Continuous detonation turbine engine with outer culvert afterburner

Abstract

The invention discloses a continuous detonation turbine engine provided with an outer culvert afterburner. An outer culvert casing of the continuous detonation turbine engine is composed of a fan casing, a heating section casing, a mixing section casing, a throat section casing, an oil injection section casing, an afterburner wall surface and an exhaust nozzle which are sequentially connected from upstream to downstream. An outer culvert air inlet channel is formed between the fan casing and the air compressor casing; the outer culvert heating channel is provided with an oil injection ignition device; a mixing channel is formed between the mixing section casing and the main combustion chamber casing; a throat channel is formed between the throat section casing and the gas casing; a circle of annular oil supply channel is arranged on the outer side of the oil injection section casing; the space in the afterburner wall surface forms an afterburner; an ignition device is arranged at the end, facing the exhaust nozzle, of the afterburner wall face. According to the continuous detonation turbine engine, by arranging the outer culvert heating channel, the incoming flow air temperature of the afterburner is effectively controlled, and stable detonation combustion of the outer culvert afterburner is achieved.

Description

Technical Field

[0001] The present invention belongs to the technical field of aeroengines, and particularly relates to a continuous detonation turbine engine provided with an external bypass afterburner combustor. Background Art

[0002] A continuous detonation engine is a power device that utilizes detonation combustion to generate thrust. As supersonic combustion, detonation combustion has a thermodynamic process similar to constant-volume combustion, featuring fast heat release and small entropy increase. Replacing the existing engine combustor with a continuous detonation combustor is expected to significantly improve the engine performance by changing the engine thermodynamic cycle and achieve a revolutionary technological breakthrough in the field of aviation power.

[0003] Among them, replacing the afterburner in a traditional turbine engine with a continuous detonation combustor is a direction with relatively prominent potential at present. For the afterburner of a low-bypass ratio turbofan engine, the high incoming flow velocity leads to incomplete combustion inside, resulting in high fuel consumption. The characteristic of fast heat release in detonation can significantly reduce the length of the combustor and improve the combustion efficiency. At the same time, there are fewer moving parts in the afterburner, making it easier to match detonation combustion.

[0004] Currently, a common method is to provide a mixing chamber in front of the afterburner. After the external bypass air is mixed with the main flow gas, they are jointly injected into the afterburner together with kerosene. However, in the detonation combustion flow field, the central region of the combustor is dominated by deflagration combustion, and this scheme cannot fully utilize the detonation pressure boost advantage. In addition, the oxygen concentration of the incoming flow after mixing is greatly reduced, making it difficult to maintain stable continuous detonation combustion. Therefore, directly introducing the external bypass air with a high oxygen concentration and specially arranging a combustor outside the afterburner to organize detonation to form a continuous detonation external bypass afterburner is another feasible scheme.

[0005] Under the current technical conditions, to form stable continuous detonation combustion using liquid kerosene, the kerosene must be rapidly mixed with hot air at a certain temperature, approximately above 500K. In an actual turbine engine, due to insufficient fan compression ratio, it is often difficult for the external bypass air to reach the temperature required for detonation initiation. Therefore, the continuous detonation external bypass afterburner scheme has the problem that the activity of the external bypass air is insufficient and it is difficult to directly form stable detonation with liquid kerosene.

[0006] In summary, how to reasonably design the layout of the afterburner, increase the temperature of the incoming air in the external bypass afterburner, and form a jet air injection scheme suitable for continuous detonation external bypass afterburner is an urgent problem to be solved. Summary of the Invention

[0007] The present invention provides a continuous detonation turbine engine provided with an external bypass afterburner combustor. The continuous detonation turbine engine effectively controls the temperature of the incoming air in the afterburner by providing an external bypass heating channel, and realizes stable detonation combustion in the external bypass afterburner combustor.

[0008] To achieve the above object, the present invention adopts the following specific technical solutions: A continuous detonation turbine engine provided with an afterburner in the bypass duct, the continuous detonation turbine engine comprising a central body, an inner duct casing, a bypass duct casing, a bypass heating channel and a fuel supply channel; the central body, the inner duct casing and the bypass duct casing are coaxially arranged and are arranged in sequence from the center to the outside along the radial direction; The central body is successively provided with a fan, a compressor, a turbine and a tail cone from the upstream to the downstream; the inner duct casing is composed of a compressor casing, a main combustion chamber casing, a turbine casing and a gas casing which are successively connected from the upstream to the downstream; the compressor casing is located outside the compressor; the space between the compressor casing and the central body forms an inner duct intake passage; the space between the main combustion chamber casing and the central body forms a main combustion chamber; the turbine casing is located outside the turbine; the space between the gas casing and the tail cone forms an inner duct gas passage; The bypass duct casing is composed of a fan casing, a heating section casing, a mixing section casing, a throat section casing, an oil injection section casing, an afterburner wall and a tail nozzle which are successively connected from the upstream to the downstream; the fan casing is located outside the fan; the space between the fan casing and the compressor casing forms a bypass duct intake passage; the bypass heating channel is arranged in the heating section casing, and the bypass heating channel is provided with an oil injection ignition device; the space between the mixing section casing and the main combustion chamber casing forms a mixing passage; the space between the throat section casing and the gas casing forms a throat passage; a circumferential annular fuel supply channel is arranged outside the oil injection section casing; the space inside the afterburner wall forms an afterburner; an ignition device is arranged at one end of the afterburner wall facing the tail nozzle.

[0009] Furthermore, the outer peripheral side of the bypass heating channel is the outer wall surface of the bypass heating channel; the oil injection ignition device is arranged on the outer wall surface of the bypass heating channel; the bypass heating channel is provided with a stepped air intake structure recessed towards the bypass duct intake passage on the upstream side of the oil injection ignition device, forming a bypass heating air intake channel; the bypass heating channel is provided with an annular rectifying channel surrounding the heating section casing on the downstream side of the oil injection ignition device; a week of jet holes are uniformly distributed on the heating section casing on the inner peripheral side of the rectifying channel.

[0010] Furthermore, the bypass heating channel is a cuboid-shaped structure, and two are symmetrically arranged in the heating section casing.

[0011] Furthermore, the central angle corresponding to the bypass heating channel in the circumferential direction is 10°-15°; There are 20-30 jet holes; The height of the stepped air intake structure extending into the bypass duct intake passage is 15-30 mm.

[0012] Furthermore, the throat passage is an air intake passage that contracts in the middle and expands at both ends.

[0013] Furthermore, support structures are evenly arranged circumferentially upstream of the fan of the central body, on the surface of the tail cone, and in the upstream and downstream regions of the compressor. The support structures are used to fixedly connect the central body to the inner casing and the outer casing.

[0014] Furthermore, the support structures arranged upstream of the fan and on the surface of the tail cone are used to connect the central body to the outer casing; the support structures arranged in the upstream and downstream regions of the compressor are used to support the inner casing.

[0015] Furthermore, an oil supply main pipe is connected to the outside of the casing of the fuel injection section of the oil supply passage for connecting an oil pump to supply fuel; a plurality of fuel nozzles are evenly distributed circumferentially inside the casing of the fuel injection section of the oil supply passage.

[0016] Furthermore, the afterburner is an empty-barrel afterburner.

[0017] Furthermore, 10 - 20 fuel nozzles are provided.

[0018] Compared with the prior art, the technical solution of the present invention has the following beneficial effects: 1. The continuous detonation turbine engine of the present invention is provided with an outer duct heating passage in the heating section casing of the outer casing, and an oil injection and ignition device is arranged in the outer duct heating passage. Since the oil injection and ignition device is arranged separately in the outer duct heating passage, the temperature of the outer duct air can be controlled by adjusting the fuel injection amount through the oil injection and ignition device, so that kerosene and the outer duct air can form detonation combustion in the afterburner better.

[0019] 2. The continuous detonation turbine engine of the present invention coaxially arranges the central body, the inner casing and the outer casing, forms an inner duct intake passage between the compressor casing and the central body, and forms an outer duct intake passage between the fan casing and the compressor casing, so that the outer duct combustible gas and the inner duct combustible gas can directly enter the afterburner, realizing the concentration stratification of fuel in the radial direction in the afterburner. The outer duct combustible gas distributed on the outside is conducive to the stable self-sustaining of detonation, and the gas in the central region forms a gas inner column, which can limit the radial expansion of the outer detonation products, and is conducive to the afterburner achieving a higher total pressure gain.

[0020] 3. The continuous detonation turbine engine of the present invention is provided with an annular rectifying passage around the heating section casing downstream of the outer duct heating passage. Thus, the rectifying passage downstream of the outer duct heating passage can make the combusted gas be injected into the outer duct more evenly. At the same time, the jet holes evenly distributed around the heating section casing on the inner side of the rectifying passage ensure that the gas has a certain radial velocity, which is conducive to mixing with the outer duct air.

[0021] 4. The continuous detonation turbine engine of the present invention is provided with a stepped air extraction structure recessed towards the side of the bypass air intake channel upstream of the bypass heating channel. The stepped bypass heating air extraction channel can form a recirculation zone upstream of the bypass heating channel, reducing the air velocity, which is beneficial to ignition and starting in the channel, thereby increasing the bypass air temperature and achieving stable detonation combustion in the bypass afterburner. Description of the Drawings

[0022] Figure 1 is a sectional view of the entire continuous detonation turbine engine; Figure 2 is an overall structure diagram of the bypass casing; Figure 3 is Figure 1 a structure diagram of the bypass heating channel in part A of Figure 4 is Figure 1 a sectional view of the bypass heating channel in part A of Figure 5 is Figure 1 a structure diagram of the fuel supply channel in part B of Figure 6 is Figure 1 a sectional view of the fuel supply channel in part B of

[0023] Reference Numerals: 1 - central body, 2 - inner casing, 3 - bypass casing, 4 - bypass heating channel, 5 - fuel supply channel, 6 - afterburner, 11 - fan, 12 - compressor, 13 - turbine, 14 - tail cone, 21 - compressor casing, 22 - main combustion chamber casing, 23 - turbine casing, 24 - gas casing, 31 - fan casing, 32 - heating section casing, 33 - mixing section casing, 34 - throat section casing, 35 - fuel injection section casing, 36 - afterburner wall, 37 - tail nozzle, 41 - outer wall of bypass heating channel, 42 - fuel injection and ignition device, 43 - jet orifice, 51 - fuel supply main pipe, 52 - fuel nozzle, 61 - ignition device, 210 - inner intake channel, 220 - main combustion chamber, 240 - inner gas channel; 310 - bypass intake channel, 330 - mixing channel, 340 - throat channel, 410 - bypass heating air extraction channel, 430 - rectifying channel. Detailed Embodiments

[0024] Next, the technical solutions in the embodiments of the present invention will be clearly and completely described in conjunction with the drawings in the embodiments of the present invention. Obviously, the described embodiments are only a part of the embodiments of the present invention, rather than all the embodiments. Based on the embodiments of the present invention, all other embodiments obtained by those of ordinary skill in the art without making creative efforts shall fall within the protection scope of the present invention.

[0025] As Figure 1As shown in the figure, an embodiment of the present invention provides a continuous detonation turbine engine provided with an afterburner in the bypass duct. By arranging a bypass heating channel, the continuous detonation turbine engine can effectively control the temperature of the incoming air in the afterburner and achieve stable detonation combustion in the afterburner in the bypass duct.

[0026] The continuous detonation turbine engine includes a central body 1, an inner casing 2, an outer casing 3, a bypass heating channel 4, and a fuel supply channel 5. Among them, the connection layout relationship between each part is as follows: The central body 1, the inner casing 2, and the outer casing 3 are coaxially arranged in sequence from the center to the outside, jointly constituting the turbine engine. On the central body 1, a fan 11, a compressor 12, a turbine 13, and a tail cone 14 are arranged in sequence from the upstream to the downstream. In this embodiment, Figure 1 the right side of the page is the upstream and the right side of the page is used as the intake end of the engine, and the left side of the page is the downstream and the left side of the page is used as the exhaust end of the engine.

[0027] An inner casing 2 is coaxially arranged outside the compressor 12 and the turbine 13. The inner casing 2 is composed of a compressor casing 21, a main combustion chamber casing 22, a turbine casing 23, and a gas casing 24, which are connected in sequence from the upstream to the downstream. Among them, the compressor casing 21 is located on the outer peripheral side of the compressor 12, and the turbine casing 23 is located on the outer peripheral side of the turbine 13. The main combustion chamber casing 22 is located between the compressor casing 21 and the turbine casing 23, and the space between the main combustion chamber casing 22 and the central body 1 constitutes the main combustion chamber 220. The space between the compressor casing 21 and the central body 1 constitutes the inner intake passage 210, and the space between the gas casing 24 and the tail cone 14 constitutes the inner gas passage 240.

[0028] An outer casing 3 is coaxially arranged between the inner casing 2 and the outer peripheral side of the fan 11. The outer casing 3 is composed of a fan casing 31, a heating section casing 32, a mixing section casing 33, a throat section casing 34, an injection section casing 35, an afterburner wall 36, and a tail nozzle 37, which are connected in sequence from the upstream to the downstream. Among them, the outer peripheral side part of the fan 11 is the fan casing 31. The space between the fan casing 31 and the compressor casing 21 constitutes the bypass intake passage 310.

[0029] Downstream of the fan casing 31 is the heating section casing 32, on which two rectangular bypass heating channels 4 are arranged, as Figure 2 and Figure 3 shown. The two rectangular bypass heating channels 4 are symmetrically arranged and evenly distributed circumferentially. The outer peripheral side of the bypass heating channel 4 is the outer wall 41 of the bypass heating channel. As Figure 1 、 Figure 3 and Figure 4As shown in the figure, an oil injection ignition device 42 is arranged on the outer annulus heating channel 4. Upstream of the oil injection ignition device 42, there is a stepped air extraction structure that is recessed radially inward along the inner side of the outer annulus air intake channel 310. An outer annulus heating air extraction channel 410 is formed within the stepped air extraction structure. Downstream of the oil injection ignition device 42, there is an annular rectification channel 430 that surrounds the heating section casing 32 for one week. A row of jet holes 43 are evenly arranged along the inner peripheral side of the rectification channel 430 for one week along the heating section casing 32.

[0030] Downstream of the outer annulus heating channel 4 is the mixing section casing 33. The space between the mixing section casing 33 and the main combustion chamber casing 22 constitutes the mixing channel 330. Downstream of the mixing section casing 33 is the throat section casing 34. The space between the throat section casing 34 and the gas casing 24 constitutes the throat channel 340. The throat channel 340 is an air extraction channel that contracts in the middle and expands at both ends, that is, the flow cross-sectional area in the middle is smaller, and the flow cross-sectional area gradually increases from the middle to both ends at the upstream and downstream ends of the middle part. Downstream of the throat section casing 34 is the oil injection section casing 35. The oil injection section casing 35 is provided with an annular oil supply channel 5 for one week. As Figure 5 and Figure 6 shown in the figure, an oil supply main pipe 51 is connected to the outside of the oil supply channel 5. The oil supply main pipe 51 is used to connect to an oil pump to supply fuel. A row of fuel nozzles 52 are evenly arranged for one week on the oil injection section casing 35 inside the oil supply channel 5. Downstream of the oil injection section casing 35 are the afterburner wall 36 and the tail nozzle 37 in sequence. The space inside the afterburner wall 36 constitutes the afterburner 6. The afterburner 6 is an empty barrel combustion chamber, and no additional walls and mixing chambers are arranged inside the afterburner 6. The outer annulus air mixed with fuel and the core gas can directly enter the afterburner 6. An ignition device 61 is arranged on the lower half of the afterburner wall 36.

[0031] Support structures are evenly arranged circumferentially on the upstream of the fan 11 of the central body 1, on the surface of the tail cone 14, and in the upstream and downstream regions of the compressor 12. The support structures arranged upstream of the fan 11 and on the surface of the tail cone 14 are used to connect the central body 1 to the outer annulus casing 3; the support structures arranged in the upstream and downstream regions of the compressor 12 are used to support the core casing 2. The central body 1 is fixedly connected to the core casing 2 and the outer annulus casing 3 through the support structures.

[0032] The working principle of the continuous detonation turbine engine of the present invention is as follows: After the engine starts, the incoming air is first compressed by the fan 11. Subsequently, a part of the air enters the core air intake channel 210, is compressed by the compressor 12 to form high-pressure air, enters the combustion chamber, and is mixed and burned with fuel. The high-temperature gas drives the turbine 13 and is introduced into the central region of the afterburner 6 through the core gas channel.

[0033] Another part of the compressed air behind the fan 11 enters the outer bypass air intake passage 310. However, due to the limited pressure ratio of the fan 11, the temperature rise of the incoming air after being compressed by the fan 11 is limited, which is not sufficient to form a continuous detonation with the liquid kerosene. Therefore, two stepped air extraction structures are symmetrically arranged on the heating section casing 32 to form an outer bypass heating air extraction passage 410, and a small part of the outer bypass air is introduced into the outer bypass heating passage 4. Fuel injection and ignition devices 42 are respectively arranged in the two outer bypass heating passages 4. The fuel and air are mixed and ignited to form high-temperature gas. After passing through the rectification passage 430 and the jet holes 43 evenly arranged circumferentially, it is introduced into the mixing passage 330. This part of the high-temperature gas is mixed with the remaining outer bypass air in the mixing passage 330 to form outer bypass air with a certain temperature. The heated outer bypass air passes through the throat section and the fuel injection section to be mixed with the fuel, and then enters the outer region of the afterburner 6. The contraction-expansion-contraction passage arranged in the throat section can better limit the influence of the detonation wave reverse transmission pressure in the afterburner 6 on the operation of the upstream fan 11. By controlling the fuel injection amount in the outer bypass heating passage 4, the temperature rise of the outer bypass air can be controlled. Since the required temperature rise amplitude of the outer bypass air is not large, the oxygen concentration of the heated outer bypass air after mixing remains basically unchanged.

[0034] The afterburner 6 is an empty-barrel combustion chamber, and no additional wall structure is provided inside to separate the outer bypass and the inner core. At the same time, the mixing chamber in front of the traditional afterburner 6 is also removed. The incoming flow at the entrance of the afterburner 6 realizes concentration stratification in the radial direction, that is, the outer bypass incoming flow with fuel is in the region close to the wall on the outside, which is used to organize detonation combustion in the afterburner 6. In the central region of the afterburner 6 is the inner core gas, which acts as a gas inner column during the outer bypass afterburning detonation combustion process, restricting the radial expansion of the outer detonation gas and enabling a higher total pressure gain. Finally, the outer bypass detonation products and the inner core gas in the afterburner 6 generate thrust after expanding through the tail nozzle 37.

[0035] Embodiment 1 As Figure 1 shown, the total length of the continuous detonation turbine engine is 1400 mm, the diameter of the inner core casing 2 is 350 mm, and the maximum diameter of the outer bypass casing 3 is 460 mm. From the center outwards are the center body 1, the inner core casing 2 and the outer bypass casing 3, and the three are coaxially connected. The incoming air is compressed by the fan 11 and sucked into the engine, and is separated by the compressor casing 21 and enters the inner core air intake passage 210 and the outer bypass air intake passage 310 respectively. The inner core air passes through the compressor 12, the main combustion chamber 220, and the turbine 13 to form gas, which is introduced into the central region of the afterburner 6 through the inner core gas passage.

[0036] There are two symmetrically arranged external bypass heating channels 4 in the external bypass casing 3. The circumferential angle of the external bypass heating channel 4 in the azimuth direction is 12°, the height is 20 mm, and the length is 170 mm. The external bypass heating channel 4 extends 20 mm upstream towards the inner side of the external bypass air inlet channel 310 to form a stepped external bypass heating air intake channel 410. After the external bypass air enters the heating section, a small part of the air will be introduced into the external bypass heating channel 4 and form high-temperature gas after combustion. An oil injection ignition device 42 is installed on the outer wall surface of the external bypass heating channel 4, and the temperature increase of the external bypass air can be controlled by controlling the fuel injection amount of the oil injection ignition device 42.

[0037] The downstream of the two external bypass heating channels 4 is connected through a rectifying channel 430 arranged circumferentially around the outer side of the heating section casing 32. 24 jet holes 43 are evenly arranged on the inner side of the rectifying channel 430. The high-temperature gas is injected into the external bypass through the jet holes 43, and is mixed with the external bypass air in the mixing channel 330, the temperature is increased, and the oxygen concentration changes little, which is beneficial to the formation of detonation with fuel in the downstream afterburner 6.

[0038] Subsequently, the heated external bypass air is accelerated through the throat channel 340. The downstream of the throat section casing 34 is the fuel injection section casing 35, and a circumferential fuel supply channel 5 is arranged on its outer side. Correspondingly, 12 fuel nozzles 52 are evenly arranged circumferentially on the inner side of the fuel injection section casing 35. The oil pump is connected to the fuel supply main pipe 51 to supply fuel. The fuel is then injected through the fuel supply channel 5 and the fuel nozzles 52 and is mixed with the heated and accelerated external bypass air. The external bypass air mixed with the fuel and the core gas enter the afterburner 6 together. There is a fuel concentration stratification in the radial direction of the afterburner 6. The outermost layer is the fuel and air for detonation combustion, which is detonated by the ignition device 61 downstream of the afterburner 6. The central area is the core gas acting as the gas inner column. The core gas restricts the radial expansion of the outer detonation products, realizes a higher total pressure gain, and more effectively exerts the advantage of detonation combustion.

[0039] Obviously, those skilled in the art can make various changes and modifications to the embodiments of the present invention without departing from the spirit and scope of the present invention. Thus, if these modifications and variations of the present invention fall within the scope of the claims of the present invention and their equivalent technologies, the present invention also intends to include these modifications and variations.

Claims

1. A continuous detonation turbine engine provided with an afterburner in the bypass duct, characterized in that, It includes a central body, an inner casing, an outer casing, an outer casing heating channel, and a fuel supply channel; the central body, the inner casing, and the outer casing are coaxially arranged and are sequentially arranged radially from the center outwards; The central body is sequentially provided with a fan, a compressor, a turbine, and a tail cone from upstream to downstream; the inner casing is composed of a compressor casing, a main combustion chamber casing, a turbine casing, and a gas casing that are sequentially connected from upstream to downstream; the compressor casing is located outside the compressor; the space between the compressor casing and the central body forms an inner intake channel; the space between the main combustion chamber casing and the central body forms a main combustion chamber; the turbine casing is located outside the turbine; the space between the gas casing and the tail cone forms an inner gas channel; The outer casing is composed of a fan casing, a heating section casing, a mixing section casing, a throat section casing, an oil injection section casing, an afterburner wall, and a tail nozzle that are sequentially connected from upstream to downstream; the fan casing is located outside the fan; the space between the fan casing and the compressor casing forms an outer intake channel; the outer casing heating channel is arranged in the heating section casing, and an oil injection ignition device is arranged in the outer casing heating channel; the space between the mixing section casing and the main combustion chamber casing forms a mixing channel; the space between the throat section casing and the gas casing forms a throat channel; a circumferential annular fuel supply channel is arranged outside the oil injection section casing; the space inside the afterburner wall forms an afterburner; an ignition device is arranged at one end of the afterburner wall facing the tail nozzle.

2. The continuous detonation turbine engine according to claim 1, wherein The outer peripheral side of the outer casing heating channel is the outer wall surface of the outer casing heating channel; the oil injection ignition device is arranged on the outer wall surface of the outer casing heating channel; the outer casing heating channel is provided with a stepped air intake structure that is recessed towards the outer intake channel side upstream of the oil injection ignition device, forming an outer casing heating air intake channel; the outer casing heating channel is provided with an annular rectifying channel that surrounds the heating section casing downstream of the oil injection ignition device; a week of jet holes are evenly distributed on the heating section casing on the inner peripheral side of the rectifying channel.

3. The continuous detonation turbine engine according to claim 2, wherein, The outer casing heating channel is a cuboid structure, and two are symmetrically arranged on the heating section casing.

4. The continuous detonation turbine engine according to claim 3, characterized in that, The central angle corresponding to the outer casing heating channel in the circumferential direction is 10° - 15°; There are 20 - 30 jet holes; The height of the stepped air intake structure extending into the outer intake channel is 15 - 30 mm.

5. The continuous detonation turbine engine according to claim 1, characterized in that, The throat channel is an air intake channel that contracts in the middle and expands at both ends.

6. The continuous detonation turbine engine according to claim 1, wherein Support structures are evenly arranged in the circumferential direction on the upstream of the fan of the central body, the surface of the tail cone, and the upstream and downstream regions of the compressor. The support structures are used to fixedly connect the central body with the inner casing and the outer casing.

7. The continuous detonation turbine engine according to claim 6, wherein The support structures arranged upstream of the fan and on the surface of the tail cone are used to connect the central body with the outer casing; the support structures arranged in the upstream and downstream regions of the compressor are used to support the inner casing.

8. The continuous detonation turbine engine according to any one of claims 1-7, characterized in that, The fuel supply channel is connected to a fuel supply main pipe outside the oil injection section casing for connecting to an oil pump to provide fuel; a plurality of fuel nozzles are evenly distributed in the circumferential direction on the inner side of the oil injection section casing.

9. The continuous detonation turbine engine according to claim 8, characterized in that, The afterburner is an empty barrel combustion chamber.

10. The continuous detonation turbine engine according to claim 8, wherein There are 10 - 20 fuel nozzles.

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