Bearing cooling device of gas turbine

Abstract

The invention provides a gas turbine bearing cooling device, and relates to the technical field of gas turbine cooling, the gas turbine bearing cooling device comprises a rotating shaft, the rotating shaft is sequentially sleeved with a gas compressor, a turbine and a combustion chamber; the guide vane assembly is arranged at the outlet end of the combustion chamber and used for guiding the high-heat gas into a turbine; the bearing is mounted in the bearing seat assembly; the heat guide part is arranged between the guide vane assembly and the bearing seat assembly; according to the gas turbine bearing cooling device provided by the invention, the heat of high-heat gas at the outlet of the combustion chamber is guided to the far-end area of the bearing seat assembly through the heat guide part. And the first end part of the heat guide part is fixedly connected with the guide vane assembly, so that an effective transfer starting point of heat is ensured. And the second end part is connected with the bearing seat assembly through the adjustable branch parts, and the heat can be uniformly distributed on the bearing seat assembly through the design of the branch parts, so that the local overheating phenomenon is avoided.

Description

Technical Field

[0001] The invention relates to the technical field of gas turbine cooling, and in particular to a bearing cooling device of a gas turbine. Background Art

[0002] The gas turbine uses a continuously flowing gas as a working fluid to drive the impeller to rotate at high speed, converting the energy of the fuel into useful work. It is a rotating impeller heat engine. It mainly includes three parts: the compressor, the combustion chamber, and the turbine: the compressor inhales air from the external atmosphere and compresses it to increase the pressure, and the air temperature is also increased accordingly; the compressed air is sent to the combustion chamber to mix with the injected fuel and burn to generate high-temperature and high-pressure gas; then it enters the turbine to expand and do work, driving the turbine to drive the compressor and the external load rotor to rotate at high speed, which can realize the conversion of part of the chemical energy of the gas or liquid fuel into mechanical work and heat energy, and can output electrical energy by connecting to a generator. Non-contact bearings (such as gas bearings) are increasingly commonly used in some high-speed occasions due to their small friction coefficient and friction torque, high motion accuracy, etc. Gas bearings rely on the pressure gas film in the bearing gap to support the rotor system. Gas bearings can be used in gas turbines. When the gas turbine is working, the gas temperature at the combustion chamber outlet is as high as 900°C. The high temperature here will be directly transmitted to the nearby bearings and bearing seats. Due to the local high temperature and uneven heat distribution, the bearings and bearing seats will be irregularly deformed. When the bearing is a gas bearing, it will also cause the seal of the gas bearing to fail, making the gas film of the gas bearing unstable and the supporting force insufficient, affecting the stable operation of the gas bearing. Summary of the invention

[0003] The present invention provides a bearing cooling device for a gas turbine, which is used to solve at least one of the technical problems raised by the above background technology.

[0004] In order to solve the above technical problems, the present invention provides a bearing cooling device for a gas turbine, comprising: a rotating shaft, on which a compressor, a turbine and a combustion chamber are sequentially sleeved; a guide vane assembly, disposed at the outlet end of the combustion chamber, for guiding the high-temperature gas into the turbine; A bearing seat assembly and a bearing, wherein the bearing is installed in the bearing seat assembly; The heat guide component is arranged between the guide vane assembly and the bearing seat assembly.

[0005] Preferably, the heat guiding component includes a first end, a second end and a connecting portion connecting the two, wherein the first end is fixedly connected to the guide vane assembly, and the second end is connected to a position of the bearing seat assembly away from the bearing through an adjustable branch portion, for guiding the heat at the combustion chamber outlet to the distal area of ​​the bearing seat assembly to achieve uniform heat distribution.

[0006] Preferably, the adjustable branch portion is distributed in a ring shape or a spoke shape, and the end of the adjustable branch portion is connected to several discrete positions of the bearing seat assembly to disperse the heat conduction path. An electromagnetic drive mechanism is provided at the end of the adjustable branch portion. The electromagnetic drive mechanism adjusts the contact angle between the adjustable branch portion and the bearing seat assembly according to the feedback signal of the temperature sensor to dynamically distribute the heat conduction direction.

[0007] Preferably, a ring groove is fixedly provided on the contact surface between the second end of the heat guiding component and the bearing seat assembly, and a plurality of small groove structures are spaced apart on one side of the ring groove to reduce the contact area and lower the heat conduction efficiency.

[0008] Preferably, the material of the heat conducting component is a high thermal conductivity metal composite material, and the surface of the heat conducting component is coated with a high temperature resistant and anti-oxidation coating.

[0009] Preferably, the material of the heat conducting component is a high thermal conductivity metal composite material, and the surface of the heat conducting component is coated with a high temperature resistant and anti-oxidation coating.

[0010] Preferably, the outer surface of the bearing seat assembly is provided with heat dissipation fins, and the distribution density of the heat dissipation fins increases in a direction away from the bearing to enhance the heat dissipation capacity of the distal area.

[0011] Preferably, the active cooling system includes an internal spiral cooling channel and an external liquid cooling circuit, wherein the spiral cooling channel is connected to the compressed gas of the compressor, and the liquid cooling circuit drives the coolant circulation through a micro pump and is electrically connected to the power generation module of the thermoelectric material layer to achieve energy recovery and coordinated heat dissipation.

[0012] Preferably, the coolant of the liquid cooling circuit is a liquid metal alloy, and its flow path is arranged crosswise with the spiral cooling channel. The heat absorbed by the liquid metal is transferred to the air intake end of the compressor through a heat exchanger to achieve waste heat recycling.

[0013] Preferably, it also includes a temperature monitoring module and a feedback control system, wherein the temperature monitoring module includes a plurality of temperature sensors distributed at key positions of the bearing seat assembly, and the feedback control system dynamically adjusts the gas flow of the active cooling system according to the sensor data, and dynamically adjusts the heat conduction efficiency of the adjustable branch part of the heat guide component. Machine learning algorithm unit, which predicts the trend of heat load changes based on historical data; The dynamic adjustment unit synchronously controls the electromagnetic drive mechanism of the adjustable branch part, the flow rate of the liquid cooling circuit and the power generation efficiency of the thermoelectric material layer according to the sensor data and the prediction results.

[0014] Compared with the prior art, the beneficial effects of the present invention are as follows: The gas turbine bearing cooling device provided by the present invention guides the heat of the high-temperature gas at the outlet of the combustion chamber to the distal region of the bearing housing assembly through a heat guiding component. The first end of the heat guiding component is fixedly connected to the guide vane assembly, ensuring the starting point of effective heat transfer. The second end is connected to the bearing housing assembly through adjustable branch parts, and the design of these branch parts enables the heat to be evenly distributed on the bearing housing assembly, avoiding local overheating.

[0015] Beneficial effects: Uniform heat distribution: Through the design of the heat guiding component, uniform heat distribution is achieved, effectively reducing the thermal stress of the bearing housing assembly and its internal bearings, and improving the reliability and service life of the equipment.

[0016] Flexible adjustment: The introduction of adjustable branch parts enables the heat conduction path to be adjusted according to actual needs, enhancing the adaptability and flexibility of the system; In the gas turbine of the present invention, a heat guiding component is arranged between the outlet end of the combustion chamber and the bearing housing that originally overlapped each other, guiding the heat at the outlet of the combustion chamber to the part of the bearing housing far from the bearing, so that the heat conducted to the bearing housing can be better evenly distributed in the bearing housing, making the bearing and the bearing housing near it evenly heated, and then evenly deformed, avoiding the formation of local high temperature at the bearing, and overcoming the defects such as air leakage, coaxiality change, uneven air film, and shaft seizure caused by irregular deformation of the gas bearing due to uneven heat absorption. Brief description of the drawings

[0017] In order to more clearly illustrate the technical solutions in the present invention or the prior art, the following will briefly introduce the drawings required for the description of the embodiments or the prior art. Obviously, the drawings in the following description are some embodiments of the present invention. For those of ordinary skill in the art, without creative efforts, other drawings can also be obtained based on these drawings.

[0018] Figure 1 is a front sectional schematic view of a bearing cooling device of a gas turbine of the present invention; Figure 2 is Figure 1 a partial enlarged schematic view of the structure at A in Figure 3 is a front view schematic view of the external liquid cooling circuit of the present invention.

[0019] Reference numerals: 1. Rotating shaft; 2. Compressor; 3. Turbine; 4. Combustion chamber; 5. Guide vane assembly; 6. Bearing seat assembly; 7. Bearing; 8. Heat guide component; 81. First end; 82. Second end; 821. Annular groove; 822. Small groove structure; 83. Connecting part; 84. Adjustable branch part; 841. Electromagnetic drive mechanism; 9. Active cooling system; 91. Internal spiral cooling channel; 92. External liquid cooling circuit; 93. Micro pump; 94. Power generation module; 95. Heat exchanger; 10. Temperature monitoring module; 101. Temperature sensor; 11. Feedback control system. DETAILED DESCRIPTION

[0020] In order to make the purpose, technical solution and advantages of the present invention clearer, the technical solution of the present invention will be clearly and completely described below in conjunction with the drawings of the present invention. Obviously, the described embodiments are part of the embodiments of the present invention, not all of the embodiments. Based on the embodiments of the present invention, all other embodiments obtained by ordinary technicians in this field without creative work are within the scope of protection of the present invention.

[0021] The preferred embodiments of the present invention are described below in conjunction with the accompanying drawings. It should be understood that the preferred embodiments described herein are only used to illustrate and explain the present invention, and are not used to limit the present invention.

[0022] In addition, in the present invention, the descriptions of "first", "second", etc. are only used for descriptive purposes, and do not specifically refer to the order or sequence, nor are they used to limit the present invention. They are only used to distinguish components or operations described with the same technical terms, and cannot be understood as indicating or implying their relative importance or implicitly indicating the number of technical features indicated. Therefore, the features defined as "first" and "second" may explicitly or implicitly include at least one of the features. In addition, the technical solutions and technical features between the various embodiments can be combined with each other, but they must be based on the ability of ordinary technicians in the field to implement them. When the combination of technical solutions is contradictory or cannot be implemented, it should be considered that such a combination of technical solutions does not exist and is not within the scope of protection required by the present invention.

[0023] The present invention provides the following embodiments Example 1 An embodiment of the present invention provides a bearing cooling device for a gas turbine, such as Figure 1 , Figure 2 As shown, it comprises: a rotating shaft 1, on which a compressor 2, a turbine 3 and a combustion chamber 4 are sequentially sleeved; A guide vane assembly 5 is provided at the outlet end of the combustion chamber 4 and is used to guide the high-temperature gas into the turbine 3; A bearing seat assembly 6 and a bearing 7, wherein the bearing 7 is installed in the bearing seat assembly 6; The heat guide component 8 is arranged between the guide vane assembly 5 and the bearing seat assembly 6 .

[0024] The heat guiding component 8 includes a first end 81, a second end 82 and a connecting portion 83 connecting the two, wherein the first end 81 is fixedly connected to the guide vane assembly 5, and the second end 82 is connected to a position of the bearing seat assembly 6 away from the bearing 7 through an adjustable branch portion 84, and is used to guide the heat at the outlet of the combustion chamber 4 to the distal area of ​​the bearing seat assembly 6 to achieve uniform heat distribution.

[0025] The working principle and beneficial effects of the above technical solution are as follows: Working principle: The gas turbine bearing cooling device provided in this embodiment guides the heat of the high-temperature gas at the outlet of the combustion chamber 4 to the distal region of the bearing seat assembly 6 through the heat guide component 8. The first end 81 of the heat guide component 8 is fixedly connected to the guide vane assembly 5, ensuring an effective starting point for heat transfer. The second end 82 is connected to the bearing seat assembly 6 through an adjustable branch portion 84. The design of these branch portions 84 enables heat to be evenly distributed on the bearing seat assembly 6, avoiding local overheating.

[0026] Beneficial effects: Uniform heat distribution: The design of the heat guide component 8 achieves uniform heat distribution, effectively reduces the thermal stress of the bearing seat assembly 6 and its internal bearing 7, and improves the reliability and service life of the equipment.

[0027] Flexible adjustment: The introduction of the adjustable branch part 84 allows the heat conduction path to be adjusted according to actual needs, thereby enhancing the adaptability and flexibility of the system; The gas turbine of the present invention is provided with a heat guiding component 8 between the outlet end of the combustion chamber 4 and the bearing 7 seat which are originally overlapped with each other, so as to guide the heat at the outlet of the combustion chamber 4 to the part of the bearing 7 seat far away from the bearing 7, so that the heat conducted to the bearing 7 seat can be better evenly distributed in the bearing 7 seat, so that the bearing 7 and the bearing 7 seats near it are heated evenly, and then deformed evenly, avoiding the formation of local high temperature at the bearing 7, and overcoming the defects of irregular deformation of the gas bearing 7 due to uneven heating, which in turn causes gas leakage, coaxiality change, uneven gas film, and jamming of the rotating shaft 1.

[0028] Example 2 On the basis of Example 1, Figure 1-Figure 2As shown, the adjustable branch portion 84 is distributed in a ring shape or a spoke shape, and the end of the adjustable branch portion 84 is connected to several discrete positions of the bearing seat assembly 6 to disperse the heat conduction path. An electromagnetic drive mechanism 841 is provided at the end of the adjustable branch portion 84. The electromagnetic drive mechanism 841 adjusts the contact angle between the adjustable branch portion 84 and the bearing seat assembly 6 according to the feedback signal of the temperature sensor 101 to dynamically distribute the heat conduction direction.

[0029] The second end 82 of the heat guiding component 8 is fixedly provided with an annular groove 821 on the contact surface with the bearing seat assembly 6. The second end 82 of the heat guiding component 8 is located on one side of the annular groove 821 and has multiple small groove structures 822 spaced apart to reduce the contact area and lower the heat conduction efficiency.

[0030] The material of the heat conducting component 8 is a high thermal conductivity metal composite material, and the surface of the heat conducting component 8 is coated with a high temperature resistant and anti-oxidation coating.

[0031] The material of the heat conducting component 8 is a high thermal conductivity metal composite material, and the surface of the heat conducting component 8 is coated with a high temperature resistant and anti-oxidation coating.

[0032] The working principle and beneficial effects of the above technical solution are as follows: Working principle: Based on Example 1, this embodiment further adjusts the contact angle between the adjustable branch part 84 and the bearing seat assembly 6 through the electromagnetic drive mechanism 841 to achieve dynamic heat distribution. At the same time, the design of the annular groove 821 and the small groove structure 822 of the second end 82 reduces the contact area with the bearing seat assembly 6 and reduces unnecessary heat conduction. The combination of high thermal conductivity metal composite material and high temperature resistant and anti-oxidation coating ensures the efficient and stable operation of the heat guide component 8.

[0033] Beneficial effects: Dynamic heat management: The introduction of the electromagnetic drive mechanism 841 enables the system to dynamically adjust the heat conduction direction according to the feedback signal of the temperature sensor 101, thereby improving the accuracy and response speed of heat management.

[0034] Reducing heat conduction efficiency: The design of the annular groove 821 and the small groove structure 822 effectively reduces unnecessary heat conduction and protects the bearing seat assembly 6 from being affected by excessively high temperatures.

[0035] Material optimization: The combination of high thermal conductivity metal composite material and high temperature resistant and anti-oxidation coating improves the durability and thermal conduction efficiency of the heat guide component 8.

[0036] Example 3 On the basis of Example 2, Figure 1 , Figure 2 and Figure 3As shown, the outer surface of the bearing seat assembly 6 is provided with heat dissipation fins 61, and the distribution density of the heat dissipation fins 61 increases in the direction away from the bearing 7 to enhance the heat dissipation capacity of the distal area.

[0037] The active cooling system 9 includes an internal spiral cooling channel 91 and an external liquid cooling circuit 92. The spiral cooling channel 91 is connected to the compressed gas of the compressor 2. The liquid cooling circuit 92 drives the coolant circulation through a micro pump 93 and is electrically connected to the power generation module 94 of the thermoelectric material layer 831 to achieve energy recovery and coordinated heat dissipation. The coolant of the liquid cooling circuit 92 is a liquid metal alloy, and its flow path is arranged crosswise with the spiral cooling channel 91. The heat absorbed by the liquid metal is transferred to the intake end of the compressor 2 through the heat exchanger 95, thereby realizing the recycling of waste heat.

[0038] The working principle and beneficial effects of the above technical solution are as follows: Working principle: Based on Example 2, this embodiment adds heat dissipation fins 61 to enhance the heat dissipation capacity of the remote area. At the same time, an active cooling system 9 is introduced to achieve double cooling through the internal spiral cooling channel 91 and the external liquid cooling circuit 92. The liquid metal alloy in the liquid cooling circuit 92 is used as a coolant, and the absorbed heat is transferred to the intake end of the compressor 2 through the heat exchanger 95, thereby realizing the reuse of waste heat.

[0039] Beneficial effects: Enhanced heat dissipation capability: The design of the heat dissipation fins 61 significantly improves the heat dissipation efficiency of the distal region of the bearing seat assembly 6 and reduces the temperature of the device.

[0040] Double cooling mechanism: The combination of the internal spiral cooling channel 91 and the external liquid cooling circuit 92 provides an efficient double cooling mechanism to ensure the stable operation of the equipment.

[0041] Waste heat recycling: Liquid metal alloy is used as a coolant, which not only improves the cooling efficiency, but also realizes the recycling of waste heat through the heat exchanger 95, thereby improving energy utilization.

[0042] Example 4 On the basis of Example 2, Figure 1 , Figure 3 , and also includes a temperature monitoring module 10 and a feedback control system. The temperature monitoring module 10 includes a plurality of temperature sensors 101 distributed at key positions of the bearing seat assembly 6. The feedback control system dynamically adjusts the gas flow of the active cooling system 9 according to the sensor data, and dynamically adjusts the thermal conductivity of the adjustable branch portion 84 of the heat guide component 8. Machine learning algorithm unit, which predicts the trend of heat load changes based on historical data; The dynamic adjustment unit synchronously controls the electromagnetic drive mechanism 841 of the adjustable branch part 84, the flow rate of the liquid cooling circuit 92 and the power generation efficiency of the thermoelectric material layer 831 according to the sensor data and the prediction results.

[0043] The working principle and beneficial effects of the above technical solution are as follows: Working principle: Based on Example 2, this embodiment adds a temperature monitoring module 10 and a feedback control system. The temperature monitoring module 10 monitors the temperature of key positions of the bearing seat assembly 6 in real time through multiple temperature sensors 101. The feedback control system dynamically adjusts the gas flow of the active cooling system 9 and the thermal conductivity of the adjustable branch part 84 of the heat guide component 8 according to the sensor data. At the same time, a machine learning algorithm unit is introduced to predict the trend of heat load changes based on historical data, further improving the intelligence and response speed of the system.

[0044] Beneficial effects: Intelligent adjustment: The introduction of the feedback control system enables the system to intelligently adjust the cooling efficiency and heat conduction path according to real-time monitoring data, thereby improving the stability and reliability of the system.

[0045] Predictive maintenance: The application of machine learning algorithm units enables the system to predict the trend of heat load changes based on historical data, providing strong support for preventive maintenance of equipment.

[0046] Comprehensive performance improvement: Through the comprehensive application of temperature monitoring, intelligent regulation and predictive maintenance, this embodiment significantly improves the overall performance and operating efficiency of the gas turbine bearing cooling device.

[0047] Finally, it should be noted that the above embodiments are only used to illustrate the technical solutions of the present invention, rather than to limit it. Although the present invention has been described in detail with reference to the aforementioned embodiments, those skilled in the art should understand that they can still modify the technical solutions described in the aforementioned embodiments, or make equivalent replacements for some of the technical features therein. However, these modifications or replacements do not deviate the essence of the corresponding technical solutions from the spirit and scope of the technical solutions of the embodiments of the present invention.

Claims

1. A bearing cooling device for a gas turbine, characterized in that: include: A rotating shaft (1), on which a compressor (2), a turbine (3) and a combustion chamber (4) are sequentially sleeved and mounted; A guide vane assembly (5), arranged at the outlet end of the combustion chamber (4), and used for guiding high-temperature gas into the turbine (3); A bearing seat assembly (6) and a bearing (7), wherein the bearing (7) is installed in the bearing seat assembly (6); A heat guide component (8) is arranged between the guide vane assembly (5) and the bearing seat assembly (6).

2. A bearing cooling device for a gas turbine according to claim 1, characterized in that: The heat guiding component (8) comprises a first end (81), a second end (82) and a connecting portion (83) connecting the first end (81) and the guide vane assembly (5), and the second end (82) is connected to a position of the bearing seat assembly (6) away from the bearing (7) through an adjustable branch portion (84), so as to guide the heat at the outlet of the combustion chamber (4) to the distal end region of the bearing seat assembly (6) to achieve uniform heat distribution.

3. A bearing cooling device for a gas turbine according to claim 2, characterized in that: The adjustable branch portion (84) is distributed in a ring shape or a spoke shape, and the end of the adjustable branch portion (84) is connected to a plurality of discrete positions of the bearing seat assembly (6) to disperse the heat conduction path. An electromagnetic drive mechanism (841) is provided at the end of the adjustable branch portion (84), and the electromagnetic drive mechanism (841) adjusts the contact angle between the adjustable branch portion (84) and the bearing seat assembly (6) according to the feedback signal of the temperature sensor (101) to dynamically distribute the heat conduction direction.

4. A gas turbine bearing cooling device according to claim 3, characterized in that: The contact surface between the second end portion (82) of the heat guiding component (8) and the bearing seat assembly (6) is fixedly provided with an annular groove (821); the second end portion (82) of the heat guiding component (8) is located on one side of the annular groove (821) and has a plurality of small groove structures (822) spaced apart from each other, so as to reduce the contact area and lower the heat conduction efficiency.

5. A gas turbine bearing cooling device according to claim 4, characterized in that: The material of the heat-conducting component (8) is a high-thermal-conductivity metal composite material, and its surface is coated with a high-temperature-resistant and anti-oxidation coating.

6. A gas turbine bearing cooling device according to claim 5, characterized in that: The material of the heat-conducting component (8) is a high-thermal-conductivity metal composite material, and its surface is coated with a high-temperature-resistant and anti-oxidation coating.

7. A gas turbine bearing cooling device according to claim 6, characterized in that: The outer surface of the bearing seat assembly (6) is provided with heat dissipation fins (61), and the distribution density of the heat dissipation fins (61) increases in a direction away from the bearing (7) to enhance the heat dissipation capacity of the distal region.

8. A gas turbine bearing cooling device according to claim 2, characterized in that: The active cooling system (9) comprises an internal spiral cooling channel (91) and an external liquid cooling circuit (92), wherein the spiral cooling channel (91) is connected to the compressed gas of the compressor (2), and the liquid cooling circuit (92) drives the circulation of the coolant through a micro pump (93) and is electrically connected to the power generation module (94) of the thermoelectric material layer (831) to achieve energy recovery and coordinated heat dissipation.

9. A gas turbine bearing cooling device according to claim 8, characterized in that: The coolant of the liquid cooling circuit (92) is a liquid metal alloy, and its flow path is arranged crosswise with the spiral cooling channel (91). The heat absorbed by the liquid metal is transferred to the air intake end of the compressor (2) through the heat exchanger (95), thereby realizing waste heat recycling.

10. A bearing cooling device for a gas turbine according to claim 9, characterized in that: The system also includes a temperature monitoring module (10) and a feedback control system. The temperature monitoring module (10) includes a plurality of temperature sensors (101) distributed at key positions of the bearing seat assembly (6). The feedback control system dynamically adjusts the gas flow of the active cooling system (9) according to the sensor data, and dynamically adjusts the heat conduction efficiency of the adjustable branch portion (84) of the heat guide component (8). Machine learning algorithm unit, which predicts the trend of heat load changes based on historical data; The dynamic adjustment unit synchronously controls the electromagnetic drive mechanism (841) of the adjustable branch part (84), the flow rate of the liquid cooling circuit (92) and the power generation efficiency of the thermoelectric material layer (831) according to the sensor data and the prediction result.

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