Scramjet engine combustion chamber based on S-bend structure flame stabilization

Abstract

The invention relates to a scramjet engine combustion chamber based on S-bend structure flame stabilization. The scramjet engine combustion chamber comprises an isolation section, an S-bend flame stabilizer section, an expansion section, an exhaust nozzle and a fuel nozzle arranged on the S-bend flame stabilizer section which are sequentially arranged in the incoming flow direction. The isolation section, the S-bend flame holder section, the expansion section and the exhaust nozzle are all of a hollow structure. The S-bend flame holder section comprises a first arc part and a second arc part which are sequentially connected in the incoming flow direction. The end part of the first arc part is connected with the end part of the isolation section, and the end part of the first central axis part of the first arc part is tangent to the end part of the isolation section central axis of the isolation section; the end part of the second arc part is connected with the end part of the expansion section, and the end part of the second central axis part of the second arc part is tangent to the end part of the expansion section central axis of the expansion section. The design scheme of an existing cavity flame stabilizing type scramjet engine combustion chamber is simplified, and the design of the overall structure of an engine has more choices.

Description

Technical Field

[0001] The invention relates to the field of aerospace, and in particular to a scramjet engine combustion chamber based on an S-bend structure for flame stabilization. Background Art

[0002] The combustion chamber is the core component of the ramjet engine. The combustion process of the ramjet engine combustion chamber includes ignition, flame propagation and flame stabilization. After the mixed airflow is ignited, the flame propagates to the entire main combustion zone to maintain stable combustion in the main combustion zone. However, since the incoming flow velocity of the ramjet engine is very high, much greater than the flame propagation velocity, the flame is very easy to quench, and the flame stabilization device plays a vital role at this time. The working principle of the flame stabilization device is to establish a low-speed flow zone in the high-speed flow field in the combustion chamber, so that the airflow speed is reduced in the low-speed flow zone, and the flame can always stay in the low-speed flow zone to act as a "permanent lamp" as a stable ignition source. However, the existing conventional cavity flame-stabilized scramjet engine is structurally restricted by the cavity configuration, and the overall configuration design of the engine is limited. Moreover, the existing cavity flame stabilizer has limited design solutions in terms of thermal protection and other aspects.

[0003] In existing scramjet engines, the S-bend is an important internal flow channel component, usually serving as a connecting section between the air inlet and the combustion chamber. Through its unique geometric configuration, it can effectively guide high-speed airflow into the combustion chamber and ensure stable combustion of the airflow in the combustion chamber. At present, the research on the flow in the S-bend mainly focuses on the study of secondary flow and flow separation in the tube, and the research direction is often aimed at reducing the flow loss in the tube.

[0004] In view of the similarity between the flow characteristics in the S-bend pipe and the concave cavity flame stabilization mechanism, it has the effect of achieving flame stabilization. Moreover, based on the existing research on the flow in the S-bend and the application of the concave cavity flame stabilizer, this can be achieved through the reasonable design of the S-bend configuration. Summary of the invention

[0005] The technical problem to be solved by the present invention is to provide a scramjet engine combustion chamber based on an S-bend structure for flame stabilization.

[0006] To achieve the above-mentioned invention object, the present invention provides a scramjet engine combustion chamber based on S-bend structure flame stabilization, comprising: an isolation section, an S-bend flame stabilizer section, an expansion section, and a tail nozzle arranged in sequence along the incoming flow direction, and a fuel nozzle arranged on the S-bend flame stabilizer section; The isolation section, the S-bend flame stabilizer section, the expansion section and the tail nozzle are all hollow structures; The S-bend flame-holder segment comprises: a first arc portion and a second arc portion connected in sequence along the incoming flow direction; The end of the first arc portion is connected to the end of the isolation segment, wherein the end of the first center axis portion of the first arc portion is tangent to the end of the center axis of the isolation segment of the isolation segment; The end of the second arc portion is connected to the end of the expansion section, wherein the end of the second center axis portion of the second arc portion is tangent to the end of the expansion section center axis of the expansion section.

[0007] According to one aspect of the present invention, the isolation section, the S-bend flame-holder section, the expansion section and the tail nozzle are respectively cylindrical structures with circular cross-sections or cylindrical structures with rectangular cross-sections.

[0008] According to one aspect of the present invention, along the incoming flow direction, the isolation section inlet flow channel height of the isolation section The height of the flame stabilizer inlet flow channel of the S-bend flame stabilizer section Satisfy between: .

[0009] According to one aspect of the present invention, along the incoming flow direction, the flame stabilizer inlet flow channel height of the S-bend flame stabilizer section is The height of the flame stabilizer outlet flow channel of the S-bend flame stabilizer section Satisfy between: .

[0010] According to one aspect of the present invention, the arc radius of the first central axis portion of the first arc portion and the second central axis portion arc radius of the second arc portion Satisfy between: ; The central angle of the first central axis portion of the first arc portion and the central angle of the second central axis portion of the second arc portion Satisfy between: .

[0011] According to one aspect of the present invention, the arc radius of the first central axis portion of the first arc portion The height of the flame stabilizer inlet flow channel Satisfy between: ; The central angle of the first central axis part satisfy: ; The central angle of the second central axis part satisfy: .

[0012] According to one aspect of the present invention, in the S-bend flame stabilizer segment, the radius of the circular cross-section perpendicular to the flame stabilizer center axis of the S-bend flame stabilizer segment Length to the center axis of the flame stabilizer satisfy: .

[0013] According to one aspect of the present invention, the isolation segment is a bilaterally expanded circular cross-section isolation segment, and the isolation segment expansion angle has a value range of: ;in, is the axial length of the isolation segment; The expansion section is a bilateral expansion circular cross-section expansion section, and its expansion section length Height of flame stabilizer outlet flow channel Satisfy between: ; The expansion section outlet flow channel height of the expansion section Height of flame stabilizer outlet flow channel Satisfy between: .

[0014] According to one aspect of the present invention, the first arc portion of the S-bend flame stabilizer segment is provided with a fuel spray hole for docking with the fuel nozzle; The distance between the center of the fuel injection hole and the front end of the first arc portion along the incoming flow direction is satisfy: ; In the horizontal direction, the fuel injection holes are symmetrically arranged on two opposite sides of the first arc portion, and the injection hole centers of the fuel injection holes are flush with the first central axis portion; The diameter of the fuel injection hole satisfies: ; The fuel injection hole satisfies the range of the injection flow and free flow pressure ratio between 2.3 and 5; The nozzle configuration of the fuel nozzle is a sonic nozzle, and its injection direction is arranged perpendicular to the wall surface of the first arc portion.

[0015] According to one aspect of the present invention, along the incoming flow direction, the isolation section inlet flow channel height of the isolation section The height of the flame stabilizer inlet flow channel of the S-bend flame stabilizer section Satisfy between: ; Along the incoming flow direction, the height of the flame stabilizer inlet flow channel of the S-bend flame stabilizer section is The height of the flame stabilizer outlet flow channel of the S-bend flame stabilizer section Satisfy between: ; The first central axis arc radius of the first arc portion and the second central axis portion arc radius of the second arc portion Satisfy between: ; The first central axis arc radius of the first arc portion The height of the flame stabilizer inlet flow channel Satisfy between: ; The central angle of the first central axis part satisfy: ; The central angle of the second central axis part satisfy: ; The isolation section is a bilaterally expanded circular cross-section isolation section, and the expansion angle of the isolation section is: ; The expansion section is a bilateral expansion circular cross-section expansion section, and its expansion section length Height of flame stabilizer outlet flow channel Satisfy between: ; The expansion section outlet flow channel height of the expansion section Height of flame stabilizer outlet flow channel Satisfy between: ; The fuel injection hole satisfies the requirement that the pressure ratio of the injection flow to the free flow is 3.5.

[0016] According to one solution of the present invention, a method for designing a scramjet engine combustion chamber using an S-bend structure to achieve flame stabilization is provided, further simplifying the design of the existing cavity flame-stabilizing scramjet engine combustion chamber, allowing more options for the design of the overall configuration of the engine, and providing more possibilities for the selection of engine thermal protection solutions.

[0017] According to one scheme of the present invention, a new scramjet combustion chamber design method is proposed, which appropriately enhances the flow separation phenomenon existing in the S-bend, utilizes the flow characteristics of the secondary flow, and realizes fuel mixing in the bend and flame stabilization of combustion.

[0018] According to one solution of the present invention, the present invention makes full use of the S-bend structure to achieve the effect of flame stabilization. The S-bend structure, which was originally a part of the isolation section, is moved back to the position of a traditional concave cavity flame stabilizer. The flow separation phenomenon and secondary flow phenomenon existing in the S-bend are utilized to achieve fuel mixing and subsequent flame stabilization in the recirculation zone on the upper side of the S-bend, which provides a new idea for the design of the scramjet engine combustion chamber.

[0019] According to one solution of the present invention, a scramjet engine based on the scramjet engine combustion chamber of the present invention can achieve a high-speed cruising state, so that its cruising speed reaches Mach 4-6.

[0020] According to a solution of the present invention, the creative introduction of an S-bend structure to remove the traditional concave structure combustion chamber can provide a new idea for engine design, further shorten the overall length of the combustion chamber, and provide more possibilities for the overall design of the engine. BRIEF DESCRIPTION OF THE DRAWINGS

[0021] Figure 1 A cross-sectional view of a scramjet combustion chamber according to an embodiment of the present invention; Figure 2 A cross-sectional dimension diagram of a scramjet engine combustion chamber according to an embodiment of the present invention; Figure 3 A top view of an S-bend flame holder segment according to an embodiment of the present invention; Figure 4 This is a working state diagram of a scramjet engine combustion chamber according to an embodiment of the present invention. DETAILED DESCRIPTION

[0022] In order to more clearly illustrate the embodiments of the present invention or the technical solutions in the prior art, the drawings required for use in the embodiments are briefly introduced below. Obviously, the drawings described below are only some embodiments of the present invention, and for ordinary technicians in this field, other drawings can be obtained based on these drawings without creative work.

[0023] When describing the embodiments of the present invention, the orientation or positional relationship expressed by the terms "longitudinal", "lateral", "up", "down", "front", "back", "left", "right", "vertical", "horizontal", "top", "bottom", "inside" and "outside" are based on the orientation or positional relationship shown in the relevant drawings and are only for the convenience of describing the present invention and simplifying the description, rather than indicating or implying that the referred device or element must have a specific orientation, be constructed and operate in a specific orientation. Therefore, the above terms should not be understood as limiting the present invention.

[0024] The present invention will be described in detail below in conjunction with the accompanying drawings and specific embodiments. The embodiments cannot be described one by one here, but the embodiments of the present invention are not therefore limited to the following embodiments.

[0025] Combination Figure 1 , Figure 2 and Figure 3As shown, according to one embodiment of the present invention, a scramjet engine combustion chamber based on S-bend flame stabilization of the present invention comprises: an isolation section 1, an S-bend flame stabilizer section 2, an expansion section 3, a tail nozzle 4 arranged in sequence along the incoming flow direction, and a fuel nozzle arranged on the S-bend flame stabilizer section 2; wherein the isolation section 1, the S-bend flame stabilizer section 2, the expansion section 3 and the tail nozzle 4 are all hollow structures. Accordingly, the isolation section 1, the S-bend flame stabilizer section 2, the expansion section 3 and the tail nozzle 4 all have corresponding central axes.

[0026] In this embodiment, the S-bend flame stabilizer segment 2 includes: a first arc portion 21 and a second arc portion 22 connected in sequence along the incoming flow direction; the end of the first arc portion 21 is connected to the end of the isolation segment 1, wherein the bending directions of the first arc portion 21 and the second arc portion 22 are different, thereby forming the basic shape of the S-bend flame stabilizer segment 2; further, the flame stabilizer segment center axis of the S-bend flame stabilizer segment 2 includes: a first center axis portion and a second center axis portion, wherein the first center axis portion and the second center axis portion are arc-shaped and connected in a tangential manner. In this embodiment, the end of the first center axis portion of the first arc portion 21 is tangent to the end of the isolation segment center axis of the isolation segment 1; the end of the second arc portion 22 is connected to the end of the expansion segment 3, wherein the end of the second center axis portion of the second arc portion 22 is tangent to the end of the expansion segment center axis of the expansion segment 3, thereby achieving a smooth connection between the isolation segment 1, the S-bend flame stabilizer segment 2 and the expansion segment 3.

[0027] In this embodiment, a pre-combustion shock wave train is provided in the isolation section 1 to decelerate and pressurize the incoming flow, thereby achieving pressure balance between low-pressure intake and high-pressure combustion; the S-bend flame stabilizer section 2 constitutes a combustion chamber to organize combustion, specifically through its S-shaped structure to achieve fuel mixing and flame stabilization in the S-bend, thereby achieving the effect of removing the traditional concave cavity configuration combustion chamber; the expansion section 3 connects the S-bend flame stabilizer section 2 and the tail nozzle 4, and the airflow gradually increases speed and reduces pressure; the tail nozzle 4 is connected to the outside atmosphere as an outlet.

[0028] Combination Figure 1 , Figure 2 and Figure 3 As shown, according to one embodiment of the present invention, the isolation section 1, the S-bend flame stabilizer section 2, the expansion section 3 and the tail nozzle 4 are respectively a cylindrical structure with a circular cross section or a cylindrical structure with a rectangular cross section. Of course, they can also be set as cylindrical structures with other regular cross-sectional shapes, so as to be selected based on corresponding actual needs. Thus, when a cylindrical structure with a circular cross section is adopted, the scramjet engine combustion chamber of the present invention can be matched with a corresponding circular cross-sectional engine, and when a cylindrical structure with a rectangular cross section is adopted, the scramjet engine combustion chamber of the present invention can be matched with a corresponding rectangular cross-sectional engine. In this embodiment, the isolation section 1, the S-bend flame stabilizer section 2, the expansion section 3 and the tail nozzle 4 are preferably cylindrical structures with a circular cross section.

[0029] In this embodiment, along the incoming flow direction, the isolation section inlet flow channel height of the isolation section 1 is Height of the flame stabilizer inlet flow channel of the S-bend flame stabilizer section 2 Satisfy between: Preferably, the isolation section inlet flow channel height of the isolation section 1 is Height of the flame stabilizer inlet flow channel of the S-bend flame stabilizer section 2 Set between 1.3.

[0030] In this embodiment, along the incoming flow direction, the height of the flame stabilizer inlet flow channel of the S-bend flame stabilizer section 2 is Height of flame stabilizer outlet flow channel of S-bend flame stabilizer section 2 Satisfy between: Preferably, the height of the flame stabilizer inlet flow channel of the S-bend flame stabilizer section 2 is Height of flame stabilizer outlet flow channel of S-bend flame stabilizer section 2 Set between 1.2.

[0031] Through the above-mentioned arrangement, by setting the flow channel height ratio of different connection positions within the above-mentioned range, the stable working performance of the present invention is effectively guaranteed, especially for the normal and stable operation of the S-bend flame stabilizer section 2. If the flow channel height ratio is further reduced (i.e., less than the minimum value of the above-mentioned range), it is easy to cause flow channel blockage, and if the flow channel height ratio is further expanded (i.e., greater than the maximum value of the above-mentioned range), it is easy to cause unstable combustion or the flame being blown out.

[0032] In this embodiment, in the S-bend flame stabilizer segment 2, the first central axis portion arc radius of the first arc portion 21 is and the second central axis portion arc radius of the second arc portion 22 Satisfy between: Preferably, the first arc portion 21 of the first central axis portion of the arc radius and the second central axis portion arc radius of the second arc portion 22 is set to 1; accordingly, the center angle of the first central axis portion of the first arc portion 21 and the second central axis portion center angle of the second arc portion 22 Satisfy between: Furthermore, the first arc portion 21 and the second arc portion 22 are tangentially connected to each other.

[0033] The above arrangement effectively ensures the accuracy and reliability of the basic configuration of the S-bend flame stabilizer segment 2, especially the central angle of the first central axis part. and the central angle of the second central axis part The equal relationship between them more accurately ensures the smoothness of the connection position between the first arc part 21 and the second arc part 22, avoids the formation of a bulge at the connection position, fully ensures the smooth and stable flow of the fluid, and provides a reliable guarantee for ensuring stable combustion in the S-bend flame stabilizer section 2.

[0034] In this embodiment, the first central axis arc radius of the first arc portion 21 is Height to the flame stabilizer inlet flow channel Satisfy between: Preferably, the first arc portion 21 of the first central axis portion of the arc radius Height to the flame stabilizer inlet flow channel The radius of the second central axis of the second arc portion 22 is set to 6.8. The radius of the arc in the first central axis section If it is determined, it can be based on the ratio Obtained.

[0035] In this embodiment, the central angle of the first central axis portion satisfy: Preferably, the central angle of the first central axis part The value is 20°.

[0036] In this embodiment, the central angle of the second central axis portion satisfy: Preferably, the central angle of the second central axis part The value is 20°.

[0037] Through the above arrangement, by adjusting the radius of the arc of the first central axis part Height to the flame stabilizer inlet flow channel The ratio range setting and the central angle of the first central axis part , the central angle of the second central axis The size restriction further plays a beneficial flame stabilizing function in the S-bend flame stabilizer section 2, which is more beneficial to ensuring the reliable and stable operation of the S-bend flame stabilizer section 2 of the present invention, and fully ensures the corresponding flame stabilizing function. Too small or the center angle of the first central axis , the central angle of the second central axis When it is too large, it will easily lead to blockage of the flow channel, otherwise the internal flame will be unstable.

[0038] In this embodiment, in the S-bend flame stabilizer segment 2, the radius of the circular cross section perpendicular to the flame stabilizer center axis of the S-bend flame stabilizer segment 2 is Length to the center axis of the flame stabilizer satisfy: ; Among them, the length of the center axis of the flame stabilizer It refers to the extension length of the central axis along the S shape.

[0039] In addition, it should be noted that when the S-bend flame stabilizer segment 2 adopts a rectangular cross-section cylindrical structure, the circular cross-section radius involved in the above formula is The value is the vertical distance between the upper or lower wall of the cross-section (i.e. the upper edge or lower edge of the cross-section) and the central axis.

[0040] Therefore, the radius of the circular cross section perpendicular to the center axis of the flame stabilizer of the S-bend flame stabilizer segment 2 is The length of the flame stabilizer centerline Uniformly changing, and then, when the flame stabilizer inlet flow channel height , flame stabilizer outlet flow channel height , the radius of the arc of the first central axis , the radius of the arc of the second central axis , the central angle of the first central axis , the central angle of the second central axis After being determined, the radius of the circular section Length to the center axis of the flame stabilizer The rate of change between them is a constant.

[0041] Through the above arrangement, the smooth transition of the internal wall connection is effectively guaranteed, and the sudden change on the wall is fully eliminated.

[0042] Combination Figure 1 , Figure 2 and Figure 3 As shown, according to one embodiment of the present invention, the isolation segment 1 is a bilaterally expanded circular cross-section isolation segment, and the isolation segment expansion angle has a value range of: ;in, is the axial length of the isolation segment 1; preferably, the isolation segment expansion angle of the isolation segment 1 is 1.3°; further, the expansion segment 3 is a bilateral expansion circular cross-section expansion segment, and its expansion segment length Height of flame stabilizer outlet flow channel Satisfy between: Preferably, the expansion section length of the expansion section 3 is Height of flame stabilizer outlet flow channel Between The value of is 2.5; further, the expansion section outlet flow channel height of the expansion section 3 Height of flame stabilizer outlet flow channel Satisfy between: Preferably, the expansion section outlet flow channel height of the expansion section 3 is Height of flame stabilizer outlet flow channel Between The value of is 1.2.

[0043] Through the above arrangement, the expansion degree of the isolation section 1 and the expansion section 3 is fully limited, and the matching of the structural dimensions with the S-bend flame stabilizer section 2 is achieved, which is more beneficial to ensure the stability and reliability of the present invention. If the above ratio range is too narrow, it will cause internal blockage, and if the above ratio range is too expanded, it will make it difficult to stabilize the flame inside.

[0044] Combination Figure 1 , Figure 2 and Figure 3 As shown, according to one embodiment of the present invention, the first arc portion 21 of the S-bend flame stabilizer segment 2 is provided with a fuel nozzle 211 for docking with the fuel nozzle; wherein, along the incoming flow direction, the distance between the nozzle center of the fuel nozzle 211 and the front end of the first arc portion 21 is satisfy: In the present embodiment, the fuel nozzle 211 is a circular hole and a liquid hydrogen nozzle, and the number thereof is preferably 2. Furthermore, along the horizontal direction, the fuel nozzle 211 is symmetrically arranged on opposite sides of the first arc portion 21, and the nozzle center of the fuel nozzle 211 is flush with the first central axis portion.

[0045] In this embodiment, the diameter of the fuel injection hole 211 satisfies: .

[0046] In this embodiment, the fuel injection hole 211 satisfies that the pressure ratio of the injection flow to the free flow is in the range of 2.3 to 5; preferably, the fuel injection hole 211 satisfies that the pressure ratio of the injection flow to the free flow is 3.5.

[0047] In this embodiment, the nozzle configuration of the fuel nozzle is a sonic nozzle, and its injection direction is arranged perpendicular to the wall surface of the first arc portion 21 , so that the fuel nozzle is arranged perpendicular to the axial direction of the first arc portion 21 .

[0048] Through the above arrangement, the position of the fuel injection hole 211 is restricted to This is to ensure that the fuel injection hole 211 is located in the first arc portion 21, so as to fully ensure that the flame stabilization area is mainly located on the upper side of the second arc portion 22, so as to ensure the stability of the flame stabilization area; if the fuel injection hole 211 is too far back, it is easy to cause the flame to be pushed forward, which seriously affects the position stability of the flame stabilization area and the mixed combustion efficiency in the S-bend flame stabilizer section 2. In addition, by further limiting the diameter of the fuel injection hole 211 and the pressure ratio of the injection flow to the free flow, it can be further ensured that no excessive flow loss will be generated under the condition of sufficient fuel penetration depth, and the mixed combustion efficiency of the present invention is further effectively guaranteed; if the pressure ratio of the injection flow to the free flow is too small, the injection will have a serious impact of insufficient depth; if the pressure ratio of the injection flow to the free flow is too large, the disturbance to the incoming flow is too large, and a large total pressure loss of the incoming flow will be generated, which is also not conducive to the reliable operation of the S-bend flame stabilizer section 2.

[0049] Based on the above configuration, the scramjet engine operating state using the scramjet engine combustion chamber of the present invention is as follows: Figure 4 As shown in FIG. 1 , the supersonic incoming flow decelerated by the inlet duct enters from the entrance of the isolation section 1, and the fuel injection hole 211 in the S-bend flame stabilizer section 2 injects fuel to achieve sufficient mixing of the fuel in the recirculation zone on the upper side of the S-bend flame stabilizer section 2. The main recirculation zone is located on the upper side of the second arc portion 22 of the S-bend flame stabilizer section 2. After ignition, the main recirculation zone is used to achieve flame stabilization. The flame stabilization area is as shown in FIG. Figure 4 As indicated by the markings.

[0050] The above contents are merely examples of specific solutions of the present invention. For devices and structures not described in detail therein, it should be understood that they can be implemented by adopting general devices and general methods available in the art.

[0051] The above is only one solution of the present invention and is not intended to limit the present invention. For those skilled in the art, the present invention may have various modifications and variations. Any modification, equivalent replacement, improvement, etc. made within the spirit and principle of the present invention shall be included in the protection scope of the present invention.

Claims

1. A scramjet combustion chamber based on S-bend flame stabilization, characterized in that: include: An isolation section (1), an S-bend flame stabilizer section (2), an expansion section (3), and a tail nozzle (4) are sequentially arranged along the incoming flow direction, and a fuel nozzle is arranged on the S-bend flame stabilizer section (2); The isolation section (1), the S-bend flame stabilizer section (2), the expansion section (3) and the tail nozzle (4) are all hollow structures; The S-bend flame stabilizer segment (2) comprises: a first arc portion (21) and a second arc portion (22) which are sequentially connected along the incoming flow direction; The end of the first arc portion (21) is connected to the end of the isolation segment (1), wherein the end of the first central axis portion of the first arc portion (21) is tangent to the end of the isolation segment central axis of the isolation segment (1); The end of the second circular arc portion (22) is connected to the end of the expansion section (3), wherein the end of the second central axis portion of the second circular arc portion (22) is tangent to the end of the expansion section central axis of the expansion section (3).

2. The scramjet engine combustion chamber based on S-bend flame stabilization according to claim 1 is characterized in that: The isolation section (1), the S-bend flame stabilizer section (2), the expansion section (3) and the tail nozzle (4) are respectively cylindrical structures with a circular cross-section or cylindrical structures with a rectangular cross-section.

3. The scramjet engine combustion chamber based on S-bend flame stabilization according to claim 2 is characterized in that: Along the incoming flow direction, the isolation section inlet flow channel height of the isolation section (1) is The height of the flame stabilizer inlet flow channel of the S-bend flame stabilizer section (2) Satisfy between: .

4. The scramjet engine combustion chamber based on S-bend flame stabilization according to claim 3 is characterized in that: Along the incoming flow direction, the height of the flame stabilizer inlet flow channel of the S-bend flame stabilizer section (2) is The height of the flame stabilizer outlet flow channel of the S-bend flame stabilizer section (2) Satisfy between: .

5. The scramjet engine combustion chamber based on S-bend flame stabilization according to claim 4 is characterized in that: The first central axis portion arc radius of the first arc portion (21) and the arc radius of the second central axis portion of the second arc portion (22) Satisfy between: ; The center angle of the first central axis portion of the first arc portion (21) and the central angle of the second central axis portion of the second arc portion (22) Satisfy between: .

6. The scramjet engine combustion chamber based on S-bend flame stabilization according to claim 5 is characterized in that: The first central axis portion arc radius of the first arc portion (21) The height of the flame stabilizer inlet flow channel Satisfy between: ; The central angle of the first central axis part satisfy: ; The central angle of the second central axis part satisfy: .

7. The scramjet engine combustion chamber based on S-bend flame stabilization according to claim 6 is characterized in that: In the S-bend flame stabilizer section (2), the radius of the circular cross-section perpendicular to the flame stabilizer center axis of the S-bend flame stabilizer section (2) Length to the center axis of the flame stabilizer satisfy: 。 8. The scramjet engine combustion chamber based on S-bend flame stabilization according to claim 7 is characterized in that: The isolation segment (1) is a bilaterally expanded circular cross-section isolation segment, and the expansion angle of the isolation segment has a value range of: ;in, is the axial length of the isolation section (1); The expansion section (3) is a double-sided expansion circular cross-section expansion section, and its expansion section length Height of flame stabilizer outlet flow channel Satisfy between: ; The expansion section outlet flow channel height of the expansion section (3) Height of flame stabilizer outlet flow channel Satisfy between: .

9. The scramjet engine combustion chamber based on S-bend flame stabilization according to claim 8, characterized in that: The first arc portion (21) of the S-bend flame stabilizer segment (2) is provided with a fuel spray hole (211) for docking with the fuel nozzle; Along the incoming flow direction, the distance between the center of the fuel injection hole (211) and the front end of the first arc portion (21) is satisfy: ; In the horizontal direction, the fuel injection holes (211) are symmetrically arranged on two opposite sides of the first arc portion (21), and the injection hole centers of the fuel injection holes (211) are flush with the first central axis portion; The diameter of the fuel injection hole (211) satisfies: ; The fuel injection hole (211) satisfies a pressure ratio of the injection flow to the free flow in a range of 2.3 to 5; The nozzle configuration of the fuel nozzle is a sonic nozzle, and its injection direction is arranged perpendicular to the wall surface of the first arc portion (21).

10. The scramjet engine combustion chamber based on S-bend flame stabilization according to claim 9, characterized in that: Along the incoming flow direction, the isolation section inlet flow channel height of the isolation section (1) is The height of the flame stabilizer inlet flow channel of the S-bend flame stabilizer section (2) Satisfy between: ; Along the incoming flow direction, the height of the flame stabilizer inlet flow channel of the S-bend flame stabilizer section (2) is The height of the flame stabilizer outlet flow channel of the S-bend flame stabilizer section (2) Satisfy between: ; The first central axis portion arc radius of the first arc portion (21) and the arc radius of the second central axis portion of the second arc portion (22) Satisfy between: ; The first central axis portion arc radius of the first arc portion (21) The height of the flame stabilizer inlet flow channel Satisfy between: ; The central angle of the first central axis part satisfy: ; The central angle of the second central axis part satisfy: ; The isolation section (1) is a bilaterally expanded circular cross-section isolation section, and the expansion angle of the isolation section is: ; The expansion section (3) is a double-sided expansion circular cross-section expansion section, and its expansion section length Height of flame stabilizer outlet flow channel Satisfy between: ; The expansion section outlet flow channel height of the expansion section (3) Height of flame stabilizer outlet flow channel Satisfy between: ; The fuel injection hole (211) satisfies a pressure ratio of injection flow to free flow of 3.5.

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