Rich-burn - Quench - Lean-burn aeroengine combustor

Abstract

The present invention provides a rich-burn-quench-lean-burn aeroengine combustor, comprising: an outer-ring flame tube, one end of which is provided with a head; a plurality of quench slots, circumferentially and evenly distributed along the outer-ring flame tube, and the cross-sectional shape of each quench slot along the radial direction of the outer-ring flame tube is a rectangular structure; a plurality of mixing holes, circumferentially and evenly distributed along the outer-ring flame tube, and the plurality of mixing holes are arranged at one end of the outer-ring flame tube far away from the head; a plurality of intermediate air intake channels, arranged between the quench slots and the mixing holes, and the plurality of intermediate air intake channels are circumferentially and evenly distributed along the outer-ring flame tube. By arranging the quench slots, rapid quenching of high-temperature gas in the main combustion zone of a conventional main combustor can be realized, thereby reducing NOx emissions, and the configuration of the main combustion chamber flame tube does not need to be greatly modified.

Description

Technical Field

[0001] This specification relates to the technical field of aeroengines, and particularly to a rich burn - quick quench - lean burn aeroengine combustor. Background Art

[0002] Air transportation is a major source of harmful emissions in the air, such as nitrogen oxides (NOx), greenhouse gas carbon dioxide (CO2), and water (H2O), and aeroengines are the only source of these pollutants. Therefore, reducing the pollution emissions of aeroengines has been one of the important driving forces for the development of aeroengine technology in recent years. Low - emission combustion technology is a technology that can directly reduce pollution emissions from the source. Currently, there are mainly two approaches: lean - burn technology and rich - burn technology. The rich burn - quick quench - lean burn (RQL) technology in rich - burn technology can effectively reduce pollution emissions, and at the same time, it can also achieve high - reliable ignition - off performance and combustion stability of the aeroengine combustor. Conventional rich burn - quick quench - lean burn (RQL) combustors adopt the layout form of main combustion holes and mixing holes of conventional main combustors. The profiles of the inner and outer ring flame tubes are convergent along the way, so as to form rich - burn combustion in the main combustion zone, the convergent profile forms rapid quenching, and lean - burn combustion is carried out downstream. Summary of the Invention

[0003] In view of this, embodiments of this specification provide a rich burn - quick quench - lean burn aeroengine combustor to achieve the purpose of reducing pollution emissions.

[0004] The technical solution of the present invention is as follows: A rich burn - quick quench - lean burn aeroengine combustor includes: an outer - ring flame tube with a head at one end; a plurality of quenching slits evenly spaced circumferentially along the outer - ring flame tube, and the cross - sectional shape of each quenching slit along the radial direction of the outer - ring flame tube is a rectangular structure; a plurality of mixing holes evenly spaced circumferentially along the outer - ring flame tube, and the plurality of mixing holes are arranged at the end of the outer - ring flame tube far from the head; a plurality of intermediate air intake channels arranged between the quenching slits and the mixing holes, and the plurality of intermediate air intake channels are evenly spaced circumferentially along the outer - ring flame tube.

[0005] Further, the positions of the plurality of quenching slits, the plurality of intermediate air intake channels, and the plurality of mixing holes correspond one by one.

[0006] Further, the effective flow area of each quenching slit is ACd_s = B * h * Cd, where B is the length of the quenching slit, h is the width of the quenching slit, Cd is the air flow coefficient of the quenching slit, and ACd_s is the effective flow area of each quenching slit.

[0007] Further, the effective flow area of all quenching slits is ACd = n * ACd_s, where n is the number of quenching slits, and ACd is the effective flow area of all quenching slits.

[0008] Further, the intake air volume W of all the quenching slots is W = ACd * √(2 * ρ * ΔP) 0.5 , where ρ is the intake air density of the quenching slot, ΔP is the pressure drop of the combustor liner, and W is the intake air volume of all the quenching slots.

[0009] Further, the number of quenching slots and the number of heads satisfy: n = a * N; where a is a coefficient, 0.5 ≤ a ≤ 3, and N is the number of heads.

[0010] Further, the distance between the quenching slot and the head outlet is Ld; where Ld = b * Hd, Hd is the height of the head outlet, b is a coefficient, and 0.4 ≤ b ≤ 0.6.

[0011] Further, the shape of the intermediate intake air passage includes a slit shape and a round hole shape.

[0012] Further, a plurality of intermediate intake air passages located in the same circumferential plane form an intake air passage group, and a plurality of intake air passage groups are arranged between the quenching slots and the mixing holes.

[0013] Compared with the prior art, the beneficial effects that can be achieved by at least one of the above technical solutions adopted in the embodiments of the present specification at least include: by providing the quenching slots, rapid quenching of the high-temperature combustion gas in the main combustion zone of the conventional main combustor can be realized, thereby reducing the NOx emissions, and no significant modification is required for the configuration of the main combustor liner. Description of the Drawings

[0014] In order to more clearly illustrate the technical solutions of the embodiments of the present application, the drawings required to be used in the embodiments will be briefly introduced below. Obviously, the drawings in the following description are only some embodiments of the present application. For those of ordinary skill in the art, other drawings can be obtained based on these drawings without creative efforts.

[0015] Figure 1 It is a schematic diagram of the quenching slot and the slit penetration jet of the main combustor in the embodiment of the present invention;

[0016] Figure 2 It is a layout schematic diagram of the slit-shaped intermediate intake air passage;

[0017] Figure 3 It is a layout schematic diagram of the round hole-shaped intermediate intake air passage.

[0018] Reference numerals in the drawings: 14, outer ring combustor liner; 15, head; 22, quenching slot; 23, intermediate intake air passage; 25, mixing hole. Detailed Embodiments

[0019] The embodiments of the present application will be described in detail below with reference to the drawings.

[0020] The following describes the implementation manners of the present application through specific examples. Those skilled in the art can easily understand other advantages and effects of the present application from the content disclosed in this specification. Obviously, the described embodiments are only a part of the embodiments of the present application, rather than all the embodiments. The present application can also be implemented or applied through other different specific implementation manners. Various details in this specification can also be modified or changed based on different viewpoints and applications without departing from the spirit of the present application. It should be noted that, without conflict, the following embodiments and the features in the embodiments can be combined with each other. All other embodiments obtained by those of ordinary skill in the art based on the embodiments in the present application without creative efforts belong to the scope protected by the present application.

[0021] As Figures 1 to 3 shown, an embodiment of the present invention provides a rich-burn-quench-lean-burn aeroengine combustor, which includes an outer-ring flame tube 14, a plurality of quench slots 22, a plurality of mixing holes 25, and a plurality of intermediate air intake channels 23. One end of the outer-ring flame tube 14 is provided with a head 15; the plurality of quench slots 22 are circumferentially and evenly distributed along the outer-ring flame tube 14, and the cross-sectional shape of each quench slot 22 along the radial direction of the outer-ring flame tube 14 is a rectangular structure; the plurality of mixing holes 25 are circumferentially and evenly distributed along the outer-ring flame tube 14, and the plurality of mixing holes 25 are arranged at one end of the outer-ring flame tube 14 away from the head 15; the plurality of intermediate air intake channels 23 are arranged between the quench slots 22 and the mixing holes 25, and the plurality of intermediate air intake channels 23 are circumferentially and evenly distributed along the outer-ring flame tube 14.

[0022] By arranging the quench slots 22, rapid quenching of the high-temperature gas in the main combustion zone of the conventional main combustor can be realized, thereby reducing NOx emissions, and no major modification is required for the configuration of the main combustion chamber flame tube.

[0023] The positions of the plurality of quench slots 22, the plurality of intermediate air intake channels 23, and the plurality of mixing holes 25 correspond one by one. By adopting the above arrangement manner in the present invention, the jet flow of the quench slot 22 can penetrate the main combustion zone as much as possible and block the main combustion zone. A flow-through area with a width of H is formed between the jet flows of the inner and outer ring flame tubes. The main combustion zone is a rich fuel combustion zone, in which the high-temperature gas quickly passes through the flow-through area with a width of H. The jet flow quenches the flame in the main combustion zone and performs lean fuel combustion downstream, realizing a rich-burn-quench-lean-burn combustion mode.

[0024] The quench slot 22 in the embodiment of the present invention can be rectangular, or can be a long strip or a runway shape with rounded corners.

[0025] Certainly, in one embodiment, the plurality of intermediate air intake channels 23 located in the same circumferential plane form an air intake channel group, and a plurality of air intake channel groups are arranged between the quench slots 22 and the mixing holes 25. That is, as Figure 2As shown, a ring of intermediate air inlet channels 23 forms an air inlet channel group, a plurality of quenching slits 22 also form a ring of quenching slit groups on the circumference, and a plurality of mixing holes 25 also form a ring of mixing hole groups. Among them, a plurality of air inlet channel groups are arranged between the mixing hole group and the quenching slit group, and along Figure 2 the axial direction shown, each unit in sequence is a quenching slit 22, a plurality of intermediate air inlet channels 23, and mixing holes 25.

[0026] The effective flow area of each quenching slit 22 is ACd_s = B * h * Cd, where B is the length of the quenching slit 22, h is the width of the quenching slit 22, Cd is the air flow coefficient of the quenching slit 22, and ACd_s is the effective flow area of each quenching slit 22.

[0027] Furthermore, the effective flow area of all the quenching slits 22 is ACd = n * ACd_s, where n is the number of quenching slits 22, and ACd is the effective flow area of all the quenching slits 22. Then the air intake volume W of all the quenching slits 22 = ACd * (2 * ρ * ΔP) 0.5 , where ρ is the intake air density of the quenching slit 22, ΔP is the pressure drop of the combustion chamber liner, and W is the air intake volume of all the quenching slits 22.

[0028] Preferably, in the embodiment of the present invention, the number of quenching slits 22 and the number of heads 15 satisfy: n = a * N; where a is a coefficient, 0.5 ≤ a ≤ 3, and N is the number of heads 15. The distance between the quenching slit 22 and the outlet of the head 15 is Ld; where Ld = b * Hd, Hd is the height of the outlet of the head 15, and b is a coefficient, and 0.4 ≤ b ≤ 0.6.

[0029] In one embodiment, the intermediate air inlet channel 23 is in a slit shape, and the number of intermediate air inlet channels 23 is 1 to 3 times the number of quenching slits 22.

[0030] In Figure 3 the embodiment shown, the shape of the intermediate air inlet channel 23 is a round hole shape. A plurality of groups of round hole-shaped intermediate air inlet channels 23 are arranged downstream of the quenching slit 22. The distance between adjacent two groups of round hole-shaped intermediate air inlet channels 23 is S, and the diameter of the round hole-shaped intermediate air inlet channel 23 is D, where S / D ≥ 2.5.

[0031] Furthermore, in the embodiment of the present invention, the number of mixing holes 25 is 1 to 2 times the number of heads 15 of the combustion chamber liner.

[0032] In an embodiment not shown, the above-mentioned quenching slits 22 are provided on both the outer ring combustion chamber liner and the inner ring combustion chamber liner, and the setting manner of the quenching slits 22 is the same as that in the above-mentioned embodiment, and details are not described herein again.

[0033] As described above, it is only the specific implementation manner of the present application, but the protection scope of the present application is not limited thereto. Any changes or substitutions that can be easily thought of by those skilled in the art within the technical scope disclosed in the present application should be covered within the protection scope of the present application. Therefore, the protection scope of the present application shall be subject to the protection scope of the claims.

Claims

1. A rich-burn - quench - lean-burn aeroengine combustor, characterized in that, Comprising: An outer ring flame tube (14) with a head (15) provided at one end; A plurality of quenching slits (22), evenly distributed at circumferential intervals along the outer ring flame tube (14), and the cross-sectional shape of each quenching slit (22) along the radial direction of the outer ring flame tube (14) is a rectangular structure; A plurality of mixing holes (25), evenly distributed at circumferential intervals along the outer ring flame tube (14), and the plurality of mixing holes (25) are provided at one end of the outer ring flame tube (14) away from the head (15); A plurality of intermediate air inlet channels (23), provided between the quenching slits (22) and the mixing holes (25), and the plurality of intermediate air inlet channels (23) are evenly distributed at circumferential intervals along the outer ring flame tube (14); The axial positions of the plurality of quenching slits (22), the plurality of intermediate air inlet channels (23), and the plurality of mixing holes (25) correspond one by one; The configuration of the tube wall at the quenching slit is the same as that of the main combustion zone tube wall; The number of quenching slits (22) and the number of heads (15) satisfy: n = a * N; where a is a coefficient, 0.5 ≤ a ≤ 3, and N is the number of heads (15); The distance between the quenching slit (22) and the outlet of the head (15) is Ld; where Ld = b * Hd, Hd is the height of the outlet of the head (15), b is a coefficient, and 0.4 ≤ b ≤ 0.

6.

2. The rich-burn - quench - lean-burn aeroengine combustor according to claim 1, wherein The effective flow area of each quenching slit (22) is ACd_s = B * h * Cd, where B is the length of the quenching slit (22), h is the width of the quenching slit (22), Cd is the air flow coefficient of the quenching slit (22), and ACd_s is the effective flow area of each quenching slit (22).

3. The rich-burn - quench - lean-burn aeroengine combustor according to claim 2, characterized in that, The effective flow area of all the quenching slits (22) is ACd = n * ACd_s, where n is the number of quenching slits (22), and ACd is the effective flow area of all the quenching slits (22).

4. The rich-burn - quench - lean-burn aeroengine combustor according to claim 3, wherein The intake air volume W of all the quenching slots (22) = ACd * (2 * ρ * ΔP) 0.5 , where ρ is the intake air density of the quenching slot (22), ΔP is the pressure drop of the combustion chamber liner, and W is the intake air volume of all the quenching slots (22).

5. The rich-burn - quench - lean-burn aeroengine combustor according to claim 1, characterized in that, The shape of the intermediate air inlet channel (23) includes a slit shape and a round hole shape.

6. The rich-burn - quench - lean-burn aeroengine combustor according to claim 1, wherein A plurality of intermediate air inlet channels (23) located in the same circumferential plane form an air inlet channel group, and a plurality of the air inlet channel groups are provided between the quenching slits (22) and the mixing holes (25).

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