Combustion device

Abstract

To prevent back fire more reliably over a longer period of time.SOLUTION: A combustion device 1 comprises a combustion chamber 10 that combusts mixed gas 73 obtained by mixing air 71 and fuel 72, and a fuel nozzle 20 that forms a flow path for supplying the mixed gas 73 to the combustion chamber 10. The fuel nozzle 20 comprises a swirl blade 30 provided in the flow path. The swirler 30 has a first shape in the flow path at a first temperature, and at a second temperature higher than the first temperature, based on the principle of thermal expansion, forms a second shape in the flow path through which the mixed gas flows more easily than in the first shape.SELECTED DRAWING: Figure 2

Description

[Technical field]

[0001] The present disclosure relates to combustion devices. [Background technology]

[0002] A detection device is known for detecting flashbacks that occur in gas turbines equipped with combustion devices that use a lean premixed combustion method. Flashbacks are a phenomenon in which a flame advances faster than the speed of fluids such as fuel and air, and the flame advances upstream through the fluid. In principle, flashbacks can occur in gas turbines that use natural gas as fuel, but it is easy to suppress flashbacks by restricting the operating conditions.

[0003] In recent years, there has been an increasing demand for hydrogen-fired gas turbines that use a mixture of natural gas and hydrogen gas, or hydrogen gas alone, as fuel, in order to realize a hydrogen society. Hydrogen gas has a faster burning speed than natural gas. Therefore, in hydrogen-fired gas turbines, flashbacks are more likely to occur than in gas turbines that consume natural gas as fuel gas. Increasing the concentration of hydrogen gas in the fuel gas narrows the conditions under which flashbacks do not occur, making it difficult to completely suppress flashbacks in practical operation.

[0004] Patent document 1 describes a combustion control device that is used in a combustion system and stops the fuel supply to a staging block including a main fuel nozzle in which a flashback has occurred based on a detection signal from a flashback detection unit that detects the flashback.

[0005] Non-Patent Document 1 describes a combustor equipped with a fuel nozzle having swirlers whose swirler angle can be changed by a stepping motor. When flashback occurs in the combustor of Non-Patent Document 1, the angle of the swirlers relative to the axial direction of the fuel nozzle is reduced to push back the flame and suppress the flashback. [Prior art documents] [Patent documents]

[0006] [Patent Document 1] International Publication No. 2015 / 097861 [Non-patent literature]

[0007] [Non-Patent Document 1] Komiyama, Kumazaki and Nishida, Journal of Thermal Science and Technology, Vol.16, No.2 (2021) Summary of the Invention [Problem to be solved by the invention]

[0008] However, the conventional configuration has room for improvement in terms of preventing flashback with higher reliability over the long term.

[0009] Therefore, an object of the present disclosure is to make it possible to prevent flashback with higher reliability over the longer term. [Means for solving the problem]

[0010] In some embodiments, a combustion device includes: (1) a combustion chamber for burning a mixed gas obtained by mixing air and fuel; a fuel nozzle forming a flow passage for supplying the mixed gas to the combustion chamber; Equipped with the fuel nozzle includes a swirler disposed in the flow passage; The swirler comprises: having a first shape in the flow channel at a first temperature; At a second temperature higher than the first temperature, a second shape is formed in the flow passage, based on the principle of thermal expansion, through which the mixed gas flows more easily than in the first shape.

[0011] In this way, the swirler provided in the combustion device forms a second shape in the flow passage that allows the mixed gas to flow more easily than the first shape at the second temperature based on the principle of thermal expansion, so that the mixed gas is supplied to the combustion chamber more vigorously at the high second temperature where flashback may occur. Therefore, even if flashback occurs, the mixed gas is supplied to the combustion chamber with force, and the flame can be pushed back into the combustion chamber, making it possible to suppress flashback. In addition, the swirler autonomously changes the ease of flow of the mixed gas based on the simple principle of thermal expansion, rather than on precise control by complex machines and electronic components, so flashback can be prevented with long-term reliability.

[0012] In one embodiment, (2) In the combustion device of (1), The swirler comprises a wing portion and a housing, The wing portion may have a fixed end fixed to the housing and a free end spaced apart from the housing.

[0013] In this way, the blade portion can change its angle with respect to the axial direction of the fuel nozzle by displacing the free end relative to the fixed end in response to changes in temperature, thereby adjusting the ease of flow of the mixed gas and preventing flashback.

[0014] In one embodiment, (3) In the combustion device of (2), The wing portion is A plate-shaped first layer, A plate-shaped second layer having a thermal expansion coefficient larger than that of the first layer; may be formed by joining the above.

[0015] In this way, the blade is made by joining the first and second plate-like layers with different thermal expansion coefficients, so it can warp in response to an increase in temperature and change its angle with respect to the axial direction of the fuel nozzle. This makes it possible to adjust the ease of flow of the mixed gas without relying on precise control using complex machines and electronic components, making it possible to prevent flashback with long-term reliability.

[0016] In one embodiment, (4) In the combustion device of (3), The blade may be disposed within the fuel nozzle at an angle such that the mixed gas supplied from the upstream of the flow passage comes into contact with the second layer.

[0017] In this way, the blades are set in the fuel nozzle at an angle such that the mixed gas supplied from the upstream of the flow path comes into contact with the second layer, which has a larger thermal expansion coefficient, so that when the temperature rises, the blades warp and the mixed gas is supplied into the combustion chamber with greater force. Therefore, even if flashback occurs, the flame can be pushed back into the combustion chamber and suppressed.

[0018] In one embodiment, (5) In the combustion device of (1), The swirler comprises: A wing portion that can freely rotate around a rotation axis; an adjustment unit that adjusts an angle of the blade portion with respect to an axial direction of the fuel nozzle by restricting a rotation of the blade portion while the mixed gas is flowing through the fuel nozzle; Equipped with The adjustment portion may change a position at which rotation of the blade portion is restricted by thermal expansion in response to a temperature rise, thereby changing an angle of the blade portion with respect to an axial direction of the fuel nozzle.

[0019] In this way, the adjustment unit, which can change the regulating position of the rotation of the blade portion due to thermal expansion, changes the angle of the blade portion relative to the axial direction of the fuel nozzle in response to the temperature rise from the first temperature to the second temperature, so that the ease of flow of the mixed gas can be adjusted with a simple configuration, and flashback can be prevented with long-term reliability.

[0020] In one embodiment, (6) In the combustion device of (5), The swirler further comprises a housing; The adjustment unit is A fixed end fixed to the housing; a free end spaced from the housing; an engagement portion that mechanically engages with the vane portion in a state in which the mixed gas flows through the fuel nozzle; The present invention may also include:

[0021] In this way, in response to a rise in temperature from the first temperature to the second temperature, the adjustment portion expands toward the free end while the fixed end remains fixed to the housing, thereby displacing the engagement portion that mechanically engages with the vane portion, thereby changing the angle of the vane portion relative to the axial direction of the fuel nozzle. Therefore, the ease of flow of the mixed gas can be adjusted with a simple configuration, and flashback can be prevented with long-term reliability.

[0022] In one embodiment, (7) In the combustion device of (6), The swirler further comprises a positioning portion mechanically coupled to the wing portion, The engagement portion of the adjustment portion may be mechanically engaged with the positioning portion in a state in which the mixed gas flows through the fuel nozzle.

[0023] In this way, when the mixed gas is flowing through the fuel nozzle, the engagement portion of the adjustment portion engages with the positioning portion mechanically connected to the wing portion, rather than with the wing portion itself, so that the adjustment portion can be located at any position that does not interfere with the flow of the mixed gas.

[0024] In one embodiment, (8) In the combustion equipment of (6) or (7), The engagement portion may be a notch in the adjustment portion.

[0025] In this way, since the engagement portion is provided as a notch in the adjustment portion, the swirler can be configured with a simple structure.

[0026] In one embodiment, (9) In any of the combustion devices described in (2) to (8), The fuel nozzle may include a plurality of the vanes.

[0027] In this way, by providing the fuel nozzle with a plurality of blade portions, the ease of flow of the mixed gas can be changed more significantly in response to an increase in temperature, and flashback can be prevented more effectively.

[0028] In one embodiment, (10) In any of the combustion devices according to (1) to (9), A plurality of said fuel nozzles may be provided.

[0029] In this way, by providing multiple fuel nozzles, each equipped with swirler vanes that can adjust the ease of flow of the mixed gas, the ease of flow of the mixed gas can be changed more significantly in response to an increase in temperature, making it possible to more effectively prevent flashback. Effect of the Invention

[0030] According to an embodiment of the present disclosure, flashback can be prevented more reliably over a longer period of time. [Brief description of the drawings]

[0031] [Figure 1] 1 is a diagram showing an example of the configuration of a combustion device according to an embodiment; [Diagram 2] FIG. 2 is a diagram illustrating an example of the configuration of the fuel nozzle in FIG. [Diagram 3] FIG. 3 is a diagram showing a configuration example of the swirler in FIG. 2. [Figure 4] 4 is a diagram showing an example of the operation of the swirler in FIG. 3. [Diagram 5] 3A to 3C are diagrams illustrating an example of the configuration and operation of the swirler of FIG. 2. [Figure 6] FIG. 3 is a diagram showing a configuration example of the swirler in FIG. 2. DETAILED DESCRIPTION OF THE PREFERRED EMBODIMENTS

[0032] <Comparative Example> In a combustion device according to a comparative example, such as that disclosed in Patent Document 1, in which fuel supply is stopped in response to detection of flashback in a staging block, the load must be reduced to a level at which fuel supply to the staging block is stopped in order to suppress flashback. Therefore, in such a comparative example, the operating efficiency of the gas turbine is significantly reduced in order to suppress flashback.

[0033] As another combustion device according to a comparative example, as described in Non-Patent Document 1, when flashback occurs in a combustor, a stepping motor is controlled to reduce the angle of the swirler with respect to the axial direction of the fuel nozzle, thereby pushing back the flame and suppressing the flashback. However, the inside of the combustion device is a harsh environment for the stepping motor, since it is high temperature and high pressure and generates combustion vibrations. In order to correct the angle of the swirler by the stepping motor in response to the occurrence of flashback, the stepping motor needs to be installed in an area close to the flame where the flashback has occurred, and therefore the stepping motor needs to be installed in a particularly harsh environment. Therefore, in the configuration according to such a comparative example, the stepping motor is considered to be prone to failure, which may be problematic in terms of long-term stable operation.

[0034] Thus, the configuration according to the comparative example has room for improvement in terms of preventing flashback with higher reliability over a longer period of time.

[0035] An object of the present disclosure is to provide a combustion device that can suppress flashback without significantly reducing operating efficiency even if flashback occurs, and that has high long-term reliability.

[0036] <Embodiment> Hereinafter, an embodiment of the present disclosure will be described with reference to the drawings. In each drawing, parts having the same configuration or function are denoted by the same reference numerals. In the description of this embodiment, duplicated descriptions of the same parts may be omitted or simplified as appropriate.

[0037] (First embodiment) FIG. 1 is a diagram showing an example of the configuration of a combustion device 1 according to an embodiment. FIG. 1 shows a schematic diagram of the combustion device 1 seen from a horizontal direction. The combustion device 1 burns a mixed gas obtained by mixing air and fuel gas. The combustion device 1 includes a combustion chamber 10 and a fuel nozzle 20. The fuel nozzle 20 includes a fuel supply port and supplies a mixed gas of air and fuel gas to the combustion chamber 10. The combustion chamber 10 has a space for burning the mixed gas supplied from the fuel nozzle 20. In this embodiment, the fuel is hydrogen gas, but is not limited thereto. For example, the fuel may be a mixed gas of hydrogen gas and natural gas, natural gas, or any fluid usable as a fuel. In this embodiment, the combustion device 1 includes a plurality of fuel nozzles 20, but the number of fuel nozzles 20 may be one.

[0038] FIG. 2 is a diagram showing an example of the configuration of the fuel nozzle 20 in FIG. 1. FIG. 2 shows a schematic diagram of the fuel nozzle 20 viewed from a horizontal direction. As shown in FIG. 2, the fuel nozzle 20 includes a swirler 30 and a duct 40. The duct 40 takes in air 71 and fuel gas 72 and supplies them to the combustion chamber 10 as mixed gas 73. The swirler 30 is provided in the flow path of the mixed gas 73. The swirler 30 includes a blade portion 33 and a housing 35. The swirler 30 includes a thermally expandable member, and when the temperature reaches a level at which flashback is suspected, the swirler 30 deforms into a shape that allows the mixed gas 73 to flow vigorously into the combustion chamber 10, thereby suppressing flashback. Flashback is when a flame in the combustion chamber 10 advances through the fuel nozzle 20 from the end of the fuel nozzle 20 facing the combustion chamber 10 toward the swirler 30 in the fuel nozzle 20. The swirler 30 autonomously changes the flowability of the mixed gas 73 based on the simple principle of thermal expansion, rather than on precise control using complex mechanical and electronic components, making it possible to prevent flashback with long-term reliability.

[0039] In the example of FIG. 2, the fuel nozzle 20 includes a plurality of blade portions 33. Therefore, the combustion device 1 can change the ease of flow of the mixed gas 73 more significantly in response to an increase in temperature, and can effectively prevent flashback. The number of blade portions 33 included in the fuel nozzle 20 may be one. Furthermore, the combustion device 1 includes a plurality of fuel nozzles 20, each of which includes a blade portion 33. By including a plurality of fuel nozzles 20, each of which includes a swirler vane 30 that can adjust the ease of flow of the mixed gas 73, the combustion device 1 can change the ease of flow of the mixed gas 73 more significantly in response to an increase in temperature, and can effectively prevent flashback.

[0040] Fig. 3 is a diagram showing a configuration example of the blade portion 33 of the swirler 30a of Fig. 2. In the example of Fig. 3, the blade portion 33 is formed by joining a plate-shaped first layer 31 and a plate-shaped second layer 32 having a larger thermal expansion coefficient than the first layer 31. The blade portion 33 of the swirler 30a has a fixed end 34 fixed to a housing 35 and a free end spaced apart from the housing 35. The blade portion 33 displaces the free end with respect to the fixed end 34 in response to a change in temperature, thereby changing the angle with respect to the axial direction 80 of the fuel nozzle 20 (see Fig. 4) and adjusting the ease of flow of the mixed gas 73, thereby making it possible to prevent flashback.

[0041] FIG. 4 is a diagram showing an example of the operation of the swirler 30a in FIG. 3. FIG. 4 shows a schematic diagram of the swirler 30a viewed from the horizontal direction. As shown in FIG. 4, the wing portion 33 is provided in the fuel nozzle 20 at an angle such that the mixed gas 73 supplied from the upstream of the flow path comes into contact with the second layer 32. In other words, the upstream edge of the wing portion 33 is a fixed end 34 fixed to the housing 35 of the swirler 30. The downstream edge of the wing portion 33 is a free end spaced apart from the housing 35. The wing portion 33 is attached to the housing 35 in a state inclined with respect to the axial direction 80 of the fuel nozzle 20.

[0042] In such a configuration, the operation of the combustion device 1 to autonomously suppress flashback will be described. A mixed gas 73 of air 71 and fuel gas 72 is guided by the swirler 30 along the axial direction 80 of the fuel nozzle 20, forming a swirling flow that depends on the inclination angle of the blade 33a. At a first temperature at which flashback does not occur, the swirler 30a has a shape that is not warped, like the blade 33a. When flashback occurs, the temperature of the swirler 30 rises as the flame advances. When the temperature of the swirler 30 rises, stress is generated in the blade 33 due to the difference in elongation due to thermal expansion between the first layer 31, which has a small thermal expansion coefficient, and the second layer 32, which has a large thermal expansion coefficient. As a result, at a second temperature at which flashback may occur, the blade 33b warps in the direction of the surface where the first layer 31, which has a small thermal expansion coefficient, is located. This warping reduces the angle of the blade 33b with respect to the axial direction 80 of the fuel nozzle 20, pushing back the flame and suppressing flashback.

[0043] In other words, at the first temperature, the mixed gas 73 is guided by the wing portion 33a and flows through the flow passage 75a that is inclined with respect to the axial direction 80. At a second temperature higher than the first temperature, the wing portion 33 has a warp (wing portion 33b). The mixed gas 73 is guided by the wing portion 33b and flows through the flow passage 75b that is inclined less with respect to the axial direction 80. That is, the swirler 30 has a first shape in the flow passage of the mixed gas 73 at the first temperature, and at a second temperature higher than the first temperature, the swirler 30 forms a second shape in the flow passage through which the mixed gas 73 flows more easily than the first shape based on the principle of thermal expansion. Therefore, at the second temperature, the mixed gas 73 flows more vigorously toward the combustion chamber 10, and the flame can be pushed back to suppress flashback.

[0044] In this way, the combustion device 1 according to this embodiment changes the inclination angle of the blade portion 33 with respect to the axial direction 80 of the fuel nozzle 20 by utilizing the temperature rise of the swirler 30 accompanying the progress of the flame when a flashback occurs, and autonomously suppresses flashback. Since the combustion device 1 can suppress flashback without changing the amount of fuel supplied, it is possible to prevent a significant decrease in operating efficiency. In addition, since the inclination angle of the blade portion 33 with respect to the axial direction 80 of the fuel nozzle 20 can be autonomously controlled without using mechanical moving parts and electronic components that control the same, it is possible to prevent flashback with higher reliability over a longer period of time.

[0045] In the example of FIG. 3, the first layer 31 and the second layer 32 are the same in size, but the first layer 31 and the second layer 32 may be different in size. When the first layer 31 and the second layer 32 are different in size, the wing portion 33 will warp at the joint surface of the first layer 31 and the second layer 32 in response to a change in temperature. In the example of FIG. 3, the number of the first layer 31 and the second layer 32 bonded to each other is the same, but the number of the first layer 31 and the second layer 32 may be different. For example, a plurality of small second layers 32 may be bonded to one first layer 31, or a plurality of small first layers 31 may be bonded to one second layer 32. Even in such a configuration, the wing portion 33 will warp at the joint surface of the first layer 31 and the second layer 32 in response to a change in temperature. In this way, at least one of the size, number, and shape of the first layer 31 and the second layer 32 bonded to each other may be different. Flashback can be effectively prevented by appropriately selecting the size, number, shape, etc. of the first layer 31 and the second layer 32 depending on the thermal expansion coefficients of the first layer 31 and the second layer 32, the shape of the fuel nozzle 20, and the flow rate of the mixed gas 73, etc.

[0046] Second embodiment The combustion device 1 according to the first embodiment includes a blade portion 33 formed by joining two members having different thermal expansion coefficients. The blade portion 33 warps at a second temperature higher than the first temperature, making the mixed gas 73 easier to flow and suppressing flashback. In contrast, the combustion device 1 according to the present embodiment includes an adjustment portion 37 that regulates the rotation of the blade portion 36 and adjusts the angle of the blade portion 36 relative to the axial direction 80 of the fuel nozzle 20, and is made of a thermally expandable member. When the temperature rises, the adjustment portion 37 changes the angle of the blade portion 36 relative to the axial direction 80 without changing the shape of the blade portion 36. Therefore, according to the configuration of the present embodiment, the ease of flow of the mixed gas 73 can be adjusted in response to the rise in temperature, and flashback can be suppressed. The configurations of the combustion device 1 and the fuel nozzle 20 are shown in FIG. 1 and FIG. 2 as in the first embodiment, and therefore detailed description will be omitted.

[0047] FIG. 5 is a diagram showing a configuration example and an operation example of the swirler 30b in FIG. 2. FIG. 6 is a diagram showing a configuration example of the swirler 30b in FIG. 2. FIG. 5 shows a schematic diagram of the swirler 30b seen from a horizontal direction. FIG. 6 shows a schematic diagram of the swirler 30b seen from vertically above. In the combustion device 1 according to this embodiment, as shown in FIG. 5, the wing portion 36 includes a positioning portion 38 and a rotating shaft 39. The rotating shaft 39 and the wing portion 36, and the rotating shaft 39 and the positioning portion 38 are fixed to each other. In other words, the swirler 30 includes a positioning portion 38 that is mechanically coupled to the wing portion 36. Therefore, as shown in FIG. 5, when viewed from the direction in which the rotating shaft 39 extends, the wing portion 36 and the positioning portion 38 may have a positional relationship that forms an L shape. The rotating shaft 39 is borne by the housing 35 of the swirler 30. As shown in FIG. 5, the positioning portion 38 can move within the range of a notch 373 provided on the side surface of the adjustment portion 37.

[0048] In this configuration, the blade portion 36 is freely rotatable about the rotation axis 39 relative to the housing 35 of the swirl vane 30 while maintaining a fixed positional relationship with the positioning portion 38. The rotation angle of the blade portion 36 is limited by the notch 373 of the adjustment portion 37 and the positioning portion 38, and the rotation angle is determined in combination with the force of the mixed gas 73 of air 71 and fuel gas 72 pressing against the blade portion 36. The adjustment portion 37 has a fixed end 371, which is one end of the adjustment portion 37, and a free end 372. The fixed end 371 is fixed to the housing 35 of the swirl vane 30. In this embodiment, the adjustment portion 37 is made of a material having a relatively high thermal expansion coefficient.

[0049] The operation of the combustion device 1 according to the present embodiment to autonomously suppress flashback will be described. A mixed gas 73 of air 71 and fuel gas 72 passes through the swirling vane 30 along the axial direction 80 of the fuel nozzle 20. As a result, the mixed gas 73 forms a swirling flow that depends on the inclination angle of the wing portion 36. Since the mixed gas 73 is ejected from the pipe 40 with sufficient momentum, the wing portion 36 is lifted by the flow of the mixed gas 73 while the mixed gas 73 is flowing. In response to this, the positioning portion 38 moves until it comes into contact with the side surface 374 of the notch 373 of the adjustment portion 37. In this way, the notch 373 acts as an engagement portion that mechanically engages with the wing portion 36 when the mixed gas 73 is flowing inside the fuel nozzle 20. Therefore, while the mixed gas 73 is flowing, the wing portion 36 forms an angle with the axial direction 80 of the fuel nozzle 20 that corresponds to the position where the positioning portion 38 comes into contact with the side surface 374 of the notch 373.

[0050] In FIG. 5, while the mixed gas 73 flows at the first temperature, the wing 36a moves until the positioning portion 38a comes into contact with the side surface 374a of the notch 373. When a flashback occurs, the temperature of the swirler 30b and the surrounding components including the adjustment portion 37 increases as the flame advances. When the temperature of the adjustment portion 37 increases, the end of the adjustment portion 37 opposite to the fixed end 371 moves toward the free end 372 of the adjustment portion 37 due to thermal expansion. As a result, the side surface 374 of the notch 373 also moves toward the free end 372 of the adjustment portion 37. As described above, since the wing 36 is lifted by the flow of the mixed gas 73, when the side surface 374 of the notch 373 moves toward the free end 372, the contact point between the positioning portion 38 and the side surface 374 also moves toward the free end 372. Therefore, there is room for the wing 36 to rotate in a direction in which the angle of the wing 36 with respect to the axial direction 80 of the fuel nozzle 20 becomes smaller. As a result, the force of the mixed gas 73 of air 71 and fuel gas 72 pushing the vane 36 causes the vane 36 to rotate in a direction that reduces the angle with respect to the axial direction 80 of the fuel nozzle 20. In this way, the adjustment portion 37 changes the position at which the rotation of the vane 36 is restricted by thermal expansion in response to an increase in temperature, thereby changing the angle of the vane 36 with respect to the axial direction 80 of the fuel nozzle 20. As a result, the mixed gas 73 can move more vigorously toward the combustion chamber 10, the flame is pushed back, and flashback is suppressed.

[0051] In other words, at the second temperature at which flashback may occur, the adjustment portion 37 expands, and the free end 372 moves from the free end 372a to the free end 372b. In response to this, the side surface 374 of the notch 373 also moves from the side surface 374a to the side surface 374b. As a result, the positioning portion 38 can move from the positioning portion 38a to the position of the positioning portion 38b, and the wing portion 36 can move from the wing portion 36a to the position of the wing portion 36b where the flow of the mixed gas 73 is not hindered. At the first temperature, the mixed gas 73 is guided by the wing portion 36a and flows through the flow passage 76a that is inclined with respect to the axial direction 80. At the second temperature that is higher than the first temperature, the wing portion 36 is lifted to the position of the wing portion 36b by the flow of the mixed gas 73. The mixed gas 73 is guided by the wing portion 36b and flows through the flow passage 76b that is inclined with respect to the axial direction 80. That is, the swirler 30 has a first shape in the flow path of the mixed gas 73 at a first temperature, and forms a second shape in which the mixed gas 73 flows more easily in the flow path than in the first shape based on the principle of thermal expansion at a second temperature higher than the first temperature. Therefore, at the second temperature, the mixed gas 73 flows more vigorously toward the combustion chamber 10, pushing back the flame and suppressing flashback.

[0052] The combustion device 1 according to this embodiment, like the combustion device 1 according to the first embodiment, utilizes the temperature rise accompanying the progression of the flame during flashback to change the angle of the blade portion 36 of the swirler 30b with respect to the axial direction 80 of the fuel nozzle 20 to autonomously suppress flashback. The combustion device 1 according to this embodiment can suppress flashback without changing the amount of fuel supplied, so it is possible to prevent a significant decrease in operating efficiency. In addition, the combustion device 1 according to this embodiment can be autonomously controlled without electronic components that control the swirler 30, so it is possible to significantly improve long-term reliability.

[0053] The present disclosure is not limited to the above-described embodiments. For example, multiple blocks shown in the block diagram may be integrated, or one block may be divided. Multiple steps shown in the flowchart may be executed in parallel or in a different order depending on the processing capacity of the device executing each step, or as necessary, instead of being executed in chronological order as described. Other modifications are possible without departing from the spirit of the present disclosure. [Explanation of symbols]

[0054] 1 Combustion equipment 10 Combustion chamber 20 Fuel Nozzle 30 Swivel Wing 31 1st layer 32 2nd layer 33 Wings 34 Fixed end 35 Case 36 Wings 37 Adjustment section 371 Fixed end 372 Free end 373 Engagement part (notch) 374 Side 38 Positioning part 39 Rotational Axis 40 conduit 71 Air 72 Fuel Gas 73 Mixed Gases 75,76 Flow path 80 Axial

Claims

1. a combustion chamber for burning a mixed gas obtained by mixing air and fuel; a fuel nozzle forming a flow passage for supplying the mixed gas to the combustion chamber; Equipped with the fuel nozzle includes a swirler disposed in the flow passage; The swirler comprises: having a first shape in the flow channel at a first temperature; forming a second shape in which the mixed gas flows more easily in the flow passage than in the first shape based on a principle of thermal expansion at a second temperature higher than the first temperature; Combustion device.

2. The swirler comprises a wing portion and a housing, The combustion device of claim 1 , wherein the wing portion comprises a fixed end fixed to the housing and a free end spaced from the housing.

3. The wing portion is A plate-shaped first layer; A plate-shaped second layer having a thermal expansion coefficient larger than that of the first layer; The above are joined together to form a The combustion device according to claim 2.

4. The combustion device according to claim 3 , wherein the vane portion is provided in the fuel nozzle at an angle such that the mixed gas supplied from the upstream of the flow passage comes into contact with the second layer.

5. The swirler comprises: A wing portion that can freely rotate around a rotation axis; an adjustment unit that adjusts an angle of the blade portion with respect to an axial direction of the fuel nozzle by restricting a rotation of the blade portion while the mixed gas is flowing through the fuel nozzle; Equipped with the adjustment portion changes a position at which the rotation of the blade portion is restricted by thermal expansion in response to a temperature rise, thereby changing an angle of the blade portion with respect to an axial direction of the fuel nozzle. The combustion device of claim 1 .

6. The swirler further comprises a housing; The adjustment unit is A fixed end fixed to the housing; a free end spaced from the housing; an engagement portion that mechanically engages with the vane portion in a state in which the mixed gas flows through the fuel nozzle; The combustion device of claim 5 , comprising:

7. The swirler further comprises a positioning portion mechanically coupled to the wing portion, the engagement portion of the adjustment portion is mechanically engaged with the positioning portion in a state in which the mixed gas flows through the fuel nozzle.

7. The combustion device according to claim 6.

8. The combustion device according to claim 6 , wherein the engagement portion is a notch in the adjustment portion.

9. The combustion apparatus of claim 2 , wherein the fuel nozzle comprises a plurality of the vanes.

10. A combustion device according to claim 1 , comprising a plurality of said fuel nozzles.

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