Axial staged combustion chamber with reentrant cavity

Abstract

The present application belongs to the technical field of gas turbine combustion chamber, and particularly relates to an axial staged combustion chamber with a cavity; the axial staged combustion chamber comprises a combustion main body, an ammonia escape prevention reduction mechanism arranged on the combustion main body, and an axial staged combustion mechanism arranged in the combustion main body; the axial staged combustion mechanism comprises a near-equivalence ratio combustion assembly arranged on one side of the combustion main body, a trapped vortex combustion assembly arranged on one side of the near-equivalence ratio combustion assembly, and an air injection lean combustion assembly arranged on the other side of the combustion main body; the present application provides the near-equivalence ratio combustion assembly, which adopts the combustion organization mode of near-equivalence ratio 1:1 at the front end, provides high-temperature gas at the front end, and can stabilize the combustion of the middle section and play the role of a duty flame.

Description

Technical Field

[0001] The invention belongs to the technical field of gas turbine combustion chambers, and in particular relates to an axially staged combustion chamber with a concave cavity. Background Art

[0002] Gas turbine combustion needs to adapt to the diverse fuel requirements of the new energy era. Among these new fuels, ammonia offers several advantages over hydrogen in certain scenarios: it is easy to liquefy and store, with an energy density comparable to fossil fuels; it is carbon-free and can be synthesized using renewable energy and carbon-free methods; and it leverages the existing technological foundation of the ammonia industry. Therefore, ammonia is a promising gas turbine fuel. However, current research into ammonia as a fuel has struggled to meet the requirements for low-pollution combustion, and mature applications are still limited. Summary of the Invention

[0003] In view of the above situation, in order to overcome the defects of the prior art, the present invention provides an axially staged combustion chamber with a concave cavity. In order to solve the problems of inactive fuel characteristics of ammonia, low flame propagation speed, narrow equivalence ratio range for stable flame combustion, and lower calorific value relative to traditional fuels, the present invention proposes a near-equivalence ratio combustion component. By adopting a combustion organization method with a near-equivalence ratio of 1:1 at the front end and providing high-temperature fuel gas at the front end, the combustion in the middle section can be made more stable, while also playing the role of a duty flame.

[0004] The technical solution adopted by the present invention is as follows: The present invention provides an axially staged combustion chamber with a concave cavity, including a combustion body, an anti-ammonia escape reduction mechanism arranged on the combustion body, and an axially staged combustion mechanism, wherein the axially staged combustion mechanism is built into the combustion body; the axially staged combustion mechanism includes a near-equivalence ratio combustion component arranged on one side of the combustion body, a trapped vortex combustion component arranged on one side of the near-equivalence ratio combustion component, and an air-injected lean combustion component arranged on the other side of the combustion body.

[0005] Furthermore, the combustion body includes a combustion chamber, a concave cavity, a front section of the flame tube, a rear section of the flame tube, an air outlet and an air inlet cavity. The combustion chamber is arranged in the combustion body, the front section of the flame tube is arranged inside one end of the combustion chamber, the concave cavity is arranged on one side of the front section of the flame tube, and the rear section of the flame tube is arranged inside the other end of the combustion chamber. The air inlet cavity is fixed to one end outside the combustion chamber, and the air outlet is fixed to the other end outside the combustion chamber.

[0006] Furthermore, the shape of the combustion chamber is a cylindrical cavity with a concave cavity, an annular cavity with concave cavities on both sides, or an annular cavity with concave cavities on one side.

[0007] Further, the air inlet one is connected with an air source, the fuel inlet two is connected with a fuel source, and the fuel inlet one is connected with an ammonia fuel source.

[0008] Further, the near-equivalence ratio combustion assembly comprises an air inlet one, a fuel inlet one, a swirler, a diffusion nozzle, a near-equivalence ratio combustion zone, an igniter one and an air inlet two, the air inlet one is arranged at one end of the air channel, the fuel inlet one is arranged at one end of the fuel channel, the swirler is arranged in the air channel, the diffusion nozzle is detachably connected to the other end of the inside of the fuel channel, the near-equivalence ratio combustion zone is arranged in the front section of the flame tube, the air inlet two is arranged on the outside of one end of the front section of the flame tube, and the igniter one is detachably connected to the upper end of the inside of the front section of the flame tube.

[0009] Further, the air inlet one is connected with an air source, the fuel inlet two is connected with a fuel source, and the fuel inlet one is connected with an ammonia fuel source.

[0010] Further, the trapped vortex combustion assembly comprises a trapped vortex rich combustion zone, an igniter two, a fuel inlet two, an air inlet three, an internal air inlet and a partition plate, the trapped vortex rich combustion zone is arranged in the cavity, the igniter two is detachably connected to the top end of the inside of the cavity, the fuel inlet two is arranged at one side of the top end of the cavity, the air inlet three is arranged on the side wall of one end of the cavity, the partition plate is arranged at one side of the top end of the inside of the cavity, and the internal air inlet is arranged on the partition plate.

[0011] Further, the air injection lean combustion assembly comprises a lean combustion zone, a mixing zone, an air inlet four and a mixing structure, the mixing zone is arranged in the rear section of the flame tube, the lean combustion zone is arranged on the other side of the inside of the rear section of the flame tube, the mixing structure is detachably connected to the top end of the rear section of the flame tube, and the air inlet four is arranged on the mixing structure.

[0012] Further, the air injection lean combustion assembly comprises a lean combustion zone, a mixing zone, an air inlet four and a mixing structure, the mixing zone is arranged in the rear section of the flame tube, the lean combustion zone is arranged on the other side of the inside of the rear section of the flame tube, the mixing structure is detachably connected to the top end of the rear section of the flame tube, and the air inlet four is arranged on the mixing structure.

[0013] Further, the air inlet one, the air inlet two, the air inlet three, the air inlet four and the air inlet five are connected with an air source, the air source is air, the fuel inlet two and the fuel inlet three are connected with a fuel source, and the fuel inlet one is connected with an ammonia fuel source.

[0014] The beneficial effects achieved by the above structure are as follows:

[0015] (1) In order to solve the problems of inactive fuel characteristics of ammonia, low flame propagation speed, narrow equivalence ratio range of stable combustion of flame and low calorific value compared with traditional fuels, the present application proposes a near-equivalence ratio combustion assembly, which adopts a near-equivalence ratio 1:1 combustion organization mode at the front end, provides high-temperature combustion gas at the front end, can make the combustion of the middle section more stable, and at the same time plays the role of duty flame.

[0016] (2) Through the vortex combustion assembly, the concave cavity vortex is adopted, two-dimensional uniform fuel gas is formed, the mixing of the middle section can be accelerated, and the uniform and complete combustion is promoted.

[0017] (3) High-temperature combustion mode is adopted, near-equivalence ratio combustion is adopted in the combustion zone, high-temperature gas enters the vortex and mainstream, which can improve the temperature of the reaction zone and accelerate the reaction.

[0018] (4) In order to further improve the practicability and popularization, through the ammonia escape prevention reduction mechanism, the high fuel NOX of ammonia in the new fuel is fully utilized, the premixed ammonia fuel in the mixer is used as a reducing agent, is added from the fuel inlet three, and the generated NOX is fully reduced to neutral N2.

[0019] (5) Through the axial staged combustion mechanism, the low pollution combustion technology for ammonia or ammonia-containing fuel is realized.

[0020] (6) Through the axial staged combustion mechanism, no additional denitration device and denitration agent are needed.

[0021] (7) Single pipe design is adopted, which is beneficial to modular application and convenient for upgrading and expansion. BRIEF DESCRIPTION OF DRAWINGS

[0022] Figure 1 It is a front view sectional view of the first embodiment of the present application;

[0023] Figure 2 It is a front view sectional view of the second embodiment of the present application;

[0024] Figure 3 It is a front view sectional view of the third embodiment of the present application.

[0025] Wherein, 1, the combustion main body, 2, axial staged combustion mechanism, 3, prevent ammonia escape reduction mechanism, 4, combustion chamber, 5, cavity, 6, flame tube front section, 7, flame tube rear section, 8, gas outlet, 9, intake cavity, 10, air passage, 11, fuel passage, 12, near equivalence ratio combustion assembly, 13, trapped vortex combustion assembly, 14, air injection lean combustion assembly, 15, air inlet one, 16, fuel inlet one, 17, swirler, 18, diffusion nozzle, 19, near equivalence ratio combustion zone, 20, igniter one, 21, air inlet two, 22, trapped vortex rich zone, 23, igniter two, 24, fuel inlet two, 25, air inlet three, 26, internal air inlet, 27, lean combustion zone, 28, mixing zone, 29, air inlet four, 30, mixing structure, 31, mixer, 32, fuel inlet three, 33, air inlet five, 34, partition plate.

[0026] The accompanying drawings are included to provide a further understanding of the application and are incorporated in and constitute a part of the specification, illustrate embodiments of the application and are included to provide a further understanding of the application, and are made a part of the specification and are used to explain the application, but do not constitute a limitation on the application. DETAILED DESCRIPTION

[0027] The technical solutions in the embodiments of the application will be clearly and completely described below with reference to the drawings in the embodiments of the application. Obviously, the described embodiments are only part of the embodiments of the application, rather than all the embodiments of the application. Based on the embodiments in the application, all other embodiments obtained by those skilled in the art without creative work fall within the scope of protection of the application.

[0028] In the description of the application, it should be understood that the terms "upper", "lower", "front", "back", "left", "right", "top", "bottom", "inner", "outer" and the like indicate the orientation or positional relationship based on the orientation or positional relationship shown in the drawings, and are only for the convenience of describing the application and simplifying the description, and do not indicate or imply that the device or element referred to must have a particular orientation, be constructed and operated in a particular orientation, and therefore cannot be understood as a limitation on the application.

[0029] Embodiment one

[0030] As shown in Figure 1 The application proposes an axial staged combustion chamber with a cavity, which comprises a combustion main body 1, a prevent ammonia escape reduction mechanism 3 and an axial staged combustion mechanism 2 arranged on the combustion main body 1, and the axial staged combustion mechanism 2 is arranged in the combustion main body 1.

[0031] The combustion main body 1 comprises a combustion chamber 4, a cavity 5, a front flame tube section 6, a rear flame tube section 7, an air outlet 8 and an air inlet cavity 9, the combustion chamber 4 is arranged in the combustion main body 1, the front flame tube section 6 is arranged at one end of the combustion chamber 4, the cavity 5 is arranged at one side of the front flame tube section 6, the rear flame tube section 7 is arranged at the other end of the combustion chamber 4, the air inlet cavity 9 is arranged at one end outside of the combustion chamber 4, and the air outlet 8 is arranged at the other end outside of the combustion chamber 4.

[0032] The combustion chamber 4 is in the shape of a column cavity with the cavity 5, or a ring cavity with double cavities 5, or a ring cavity with a single cavity 5.

[0033] The air inlet cavity 9 comprises an air passage 10 and a fuel passage 11, the air passage 10 is arranged at the top end of the air inlet cavity 9, the fuel passage 11 is arranged inside the air inlet cavity 9, and the fuel passage 11 is arranged at the lower end of the air passage 10.

[0034] The near-equivalence ratio combustion assembly 12 comprises an air inlet 15, a fuel inlet 16, a swirler 17, a diffusion nozzle 18, a near-equivalence ratio combustion zone 19, an igniter 20 and an air inlet 21, the air inlet 15 is arranged at one end of the air passage 10, the fuel inlet 16 is arranged at one end of the fuel passage 11, the swirler 17 is arranged inside the air passage 10, the diffusion nozzle 18 is detachably connected to the other end inside the fuel passage 11, the near-equivalence ratio combustion zone 19 is arranged inside the front flame tube section 6, the air inlet 21 is arranged through the outer wall of one end of the front flame tube section 6, and the igniter 20 is detachably connected to the upper end inside the front flame tube section 6.

[0035] The air connected to the air inlet 15 and the fuel connected to the fuel inlet 16 adopt a near-equivalence ratio combustion organization mode of 1:1.

[0036] The trapped vortex combustion assembly 13 comprises a trapped vortex rich combustion zone 22, an igniter 23, a fuel inlet 24, an air inlet 25, an internal air inlet 26 and a partition plate 34, the trapped vortex rich combustion zone 22 is arranged inside the cavity 5, the igniter 23 is detachably connected to the top end inside the cavity 5, the fuel inlet 24 is arranged at one side of the top end of the cavity 5, the air inlet 25 is arranged on the side wall of one end of the cavity 5, the partition plate 34 is arranged at one side of the top end inside the cavity 5, and the internal air inlet 26 is arranged on the partition plate 34.

[0037] The air injection lean combustion assembly 14 comprises a lean combustion zone 27, a mixing zone 28, an air inlet 29 and a mixing structure 30, the mixing zone 28 is arranged at one side of the rear flame tube section 7, the lean combustion zone 27 is arranged at the other side inside the rear flame tube section 7, the mixing structure 30 is detachably connected to the top end of the rear flame tube section 7, and the air inlet 29 is arranged on the mixing structure 30.

[0038] The ammonia-escape-preventing reduction mechanism 3 comprises a mixer 31, a fuel inlet three 32 and an air inlet five 33, the mixer 31 is arranged through the lower end of the other end side wall of the cavity 5, the air inlet five 33 is arranged on one side of the mixer 31, and the fuel inlet three 32 is arranged on the upper end of the mixer 31.

[0039] The air inlets one 15, two 21, three 25, four 29 and five 33 are connected with an air source, the air source is air; the fuel inlets two 24 and three 32 are connected with fuel, and the fuel inlet one 16 is connected with ammonia fuel.

[0040] In specific use, when combustion is performed, the air inlet one 15 is connected with air, the fuel inlet one 16 is connected with fuel, the air stabilizes the flame through the cyclone 17, the fuel diffuses and burns through the diffusion nozzle 18, the igniter one 20 is used for ignition, the air connected with the air inlet one 15 and the fuel connected with the fuel inlet one 16 adopt a combustion organization mode of near equivalence ratio 1:1, a typical value is 1.1, a near equivalence ratio combustion zone 19 is formed, high-temperature gas is provided, the middle section can be more stably combusted, and the near equivalence ratio combustion zone 19 also plays a role of a duty flame, the air inlets two 21 and three 25 cool the wall surface and provide combustion air, the air introduced through the air inlet three 25 and the internal air inlet 26 mixes with the high-temperature air of the near equivalence ratio combustion zone 19 and enters the cavity 5, diffusion combustion is formed, a two-dimensional uniform fuel-rich gas is formed in a way of cavity 5 vortex, the mixing of the middle section can be accelerated, and uniform and complete combustion is promoted, the fuel NOX of ammonia in the new fuel is high, the reducibility of ammonia is fully utilized, the premixed ammonia fuel in the mixer 31 is taken as a reducing agent, is added from the fuel inlet three 32, and the generated NOX is fully reduced to neutral N2, air is introduced from the air inlet four 29, gas mixing is performed at the mixing zone 28, lean fuel combustion is realized at the lean fuel combustion zone 27, and finally the tail gas is discharged from the gas outlet 8, which is the whole working process of the present application, and the step can be repeated next time.

[0041] Embodiment two

[0042] The difference between the embodiment and the embodiment one is that, as shown in the figure, the shape of the combustion chamber 4 is a ring-type combustion chamber with double cavities 5, the symmetry axis of the columnar combustion chamber with the cavity 5 is biased downward, and the symmetry is rotated one circle to form the ring-type combustion chamber with double cavities 5. Figure 2 Embodiment three

[0043] The difference between the embodiment and the embodiment one is that, as shown in the figure, the shape of the combustion chamber 4 is a ring-type combustion chamber with single cavity 5, the symmetry axis of the columnar combustion chamber with the cavity 5 (the lower half is removed and the air inlet cavity is not included) is biased downward, and the symmetry is rotated one circle to form the ring-type combustion chamber with single cavity 5.

[0044] Figure 3 ​​

[0045] It is to be understood that the terminology used herein such as first and second, and the like, is only used to distinguish one entity or action from another entity or action, and does not necessarily require or imply any such actual relationship or order between such entities or actions. Moreover, the terms "comprises", "comprising", or any other variations thereof, are intended to cover a non-exclusive inclusion, such that a process, method, article, or apparatus that comprises a list of elements does not include only those elements but can include other elements not expressly listed or inherent to such process, method, article, or apparatus.

[0046] While the embodiments of the application have been shown and described, it is to be understood that the embodiments of the application are capable of numerous changes, modifications, substitutions, and alterations, and many embodiments of the application will occur to those skilled in the art upon reading this description and that scope of the application should be limited only by the scope of the claims and the equivalents thereof.

[0047] The above description of the application and its embodiments is not restrictive, and the embodiments shown in the drawings are only one of the embodiments of the application, and the actual structure is not limited thereto. In general, if a person skilled in the art is inspired by it, without departing from the purpose of the application, without creative design, similar structure and embodiments of the technical solution should belong to the protection scope of the application.

Claims

1. An axially staged combustion chamber with a concave cavity, comprising a combustion body (1) and an ammonia escape prevention reduction mechanism (3) arranged on the combustion body (1), characterized in that: The axially staged combustion mechanism (2) is also included, and the axially staged combustion mechanism (2) is internally arranged in the combustion body (1); the axially staged combustion mechanism (2) includes a near-equivalence ratio combustion assembly (12) arranged on one side of the combustion body (1), a trapped vortex combustion assembly (13) arranged on one side of the near-equivalence ratio combustion assembly (12), and an air injection lean combustion assembly (14) arranged on the other side inside the combustion body (1); The combustion body (1) comprises a combustion chamber (4), a concave cavity (5), a flame tube front section (6), a flame tube rear section (7), an air outlet (8) and an air inlet cavity (9); the combustion chamber (4) is arranged in the combustion body (1); the flame tube front section (6) is arranged inside one end of the combustion chamber (4); the concave cavity (5) is arranged on one side of the flame tube front section (6); the flame tube rear section (7) is arranged inside the other end of the combustion chamber (4); the air inlet cavity (9) is fixed to one end outside the combustion chamber (4); and the air outlet (8) is fixed to the other end outside the combustion chamber (4); The combustion chamber (4) is shaped as a cylindrical cavity with a concave cavity (5), an annular cavity with concave cavities (5) on both sides, or an annular cavity with concave cavities (5) on one side; The air intake cavity (9) comprises an air channel (10) and a fuel channel (11), wherein the air channel (10) is disposed at the top end of the air intake cavity (9), and the fuel channel (11) is disposed inside the air intake cavity (9), and the fuel channel (11) is disposed at the bottom end of the air channel (10); The near-equivalence ratio combustion assembly (12) includes an air inlet (15), a fuel inlet (16), a swirler (17), a diffusion nozzle (18), a near-equivalence ratio combustion zone (19), an igniter (20) and an air inlet (21), wherein the air inlet (15) is opened at one end of the air channel (10), the fuel inlet (16) is opened at one end of the fuel channel (11), the swirler (17) is built into the air channel (10), the diffusion nozzle (18) is detachably connected to the other end inside the fuel channel (11), the near-equivalence ratio combustion zone (19) is built into the front section of the flame tube (6), the air inlet (21) is through-set on the upper side of the outer wall of one end of the front section of the flame tube (6), and the igniter (20) is detachably connected to the upper end inside the front section of the flame tube (6); The trapped vortex combustion assembly (13) includes a trapped vortex rich combustion zone (22), an igniter 2 (23), a fuel inlet 2 (24), an air inlet 3 (25), an internal air inlet (26) and a partition plate (34), wherein the trapped vortex rich combustion zone (22) is built into the concave cavity (5), the igniter 2 (23) is detachably connected to the internal top end of the concave cavity (5), the fuel inlet 2 (24) is provided on one side of the top end of the concave cavity (5), the air inlet 3 (25) is provided on one end side wall of the concave cavity (5), the partition plate (34) is provided on one side of the internal top end of the concave cavity (5), and the internal air inlet (26) is provided on the partition plate (34); The air injection type lean combustion assembly (14) includes a lean combustion zone (27), a mixing zone (28), an air inlet four (29) and a mixing structure (30), wherein the mixing zone (28) is arranged on one side of the flame tube rear section (7), the lean combustion zone (27) is arranged on the other side of the flame tube rear section (7), the mixing structure (30) is detachably connected to the top end of the flame tube rear section (7), and the air inlet four (29) is opened on the mixing structure (30); The ammonia escape prevention reduction mechanism (3) comprises a mixer (31), a fuel inlet three (32) and an air inlet five (33); the mixer (31) is provided through the lower end of the side wall at the other end of the concave cavity (5); the air inlet five (33) is provided on one side of the mixer (31); and the fuel inlet three (32) is provided at the upper end of the mixer (31).

2. The axially staged combustion chamber with a concave cavity according to claim 1, characterized in that: The air connected to the air inlet 1 (15) and the fuel connected to the fuel inlet 1 (16) adopt a combustion organization mode with a nearly equivalence ratio of 1:

1.

3. The axially staged combustion chamber with a concave cavity according to claim 1, characterized in that: The air inlet 1 (15), air inlet 2 (21), air inlet 3 (25), air inlet 4 (29) and air inlet 5 (33) are connected to an external gas source, which is air; the fuel inlet 2 (24) and fuel inlet 3 (32) are connected to an external fuel, and the fuel inlet 1 (16) is connected to an external ammonia fuel.

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