A gas turbine combustor structure with circumferentially dispersed main combustion nozzles

Abstract

The present invention discloses a gas turbine combustor structure with circumferentially dispersed main combustion nozzles. By setting the fuel injection part at the head of the flame tube as a pilot nozzle and a main combustion nozzle ring successively arranged around the pilot nozzle from inside to outside, each main combustion nozzle ring includes a plurality of main combustion nozzles arranged circumferentially and at intervals. At least one main combustion nozzle fuel injection hole corresponding in the circumferential direction is arranged on the opposite surfaces of adjacent main combustion nozzles, and a main combustion nozzle air hole corresponding and of the same size is arranged at each main combustion nozzle fuel injection hole. By setting a plurality of main combustion nozzle fuel injection holes and main combustion nozzle air holes to form separated small flames in a micro-premixed manner, the residence time of high-temperature flames is reduced, thereby achieving low NOx emissions of hydrogen; moreover, all the main combustion nozzle air holes are of the same size and are opposite to each other in pairs, ensuring that the air jets form an inner vortex and an outer vortex, and the sizes are symmetrical and the shapes are stable, which is beneficial to the anchoring of the flame and realizes stable combustion.

Description

Technical Field

[0001] The present invention belongs to the technical field of gas turbine combustors, and particularly relates to a gas turbine combustor structure with circumferentially dispersed main combustion nozzles. Background Art

[0002] To meet the increasingly stringent environmental protection regulations and the demand for reducing carbon emissions, the technological development of gas turbines shows a trend of low emissions, high parameters, multi-fuel, and flexible operation over a wide range of operating conditions. Among them, in order to cope with the changes in the energy structure system and the future energy layout, it is necessary to gradually increase the hydrogen content in the gas turbine fuel until pure hydrogen combustion is achieved. Hydrogen has extremely active chemical properties, with a relatively high adiabatic flame temperature, laminar flame speed, and thermal diffusion coefficient, a relatively low minimum ignition energy, and ignition delay time. These physical properties determine that the combustion of hydrogen has technical difficulties such as flashback, spontaneous ignition, high emissions, and thermoacoustic oscillations. To solve these difficulties, in terms of combustion organization methods, mostly new combustion methods such as micro-premixed combustion, staged combustion, arrayed vortex, low-swirl burners, and diffusion dilution combustion are adopted.

[0003] Patent CN106461211A discloses a combustion device for a gas turbine engine, including a nozzle and a burner based on the MMX (Micro-Mix) micro-mixing combustion principle, as shown in Figure 13 . It relies on the (Jet-In-Crossflow, JICF) non-premixed cross jet to achieve mixing and has inherent safety against flashback. Multiple independent small flame structures are formed downstream, which can reduce the residence time of the flame and theoretically greatly reduce NOx emissions. Specifically, in JICF, the fuel flow is injected perpendicular to the air flow to form a counter-rotating vortex pair (CRVP), which is crucial for the mixing of fuel and oxidizer. And since there is no additional barrier, aerodynamic losses can be reduced. The geometry of the air guiding panels (AGP) and the fuel section, as bluff bodies, causes the formation of the vortex pair. The larger fan-shaped vortex conveys the hot combustion gas to the starting point of the reaction zone, and the flame is stabilized between these two vortices. The stable formation of the vortex pair depends on the guarantee of the portal flow velocity and the nozzle arrangement method in pairs.

[0004] To exert the highest energy density, the nozzle of Patent CN106461211A adopts a circumferential arrangement of several layers in a ring shape, as shown in Figures 14 - 15 . However, as the radius decreases from the periphery to the center, the circumference available for arranging the portals in each layer of this method will gradually decrease, and a trade-off must be made between the unified portal size and the portal arrangement method in pairs, which will inevitably go against the original intention of the low-nitrogen combustion and flame stabilization mechanism of the micro-premixed technology. Summary of the Invention

[0005] To solve the above problems, the present invention provides a gas turbine combustion chamber structure with circumferentially dispersed main combustion nozzles, and the technical solution is as follows:

[0006] A gas turbine combustion chamber structure with circumferentially dispersed main combustion nozzles of the present invention includes:

[0007] A flame tube, the inner side of which forms a combustion chamber, and the axis of the flame tube is set as the first axis;

[0008] A fuel injection part, including a pilot nozzle and at least one main combustion nozzle ring; the pilot nozzle is arranged at the head of the flame tube and along the first axis; the main combustion nozzle ring surrounds the pilot nozzle and is arranged in sequence from inside to outside; wherein, the main combustion nozzle ring includes a plurality of main combustion nozzles circumferentially and spaced apart with the first axis as the center of the circle, at least one corresponding main combustion nozzle fuel injection port is arranged on the opposite surfaces of adjacent main combustion nozzles, and a main combustion nozzle air flow channel is formed between adjacent main combustion nozzles; a main combustion nozzle air hole corresponding to each main combustion nozzle fuel injection port is arranged in the main combustion nozzle air flow channel, and the sizes and shapes of the main combustion nozzle air holes are the same;

[0009] An air supply part, the output end of the air supply part is communicated with each main combustion nozzle air flow channel and the pilot nozzle.

[0010] In the gas turbine combustion chamber structure with circumferentially dispersed main combustion nozzles of the present invention, the number of the main combustion nozzle rings is two or more. Between two adjacent main combustion nozzle rings, the number of the main combustion nozzles of the inner main combustion nozzle ring is n, and the number of the main combustion nozzles of the outer main combustion nozzle ring is 2n, and n≥6;

[0011] Between two adjacent main combustion nozzle rings, the main combustion nozzles of the inner main combustion nozzle ring and the main combustion nozzles of the outer main combustion nozzle ring are staggered with each other.

[0012] In the gas turbine combustion chamber structure with circumferentially dispersed main combustion nozzles of the present invention, the main combustion nozzle includes a main combustion nozzle fuel channel, a main combustion nozzle fuel box, a main combustion nozzle air baffle, a main combustion nozzle outer deflector, and a main combustion nozzle inner deflector;

[0013] Each of the main burner fuel boxes is connected to a main burner fuel channel for connecting to an external fuel supply end; a plurality of the main burner fuel boxes are arranged at intervals along the circumferential direction to form an annular structure, and at least one main burner fuel nozzle is radially arranged on both sides of the main burner fuel box; the main burner outer guide plate is connected to the outer sides of two adjacent main burner fuel boxes in the radial direction, and the main burner inner guide plate is connected to the inner sides of two adjacent main burner fuel boxes in the radial direction;

[0014] The main burner nozzle air flow channel is located between the adjacent main burner nozzle fuel boxes, the main burner nozzle outer guide plates and the main burner nozzle inner guide plates. The main burner nozzle air baffle is arranged in the main burner nozzle air flow channel, and the main burner nozzle air baffle is provided with a notch for forming the main burner nozzle air door hole.

[0015] The gas turbine combustion chamber structure of the main combustion nozzles of the present invention is circumferentially dispersedly arranged, wherein the duty nozzle comprises a duty nozzle fuel channel, a duty nozzle air guide plate, a duty nozzle fuel guide column, a duty nozzle air baffle, and a duty nozzle fuel box;

[0016] The duty nozzle fuel box is connected to a duty nozzle fuel channel for connecting to an external fuel supply end; a plurality of duty nozzle fuel nozzles are provided on the outer wall of the duty nozzle fuel box; the duty nozzle air baffle is arranged around the duty nozzle fuel box, and a notch is provided on the duty nozzle air baffle for forming a duty nozzle air door hole; the duty nozzle air guide plate is connected to the duty nozzle air baffle, and the duty nozzle air guide plate is sleeved on the duty nozzle fuel box and forms a duty nozzle air flow channel connected to the duty nozzle air door hole; the duty nozzle air flow channel is connected to the air supply part;

[0017] Among them, the inner cavity of the duty nozzle fuel box is provided with an axial annular protrusion corresponding to the duty nozzle fuel nozzle, and a plurality of duty nozzle fuel guide columns are axially arranged in the axial annular protrusion, and each of the duty nozzle fuel guide columns is connected to the corresponding duty nozzle fuel nozzle.

[0018] In the gas turbine combustion chamber structure with the main combustion nozzles dispersedly arranged in the circumferential direction of the present invention, the cross section of the duty nozzle fuel box is a regular polygon, and each side surface of the duty nozzle fuel box in the circumferential direction is provided with at least one duty nozzle fuel nozzle.

[0019] The gas turbine combustion chamber structure with the main combustion nozzles dispersedly arranged in the circumferential direction of the present invention, the air supply part comprises an outer casing and a combustion chamber head end cover;

[0020] The head of the flame tube extends outward to form an extension wall, and the extension end of the extension wall is provided with the end cover of the combustion chamber head, forming an intake air rectification cavity; the outer casing is sleeved on the flame tube and the extension wall and connected to the end cover of the combustion chamber head, and a counter-flow intake air passage is formed between the flame tube, the extension wall and the outer casing; the extension wall is evenly distributed with rectification holes communicating the intake air rectification cavity and the counter-flow intake air passage.

[0021] In the gas turbine combustion chamber structure with circumferentially dispersed main combustion nozzles of the present invention, both the outer casing and the flame tube are flared cylindrical cavities.

[0022] In the gas turbine combustion chamber structure with circumferentially dispersed main combustion nozzles of the present invention, a plurality of film cooling holes communicating the counter-flow intake air passage are arranged on the inner wall surface of the flame tube along the air flow direction, and a film wall corresponding to the film cooling holes is arranged on the inner wall surface of the flame tube. The film wall is a transition-shaped thin plate with different diameters upstream and downstream. The upstream wall of the film wall is connected to the inner wall surface of the flame tube, and the downstream wall of the film wall is parallel to the inner wall surface of the flame tube.

[0023] The gas turbine combustion chamber structure with circumferentially dispersed main combustion nozzles of the present invention further includes a support and sealing device, and the support and sealing device is connected between the outer deflector of the main combustion nozzle and the inner wall surface of the flame tube.

[0024] In the gas turbine combustion chamber structure with circumferentially dispersed main combustion nozzles of the present invention, the number of the main combustion nozzle rings is two, which are respectively an inner ring main combustion nozzle ring and an outer ring main combustion nozzle ring arranged in combination;

[0025] Six main combustion nozzles are evenly distributed on the inner ring main combustion nozzle ring, and twelve main combustion nozzles are evenly distributed on the outer ring main combustion nozzle ring; the outer deflector of the main combustion nozzle on the inner ring main combustion nozzle ring and the inner deflector of the main combustion nozzle on the outer ring main combustion nozzle ring are combined into a main combustion nozzle middle deflector; and a main combustion nozzle partition plate for separating the main combustion nozzle air flow channels on both sides is arranged on the side of the main combustion nozzle air baffle away from the combustion chamber.

[0026] Due to the adoption of the above technical solutions, the present invention has the following advantages and positive effects compared with the prior art:

[0027] In an embodiment of the present invention, the fuel injection part at the head of the combustion chamber is set as a pilot nozzle and a main combustion nozzle ring arranged successively from inside to outside around the pilot nozzle. Each main combustion nozzle ring includes a number of main combustion nozzles arranged circumferentially and at intervals. At least one main combustion nozzle fuel injection hole corresponding in the circumferential direction is arranged on the opposite surfaces of adjacent main combustion nozzles, and a main combustion nozzle air hole corresponding and of the same size is arranged at each main combustion nozzle fuel injection hole. By arranging a plurality of main combustion nozzle fuel injection holes and main combustion nozzle air holes to form separated small flames in a micro-premixed manner, the residence time of the high-temperature flame is reduced, thereby achieving low NOx emissions of hydrogen; moreover, all the main combustion nozzle air holes are of the same size and are opposite to each other in pairs, ensuring that the air jet forms an inner vortex and an outer vortex, and the sizes are symmetrical and the shapes are stable, which is beneficial to the anchoring of the flame and realizes stable combustion. Description of the Drawings

[0028] Figure 1 It is a structural composition diagram of a gas turbine combustion chamber with circumferentially dispersed main combustion nozzles according to Embodiment 1 of the present invention;

[0029] Figure 2 It is a view in the A-A direction of the structure of a gas turbine combustion chamber with circumferentially dispersed main combustion nozzles according to Embodiment 1 of the present invention;

[0030] Figure 3 It is a view in the B-B direction of the structure of a gas turbine combustion chamber with circumferentially dispersed main combustion nozzles according to Embodiment 1 of the present invention;

[0031] Figure 4 It is a schematic diagram of the main combustion nozzles of the structure of a gas turbine combustion chamber with circumferentially dispersed main combustion nozzles according to Embodiment 1 of the present invention;

[0032] Figure 5 It is a sectional view of the pilot nozzle of the structure of a gas turbine combustion chamber with circumferentially dispersed main combustion nozzles according to Embodiments 1 and 2 of the present invention;

[0033] Figure 6 It is an axonometric view of the pilot nozzle of the structure of a gas turbine combustion chamber with circumferentially dispersed main combustion nozzles according to Embodiments 1 and 2 of the present invention;

[0034] Figure 7 It is a partial flow field schematic diagram of the main combustion area of the structure of a gas turbine combustion chamber with circumferentially dispersed main combustion nozzles according to Embodiment 1 of the present invention;

[0035] Figure 8 It is a structural composition diagram of a gas turbine combustion chamber with circumferentially dispersed main combustion nozzles according to Embodiment 2 of the present invention;

[0036] Figure 9View A-A of the gas turbine combustor structure with circumferentially dispersed main combustion nozzles according to the second embodiment of the present invention;

[0037] Figure 10 View B-B of the gas turbine combustor structure with circumferentially dispersed main combustion nozzles according to the second embodiment of the present invention;

[0038] Figure 11 Schematic diagram of the main combustion nozzle of the gas turbine combustor structure with circumferentially dispersed main combustion nozzles according to the second embodiment of the present invention;

[0039] Figure 12 Partial flow field schematic diagram of the main combustion region of the gas turbine combustor structure with circumferentially dispersed main combustion nozzles according to the second embodiment of the present invention;

[0040] Figure 13 Schematic diagram of the micro-premixing principle described in the background;

[0041] Figure 14 Arrangement method of the combustor head in the patent described in the background;

[0042] Figure 15 Detail enlarged view of the arrangement method of the combustor head in the patent described in the background.

[0043] Explanation of reference numerals: 1: Main combustion nozzle; 1-1: Fuel channel of the main combustion nozzle; 1-2: Fuel cartridge of the main combustion nozzle; 1-3: Air orifice of the main combustion nozzle; 1-4: Fuel injection port of the main combustion nozzle; 1-5: Air baffle of the main combustion nozzle; 1-6: Outer flow guide plate of the main combustion nozzle; 1-7: Inner flow guide plate of the main combustion nozzle; 1-8: Middle flow guide plate of the main combustion nozzle; 1-9: Partition plate of the main combustion nozzle; 2: Pilot nozzle; 2-1: Fuel channel of the pilot nozzle; 2-2: Air flow guide plate of the pilot nozzle; 2-3: Fuel guide column of the pilot nozzle; 2-4: Air orifice of the pilot nozzle; 2-5: Fuel injection port of the pilot nozzle; 2-6: Air baffle of the pilot nozzle; 2-7: Fuel cartridge of the pilot nozzle; 3: Outer casing; 4: Combustion liner; 4-1: Rectifying hole; 4-2: Film cooling hole; 4-3: Film wall; 5: Support sealing device; 6: Inlet rectifying cavity; 7: Combustor head end cover; 8: Countercurrent inlet channel; 9: Combustor. Detailed implementation manners

[0044] The following further elaborates in detail on a gas turbine combustor structure with circumferentially dispersed main combustion nozzles proposed by the present invention in combination with the accompanying drawings and specific embodiments. The advantages and features of the present invention will be clearer according to the following description and the claims.

[0045] Embodiment 1

[0046] Refer to Figures 1 - 6, in one embodiment, a structure of a gas turbine combustor 9 with circumferentially distributed main combustion nozzles 1 includes a flame tube 4, a fuel injection part, and an air supply part.

[0047] A combustion chamber 9 is formed inside the flame tube 4. The axis of the flame tube 4 is set as the first axis. The fuel injection part includes a pilot nozzle 2 and at least one main combustion nozzle ring 1. The pilot nozzle 2 is arranged at the head of the flame tube 4 and along the first axis. The main combustion nozzle ring 1 surrounds the pilot nozzle 2 and is arranged in sequence from inside to outside. Among them, the main combustion nozzle ring 1 includes a number of main combustion nozzles 1 that are circumferentially and spaced apart with the first axis as the center of the circle. At least one corresponding main combustion nozzle fuel orifice 1-4 is provided on the opposite surfaces of adjacent main combustion nozzles 1, and a main combustion nozzle air flow channel is formed between adjacent main combustion nozzles 1. A main combustion nozzle air orifice 1-3 corresponding to each main combustion nozzle fuel orifice 1-4 is provided in the main combustion nozzle air flow channel, and the sizes and shapes of the main combustion nozzle air orifices 1-3 are the same. The output end of the air supply part is connected to each main combustion nozzle air flow channel and the pilot nozzle 2 to provide the air required for the combustion of the main combustion nozzles 1 and the pilot nozzle 2.

[0048] In this embodiment, by setting the fuel injection part at the head of the flame tube 4 as the pilot nozzle 2 and the main combustion nozzle ring 1 that surrounds the pilot nozzle 2 in sequence from inside to outside, each main combustion nozzle ring 1 includes a number of main combustion nozzles 1 that are circumferentially and spaced apart. At least one main combustion nozzle fuel hole corresponding in the circumferential direction is provided on the opposite surfaces of adjacent main combustion nozzles 1, and a corresponding main combustion nozzle air orifice 1-3 with the same size is provided at each main combustion nozzle fuel hole. By setting a number of main combustion nozzle fuel holes and main combustion nozzle air orifices 1-3 to form separated small flames in a micro-premixed manner, the residence time of the high-temperature flame is reduced, thereby achieving low NOx emissions of hydrogen; and, all the main combustion nozzle air orifices are of the same size and are opposite to each other in pairs, ensuring that the air jets form an inner vortex and an outer vortex, and the sizes are symmetrical and the shapes are stable, which is beneficial to the anchoring of the flame and realizes stable combustion.

[0049] Next, taking the number of the main combustion nozzle rings 1 as one as an example, the specific structure of the structure of the gas turbine combustor 9 with circumferentially distributed main combustion nozzles 1 in this embodiment will be further described:

[0050] Refer to Figure 2 Figure 4 , in this main combustion nozzle ring 1, the main combustion nozzles 1 therein may specifically include a main combustion nozzle fuel passage 1-1, a main combustion nozzle fuel cartridge 1-2, a main combustion nozzle air baffle 1-5, a main combustion nozzle outer deflector 1-6, and a main combustion nozzle inner deflector 1-7.

[0051] Each main burner fuel box 1-2 is connected to a main burner fuel channel 1-1 for connecting to an external fuel supply end, and the main burner fuel channel 1-1 is arranged axially and connected to the side of the main burner fuel box 1-2 away from the combustion chamber 9. A plurality of main burner fuel boxes 1-2 are arranged at intervals along the circumferential direction to form an annular structure, and the main burner fuel box 1-2 is provided with at least one main burner fuel nozzle 1-4 (specifically, it can be one, two or three, and the corresponding main burner fuel nozzles 1-4 on each main burner fuel box 1-2 are all located on a circle with the axis of the flame tube 4 as the center) uniformly distributed along the radial direction on both sides of the circumferential direction. The main burner nozzle outer guide plate 1-6 is connected to the radially outer sides of two adjacent main burner nozzle fuel boxes 1-2, and the main burner nozzle inner guide plate 1-7 is connected to the radially inner sides of two adjacent main burner nozzle fuel boxes 1-2 (that is, the two adjacent main burner nozzle fuel boxes 1-2 are connected by the main burner nozzle outer guide plate 1-6 and the main burner nozzle inner guide plate 1-7).

[0052] Among them, the space enclosed by the adjacent main fuel nozzle fuel box 1-2, the main fuel nozzle outer guide plate 1-6 and the main fuel nozzle inner guide plate 1-7 is the air flow channel of the main fuel nozzle 1, and the above-mentioned main fuel nozzle air baffle 1-5 is arranged in the air flow channel of the main fuel nozzle 1, and the main fuel nozzle air baffle 1-5 is provided with a notch for forming a main fuel nozzle air door hole 1-3, which is used to block the air entering the air flow channel of the main fuel nozzle 1 and guide the air to flow to each main fuel nozzle air door hole 1-3.

[0053] The fuel passes through the main burner fuel channel 1-1 and enters the main burner fuel box 1-2, where it completes the pressure equalization and distribution process, and then is quickly ejected horizontally from the main burner fuel nozzle 1-4 to quickly mix with the air.

[0054] See also Figure 5 and Figure 6 In this embodiment, the duty nozzle 2 may specifically include a duty nozzle fuel channel 2-1, a duty nozzle air guide plate 2-2, a duty nozzle fuel guide column 2-3, a duty nozzle 2 air baffle 2-6, and a duty nozzle 2 fuel box.

[0055] The duty nozzle 2 fuel cartridge is connected to a duty nozzle fuel passage for connecting an external fuel supply end, which is also axially arranged and connected to the side of the duty nozzle 2 fuel cartridge away from the combustion chamber 9. A number of duty nozzle 2 fuel injection ports 2-5 are provided on the outer side wall of the duty nozzle 2 fuel cartridge. The duty nozzle 2 air baffle 2-6 surrounds the duty nozzle 2 fuel cartridge, and a notch for forming a duty nozzle air opening 2-4 is provided on the duty nozzle 2 air baffle 2-6. The duty nozzle air deflector 2-2 is connected to the duty nozzle 2 air baffle 2-6, and the duty nozzle air deflector 2-2 is sleeved on the duty nozzle 2 fuel cartridge and forms a duty nozzle 2 air flow passage communicating with the duty nozzle air opening 2-4. The duty nozzle 2 air flow passage is communicated with the air supply part. After air enters the duty nozzle 2 air flow passage, it is blocked by the duty nozzle air deflector 2-2 and guided to flow to each duty nozzle air opening 2-4.

[0056] An axial annular protrusion corresponding to the duty nozzle 2 fuel injection port 2-5 is provided in the inner cavity of the duty nozzle 2 fuel cartridge. The center of the annular protrusion is the buffer area of the duty nozzle 2 fuel cartridge for buffering fuel. A number of duty nozzle fuel guide columns 2-3 are axially arranged in the axial annular protrusion, and each duty nozzle fuel guide column 2-3 communicates with the corresponding duty nozzle 2 fuel injection port 2-5.

[0057] Among them, the outer edge of the duty nozzle 2 air baffle 2-6 is connected to the inner side in the radial direction of each main burner nozzle inner deflector 1-7 and each main burner nozzle fuel cartridge 1-2.

[0058] Further, the cross-section of the duty nozzle 2 fuel cartridge is a regular polygon (preferably a quadrilateral, hexagon, or octagon), and at least one duty nozzle 2 fuel injection port 2-5 (specifically, it can be one, two, or three) is provided on each side of the duty nozzle 2 fuel cartridge in the circumferential direction.

[0059] Fuel enters the duty nozzle 2 fuel cartridge through the duty nozzle fuel passage 2-1, where the pressure equalization and distribution process are completed, and then it is quickly ejected laterally from each duty nozzle 2 fuel injection port 2-5 through the duty nozzle fuel guide column 2-3 and quickly mixed with air.

[0060] See Figure 1 , in this embodiment, the air supply part may specifically include an outer casing 3 and a combustion chamber head end cover 7.

[0061] The head of the flame tube 4 extends outward to form an extension wall (extending in the direction away from the combustion chamber 9). The extension end of the extension wall is provided with a combustion chamber head end cover 7, forming an intake air rectification cavity 6 communicating with the head of the flame tube 4. The outer casing 3 is sleeved on the flame tube 4 and the extension wall and connected to the combustion chamber head end cover 7, and forms a countercurrent intake air passage 8 located between the flame tube 4, the extension wall and the outer casing 3. The extension wall is evenly distributed with rectification holes 4-1 communicating the intake air rectification cavity 6 and the countercurrent intake air passage 8.

[0062] The rectification holes 4-1 are arranged in several rows along the direction of the air flow and are evenly distributed circumferentially along the extension wall. As one of the means to adjust the pressure loss and the proportion of the air volume at the head, the relevant performance parameters such as the number and aperture of the rectification holes 4-1 are set according to the requirements of the thermal protection design.

[0063] Air is sent to the head of the combustion chamber 9 through the countercurrent intake air passage 8, and then enters the intake air rectification cavity 6 through the multi-row rectification holes 4-1 evenly distributed circumferentially. The equalization and distribution process are completed here. With the guiding action of the outer guiding plate 1-6 of the main combustion nozzle, the inner guiding plate 1-7 of the main combustion nozzle, and the air guiding plate 2-2 of the pilot nozzle, the air is respectively sprayed into the downstream combustion chamber 9 along the axis direction of the flame tube 4 from the air holes 1-3 of the main combustion nozzle and the air holes 2-4 of the pilot nozzle. On the way, it quickly mixes with the fuel laterally sprayed from the fuel injection ports 1-4 of the main combustion nozzle and the fuel injection ports 2-5 of the pilot nozzle 2, and combustion reaction occurs in the combustion chamber 9 to form dispersed small flames.

[0064] Furthermore, both the outer casing 3 and the flame tube 4 are flared cylindrical cavities, and they jointly form the air countercurrent intake air passage 8.

[0065] On the inner wall surface of the flame tube 4, there may be provided several film cooling holes 4-2 communicating with the countercurrent intake air passage 8 along the air flow direction (the film cooling holes 4-2 can be arranged in multiple places according to the cooling requirements of the wall surface of the flame tube 4, and the diameter and circumferential number of the film cooling holes 4-2 at each place can be designed as required according to the actual situation). And on the inner wall surface of the flame tube 4, there is a film wall 4-3 corresponding to the outlet of the film cooling holes 4-2. The film wall 4-3 is a transition-shaped thin plate with different diameters upstream and downstream. The upstream wall of the film wall 4-3 is welded to the inner wall surface of the flame tube 4, and the downstream wall of the film wall 4-3 is parallel to the inner wall surface of the flame tube 4 to facilitate the formation of a cooling air film at the wall attachment of the flame tube 4.

[0066] See Figure 1 , in this embodiment, the structure of the gas turbine combustion chamber 9 with the main combustion nozzles 1 circumferentially and dispersedly arranged may further include a support and sealing device 5. The support and sealing device 5 is connected between the outer guiding plate 1-6 of the main combustion nozzle and the inner wall surface of the flame tube 4 for the connection and positioning between the flame tube 4 and the outer guiding plate 1-6 of the main combustion nozzle. Preferably, its specific form can be a hula sealing structure.

[0067] See Figure 3 The main combustion nozzle fuel cartridge 1-2, the main combustion nozzle air baffle 1-5, the pilot nozzle 2 air baffle 2-6 and the pilot nozzle 2 fuel cartridge together constitute the head of the burner facing the fire side.

[0068] See Figure 7 As shown in Figure 7 , a cross-section of the flow field of a gas turbine combustor 9 with the main combustion nozzles 1 circumferentially dispersed in one embodiment of the present invention is intercepted. The door openings arranged in pairs ensure that the air jets form an inner vortex and an outer vortex, which are symmetric in size and stable in shape, facilitating the anchoring of the flame. At the same time, separated small flames are formed by the micro-premixing method, reducing the residence time of the high-temperature flame, thereby achieving low NOx emissions and stable combustion of hydrogen.

[0069] See Figure 1 and Figure 2 and Figure 3 As shown in Figure 1 , Figure 2 , and Figure 3 , the structure of the gas turbine combustor 9 with the main combustion nozzles 1 circumferentially dispersed in one embodiment of the present invention adopts the arrangement of "one pilot nozzle 2 + six main combustion nozzles 1 circumferentially dispersed in one week", mainly for micro-power units.

[0070] Embodiment 2

[0071] See Figures 8 - 11 As shown in Figures 8 - 11 , in this embodiment, on the basis of the above embodiment, the case where the number of rings of the main combustion nozzles 1 is two or more is described:

[0072] In this embodiment, when the number of rings of the main combustion nozzles 1 is two or more, between adjacent rings of the main combustion nozzles 1, the number of the main combustion nozzles 1 in the inner ring of the main combustion nozzles 1 is n, and the number of the main combustion nozzles 1 in the outer ring of the main combustion nozzles 1 is 2n, and n≥6. Between adjacent rings of the main combustion nozzles 1, the main combustion nozzles 1 in the inner ring of the main combustion nozzles 1 and the main combustion nozzles 1 in the outer ring of the main combustion nozzles 1 are staggeredly distributed.

[0073] The following further illustrates by taking the number of rings of the main combustion nozzles 1 being two as an example:

[0074] In this embodiment, when the number of rings of the main combustion nozzles 1 is two, the two rings of the main combustion nozzles 1 are respectively an inner ring of the main combustion nozzles 1 and an outer ring of the main combustion nozzles 1 which are combinedly arranged.

[0075] The number of the pilot nozzles 2 is still one, which is arranged at the center, and the specific structure remains unchanged. The structure of the countercurrent intake passage 8 remains unchanged, only the relative dimensions are enlarged.

[0076] Six main combustion nozzles 1 are evenly distributed on the inner ring of the main combustion nozzle 1 ring, and twelve main combustion nozzles 1 are evenly distributed on the outer ring of the main combustion nozzle 1 ring. And the main combustion nozzles 1 in the two weeks are exactly staggered, that is, the central axes of adjacent main combustion nozzles 1 are not parallel. The main combustion nozzle outer deflector 1-6 of the inner ring of the main combustion nozzle 1 ring and the main combustion nozzle inner deflector 1-7 of the outer ring of the main combustion nozzle 1 ring are combined into the main combustion nozzle middle deflector 1-8. And a main combustion nozzle separator 1-9 for separating the air flow paths of the main combustion nozzles 1 on both sides is provided on the side of the main combustion nozzle air baffle 1-5 away from the combustion chamber 9.

[0077] The area surrounded by the flame tube 4, the combustion chamber head end cover 7, the main combustion nozzle 1, and the pilot nozzle 2 forms an intake air rectification cavity 6. The downstream area of the air flow surrounded by the flame tube 4, the main combustion nozzle 1, and the pilot nozzle 2 forms a combustion chamber 9.

[0078] Preferably, the number of each side of the main combustion nozzle fuel nozzles 1-4 on both sides of the main combustion nozzle fuel cartridge 1-2 in this embodiment can be five.

[0079] See Figure 8 , the support sealing device 5 is used for the connection and positioning between the flame tube 4 and the main combustion nozzle outer deflector 1-6. Preferably, its specific form is a hula sealing structure.

[0080] See Figure 10 , the main combustion nozzle fuel cartridge 1-2, the main combustion nozzle air baffle 1-5, the pilot nozzle 2 air baffle 2-6, and the pilot nozzle 2 fuel cartridge together constitute the head of the burner facing the fire surface.

[0081] See Figure 12 , a cross-section of the flow field of a structure of a gas turbine combustion chamber 9 with the main combustion nozzles 1 circumferentially and dispersedly arranged in one of the embodiments is intercepted. The door openings arranged in pairs ensure that the air jets form an inner vortex and an outer vortex, and they are symmetric in size and stable in shape, which is beneficial to the anchoring of the flame. At the same time, small separated flames are formed through the micro-premixing method, reducing the residence time of the high-temperature flame, thereby achieving low NOx emissions and stable combustion of hydrogen.

[0082] See Figure 8 , Figure 9 , Figure 10 , for the structure of a gas turbine combustion chamber 9 with the main combustion nozzles 1 circumferentially and dispersedly arranged in one of the embodiments, the arrangement method of "one pilot nozzle 2 + eighteen main combustion nozzles 1 arranged circumferentially and dispersedly in two weeks" is adopted, mainly for medium and small power units.

[0083] The above has described the embodiments of the present invention in detail with reference to the accompanying drawings, but the present invention is not limited to the above embodiments. Even if various changes are made to the present invention, provided that these changes fall within the scope of the claims of the present invention and their equivalent technologies, they still fall within the protection scope of the present invention.

Claims

1. A gas turbine combustor structure with circumferentially dispersed main combustion nozzles, characterized in that, it includes: A flame tube, with a combustion chamber formed inside it, and the axis of the flame tube is set as the first axis; A fuel injection part, including a pilot nozzle and at least one main combustion nozzle ring; the pilot nozzle is arranged at the head of the flame tube and along the first axis; the main combustion nozzle ring surrounds the pilot nozzle and is arranged in sequence from inside to outside; wherein, the main combustion nozzle ring includes a number of main combustion nozzles circumferentially and spaced apart with the first axis as the center of the circle, and at least one corresponding main combustion nozzle fuel injection port is provided on the opposite surfaces of adjacent main combustion nozzles, and a main combustion nozzle air flow channel is formed between adjacent main combustion nozzles; a main combustion nozzle air hole corresponding to each main combustion nozzle fuel injection port is provided in the main combustion nozzle air flow channel, and the size and shape of the main combustion nozzle air holes are the same; An air supply part, the output end of the air supply part is communicated with each main combustion nozzle air flow channel and the pilot nozzle; The main combustion nozzle includes a main combustion nozzle fuel channel, a main combustion nozzle fuel box, a main combustion nozzle air baffle, a main combustion nozzle outer deflector, and a main combustion nozzle inner deflector; Each main combustion nozzle fuel box is communicated with a main combustion nozzle fuel channel for communicating with an external fuel supply end; a plurality of main combustion nozzle fuel boxes are arranged at intervals in the circumferential direction to form an annular structure, and at least one main combustion nozzle fuel injection port arranged radially is provided on both sides of the main combustion nozzle fuel box in the circumferential direction; the main combustion nozzle outer deflector is connected to the outer side in the radial direction of adjacent two main combustion nozzle fuel boxes, and the main combustion nozzle inner deflector is connected to the inner side in the radial direction of adjacent two main combustion nozzle fuel boxes; The main combustion nozzle air flow channel is formed between adjacent main combustion nozzle fuel boxes, the main combustion nozzle outer deflector and the main combustion nozzle inner deflector, the main combustion nozzle air baffle is arranged in the main combustion nozzle air flow channel, and a notch for forming the main combustion nozzle air hole is provided on the main combustion nozzle air baffle.

2. The gas turbine combustor structure with circumferentially dispersed main combustion nozzles according to claim 1, characterized in that, The number of the main combustion nozzle rings is two or more. Between adjacent two main combustion nozzle rings, the number of the main combustion nozzles of the inner main combustion nozzle ring is n, the number of the main combustion nozzles of the outer main combustion nozzle ring is 2n, and n≥6; Between adjacent two main combustion nozzle rings, the main combustion nozzles of the inner main combustion nozzle ring and the main combustion nozzles of the outer main combustion nozzle ring are staggered with each other.

3. The gas turbine combustor structure with circumferentially dispersed main combustion nozzles according to claim 1, characterized in that, The pilot nozzle includes a pilot nozzle fuel channel, a pilot nozzle air deflector, a pilot nozzle fuel guide column, a pilot nozzle air baffle, and a pilot nozzle fuel box; The duty nozzle fuel box is connected to a duty nozzle fuel channel for connecting to an external fuel supply end; a plurality of duty nozzle fuel nozzles are provided on the outer wall of the duty nozzle fuel box; the duty nozzle air baffle is arranged around the duty nozzle fuel box, and a notch is provided on the duty nozzle air baffle for forming a duty nozzle air door hole; the duty nozzle air guide plate is connected to the duty nozzle air baffle, and the duty nozzle air guide plate is sleeved on the duty nozzle fuel box and forms a duty nozzle air flow channel connected to the duty nozzle air door hole; the duty nozzle air flow channel is connected to the air supply part; Among them, the inner cavity of the duty nozzle fuel box is provided with an axial annular protrusion corresponding to the duty nozzle fuel nozzle, and a plurality of duty nozzle fuel guide columns are axially arranged in the axial annular protrusion, and each of the duty nozzle fuel guide columns is connected to the corresponding duty nozzle fuel nozzle.

4. The gas turbine combustion chamber structure with the main combustion nozzles dispersedly arranged in the circumferential direction according to claim 3, It is characterized in that The cross section of the service nozzle fuel box is a regular polygon, and each side surface of the service nozzle fuel box in the circumferential direction is provided with at least one service nozzle fuel nozzle.

5. The gas turbine combustion chamber structure with the main combustion nozzles dispersedly arranged in the circumferential direction according to claim 1, It is characterized in that The air supply unit includes an outer casing and a combustion chamber head end cover; The head of the flame tube extends outward to form an extension wall, and the extended end of the extension wall is provided with the combustion chamber head end cover to form an air intake rectification cavity; the outer casing is sleeved on the flame tube and the extension wall and connected to the combustion chamber head end cover, and forms a counter-flow air intake passage located between the flame tube, the extension wall and the outer casing; the extension wall is evenly distributed with rectification holes connecting the air intake rectification cavity and the counter-flow air intake passage.

6. The gas turbine combustion chamber structure with the main combustion nozzles dispersedly arranged in the circumferential direction according to claim 5, It is characterized in that The outer casing and the flame tube are both expanded cylindrical cavities.

7. The gas turbine combustion chamber structure with the main combustion nozzles dispersedly arranged in the circumferential direction according to claim 5, It is characterized in that A plurality of air film cooling holes connected to the counter-flow air inlet passage are arranged on the inner wall surface of the flame tube along the air flow direction, and an air film wall corresponding to the air film cooling holes is arranged on the inner wall surface of the flame tube, and the air film wall is a transitional thin plate with different diameters upstream and downstream, the upstream wall of the air film wall is connected to the inner wall surface of the flame tube, and the downstream wall of the air film wall is parallel to the inner wall surface of the flame tube.

8. The gas turbine combustion chamber structure with the main combustion nozzles dispersedly arranged in the circumferential direction according to claim 1, It is characterized in that It also includes a supporting sealing device, which is connected between the outer guide plate of the main combustion nozzle and the inner wall surface of the flame tube.

9. The gas turbine combustion chamber structure with the main combustion nozzles dispersedly arranged in the circumferential direction according to claim 1, It is characterized in that The number of the main combustion nozzle rings is two, which are an inner ring main combustion nozzle ring and an outer ring main combustion nozzle ring which are arranged in combination; Six of the main combustion nozzles are evenly distributed on the inner ring main combustion nozzle ring, and twelve of the main combustion nozzles are evenly distributed on the outer ring main combustion nozzle ring; the outer flow guide plate of the main combustion nozzle on the inner ring main combustion nozzle ring and the inner flow guide plate of the main combustion nozzle on the outer ring main combustion nozzle ring are combined into the middle flow guide plate of the main combustion nozzle; and a main combustion nozzle partition plate for separating the main combustion nozzle air flow channels on both sides is provided on the side of the main combustion nozzle air baffle away from the combustion chamber.

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