Corrugated wall shock generator for enhanced combustion and flame stabilization

Abstract

The invention relates to a corrugated wall shock wave generator for combustion stabilization and flame enhancement, comprising an isolation section and a concave cavity section, wherein the isolation section has an expansion tendency toward the concave cavity section; the isolation section also serves as a fuel injection section, and a shock wave generator is arranged on the fuel injection section, the shock wave generator being a corrugated wall structure, wherein a convex corrugated wall is arranged upstream of the fuel injection section, which can compress incoming air, increase air static temperature and pressure, and enhance turbulent pulsation and mixing efficiency; a deformed corrugated wall is arranged downstream of the fuel injection section; the deformed corrugated wall switches between a concave corrugated wall and a convex corrugated wall according to different incoming flow conditions; when the incoming flow condition is a low Mach number, the deformed corrugated wall is a convex corrugated wall, so as to compress the incoming flow and increase the pressure; when the incoming flow condition is a high Mach number, the deformed corrugated wall switches to a concave corrugated wall, so as to increase mixing while avoiding a large total pressure loss, thereby being able to meet the performance improvement of the engine under different incoming flow conditions.

Description

Technical Field

[0001] The invention relates to the technical field of engines, and in particular to a corrugated wall shock wave generator with enhanced combustion and flame stabilization. Background Art

[0002] In the field of aerospace, ramjet engines, as key power devices, are of great significance to the flight of aircraft. Under high Mach number inflow conditions, conventional ramjet engines are prone to flame flashback or flameout risks, which will seriously affect the stable operation and performance of the engine. Under low Mach number inflow conditions, ramjet engines are prone to excessive back pressure in the combustion chamber when working, resulting in the inlet duct not starting and the engine not being able to work normally.

[0003] As a device that can generate strong oblique shock waves in the flow channel of the engine, the shock wave generator has unique advantages. Through a simple geometric form, it can effectively compress the incoming air, significantly increase the static temperature and static pressure of the air, and create more favorable conditions for engine combustion.

[0004] However, the shock wave generator will bring certain resistance and pressure loss during operation. How to improve the combustion efficiency and enhance the combustion performance of the engine under controllable resistance and loss through reasonable design has become a problem to be solved. Summary of the invention

[0005] Based on this, it is necessary to provide a corrugated wall shock wave generator with combustion stabilization and flame enhancement that can improve the combustion stability of scramjet engines and increase combustion efficiency under different incoming flow conditions in order to address the above technical problems.

[0006] A corrugated wall shock wave generator for combustion stabilization and flame enhancement comprises an isolation section and a concave cavity section, wherein the isolation section has an expansion tendency toward the concave cavity section; the isolation section also serves as a fuel injection section, and a shock wave generator is arranged on the fuel injection section, wherein the shock wave generator is a corrugated wall structure, wherein a convex corrugated wall is arranged upstream of the fuel injection section, and a deformed corrugated wall is arranged downstream of the fuel injection section; the deformed corrugated wall switches between a concave corrugated wall and a convex corrugated wall according to different incoming flow conditions; when the incoming flow condition is low Mach number, the deformed corrugated wall is a convex corrugated wall to compress the incoming flow and increase the pressure; when the incoming flow condition is high Mach number, the deformed corrugated wall switches to a concave corrugated wall to increase mixing while avoiding a large total pressure loss.

[0007] In one embodiment, the overall length of the corrugated wall is 1 / 6 to 1 / 4 of the height of the inlet flow channel of the isolation section.

[0008] In one embodiment, the corrugated wall includes more than two arc segments.

[0009] In one embodiment, the arc segments are connected by circular arcs, and the circular arcs are tangent to the arc segments adjacent to each other on both sides.

[0010] In one embodiment, the angle of the arc is 20° to 40°.

[0011] In one embodiment, the height of the arc segment satisfies:

[0012] ;

[0013] In the formula, Indicates the axial distance The height of the place; Indicates the maximum vertical distance of a single arc segment; Indicates the total length of a single arc segment in straight-line distance; Indicates the axial distance from the starting point at a certain point.

[0014] In one of the embodiments, the shock wave generator disposed on the fuel injection section has an arc section in its corrugated wall structure closest to the fuel injection hole and a distance from the fuel injection hole of 1 / 20 to 1 / 10 of the height of the isolation section inlet flow channel.

[0015] In one of the embodiments, the corrugated wall is made of high entropy shape memory alloy.

[0016] In one embodiment, in the fuel injection section, the distance between the fuel injection hole and the front edge of the concave cavity section is l jet for: 1 / 3d 1 <l jet <2 / 3d 1; among them, d 1 is the height of the inlet flow channel of the isolation section.

[0017] In one embodiment, the height of the trailing edge flow channel of the concave cavity section is d 4 and the height of the inlet flow channel of the isolation section d The ratio of 1 is: 1.25≤ d 4 / d 1≤1.50.

[0018] The above-mentioned corrugated wall shock generator with enhanced combustion flame stabilization includes an isolation section and a concave cavity section, and the isolation section tends to expand toward the concave cavity section; the isolation section also serves as a fuel injection section, and a shock generator is arranged on the fuel injection section, and the shock generator is a corrugated wall structure, wherein a convex corrugated wall is arranged upstream of the fuel injection section, which can compress the incoming air, increase the static temperature and pressure of the air, and enhance the turbulent pulsation and mixing efficiency; a deformed corrugated wall is arranged downstream of the fuel injection section; the deformed corrugated wall switches between a concave corrugated wall and a convex corrugated wall according to different incoming flow conditions; when the incoming flow condition is low Mach number, the deformed corrugated wall is a convex corrugated wall to achieve compression of the incoming flow and increase the pressure; when the incoming flow condition is high Mach number, the deformed corrugated wall switches to a concave corrugated wall to achieve increased mixing while avoiding a large total pressure loss, thereby being able to meet the performance improvement of the engine under different incoming flow conditions. BRIEF DESCRIPTION OF THE DRAWINGS

[0019] 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 or the description of the prior art will be briefly introduced below. 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 the structures shown in these drawings without paying creative work.

[0020] Figure 1 A cross-sectional schematic diagram of an engine combustion chamber in which a corrugated wall shock wave generator is installed in one embodiment;

[0021] Figure 2 A schematic diagram of the dimensions of an engine combustion chamber in which a corrugated wall shock wave generator is installed in one embodiment;

[0022] Figure 3 A schematic diagram of the structure of a raised corrugated wall in one embodiment;

[0023] Figure 4 A schematic diagram of the interaction between the shock wave and the fuel jet formed under the condition of high Mach number incoming flow in one embodiment;

[0024] Figure 5 A schematic diagram of the interaction between the shock wave and the fuel jet formed under the condition of low Mach number incoming flow in one embodiment;

[0025] Description of reference numerals:

[0026] Isolation section 1, concave cavity section 2, straight throat section 3, expansion section 4, convex corrugated wall 51, deformed corrugated wall 52, arc section 53.

[0027] The purpose, features and advantages of the present invention will be further described with reference to the accompanying drawings in conjunction with the embodiments. DETAILED DESCRIPTION

[0028] The following will be combined with the drawings in the embodiments of the present invention to clearly and completely describe the technical solutions in the embodiments of the present invention. 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 creative work are within the scope of protection of the present invention.

[0029] It should be noted that all directional indications (such as up, down, left, right, front, back, etc.) in the embodiments of the present invention are only used to explain the relative position relationship, movement status, etc. between the components under a certain specific posture (as shown in the accompanying drawings). If the specific posture changes, the directional indication will also change accordingly.

[0030] In the present invention, unless otherwise clearly specified and limited, the terms "connection", "fixation", etc. should be understood in a broad sense. For example, "fixation" can be a fixed connection, a detachable connection, or an integral connection; it can be a mechanical connection, an electrical connection, a physical connection, or a wireless communication connection; it can be a direct connection, or an indirect connection through an intermediate medium, or it can be the internal connection of two elements or the interaction relationship between two elements, unless otherwise clearly defined. For ordinary technicians in this field, the specific meanings of the above terms in the present invention can be understood according to specific circumstances.

[0031] It can be understood that the technical solutions between the various embodiments of the present invention can be combined with each other, but it must be based on the fact that ordinary technicians in the field can implement it. When the combination of technical solutions is contradictory or cannot be implemented, it should be deemed that such combination of technical solutions does not exist and is not within the scope of protection required by the present invention.

[0032] The following will describe the implementation of the present invention in detail with reference to the accompanying drawings in the embodiment diagram of the present invention.

[0033] This embodiment discloses a corrugated wall shock wave generator with enhanced combustion flame stabilization, which solves the technical problem that the combustion instability of the existing ramjet engine combustion chamber is enhanced under high Mach number incoming flow conditions, while the anti-back pressure ability is insufficient under low Mach number. Different corrugated wall configurations, distribution methods and fuel injection schemes are adopted for different incoming flow Mach numbers. A convex corrugated wall 51 is adopted upstream of the injection to compress the incoming air, increase the static temperature and pressure of the air, and enhance the turbulent pulsation and mixing efficiency. Downstream of the injection, a deformed corrugated wall 52 is prepared by using a high entropy shape memory alloy, so as to realize the active deformation of the corrugated wall according to different incoming flow conditions. Under high Mach number incoming flow conditions, it can be deformed into a concave corrugated wall, while increasing mixing and avoiding a large total pressure loss; under low Mach number incoming flow conditions, it can be deformed into a convex corrugated wall, thereby further compressing the incoming flow to increase the pressure and playing a role in anti-back pressure. The present invention can take into account the flame stabilization performance of the engine under high Mach number conditions and the anti-back pressure ability under low Mach number conditions.

[0034] like Figures 1 to 3 As shown, the corrugated wall shock wave generator with enhanced combustion and flame stabilization provided by this embodiment is mainly used in ramjet engines and scramjet engines. The engine configuration can be a rectangular cross section or an axisymmetric circular cross section. In the combustion chamber of the rectangular cross section engine, the concave cavity section 2 is arranged symmetrically on the upper and lower walls; in the combustion chamber of the axisymmetric circular cross section engine, the concave cavity section 2 is a ring structure.

[0035] Figure 1 A cross-sectional schematic diagram of the engine combustion chamber is given. The engine combustion chamber is divided into four parts from upstream to downstream, namely, the isolation section 1, the concave cavity section 2, the straight throat section 3, and the expansion section 4. Among them, the isolation section 1 also serves as the fuel injection section, which has an expansion trend toward the concave cavity section; fuel injection holes and shock wave generators are arranged on the wall of the isolation section 1 (i.e., the fuel injection section). A concave cavity flame stabilizer is provided on the concave cavity section 2, which is mainly used for ramjet combustion organization within a certain range of flight Mach numbers (Ma6-8); the straight throat section 3 is used to connect the concave cavity section 2 and the expansion section 4, and is used to gradually increase the speed and reduce the pressure of the airflow; the expansion section 4 connects the combustion chamber with the outside atmosphere.

[0036] The shock wave generator is a corrugated wall structure, including a convex corrugated wall 51 and a deformed corrugated wall 52. Among them, the convex corrugated wall 51 is set upstream of the fuel injection section, which can compress the incoming air, increase the static temperature and pressure of the air, and enhance the turbulent pulsation and mixing efficiency; the deformed corrugated wall 52 is set downstream of the fuel injection section; the deformed corrugated wall 52 switches between the concave corrugated wall and the convex corrugated wall according to different incoming flow conditions; when it is a low Mach number incoming flow condition, the deformed corrugated wall is a convex corrugated wall to achieve compression of the incoming flow to increase the pressure and play a role in resisting back pressure; when it is a high Mach number incoming flow condition, the deformed corrugated wall switches to a concave corrugated wall, while achieving increased mixing, avoiding a large total pressure loss, so as to meet the performance improvement of the engine under different incoming flow conditions.

[0037] Specifically, this embodiment takes the high Mach number inflow condition as an example and gives the following Figure 1 and Figure 2 The schematic diagram of the design of the scheme with a convex corrugated wall 51 at the upstream and a concave corrugated wall at the downstream is shown; under high Mach number incoming flow conditions, the shock wave train formed by the convex corrugated wall 51 at the upstream and the reflow zone of the concave corrugated wall at the downstream are used to promote fuel mixing. Correspondingly, if the incoming flow condition is low Mach number, the concave corrugated wall at the downstream is deformed into a convex corrugated wall.

[0038] The parameter design of the isolation section 1 and fuel injection section is as follows: Figure 2 As shown, l 1 is the length of isolation segment 1, l 2 is the length of the concave cavity section 2, l 3 is the length of the straight throat section 3, l 4 is the length of the expansion section 4, d 1 is the height of the inlet flow channel of isolation section 1, d 2 is the outlet flow channel height of isolation section 1, d 3 is the height of the flow channel in the middle of the concave cavity section 2, d 4 is the flow channel height of the straight throat section 3, d 5 is the height of the outlet flow channel of expansion section 4, α is the inclination angle of the rear wall of cavity section 2, l jet1 、l jet2 is the distance between the center of the two groups of fuel injection holes and the front edge of the cavity (the arrows represent the position and injection direction of the fuel injection holes), l s1 、l s2 is the distance between the two ends of the upstream convex corrugated wall 51 of the fuel injection hole and the front edge of the concave cavity section 2, l s3 、l s4 It is the distance from the front edge of the cavity to the two ends of the deformed corrugated wall 52 downstream of the fuel injection hole.

[0039] At the cruising state of Mach number 6-8, the height of the trailing edge flow channel of the concave cavity section 2 is d 4 Height of the inlet flow channel of the isolation section d The ratio of 1 is: 1.25≤ d 4 / d 1≤1.50, preferably 1.33. The length-to-depth ratio of the concave cavity section 2 is in the range of 6<( d 3 -d 2) / ( 2l 3) <8, preferably 7, the inclination angle of the rear wall of the concave cavity section 2 α is 45°.

[0040] On the isolation section 1, the expansion angle range of the double-sided expansion inclined wall is 3.0°< arctan((d 2 -d 1 ) / (2l 1 )) <4.8°, preferably 4.2°. The distance between the fuel injection hole and the front edge of the cavity section l jet for: 1 / 3d 1 <l jet <2 / 3d 1. In this embodiment, two groups of fuel injection holes are provided, and the positions of the two groups of fuel injection holes should meet 1 / 3d 1 <l jet1 <l jet2 < 2 / 3d 1. The distance between two sets of fuel injection holes l jet2 ~l jet1 Preferably 1 / 5d 1. The fuel injection holes are preferably round holes and ethylene injection holes. The number of injection holes is preferably 8. All fuel injection holes are preferably evenly distributed along the radial direction. The diameter of a single fuel injection hole is preferably d jet ≤4mm. The nozzle configuration of all fuel injection holes is preferably a sonic nozzle, which is arranged perpendicular to the axial direction at 90°.

[0041] like Figure 3 FIG. 1 is a schematic diagram of the structure of the convex corrugated wall 51 provided in this embodiment. The convex corrugated wall 51 includes more than two arc segments 53. In this embodiment, three arc segments 53 are shown, wherein: is the total length of a single arc segment in straight-line distance, θ is the arc angle at the connection of the arc segment 53, Ris the arc radius at the connection of the arc segment 53, h The axial distance It can be seen that the arc segments 53 in the raised corrugated wall 51 protrude from the wall surface, and the arc segments 53 are connected by arcs, and the arcs are tangent to the arc segments 53 adjacent to each other on both sides.

[0042] The downstream deformed corrugated wall 52 is made of high entropy shape memory alloy. By taking temperature as an active input signal and utilizing the transformation of high entropy shape memory alloy between martensite and austenite, the active deformation of the inner wall surface of the isolation section 1 is realized, thereby realizing the switching between the convex corrugated wall and the concave corrugated wall. When the downstream deformed corrugated wall 52 is a convex corrugated wall, its structure, position and size parameters are the same as those of the upstream convex corrugated wall 51; when the downstream deformed corrugated wall 52 is a concave corrugated wall, its structure is opposite to that of the convex corrugated wall, and its position and size parameters are the same. Therefore, in this embodiment, only the parameters of the upstream convex corrugated wall 51 are described, and the downstream deformed corrugated wall 52 can be designed accordingly, which will not be repeated here.

[0043] The convex corrugated wall 51 is located upstream of the fuel injection hole, and the distance between the arc section 53 of the convex corrugated wall 51 closest to the fuel injection hole and the fuel injection hole is 1 / 20 to 1 / 10 of the height of the inlet flow channel of the isolation section. d 1. In this embodiment, since two groups of fuel injection holes are provided, the distance between the arc segment 53 closest to the fuel injection hole and the fuel injection hole should satisfy: 1 / 20d 1 <l s3 ~l jet2 <1 / 10d 1, preferably 1 / 12d 1. The overall length of the raised corrugated wall 51 is 1 / 6 to 1 / 4 of the height of the inlet flow channel of the isolation section, expressed as 1 / 6d 1 <l s4 ~l s3 <1 / 4d 1. The height of the arc segment 53 satisfies:

[0044] ;

[0045] In the formula, Indicates the axial distance The height of the place; Indicates the maximum vertical distance of a single arc segment; Indicates the total length of a single arc segment in straight-line distance; Indicates the axial distance from the starting point at a certain point.

[0046] In this embodiment, since the upstream convex corrugated wall 51 includes three arc segments 53, the total length of a single arc segment in a straight line distance is l 0= 1 / 3 ( l s4 -l s3 ), the maximum vertical distance of a single arc segment The height of the flow channel at any point in the isolation section 1 should be greater than the height of the flow channel at the isolation section entrance. d 1, preferably 1 / 5l 0. The angle of the arc connecting the two arc segments 53 is 20° to 40°, preferably 30°, and the arc is tangent to the arc segments 53 on both sides. After the parameters of the arc segment 53 and the arc angle are determined according to the geometric relationship, the radius of the arc R It can also be determined that, based on this, the complete size parameters and setting position of the raised corrugated wall 51 are obtained.

[0047] like Figure 4 As shown, when the incoming flow enters the isolation section 1, the upstream convex corrugated wall 5 generates a compression bow shock wave, thereby decelerating and increasing the pressure, and at the same time, the shock wave intersects and reflects at the center of the flow channel.

[0048] The fuel is ejected from the nozzle at a speed u jet After ejection, it is distributed on the spanwise plane perpendicular to the center trace direction, and the formula of the center trace is:

[0049] y / d jet =c 1( x / d jet ) c2 J c3 ;

[0050] The formula is based on the nozzle center as the origin and the mainstream direction as the x The positive direction of the axis and the injection direction are y In the coordinate system of the positive direction of the axis; J is the fuel / air momentum ratio: J= ( ρ jet u 2 jet ) / ( ρ air u 2 air ),in ρ jet is the fuel density, ρair and u air is the density and velocity of incoming air; the empirical constant in the formula is c 1 = 1.6, c 2 = 1 / 3, c 3 = 1 / 3.

[0051] The reflected shock wave interacts with the fuel jet, and the larger mixing area provided by the concave corrugated wall further promotes the mixing of the fuel. At this time, the airflow generates extremely high pressure after passing through the compression shock wave, and enters the concave cavity for combustion after being fully mixed with the fuel injection jet, greatly reducing the risk of flame flashback and blowout, enhancing stability and improving combustion efficiency.

[0052] When the corrugated wall shock wave generator designed by the present invention is used in a cruising state with a Mach number of 4-6, the downstream deformed corrugated wall 52 is switched from a concave corrugated wall to a convex corrugated wall, which can further enhance fuel mixing. Figure 5 As shown, the injection distance l jet1 、l jet2 and the downstream corrugation wall distance l s3 、l s4 The shock wave generated by the injection and the shock wave generated by the rear raised corrugated wall intersect at the entrance of the cavity, so that the pressure in the shock wave intersection area is significantly increased, which not only promotes the pressure increase in the combustion chamber, but also has the effect of resisting back pressure.

[0053] The corrugated wall shock wave generator for combustion stabilization and flame enhancement described in the present invention can work in the scramjet combustion chamber of two ramjet combustion modes, namely, sub-combustion and scramjet combustion. The upstream convex corrugated wall 51 is used to generate shock waves to enhance the flame stabilization in the cavity, and the downstream deformed corrugated wall 52 is deformed and switched according to the situation. When it is a concave corrugated wall, it can provide a larger mixing area, which is equivalent to increasing the fuel injection depth and taking into account the low-loss drag reduction effect; when it is a convex corrugated wall, in addition to further promoting fuel mixing, it can also play a role in resisting back pressure. Based on this, the required corrugated wall configuration can be reasonably arranged according to the specific flight conditions.

[0054] When the incoming flow Mach number is large, the bow shock wave intensity in front of the fuel injection hole is high, and the interaction effect between the reflected shock wave and the fuel jet is stronger, which has a stronger mixing and combustion-supporting effect, effectively reducing the risk of flame extinguishing; when the incoming flow Mach number is small, the shock wave intensity is low, and the deceleration and pressurization effect on the mainstream is weak. At the same time, the convex corrugated wall downstream is used to resist the back pressure, reducing the risk of the intake duct not starting due to the forward push of the back pressure. Under the premise that the flow resistance and total pressure loss do not increase significantly, the present invention can effectively improve the flame stabilization performance of the engine combustion chamber, improve the combustion efficiency, and take into account the least resistance and total pressure loss as much as possible.

[0055] The technical features of the above embodiments may be combined arbitrarily. To make the description concise, not all possible combinations of the technical features in the above embodiments are described. However, as long as there is no contradiction in the combination of these technical features, they should be considered to be within the scope of this specification.

[0056] The above-mentioned embodiments only express several implementation modes of the present invention, and the description thereof is relatively specific and detailed, but it cannot be understood as limiting the scope of the invention. It should be pointed out that, for a person of ordinary skill in the art, several modifications and improvements can be made without departing from the concept of the present invention, and these all belong to the protection scope of the present invention. Therefore, the protection scope of the present invention shall be subject to the attached claims.

Claims

1. A corrugated wall shock wave generator with enhanced combustion and flame stabilization, comprising an isolation section and a concave cavity section, characterized in that: The isolation section has an expansion trend toward the concave cavity section; The isolation section also serves as a fuel injection section, and a shock wave generator is arranged on the fuel injection section. The shock wave generator is a corrugated wall structure, wherein a convex corrugated wall is arranged upstream of the fuel injection section, and a deformed corrugated wall is arranged downstream of the fuel injection section; The deformed corrugated wall switches between a concave corrugated wall and a convex corrugated wall according to different incoming flow conditions; when the incoming flow condition is low Mach number, the deformed corrugated wall is a convex corrugated wall to achieve compressing the incoming flow to increase the pressure; when the incoming flow condition is high Mach number, the deformed corrugated wall switches to a concave corrugated wall to achieve increased mixing while avoiding a large total pressure loss.

2. The ripple wall shock wave generator with combustion stabilization and flame enhancement according to claim 1 is characterized in that: The overall length of the corrugated wall is 1 / 6 to 1 / 4 of the height of the inlet flow channel of the isolation section.

3. The ripple wall shock wave generator with combustion stabilization and flame enhancement according to claim 2 is characterized in that: The corrugated wall includes more than two arc segments.

4. The ripple wall shock wave generator with combustion stabilization and flame enhancement according to claim 3 is characterized in that: The arc segments are connected by circular arcs, and the circular arcs are tangent to the arc segments adjacent to each other on both sides.

5. The ripple wall shock wave generator with combustion stabilization and flame enhancement according to claim 4, characterized in that: The angle of the arc is 20° to 40°.

6. The ripple wall shock wave generator with enhanced combustion and flame stabilization according to claim 3, characterized in that: The height of the arc segment satisfies: ； In the formula, Indicates the axial distance The height of the place; Indicates the maximum vertical distance of a single arc segment; Indicates the total length of a single arc segment in straight-line distance; Indicates the axial distance from the starting point at a certain point.

7. The ripple wall shock wave generator with enhanced combustion and flame stabilization according to any one of claims 1 to 6, characterized in that: The shock wave generator disposed on the fuel injection section has an arc section in its corrugated wall structure that is closest to the fuel injection hole and a distance from the fuel injection hole of 1 / 20 to 1 / 10 of the height of the isolation section inlet flow channel.

8. The ripple wall shock wave generator with enhanced combustion and flame stabilization according to any one of claims 1 to 6, characterized in that: The corrugated wall is made of high entropy shape memory alloy.

9. The corrugated wall shock wave generator with enhanced combustion and flame stabilization according to any one of claims 1 to 6, characterized in that: In the fuel injection section, the distance between the fuel injection hole and the front edge of the concave cavity section is l jet for: 1 / 3d 1 <l jet <2 / 3d 1; among them, d 1 is the height of the inlet flow channel of the isolation section.

10. The corrugated wall shock wave generator with enhanced combustion and flame stabilization according to any one of claims 1 to 6, characterized in that: The trailing edge flow channel height of the concave cavity section d 4 and the height of the inlet flow channel of the isolation section d The ratio of 1 is: 1.25≤ d 4 / d 1≤1.50.

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