage due to uneven gas distribution.

[0047] The flow divider 60 provided in this disclosure is also provided with a flow divider blade, which can realize the flow divider and guide function of compressed gas.

[0048] It should be noted that the compressed gas flowing into the intake passage can be evenly distributed among the multiple exhaust passages, or the compressed gas flow rates in the multiple exhaust passages can be different, and this disclosure does not impose any restrictions on this.

[0049] In one exemplary embodiment provided in this disclosure, the diverter 60 may be a multi-way valve.

[0050] Alternatively, in other embodiments provided in this disclosure, the diverter 60 may also be an airflow distributor or a diverter.

[0051] Because the temperature conditions vary at different locations within the turbine assembly 40—for example, the turbine blades rotate at different speeds in different areas, and the rotor and stator rotate at different speeds—optionally, the turbine assembly 40 can have multiple airflow inlets to achieve cooling of different areas of the turbine assembly 40. Each airflow inlet is connected to a different area of ​​the internal chamber of the turbine assembly 40, and each exhaust channel is connected to each airflow inlet in a corresponding manner. In other words, compressed gas can enter different areas of the internal chamber of the turbine assembly 40 through different exhaust channels and airflow inlets, thereby achieving directional cooling of the turbine blades located in different areas of the internal chamber of the turbine assembly 40, further improving the heat dissipation effect on the turbine blades.

[0052] It should be noted that the gas turbine 1 mentioned above may also include a controller and multiple temperature and pressure sensors. The controller is connected to multiple temperature and pressure sensors and the flow divider 60 respectively. Each temperature and pressure sensor can monitor the pressure at each airflow inlet, and thus control the flow divider 60 to divert the airflow according to the measured temperature and pressure parameters. For example, more compressed air can be allocated to the airflow inlet with higher pressure and temperature, and less compressed air can be allocated to the airflow inlet with lower pressure and temperature, thereby achieving adaptive cooling for different areas.

[0053] A second aspect of this disclosure provides a thermal power generation system including the gas turbine 1 described above. This thermal power generation system possesses all the beneficial effects of the gas turbine 1 described above, which will not be elaborated upon in this disclosure.

[0054] Optionally, the cooling assembly 30 includes a heat exchanger 31, which also has a cooling medium inlet 34 and a cooling medium outlet 35. The thermal power generation system includes a boiler and a cooling system (not shown). The cooling medium inlet 34 of the heat exchanger 31 is connected to the cooling system, and the cooling medium outlet 35 of the heat exchanger 31 is connected to the boiler's water inlet. In other words, during the cooling of the compressed gas, the cooling capacity of the cooling water in the thermal power generation system's cooling system is utilized, eliminating the need for additional equipment for supplying the cooling medium, thus reducing modification and cooling costs. Furthermore, the cooling medium can also recover heat from the compressed gas and return it to the boiler after exchanging heat with the compressed gas in the heat exchanger 31 (increasing the temperature of the water returning to the boiler), thereby increasing the amount of steam circulating in the waste heat boiler and further improving the overall efficiency of the gas-steam combined cycle.

[0055] The preferred embodiments of this disclosure have been described in detail above with reference to the accompanying drawings. However, this disclosure is not limited to the specific details of the above embodiments. Within the scope of the technical concept of this disclosure, various simple modifications can be made to the technical solutions of this disclosure, and these simple modifications all fall within the protection scope of this disclosure.

[0056] It should also be noted that the various specific technical features described in the above specific embodiments can be combined in any suitable manner without contradiction. In order to avoid unnecessary repetition, this disclosure will not describe the various possible combinations separately.

[0057] Furthermore, various different embodiments of this disclosure can be combined in any way, as long as they do not violate the spirit of this disclosure, they should also be regarded as the content disclosed in this disclosure.

Claims

1. A gas turbine, characterized in that, It includes a main compressor assembly, a secondary compressor, a cooling assembly, and a turbine assembly. The main compressor assembly includes a primary compression unit, a final compression unit, and multiple intermediate compression units located between the primary compression unit and the final compression unit. Each intermediate compression unit has an air extraction port that communicates with its internal cavity. The air inlet of the auxiliary compressor is connected to the air extraction port of one of the intermediate compression units via the cooling assembly, and the exhaust port of the auxiliary compressor is connected to the internal chamber of the turbine assembly. The cooling assembly is disposed between the intermediate compression unit, which is connected to the air inlet of the auxiliary compressor, and the turbine assembly, and is used to cool the gas before it enters the internal chamber of the turbine assembly.

2. The gas turbine according to claim 1, characterized in that, The cooling assembly includes a heat exchanger with a heat exchange chamber, a hot fluid inlet and a hot fluid outlet, and a gas passage communicating with the hot fluid inlet and the hot fluid outlet. The hot fluid inlet is connected to the extraction port of the intermediate compression unit, and the hot fluid outlet is connected to the inlet of the auxiliary compressor.

3. The gas turbine according to claim 2, characterized in that, The heat exchanger also has a cooling medium inlet and a cooling medium outlet, as well as a cooling medium pipe located inside the heat exchanger and connected to the cooling medium inlet and the cooling medium outlet respectively. The inner wall of the heat exchanger and the outer wall of the cooling medium pipe together restrict the gas passage.

4. The gas turbine according to claim 3, characterized in that, The cooling medium pipe is arranged in a curved shape inside the heat exchange chamber.

5. The gas turbine according to any one of claims 1-4, characterized in that, The gas pressure at the exhaust port of the auxiliary compressor is 1.1 to 1.2 times the gas pressure at the inlet of the auxiliary compressor.

6. The gas turbine according to any one of claims 1-4, characterized in that, The gas turbine also includes a combustion chamber, the exhaust port of the final stage compression unit is connected to the inlet of the combustion chamber, and the outlet of the combustion chamber is connected to the internal chamber of the turbine assembly.

7. The gas turbine according to any one of claims 1-4, characterized in that, The gas turbine also includes a flow divider, which has a flow divider cavity, an intake passage communicating with the flow divider cavity, and multiple exhaust passages. The intake passage is connected to the exhaust port of the auxiliary compressor, and the multiple exhaust passages are respectively connected to the internal chambers of the turbine assembly.

8. The gas turbine according to claim 7, characterized in that, The turbine assembly has multiple airflow inlets, each airflow inlet is connected to a different region of the internal chamber of the turbine assembly, and each exhaust channel is connected to each airflow inlet in a one-to-one correspondence.

9. A thermal power generation system, characterized in that, Includes the gas turbine according to any one of claims 1-8.

10. The thermal power generation system according to claim 9, characterized in that, The cooling assembly includes a heat exchanger, which also has a cooling medium inlet and a cooling medium outlet. The thermal power generation system includes a boiler and a cooling system. The cooling medium inlet of the heat exchanger is connected to the cooling system, and the cooling medium outlet of the heat exchanger is connected to the water inlet of the boiler.

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