A gas turbine combustor and a gas turbine

Abstract

The application relates to the technical field of gas turbines, and discloses a gas turbine combustion chamber and a gas turbine, which comprise a combustion chamber outer shell and a gas inlet pipe, a combustion chamber inner shell is arranged in the middle of the inner side of the combustion chamber outer shell, a combustion chamber is formed between the combustion chamber outer shell and the combustion chamber inner shell, one end of the combustion chamber outer shell is a gas inlet face, a connection face of the gas inlet face is an air inlet face, a gas inlet pipe is arranged on the gas inlet face, and an air outlet pipe is arranged on the air inlet face. According to the application, the pressure of compressed air is different, the top plate is driven to overcome the elastic force of the V-shaped elastic sheet and to rise, a part of the compressed air flows to the periphery under the backflow action of the top plate, the mixing uniformity of the gas and the air is improved, the combustion efficiency is improved, the compressed air is prevented from directly blowing on the gas nozzle through the action of the top plate, and the stability of combustion is ensured.

Description

TECHNICAL FIELD

[0001] The present application relates to the field of gas turbine technology, in particular to a gas turbine combustion chamber and a gas turbine. BACKGROUND

[0002] A gas turbine is an internal combustion engine that converts the energy of fuel into useful work, belonging to a kind of heat engine. The working principle of a gas turbine involves three main parts: a compressor, a combustion chamber, and a turbine. Air first enters the compressor, where it is compressed to increase pressure. Then, these high-pressure gases enter the combustion chamber, mix with the injected fuel and burn, producing high-temperature and high-pressure gases. Finally, these high-temperature and high-pressure gases flow through the turbine, pushing the turbine blades to rotate, thereby generating mechanical work or electricity.

[0003] The combustion chamber of a gas turbine is a combustion device made of high-temperature resistant alloy material, and is one of the essential components of a gas turbine engine. It is located between the compressor and the turbine, responsible for converting the chemical energy of fuel into heat energy through combustion chemical reactions, forming high-temperature and high-pressure combustion products to drive the turbine to do work.

[0004] The existing gas turbine combustion chamber nozzle has the problem of uneven mixing of gas and air in the premixing channel, which can easily lead to unstable combustion. In addition, in some combustion chamber designs, the air inlet directly blows towards the gas nozzle, which may affect the stability of the flame, especially under variable operating conditions, affecting the operating stability of the gas turbine. SUMMARY

[0005] The purpose of the present application is to provide a gas turbine combustion chamber and a gas turbine to solve the problems raised in the background.

[0006] To achieve the above-mentioned purpose, the present application provides the following technical solution: a gas turbine combustion chamber, comprising: a combustion chamber outer shell and a gas inlet pipe, a combustion chamber inner shell is arranged on the inner side of the combustion chamber outer shell, a combustion chamber is formed between the combustion chamber outer shell and the combustion chamber inner shell, one end of the combustion chamber outer shell is a gas inlet face, the connection face of the gas inlet face is an air inlet face, a gas inlet pipe is arranged on the gas inlet face, an outlet pipe is arranged on the air inlet face, a gas nozzle is arranged at one end of the gas inlet pipe inside the combustion chamber, a retaining ring is arranged on the outer side of the gas nozzle and the outlet pipe of the combustion chamber inner wall, V-shaped elastic sheets are arranged on both sides of the retaining ring, a top plate is arranged on the top of the V-shaped elastic sheets, and the top plate is located directly above the outlet of the outlet pipe.

[0007] As a further description of the present application, one end of the gas inlet pipe is connected with a gas ring pipe, and one side of the gas ring pipe is provided with a gas delivery pipe.

[0008] As a further illustration of the present application, the air outlet pipe is provided with an air ring pipe at one end, and the air ring pipe is provided with a compressed air delivery pipe at one side.

[0009] As a further illustration of the present application, the combustion chamber outer shell is provided with an air shell at the outer wall near the air inlet surface, and the air shell is provided with a connecting pipe at one end, the connecting pipe is connected with the air ring pipe at one end, and the air outlet pipe is connected with the air shell at one end.

[0010] As a further illustration of the present application, the air outlet direction of the connecting pipe air outlet is tangent to the inner wall of the air shell, and the air shell is provided with an annular baffle on the inner wall, and the combustion chamber outer shell is also provided with an annular baffle inside the air shell, and the annular baffles on the combustion chamber outer shell and the air shell are arranged in an equal interval staggered manner.

[0011] As a further illustration of the present application, the height of the annular baffle is less than the cavity height of the air shell.

[0012] As a further illustration of the present application, the angle between the gas inlet surface and the air inlet surface is greater than 90 degrees, and the combustion chamber outer shell and the combustion chamber inner shell are in an open state at one end.

[0013] As a further illustration of the present application, the gas inlet surface is provided with a gas pipe hole, and the air inlet surface is provided with an air pipe hole.

[0014] As a further illustration of the present application, the gas inlet surface is provided with a plurality of gas inlet pipes, and the plurality of gas inlet pipes are uniformly arranged in a circumferential direction on the gas inlet surface, the number of the air outlet pipes is the same as the number of the gas inlet pipes, and the air outlet pipes are uniformly arranged in a circumferential direction on the air inlet surface.

[0015] A gas turbine comprising the gas turbine combustion chamber.

[0016] Compared with the prior art, the present application has the following beneficial effects:

[0017] The combustion chamber shell, the blocking ring and the top plate are arranged, when the gas turbine combustion chamber is used, the gas is conveyed to the gas ring pipe through the gas conveying pipe, the gas is uniformly conveyed to the gas conveying pipe through the gas ring pipe, and then the gas is conveyed to the gas nozzle through the gas conveying pipe and sprayed to the combustion chamber, meanwhile, the compressed air in the compressor is sent to the air ring pipe through the compressed air conveying pipe, the compressed air is sent to the air shell through the connecting pipe tangentially, the compressed air can be fully contacted with the combustion chamber shell in the air shell through the arrangement of the annular baffle, the compressed air is heated through the waste heat of the combustion chamber shell, and finally the heated compressed air is sent to the combustion chamber through the air outlet pipe, after the compressed air and the gas are sent to the inside of the combustion chamber, part of the air is contacted with the gas through the action of the blocking ring, in addition, after the compressed air enters the inside of the combustion chamber through the action of the top plate above the air outlet pipe, according to the different compressed air pressure, the top plate is driven to rise to overcome the elastic force of the V-shaped elastic sheet, so that part of the compressed air flows to the surrounding under the backflow action of the top plate, the mixing uniformity of the gas and the air is increased, the combustion efficiency is improved, and the straight blowing of the compressed air to the gas nozzle is avoided through the action of the top plate, so that the stability of combustion is ensured. BRIEF DESCRIPTION OF DRAWINGS

[0018] Figure 1 It is a perspective view of a gas turbine combustion chamber and a gas turbine of the present application;

[0019] Figure 2 It is a perspective view of a gas turbine combustion chamber and a gas turbine of the present application;

[0020] Figure 3 It is a front view of a gas turbine combustion chamber and a gas turbine of the present application;

[0021] Figure 4 It is a left view of a gas turbine combustion chamber and a gas turbine of the present application;

[0022] Figure 5 It is a right view of a gas turbine combustion chamber and a gas turbine of the present application;

[0023] Figure 6 It is a top view of a gas turbine combustion chamber and a gas turbine of the present application;

[0024] Figure 7 It is a combustion chamber shell structure schematic view of a gas turbine combustion chamber and a gas turbine of the present application;

[0025] Figure 8 It is an internal structure schematic view of a gas turbine combustion chamber and a gas turbine of the present application;

[0026] Figure 9It is a main sectional view of a gas turbine combustor and a gas turbine of the present application.

[0027] Figure 10 It is a blocking ring connecting structure schematic diagram of a gas turbine combustor and a gas turbine of the present application.

[0028] In the figure: 1, combustor outer shell; 2, gas inlet pipe; 3, gas ring pipe; 4, gas delivery pipe; 5, air shell; 6, air ring pipe; 7, connecting pipe; 8, gas outlet pipe; 9, annular baffle; 10, blocking ring; 11, V-shaped elastic sheet; 12, top plate; 13, gas pipe hole; 14, air pipe hole; 15, gas nozzle; 16, combustor inner shell; 17, gas inlet face; 18, air inlet face; 19, compressed air delivery pipe. DETAILED DESCRIPTION

[0029] 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 part of the embodiments of the present application, not all the embodiments.

[0030] Please refer to Figures 1-10 The present application provides a technical solution: a gas turbine combustor, comprising: a combustor outer shell 1 and a gas inlet pipe 2, a combustor inner shell 16 is arranged in the center of the inner side of the combustor outer shell 1, a combustor is formed between the combustor outer shell 1 and the combustor inner shell 16, and the space between the combustor outer shell and the combustor inner shell forms the combustor. This double-shell structure helps to protect the interior of the combustor from external influences while providing sufficient space for the mixing and combustion process of gas and air.

[0031] The combustor outer shell 1 has a gas inlet face 17 at one end, and the connecting face of the gas inlet face 17 is an air inlet face 18. The gas inlet pipe 2 is arranged on the gas inlet face 17, and the gas outlet pipe 8 is arranged on the air inlet face 18. The gas nozzle 15 is arranged at the inner end of the combustor of the gas inlet pipe 2, and the blocking ring 10 is arranged on the inner wall of the combustor outside the gas nozzle 15 and the gas outlet pipe 8. The blocking ring on the inner wall of the combustor helps to guide the airflow, so that part of the air can better contact with the gas, thereby improving the mixing effect.

[0032] The V-shaped elastic sheet 11 is provided on both sides of the baffle ring 10, and the top of the V-shaped elastic sheet 11 is provided with a top plate 12 located directly above the gas outlet of the air outlet pipe 8. The top plate 12 is located directly above the gas outlet of the air outlet pipe, and its position can move up and down according to the change of the pressure of compressed air. This design can not only avoid the direct blowing of compressed air to the gas nozzle, but also increase the turbulence degree of air flow, thereby improving the uniformity of gas and air mixing. The V-shaped elastic sheet 11 is connected to the two sides of the baffle ring, and the top is connected to the top plate 12. This elastic structure allows the top plate to move up and down within a certain range, while providing sufficient support force to maintain the stable position of the top plate 12. Through the joint action of the baffle ring 10, the top plate 12 and the V-shaped elastic sheet 11, the uniformity of gas and air mixing can be effectively improved, which is crucial for improving combustion efficiency and reducing pollutant emissions. The design of the top plate 12 avoids the direct blowing of compressed air to the gas nozzle, which helps to maintain the stability of the flame and reduce the combustion instability caused by air flow interference. This design provides a new solution for gas turbine combustion chamber air flow control by introducing a movable top plate 12 and elastic sheet structure. The compact layout design makes full use of the space of the combustion chamber, which helps to reduce the overall size of the gas turbine and reduce the manufacturing cost.

[0033] The gas inlet pipe 2 is connected to the gas ring pipe 3 at one end, and the gas ring pipe 3 is provided with a gas delivery pipe 4 on one side. The gas is delivered to the gas ring pipe 3 through the gas delivery pipe 4, and then evenly delivered to the gas delivery pipe 4 through the gas ring pipe 3, and then delivered to the gas nozzle 15 through the gas delivery pipe 4 and sprayed into the combustion chamber.

[0034] The air ring pipe 6 is provided at one end of the air outlet pipe 8, and the compressed air delivery pipe 19 is provided on one side of the air ring pipe 6. The outer wall of the combustion chamber shell 1 is provided with an air shell 5 near the air inlet face 18 on one side, and the outer wall of the air shell 5 is provided with a connecting pipe 7 at one end. The connecting pipe 7 is connected to the air ring pipe 6 at one end, and the air outlet pipe 8 is connected to one end of the air shell 5. The outlet of the connecting pipe 7 is tangent to the inner wall of the air shell 5, and the inner wall of the air shell 5 is provided with a ring baffle 9. The outer wall of the combustion chamber shell 1 is also provided with a ring baffle 9 inside the air shell 5, and the ring baffles 9 on the combustion chamber shell 1 and the air shell 5 are arranged in equal intervals. The arrangement of the ring baffles 9 allows the compressed air to fully contact the combustion chamber shell 1 in the air shell 5, and the compressed air is heated by the waste heat of the combustion chamber shell 1, and finally the heated compressed air is sent into the combustion chamber through the air outlet pipe 8.

[0035] By allowing compressed air to come into contact with the combustion chamber outer shell in the air casing, the waste heat from the combustion chamber outer shell can be utilized to preheat these air. This preheating process can increase the temperature of the air entering the combustion chamber, thereby accelerating the combustion reaction and improving thermal efficiency. By recycling the waste heat from the combustion chamber outer shell, energy loss can be reduced and the overall system efficiency can be improved. This method is an effective heat recovery strategy that helps to improve the overall performance of the gas turbine.

[0036] By preheating the compressed air, the temperature difference inside the combustion chamber can be reduced, thereby reducing the thermal stress on the inner wall material of the combustion chamber and prolonging the service life of the equipment.

[0037] The height of the annular baffle 9 is less than the cavity height of the air casing 5, ensuring that the compressed air can flow smoothly between the annular baffles 9.

[0038] The angle between the gas inlet face 17 and the air inlet face 18 is greater than 90 degrees, and the combustion chamber outer shell 1 and the combustion chamber inner shell 16 at one end are in an open state. When the angle between the gas inlet face and the air inlet face is greater than 90 degrees, it helps to form a larger vortex in the combustion chamber, which can promote the effective mixing of gas and air. By increasing the angle, it can avoid the air blowing directly to the gas nozzle, reducing the possibility of gas being blown away directly, thereby ensuring the sufficient mixing of gas and air. Avoiding the direct blowing of air to the gas nozzle helps to reduce the area of incomplete combustion caused by uneven mixing, thereby improving the combustion efficiency. More complete combustion can reduce the generation of pollutants such as nitrogen oxides and carbon monoxide, meeting the increasingly stringent environmental protection standards.

[0039] Gas pipe holes 13 are provided on the gas inlet face 17, and air pipe holes 14 are provided on the air inlet face 18. They are used for the installation of gas inlet pipes 2 or outlet pipes 8. In the design of the gas turbine combustion chamber, gas pipe holes 13 are provided on the gas inlet face 17, which are used to install gas inlet pipes 2. The function of the gas inlet pipe is to deliver fuel into the combustion chamber, mix with air from the compressor and burn to form high-temperature and high-pressure gas. This design helps to achieve uniform mixing of fuel and air, thereby improving combustion efficiency and reducing pollutant emissions. Similarly, air pipe holes 14 are provided on the air inlet face 18, which are used to install outlet pipes 8. The number of outlet pipes is usually the same as the number of gas inlet pipes, which helps to maintain the pressure balance and uniformity of airflow in the combustion chamber. The function of the outlet pipe is to deliver compressed air into the combustion chamber, mix with fuel and participate in the combustion process. Through reasonable layout design, efficient combustion process can be achieved to meet the needs of different application fields.

[0040] The number of outlet pipes 8 is the same as that of gas inlet pipes 2, which helps to maintain the pressure balance and uniformity of airflow in the combustion chamber, thereby improving the stability of combustion.

[0041] The plurality of gas inlet pipes 2 are uniformly arranged on the gas inlet face 17, and the number of the gas outlet pipes 8 is the same as that of the gas inlet pipes 2, and the gas outlet pipes 8 are uniformly arranged on the air inlet face 18. The uniform arrangement of the gas inlet pipes 2 on the gas inlet face 17 helps to realize uniform mixing of fuel and air, thereby improving combustion efficiency and reducing pollutant emissions. The uniform arrangement of the gas outlet pipes 8 on the air inlet face 18 helps to ensure uniformity of air flow and pressure distribution in the combustion chamber, thereby improving combustion stability. Uniform air flow distribution also helps to maintain flame stability, especially when the gas turbine is operating under variable conditions.

[0042] A gas turbine comprises a gas turbine combustion chamber.

[0043] In use, the gas turbine combustion chamber, the gas is delivered to the gas ring pipe 3 through the gas delivery pipe 4, and the gas is uniformly delivered to the gas delivery pipe 4 through the gas ring pipe 3, and then delivered to the gas nozzle 15 through the gas delivery pipe 4, while the compressed air in the compressor is sent to the air ring pipe 6 through the compressed air delivery pipe 19, and is sent to the air casing 5 through the connecting pipe 7, and the compressed air is fully contacted with the combustion chamber outer casing 1 through the arrangement of the annular baffle 9, and the compressed air is heated by the waste heat of the combustion chamber outer casing 1, and finally the heated compressed air is sent to the combustion chamber through the gas outlet pipe 8. After the compressed air and the gas are sent into the combustion chamber, part of the air is contacted with the gas through the action of the baffle ring, and in addition, after the compressed air enters the combustion chamber, according to the different pressure of the compressed air, the top plate 12 is driven to overcome the elastic force of the V-shaped elastic sheet 11 to rise, so that part of the compressed air flows to the surrounding under the backflow action of the top plate 12, increasing the uniformity of the gas and air mixture, improving the combustion efficiency, and at the same time, avoiding the direct blowing of the compressed air to the gas nozzle 15 through the action of the top plate 12, ensuring the stability of the combustion.

[0044] Based on the embodiments in the present application, all other embodiments obtained by those of ordinary skill in the art without creative labor fall within the scope of protection of the present application.

Claims

1. A gas turbine combustor comprising: The combustion chamber outer shell (1) and the gas inlet pipe (2) are characterized in that: a combustion chamber inner shell (16) is arranged in the center of the inner side of the combustion chamber outer shell (1), a combustion chamber is formed between the combustion chamber outer shell (1) and the combustion chamber inner shell (16), one end of the combustion chamber outer shell (1) is a gas inlet face (17), a connecting face of the gas inlet face (17) is an air inlet face (18), a gas inlet pipe (2) is arranged on the gas inlet face (17), an air outlet pipe (8) is arranged on the air inlet face (18), the gas inlet pipe (2) is provided with a gas nozzle (15) at one end inside the combustion chamber, a baffle ring (10) is arranged on the inner wall of the combustion chamber outside the gas nozzle (15) and the air outlet pipe (8), V-shaped elastic sheets (11) are arranged on both sides of the baffle ring (10), a top plate (12) is arranged on the top of the V-shaped elastic sheet (11), and the top plate (12) is arranged above the air outlet of the air outlet pipe (8). One end of the air outlet pipe (8) is provided with an air ring pipe (6), one side of the air ring pipe (6) is provided with a compressed air conveying pipe (19). The outer wall of the combustion chamber outer shell (1) is provided with an air shell (5) near one side of the air inlet face (18), one end of the outer wall of the air shell (5) is provided with a connecting pipe (7), one end of the connecting pipe (7) is connected with the air ring pipe (6), and one end of the air outlet pipe (8) is connected with one end of the air shell (5). The air outlet direction of the air outlet of the connecting pipe (7) is tangent to the inner wall of the air shell (5), the inner wall of the air shell (5) is provided with an annular baffle (9), the outer wall of the combustion chamber outer shell (1) is also provided with the annular baffle (9) inside the air shell (5), and the annular baffles (9) on the combustion chamber outer shell (1) and the air shell (5) are arranged in an equal interval staggered mode.

2. A combustor according to claim 1 wherein: One end of the gas inlet pipe (2) is connected with a gas ring pipe (3), one side of the gas ring pipe (3) is provided with a gas conveying pipe (4).

3. A combustor according to claim 1 wherein: The height of the annular baffle (9) is smaller than the cavity height of the air shell (5).

4. A combustor according to claim 1 wherein: The included angle between the gas inlet face (17) and the air inlet face (18) is greater than 90 degrees, and one end between the combustion chamber outer shell (1) and the combustion chamber inner shell (16) is in an open state.

5. A combustor according to claim 1 wherein: Gas pipe holes (13) are arranged on the gas inlet face (17), and air pipe holes (14) are arranged on the air inlet face (18).

6. A combustor according to claim 1 wherein: A plurality of gas inlet pipes (2) are arranged on the gas inlet face (17) in a circumferential uniform mode, the number of the air outlet pipes (8) is the same as that of the gas inlet pipes (2), and the air outlet pipes (8) are arranged on the air inlet face (18) in a circumferential uniform mode.

7. A gas turbine engine characterized by: The gas turbine combustion chamber comprises the combustion chamber outer shell and the gas inlet pipe. The gas turbine combustion chamber comprises the combustion chamber outer shell and the gas inlet pipe.

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