A temperature control protection system applied to a high-temperature wall surface of a gas turbine

Abstract

The application discloses a temperature control protection system applied to a high-temperature wall surface of a gas turbine, which comprises a gas turbine body and a double-layer combustion chamber located in the gas turbine body, wherein the double-layer combustion chamber is internally provided with the temperature control protection system, a partition cavity is formed in the double-layer combustion chamber, and the temperature control protection system comprises an automatic wall surface replacement assembly, a detector, a liquid inlet ring, a cooling assembly and a liquid discharge ring; the automatic wall surface replacement assembly is internally provided on the inner wall of the double-layer combustion chamber, the automatic wall surface replacement assembly is composed of two groups of wall surface replacement devices, the two groups of wall surface replacement devices are symmetrically arranged in the double-layer combustion chamber, the detector is installed on the inner wall of the double-layer combustion chamber, the liquid inlet ring is installed at the right end of the double-layer combustion chamber, and the liquid discharge ring is installed at the left end of the double-layer combustion chamber. The temperature control protection system for the high-temperature wall surface of the gas turbine can realize temperature detection control of the interior of the combustion chamber and automatic replacement of the wall surface.

Description

TECHNICAL FIELD

[0001] The present application relates to the technical field of gas turbines, in particular to a temperature control protection system applied to the high-temperature wall surface of a gas turbine. BACKGROUND

[0002] A gas turbine, also known as a gas engine, is a device that converts high-temperature and high-pressure gas generated by fuel combustion into mechanical energy. It is a heat engine that mixes fuel with compressed air and burns it at high temperature and high pressure, then uses the high-temperature and high-pressure gas generated by combustion to drive the turbine to rotate, thereby providing power or driving mechanical devices. Gas turbines are commonly used for power devices in aircraft, power generation units in power plants, propulsion systems in ships, and industrial fields. It has the advantages of high efficiency, fast start-up, and lightweight, and is widely used in situations that require high power output and high efficiency.

[0003] However, the existing gas turbine has the following problems in the process of working: in a high-temperature environment, various materials inside the gas turbine, such as the combustion chamber wall plate, will be affected by high temperature. If the thermal stability of the material is insufficient, it may cause problems such as oxidation, creep or ablation of the material, thereby reducing the service life and performance of the material. In addition, the gas turbine usually adopts cooling technology to reduce the temperature of the high-temperature area to protect the key components from overheating. However, in a high-temperature state, the cooling effect may decrease, causing the temperature of the components to rise, thereby increasing the risk of thermal stress and thermal fatigue. Therefore, a corresponding technical solution is needed to solve the existing technical problems. SUMMARY

[0004] The purpose of the present application is to provide a temperature control protection system applied to the high-temperature wall surface of a gas turbine, which solves the problem that in a high-temperature environment, various materials inside the gas turbine, such as the combustion chamber wall plate, will be affected by high temperature. If the thermal stability of the material is insufficient, it may cause problems such as oxidation, creep or ablation of the material, thereby reducing the service life and performance of the material. In addition, the gas turbine usually adopts cooling technology to reduce the temperature of the high-temperature area to protect the key components from overheating. However, in a high-temperature state, the cooling effect may decrease, causing the temperature of the components to rise, thereby increasing the risk of thermal stress and thermal fatigue. This technical problem is solved.

[0005] In order to achieve the above object, the present application provides the following technical scheme: A temperature control protection system applied to a high-temperature wall surface of a gas turbine, comprising a gas turbine body and a double-layer combustion chamber located inside the gas turbine body, wherein the double-layer combustion chamber is internally provided with the temperature control protection system, a partition cavity is formed inside the double-layer combustion chamber, and the temperature control protection system comprises an automatic wall surface replacement assembly, a detector, a liquid inlet ring, a cooling assembly and a liquid outlet ring; the automatic wall surface replacement assembly is internally provided on the inner wall of the double-layer combustion chamber; the automatic wall surface replacement assembly is composed of two groups of wall surface replacement devices which are symmetrically arranged inside the double-layer combustion chamber; the detector is installed on the inner wall of the double-layer combustion chamber; the liquid inlet ring is installed at the right end of the double-layer combustion chamber; the liquid outlet ring is installed at the left end of the double-layer combustion chamber; and the cooling assembly is internally provided in the partition cavity and connected with the liquid inlet ring and the liquid outlet ring at both ends.

[0006] The wall surface replacement device comprises a shell, a storage roller, a nickel-based alloy wall plate, a storage cylinder, a winding roller and a driving motor; the shell is internally provided on the inner wall of the double-layer combustion chamber; the storage roller is divided into two groups and symmetrically installed in the shell; the nickel-based alloy wall plate is divided into two groups and wound on the two groups of storage rollers; the nickel-based alloy wall plate is laid along the inner wall of the double-layer combustion chamber and the outer end thereof passes through the storage cylinder; the storage cylinder is installed on the outer wall of the double-layer combustion chamber; the winding roller is connected with the outer end of the nickel-based alloy wall plate; and the driving motor is installed at one end of the storage cylinder and the power output end thereof is connected with the end portion of the winding roller.

[0007] The cooling assembly comprises a liquid guide cooling pipe and a cooling cover installed at the bottom of the liquid guide cooling pipe; a corrugated liquid guide plate is arranged inside the cooling cover; the corrugated liquid guide plate is attached to the double-layer combustion chamber; and cooling covers are also connected between adjacent two groups of liquid guide cooling pipes.

[0008] As a preferred mode of the present application, the nickel-based alloy wall plate adopts a nickel-based alloy material and an arc-shaped structure, and the radius of the nickel-based alloy is the same as the radius of the inner wall of the double-layer combustion chamber.

[0009] As a preferred mode of the present application, the detector comprises a mounting plate, a temperature sensor and an electrochemical sensor installed on the mounting plate; the temperature sensor and the electrochemical sensor are connected with a controller; and the controller is connected with the wall surface replacement device and the cooling assembly.

[0010] As a preferred mode of the present application, the liquid inlet ring comprises a ring body one, a ring-shaped water inlet pipe, a liquid inlet pipe and a drainage pipe; the ring body one is installed at the end of the double-layer combustion chamber; the ring-shaped water inlet pipe is installed on the ring body one; the liquid inlet pipe is installed at the top of the ring-shaped water inlet pipe; the drainage pipe is divided into a plurality of groups and uniformly installed at the inner end of the ring-shaped water inlet pipe; and the drainage pipe is connected with the liquid guide cooling pipe.

[0011] As a preferred way of the present application, the liquid discharge ring comprises a ring body two, a ring-shaped drain pipe, a liquid discharge pipe and a lead-out pipe, the ring body two is installed at the end of the double-layer combustion chamber, the ring-shaped drain pipe is installed on the ring body two, the liquid discharge pipe is installed at the bottom of the ring-shaped drain pipe, the lead-out pipe is divided into several groups and is uniformly installed on the inner side of the ring-shaped drain pipe, and the lead-out pipe is communicated with the liquid guide cooling pipe.

[0012] As a preferred way of the present application, the cooling cover is a hollow semi-cylindrical structure and is attached to the inner wall of the double-layer combustion chamber.

[0013] As a preferred way of the present application, the corrugated liquid guide plate is undulating and has a corrugated structure as a whole, and the corrugated liquid guide plate is in contact with the inner wall of the double-layer combustion chamber.

[0014] Compared with the prior art, the present application has the following advantages:

[0015] 1. The present application improves the inner wall structure of the existing combustion chamber of a gas turbine, and designs a high-temperature wall temperature control protection system for a gas turbine, which is built-in the combustion chamber of the gas turbine and comprises an automatic wall replacement assembly, a detector, a liquid inlet ring, a cooling assembly and a liquid discharge ring. The temperature inside the combustion chamber is detected, and when the temperature borne by the inner wall of the combustion chamber is too high, the cooling liquid is introduced into the cooling assembly through the liquid inlet ring, the inner wall of the combustion chamber is cooled by the cooling assembly, and the cooled liquid is discharged outside through the liquid discharge ring. In addition, the oxidation of the inner wall of the combustion chamber can be detected by the detector, and when the performance of the wall plate inside the combustion chamber decreases, the inner wall of the combustion chamber can be replaced by the automatic replacement assembly, so that the normal operation of the combustion chamber is ensured.

[0016] 2. The high-temperature wall temperature control protection system for a gas turbine designed by the present application can realize temperature detection control inside the combustion chamber and automatic replacement of the wall. BRIEF DESCRIPTION OF DRAWINGS

[0017] Figure 1 It is the overall structure diagram of the present application;

[0018] Figure 2 It is the structure diagram of the automatic wall replacement assembly of the present application;

[0019] Figure 3 It is the structure diagram of the liquid inlet ring of the present application;

[0020] Figure 4 It is the structure diagram of the liquid discharge ring of the present application;

[0021] Figure 5 It is the structure diagram of the cooling assembly of the present application;

[0022] Figure 6 The local structure diagram of the cooling assembly.

[0023] In the figure: 1, gas turbine body; 2, double-layer combustion chamber; 3, partition cavity; 4, automatic wall replacement assembly; 5, detector; 6, liquid inlet ring; 7, cooling assembly; 8, liquid outlet ring; 9, wall replacement device; 10, shell; 11, storage roller; 12, nickel-based alloy wall plate; 13, storage cylinder; 14, winding roller; 15, driving motor; 16, liquid guide cooling pipe; 17, cooling cover; 18, corrugated liquid guide plate; 19, mounting plate; 20, temperature sensor; 21, electrochemical sensor; 22, controller; 23, ring body one; 24, annular water inlet pipe; 25, liquid inlet pipe; 26, drainage pipe; 27, ring body two; 28, annular drainage pipe; 29, liquid outlet pipe; 30, outlet pipe. DETAILED DESCRIPTION

[0024] The technical solutions in the embodiments of the present application will be clearly and completely described below with reference to the drawings in the embodiments of the present application. Obviously, the described embodiments are only a part of the embodiments of the present application, rather than all the embodiments. Based on the embodiments in the present application, all other embodiments obtained by those skilled in the art without creative work fall within the scope of protection of the present application.

[0025] Please refer to Figures 1-6 The present application provides a technical solution: a temperature control protection system applied to the high-temperature wall surface of a gas turbine, which comprises a gas turbine body 1 and a double-layer combustion chamber 2 located inside the gas turbine body 1. The double-layer combustion chamber 2 is internally provided with a temperature control protection system, and a partition cavity 3 is formed inside the double-layer combustion chamber 2. The temperature control protection system comprises an automatic wall replacement assembly 4, a detector 5, a liquid inlet ring 6, a cooling assembly 7 and a liquid outlet ring 8. The automatic wall replacement assembly 4 is internally provided on the inner wall of the double-layer combustion chamber 2, and the automatic wall replacement assembly 4 is composed of two groups of wall replacement devices 9. The two groups of wall replacement devices 9 are symmetrically arranged in the double-layer combustion chamber 2. The detector 5 is installed on the inner wall of the double-layer combustion chamber 2. The liquid inlet ring 6 is installed at the right end of the double-layer combustion chamber 2. The liquid outlet ring 8 is installed at the left end of the double-layer combustion chamber 2. The cooling assembly 7 is internally provided in the partition cavity 3 and connected with the liquid inlet ring 6 and the liquid outlet ring 8 at both ends.

[0026] The wall surface changer 9 comprises a shell 10, receiving rollers 11, nickel-based alloy wall plates 12, a receiving cylinder 13, a winding roller 14 and a driving motor 15. The shell 10 is arranged on the inner wall of the double-layer combustion chamber 2. The receiving rollers 11 are symmetrically arranged in two groups in the shell 10. The nickel-based alloy wall plates 12 are symmetrically arranged in two groups and wound on the receiving rollers 11. The nickel-based alloy wall plates 12 are arranged along the inner wall of the double-layer combustion chamber 2 and the outer ends of the nickel-based alloy wall plates 12 pass through the receiving cylinder 13. The receiving cylinder 13 is arranged on the outer wall of the double-layer combustion chamber 2. The winding roller 14 is connected to the outer ends of the nickel-based alloy wall plates 12. The driving motor 15 is arranged on one end of the receiving cylinder 13 and the power output end of the driving motor 15 is connected to the end of the winding roller 14. When the nickel-based alloy wall plates 12 need to be replaced, the driving motor 15 drives the winding roller 14 to rotate. In the process of rotating, the used nickel-based alloy wall plates are pulled outwards and wound, so that the wall surface of the double-layer combustion chamber 2 is replaced, and the use effect of the double-layer combustion chamber 2 is ensured.

[0027] The cooling assembly 7 comprises liquid guide cooling pipes 16 and cooling covers 17 arranged on the bottom of the liquid guide cooling pipes 16. The cooling covers 17 are internally provided with corrugated liquid guide plates 18. The corrugated liquid guide plates 18 are attached to the double-layer combustion chamber 2. Adjacent two groups of the liquid guide cooling pipes 16 are connected with the cooling covers 17. The cooling liquid is guided into the cooling covers 17 and the corrugated liquid guide plates 18 through the liquid guide cooling pipes 16. The double-layer combustion chamber 2 is conveniently subjected to omnibearing temperature control treatment through the cooling covers 17 and the corrugated liquid guide plates 18.

[0028] Further improvement is that, as shown in Figure 1 The nickel-based alloy wall plates 12 are made of nickel-based alloy material and have arc-shaped structure. The curvature of the nickel-based alloy wall plates 12 is the same as the curvature of the inner wall of the double-layer combustion chamber 2. The nickel-based alloy has excellent high-temperature resistance and oxidation resistance and is commonly used for manufacturing the inner wall of the combustion chamber of the gas turbine.

[0029] Further improvement is that, as shown in Figure 1 The detector 5 comprises a mounting plate 19, temperature sensors 20 and electrochemical sensors 21 arranged on the mounting plate 19. The temperature sensors 20 and the electrochemical sensors 21 are connected with a controller 22. The controller 22 is connected with the wall surface changer 9 and the cooling assembly 7. The temperature inside the double-layer combustion chamber 2 can be detected through the temperature sensors 20. When the temperature is too high, the temperature is reduced. In addition, the oxidation degree of the wall surface of the double-layer combustion chamber 2 is detected through the electrochemical sensors 21. When the performance of the wall surface of the double-layer combustion chamber 2 is obviously decreased, the wall surface changer 4 can be used to replace the wall surface.

[0030] Further improvement is that, as shown in Figure 3As shown: the liquid inlet ring 6 includes ring body one 23, annular water inlet pipe 24, liquid inlet pipe 25 and drainage pipe 26, the ring body one 23 is installed at the end of the double-layer combustion chamber 2, the annular water inlet pipe 24 is installed on the ring body one 23, the liquid inlet pipe 25 is installed at the top of the annular water inlet pipe 24, the drainage pipe 26 is divided into several groups and is uniformly installed at the inner end of the annular water inlet pipe 24, the drainage pipe 26 is communicated with the liquid guide cooling pipe 16, and the liquid for cooling is guided into the cooling assembly 7 through the liquid inlet ring 6.

[0031] Further improved, as Figure 4 As shown: the liquid outlet ring 8 includes ring body two 27, annular drain pipe 28, liquid outlet pipe 29 and outlet pipe 30, the ring body two 27 is installed at the end of the double-layer combustion chamber 2, the annular drain pipe 28 is installed on the ring body two 27, the liquid outlet pipe 29 is installed at the bottom of the annular drain pipe 28, the outlet pipe 30 is divided into several groups and is uniformly installed at the inner side of the annular drain pipe 28, the outlet pipe 30 is communicated with the liquid guide cooling pipe 16, and the liquid after heat absorption is guided out through the liquid outlet ring 8.

[0032] Further improved, as Figure 6 As shown: the cooling cover 17 is a hollow semicylindrical structure and is attached to the inner wall of the double-layer combustion chamber 2, which is convenient for better temperature control treatment of the double-layer combustion chamber 2.

[0033] Specifically, the corrugated liquid guide plate 18 is undulating and has a corrugated structure as a whole, and the corrugated liquid guide plate 18 is in contact with the inner wall of the double-layer combustion chamber 2, which is convenient for better cooling treatment of the inner wall of the double-layer combustion chamber 2 by the liquid.

[0034] In use: the temperature sensor 20 can detect the internal temperature of the double-layer combustion chamber 2 in real time, and when the temperature is too high, the cooling liquid is guided into the cooling assembly 7 through the liquid inlet ring 6, the cooling liquid is guided into the cooling cover 17 and the corrugated liquid guide plate 18 through the liquid guide cooling pipe 16, the cooling cover 17 and the corrugated liquid guide plate 18 are convenient for omnidirectional temperature control treatment of the double-layer combustion chamber 2, the liquid after heat absorption is guided out through the liquid outlet ring 8, and the degree of oxidation of the wall surface of the double-layer combustion chamber 2 is detected by the electrochemical sensor 21, when the performance of the wall surface of the double-layer combustion chamber 2 is obviously decreased, the wall surface can be replaced by the automatic wall surface replacement assembly 4, when the nickel-based alloy wall plate 12 needs to be replaced, the driving motor 15 drives the winding roller 14 to rotate, and the used nickel-based alloy wall plate is pulled out and wound outside in the process of rotation, so that the purpose of replacing the wall surface of the double-layer combustion chamber 2 is achieved, and the use effect of the double-layer combustion chamber 2 is ensured.

[0035] In the description of the present application, it needs to be understood that the terms "coaxial", "bottom", "one end", "top", "middle", "the other end", "upper", "one side", "top", "inner", "front", "central", "both ends" and the like indicate the orientation or positional relationship based on the orientation or positional relationship shown in the drawings, which is only for the convenience of describing the present application and simplifying the description, and does not indicate or imply that the device or element referred to must have a particular orientation, be constructed and operated in a particular orientation, and therefore cannot be understood as a limitation of the present application.

[0036] In addition, the terms "first", "second", "third", "fourth" are only for descriptive purposes, and cannot be understood as indicating or implying relative importance or implicitly indicating the number of technical features indicated, so that the features with "first", "second", "third", "fourth" can be explicitly or implicitly include at least one of the features.

[0037] In the present application, unless otherwise explicitly specified and limited, the terms "mounting", "setting", "connecting", "fixing", "screwed" and the like should be understood in a broad sense, for example, it can be fixedly connected, or it can be detachably connected, or it can be integrated; it can be mechanically connected, or it can be electrically connected; it can be directly connected, or it can be indirectly connected through an intermediate medium; it can be the internal communication of two elements or the interaction relationship between two elements, unless otherwise explicitly limited, the above-mentioned terms in the present application can be understood according to the specific meaning of the above-mentioned terms in the present application by the person skilled in the art.

[0038] Finally, it should be pointed out that: the above-mentioned only for the preferred embodiments of the present application, and does not limit the present application, although the present application has been described in detail with reference to the foregoing embodiments, for the person skilled in the art, it still can modify the technical solutions recorded in the foregoing embodiments, or make equivalent replacement for part of the technical features. Any modification, equivalent replacement, improvement, etc. made within the spirit and principles of the present application shall be included in the protection scope of the present application.

Claims

1. A temperature control protection system for high-temperature walls of a gas turbine, comprising a gas turbine body (1) and a double-layer combustion chamber (2) located inside the gas turbine body (1), wherein the double-layer combustion chamber (2) has a built-in temperature control protection system, characterized in that: The double-layer combustion chamber (2) has a cavity (3) inside. The temperature control protection system includes an automatic wall replacement assembly (4), a detector (5), an inlet ring (6), a cooling assembly (7), and a drain ring (8). The automatic wall replacement assembly (4) is built into the inner wall of the double-layer combustion chamber (2). The automatic wall replacement assembly (4) consists of two sets of wall replacement devices (9). The two sets of wall replacement devices (9) are symmetrically arranged in the double-layer combustion chamber (2). The detector (5) is installed on the inner wall of the double-layer combustion chamber (2). The inlet ring (6) is installed at the right end of the double-layer combustion chamber (2). The drain ring (8) is installed at the left end of the double-layer combustion chamber (2). The cooling assembly (7) is built into the cavity (3) and its two ends are connected to the inlet ring (6) and the drain ring (8) respectively. The wall replacement device (9) includes a housing (10), a receiving roller (11), a nickel-based alloy wall panel (12), a receiving cylinder (13), a take-up roller (14), and a drive motor (15). The housing (10) is built into the inner wall of the double-layer combustion chamber (2). The receiving roller (11) is divided into two groups and symmetrically installed inside the housing (10). The nickel-based alloy wall panel (12) is divided into two groups and wound around the two groups of receiving rollers (11). The nickel-based alloy wall panel (12) is laid along the inner wall of the double-layer combustion chamber (2) and its outer end is connected to the receiving cylinder (13). The receiving cylinder (13) is installed on the outer wall of the double-layer combustion chamber (2). The take-up roller (14) is connected to the outer end of the nickel-based alloy wall panel (12). The drive motor (15) is installed at one end of the receiving cylinder (13) and its power output end is connected to the end of the take-up roller (14). The cooling assembly (7) includes a liquid-conducting cooling pipe (16) and a cooling cover (17) installed at the bottom of the liquid-conducting cooling pipe (16). A corrugated liquid-conducting plate (18) is provided inside the cooling cover (17). The corrugated liquid-conducting plate (18) is attached to the double-layer combustion chamber (2). A cooling cover (17) is also connected between two adjacent sets of liquid-conducting cooling pipes (16).

2. The temperature control and protection system for high-temperature walls of a gas turbine according to claim 1, characterized in that: The nickel-based alloy wall panel (12) is made of nickel-based alloy material and has an arc-shaped structure. The arc of the nickel-based alloy wall panel (12) is the same as the arc of the inner wall of the double-layer combustion chamber (2).

3. The temperature control and protection system for high-temperature walls of a gas turbine according to claim 1, characterized in that: The detector (5) includes a mounting plate (19) and a temperature sensor (20) and an electrochemical sensor (21) mounted on the mounting plate (19). The temperature sensor (20) and the electrochemical sensor (21) are connected to a controller (22), which is connected to a wall changer (9) and a cooling assembly (7).

4. The temperature control and protection system for high-temperature walls of a gas turbine according to claim 1, characterized in that: The liquid inlet ring (6) includes a ring body (23), an annular water inlet pipe (24), a liquid inlet pipe (25), and a drain pipe (26). The ring body (23) is installed at the end of the double-layer combustion chamber (2). The annular water inlet pipe (24) is installed on the ring body (23). The liquid inlet pipe (25) is installed at the top of the annular water inlet pipe (24). The drain pipe (26) is divided into several groups and evenly installed at the inner end of the annular water inlet pipe (24). The drain pipe (26) is connected to the liquid cooling pipe (16).

5. A temperature control and protection system for high-temperature walls of a gas turbine according to claim 4, characterized in that: The drain ring (8) includes a second ring body (27), an annular drain pipe (28), a drain pipe (29), and an outlet pipe (30). The second ring body (27) is installed at the end of the double-layer combustion chamber (2). The annular drain pipe (28) is installed on the second ring body (27). The drain pipe (29) is installed at the bottom of the annular drain pipe (28). The outlet pipe (30) is divided into several groups and evenly installed on the inner side of the annular drain pipe (28). The outlet pipe (30) is connected to the liquid cooling pipe (16).

6. The temperature control and protection system for high-temperature walls of a gas turbine according to claim 1, characterized in that: The cooling shroud (17) is a hollow semi-cylindrical structure and is attached to the inner wall of the double-layer combustion chamber (2).

7. A temperature control and protection system for high-temperature walls of a gas turbine according to claim 6, characterized in that: The corrugated liquid guide plate (18) has an undulating structure and is corrugated overall.

8. A temperature control and protection system for high-temperature walls of a gas turbine according to claim 7, characterized in that: The corrugated liquid guide plate (18) is in contact with the inner wall of the double-layer combustion chamber (2).

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