Gas turbine swirl burner and combustion chamber for supplementary-fired compressed air energy storage

Abstract

The present invention discloses a gas turbine swirl burner and a combustion chamber for a supplementary combustion compressed air energy storage, belonging to the field of supplementary combustion compressed air and other integrated energy. The swirl burner of the present invention includes an outer ring, a petal structure is connected to the center of the outer ring, one side of the petal structure is connected to a connecting column, the outermost end of the connecting column is connected to a combustion-supporting disc, each petal of the petal structure has a petal center hole, a middle through hole is arranged in the center of the connecting column, the middle through hole communicates with the center of the petal structure and the center of the combustion-supporting disc, and an annular hole is arranged on the combustion-supporting disc. The present invention has the advantages of simple structure, facilitating air flow, slowing down air flow impact, forming a turbulent flow, and promoting air flow mixing.

Description

Technical Field

[0001] The present invention belongs to the field of supplementary combustion compressed air and other integrated energy, and particularly relates to a gas turbine swirl burner and combustion chamber for supplementary combustion compressed air energy storage. Background Technique

[0002] A gas turbine is an impeller-type power machine that uses gas as the working medium and converts the heat released during fuel combustion into useful work. Compared with other commonly used power devices at present, the main advantages of gas turbines are light weight and small volume. In addition, they also have the advantages of simple equipment, no need for water, and fast starting and acceleration. Due to the significant advantages and great development potential of gas turbines, with the continuous development of technology and the continuous improvement of performance, they have broad development prospects.

[0003] Swirl combustion is an effective means of strengthening combustion, and a swirler is an important device for realizing swirl combustion. The swirler is one of the most important components of a swirl combustion chamber, and its performance directly affects the operation and performance of the combustion chamber. Due to the strong rotation of the air flow generating a recirculation zone, the mixture of unburned fuel and air entering the flame tube can be smoothly ignited. The swirl combustion chamber has the advantages of compact structure, short flame length, good combustion stability, high combustion efficiency, and low pollutant emissions. As one of the key components of the swirl combustion chamber, the swirler has a direct impact on the working performance of the combustion chamber.

[0004] Supplementary combustion compressed air uses a gas turbine as the core equipment. In addition to directly outputting part of the power, the waste heat of the tail exhaust can heat the compressed air to make it have the ability to generate electricity, further improving the power generation efficiency. The development of gas turbines in China is relatively late, and small and medium-sized gas turbines for compressed air are rarely used. Moreover, the existing gas turbine swirl burners are for large gas turbines. Summary of the Invention

[0005] To solve the above problems, the present invention discloses a gas turbine swirl burner and combustion chamber for supplementary combustion compressed air energy storage. This small burner has the advantages of simple structure, facilitating air flow, reducing air flow impact, forming turbulent flow, and promoting air flow mixing.

[0006] To achieve the above object, the technical solution of the present invention is as follows:

[0007] A gas turbine swirl burner for supplementary combustion compressed air energy storage includes an outer ring. A petal structure is connected to the center of the outer ring. One side of the petal structure is connected to a connecting column, and the outermost end of the connecting column is connected to a combustion assisting disk. Each petal of the petal structure has a petal center hole. A middle through hole is provided in the center of the connecting column, and the middle through hole communicates with the center of the petal structure and the center of the combustion assisting disk. An annular hole is provided on the combustion assisting disk.

[0008] Further, in the petal structure, the number of petals is 8, and the adjacent petals are arranged symmetrically at an angle of 45°. There is a petal center hole in the middle of each petal. The number of petal center holes is the same as the number of petals, a total of 8, and the angle between adjacent two petal center holes is 45°.

[0009] Further, the connecting column and the combustion-supporting disc are connected together by welding, and the petal structure is also welded to the connecting column and the petal structure is welded to the outer ring.

[0010] Further, there are a total of 12 annular holes, and the angle between each annular hole is 30°.

[0011] Further, the diameter of the combustion-supporting disc is the same as the diameter of the outer ring.

[0012] A gas turbine combustor for a supplementary combustion type compressed air energy storage, the combustor includes a long straight section, a combustion section, and a contraction section, and the above-mentioned gas turbine swirl combustor for supplementary combustion type compressed air energy storage is installed in the long straight section.

[0013] Further, the combustion section is an arc-shaped mechanism.

[0014] The beneficial effects of the present invention are as follows:

[0015] 1. The combustor of the present invention includes a long straight section, a combustion section, and a contraction section. The swirler is installed in the long straight section of the combustor, the gas burns sufficiently in the combustion section, and the burned gas is discharged through the contraction section. The combustion section is an arc-shaped structure, which is convenient for the gas to burn sufficiently inside.

[0016] 2. In the present invention, the connecting column and the combustion-supporting disc can slow down the airflow impact and form a turbulent flow. In addition, after the airflow impacts the combustion-supporting disc, the droplets are easily broken, which is convenient for the airflow droplet atomization. The airflow enters the swirler in several ways. One way is through the middle through hole and enters at a high speed. Another way is through the petal center hole of the petal. The last way is through the petal gap and enters the swirler. The three-way airflow enters the swirler at different speeds. At the same time, the connecting column and the combustion-supporting disc form a negative pressure area, and the several-way different airflows are fully mixed in this area. Since the several-way airflows have different speeds, different energies, and different temperatures, the full mixing helps combustion and improves the combustion sufficiency. In addition, the different speeds of the several-way different airflows can provide fuel for different regions of the combustor, which helps the combustion to be uniform and eliminates the structural damage to the combustor caused by insufficient combustion and uneven temperature.

[0017] 3. Compared with the previous large gas turbine swirl burners, the structure of the present invention is simple, forming a unique negative pressure area and turbulent flow area. This structure helps to reduce the speed, fully mix, and promote the atomization of the air flow. In addition, it can also increase the residence time of the air flow in the swirl area, which is conducive to stable and continuous combustion. It eliminates the problems of excessive combustion intensity when the impact speed of the air flow is too high and flameout when the air flow is briefly terminated. BRIEF DESCRIPTION OF THE DRAWINGS

[0018] Figure 1 is a schematic structural diagram of the swirl burner of the present invention.

[0019] Figure 2 is a schematic structural diagram of the combustion chamber of the present invention.

[0020] LIST OF DRAWING REFERENCES:

[0021] 1. Outer ring; 2. Petal structure; 3. Petal center hole; 4. Combustion assisting plate; 5. Intermediate through hole; 6. Annular hole; 7. Connecting column; 8. Combustion chamber. DETAILED DESCRIPTION OF THE EMBODIMENTS

[0022] The present invention will be further illustrated below in conjunction with the drawings and specific embodiments. It should be understood that the following specific embodiments are only used to illustrate the present invention and not to limit the scope of the present invention.

[0023] Example 1:

[0024] As Figure 1 shown, the gas turbine swirl burner for supplementary combustion compressed air energy storage described in this embodiment includes an outer ring 1. A petal structure 2 is connected to the center of the outer ring. One side of the petal structure is connected to a connecting column 7, and the outermost end of the connecting column is connected to a combustion assisting plate 4. Each petal of the petal structure has a petal center hole 3. An intermediate through hole 5 is provided in the center of the connecting column, and the intermediate through hole communicates with the center of the petal structure and the center of the combustion assisting plate. An annular hole 6 is provided on the combustion assisting plate.

[0025] Example 2:

[0026] In the petal structure described in this embodiment, the number of petals is 8, and the adjacent petals are arranged symmetrically at an angle of 45°. Each petal has a petal center hole in the middle. The number of petal center holes is the same as the number of petals, a total of 8, and the angle between adjacent two petal center holes is 45°.

[0027] Example 3:

[0028] In this embodiment, the connecting column and the combustion-supporting disc are connected together by welding. The petal structure is also welded to the connecting column and the outer ring. The diameter of the combustion-supporting disc is the same as that of the outer ring. The length of the outer ring is 20 cm, and the length of the petal is the same as that of the outer ring, both being 20 cm. The diameter of the combustion-supporting disc is 20 cm. The diameters of the annular holes and the central holes of the petals are both 2 cm. The diameter of the through hole is 8 cm. The length of the connecting column is also 20 cm.

[0029] Embodiment 4:

[0030] In this embodiment, there are a total of 12 annular holes, and the angle between each annular hole is 30°.

[0031] Embodiment 5:

[0032] A gas turbine combustor for supplementary combustion of compressed air, the combustor includes a long straight section, a combustion section, and a contraction section. The long straight section is equipped with the gas turbine swirl burner for supplementary combustion of compressed air energy storage described in any one of Embodiments 1-4. In this embodiment, the combustion section is an arc-shaped mechanism.

[0033] The working process and principle of the present invention:

[0034] The petal is connected to the connecting column, and the connecting column is connected to the combustion-supporting disc. Both are connected together by welding. The connecting column and the combustion-supporting disc form a side annular groove area, which is a negative pressure structure. The middle column can disturb and mix the air flow. This structure can form a turbulent flow, and the air flow is fully mixed, stirred, and blended in this area.

[0035] During the test process, the swirler is installed inside the combustor. One way for the air flow is to enter the combustor at high speed through the middle through hole. Another way is to enter the swirler through the central hole of the petal. The last way is to enter the swirler through the petal gap. These two air flows are affected by the connecting column and the combustion-supporting disc structure and are fully mixed and stirred in this area. Among them, it also collides with the combustion-supporting disc to form droplets, which will promote atomization. The air flow in this area is atomized and mixed, and then a part of the air flow enters the combustor through the annular holes.

[0036] This structure forms a unique negative pressure area and turbulent flow area at the connecting column and the combustion-supporting disc. This structure helps to reduce the speed, fully mix, and promote the atomization of the air flow. In addition, it can also increase the residence time of the air flow in the swirl area, which helps to stabilize and sustain combustion. It eliminates the problems of too strong combustion when the impact speed of the air flow is too large and flameout when the air flow is briefly terminated.

[0037] The burner of this structure has good mixing effect and good atomization effect, resulting in full combustion during combustion and improved combustion efficiency.

[0038] It should be noted that the above content only illustrates the technical idea of the present invention and cannot be used to limit the protection scope of the present invention. For those of ordinary skill in the art, without departing from the principle of the present invention, several improvements and refinements can still be made, and these improvements and refinements all fall within the protection scope of the claims of the present invention.

Claims

1. A swirl combustor for a gas turbine in a supplementary combustion compressed air energy storage system, characterized in that, The swirl burner includes an outer ring, and a petal structure is connected to the center of the outer ring. One side of the petal structure is connected to a connecting column, and the outermost end of the connecting column is connected to a combustion assisting disc. Each petal of the petal structure has a petal center hole. A middle through hole is arranged in the center of the connecting column, and the middle through hole communicates with the center of the petal structure and the center of the combustion assisting disc. An annular hole is arranged on the combustion assisting disc; in the petal structure, the number of petals is 8, and adjacent petals are arranged at a symmetrical angle of 45°. Each petal has a petal center hole in the middle, and the number of petal center holes is the same as the number of petals, a total of 8, and the angle between adjacent two petal center holes is 45°; the connecting column and the combustion assisting disc are connected together by welding, and the petal structure is also welded to the connecting column and the petal structure is also welded to the outer ring.

2. The swirl combustor of a gas turbine for supplementary firing compressed air energy storage according to claim 1, characterized in that, There are a total of 12 annular holes, and the angle between each annular hole is 30°.

3. The gas turbine swirl burner for supplementary combustion compressed air energy storage according to claim 1, wherein The diameter of the combustion assisting disc is the same as the diameter of the outer ring.

4. A gas turbine combustor for afterburning compressed air, characterized in that, The combustion chamber includes a long straight section, a combustion section, and a contraction section. The long straight section is equipped with the above-mentioned gas turbine swirl burner for supplementary combustion compressed air energy storage.

5. The gas turbine combustor for afterburning compressed air according to claim 4, characterized in that, The combustion section is an arc-shaped mechanism.

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