Multi-stage rotational flow micro gas turbine combustor

Abstract

The utility model provides a multi-stage rotational flow micro gas turbine combustor, and relates to the field of gas turbines. The multi-stage rotational flow micro gas turbine combustor comprises a combustion chamber and a nozzle installed in the combustion chamber, the combustion chamber comprises a first-stage combustion chamber, a second-stage combustion chamber and a third-stage combustion chamber, and a primary air inlet, a secondary air inlet and a third-stage air inlet are formed in the combustion chamber and used for conveying air into the combustion chamber. Notches are formed in the first-stage combustion chamber and the second-stage combustion chamber; according to the multi-stage rotational flow micro gas turbine combustor, the three-stage combustion chamber design is adopted, the length is decreased in sequence, combustion requirements of different stages can be met, the combustion efficiency is improved, by arranging the spiral scrapers in the combustion chambers, the residence time of fuel and air is prolonged, sufficient combustion is promoted, and the incomplete combustion probability is reduced; and the scraping plate rotates, so that residues on the inner wall of the combustion chamber can be scraped, and the smoke exhaust rate can be increased.

Description

Technical Field

[0001] This utility model relates to the field of gas turbines, specifically a multi-stage swirl micro gas turbine burner. Background Technology

[0002] A gas turbine is a rotary power machine that uses continuously flowing gas as its working fluid to convert the chemical energy of fuel into mechanical energy. A gas turbine consists of a compressor, a combustion chamber, and a turbine. Air enters the gas turbine through the inlet and is compressed stage by stage in the compressor, with its pressure and temperature continuously increasing. The compressed air then enters the combustion chamber, where it mixes and burns with the injected fuel, further increasing the gas's temperature and pressure to form high-temperature, high-pressure gas. This high-temperature, high-pressure gas enters the turbine, where it expands and depressurizes, driving the turbine blades to rotate and converting the gas's internal energy into mechanical energy, thus achieving energy output. Multi-stage swirling micro gas turbine combustors typically consist of multiple swirling blades or swirlers. These swirlers are arranged in stages along the axial or radial direction of the combustor; for example, common structures include two-stage or three-stage swirling structures. Each stage of the swirler has a specific angle and shape, causing the airflow to rotate with different intensities and directions, thereby forming a complex and orderly flow field within the combustion chamber. Multi-stage swirling allows for thorough mixing of fuel and air, achieving more complete combustion, thus improving combustion efficiency and increasing the output power and thermal efficiency of the micro gas turbine.

[0003] In traditional multi-stage swirl micro gas turbine burners, impurities accumulate in the air duct. With long-term use, the impurities gradually increase, reducing the effective flow area of ​​the air duct, resulting in reduced and uneven airflow. This leads to insufficient oxygen content for complete fuel combustion, thus reducing combustion efficiency. Furthermore, the short residence time of fuel and air in the combustion chamber prevents the combustion reaction from proceeding fully, easily resulting in incomplete combustion. Utility Model Content

[0004] To address the shortcomings of existing technologies, this invention provides a multi-stage swirl micro gas turbine burner that solves the problems of low combustion efficiency and incomplete combustion.

[0005] To achieve the above objectives, this utility model is implemented through the following technical solution: a multi-stage swirl micro gas turbine burner, comprising a combustion chamber and a nozzle installed in the combustion chamber. The combustion chamber includes a primary combustion chamber, a secondary combustion chamber, and a tertiary combustion chamber. The combustion chamber is provided with a primary air inlet, a secondary air inlet, and a tertiary air inlet for supplying air into the combustion chamber. Both the primary and secondary combustion chambers are provided with slots, through which unburned fuel in the primary combustion chamber enters the secondary and tertiary combustion chambers sequentially.

[0006] The combustion chamber is equipped with several spiral scrapers, which contact the inner walls of the first-stage, second-stage, and third-stage combustion chambers respectively. One end of each scraper is equipped with a turbine mechanism to drive the scraper to rotate. When the air pressure in the combustion chamber increases, the blade tilt angle of the turbine mechanism increases accordingly.

[0007] Preferably, the lengths of the primary combustion chamber, secondary combustion chamber, and tertiary combustion chamber decrease sequentially.

[0008] Preferably, the turbine mechanism further includes a connecting frame, a connecting shaft, a sleeve, a fixed cylinder, a rotating component, and a torsion spring. The sleeve is rotatably connected to the outer side of the three-stage combustion chamber. The connecting frame is fixedly connected to the sleeve and also to the connecting shaft. The connecting shaft is fixedly connected to the fixed cylinder. One end of the rotating component is rotatably connected to the fixed cylinder, and the other end is fixedly connected to the blade. Both ends of the torsion spring are fixedly connected to the rotating component and the fixed cylinder, respectively.

[0009] Preferably, one side of the connecting frame is fixedly connected to several sets of support plates, and the inner rings of several scrapers are respectively fixedly connected to several sets of support plates.

[0010] Preferably, a limiting groove is formed inside the fixed cylinder, and a limiting block is rotatably connected inside the limiting groove. The limiting block is fixedly connected to the outer side of the rotating component.

[0011] Preferably, the cross-sections of the primary combustion chamber, the secondary combustion chamber, and the tertiary combustion chamber are all circular, and the three are located at the same axis.

[0012] Preferably, the contact surface between the sleeve and the third-stage combustion chamber is roughened, and there is friction between them.

[0013] Preferably, the blades are inclined.

[0014] Compared with the prior art, this utility model has the following beneficial effects: It adopts a three-stage combustion chamber design with progressively decreasing lengths, which can adapt to the combustion needs of different stages, improve combustion efficiency, reduce fuel waste and pollutant emissions, and supplement oxygen by supplying air to the combustion chamber to aid combustion, enhance mixing, and improve combustion efficiency. By setting spiral scrapers in the combustion chamber, the residence time of fuel and air is increased, promoting complete combustion and reducing the probability of incomplete combustion. The inclined blades can guide the flue gas to be discharged spirally, which can contact the turbine of the generator for a longer time and a larger area compared with straight discharge, thus improving the turbine's power generation efficiency. Through the turbine mechanism, when the fuel delivery changes, the air pressure changes, causing the blades to automatically adjust their angle and rotate. The rotating scraper can not only scrape off the residue on the inner wall of the combustion chamber, but also increase the flue gas discharge rate and prevent excessive air pressure from damaging the combustion chamber. Attached Figure Description

[0015] Figure 1This is a schematic diagram of the overall structure of this utility model;

[0016] Figure 2 This is a schematic diagram of the internal structure of the first-stage combustion chamber, second-stage combustion chamber, and third-stage combustion chamber of this utility model;

[0017] Figure 3 This is a sectional view of the front view of the first-stage combustion chamber, the second-stage combustion chamber, and the third-stage combustion chamber of this utility model;

[0018] Figure 4 This is a sectional view of the side view of the turbine mechanism of this utility model;

[0019] Figure 5 This is a sectional view of the side view of the three-stage combustion chamber and scraper of this utility model;

[0020] Figure 6 This is a sectional view of the side view of the three-stage combustion chamber of this utility model;

[0021] Figure 7 This is a partial sectional view of the fixing cylinder of this utility model;

[0022] Figure 8 This utility model Figure 7 Enlarged schematic diagram of the structure at point A in the middle.

[0023] The components are: 1. Nozzle; 2. Primary combustion chamber; 3. Secondary combustion chamber; 4. Tertiary combustion chamber; 5. Primary air inlet; 6. Secondary air inlet; 7. Tertiary air inlet; 8. Groove; 9. Scraper; 10. Turbine mechanism; 101. Blade; 102. Connecting frame; 103. Connecting shaft; 104. Sleeve; 105. Fixed cylinder; 106. Rotating component; 107. Torsion spring; 11. Support plate; 12. Limiting groove; 13. Limiting block. Detailed Implementation

[0024] like Figures 1-8As shown, a multi-stage swirl micro gas turbine combustor includes a combustion chamber and a nozzle 1 installed inside the combustion chamber. The nozzle 1 mixes fuel and air in a certain proportion and injects it into the combustion chamber to ensure complete and stable combustion of the fuel. The combustion chamber includes a primary combustion chamber 2, a secondary combustion chamber 3, and a tertiary combustion chamber 4, with the lengths of the primary combustion chamber 2, secondary combustion chamber 3, and tertiary combustion chamber 4 decreasing sequentially. The primary combustion chamber 2 is where the fuel and air initially mix and burn; it needs sufficient length to ensure that the fuel can fully mix with the air and begin stable combustion. The fuel undergoes initial and intense combustion in the primary combustion chamber 2, releasing a large amount of heat and providing the base temperature and energy for subsequent combustion. After the initial combustion in the primary combustion chamber 2, the combustion products and unreacted substances enter the secondary combustion chamber 3. At this point, since the primary combustion chamber 2 has already provided... Given a certain temperature and reaction basis, the combustion reaction in the secondary combustion chamber 3 is relatively more intense and rapid, requiring a relatively smaller reaction space, meaning the length can be appropriately shortened. Similarly, the substance entering the tertiary combustion chamber 4 is a small amount of unreacted substance remaining after the first two stages of combustion. Under higher temperature and more thorough mixing conditions, it can complete combustion in a shorter space, so the length of the tertiary combustion chamber 4 is further reduced. The cross-sections of the primary combustion chamber 2, the secondary combustion chamber 3, and the tertiary combustion chamber 4 are all circular, and all three are located on the same axis. The combustion chamber is equipped with a primary air inlet 5, a secondary air inlet 6, and a tertiary air inlet 7, which are used to supply air into the combustion chamber. The primary combustion chamber 2 and the secondary combustion chamber 3 are both provided with slots 8, through which unburned fuel in the primary combustion chamber 2 enters the secondary combustion chamber 3 and the tertiary combustion chamber 4 in sequence.

[0025] Several spiral scrapers 9 are installed in the combustion chamber. These scrapers 9 contact the inner walls of the first-stage combustion chamber 2, the second-stage combustion chamber 3, and the third-stage combustion chamber 4, respectively. A turbine mechanism 10 is installed at one end of each scraper 9 to drive its rotation. When the air pressure inside the combustion chamber increases, the tilt angle of the blades 101 of the turbine mechanism 10 increases accordingly. The turbine mechanism 10 also includes a connecting frame 102, a connecting shaft 103, a sleeve 104, a fixed cylinder 105, a rotating component 106, and a torsion spring 107. The sleeve 104 is rotatably connected to the outer side of the third-stage combustion chamber 4. The connecting frame 102 is fixedly connected to the sleeve 104 and also to the connecting shaft 103. The connecting shaft 103 is fixedly connected to the fixed cylinder 105. One end of the rotating component 106 is rotatably connected to the fixed cylinder 105, and the other end is fixedly connected to the blades 101. Both ends of the torsion spring 107 are fixedly connected to the rotating component 106 and the fixed cylinder 105, respectively. The blades 101 and the rotating component 106 are both configured as... Several blades 101 rotate when the gas generated during operation in the combustion chamber is discharged. The blades 101 drive the rotating component 106 to rotate, and the rotating component 106 drives the fixed cylinder 105 to rotate, thereby causing the connecting frame 102 to drive the scraper 9 to rotate. When the scraper 9 rotates, it can scrape off the residue on the inner wall of the combustion chamber. Several sets of support plates 11 are fixedly connected to one side of the connecting frame 102. The inner rings of several scrapers 9 are fixedly connected to several sets of support plates 11 respectively. By setting the support plates 11, the stability of the scraper 9 is improved, ensuring that the scraper 9 always fits the combustion chamber. A limiting groove 12 is opened in the fixed cylinder 105. A limiting block 13 is rotatably connected in the limiting groove 12. The limiting block 13 is fixedly connected to the outer side of the rotating component 106 to limit the maximum tilt angle of the rotating component 106 and the blades 101. The contact surface between the sleeve 104 and the third-stage combustion chamber 4 is roughened, and there is friction between the two. The blades 101 are tilted.

[0026] In operation, fuel and air are first mixed in a certain proportion through nozzle 1 and injected into the combustion chamber, where the fuel burns. Unburned fuel in the primary combustion chamber 2 enters the secondary combustion chamber 3 and tertiary combustion chamber 4 through slot 8 for further combustion. The lengths of the primary, secondary, and tertiary combustion chambers decrease sequentially. This is because the primary combustion chamber 2 is where the fuel and air initially mix and burn; it needs sufficient length to ensure thorough mixing and stable combustion. The initial, intense combustion in the primary combustion chamber 2 releases a large amount of heat, providing the base temperature and energy for subsequent combustion. After this initial combustion, the combustion products and unreacted substances enter the secondary combustion chamber 3. Since the primary combustion chamber 2 has already provided a certain temperature and reaction base, the combustion reaction in the secondary combustion chamber 3 is relatively more intense and rapid, requiring a smaller reaction space; therefore, its length can be appropriately shortened. Similarly, the length of the secondary combustion chamber 3 decreases as the fuel enters the tertiary combustion chamber 4. The remaining unreacted material after the first two stages of combustion can be burned in a shorter space under higher temperatures and more thorough mixing conditions, so the length of the third-stage combustion chamber 4 is further reduced. Then, air is supplied to the first-stage combustion chamber 2, the second-stage combustion chamber 3, and the third-stage combustion chamber 4 through the primary air inlet 5, the secondary air inlet 6, and the tertiary air inlet 7, respectively. The primary air inlet 5 supplies air to the first-stage combustion chamber 2 to assist combustion, providing the oxygen required for the initial combustion of the fuel, promoting the evaporation of moisture and the release of volatiles, allowing the fuel to be quickly ignited and forming a stable combustion environment. The secondary air inlet 6 supplies air to the second-stage combustion chamber 3 to supplement oxygen so that the unburned material can continue to burn, thereby improving combustion efficiency and enhancing turbulent mixing to allow oxygen to fully contact and react with the combustible material. The tertiary air inlet 7 supplies air to the third-stage combustion chamber 4 to allow the combustible components remaining after the first two stages of combustion to burn again, improving energy utilization, reducing flue gas temperature to protect downstream equipment, further reducing pollutant emissions, and making the flue gas cleaner.

[0027] Following this, the fuel, air, and flue gas in the first-stage combustion chamber 2, second-stage combustion chamber 3, and third-stage combustion chamber 4 can flow along several scrapers 9. Since the scrapers 9 are spiral-shaped, the residence time of fuel and air in the combustion chamber can be increased, thereby allowing the combustion reaction to proceed fully and reducing the probability of incomplete combustion. When the gas is discharged from the outlet of the combustion chamber, it will impact the blades 101 of the turbine mechanism 10. Since the blades 101 are inclined, they can guide the flue gas, causing it to be discharged in a spiral direction. The flue gas discharged in a spiral direction can impact the turbine blades of the generator more continuously and evenly. Compared with the flue gas discharged in a straight line, the flue gas flowing in a spiral can contact the turbine blades for a longer time and a larger area, allowing the flue gas energy to be transferred to the turbine more fully, converting it into more mechanical energy and improving the power generation efficiency of the turbine.

[0028] Next, due to the friction between the third-stage combustion chamber 4 and the sleeve 104, when the fuel delivery volume in the combustion chamber is small, the internal air pressure is low, and the blade 101 only serves as a guide and does not rotate, ensuring more complete combustion of the fuel. When the fuel delivery volume in the combustion chamber increases, the internal air pressure continues to increase, causing the blade 101 to experience greater force. When the force on the blade 101 exceeds the torque of the torsion spring 107, the blade 101 will rotate, increasing its angle and thus increasing the exhaust volume. The rotation of the blade 101 will drive the rotating component 106 to rotate, which in turn drives the limiting block 13 to rotate. When one side of the limiting block 13 abuts against the limiting position... When the blade 101 is on the other side of the groove 12, the blade 101 drives the rotating part 106 to rotate circumferentially. The rotating part 106 drives the fixed cylinder 105 to rotate. The fixed cylinder 105 drives the connecting shaft 103 to rotate. The connecting shaft 103 drives the connecting frame 102 to rotate. The connecting frame 102 overcomes the friction between the sleeve 104 and the third-stage combustion chamber 4 and drives the sleeve 104 to rotate. This enables the connecting frame 102 to drive the scraper 9 to rotate. When the scraper 9 rotates, due to its spiral design, it can scrape off the residue on the inner wall of the combustion chamber and discharge it to the outlet of the combustion chamber. Moreover, during the rotation of the scraper 9, it can also increase the exhaust rate of the flue gas, further increase the exhaust volume, and prevent the excessive gas pressure from damaging the combustion chamber.

[0029] Although embodiments of the present invention have been shown and described, it will be understood by those skilled in the art that various changes, modifications, substitutions and alterations can be made to these embodiments without departing from the principles and spirit of the present invention, the scope of which is defined by the appended claims and their equivalents.

Claims

1. A multistage cyclone microturbine combustor comprising a combustion chamber and a nozzle (1) mounted in the combustion chamber, characterized in that: The combustion chamber comprises a first combustion chamber (2), a second combustion chamber (3) and a third combustion chamber (4), and is provided with a primary air inlet (5), a secondary air inlet (6) and a tertiary air inlet (7) for conveying air into the combustion chamber; the first combustion chamber (2) and the second combustion chamber (3) are both provided with notches (8), and the unburned fuel in the first combustion chamber (2) enters the second combustion chamber (3) and the third combustion chamber (4) in sequence through the notches (8); A plurality of spiral scrapers (9) are installed in the combustion chamber, and the plurality of scrapers (9) are in contact with the inner walls of the first combustion chamber (2), the second combustion chamber (3) and the third combustion chamber (4), respectively; one end of the plurality of scrapers (9) is provided with a turbine mechanism (10) for driving the rotation of the scraper (9); when the air pressure in the combustion chamber increases, the inclination angle of the blade (101) of the turbine mechanism (10) increases accordingly.

2. A multi-stage cyclone microturbine combustor according to claim 1, characterized in that: The lengths of the first combustion chamber (2), the second combustion chamber (3) and the third combustion chamber (4) decrease in sequence.

3. A multi-stage cyclone microturbine combustor according to claim 1, wherein: The turbine mechanism (10) further comprises a connecting frame (102), a connecting shaft (103), a sleeve (104), a fixed cylinder (105), a rotating part (106) and a torsional spring (107); the sleeve (104) is rotatably connected to the outside of the third combustion chamber (4); the connecting frame (102) is fixedly connected to the sleeve (104) and the connecting shaft (103); the connecting shaft (103) is fixedly connected to the fixed cylinder (105); one end of the rotating part (106) is rotatably connected to the fixed cylinder (105), and the other end is fixedly connected to the blade (101); the torsional spring (107) is fixedly connected to the rotating part (106) and the fixed cylinder (105) at both ends.

4. A multi-stage cyclone microturbine combustor according to claim 3, wherein: A plurality of groups of support plates (11) are fixedly connected to one side of the connecting frame (102); the inner rings of the plurality of scrapers (9) are fixedly connected to the plurality of groups of support plates (11).

5. A multi-stage cyclone microturbine combustor according to claim 3, wherein: A limiting groove (12) is formed in the fixed cylinder (105), and a limiting block (13) is rotatably connected in the limiting groove (12); the limiting block (13) is fixedly connected to the outside of the rotating part (106).

6. A multi-stage cyclone microturbine combustor according to claim 1, wherein: The cross sections of the first combustion chamber (2), the second combustion chamber (3) and the third combustion chamber (4) are all circular, and the three are located at the same axis.

7. A multi-stage cyclone microturbine combustor according to claim 3, wherein: The contact surface between the sleeve (104) and the third combustion chamber (4) is provided with a rough surface, and there is a friction force between the two.

8. A multi-stage cyclone microturbine combustor according to claim 1, wherein: The blade (101) is inclined.

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