A strut-type supersonic combustor coupled with a wall-swept nozzle

Abstract

The present invention discloses a strut-type supersonic combustor coupled with wall-swept nozzles, relating to the technical field of scramjet engines. The combustor comprises a central strut and multiple wall-swept nozzles. One end of the combustor body serves as an air inlet, and the other end serves as an air outlet. The central strut is fixedly mounted within the combustor body and is provided with multiple fuel injection holes for injecting fuel into the combustor body. Multiple sweep nozzles are circumferentially arranged on the inner wall of the combustor body, each sweep nozzle being configured to sweep fuel into the combustor body. The strut-type supersonic combustor coupled with wall-swept nozzles provided by the present invention enhances fuel diffusion and mixing, thereby improving combustion efficiency.

Description

Technical Field

[0001] The present invention relates to the technical field of scramjet engines, and in particular to a support plate type supersonic combustion chamber coupled with a wall swept nozzle. Background Art

[0002] Scramjets, characterized by their low mass, simple structure, and high specific impulse at high Mach numbers, are hailed as the third revolution in aviation after propellers and jet propulsion. Under high-speed flight conditions, air velocity in a scramjet's combustion chamber can reach kilometers per second, while the fuel's residence time in the chamber is mere milliseconds, complicating fuel mixing and combustion. To ensure rapid fuel mixing and combustion during this short residence time, improving the fuel-air mixing efficiency in the supersonic combustion chamber is essential.

[0003] Currently, the mainstream combustion stabilization scheme in scramjet combustion chambers mainly includes center support plate combustion stabilization. As an efficient and reliable flame stabilizer, the center support plate has been used in various scramjet engine combustion chambers. The support plate can inject fuel in the center area of ​​the mainstream, effectively increasing the utilization rate of the mainstream air; however, the fuel injection range on the center support plate is limited, and the fuel mixing efficiency is still low. Summary of the Invention

[0004] The purpose of the present invention is to provide a support plate type supersonic combustion chamber coupled with a wall swept nozzle to solve the problems existing in the above-mentioned prior art, enhance the diffusion and mixing of fuel, and thus improve the combustion efficiency.

[0005] To achieve the above object, the present invention provides the following solutions:

[0006] The present invention provides a support plate type supersonic combustion chamber coupled with a wall-swept nozzle, comprising a combustion chamber body, a central support plate and a plurality of sweep nozzles; one end of the combustion chamber body is an air inlet end, and the other end is an air outlet end; the central support plate is fixedly arranged in the combustion chamber body, and the central support plate is provided with a plurality of fuel spray holes for injecting fuel into the combustion chamber body; a plurality of sweep nozzles are circumferentially arranged on the inner wall of the combustion chamber body, and each of the sweep nozzles is used to sweep and inject fuel into the combustion chamber body.

[0007] Preferably, the central support plate is arranged in the combustion chamber body along the air flow direction, and the front end of the central support plate close to the air inlet end is set as a tapered end, and the plurality of fuel injection holes are arranged on both sides of the tapered end.

[0008] Preferably, the plurality of fuel injection holes on both sides of the tapered end are symmetrically arranged.

[0009] Preferably, each of the sweeping nozzles is configured as a self-excited sweeping nozzle.

[0010] Preferably, the combustion chamber body includes an isolation section, an expansion section and an equal straight section that are connected in sequence along the air flow direction, one end of the isolation section is the air inlet end, and one end of the equal straight section is the air outlet end; the central support plate is fixedly arranged on the bottom wall of the isolation section; and the plurality of sweep nozzles are fixedly arranged on the top wall and side wall of the expansion section along the circumferential direction.

[0011] Preferably, one side end of the central support plate facing away from the air inlet end is flush with one side end of the isolation section facing away from the air inlet end.

[0012] Preferably, a plurality of the sweep nozzles are fixedly arranged along the circumferential direction on the inner wall of the side end of the expansion section away from the isolation section, and the sweep nozzles on the opposite side walls of the expansion section are symmetrically arranged.

[0013] Preferably, it further comprises an air inlet and a nozzle respectively connected to the air inlet end and the air outlet end, wherein the air inlet is used for introducing gas and the nozzle is used for exhausting gas.

[0014] Preferably, the cross-sectional size of the air inlet duct gradually decreases along the airflow direction.

[0015] Preferably, the cross-sectional size of the nozzle increases along the airflow direction.

[0016] Compared with the prior art, the present invention has achieved the following technical effects:

[0017] The support plate type supersonic combustion chamber coupled with the wall-surface swept nozzle provided by the present invention has a central support plate and multiple swept nozzles arranged in the combustion chamber body. Multiple fuel nozzle holes are arranged on the central support plate to spray fuel into the combustion chamber body. In conjunction with the multiple swept nozzles arranged circumferentially, the fuel is swept and sprayed from the wall, thereby increasing the fuel penetration depth in the combustion chamber body and improving the mixing efficiency of the fuel, thereby improving the combustion efficiency. BRIEF DESCRIPTION OF THE DRAWINGS

[0018] In order to more clearly illustrate the embodiments of the present invention or the technical solutions in the prior art, the following briefly introduces the drawings required for use in the embodiments. Obviously, the drawings described below are only some embodiments of the present invention. For ordinary technicians in this field, other drawings can be obtained based on these drawings without paying any creative work.

[0019] Figure 1 A front view of a support plate type supersonic combustion chamber coupled with a wall-swept nozzle provided in Example 1;

[0020] Figure 2 A top view of a support plate type supersonic combustion chamber coupled with a wall-swept nozzle provided in Example 1;

[0021] Figure 3A side view of a support plate type supersonic combustion chamber coupled with a wall-swept nozzle provided in Example 1.

[0022] In the figure: 1-bracket-type supersonic combustor coupled with a swept nozzle; 10-combustion chamber body; 11-isolating section; 12-expanding section; 13-straight section; 20-center support plate; 21-conical end; 22-fuel nozzle hole; 30-swept nozzle; 40-inlet duct; 50-nozzle. DETAILED DESCRIPTION

[0023] The following will clearly and completely describe the technical solutions in the embodiments of the present invention in conjunction with the accompanying drawings. Obviously, the described embodiments are only part of the embodiments of the present invention, not all of the embodiments. Based on the embodiments of the present invention, all other embodiments obtained by ordinary technicians in this field without making creative efforts are within the scope of protection of the present invention.

[0024] The purpose of the present invention is to provide a support plate type supersonic combustion chamber coupled with a wall swept nozzle to solve the problems existing in the above-mentioned prior art, enhance the diffusion and mixing of fuel, and thus improve the combustion efficiency.

[0025] In order to make the above-mentioned objects, features and advantages of the present invention more obvious and easy to understand, the present invention is further described in detail below with reference to the accompanying drawings and specific embodiments.

[0026] Example 1

[0027] This embodiment provides a support plate type supersonic combustion chamber 1 coupled with a swept nozzle, see Figure 1-Figure 3 , including a combustion chamber body 10, a central support plate 20 and a plurality of sweep nozzles 30; one end of the combustion chamber body 10 is an air inlet end, and the other end is an air outlet end; the central support plate 20 is fixedly arranged in the combustion chamber body 10, and the central support plate 20 is provided with a plurality of fuel nozzles 22 for injecting fuel into the combustion chamber body 10; a plurality of sweep nozzles 30 are circumferentially arranged on the inner wall of the combustion chamber body 10, and each sweep nozzle 30 is used to sweep and inject fuel into the combustion chamber body 10.

[0028] A central support plate 20 and a plurality of sweep nozzles 30 are provided in the combustion chamber body 10. A plurality of fuel nozzle holes 22 are provided on the central support plate 20 to spray fuel into the combustion chamber body 10. In conjunction with the plurality of sweep nozzles 30 arranged circumferentially, the fuel is swept and sprayed from the wall surface, thereby increasing the fuel penetration depth in the combustion chamber body 10 and improving the mixing efficiency of the fuel, thereby improving the combustion efficiency.

[0029] The fuel injection holes 22 of the center support plate 20 and the sweep nozzles 30 are connected to an external fuel supply.

[0030] Among the optional solutions of this embodiment, it is more preferred to refer to Figure 2 The center support plate 20 is arranged in the combustion chamber body 10 along the air flow direction, and the front end of the center support plate 20 close to the air intake end is set as a tapered end 21, and multiple fuel injection holes 22 are set on both sides of the tapered end 21; by setting the front end as the tapered end 21, the air resistance is reduced, and the fuel injection holes 22 are set on the side of the tapered end 21 to facilitate the mixing of fuel and air.

[0031] In an optional solution of this embodiment, it is more preferred that the multiple fuel injection holes 22 on both sides of the tapered end 21 are symmetrically arranged to ensure uniform mixing on both sides of the central support plate 20.

[0032] In the optional scheme of this embodiment, it is more preferred that the sweep nozzles 30 are all configured as sweep nozzles. The structure of the sweep nozzle adopts the existing self-excited sweep nozzle for scramjet engines, which has a main cavity and a feedback reflux channel. Reflux bubbles are generated in the main cavity, so that the fluid flows along the inner wall of the main cavity and is ejected in a certain direction at the outlet of the sweep nozzle, and oscillates periodically with a frequency of 1000 to 1600 Hz. The reflux channel is located on both sides of the main cavity, connected to the main cavity and at a certain angle. The flow channel width is 0.5 to 1 mm, which can meet the injection requirements under supersonic combustion conditions; compared with the traditional direct-injection sweep nozzle on the wall, the sweep nozzle allows the fuel to have a larger sweep area, so that the fuel can fill the combustion chamber, can minimize the number of sweep nozzles, increase the fuel penetration depth, and enhance the fuel mixing efficiency and atomization performance.

[0033] Further preferably, the sweep nozzle fuel sweep angle is 30 to 90 degrees, and the number and distribution position are determined according to the size of the combustion chamber body 10, so that the injection ranges of adjacent sweep nozzles are connected in the circumferential direction to achieve full sweep of the top wall and side walls.

[0034] In the optional scheme of this embodiment, it is more preferred that the combustion chamber body 10 includes an isolation section 11, an expansion section 12 and an equal straight section 13 connected in sequence along the airflow direction, one end of the isolation section 11 is the air inlet end, and one end of the equal straight section 13 is the air outlet end; the central support plate 20 is fixedly arranged on the bottom wall of the isolation section 11; multiple sweep nozzles 30 are fixedly arranged on the top wall and side wall of the expansion section 12 along the circumferential direction; wherein, the isolation section 11 is used to resist the non-start phenomenon induced by the back pressure generated by combustion in the combustion chamber to ensure the stable operation of the front air inlet 40; the expansion section 12 plays a role in resisting back pressure inside the combustion chamber to ensure a stable combustion process; the equal straight section 13 will generate a thermal throat in the subsonic mode, accelerating the subsonic airflow to a supersonic state; wherein the expansion ratio of the expansion section 12 can be 1.6, that is, the rear end cross-sectional area is 1.6 times the front end cross-sectional area; the specific size of the combustion chamber body 10 can be determined according to actual needs.

[0035] In an alternative embodiment of this embodiment, it is preferred that the end of the center support plate 20 facing away from the air inlet end is flush with the end of the isolation section 11 facing away from the air inlet end. The center support plate is positioned in this manner relative to the wall-swept nozzle, allowing the fuel to fill the entire combustion chamber, enhancing fuel mixing and improving combustion efficiency.

[0036] In the optional scheme of this embodiment, it is more preferred that multiple sweeping nozzles 30 are fixedly arranged along the circumferential direction on the inner wall of the side end of the expansion section 12 away from the isolation section 11, and the sweeping nozzles 30 on the opposite side walls of the expansion section 12 are symmetrically arranged to improve the uniformity of mixing.

[0037] Among the optional solutions of this embodiment, it is more preferred that the support plate type supersonic combustion chamber 1 coupled with the swept nozzle provided in this embodiment also includes an air inlet 40 and a nozzle 50 respectively connected to the air inlet end and the air outlet end. The air inlet 40 is provided to facilitate the introduction of gas, and the nozzle 50 is provided to facilitate the ejection of exhaust gas.

[0038] In the optional solution of this embodiment, it is more preferred that the cross-sectional size of the air inlet duct 40 gradually decreases along the airflow direction.

[0039] In an optional solution of this embodiment, it is more preferred that the cross-sectional size of the nozzle 50 increases along the airflow direction, wherein the expansion ratio of the nozzle 50 may be 1.3, that is, the cross-sectional area of ​​the rear end is 1.3 times the cross-sectional area of ​​the front end.

[0040] The present invention uses specific examples to illustrate the principles and implementation methods of the present invention. The above examples are only intended to help understand the method and core concept of the present invention. At the same time, those skilled in the art will find that the specific implementation methods and application scopes may vary based on the concept of the present invention. In summary, the contents of this specification should not be construed as limiting the present invention.

Claims

1. A strut-type supersonic combustor coupled with a swept nozzle, characterized by: include: A combustion chamber body (10), wherein the combustion chamber body (10) comprises an isolation section (11), an expansion section (12), and a straight section (13) that are sequentially connected along the airflow direction, one end of the isolation section (11) being an air inlet end, and one end of the straight section (13) being an air outlet end; a central support plate (20), the central support plate (20) being fixedly arranged on the bottom wall of the isolation section (11); a plurality of fuel injection holes (22) for injecting fuel into the combustion chamber body (10) being arranged on the central support plate (20); the central support plate (20) being arranged in the combustion chamber body (10) along the airflow direction, and a front end of the central support plate (20) close to the air inlet end being arranged as a tapered end (21); the plurality of fuel injection holes (22) being arranged on both sides of the tapered end (21); and the plurality of fuel injection holes (22) on both sides of the tapered end (21) being symmetrically arranged; and A plurality of sweep nozzles (30) are fixedly arranged along the circumferential direction on the inner wall of the side end of the expansion section (12) away from the isolation section (11), and the sweep nozzles (30) on the opposite side walls of the expansion section (12) are symmetrically arranged; each sweep nozzle (30) is used to sweep and spray fuel into the combustion chamber body (10).

2. The strut-type supersonic combustor coupled with a swept nozzle according to claim 1, characterized in that: The sweeping nozzles (30) are all configured as sweeping nozzles.

3. The strut-type supersonic combustor coupled with a swept nozzle according to claim 1, characterized in that: One side end of the central support plate (20) facing away from the air inlet end is flush with one side end of the isolation section (11) facing away from the air inlet end.

4. The strut-type supersonic combustor coupled with a swept nozzle according to claim 1, characterized in that: It also includes an air inlet (40) and a nozzle (50) respectively connected to the air inlet end and the air outlet end. The air inlet (40) is used to introduce gas, and the nozzle (50) is used to discharge gas.

5. The strut-type supersonic combustor coupled with a swept nozzle according to claim 4, characterized in that: The cross-sectional size of the air inlet duct (40) gradually decreases along the airflow direction.

6. The strut-type supersonic combustor coupled with a swept nozzle according to claim 4, characterized in that: The cross-sectional dimension of the nozzle (50) increases along the airflow direction.

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