A strut-inboard embedded plasma igniter suitable for a scramjet engine

Abstract

The application discloses a strut plate embedded plasma igniter suitable for a scramjet engine and relates to the technical field of the scramjet engine.The strut plate embedded plasma igniter comprises a strut plate main body, and fuel main flow channels, oxygen main flow channels and an embedded channel are arranged on the strut plate main body; a plurality of fuel injection holes are arranged on the side wall of the fuel main flow channel; the oxygen main flow channel is in communication with the embedded channel, and an anode core is arranged in the embedded channel; a detachable head is arranged at one end of the embedded channel facing a combustion chamber, and a plurality of communication holes are arranged on the detachable head. A circular axis-symmetrical hypersonic combustion chamber is connected to the outside of the strut plate main body. The strut plate embedded plasma igniter suitable for the scramjet engine has the advantages of a stable combustion strut plate and a plasma igniter, has the characteristics of good insulation and partial stable combustion, and can ensure stable ignition of the axis-symmetrical supersonic combustion chamber.

Description

Technical Field

[0001] This invention relates to the field of scramjet engine technology, and in particular to a plate-embedded plasma igniter suitable for scramjet engines. Background Technology

[0002] Hypersonic vehicles, with their extremely high speeds and formidable strike capabilities, are a current research hotspot in the aerospace field. Scramjet engines, as a primary power source for hypersonic vehicles, are hailed as the third revolution in aviation history after propellers and jet propulsion due to their high specific impulse and speed. In supersonic combustion chambers, fuel-air mixing is a crucial technology and a prerequisite for efficient combustion. Because the mainstream velocity in a supersonic combustion chamber is extremely high, its momentum is much greater than that of the fuel, resulting in very limited fuel penetration depth and relatively difficult ignition. Furthermore, for liquid fuels such as aviation kerosene, the process of fragmentation, atomization, and mixing before combustion can directly lead to an ignition delay time greater than the residence time in the combustion chamber, resulting in inefficient combustion. Therefore, enhancing fuel-air mixing in supersonic combustion chambers is essential. Simultaneously, due to the structural symmetry of axisymmetric combustion chambers, a stable ignition method that does not disrupt the flow field structure is needed.

[0003] Currently, there are two main methods for enhancing mixing in supersonic combustors: passive mixing enhancement technology and active mixing enhancement technology. Passive mixing enhancement technology mainly enhances mixing by inducing a backflow zone or vortex based on different injection methods and configurations, while active mixing enhancement technology mainly enhances mixing by generating large-scale self-excitation. Passive mixing enhancement technologies mainly include supports, cavities, wall injection, shock wave generators, and counter-current injection, while active mixing enhancement technologies mainly include pulsed jets and corrugated walls. Considering that active mixing enhancement technology requires the introduction of additional structures, it will increase the load on the aircraft, and the reliability of electrical and control components is difficult to guarantee in complex flow environments. Therefore, from the perspective of passive mixing enhancement technology, constructing a backflow zone is a better choice for enhancing mixing. Currently, the main methods for ignition of circular axisymmetric combustion chambers include hot jet ignition, hydrogen ignition, spark plug ignition, and plasma ignition. Hot jet ignition and hydrogen ignition require complex supply and control systems, while spark plug ignition has low power. Therefore, plasma ignition was chosen for the design. Summary of the Invention

[0004] This invention, based on the combustion chamber of an axisymmetric scramjet engine, proposes a support plate-embedded plasma igniter suitable for scramjet engines to save space and ensure stable ignition. This igniter is embedded in a combustion stabilization support plate, where ionized oxygen discharges at the rear of the plate. Simultaneously, the combustion stabilization support plate is fixedly connected to the inner wall of the combustion chamber for stable support. A fuel injection port is located at the front end of the plate, where the injected aviation kerosene is entrained below a detachable head and ignited by ionized gas, achieving the purpose of ignition in an axisymmetric supersonic combustion chamber.

[0005] To achieve the above objectives, the present invention provides the following solution:

[0006] This invention provides a support plate-embedded plasma igniter suitable for scramjet engines, comprising a support plate body, wherein the support plate body is provided with a fuel main channel, an oxygen main channel and an embedded channel; the side wall of the fuel main channel is provided with a plurality of fuel injection holes; the oxygen main channel is connected to the embedded channel, and an anode core is provided in the embedded channel; a detachable head is provided at the end of the embedded channel facing the combustion chamber, and the detachable head is provided with a plurality of connecting holes.

[0007] Optionally, one end of the support plate body is a leading edge with a triangular cross-section, and the other end of the support plate body is a tail that gradually expands outward; the fuel main flow channel is disposed on the leading edge, and the oxygen main flow channel and the embedded channel are disposed on the tail.

[0008] Optionally, the bottom of the main oxygen channel is connected to the embedded channel via a through hole.

[0009] Optionally, the main fuel channel is connected to the fuel supply line.

[0010] Optionally, the main oxygen channel is connected to the oxygen supply pipe.

[0011] Optionally, the embedded channel is connected to the insulating fixing sleeve, one end of the anode core is disposed inside the insulating fixing sleeve, and the other end of the anode core extends into the embedded channel. An insulating T-shaped sleeve is disposed around the anode core in the embedded channel.

[0012] Optionally, both the insulating T-sleeve and the insulating fixing sleeve are made of ceramic material.

[0013] Optionally, the detachable head is connected to the embedded channel by a thread.

[0014] Optionally, the distance between the inner wall of the fuel main channel and the oxygen main channel and the outer wall of the support plate body is not less than 1.5 mm.

[0015] Optionally, the anode core is made of tungsten.

[0016] The present invention achieves the following technical effects compared to the prior art:

[0017] The plasma igniter embedded in the support plate of the present invention, which is suitable for scramjet engines, combines the advantages of a flame-stabilizing support plate and a plasma igniter. It has the characteristics of good insulation and partial flame stabilization, and can ensure stable ignition in the axisymmetric supersonic combustion chamber. Attached Figure Description

[0018] To more clearly illustrate the technical solutions in the embodiments of the present invention or the prior art, the drawings used in the embodiments will be briefly introduced below. Obviously, the drawings described below are only some embodiments of the present invention. For those skilled in the art, other drawings can be obtained based on these drawings without creative effort.

[0019] Figure 1 This is a schematic diagram of the structure of the support plate embedded plasma igniter of the present invention applicable to scramjet engines;

[0020] Figure 2 This is a structural schematic diagram from another perspective of the plasma igniter embedded in the support plate of the present invention, applicable to scramjet engines.

[0021] Figure 3 This is a cross-sectional view of the plasma igniter embedded in the support plate of the present invention, applicable to scramjet engines.

[0022] Explanation of reference numerals in the attached drawings: 1. Main support plate; 2. Main fuel flow channel; 3. Fuel injection hole; 4. Main oxygen flow channel; 5. Through hole; 6. Embedded channel; 7. Anode core; 8. Insulating fixing sleeve; 9. Insulating T-shaped sleeve; 10. Detachable head; 11. Leading edge; 12. Tail end; 13. Fuel supply pipe; 14. Oxygen supply pipe. Detailed Implementation

[0023] The technical solutions of the embodiments of the present invention will be clearly and completely described below with reference to the accompanying drawings. Obviously, the described embodiments are only some embodiments of the present invention, and not all embodiments. Based on the embodiments of the present invention, all other embodiments obtained by those skilled in the art without creative effort are within the scope of protection of the present invention.

[0024] like Figures 1 to 3As shown, this embodiment provides a support plate-embedded plasma igniter suitable for scramjet engines, including a support plate body 1. The support plate body 1 is provided with a fuel main channel 2, an oxygen main channel 4, and an embedded channel 6. Multiple fuel injection holes 3 are provided on the side wall of the fuel main channel 2. The oxygen main channel 4 is connected to the embedded channel 6, and an anode core 7 is provided within the embedded channel 6. A detachable head 10 is provided at the end of the embedded channel 6 facing the combustion chamber, and multiple connecting holes 5 are provided on the detachable head 10. A circular axisymmetric hypersonic combustion chamber is externally connected to the support plate body 1.

[0025] In this specific embodiment, one end of the support plate body 1 is a triangular front edge 11, and the other end is a gradually expanding tail 12. The fuel main channel 2 is located on the front edge 11, and the oxygen main channel 4 and the embedded channel 6 are located on the tail 12. More specifically, a fuel supply pipe 13 is threadedly connected to the upper inner wall of the fuel main channel 2, through which fuel is supplied to the fuel main channel 2. An oxygen supply pipe 14 is threadedly connected to the upper inner wall of the oxygen main channel 4, through which oxygen flows to the plasma igniter via the oxygen supply pipe 14, the oxygen main channel 4, and the through hole 5. The through hole 5 is located at the gap between the insulating T-shaped sleeve 9 and the detachable head 10, thus providing an oxygen supply path for the plasma igniter.

[0026] The embedded channel 6 is connected to the insulating fixing sleeve 8. One end of the anode core 7 is located inside the insulating fixing sleeve 8, and the other end of the anode core 7 extends into the embedded channel 6. An insulating T-shaped sleeve 9 is arranged around the anode core 7 within the embedded channel 6. More specifically, the insulating T-shaped sleeve 9 is located between the anode core 7 and the igniter embedded channel 6. The upper end of the igniter embedded channel 6 is threaded with the insulating fixing sleeve 8. Both the insulating T-shaped sleeve 9 and the insulating fixing sleeve 8 are made of ceramic material, which together achieves insulation between the anode core 7 and the support plate body 1. The lower end of the igniter embedded channel 6 is threaded with a detachable head 10, which allows ionized gas to be ejected from the porous structure of the detachable head 10.

[0027] The distance between the inner wall of the fuel main channel 2 and the oxygen main channel 4 and the outer wall of the support plate body 1 is not less than 1.5mm.

[0028] The anode core 7 is located at the center of the embedded channel 6 of the igniter. It is made of tungsten material and can withstand the high temperature brought by the discharge.

[0029] The working principle of the plate-embedded plasma igniter for scramjet engines in this embodiment is as follows:

[0030] Before use, the fuel supply pipe 13 and the oxygen supply pipe 14 are connected to the fuel tank and the gas cylinder, respectively, to introduce aviation kerosene and oxygen, which are then transported through the fuel main channel 2 and the oxygen main channel 4. The anode core 7 is connected to the positive terminal of the power supply, and the main body 1 of the support plate is grounded as a whole. During use, the fuel is sprayed out from both sides of the front end of the support plate through the fuel injection hole 3, and after exchanging momentum with the high-speed incoming flow, it diffuses along the flow. A low-speed backflow zone of a certain scale is generated behind the tail 12 of the support plate main body 1. The oxygen flows through the oxygen main channel 4 and the through hole 5 to the ionization zone between the anode core 7 and the detachable head 10. The oxygen is ionized under high pressure and sprayed out through the porous structure of the detachable head 10, igniting the fuel sucked in below the tail 12 of the support plate due to the central cone, thereby achieving stable ignition of the circular axisymmetric combustion chamber.

[0031] It should be noted that, for those skilled in the art, it is obvious that the present invention is not limited to the details of the above exemplary embodiments, and that the present invention can be implemented in other specific forms without departing from the spirit or essential characteristics of the invention. Therefore, the embodiments should be considered exemplary and non-limiting in all respects, and the scope of the invention is defined by the appended claims rather than the foregoing description. Thus, all variations falling within the meaning and scope of equivalents of the claims are intended to be included within the present invention, and no reference numerals in the claims should be construed as limiting the scope of the claims.

[0032] This specification uses specific examples to illustrate the principles and implementation methods of the present invention. The descriptions of the above embodiments are only for the purpose of helping to understand the method and core ideas of the present invention. Furthermore, those skilled in the art will recognize that, based on the ideas of the present invention, there will be changes in the specific implementation methods and application scope. Therefore, the content of this specification should not be construed as a limitation of the present invention.

Claims

1. A strut-in-plate plasma igniter suitable for use in a scramjet engine, the igniter comprising: The supporting plate body is provided with a fuel main flow channel, an oxygen main flow channel and an embedded channel; the side wall of the fuel main flow channel is provided with a plurality of fuel injection holes; the oxygen main flow channel is communicated with the embedded channel, and the embedded channel is provided with an anode core; the embedded channel is provided with a detachable head at one end facing the combustion chamber, and the detachable head is provided with a plurality of communication holes.

2. The strut-in-shoe plasma igniter suitable for a scramjet engine according to claim 1, wherein One end of the supporting plate body is a front edge with a triangular cross section, and the other end of the supporting plate body is a tail portion gradually expanding outward; the fuel main flow channel is arranged on the front edge, and the oxygen main flow channel and the embedded channel are arranged on the tail portion.

3. The strut-and-blade inner-embedded plasma igniter suitable for a scramjet as defined in claim 1, wherein The bottom of the oxygen main flow channel is communicated with the embedded channel through a through hole.

4. The strut-and-blade inner-embedded plasma igniter suitable for a scramjet as defined in claim 1, wherein The fuel main flow channel is communicated with a fuel supply pipe.

5. The strut-in-shoe plasma igniter suitable for a scramjet engine according to claim 1, wherein, The oxygen main flow channel is communicated with an oxygen supply pipe.

6. The strut-and-blade inner-embedded plasma igniter suitable for a scramjet as defined in claim 1, wherein The embedded channel is communicated with an insulating fixed sleeve, one end of the anode core is arranged in the insulating fixed sleeve, the other end of the anode core extends into the embedded channel, and an insulating T-shaped sleeve is arranged around the anode core in the embedded channel.

7. The strut-in-shoe plasma igniter suitable for use in a scramjet engine according to claim 6, wherein, The insulating T-shaped sleeve and the insulating fixed sleeve are made of ceramic material.

8. The strut-and-blade inner-embedded plasma igniter suitable for a scramjet as defined in claim 1, wherein The detachable head and the embedded channel are connected through threads.

9. The strut-and-blade inner-embedded plasma igniter suitable for a scramjet as defined in claim 1, wherein The distance between the inner wall of the fuel main flow channel and the oxygen main flow channel and the outer wall of the supporting plate body is not less than 1.5 mm.

10. The strut-in-shoe plasma igniter suitable for use in a scramjet engine according to claim 1, wherein, The anode core is made of tungsten.

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