Turbulent burner and gas turbine

Abstract

The turbulent burner comprises a first fuel pipe, one end of the first fuel pipe is a first fuel inlet, the other end of the first fuel pipe is provided with a first panel, a first nozzle is arranged on the first panel, and a second nozzle is arranged at the position, close to the first panel, of the side wall of the first fuel pipe; the first gas pipe is arranged on the outer side of the first fuel pipe in a sleeving manner; the first swirl vane is arranged in an annular space between the first gas pipe and the first fuel pipe; the first adjusting mechanism is arranged in the first fuel pipe and comprises a first valve body and a second valve body, the first valve body controls opening and closing of the first nozzle, and the second valve body controls opening and closing of the second nozzle. The turbulent burner can flexibly adjust the fuel injection mode, optimizes the mixing of fuel and air, improves the combustion efficiency and stability, and is suitable for combusting various fuels and different combustion conditions at the same time.

Description

Technical Field

[0001] The present invention relates to the technical field of gas turbine burners, and in particular to an adjustable dual-fuel multi-stage swirl burner, which is suitable for burning medium and low calorific value fuels and has high efficiency, stable combustion and low NOx emission performance. Background Art

[0002] In the field of gas turbine burner technology, the design of traditional burners generally has problems such as insufficient fuel adaptability and limited emission control capabilities. Currently, most burners use fixed-structure nozzles and air flow channels, and their swirl intensity and fuel injection angle lack dynamic adjustment functions. When the type of fuel changes, for example, switching from high-calorific value natural gas to medium- and low-calorific value fuels such as zero-carbon ammonia fuel or biomass gas, it is necessary to physically transform the internal structure of the burner or redesign the nozzle layout, resulting in high equipment modification costs and long cycles. Especially for fuels with significant differences in chemical reaction rates such as ammonia fuel, it is difficult for existing burners to achieve efficient mixing of fuel and air through simple parameter adjustments, and problems such as flame instability and combustion oscillation are prone to occur. In addition, the traditional single-stage swirl structure has insufficient control accuracy for the staged air supply, the mixing uniformity of fuel and air is poor, and local high-temperature areas are easily formed in the combustion chamber, resulting in increased thermal nitrogen oxides (NOx) emissions. Summary of the Invention

[0003] In order to overcome the defects in the prior art, the first object of the present invention is to provide a swirl burner, and the second object of the present invention is to provide a gas turbine.

[0004] In order to achieve the above object, the technical solution adopted by the present invention is:

[0005] In a first aspect, a swirl burner comprises:

[0006] a first fuel pipe having a first fuel inlet at one end and a first panel at the other end, a first nozzle being provided on the first panel, and a second nozzle being provided on a side wall of the first fuel pipe;

[0007] a first gas pipe, sleeved on the outside of the first fuel pipe;

[0008] a first swirl blade arranged in an annular space between the first gas pipe and the first fuel pipe;

[0009] The first regulating mechanism is arranged in the first fuel pipe and includes a first valve body and a second valve body. The first valve body controls the opening and closing of the first nozzle, and the second valve body controls the opening and closing of the second nozzle.

[0010] The first panel is provided with multiple first nozzles. In actual processing, the multiple first nozzles can be distributed in a circular pattern with equal intervals along the edge of the first panel. The number of first nozzles can be set to 6 to 10. Optionally, the number of first nozzles is 8. The first nozzles are tilted from the side facing the first fuel inlet to the side facing away from the first fuel inlet, and from farther away from the edge of the first panel to closer to the edge of the first panel. The axis of the first nozzle forms an angle of 0° to 60° with the central axis of the first fuel pipe. By tilting the first nozzles, the fuel is injected at an inclined angle. The tilted first nozzle arrangement facilitates adjusting the mixing efficiency of the injected fuel and the primary gas, enabling lean, rich, and stoichiometric combustion in localized areas, thereby avoiding incomplete combustion and high NOx emissions. The first fuel pipe, first gas pipe, and first swirl vanes constitute a primary swirler, in which the primary gas, which can be air, flows. As the air flows through the annular space between the first fuel pipe and the first gas pipe, the first swirl vanes cause the air to swirl, forming a primary swirl gas with a strong swirl characteristic.

[0011] Optionally, the second nozzle is arranged at the first fuel pipe near the first panel. In actual processing, multiple second nozzles can be arranged at equal intervals around the side wall of the first fuel pipe. The number of second nozzles can be set to 6 to 10. Optionally, the number of second nozzles is 8. The axis of the second nozzle is at an angle of 60° to 90° with the central axis of the first fuel pipe. The inclination direction of the second nozzle is the vector direction of the fuel flow. The inclined setting of the second nozzle is also conducive to adjusting the mixing efficiency of the injected fuel and the primary gas. The mixing efficiency of the fuel injected by the second nozzle and the primary gas is higher, which reduces the mixing length required for the fuel and gas, and is suitable for fuels with low calorific value.

[0012] The first nozzle is located at the end face of the first fuel pipe, with its spray direction forming a small angle (0° to 60°) with the central axis of the first fuel pipe, primarily axially spraying. Compared to the second nozzle, the first nozzle has a higher fuel flow rate and significantly shortens the fuel's residence time at the nozzle, effectively reducing erosion damage to the nozzle caused by high-temperature flames and improving the nozzle's durability under conditions with fuels having high chemical reaction rates.

[0013] The second nozzle is located on the side wall of the first fuel pipe. The injection direction has a large angle (60° to 90°) with the central axis of the first fuel pipe, and is mainly radial or tangential. The fuel flow rate is lower and the coverage range is wider.

[0014] By simultaneously providing a first nozzle and a second nozzle on the first fuel pipe, the performance and applicability of a swirl burner can be significantly improved. When burning gas fuels with a high chemical reaction rate, opening the first nozzle allows the fuel to quickly mix with air and burn, providing a stable fire source for the combustion process. It can also be used in conjunction with the second nozzle to increase the fuel injection rate under high-load conditions. When burning gas fuels with a low chemical reaction rate, closing the first nozzle and opening the second nozzle improves the fuel-air mixing efficiency and ensures sufficient combustion of the low-reaction-rate fuel. Furthermore, opening both nozzles simultaneously reduces the fuel injection velocity, resulting in more uniform fuel distribution within the combustion chamber and improving combustion stability and efficiency. Because it can be used to burn both high- and low-reaction-rate fuels, the burner's applicable fuel range is expanded, enhancing its versatility. Generally, gas fuels with an activation energy below 40 kJ / mol are considered to have a high chemical reaction rate, those with an activation energy between 40 and 120 kJ / mol are considered to have a medium chemical reaction rate, and those with an activation energy greater than 120 kJ / mol are considered to have a low chemical reaction rate.

[0015] Optionally, the first valve body includes:

[0016] a second panel, attached to the inner side of the first panel, and having a first through hole corresponding to the first nozzle;

[0017] The first control rod is vertically connected to the second panel, and the first control rod can drive the second panel to rotate around the axis so that the first through hole and the first nozzle are arranged opposite to or staggered. Optionally, the first control rod can be driven by a servo motor.

[0018] The coordination of the second panel and the first control lever enables precise adjustment of fuel injection from the first nozzle, allowing for flexible adjustment of the fuel injection pattern and injection volume based on varying fuel characteristics and operating conditions. For example, when burning a gas fuel with a low chemical reaction rate, the first valve stem can be rotated to offset the first through-hole on the second panel from the first nozzle, closing the first nozzle and allowing fuel to be injected only from the second nozzle, improving fuel-air mixing efficiency. Conversely, when burning a gas fuel with a higher chemical reaction rate, the first control lever can be rotated to align the first through-hole with the first nozzle, opening the first nozzle and preventing high-temperature flame erosion of the burner nozzle. Under high-load conditions, the first control lever can be manipulated to operate both the first and second nozzles simultaneously, reducing the fuel injection velocity while meeting high load requirements. This precise adjustment capability enhances the burner's adaptability to a variety of complex operating conditions and is easy to operate, eliminating the need for extensive disassembly or component replacement, effectively reducing maintenance costs and improving the overall performance and reliability of the burner.

[0019] The second valve body includes:

[0020] a collar, nested in the first fuel pipe, the collar being provided with a second through hole corresponding to the second nozzle;

[0021] A second control rod, one end of which is connected to the collar and the other end of which is provided with a limit block;

[0022] The end of the first fuel pipe away from the first panel is provided with a limiting groove matched with the limiting block, and the limiting block can slide along the limiting groove to drive the collar to rotate, so that the second through hole and the second nozzle are arranged oppositely or staggered.

[0023] Optionally, the second control rod may be driven by a servo motor.

[0024] Specifically, the limiting block and the limiting groove are in matching arc shapes, and the limiting groove is longer than the limiting block. The limiting block is slid along the limiting groove to drive the collar to rotate, so that the second through hole and the second nozzle are aligned or misaligned.

[0025] Optionally, there are two second control rods, which are arranged opposite to each other and connected to the collar. The second control rods are fan-shaped, which facilitates their rotation in the first fuel pipe.

[0026] Corresponding bolt holes are provided on the stop block and the first fuel pipe. Once the stop block is properly positioned within the arc-shaped stop slot, bolts can be used to connect the stop block and the corresponding bolt holes on the first fuel pipe, thereby fixing the position of the stop block and, consequently, the positional relationship between the second through hole and the second nozzle, ensuring reliable control under various operating conditions.

[0027] Through the cooperation of the collar and the second control rod, the fuel injection control of the second nozzle is more precise and can be flexibly adjusted according to different combustion conditions. Under low load conditions and low air and fuel mixing efficiency, the collar can be rotated by sliding the limit block to align the second through hole with the second nozzle, open the second nozzle, improve the mixing efficiency of the fuel and air, achieve partial premixing, and effectively reduce the axial space required for complete combustion of the fuel, making the combustion chamber structure compact and ensuring that the fuel can be completely burned. When it is necessary to adjust the fuel injection mode to adapt to different fuel characteristics, the second valve body structure can also be used to accurately control the opening and closing of the second nozzle, thereby enhancing the burner's adaptability to various complex working conditions. In addition, this structural design is simple and reliable, and the operation process does not require complicated steps, nor does it require large-scale disassembly or replacement of parts of the burner, effectively reducing maintenance costs, improving the stability and reliability of the burner, and ensuring that it can operate efficiently under different working environments.

[0028] Optionally, the burner further comprises:

[0029] a first sleeve, sleeved on the outside of the first gas pipe;

[0030] a second fuel pipe disposed in the first sleeve, one end of the second fuel pipe being a second fuel inlet, the other end of the second fuel pipe being a second fuel outlet, the second fuel outlet being on the same side as the first nozzle as the third nozzle;

[0031] The secondary cyclone is sleeved on the outer side of the first sleeve.

[0032] Optionally, the secondary cyclone includes a second inner gas tube, a second outer gas tube, and second swirl blades. The second inner gas tube is sleeved outside the first sleeve, the second outer gas tube is sleeved outside the second inner gas tube, and the second swirl blades are arranged in the annular space between the second inner gas tube and the second outer gas tube. Secondary gas, which may be air, flows in the secondary cyclone. When the air flows through the annular space, the second swirl blades cause the air to rotate, thereby forming a secondary swirl gas with strong rotational characteristics.

[0033] Optionally, the number of the second swirl blades is 8 to 22, the thickness of the second swirl blades is 1.5 mm, and the angle between the blades and the central axis of the burner is 0 to 75°. Generally, for low-calorific value fuels, the number of blades can be increased, and the angle between the blades and the central axis can be increased. Conversely, for high-calorific value fuels, the number of blades can be reduced, but not less than 8, and the angle between the blades and the central axis can be reduced, preferably not less than 35°.

[0034] Optionally, there are multiple second fuel pipes, and the first sleeve is provided with multiple first cylindrical through-holes compatible with the second fuel pipes, with the second fuel pipes disposed within the first cylindrical through-holes. Optionally, the multiple second fuel pipes may be arranged in a circular pattern with equal intervals along the end surface of the first sleeve. The number of second fuel pipes can be set based on actual operating conditions. Generally, the number of second fuel pipes can be set to 6 to 10. Optionally, there are 8 second fuel pipes, arranged in a circular pattern with equal intervals along the end surface of the first sleeve.

[0035] Optionally, the second fuel pipe may be a one-piece structure or comprised of multiple pipe components. Specifically, the second fuel pipe may include a first straight pipe and a first curved pipe connected to the first straight pipe. The end of the first straight pipe facing away from the first curved pipe forms a second fuel inlet, and the end of the first curved pipe facing away from the first straight pipe forms a second fuel outlet, i.e., a third nozzle.

[0036] The curvature of the first bend is 0° to 90°. The use of an arc-shaped nozzle can reduce the pressure loss of fuel injection and make the flow rate of the injected fuel uniform. By setting the first bend and changing the outlet angle of the third nozzle, the injection direction of the fuel ejected from the second fuel pipe can be better matched with the gas in the secondary swirler, thereby enhancing the synergy between the two, improving the fuel and gas mixing efficiency, and allowing the fuel to be more evenly dispersed in the gas, expanding the mixing area, and avoiding local over-concentration or over-leanness. At the same time, the curvature design of the first bend can match the complex air flow field distribution inside the burner, so that the fuel is injected into the area with appropriate flow rate and pressure, reducing flow resistance and ensuring smooth and stable injection. In addition, it helps to form a stable flame, avoid problems such as jitter and flameout, and can adapt to different combustion conditions, such as load changes or changes in fuel type, to ensure a safe, reliable and efficient combustion process.

[0037] The opening directions of multiple third nozzles in a swirl burner can be individually adjusted based on usage conditions. For example, all third nozzles can be oriented toward the side facing away from the burner center; or all third nozzles can be oriented toward the burner center; or some third nozzles can be oriented toward the side facing away from the burner center, while others can be oriented toward the burner center.

[0038] Optionally, the swirl burner further includes a second adjustment mechanism, which is provided on the first sleeve and is used to drive the first curved pipe to rotate around the axis of the first straight pipe to adjust the injection direction of the third nozzle. Specifically, the second adjustment mechanism includes:

[0039] a first limiting portion, provided on a side of the first sleeve facing the first nozzle;

[0040] a first ring gear, disposed between the first limiting portion and the first sleeve;

[0041] The first gear is sleeved on the first bend of the second fuel pipe and meshes with the first gear ring.

[0042] The second adjustment mechanism has a simple structure, achieving compact space utilization and simple power transmission. When one of the first curved pipes is rotated, the first curved pipe drives the first gear fixedly connected to it to rotate, the first gear drives the first ring gear to rotate, and the first ring gear drives the other first gears to rotate, thereby causing the other first curved pipes to rotate synchronously, facilitating adjustment of the opening direction of the third nozzle.

[0043] The second adjustment mechanism optimizes the mixing of fuel and air and adapts to different fuel characteristics. For fuels with low chemical reaction rates, the injection direction of the third nozzle can be adjusted to be in the same direction as the secondary air, enhancing the swirl intensity and improving the combustion efficiency of low-calorific value fuels. The second adjustment mechanism also enables the burner to adapt to different operating conditions, flexibly adjusting the injection direction under high and low load conditions to achieve optimal mixing. This mechanism expands the burner's applicable fuel range, is compatible with multiple fuels, and enables stratified combustion. At the same time, it helps improve combustion stability and efficiency, stabilizes the flame, avoids jitter and flameout, ensures full fuel combustion, and improves combustion efficiency. In addition, by optimizing the mixing and combustion process, it can reduce local high-temperature areas within the combustion chamber, reduce thermal and fuel-type NOx emissions, and benefit the environment.

[0044] It is understood that the first straight tube can be fixedly connected to the first sleeve, and the first curved tube can be provided on the side of the first sleeve facing the first nozzle. The first straight tube and the first curved tube are relatively connected. A first locking mechanism can be provided on the first sleeve or the first limiting portion to fix the first curved tube relative to the first sleeve after the first curved tube is adjusted in position.

[0045] Optionally, the first limiting portion is provided with a first placement position for placing the first gear. The first limiting portion can be either an integral structure or a split structure. A split structure facilitates assembly of the second adjustment mechanism with the second fuel pipe. Specifically, the split first limiting portion can include a first limiting first subsection and a first limiting second subsection. The first limiting first subsection is provided with a first semicircular notch that cooperates with the first gear, forming the first placement position for the first gear, and a second semicircular notch that cooperates with the first straight tube. The first limiting second subsection is provided with a third semicircular notch that cooperates with the first straight tube. The second and third semicircular notches combine to form a first cylindrical through hole that cooperates with the first straight tube. The first limiting portion can limit the radial and axial movement of the first gear, the first gear ring, and the first elbow in the first sleeve, but does not limit their circumferential rotation. This ensures that when the first gear ring rotates, it can accurately drive the first gear and synchronously drive the first elbow to rotate, thereby achieving angle adjustment of the third nozzle.

[0046] Optionally, the swirl burner further includes:

[0047] a second sleeve, sleeved on the outside of the secondary cyclone;

[0048] a third fuel pipe, disposed in the second sleeve, with one end on the same side as the first nozzle forming a fourth nozzle;

[0049] The third gas pipe is sleeved outside the second sleeve. The third gas pipe flows with a tertiary gas, which may be air.

[0050] Optionally, there are multiple third fuel pipes. Multiple second cylindrical through-holes compatible with the third fuel pipes are provided within the second sleeve, and the third fuel pipes are disposed within the second cylindrical through-holes. Optionally, the multiple third fuel pipes may be arranged in a circular pattern with equal spacing along the end surface of the second sleeve. The number of third fuel pipes can be set based on actual operating conditions. Generally, the number of third fuel pipes can be set to 12 to 18. Optionally, there are 16 third fuel pipes, arranged in a circular pattern with equal spacing along the end surface of the second sleeve.

[0051] Optionally, the third fuel pipe may be a one-piece structure or comprised of multiple pipes. Specifically, the third fuel pipe may include a second straight pipe and a second curved pipe connected to the second straight pipe. The end of the second straight pipe facing away from the second curved pipe forms a third fuel inlet, while the end of the second curved pipe facing away from the first straight pipe forms a third fuel outlet, i.e., a fourth nozzle.

[0052] The curvature of the second bend is 0° to 90°, and the use of an arc nozzle can reduce the pressure loss of fuel injection and make the flow rate of the injected fuel uniform. The second bend has a certain curvature, which can make the injection direction of the fuel ejected from the third fuel pipe better match the air in the third gas pipe, enhance the synergy between the two, improve the fuel and air mixing efficiency, make the fuel more evenly dispersed in the air, expand the mixing area, and avoid local over-concentration or over-leanness. At the same time, the curvature design can match the complex air flow field distribution inside the burner, so that the fuel is injected into the area with appropriate flow rate and pressure, reduce flow resistance, and ensure smooth and stable injection. In addition, it helps to form a stable flame, avoid jitter and flameout problems, and can adapt to different combustion conditions, such as load changes or changes in fuel type, to ensure a safe, reliable and efficient combustion process.

[0053] The opening directions of multiple fourth nozzles in a swirl burner can be individually adjusted based on usage conditions. For example, all fourth nozzles can be oriented away from the burner center; or all fourth nozzles can be oriented toward the burner center; or some fourth nozzles can be oriented away from the burner center, while others can be oriented toward the burner center.

[0054] Optionally, the swirl burner further includes a third adjustment mechanism, which is provided on the second sleeve and is used to drive the second curved pipe to rotate around the axis of its second straight pipe to adjust the injection direction of the fourth nozzle. Specifically, the third adjustment mechanism includes:

[0055] a second limiting portion, provided on a side of the second sleeve facing the first nozzle;

[0056] a second ring gear, disposed between the second limiting portion and the second sleeve;

[0057] The second gear is sleeved on the second bend of the third fuel pipe and meshes with the second gear ring.

[0058] This third adjustment mechanism features a simple structure, enabling compact space utilization and streamlined power transmission. Rotating one of the second curved tubes drives the second gear fixed to it, which in turn drives the second ring gear, which in turn drives the other second gears. This synchronizes the rotation of the other second curved tubes, facilitating adjustment of the opening direction of the fourth nozzle. Similarly, the third adjustment mechanism optimizes the fuel-air mixture and adapts to different fuel characteristics.

[0059] It is understood that the second straight tube can be fixedly connected to the second sleeve, and the second curved tube can be provided on the side of the second sleeve facing the first nozzle. The second straight tube and the second curved tube are relatively connected. A second locking mechanism can be provided on the second sleeve or the second limiting portion to fix the second curved tube relative to the second sleeve after the second curved tube is adjusted.

[0060] Optionally, the second limiting portion is provided with a second placement location for the second gear. The second limiting portion can be either a one-piece structure or a split structure. A split structure facilitates assembly of the third adjustment mechanism and the third fuel pipe. Specifically, the split second limiting portion can include a second limiting first subsection and a second limiting second subsection. The second limiting first subsection is provided with a fourth semicircular notch that mates with the second gear, forming the second placement location for the second gear, and a fifth semicircular notch that mates with the second straight pipe. The second limiting second subsection is provided with a sixth semicircular notch that mates with the second straight pipe. The fifth and sixth semicircular notches combine to form a second cylindrical through hole that mates with the second straight pipe. The second limiting portion limits the radial and axial movement of the second gear, second gear ring, and second elbow in the second sleeve, but does not limit their circumferential rotation. This ensures that when the second gear ring rotates, it can precisely drive the second gear and synchronously drive the second elbow to achieve angle adjustment of the fourth nozzle.

[0061] According to actual usage, more combustion units consisting of fuel pipes, gas pipes, swirl blades and regulating mechanisms can be set up according to the arrangement of the above-mentioned fuel pipes, gas pipes, swirl blades and regulating mechanisms to meet the situation of simultaneous combustion of more than three fuels.

[0062] Optionally, the burner further includes a fuel diversion device, and the fuel diversion device includes:

[0063] a fourth fuel pipe, one end of which is a fourth fuel inlet and the other end of which is connected to a fuel branch pipe;

[0064] a first circulating pipe having a first side hole formed on its circumference and a first end hole formed on its end face, the first side hole being connected to one end of the fuel branch pipe, and the first end hole being connected to the second fuel inlet;

[0065] The second circulation pipe has a second side hole on its circumference and a second end hole on its end face. The second side hole is communicated with the other end of the fuel branch pipe, and the second end hole is communicated with the third fuel inlet.

[0066] According to actual application requirements, the diverter pipe can be a straight pipe with uniform diameter, or a straight pipe with gradually changing diameter to meet the fuel flow requirements in different fuel pipes.

[0067] The fuel distribution device distributes fuel from a single fuel inlet to the secondary and tertiary combustion units in a preset ratio through the graded flow diversion of the first and second circulation pipes. These first and second circulation pipes act as fuel collection and buffers, ensuring uniform fuel distribution and stabilizing fuel pressure. This also reduces the number of fuel delivery pipes, making the burner structure more compact, preventing excessive fuel pipes from interfering with air flow through the air deflector, and facilitating installation and maintenance.

[0068] Optionally, the burner further includes an air diversion structure, and the air diversion structure includes:

[0069] A first air guide plate is provided with a through hole for the first fuel pipe to pass through, and the first air guide plate forms a first air flow channel on the side facing the fuel inlet for distributing air to the primary cyclone;

[0070] The second air guide plate is arranged on the side of the first air guide plate facing away from the fuel inlet. The diameter of the second air guide plate is smaller than the diameter of the first air guide plate. A second air flow channel is formed between the first air guide plate and the second air guide plate, which is used to distribute air to the secondary cyclone. The third air flow channel is formed on the side of the second air guide plate facing away from the fuel inlet, which is used to distribute air to the third gas pipe.

[0071] Through the stepped design of the multi-stage air guide plate, the air diversion structure can dynamically distribute air to different combustion units according to combustion requirements, ensuring that the oxygen concentration of each stage of combustion matches the fuel injection amount, inhibiting the formation of local high-temperature areas, and thus effectively reducing thermal NOx generation.

[0072] The operation mode of the above burners can be adjusted according to the fuel type and working conditions. The following are some examples of possible operation modes:

[0073] 1. Single fuel combustion mode:

[0074] When using only a single fuel, the fuel injection pattern is adjusted via the first and second valve bodies. Under low-load conditions, the first nozzle is closed and the second nozzle is opened. The lateral injection from the second nozzle enhances the mixing efficiency of the fuel and the primary swirl air, shortening the axial space required for combustion and improving low-load stability. Under high-load conditions, the first and second nozzles are opened simultaneously to increase fuel flow without increasing flow velocity, ensuring a compact combustion chamber structure and complete fuel combustion. At this point, the fuel injection direction of the third and fourth nozzles is preferably radially outward, mixing with the corresponding swirl air to achieve stratified combustion, reducing localized high temperatures and NOx generation.

[0075] 2. Dual-fuel co-combustion mode:

[0076] When using two fuels with different calorific values ​​or reaction rates, the fuel with higher calorific value or faster reaction rate is injected through the first and second nozzles, and the fuel with lower calorific value is delivered through the third and fourth nozzles. The injection direction of the third and fourth nozzles is adjusted synchronously by rotating the ring gear, and the air distribution is adjusted in combination with the size of the air guide plate:

[0077] Method 1: The third and fourth nozzles are each half directed toward the center and the outside of the burner. The diameter of the first air guide plate is reduced to increase the primary air flow in the first-stage cyclone. Simultaneously, the diameter of the second air guide plate is reduced to increase the secondary air flow in the second-stage cyclone to ensure complete combustion of the fuel in the mixing area.

[0078] Method 2: All third and fourth nozzles are pointed towards the center. The diameter of the first air guide plate needs to be reduced to increase the primary air flow, and the diameter of the second air guide plate needs to be reduced to increase the secondary air flow, while reducing the tertiary air supply.

[0079] Method 3: All third nozzles face outward, and all fourth nozzles face inward. Simply reduce the diameter of the second air guide plate to increase the secondary air flow in the secondary cyclone and reduce the tertiary air flow in the third gas pipe.

[0080] Method 4: All nozzles are arranged tangentially, in line with the swirl direction. No need to adjust the air guide plate, but the overall swirl intensity is enhanced, significantly improving the mixing efficiency and combustion stability of low calorific value fuels.

[0081] By rotating the valve body to control the nozzle opening and closing, combined with flexible adjustment of the deflector edge diameter, primary, secondary, and tertiary air flow can be dynamically allocated to suit different fuel injection patterns. For example, in dual-fuel combustion, the diameter of the first deflector can be reduced to prioritize the primary swirl air demand, while the second deflector can be adjusted simultaneously to optimize the secondary and tertiary air ratios. Furthermore, the design of the fuel straight pipe and diverter device avoids fuel premixing, directly achieving stratified combustion and further reducing NOx emissions.

[0082] The burner supports smooth switching from single to dual fuels and is suitable for combinations of high-calorific-value fuels with medium- and low-calorific-value fuels such as ammonia and biomass gas. By adjusting nozzle direction, air flow, and swirl intensity, it can adapt to different loads, fuel characteristics, and emission requirements, ensuring the coordinated optimization of efficient and stable combustion and environmental performance.

[0083] A second aspect provides a gas turbine including the aforementioned swirl burner. The combustion chamber of the gas turbine comprises an annular air flow channel formed by a front outer tube, a rear outer tube, a flame tube, and a tail tube, with an end cap at the front end. The fuel pipe of the swirl burner is fixedly connected to the end cap. A first air guide plate and a second air guide plate within the swirl burner divide the air into three streams. The end cap and the first air guide plate form a primary air flow channel, the first and second air guide plates form a secondary air flow channel, and the second air guide plate and the front outer tube form a tertiary air flow channel. During operation, air, after being compressed by the compressor, flows through the annular air flow channel to the combustion chamber head. Due to the obstruction and diameter setting of the first and second air guide plates, the air is divided into three streams: the first stream flows through the primary swirler via the primary air flow channel, the second stream flows through the secondary swirler via the secondary air flow channel, and the third stream flows through the tertiary air flow channel to the third gas pipe. Each level of air is thoroughly mixed with the fuel in the combustion chamber, resulting in stable and efficient combustion. The high-temperature gases generated by the combustion flow within the combustion chamber and are then discharged.

[0084] Due to the application of the above technical solution, the present invention has the following advantages compared with the prior art:

[0085] 1. By configuring the first and second nozzles, the activation method can be selected based on the chemical reaction rate of the fuel. For fuels with high chemical reaction rates, opening the first nozzle allows for rapid mixing and combustion. For fuels with low chemical reaction rates, closing the first nozzle and opening the second nozzle improves mixing efficiency. Simultaneously opening both nozzles can also reduce the injection velocity, accommodating high-load conditions.

[0086] 2. The first valve body and the second valve body in the first adjustment mechanism respectively control the opening and closing of the first nozzle and the second nozzle. By rotating the first control rod to drive the second panel to rotate, and sliding the limit block along the arc-shaped limit groove to drive the ring to rotate, precise alignment or misalignment control is achieved. It has a simple structure and is easy to operate.

[0087] 3. The second and third adjustment mechanisms respectively drive the first and second curved pipes to rotate about the axis of their respective straight pipes, adjusting the injection direction of the third and fourth nozzles to better mix the fuel and air and improve combustion efficiency. The adjustment mechanisms are driven by the meshing of the ring gear and gears, ensuring stable transmission.

[0088] 4. The fuel diversion device distributes the fuel from a single fuel inlet to the secondary and tertiary combustion units in a preset proportion through the first and second circulation pipes, adapting to the needs of different combustion stages, optimizing the fuel-air mixing, improving combustion efficiency, enhancing combustion stability, expanding fuel applicability, and facilitating maintenance and management.

[0089] 5. The first and second air guide plates of the air diversion structure form the first, second and third air flow channels, which distribute air to the first-stage cyclone, the second-stage cyclone and the third gas pipe respectively, ensuring that each combustion unit has an appropriate amount of air supply to promote full combustion of the fuel.

[0090] 6. Each component is arranged in a nested manner, making full use of space and making the burner compact and suitable for a variety of installation environments. At the same time, the components are relatively independent, making them easy to disassemble, install, maintain and repair.

[0091] In order to make the above and other objects, features and advantages of the present invention more obvious and easy to understand, preferred embodiments are given below and described in detail with reference to the accompanying drawings. BRIEF DESCRIPTION OF THE DRAWINGS

[0092] In order to more clearly illustrate the embodiments of the present invention or the technical solutions in the prior art, the following briefly introduces the drawings required for use in the embodiments or the description of the prior art. Obviously, the drawings described below are only some embodiments of the present invention. For ordinary technicians in this field, other drawings can be obtained based on these drawings without paying any creative work.

[0093] Figure 1 1 is a schematic structural diagram of a swirl burner according to an embodiment of the present invention;

[0094] Figure 2 This is a schematic diagram of the structure of a primary combustion unit in an embodiment of the present invention;

[0095] Figure 3 This is a side view of the primary combustion unit in the embodiment of the present invention. Figure 1 ;

[0096] Figure 4 This is a side view of the primary combustion unit in the embodiment of the present invention. Figure 2 ;

[0097] Figure 5 is a schematic diagram of a first adjustment mechanism in an embodiment of the present invention;

[0098] Figure 6 This is a schematic structural diagram of the first valve body in an embodiment of the present invention;

[0099] Figure 7 Schematic diagram of the structure of the second valve body in an embodiment of the present invention;

[0100] Figure 8 This is a schematic diagram of the structure of a secondary combustion unit in an embodiment of the present invention;

[0101] Figure 9 This is a schematic diagram of the assembly of the secondary combustion unit and the primary combustion unit in an embodiment of the present invention;

[0102] Figure 10 1 is a schematic structural diagram of a first sleeve in an embodiment of the present invention;

[0103] Figure 11 This is a schematic diagram of the assembly of the first sleeve and the second fuel pipe in an embodiment of the present invention;

[0104] Figure 12 Schematic diagram of the structure of the secondary cyclone in an embodiment of the present invention;

[0105] Figure 13 is a schematic diagram of a second adjustment mechanism in an embodiment of the present invention;

[0106] Figure 14 This is a schematic diagram of the structure of a three-stage combustion unit in an embodiment of the present invention;

[0107] Figure 15 1 is a schematic diagram of the structure of the second sleeve in an embodiment of the present invention;

[0108] Figure 16 This is a schematic diagram of the assembly of the second sleeve and the third fuel pipe in an embodiment of the present invention;

[0109] Figure 17 is a schematic diagram of a third adjustment mechanism in an embodiment of the present invention;

[0110] Figure 18 1 is a side view of a swirl burner according to an embodiment of the present invention;

[0111] Figure 19 This is a schematic diagram of the diversion structure in the embodiment of the present invention. Figure 1 ;

[0112] Figure 20 This is a schematic diagram of the diversion structure in the embodiment of the present invention. Figure 2 ;

[0113] Figure 21 Schematic diagram of a gas turbine according to an embodiment of the present invention.

[0114] Reference numerals in the above drawings:

[0115] 1. Primary combustion unit; 11. First fuel pipe; 111. First fuel inlet; 112. First nozzle; 113. Second nozzle; 114. First panel; 115. Stopper; 12. First gas pipe; 13. First swirl blade; 14. First valve body; 141. Second panel; 142. First control rod; 143. First through hole; 15. Second valve body; 151. Collar; 152. Second control rod; 153. Second through hole; 154. Stopper;

[0116] 2. Secondary combustion unit; 21. First sleeve; 211. First cylindrical through hole; 22. Second fuel pipe; 221. First straight pipe; 222. First curved pipe; 223. Third nozzle; 23. Second inner gas pipe; 24. Second outer gas pipe; 25. Second swirl blade; 26. Second adjustment mechanism; 261. First position limiter; 2611. First placement position; 2612. First position limiter first subsection; 2613. First position limiter second subsection; 262. First ring gear; 263. First gear;

[0117] 3. Three-stage combustion unit; 31. Second sleeve; 311. Second cylindrical through hole; 32. Third gas pipe; 33. Third regulating mechanism; 331. Second position-limiting portion; 3311. Second placement position; 3312. Second position-limiting first subsection; 3313. Second position-limiting second subsection; 332. Second ring gear; 333. Second gear; 34. Third fuel pipe; 341. Second straight pipe; 342. Second curved pipe; 343. Fourth nozzle;

[0118] 4. Air diversion structure; 41. First air guide plate; 42. Second air guide plate; 43. First air flow channel; 44. Second air flow channel; 45. Third air flow channel;

[0119] 5. Fuel distribution device; 51. Fourth fuel pipe; 52. Fuel branch pipe; 53. First circulation pipe; 531. First end hole; 54. Second circulation pipe; 541. Second end hole;

[0120] 6. Front outer tube; 7. Rear outer tube; 8. Flame tube; 9. Tail tube; 10. End cover. DETAILED DESCRIPTION

[0121] The following will clearly and completely describe the technical solutions in the embodiments of the present invention in conjunction with the accompanying drawings. Obviously, the described embodiments are only part of the embodiments of the present invention, not all of the embodiments. Based on the embodiments of the present invention, all other embodiments obtained by ordinary technicians in this field without making creative efforts are within the scope of protection of the present invention.

[0122] Example 1: See Figure 1As shown, a swirl burner includes a primary combustion unit 1. The primary combustion unit 1 includes a primary swirler and a first regulating mechanism, wherein the first regulating mechanism is used to regulate the opening and closing of a nozzle on a first fuel pipe in the primary swirler.

[0123] See also Figure 2 As shown, the first-stage swirler includes a first fuel pipe 11, a first gas pipe 12 and a first swirl blade 13 arranged between the first fuel pipe 11 and the first gas pipe 12. The first-stage swirler flows with a first-stage gas. The gas can be air. When the air flows through the annular space between the first fuel pipe 11 and the first gas pipe 12, the first swirl blade 13 will cause the air to rotate, thereby forming a first-stage swirl gas with strong rotation characteristics. The first fuel pipe 11 is a cylindrical tube, one end of which is a first fuel inlet 111, and the other end is provided with a circular first panel 114. A first nozzle 112 is provided on the first panel 114, and a second nozzle 113 is provided on the side wall of the first fuel pipe 11. The first gas pipe 12 is a cylindrical tube, which is coaxially sleeved on the outside of the first fuel pipe 11. See Figure 5 As shown, the first regulating mechanism is provided in the first fuel pipe 11 and includes a first valve body 14 and a second valve body 15 . The first valve body 14 controls the opening and closing of the first nozzle 112 , and the second valve body 15 controls the opening and closing of the second nozzle 113 .

[0124] In one possible embodiment, see Figure 3 As shown, the first panel 114 is provided with eight first nozzles 112, which are distributed in a circular pattern with equal intervals along the edge of the first panel 114. The first nozzles 112 are inclined cylindrical holes formed in the first panel 114. The first nozzles 112 are inclined from the side facing the first fuel inlet 111 to the side facing away from the first fuel inlet 111, and from away from the edge of the first panel 114 to closer to the edge of the first panel 114. The axis of the first nozzle 112 forms a 45° angle with the central axis of the first fuel pipe 11.

[0125] In one possible embodiment, eight second nozzles 113 are provided on the sidewall of the first fuel pipe 11. The eight second nozzles 113 are evenly spaced around the sidewall of the first fuel pipe 11. The axes of the second nozzles 113 form a 90° angle with the central axis of the first fuel pipe 11. Optionally, the second nozzles 113 are provided on the first fuel pipe 11 near the first panel 114.

[0126] In one possible embodiment, see Figure 6As shown, the first valve body 14 includes a second panel 141 and a first control rod 142. The second panel 141 is attached to the inside of the first panel 114 and defines a first through-hole 143 corresponding to the first nozzle 112. The diameter of the first through-hole 143 is the same as that of the first nozzle 112. The first control rod 142 is perpendicularly connected to the center of the second panel 141. Rotating the first control rod 142 drives the second panel 141 about its axis, aligning or misaligning the first through-hole 143 with the first nozzle 112. When the first through-hole 143 is aligned with the first nozzle 112, fuel entering from the first fuel inlet 111 can pass through the first through-hole 143 and the first nozzle 112 sequentially. When the first through-hole 143 is misaligned with the first nozzle 112, the second panel 141 blocks the first nozzle 112, and fuel entering from the first fuel inlet 111 is blocked by the second panel 141 and cannot enter the first nozzle 112. Optionally, the first control rod 142 may be driven to rotate by a servo motor.

[0127] In one possible embodiment, see Figure 7 As shown, the second valve body 15 includes a collar 151 and two control rods. The collar 151 is a circular ring that nests within the first fuel pipe 11, with its outer wall fitting against the inner wall of the first fuel pipe 11. A second through-hole 153 is defined in the collar 151, corresponding to the second nozzle 113. The diameter of the second through-hole 153 is the same as that of the second nozzle 113. A second control rod 152 is connected to the collar 151 at one end and has an arcuate stopper 154 at the other end. An arcuate stopper 115 is defined at the end of the first fuel pipe 11 facing away from the first panel 114, which engages with the stopper 154. The length of the stopper 115 is greater than that of the stopper 154. By sliding the stopper 154 along the stopper 115, the collar 151 is rotated, aligning or offsetting the second through-hole 153 with the second nozzle 113. When the second through-hole 153 is aligned with the second nozzle 113, fuel entering from the first fuel inlet 111 can sequentially pass through the second through-hole 153 and the second nozzle 113. When the second through-hole 153 and the second nozzle 113 are misaligned, the collar 151 seals the second nozzle 113, and fuel entering from the first fuel inlet 111 is blocked by the collar 151 and cannot enter the second nozzle 113. Two second control rods 152 are arranged opposite each other and connected to the collar 151. The second control rods 152 are cylindrical in shape, facilitating their rotation within the first fuel pipe 11. Optionally, the second control rods 152 can be driven for rotation by a servo motor.

[0128] In one possible embodiment, see Figure 4As shown, corresponding bolt holes are provided on the stop block 154 and the first fuel pipe 11. Once the stop block 154 is properly positioned within the arcuate stop groove 115, bolts can be used to connect the stop block 154 and the corresponding bolt holes on the first fuel pipe 11, thereby fixing the position of the stop block 154. This also fixes the positional relationship between the second through hole 153 and the second nozzle 113, ensuring reliable control under different operating conditions.

[0129] In one possible embodiment, the first swirl blades 13 include ten blades and are disposed in the annular space between the first fuel pipe 11 and the first gas pipe 12. The angle between the first swirl blades 13 and the central axis of the first fuel pipe 11 is between 35° and 75°. The swirl blade angles are designed to balance swirl intensity and flow resistance. Smaller angles are suitable for gentle combustion under low-load conditions, while larger angles are suitable for enhanced mixing under high-load conditions, thereby achieving efficient, low-pollution combustion over a wide load range.

[0130] In one possible implementation, see Figure 8 As shown, the swirl burner further includes a secondary combustion unit 2, which includes a first sleeve 21, a second fuel pipe 22, a secondary swirler and a second adjustment mechanism 26. Figure 9 As shown, the first sleeve 21 is a cylindrical tube coaxially sleeved outside the first gas pipe 12. The second fuel pipe 22 is disposed within the first sleeve 21. One end of the second fuel pipe 22 is a second fuel inlet, and the other end of the second fuel pipe 22 is a second fuel outlet. The second fuel outlet is located on the same side as the first nozzle 112 and serves as the third nozzle 223. The secondary cyclone is coaxially sleeved outside the first sleeve 21.

[0131] See also Figure 10 As shown, the first sleeve 21 is provided with eight first cylindrical through holes 211 adapted to the second fuel pipe 22. The first cylindrical through holes 211 penetrate the two opposite end surfaces of the first sleeve 21 and are distributed in an annular manner with equal intervals along the end surface of the first sleeve 21. Figure 11 As shown, there are eight second fuel pipes 22, each mounted within the first cylindrical through-hole 211 of the first sleeve 21. Each second fuel pipe 22 is fixedly connected to the first sleeve 21. One end of each second fuel pipe 22 serves as a second fuel inlet, while the other end, on the same side as the first nozzle 112, serves as a second fuel outlet, i.e., the third nozzle 223.

[0132] In one possible embodiment, the second fuel pipe 22 is composed of multiple pipes. Specifically, the second fuel pipe 22 includes a first straight pipe 221 and a first curved pipe 222 that is connected to the first straight pipe 221. The end of the first straight pipe 221 facing away from the first curved pipe 222 forms a second fuel inlet, while the end of the first curved pipe 222 facing away from the first straight pipe 221 forms a second fuel outlet, namely, a third nozzle 223.

[0133] The curvature of the first bend 222 is 0° to 90°. The use of an arc-shaped nozzle can reduce the pressure loss of fuel injection and make the flow rate of the injected fuel uniform. By setting the first bend 222 and changing the outlet angle of the third nozzle 223, the injection direction of the fuel ejected from the second fuel pipe 22 can be better matched with the gas in the secondary swirler, thereby enhancing the synergistic effect between the two, improving the mixing efficiency of the fuel and the gas, allowing the fuel to be more evenly dispersed in the gas, expanding the mixing area, and avoiding local over-concentration or over-leanness. At the same time, the curvature design of the first bend 222 can match the complex air flow field distribution inside the burner, so that the fuel is injected into the area with appropriate flow rate and pressure, reducing flow resistance and ensuring smooth and stable injection. In addition, it helps to form a stable flame, avoid jitter and flameout problems, and can adapt to different combustion conditions, such as load changes or changes in fuel types, to ensure that the combustion process is safe, reliable and efficient.

[0134] In one possible embodiment, the openings of all the third nozzles 223 are oriented toward a side facing away from the center of the burner.

[0135] In one possible embodiment, the openings of all the third nozzles 223 are directed toward one side of the burner center.

[0136] In a possible embodiment, the openings of some of the third nozzles 223 face toward the side facing away from the center of the burner, and the openings of some of the third nozzles 223 face toward the side of the center of the burner.

[0137] See also Figure 12 As shown, the secondary cyclone includes a second gas inner tube 23, a second gas outer tube 24, and second swirl blades 25. The second gas inner tube 23 and the second gas outer tube 24 are both cylindrical tubes. The second gas inner tube 23 is coaxially sleeved on the outside of the first sleeve 21, and the second gas outer tube 24 is coaxially sleeved on the outside of the second gas inner tube 23. The second swirl blades 25 are arranged in the annular space between the second gas inner tube 23 and the second gas outer tube 24. The secondary gas flows in the secondary cyclone. The gas can be air. When the air flows through the annular space, the second swirl blades 25 cause the air to rotate, thereby forming a secondary swirl gas with strong rotation characteristics.

[0138] In one possible embodiment, the number of second swirl blades 25 is 20, the thickness of the second swirl blades 25 is 1.5 mm, and the angle between the blades and the central axis of the burner is 60°. Generally, for low-calorific value fuels, the number of blades can be increased, and the angle between the blades and the central axis can be increased. Conversely, for high-calorific value fuels, the number of blades can be reduced, but not less than 8, and the angle between the blades and the central axis can be reduced, preferably not less than 35°.

[0139] In one possible embodiment, see Figure 13 As shown, the swirl burner also includes a second adjusting mechanism 26, which is provided on the first sleeve 21. The second adjusting mechanism 26 is used to drive the first curved pipe 222 to rotate around the axis of its first straight pipe 221 to adjust the injection direction of the third nozzle 223.

[0140] In a possible embodiment, the second adjustment mechanism 26 includes:

[0141] A first limiting portion 261 is provided on a side of the first sleeve 21 facing the first nozzle 112;

[0142] A first gear ring 262 is provided between the first limiting portion 261 and the first sleeve 21;

[0143] The first gear 263 is sleeved on the first elbow 222 of the second fuel pipe 22 and meshes with the first gear ring 262 .

[0144] The second adjustment mechanism 26 has a simple structure, achieving compact space utilization and simple power transmission. When one of the first curved tubes 222 is rotated, the first curved tube 222 drives the first gear 263 fixedly connected thereto to rotate, which in turn drives the first ring gear 262 to rotate, which in turn drives the other first gears 263 to rotate, thereby causing the other first curved tubes 222 to rotate synchronously, facilitating adjustment of the opening direction of the third nozzle 223.

[0145] The provision of the second regulating mechanism 26 can optimize the mixing of fuel and air and adapt to different fuel characteristics. For fuels with low chemical reaction rates, the injection direction of the third nozzle 223 can be adjusted to the same direction as the secondary air, thereby enhancing the swirl intensity and improving the combustion efficiency of low calorific value fuels. The provision of the second regulating mechanism 26 can also enable the burner to adapt to different operating conditions, flexibly adjust the injection direction under high and low load conditions, and achieve optimal mixing. This mechanism expands the applicable fuel range of the burner, is compatible with a variety of fuels, and achieves stratified combustion. At the same time, it helps to improve combustion stability and efficiency, stabilize the flame, avoid shaking and flameout, ensure full combustion of the fuel, and reduce energy consumption. In addition, by optimizing the mixing and combustion process, it can reduce local high-temperature areas in the combustion chamber, reduce thermal and fuel-type NOx emissions, and benefit environmental protection.

[0146] In one possible embodiment, the first limiting portion 261 is provided with a first placement position 2611 for placing the first gear 263. The first limiting portion 261 is a split structure. When a split structure is adopted, the assembly of the second adjustment mechanism 26 and the second fuel pipe 22 can be facilitated. Specifically, the split first limiting portion 261 includes a first limiting first sub-section 2612 and a first limiting second sub-section 2613. The first limiting first sub-section 2612 is provided with a first semicircular notch that cooperates with the first gear 263, the first semicircular notch forming the first placement position 2611 of the first gear 263, and a second semicircular notch that cooperates with the first straight tube 221, the first limiting second sub-section 2613 has a third semicircular notch that cooperates with the first straight tube 221, and the second and third semicircular notches are combined to form a first cylindrical through hole 211 that cooperates with the first straight tube 221. The first limiting portion 261 can limit the radial and axial movement of the first gear 263, the first gear ring 262 and the first curved pipe 222 in the first sleeve 21, but does not limit their circumferential rotation, ensuring that when the first gear ring 262 rotates, it can accurately drive the first gear 263 and synchronously drive the first curved pipe 222 to rotate, thereby realizing the angle adjustment of the third nozzle 223.

[0147] In one possible embodiment, see Figure 14 As shown, the swirl burner also includes a three-stage combustion unit 3. The three-stage combustion unit 3 includes a three-stage DC converter and a third regulating mechanism 33. The three-stage DC converter includes a second sleeve 31 and a third gas pipe 32. The second sleeve 31 is a cylindrical cylinder, which is coaxially sleeved on the outside of the two-stage swirler. A third fuel pipe 34 is provided in the second sleeve 31. The third gas pipe 32 is coaxially sleeved on the outside of the second sleeve 31. The third gas pipe 32 flows in the third gas pipe 32. The gas can be air.

[0148] See also Figure 15As shown, the second sleeve 31 is provided with 14 second cylindrical through holes 311 adapted to the third fuel pipe 34. The second cylindrical through holes 311 pass through the two opposite end surfaces of the second sleeve 31 and are distributed in an annular manner with equal intervals along the end surface of the second sleeve 31. Figure 16 As shown, there are 14 third fuel pipes 34, each of which is disposed within the second cylindrical through-hole 311 of the second sleeve 31. Each third fuel pipe 34 is fixedly connected to the second sleeve 31. One end of each third fuel pipe 34 serves as a third fuel inlet, and the other end on the same side as the first nozzle 112 serves as a third fuel outlet, i.e., the fourth nozzle 343.

[0149] In one possible embodiment, the third fuel pipe 34 is composed of multiple pipes. Specifically, the third fuel pipe 34 includes a second straight pipe 341 and a second curved pipe 342 connected to the second straight pipe 341. The end of the second straight pipe 341 facing away from the second curved pipe 342 forms a third fuel inlet, while the end of the second curved pipe 342 facing away from the first straight pipe 221 forms a third fuel outlet, namely, a fourth nozzle 343.

[0150] The curvature of the second bend 342 is 0° to 90°. The use of an arc nozzle can reduce the pressure loss of fuel injection and make the flow rate of the injected fuel uniform. The second bend 342 has a certain curvature, which can make the injection direction of the fuel ejected from the third fuel pipe 34 better match the air in the third gas pipe 32, enhance the synergy between the two, improve the fuel and air mixing efficiency, make the fuel more evenly dispersed in the air, expand the mixing area, and avoid local over-concentration or over-leanness. At the same time, the curvature design can match the complex air flow field distribution inside the burner, so that the fuel is injected into the area with appropriate flow rate and pressure, reduce flow resistance, and ensure smooth and stable injection. In addition, it helps to form a stable flame, avoid problems such as jitter and flameout, and can adapt to different combustion conditions, such as load changes or changes in fuel type, to ensure that the combustion process is safe, reliable and efficient.

[0151] In one possible embodiment, the openings of all the fourth nozzles 343 are oriented toward a side facing away from the center of the burner.

[0152] In one possible implementation, the openings of all the fourth nozzles 343 are oriented toward one side of the burner center.

[0153] In a possible embodiment, the openings of some of the fourth nozzles 343 face the side away from the center of the burner, and the openings of some of the fourth nozzles 343 face the side of the center of the burner.

[0154] In one possible embodiment, see Figure 17As shown, the swirl burner also includes a third adjustment mechanism 33, which is provided on the second sleeve 31. The third adjustment mechanism 33 is used to drive the second curved pipe 342 to rotate around the axis of its second straight pipe 341 to adjust the injection direction of the fourth nozzle 343.

[0155] In one possible implementation, the third adjustment mechanism 33 includes:

[0156] A second limiting portion is provided on a side of the second sleeve 31 facing the first nozzle 112;

[0157] A second gear ring 332 is provided between the second limiting portion and the second sleeve 31;

[0158] The second gear 333 is sleeved on the second bend pipe 342 of the third fuel pipe 34 and meshes with the second gear ring 332 .

[0159] The third adjustment mechanism 33 has a simple structure, achieving compact space utilization and simple power transmission. When one of the second curved tubes 342 is rotated, it drives the second gear 333 fixed to it, which in turn drives the second ring gear 332, which in turn drives the other second gears 333, thereby causing the other second curved tubes 342 to rotate synchronously, facilitating adjustment of the opening direction of the fourth nozzle 343. Similarly, the provision of the third adjustment mechanism 33 optimizes the mixing of fuel and air and adapts to different fuel characteristics.

[0160] In one possible embodiment, the second limiting portion 331 is provided with a second placement position 3311 for placing the second gear 333. The second limiting portion 331 is a split structure. When a split structure is adopted, the assembly of the third adjustment mechanism 33 and the third fuel pipe 34 can be facilitated. Specifically, the split second limiting portion 331 may include a second limiting first sub-section 3312 and a second limiting second sub-section 3313. The second limiting first sub-section 3312 is provided with a fourth semicircular notch that cooperates with the second gear 333, and the fourth semicircular notch forms the second placement position 3311 of the second gear 333, as well as a fifth semicircular notch that cooperates with the second straight tube 341. The second limiting second sub-section 3313 is provided with a sixth semicircular notch that cooperates with the second straight tube 341. The fifth and sixth semicircular notches are combined to form a second cylindrical through hole 311 that cooperates with the second straight tube 341. The second limiting portion 331 can limit the radial and axial movement of the second gear 333, the second gear ring 332 and the second curved pipe 342 in the second sleeve 31, but does not limit their circumferential rotation, ensuring that when the second gear ring 332 rotates, it can accurately drive the second gear 333 and synchronously drive the second curved pipe 342 to rotate, thereby realizing the angle adjustment of the fourth nozzle 343.

[0161] In one possible embodiment, the burner further includes an air diversion structure 4, which includes a first air guide plate 41 and a second air guide plate 42. The first air guide plate 41 and the second air guide plate 42 are trumpet-shaped. The first air guide plate 41 is provided with a through hole for the first fuel pipe 11 to pass through. The first air guide plate 41 forms a first air flow channel 43 on the side facing the fuel inlet, which is used to distribute air to the first-stage cyclone. The second air guide plate 42 is provided on the side of the first air guide plate 41 facing away from the fuel inlet. The diameter of the second air guide plate 42 is smaller than the diameter of the first air guide plate 41. A second air flow channel 44 is formed between the first air guide plate 41 and the second air guide plate 42, which is used to distribute air to the second-stage cyclone. The second air guide plate 42 forms a third air flow channel 45 on the side facing away from the fuel inlet, which is used to distribute air to the third-stage direct current device.

[0162] Example 2: A swirl burner, whose structure is basically the same as the swirl burner in Example 1, except that it also includes a fuel diversion device 5 to achieve graded distribution of fuel. The fuel diversion device 5 includes a fourth fuel pipe 51, a fuel branch pipe 52, a first circulation pipe 53, and a second circulation pipe 54. There are four fourth fuel pipes 51, which are curved pipes with one end as the fourth fuel inlet and the other end connected to the fuel branch pipe 52. The fuel branch pipe 52 is a straight pipe with a first interface and a second interface at each end, and the pipe diameter is uniform.

[0163] The first circulation tube 53 is annular and has four first side holes on its circumference, which communicate with the first interface of the fuel branch tube 52. A first end hole 531 is provided on the end surface facing the first nozzle 112, the number of which matches that of the second fuel tube 22. A first fuel flow channel is distributed within the first circulation tube 53, connecting the first side holes with the first end hole 531, for transporting fuel to the second fuel tube 22. The second circulation tube 54 is coaxially sleeved on the outside of the first circulation tube 53, and has four second side holes on its circumference, which communicate with the second interface of the fuel branch tube 52. A second end hole 541 is provided on the end surface, the number of which matches that of the third fuel tube 34. A second fuel flow channel is provided within the second circulation tube 54, connecting the second side holes with the second end hole 541, for transporting fuel to the third fuel tube 34.

[0164] The fuel distribution device 5 distributes fuel from a single fuel inlet to the secondary and tertiary combustion units 3 in a preset ratio through the coordinated action of the first and second circulation pipes 53 and 54. After entering the fuel distribution pipe 52 through the fourth fuel pipe 51, the fuel flows through the first and second ports, respectively, into the first and second circulation pipes 54. Then, through the side holes and end holes, it enters the second fuel pipe 22 and the third fuel pipe 34, respectively, achieving staged combustion control. This design optimizes fuel distribution efficiency and ensures that different combustion units are adapted to the different fuel requirements.

[0165] This embodiment also discloses a gas turbine including the aforementioned swirl burner. The exterior of the gas turbine's combustion chamber is composed of a front outer tube 6, a rear outer tube 7, a flame tube 8, and a tail tube 9, forming an annular air flow path. The front end is provided with an end cap. The swirl burner's fuel pipe is fixedly connected to the end cap. Inside the swirl burner, a first air guide plate 41 and a second air guide plate 42 divide the air into three streams. The end cap and the first air guide plate 41 form a primary air flow path, the first and second air guide plates 41 and 42 form a secondary air flow path, and the second air guide plate 42 and the front outer tube 6 form a tertiary air flow path. During operation, air, after being compressed by the compressor, flows through the annular air flow path to the combustion chamber head. Due to the obstruction and diameter of the first and second air guide plates 42, the air is divided into three streams: the first stream flows through the primary swirler via the primary air flow path, the second stream flows through the secondary swirler via the secondary air flow path, and the third stream flows through the tertiary air flow path to the third gas pipe 32. The air at each level is fully mixed with the fuel in the combustion chamber and burns at the burner. The high-temperature gas generated by the combustion flows inside the combustion chamber and is then discharged.

[0166] Specific embodiments are used in the present invention to illustrate the principles and implementation methods of the present invention. The description of the above embodiments is only used to help understand the method of the present invention and its core ideas. At the same time, for those skilled in the art, according to the ideas of the present invention, there may be changes in the specific implementation methods and application scopes. In summary, the contents of this specification should not be understood as limiting the present invention.

Claims

1. A swirl burner, characterized in that: include: a first fuel pipe having a first fuel inlet at one end and a first panel at the other end, a first nozzle being provided on the first panel, and a second nozzle being provided on a side wall of the first fuel pipe; a first gas pipe, sleeved on the outside of the first fuel pipe; a first swirl blade, arranged between the first gas pipe and the first fuel pipe; The first regulating mechanism is arranged in the first fuel pipe and includes a first valve body and a second valve body. The first valve body controls the opening and closing of the first nozzle, and the second valve body controls the opening and closing of the second nozzle.

2. The swirl burner according to claim 1, characterized in that: The first valve body includes: a second panel, attached to the inner side of the first panel, and having a first through hole corresponding to the first nozzle; The first control rod is vertically connected to the second panel. The first control rod can drive the second panel to rotate around the axis so that the first through hole and the first nozzle are arranged opposite to each other or staggered.

3. The swirl burner according to claim 1, characterized in that The second valve body includes: a collar, nested in the first fuel pipe, the collar being provided with a second through hole corresponding to the second nozzle; A second control rod, one end of which is connected to the collar and the other end of which is provided with a limit block; The end of the first fuel pipe away from the first panel is provided with a limiting groove matched with the limiting block, and the limiting block can slide along the limiting groove to drive the collar to rotate, so that the second through hole and the second nozzle are arranged oppositely or staggered.

4. The swirl burner according to claim 1, characterized in that Also includes: a first sleeve, sleeved on the outside of the first gas pipe; a second fuel pipe, disposed in the first sleeve, with one end on the same side as the first nozzle forming a third nozzle; The secondary cyclone is sleeved on the outer side of the first sleeve.

5. The swirl burner according to claim 4, characterized in that: The invention also includes a second adjustment mechanism, which is provided on the first sleeve and includes: a first limiting portion, provided on a side of the first sleeve facing the first nozzle; a first ring gear, disposed between the first limiting portion and the first sleeve; The first gear is sleeved on the first bend of the second fuel pipe and meshes with the first gear ring.

6. The swirl burner according to claim 1, characterized in that Also includes: a second sleeve, sleeved on the outside of the secondary cyclone; a third fuel pipe, disposed in the second sleeve, with one end on the same side as the first nozzle forming a fourth nozzle; The third gas pipe is sleeved on the outside of the second sleeve.

7. The swirl burner according to claim 6, characterized in that The device further includes a third adjustment mechanism, which is provided on the second sleeve and includes: a second limiting portion, provided on a side of the second sleeve facing the first nozzle; a second ring gear, disposed between the second limiting portion and the second sleeve; The second gear is sleeved on the second bend of the third fuel pipe and meshes with the second gear ring.

8. The swirl burner according to claim 4 or 6, characterized in that: Also included is a fuel diversion device, the fuel diversion device comprising: a fourth fuel pipe, one end of which is a fourth fuel inlet and the other end of which is connected to a fuel branch pipe; a first circulating pipe having a first side hole formed on its circumference and a first end hole formed on its end face, the first side hole being connected to one end of the fuel branch pipe, and the first end hole being connected to the second fuel inlet; The second circulation pipe has a second side hole on its circumference and a second end hole on its end face. The second side hole is communicated with the other end of the fuel branch pipe, and the second end hole is communicated with the third fuel inlet.

9. The swirl burner according to claim 6, characterized in that It also includes an air diversion structure, the air diversion structure including: A first air guide plate is provided with a through hole for the first fuel pipe to pass through, and the first air guide plate forms a first air flow channel on the side facing the fuel inlet for distributing air to the primary cyclone; The second air guide plate is arranged on the side of the first air guide plate facing away from the fuel inlet. The diameter of the second air guide plate is smaller than the diameter of the first air guide plate. A second air flow channel is formed between the first air guide plate and the second air guide plate, which is used to distribute air to the secondary cyclone. The third air flow channel is formed on the side of the second air guide plate facing away from the fuel inlet, which is used to distribute air to the third gas pipe.

10. A gas turbine, characterized in that: The invention comprises the swirl burner according to any one of claims 1 to 9.

Images