Plasma fuel activation device for hyperbolic combustion chamber fuel injection rod

Abstract

The application provides a subsonic ram combustor oil injection rod plasma fuel activation device, comprising a combustor shell (1), an oil injection rod (2), a flame stabilizer (3) and a plasma exciter (4); wherein the plasma exciter (4) is composed of a high-voltage electrode (5), a low-voltage electrode (6), a ceramic inner core (7) and a metal outer sleeve (8). The application also provides a subsonic ram combustor oil injection rod plasma fuel activation method. The application is used to solve the problems of difficult ignition and low combustion efficiency of the subsonic ram combustor under low working conditions. The application adopts an innovative sliding arc plasma excitation device behind the oil injection rod of the subsonic ram combustor, so that the working performance optimization of the subsonic ram combustor in a wide incoming flow parameter range can be realized without adding a geometric adjustable mechanism.

Description

Technical Field

[0001] This invention relates to the field of aero-engines, and more particularly to a plasma fuel activation device for the fuel injector rod of a ramjet combustion chamber. Background Technology

[0002] Turbine-based combined cycle (TBCC) engines are one of the ideal power forms for high-speed near-space vehicles. Among various combination forms, the technical solution that combines turbojet engines and subsonic ramjet engines has advantages such as high technical maturity and controllable development risks.

[0003] At low speeds, the TBCC engine is powered by the turbine engine. As the flight speed increases, the engine enters a mode transition phase, the turbine engine gradually stops working, and the subsonic ramjet engine ignites and starts, providing thrust to the aircraft independently.

[0004] Turbojet engines typically operate at speeds between Mach 0 and 2.0, while subsonic ramjet engines operate at Mach 2.0 to 5.0. Because the speed ranges of the two power forms overlap little, TBCC engines suffer from insufficient thrust and poor acceleration during mode transitions, which seriously affects flight safety.

[0005] There are two main approaches to solving the above problems: one is to broaden the upper limit of the operating speed of the turbine engine, and the other is to broaden the lower limit of the ignition and start-up speed of the subsonic ramjet engine. When adopting the second approach, namely broadening the lower limit of the start-up speed of the subsonic ramjet engine, the relatively low flight speed results in a lower total inlet temperature of the combustion chamber and poor fuel atomization and evaporation characteristics, leading to difficulties in ignition of the subsonic ramjet combustion chamber, insufficient combustion efficiency, and difficulty in meeting the performance requirements of the aircraft's propulsion system.

[0006] A typical sub-gas ramjet combustion chamber mainly consists of two parts: the fuel injector and the flame stabilizer. The fuel injector serves as the main fuel supply line to the combustion chamber, accounting for approximately 80%-90% of the total fuel supply. The remaining fuel is supplied to the flame stabilizer and ignited, thus igniting the fuel in the main fuel line. Existing technologies primarily improve the ignition performance of the combustion chamber under low operating conditions by optimizing the stabilizer's geometry and dimensions. However, due to the relatively small fuel supply to the stabilizer, optimization studies targeting it are unlikely to significantly improve the overall combustion efficiency of the combustion chamber. Therefore, the improvement in engine thrust performance is limited, and the problem of insufficient thrust during the mode transition phase of a TBCC engine remains unresolved.

[0007] Existing research results indicate that plasma possesses significant thermal and chemical effects, showing promising application prospects in promoting the atomization and evaporation of liquid kerosene and enhancing its chemical activity.

[0008] In summary, applying plasma to the fuel injector of a submersible ramjet combustion chamber to treat the fuel in the main fuel circuit is expected to significantly improve the chemical activity of liquid kerosene, thereby widening the lower limit of the ignition and start-up speed of the submersible ramjet combustion chamber and improving the thrust performance of the engine under low operating conditions. Summary of the Invention

[0009] To address the problems existing in the prior art, this invention proposes a plasma fuel activation device for a ramjet combustion chamber injector rod, comprising a combustion chamber housing 1, an injector rod 2, a flame stabilizer 3, and a plasma exciter 4; wherein...

[0010] The combustion chamber shell 1 is a cylindrical hollow cylinder;

[0011] The fuel injector 2 is a hollow metal rod. On the cross-section near the combustion chamber inlet, multiple identical fuel injectors 2 are evenly arranged along the circumference. Each fuel injector 2 is fixed to the combustion chamber shell 1 along the circumferential radius of the combustion chamber. One end of the fuel injector 2 is closed inside the combustion chamber, and the other end outside the combustion chamber shell is connected to the engine fuel supply line. Multiple fuel injector holes are opened on the wall of each fuel injector 2. The direction of the injection holes is downstream along the axis of the combustion chamber. The multiple injection holes are kept at a certain distance from the far end of the fuel injector 2.

[0012] The flame stabilizer 3 is a common evaporative flame stabilizer in submersible ramjet combustion chambers. It is coaxial with and fixedly connected to the combustion chamber housing 1 and is located downstream of the fuel injection rod.

[0013] The plasma exciter 4 is arranged in pairs with the oil injection rod 2, and the number of them is the same. It is located directly behind the oil injection rod, and is the same as the oil injection rod 2 in radial position. In axial direction, it is located downstream of the oil injection rod 2 and maintains a certain distance from it.

[0014] The plasma exciter 4 includes a high-voltage electrode 5, a low-voltage electrode 6, a ceramic inner core 7, and a metal outer casing 8;

[0015] The ceramic core 7 is a slender solid cylinder, shorter than the fuel injector 2. Two symmetrical through holes are drilled along the direction parallel to the axis of the ceramic core 7, with the center of the end face as the symmetrical point in its diameter direction. These holes serve as pre-made circular holes for inserting the high-voltage electrode 5 and the low-voltage electrode 6.

[0016] Both the high-voltage electrode 5 and the low-voltage electrode 6 are slender cylinders, slightly longer than the ceramic core 7. The two metal electrodes are tightly fitted into the pre-made circular holes in the cylindrical ceramic core 7. The length of the end of the metal electrode that penetrates into the combustion chamber is greater than the length of the ceramic core, so it can be exposed inside the combustion chamber. The end of the metal electrode that is outside the combustion chamber shell is also exposed and connected to the power supply through a wire.

[0017] The surface of the ceramic inner core 7 extending into the combustion chamber is stepped, with two steps, one high and one low, each occupying a semicircle. The length of the semicircle where the low-pressure electrode 6 is fixed is greater than the length of the semicircle where the high-pressure electrode 5 is fixed.

[0018] The metal jacket 8 is a hollow cylindrical outer tube, and its length is slightly shorter than the shortest length of the ceramic inner core 7. The inner diameter of the metal jacket 8 is equal to or slightly larger than the outer diameter of the ceramic inner core 7, so that the ceramic inner core 7 can be tightly fitted and inserted into it. One end of the metal jacket 8 outside the combustion chamber shell is flush with the outer end face of the ceramic inner core 7, and the ceramic inner core 7 is fixedly connected to the metal jacket 8. The plasma exciter 4 is fixedly connected to the combustion chamber shell 1 through the metal jacket 8.

[0019] In one specific embodiment of the present invention, two injection holes are opened on the wall of each injection rod, and the distances between the two injection holes and the far end of the injection rod are 15mm and 40mm, respectively.

[0020] In another specific embodiment of the invention, the plasma exciter 4 is located 15 mm downstream of the fuel injection rod 2 in the axial direction.

[0021] In one embodiment of the present invention, the combustion chamber housing 1 is made of a high-temperature alloy; the flame stabilizer 3 is made of a high-temperature alloy; and the high-voltage electrode 5 and the low-voltage electrode 6 are made of tungsten metal.

[0022] In another specific embodiment of the present invention, there are 6 fuel injection rods in the ramjet combustion chamber, which are evenly arranged in the circumference, and each fuel injection rod has 2 fuel injection holes; the plasma exciter appears in a group with the fuel injection rods, corresponding one-to-one, and there are also 6 rods, located 15mm behind the fuel injection rods.

[0023] In another specific embodiment of the present invention

[0024] The combustion chamber shell 1 has a wall thickness of 10mm, an inner diameter of 240mm, and a length of 400mm;

[0025] The outer diameter of the fuel injector 2 is 8mm, the inner diameter is 4mm, the total length is 120mm, and the length extending into the combustion chamber is 100mm. There are two fuel injection holes arranged on the fuel injector 2, with the distances between the injection holes and the far end of the fuel injector 20mm and 45mm respectively, and the diameter of the injection holes is 1mm.

[0026] The metal jacket 8 is cylindrical, with an outer diameter of 8mm, an inner diameter of 6mm, a total length of 70mm, and a length extending 50mm into the combustion chamber.

[0027] The ceramic inner core 7 has an outer diameter of 6mm. The upper end of the ceramic inner core is flat and flush with the upper surface of the metal outer casing 8. The lower surface of the inner core extends into the combustion chamber and is divided into two equal parts. One half is used to fix the low-pressure electrode 6 and the other half is used to fix the high-pressure electrode 5. The semi-cylindrical length of the half ...

[0028] The high-pressure electrode 5 and the low-pressure electrode 6 are both 1 mm in diameter, with total lengths of 82.5 mm and 87.5 mm respectively, and their lengths extending into the combustion chamber are 62.5 mm and 67.5 mm respectively.

[0029] Furthermore, in one embodiment of the present invention, the working principle of the above-mentioned ramjet combustion chamber injector plasma fuel activation device is as follows: when the ramjet combustion chamber of the TBCC engine is started, a voltage is applied between the high-voltage electrode 5 and the low-voltage electrode 6 of the plasma exciter 4 through an external plasma power supply. When the voltage exceeds the breakdown voltage between the two electrodes, an electric arc plasma discharge is formed between the electrodes. Under the action of airflow, the electric arc plasma discharge channel is continuously stretched and eventually breaks. Subsequently, a breakdown discharge is re-formed between the electrodes to form an electric arc, and the above process is repeated periodically.

[0030] The advantages of this invention are as follows:

[0031] By generating an electric arc plasma discharge to activate the fuel injected by the fuel injector, the ignition and shutdown performance and combustion efficiency of the subsonic ramjet combustion chamber under low operating conditions can be improved, significantly enhancing the propulsion efficiency during the mode transition phase of the TBCC engine.

[0032] Plasma discharge has the advantages of simple structure, adjustable discharge parameters, high frequency response, and good adaptability to incoming flow. It can achieve ignition and combustion control over a wide parameter range without changing the geometry of the combustion chamber. Attached Figure Description

[0033] Figure 1 This is a cross-sectional view of the present invention;

[0034] Figure 2 Here is a simplified structural diagram of a plasma actuator;

[0035] Reference numerals: ① Combustion chamber shell, ② Injection rod, ③ Flame stabilizer, ④ Plasma actuator, ⑤ High-voltage electrode, ⑥ Low-voltage electrode, ⑦ Ceramic core, ⑧ Metal jacket. Detailed Implementation

[0036] To enable those skilled in the art to better understand the present invention, the present invention will be further described in detail below with reference to the accompanying drawings and the following embodiments.

[0037] like Figure 1 As shown, a plasma fuel activation device for a ramjet combustion chamber includes a combustion chamber housing 1, a fuel injector 2, a flame stabilizer 3, and a plasma exciter 4.

[0038] The combustion chamber shell 1 is a cylindrical hollow cylinder made of high-temperature alloy.

[0039] The fuel injector 2 is a hollow metal rod. Multiple identical fuel injectors 2 are evenly arranged circumferentially on a cross-section near the combustion chamber inlet. Each fuel injector 2 is fixed to the combustion chamber shell 1, for example, by welding, along the circumferential radius of the combustion chamber. One end of the injector 2 is closed inside the combustion chamber, while the other end outside the combustion chamber shell is connected to the engine fuel supply line. Each fuel injector 2 has, for example, two injection holes on its wall, pointing downstream along the combustion chamber axis. The distances of the two injection holes from the far end of the fuel injector 2 are 15mm and 40mm, respectively. High-pressure kerosene is ejected from the injection holes, atomized into fine droplets under pressure, and sprayed downstream in an approximately conical shape.

[0040] The flame stabilizer 3 is a common evaporative flame stabilizer in sub-gas ramjet combustion chambers (Zheng Dianfeng, Zhang Huiqiang, Lin Wenyi, et al. Experimental study on the combustion performance of evaporative stabilizers at normal and low pressure [J]. Journal of Harbin Institute of Technology, 2004(12): 1724-1728.). It is coaxial with the combustion chamber shell 1, made of high-temperature alloy, located downstream of the fuel injector rod, and fixed to the combustion chamber shell 1 by bolts through a mounting bracket.

[0041] The plasma exciter 4 is arranged in pairs with the fuel injection rod 2, and the number of them is the same. It is located directly behind the fuel injection rod and is in the same radial position as the fuel injection rod 2. In the axial direction, it is located, for example, 15 mm downstream of the fuel injection rod 2.

[0042] like Figure 2 As shown, the plasma exciter 4 consists of a high-voltage electrode 5, a low-voltage electrode 6, a ceramic inner core 7, and a metal outer casing 8.

[0043] The ceramic core 7 is a slender solid cylinder, shorter than the fuel injector 2. Two symmetrical through holes are drilled along the diameter direction of the ceramic core 7 with the center of the end face as the symmetrical point, parallel to the axis of the ceramic core 7, to serve as pre-made circular holes for inserting the high-voltage electrode 5 and the low-voltage electrode 6.

[0044] The high-voltage electrode 5 and the low-voltage electrode 6 are made of tungsten metal and are both slender cylinders, slightly longer than the ceramic core 7. The two metal electrodes are tightly fitted into the pre-made circular holes in the cylindrical ceramic core 7 and fixed with high-temperature adhesive. The length of the end of the metal electrode that penetrates into the combustion chamber is greater than the length of the ceramic core, so it can be exposed inside the combustion chamber. The end of the metal electrode that is outside the combustion chamber shell is also exposed and connected to the power supply through a wire.

[0045] The surface of the ceramic inner core 7 extending into the combustion chamber is stepped, with two steps, one high and one low, each occupying a semicircle. The length of the semicircle where the low-pressure electrode 6 is fixed is greater than the length of the semicircle where the high-pressure electrode 5 is fixed.

[0046] The metal jacket 8 is a hollow cylindrical outer tube, slightly shorter than the shortest length of the ceramic inner core 7. The inner diameter of the metal jacket 8 is equal to or slightly larger than the outer diameter of the ceramic inner core 7, facilitating a tight fit between the ceramic inner core 7 and the outer tube. One end of the metal jacket 8 outside the combustion chamber housing is flush with the outer end face of the ceramic inner core 7, and the ceramic inner core 7 and the metal jacket 8 are fixed together, for example, by adhesive bonding. The plasma exciter 4 is fixedly connected to the combustion chamber housing 1 via the metal jacket 8. In a specific embodiment of the invention, the end of the metal jacket 8 near the combustion chamber housing is designed with mounting threads, and is fixed to the combustion chamber housing 1 by a threaded connection.

[0047] The working principle of the radial plasma fuel activation device of the ramjet combustion chamber injector is as follows: When the ramjet combustion chamber of the TBCC engine starts, a voltage is applied between the high-voltage electrode 5 and the low-voltage electrode 6 of the plasma exciter 4 through an external plasma power supply. When the voltage exceeds the breakdown voltage between the two electrodes, an electric arc plasma discharge is formed between the electrodes. Under the action of airflow, the electric arc plasma discharge channel is continuously stretched and eventually breaks. Then, the electric arc is re-formed by breakdown discharge between the electrodes, and the above process is repeated periodically.

[0048] By generating an electric arc plasma through discharge, the significant thermal effect of the arc heats the kerosene ejected from the injection hole, accelerating its atomization and evaporation into small droplets. Simultaneously, the chemical reactivity of the arc plasma causes some of the kerosene to undergo a cracking chemical reaction, producing highly reactive small-molecule products such as H2, CH4, and C2H2, thereby enhancing the chemical reactivity of the fuel-air mixture. Through these two effects, the difficulty of igniting the ramjet combustion chamber is reduced, and the combustion efficiency is improved, thus enhancing the performance of the ramjet combustion chamber.

[0049] like Figure 1-2 As shown, in a specific embodiment of the present invention:

[0050] The combustion chamber shell 1 has a wall thickness of 10mm, an inner diameter of 240mm, and a length of 400mm;

[0051] The outer diameter of the fuel injector 2 is 8mm, the inner diameter is 4mm, the total length is 120mm, and the length extending into the combustion chamber is 100mm. Two fuel injection holes are arranged on the fuel injector, which are 20mm and 45mm away from the far end of the fuel injector, respectively (the far end refers to the end that is far away from the fuel supply inlet, that is, the end that is inserted into the combustion chamber). The diameter of the fuel injection hole is 1mm.

[0052] The metal casing 8 of the plasma actuator 4 is cylindrical, with an outer diameter of 8mm, an inner diameter of 6mm, a total length of 70mm, and a length of 50mm extending into the combustion chamber.

[0053] The ceramic inner core 7 of the plasma exciter 4 is cylindrical with an outer diameter of 6mm. The upper end of the ceramic inner core is flat and flush with the upper surface of the metal jacket 8. The lower surface of the inner core extends into the combustion chamber and is divided into two equal parts. One half is used to fix the low-pressure electrode 6 and the other half is used to fix the high-pressure electrode 5. The length of the semi-cylinder that fixes the low-pressure electrode 6 is 65mm and the length of the semi-cylinder that fixes the high-pressure electrode 5 is 60mm. The two semi-cylinders are stepped.

[0054] Both the high-pressure electrode 5 and the low-pressure electrode 6 are straight cylinders with a diameter of 1 mm and total lengths of 82.5 mm and 87.5 mm, respectively. Their lengths extending into the combustion chamber are 62.5 mm and 67.5 mm, respectively.

[0055] The performance improvement of existing sub-gas ramjet combustors is mainly achieved through the optimization design of the flame stabilizer geometry. Plasma discharge has the advantages of simple structure, adjustable discharge parameters, high frequency response and good adaptability to incoming flow. It can achieve ignition and combustion control within a wide parameter range without changing the geometry of the combustor.

[0056] In another embodiment of the present invention:

[0057] The flame stabilizer 3 of the ramjet combustion chamber adopts the evaporative flame stabilizer commonly used in ramjet combustion chambers, and is fixed to the combustion chamber shell by bolts through a mounting bracket;

[0058] The sub-steam ramjet combustion chamber contains six fuel injectors, evenly arranged circumferentially, each with two injection holes. The plasma exciter appears in a group with the fuel injectors, corresponding one-to-one, also consisting of six units, located 15mm directly behind the fuel injectors.

[0059] A method for activating liquid kerosene plasma fuel gas in the injector rod of a ramjet combustion chamber is also provided. Based on the aforementioned plasma fuel activation device for the injector rod of a ramjet combustion chamber, the method is as follows: When the ramjet combustion chamber of the TBCC engine is started, a voltage is applied between the high-voltage electrode 5 and the low-voltage electrode 6 of the plasma exciter 4 through an external plasma power supply. When the voltage exceeds the breakdown voltage between the two electrodes, an electric arc plasma discharge is formed between the electrodes. Under the action of airflow, the electric arc plasma discharge channel is continuously stretched and eventually breaks. Subsequently, the electric arc is re-established by breakdown discharge between the electrodes, and the above process is repeated periodically.

[0060] By generating an electric arc plasma through discharge, the significant thermal effect of the arc heats the kerosene ejected from the injection hole, accelerating its atomization and evaporation into small droplets. Simultaneously, the chemical reactivity of the arc plasma causes some of the kerosene to undergo a cracking chemical reaction, producing highly reactive small-molecule products such as H2, CH4, and C2H2, thereby enhancing the chemical reactivity of the fuel-air mixture. Through these two effects, the difficulty of igniting the ramjet combustion chamber is reduced, and the combustion efficiency is improved, thus enhancing the performance of the ramjet combustion chamber.

Claims

1. A subsonic ramjet combustion chamber fuel injection rod plasma fuel activation apparatus, characterized by, The combustion chamber shell (1), the oil injection rod (2), the flame stabilizer (3), the plasma exciter (4) are included The combustion chamber shell (1) is a cylindrical hollow cylinder The oil injection rod (2) is a hollow metal rod, a plurality of identical oil injection rods (2) are uniformly arranged on the cross section near the inlet of the combustion chamber in the circumferential direction, each oil injection rod (2) is fixed on the combustion chamber shell (1) along the direction of the combustion chamber circumferential radius, the end deep into the combustion chamber is closed, the end outside the combustion chamber shell is connected with the engine oil supply pipeline, a plurality of oil injection holes are opened on the wall of each oil injection rod, the direction of the oil injection hole points to the downstream along the axis direction of the combustion chamber, and the distance between the plurality of oil injection holes and the distal end of the oil injection rod is kept constant The flame stabilizer (3) is a common evaporation type flame stabilizer of a subsonic ramjet combustion chamber, which is coaxial with and fixedly connected with the combustion chamber shell (1) and located downstream of the oil injection rod The plasma exciter (4) is arranged in pairs with the oil injection rod (2) and has the same number, located directly behind the oil injection rod (2), has the same radial position as the oil injection rod (2), and is located downstream of the oil injection rod (2) in the axial direction and keeps a certain distance from the oil injection rod (2) The plasma exciter (4) includes a high-voltage electrode (5), a low-voltage electrode (6), a ceramic inner core (7) and a metal outer sleeve (8) The ceramic inner core (7) is an elongated solid cylinder, and the length is shorter than that of the oil injection rod (2); two symmetric through holes are punched in the diameter direction of the ceramic inner core (7) end face with the end face center as the symmetric point along the parallel direction of the ceramic inner core (7) axis as the prefabricated round hole for inserting the high-voltage electrode (5) and the low-voltage electrode (6) The high-voltage electrode (5) and the low-voltage electrode (6) are both elongated cylinders, and the length is slightly longer than that of the ceramic inner core (7); the two metal electrodes are inserted into the prefabricated round hole of the cylindrical ceramic inner core (7) in a tight fit, and the length of the metal electrode deep into the combustion chamber is longer than that of the ceramic inner core, so it can be exposed in the combustion chamber The end of the metal electrode outside the combustion chamber shell is also exposed outside and connected with the power supply through a wire The surface of the ceramic inner core (7) deep into the combustion chamber is stepped, and the high and low steps each occupy a semicircle; the semicircle length where the low-voltage electrode (6) is fixed is longer than the semicircle length where the high-voltage electrode (5) is fixed The metal outer sleeve (8) is a hollow cylindrical outer sleeve, and the length is slightly shorter than the shortest length of the ceramic inner core (7); the inner diameter of the metal outer sleeve (8) is equal to or slightly larger than the outer diameter of the ceramic inner core (7), so that the ceramic inner core (7) can be inserted into it in a tight fit The end of the metal outer sleeve (8) outside the combustion chamber shell is flush with the outer end surface of the ceramic inner core (7), and the ceramic inner core (7) is fixedly connected with the metal outer sleeve (8); the plasma exciter (4) is fixedly connected with the combustion chamber shell (1) through the metal outer sleeve (8).

2. The hybrid ramjet combustor fueling post plasma fuel activation apparatus of claim 1 wherein, Two oil injection holes are opened on the wall of each oil injection rod, and the distance between the two oil injection holes and the distal end of the oil injection rod is 15mm and 40mm respectively.

3. The hybrid ramjet combustor fuel rod plasma fuel activation apparatus of claim 1 wherein, The plasma exciter (4) is located 15mm downstream of the oil injection rod (2) in the axial direction.

4. The hybrid ramjet combustor fuel rod plasma fuel activation apparatus of claim 1 wherein, The combustion chamber shell (1) is made of high-temperature alloy; the flame stabilizer (3) is made of high-temperature alloy; the high-voltage electrode (5) and the low-voltage electrode (6) are made of metal tungsten.

5. The SCRC fuel oil injection rod plasma fuel oil activation apparatus of claim 1 wherein, The number of oil injection rods in the subsonic ram combustor is 6, which are arranged uniformly in the circumferential direction, and 2 oil injection holes are arranged on each oil injection rod; the plasma exciter is arranged in groups corresponding to the oil injection rods, and the number of plasma exciters is also 6, which are located 15 mm behind the oil injection rods.

6. The subsonic ram combustor oil injection rod plasma fuel activation device of claim 1, wherein, The wall thickness of the combustor shell (1) is 10 mm, the inner diameter is 240 mm, and the length is 400 mm; The outer diameter of the oil injection rod (2) is 8 mm, the inner diameter is 4 mm, the total length is 120 mm, and the length into the combustor is 100 mm. Two oil injection holes are arranged on the oil injection rod, and the distances between the oil injection holes and the distal end of the oil injection rod are 20 mm and 45 mm, respectively. The diameter of the oil injection hole is 1 mm; The metal sleeve (8) is cylindrical, with an outer diameter of 8 mm, an inner diameter of 6 mm, a total length of 70 mm, and a length into the combustor of 50 mm; The outer diameter of the ceramic inner core (7) is 6 mm. The upper end of the ceramic inner core is a flat surface and is flush with the upper surface of the metal sleeve (8). The lower surface into the combustor is divided into two parts, one half of which is fixed with a low-voltage electrode (6) and the other half is fixed with a high-voltage electrode (5). The half-cylinder length of the fixed low-voltage electrode (6) is 65 mm, and the half-cylinder length of the fixed high-voltage electrode (5) is 60 mm; The diameters of the high-voltage electrode (5) and the low-voltage electrode (6) are both 1 mm, and the total lengths are 82.5 mm and 87.5 mm, respectively. The lengths into the combustor are 62.5 mm and 67.5 mm, respectively.

7. The Scramjet combustor fuel rod plasma fuel activation apparatus of claim 1 wherein, The working principle of the device is as follows: when the TBCC engine ram combustor starts, an external plasma power source is connected to apply a voltage between the high-voltage electrode (5) and the low-voltage electrode (6) of the plasma exciter (4). When the voltage exceeds the breakdown voltage between the two electrodes, an electric arc plasma discharge is formed between the electrodes. Under the action of the airflow, the electric arc plasma discharge channel is continuously elongated and eventually broken. Then, a new electric arc is formed between the electrodes by re-breaking down the discharge, and the above process is periodically repeated.

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