A scramjet combustor with adjustable injection area

Abstract

The application discloses a scramjet engine combustion chamber with adjustable injection area and relates to the technical field of scramjet engines.The scramjet engine combustion chamber with adjustable injection area comprises an auxiliary air pipe channel and a fuel nozzle, the middle part of a first outer pipe is provided with the auxiliary air pipe channel, support blocks are integrally arranged on the two sides of the auxiliary air pipe channel, the inner end of the auxiliary air pipe channel is provided with an adjusting assembly for the flow direction of auxiliary air flow, and the adjusting assembly comprises a fixed disc, a servo motor, a first flow guide plate and a second flow guide plate. The scramjet engine combustion chamber with adjustable injection area can make full use of oxygen in the atmosphere without carrying a large amount of oxidant when flying at a high speed. When oxygen enters the auxiliary air pipe channel, the design of the adjusting assembly can break and decompose foreign matters, which is convenient for quickly eliminating the foreign matters when igniting by the fuel nozzle in the subsequent process, and can also avoid the influence of the foreign matters on the ignition of the fuel nozzle when the air flow circulates, thereby maintaining the stability of ignition.

Description

Technical Field

[0001] The present invention relates to the technical field of scramjet engines, and in particular to a scramjet engine combustion chamber with adjustable injection area. Background Art

[0002] Cavity flameholders are currently widely used in scramjet engine combustors. Supersonic airflow through the cavity creates a recirculation zone within the cavity, which allows the flame to remain stationary and serve as a new source of ignition for upstream fuel, thus achieving flame stability. The cavity combines fuel injection, mixing enhancement, and flame stabilization in a supersonic combustor, playing a vital role in improving scramjet engine performance.

[0003] Currently, the scramjet combustion chamber controls the flame injection area by changing the direction of the airflow. When the airflow direction changes, it brings greater energy, resulting in unstable ignition.

[0004] Therefore, in view of this, the existing structure and deficiencies are studied and improved, and a scramjet engine combustion chamber with adjustable injection area is proposed. Summary of the Invention

[0005] In view of the shortcomings of the prior art, the present invention provides a scramjet engine combustion chamber with adjustable injection area, which solves the problems raised in the above background technology.

[0006] To achieve the above objectives, the present invention is implemented through the following technical solutions: a scramjet engine combustion chamber with adjustable injection area, comprising an auxiliary air duct channel and a fuel nozzle, an auxiliary air duct channel is provided in the middle of the first outer tube, and support blocks are integrally installed on both sides of the auxiliary air duct channel, an internal end of the auxiliary air duct channel is provided with an adjustment component for assisting the airflow direction, and the adjustment component includes a fixed disk, a servo motor, a first guide plate and a second guide plate, a servo motor is provided on the outer surface of the fixed disk, and two groups of servo motors are provided, the output end of one group of servo motors is connected to the first guide plate through a drive shaft, and the output end of the other group of servo motors is connected to the second guide plate through a drive shaft, a compressor is provided in the middle of one end of the auxiliary air duct channel, and the fuel nozzles are provided on both sides of the compressor.

[0007] Furthermore, an adjustment component for controlling the air flow rate is provided at one end of the auxiliary airway channel away from the adjustment component, and two groups of the adjustment components are provided.

[0008] Furthermore, the adjustment component includes a cylinder, an adjustment guide plate and a built-in groove, and the cylinder is arranged inside the built-in groove, and the adjustment guide plate is installed at the output end of the cylinder.

[0009] Furthermore, the shape and structure of the adjustment guide plate are consistent with the shape and structure of the auxiliary tracheal channel, and the auxiliary tracheal channel forms an integrated structure with the auxiliary tracheal channel through the support block.

[0010] Furthermore, a fourth outer tube is provided on the right side of the first outer tube, and a second outer tube is installed on the right side of the fourth outer tube, and an inner cover is provided on one side of the outer wall of the second outer tube.

[0011] Furthermore, a third outer tube is provided on the right side of the second outer tube, and the cross section of the third outer tube is a trapezoidal structure.

[0012] Furthermore, a protection component for protecting the third outer tube is provided inside the third outer tube, and six groups of the protection components are arranged in a ring shape around the middle of the third outer tube.

[0013] Furthermore, the protective assembly includes an internal spring and a protective plate, and the outer surface of the internal spring is provided with a protective plate.

[0014] Furthermore, two groups of support blocks are provided, and the outer surfaces of the two groups of support blocks are both installed with transition components for blocking foreign objects.

[0015] Furthermore, the transition component includes a blade, a fixed ring and a stabilizing block, and the blade is provided inside the fixed ring, and the stabilizing block is annularly installed on the outer surface of the fixed ring.

[0016] The present invention provides a scramjet engine combustion chamber with adjustable injection area, which has the following beneficial effects:

[0017] 1. This scramjet engine combustor with adjustable injection area can control the positions of the first and second guide plates through the design of an adjustment component, thereby directing the bottom airflow to the compressor and maintaining the flow of airflow above the compressor. Another set of servo motors and a drive shaft can drive the second guide plate to rotate. Rotation of the second guide plate can divert airflow from the upper layer of the compressor downward. The airflow direction guidance design can control the range of the injection area. Two sets of servo motors are provided, respectively controlling the first and second guide plates. This allows the first and second guide plates to follow each other when the airflow direction changes, thereby avoiding the large energy generated by the airflow changing direction and maintaining stable fuel nozzle ignition.

[0018] 2. The scramjet engine combustion chamber with adjustable injection area, when flying at high speed, uses the air intake at the front of the engine to introduce atmospheric air into the engine, which is then compressed. Inside the engine, liquid fuel is injected into the high-pressure, high-temperature compressed air. During injection, the third outer tube is protected by the design of the protective component, reducing damage to the third outer tube.

[0019] 3. The scramjet engine combustion chamber with adjustable injection area can fully utilize the oxygen in the atmosphere during high-speed flight without carrying a large amount of oxidizer. When oxygen enters the auxiliary air duct, the design of the transition component can crush and decompose foreign matter, making it easy to quickly eliminate it during subsequent ignition using the fuel nozzle. It can also prevent foreign matter from affecting the ignition of the fuel nozzle during airflow, thereby maintaining ignition stability. BRIEF DESCRIPTION OF THE DRAWINGS

[0020] Figure 1 This is a partial cross-sectional structural diagram of a scramjet engine combustion chamber with adjustable injection area according to the present invention;

[0021] Figure 2 This is a schematic diagram of the external structure of a scramjet engine combustion chamber with adjustable injection area according to the present invention;

[0022] Figure 3 This is a schematic diagram of a half-section structure of a scramjet engine combustion chamber with adjustable injection area according to the present invention;

[0023] Figure 4 This is a schematic diagram of the connection structure of the second guide plate of a scramjet engine combustion chamber with adjustable injection area according to the present invention;

[0024] Figure 5 This is a schematic diagram of the three-dimensional structure of the third outer tube of a scramjet engine combustion chamber with adjustable injection area according to the present invention.

[0025] In the figure: 1. Auxiliary air pipe channel; 2. Adjustment component; 201. Cylinder; 202. Adjustment guide plate; 203. Built-in groove; 3. First outer tube; 4. Support block; 5. Compressor; 6. Fuel nozzle; 7. Second outer tube; 8. Third outer tube; 9. Fourth outer tube; 10. Inner cover; 11. Auxiliary groove; 12. Transition component; 1201. Blade; 1202. Fixed ring; 1203. Stabilizing block; 13. Adjustment component; 1301. Fixed disk; 1302. Servo motor; 1303. First guide plate; 1304. Second guide plate; 14. Protection component; 1401. Built-in spring; 1402. Protection plate. DETAILED DESCRIPTION

[0026] The following embodiments of the present invention are described in further detail with reference to the accompanying drawings and examples. The following examples are used to illustrate the present invention but are not intended to limit the scope of the present invention.

[0027] like Figure 1 、 Figure 2 、 Figure 4 Figure 5As shown, the present invention provides a technical solution: a scramjet engine combustion chamber with adjustable injection area, comprising an auxiliary air pipe channel 1, an adjustment component 2, a cylinder 201, an adjustment guide plate 202, a built-in groove 203, a first outer tube 3, a support block 4, a compressor 5, a fuel nozzle 6, a second outer tube 7, a third outer tube 8, a fourth outer tube 9, an inner cover 10, an auxiliary groove 11, a transition component 12, a blade 1201, a fixing ring 1202, a stabilizing block 1203, an adjustment component 13, a fixing plate 1301, a servo motor 1302, a first guide plate 1303, a second guide plate 1304, a protective component 14, a built-in spring 1401 and a protective plate 1402, an auxiliary air pipe channel 1 is provided in the middle of the first outer tube 3, and the ... Support blocks 4 are integrally installed on both sides of the auxiliary air pipe channel 1, a fourth outer tube 9 is provided on the right side of the first outer tube 3, and a second outer tube 7 is installed on the right side of the fourth outer tube 9, an inner cover 10 is provided on one side of the outer wall of the second outer tube 7, a third outer tube 8 is provided on the right side of the second outer tube 7, and the cross-section of the third outer tube 8 is a trapezoidal structure. The first outer tube 3, the second outer tube 7, the third outer tube 8 and the fourth outer tube 9 are used to accommodate, compose and protect the engine combustion chamber components. An adjustment component 13 for assisting the airflow direction is provided at one end of the interior of the auxiliary air pipe channel 1, and the adjustment component 13 includes a fixed disk 1301, a servo motor 1302, a first guide plate 1303 and a second guide plate 1304. The outer surface of the fixed disk 1301 A servo motor 1302 is provided, and two groups of servo motors 1302 are provided. The output end of one group of servo motors 1302 is connected to the first guide plate 1303 through a drive shaft, and the output end of the other group of servo motors 1302 is connected to the second guide plate 1304 through a drive shaft. The airflow enters the interior of the first outer tube 3 through the left side of the auxiliary air pipe channel 1. When the airflow flows to the first outer tube 3, the design of a group of servo motors 1302 and the drive shaft can drive the first guide plate 1303 to rotate, so that the first guide plate 1303 can be rotated out from the interior of the auxiliary groove 11, so that the first guide plate 1303 can close the bottom airflow to the compressor 5 and maintain the circulation of the airflow above the compressor 5. , through the design of another set of servo motors 1302 and drive shafts, the second guide plate 1304 can be driven to rotate. By rotating the second guide plate 1304, the upper airflow to the compressor 5 can be guided downward. The range of the injection area can be controlled by designing the airflow direction. In addition, two groups of servo motors 1302 are provided, which respectively control the first guide plate 1303 and the second guide plate 1304, so that the first guide plate 1303 and the second guide plate 1304 can follow each other when the airflow direction changes, avoiding the large energy generated by the airflow when the direction changes, and maintaining the stability of the fuel nozzle 6 during ignition. The compressor 5 is provided in the middle of one end of the auxiliary air pipe channel 1, and the fuel nozzles 6 are provided on both sides of the compressor 5.

[0028] like Figure 1As shown, an adjusting component 2 for controlling the air flow rate is provided at one end of the auxiliary air pipe channel 1 away from the adjusting component 13. The adjusting component 2 is provided with two groups. The adjusting component 2 includes a cylinder 201, an adjusting guide plate 202 and a built-in groove 203. The built-in groove 203 is provided with a cylinder 201. The output end of the cylinder 201 is installed with an adjusting guide plate 202. The shape and structure of the adjusting guide plate 202 are consistent with the shape and structure of the auxiliary air pipe channel 1, and the auxiliary air pipe channel 1 forms an integrated structure with the auxiliary air pipe channel 1 through the support block 4. The design of the shape and structure of the auxiliary air pipe channel 1 can make the air flow enter the first outer tube 3 more smoothly. The design of the cylinder 201 in the built-in groove 203 can control the upper and lower position movement of the adjusting guide plate 202. The upper and lower position movement of the adjusting guide plate 202 can control the intake flux, which is convenient for using the first guide plate 1303 and the second guide plate 1304 to guide and control the air flow, thereby indirectly adjusting the injection area.

[0029] like Figure 3 and Figure 5 As shown, the interior of the third outer tube 8 is provided with a protective assembly 14 for protecting the third outer tube 8, and the protective assembly 14 is provided with six groups in a ring around the middle of the third outer tube 8. The protective assembly 14 includes an internal spring 1401 and a protective plate 1402, and the outer surface of the internal spring 1401 is provided with a protective plate 1402. When the fuel nozzle 6 is ignited, the burning flame is ejected from the third outer tube 8, and high temperature is generated during the ejection. The design of the protective plate 1402 provided on the inner surface of the third outer tube 8 can protect it from the inside of the third outer tube 8, and a large amount of energy is generated during the ejection. The elastic connection design between the protective plate 1402 and the internal spring 1401 can In order to provide elastic buffering protection for the third outer tube 8 during injection, two groups of support blocks 4 are provided. The outer surfaces of the two groups of support blocks 4 are installed with transition components 12 for blocking foreign matter. The transition component 12 includes a blade 1201, a fixing ring 1202 and a stabilizing block 1203. The fixing ring 1202 is provided with a blade 1201 inside, and the outer surface of the fixing ring 1202 is annularly installed with a stabilizing block 1203. When the airflow enters the first outer tube 3 from the auxiliary air pipe channel 1, the blades 1201 are distributed vertically and horizontally to form a filtering structure. When foreign matter enters the airflow, the airflow velocity can cut and crush the foreign matter, so as to facilitate subsequent ignition using the fuel nozzle 6.

[0030] In summary, if Figure 1-Figure 5As shown, the scramjet combustion chamber has an adjustable injection area. Scramjet engines generally use liquid alkanes or similar fuels as their energy source. Liquid fuel is injected into the engine from the fuel supply system and mixed with air to form a combustible mixture. During high-speed flight, the air intake at the front of the engine draws atmospheric air into the engine, which is then compressed. Inside the engine, liquid fuel is injected into the high-pressure, high-temperature compressed air to form a combustible mixture. This mixture is then ignited, causing a combustion reaction. Thrust generation: The high-temperature, high-pressure gases released by combustion are ejected through the engine's nozzle, generating thrust. This thrust propels the aircraft forward. During high-speed flight, it can fully utilize the oxygen in the atmosphere without carrying a large amount of oxidant. When in use, when oxygen enters the auxiliary airway channel 1, the shape and structure design of the auxiliary airway channel 1 can make the airflow enter the first outer tube 3 more smoothly. The design of the cylinder 201 in the built-in groove 203 can control the upward and downward movement of the guide plate 202. By adjusting the upward and downward movement of the guide plate 202, the intake flux can be controlled, and the airflow can be guided and controlled by the first guide plate 1303 and the second guide plate 1304. The injection area is adjusted indirectly. When the airflow enters the first outer tube 3 from the auxiliary air pipe channel 1, the blades 1201 are distributed vertically and horizontally to form a filtering structure. When foreign matter enters the airflow, the foreign matter can be cut and broken by the airflow velocity, which is convenient for subsequent ignition using the fuel nozzle 6. Then the airflow enters the first outer tube 3 through the left side of the auxiliary air pipe channel 1. When the airflow flows to the first outer tube 3, the first guide plate 1303 can be driven to rotate by a set of servo motors 1302 and the drive shaft design, so that the first guide plate 1303 can be The first guide plate 1303 is rotated out, so that the bottom airflow to the compressor 5 can be closed and the airflow to the top of the compressor 5 can be kept flowing. The second guide plate 1304 can be driven to rotate by another set of servo motors 1302 and the drive shaft design. The upper airflow to the compressor 5 can be guided downward by rotating the second guide plate 1304. The range of the injection area can be controlled by the airflow direction guide design. In addition, two sets of servo motors 1302 are provided, which respectively control the first guide plate 1303 and the second guide plate 1304, so that the airflow direction can be controlled. When the direction changes, the first guide plate 1303 and the second guide plate 1304 can follow each other to avoid the large energy generated by the airflow when the direction changes, maintain the stability of the fuel nozzle 6 when igniting, and finally ignite the fuel nozzle 6, and the burning flame is ejected from the third outer tube 8. High temperature will be generated during the ejection. The design of the protective plate 1402 provided on the inner surface of the third outer tube 8 can protect it from the inside of the third outer tube 8. The large energy generated during the ejection is designed to be elastically connected with the built-in spring 1401, so that the third outer tube 8 can be elastically buffered and protected during the ejection.

[0031] The embodiments of the present invention are presented for purposes of illustration and description and are not intended to be exhaustive or to limit the invention to the disclosed forms. Many modifications and variations will be apparent to those skilled in the art. The embodiments are chosen and described in order to better illustrate the principles of the invention and its practical application and to enable those skilled in the art to understand the invention and design various embodiments with various modifications as suited for specific applications.

Claims

1. A scramjet combustion chamber with adjustable injection area, comprising an auxiliary air duct channel (1), a first outer tube (3) and a fuel nozzle (6), characterized in that: An auxiliary airway channel (1) is provided in the middle of the first outer tube (3), and support blocks (4) are integrally installed on both sides of the auxiliary airway channel (1). An adjustment component (13) for adjusting the flow direction of the auxiliary airflow is provided at one end inside the auxiliary airway channel (1), and the adjustment component (13) comprises a fixed disk (1301), a servo motor (1302), a first guide plate (1303) and a second guide plate (1304). The servo motor (1302) is provided on the outer surface of the fixed disk (1301), and the servo motor (1302) is provided with two groups, one group of output ends of the servo motor (1302) A first guide plate (1303) is connected via a drive shaft, and another set of output ends of the servo motor (1302) is connected via a drive shaft to a second guide plate (1304). A compressor (5) is provided in the middle of one end of the auxiliary air pipe channel (1), and the fuel nozzles (6) are provided on both sides of the compressor (5). An adjustment component (2) for controlling the air flow rate is provided at one end of the auxiliary air pipe channel (1) away from the adjustment component (13). The adjustment component (2) is provided with two groups, and the adjustment component (2) includes a cylinder (201), an adjustment guide plate (202) and a built-in groove (203), and the built-in groove (203) 03) is provided with a cylinder (201) inside, an adjustment guide plate (202) is installed at the output end of the cylinder (201), a fourth outer tube (9) is provided on the right side of the first outer tube (3), and a second outer tube (7) is installed on the right side of the fourth outer tube (9), an inner cover (10) is provided on one side of the outer wall of the second outer tube (7), a third outer tube (8) is provided on the right side of the second outer tube (7), and the cross section of the third outer tube (8) is a trapezoidal structure, a protective component (14) for protecting the third outer tube (8) is provided inside the third outer tube (8), and the protective component (14) is provided with respect to the middle ring of the third outer tube (8). Six groups are provided in the shape of a plurality of support blocks, wherein the protective component (14) includes a built-in spring (1401) and a protective plate (1402), and the outer surface of the built-in spring (1401) is provided with a protective plate (1402), and the support block (4) is provided with two groups, and the outer surfaces of the two groups of support blocks (4) are both installed with a transition component (12) for blocking foreign matter, and the transition component (12) includes a blade (1201), a fixing ring (1202) and a stabilizing block (1203), and the interior of the fixing ring (1202) is provided with a blade (1201), and the outer surface of the fixing ring (1202) is annularly installed with a stabilizing block (1203).

2. The scramjet engine combustion chamber with adjustable injection area according to claim 1, characterized in that: The shape and structure of the adjustment guide plate (202) matches the shape and structure of the auxiliary tracheal channel (1).

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