A continuous detonation turbine engine with an external afterburner

Abstract

The present invention discloses a continuous detonation turbine engine equipped with an external afterburner. The external 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 injection section casing, an afterburner chamber wall, and a tail nozzle, which are connected in sequence from upstream to downstream. An external duct intake passage is formed between the fan casing and the compressor casing. The external duct heating passage is provided with an injection ignition device. A mixing passage is formed between the mixing section casing and the main combustion chamber casing. A throat passage is formed between the throat section casing and the gas casing. An annular oil supply passage is arranged on the outer side of the injection section casing. The space within the afterburner chamber wall constitutes the afterburner. An ignition device is arranged on the end of the afterburner chamber wall facing the tail nozzle. By providing the external duct heating passage, the continuous detonation turbine engine effectively controls the temperature of the air flowing into the afterburner chamber, achieving stable detonation combustion in the external duct afterburner chamber.

Description

Technical Field

[0001] The present invention belongs to the technical field of aviation engines, and in particular relates to a continuous detonation turbine engine provided with an external afterburner combustion chamber. Background Art

[0002] A continuous detonation engine is a propulsion system that uses detonation combustion to generate thrust. As a supersonic combustion process, detonation combustion's thermodynamic process resembles constant-volume combustion, characterized by rapid heat release and minimal entropy increase. Replacing existing engine combustion chambers with continuous detonation combustion chambers is expected to significantly improve engine performance by altering the engine's thermodynamic cycle, potentially achieving a transformative technological breakthrough in aviation propulsion.

[0003] Among them, replacing the afterburner in traditional turbofan engines with a continuous detonation combustion chamber presents a promising approach. The high inflow velocity in the afterburner of a low-bypass turbofan engine leads to incomplete combustion, resulting in higher fuel consumption. However, the rapid heat release of detonation significantly reduces the length of the combustion chamber, improving combustion efficiency. Furthermore, the fewer moving parts in the afterburner make it easier to adapt to detonation combustion.

[0004] A common method currently involves installing a mixing chamber in front of the afterburner. This mixes the sump air with the main gas and then injects it into the afterburner along with kerosene. However, in the detonation combustion flow field, the center of the combustion chamber is dominated by slow burn, so this solution cannot fully utilize the advantages of detonation boosting. Furthermore, the oxygen concentration of the mixed incoming flow is significantly reduced, making it difficult to maintain stable and continuous detonation combustion. Therefore, another feasible solution is to directly introduce high-oxygen-concentration sump air and set up a dedicated combustion chamber outside the afterburner to organize detonation, thereby creating a continuous detonation sump afterburner.

[0005] Under current technical conditions, to achieve stable continuous detonation combustion using liquid kerosene, the kerosene must be rapidly mixed with hot air reaching a certain temperature, approximately 500K or higher. However, in actual turbine engines, due to the insufficient fan compression ratio, the sump air often struggles to reach the required temperature for detonation. Therefore, continuous detonation sump afterburner schemes suffer from insufficient sump air activity, making it difficult to directly form a stable detonation with the liquid kerosene.

[0006] In summary, how to reasonably design the afterburner layout, increase the incoming air temperature of the culvert afterburner, and form an injection and bleed air scheme suitable for continuous detonation culvert 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 afterburner combustion chamber. The continuous detonation turbine engine effectively controls the temperature of the air flowing into the afterburner combustion chamber by providing an external heating channel, thereby achieving stable detonation combustion in the external afterburner combustion chamber.

[0008] In order to achieve the above object, the present invention adopts the following specific technical solutions:

[0009] A continuous detonation turbine engine with an external afterburner, the continuous detonation turbine engine comprising a center body, an inner casing, an outer casing, an outer casing heating channel, and an oil supply channel; the center body, the inner casing, and the outer casing are coaxially arranged and arranged radially outward in sequence;

[0010] The center body is arranged with a fan, compressor, turbine and tail cone from upstream to downstream; the inner casing is composed of the compressor casing, main combustion chamber casing, turbine casing and gas casing connected in sequence from upstream to downstream; the compressor casing is located outside the compressor; the space between the compressor casing and the center body constitutes the inner air intake channel; the space between the main combustion chamber casing and the center body constitutes the main combustion chamber; the turbine casing is located outside the turbine; the space between the gas casing and the tail cone constitutes the inner gas channel;

[0011] The outer culvert casing is composed of a fan casing, a heating section casing, a mixing section casing, a throat section casing, an injection section casing, an afterburner combustion chamber wall and a tail nozzle, which are connected in sequence from upstream to downstream; the fan casing is located on the outside of the fan; the space between the fan casing and the compressor casing constitutes the outer culvert air intake channel; the heating section casing is provided with an outer culvert heating channel, and the outer culvert heating channel is provided with an injection ignition device; the space between the mixing section casing and the main combustion chamber casing constitutes the mixing channel; the space between the throat section casing and the gas casing constitutes the throat channel; a ring-shaped oil supply channel is arranged on the outside of the injection section casing; the space inside the afterburner combustion chamber wall constitutes the afterburner combustion chamber; and an ignition device is arranged on the end of the afterburner combustion chamber wall facing the tail nozzle.

[0012] Furthermore, the outer peripheral side of the outer culvert heating channel is the outer wall surface of the outer culvert heating channel; the fuel injection ignition device is arranged on the outer wall surface of the outer culvert heating channel; the outer culvert heating channel is provided with a stepped air induction structure recessed toward one side of the outer culvert air inlet channel upstream of the fuel injection ignition device, forming an outer culvert heating air induction channel; the outer culvert heating channel is provided with an annular rectifying channel surrounding the heating section casing downstream of the fuel injection ignition device; a circle of jet holes is evenly distributed on the heating section casing on the inner peripheral side of the rectifying channel.

[0013] Furthermore, the outer heating channel is a rectangular parallelepiped structure, and two of them are symmetrically arranged in the heating section casing.

[0014] Furthermore, the central angle of the outer heating channel corresponding to the circumference is 10°-15°;

[0015] There are 20-30 air jet holes.

[0016] The height of the stepped air inlet structure extending into the outer culvert air inlet passage is 15-30 mm.

[0017] Furthermore, the throat passage is an air inlet passage that contracts in the middle and expands at both ends.

[0018] Furthermore, support structures are evenly arranged along the circumference on the fan upstream, tail cone surface and compressor upstream and downstream areas of the center body, and the support structures are used to fix the center body with the inner casing and the outer casing.

[0019] Furthermore, the support structures arranged on the upstream surface of the fan and the tail cone are used to connect the center body and the outer casing; the support structures arranged in the upstream and downstream areas of the compressor are used to support the inner casing.

[0020] Furthermore, the fuel supply channel is connected to a fuel supply main pipe on the outside of the fuel injection section casing for connecting to an oil pump to provide fuel; the fuel supply channel is provided with a plurality of fuel nozzles evenly distributed along the circumference on the inside of the fuel injection section casing.

[0021] Furthermore, the afterburner is an empty barrel combustion chamber.

[0022] Furthermore, 10-20 fuel nozzles are provided.

[0023] Compared with the prior art, the technical solution of the present invention has the following beneficial effects:

[0024] 1. The continuous detonation turbine engine of the present invention is provided with a duct heating channel in the heating section of the duct casing. The duct heating channel is provided with a fuel injection ignition device. Since the fuel injection ignition device is separately arranged in the duct heating channel, the duct air temperature is controlled by adjusting the fuel injection amount through the fuel injection ignition device, thereby better enabling kerosene and duct air to form detonation combustion in the afterburner.

[0025] 2. The continuous detonation turbine engine of the present invention coaxially arranges the center body, inner casing and outer casing, forms an inner air intake channel between the compressor casing and the center body, and forms an outer air intake channel between the fan casing and the compressor casing, so that the outer combustible gas and the inner combustible gas can directly enter the afterburner, realizing radial fuel concentration stratification in the afterburner. The outer distributed outer combustible gas is conducive to stable self-sustaining detonation, and the gas in the central area forms an inner gas column, which can limit the radial expansion of the outer detonation products, which is conducive to achieving a higher total pressure gain in the afterburner.

[0026] 3. The continuous detonation turbine engine of the present invention is provided with an annular rectifying channel surrounding the heating section casing downstream of the outer culvert heating channel, so that the rectifying channel downstream of the outer culvert heating channel can make the post-combustion combustion gas more evenly injected into the outer culvert. At the same time, the injection holes evenly distributed around the heating section casing inside the rectifying channel ensure that the combustion gas has a certain radial velocity, which is conducive to mixing with the outer culvert air.

[0027] 4. The continuous detonation turbine engine of the present invention is provided with a stepped air inlet structure recessed toward one side of the outer duct air inlet channel upstream of the outer duct heating channel. The stepped outer duct heating air inlet channel can form a recirculation zone upstream of the outer duct heating channel, thereby reducing the air flow rate and facilitating ignition and starting in the channel, thereby increasing the outer duct air temperature and realizing stable detonation combustion in the outer duct afterburner. BRIEF DESCRIPTION OF THE DRAWINGS

[0028] Figure 1 It is a cross-sectional view of the entire continuous detonation turbine engine;

[0029] Figure 2 This is the overall structural diagram of the outer casing;

[0030] Figure 3 for Figure 1 Structural diagram of the outer heating channel in part A;

[0031] Figure 4 for Figure 1 Section A of the outer heating channel;

[0032] Figure 5 for Figure 1 Structural diagram of the oil supply channel in part B;

[0033] Figure 6 for Figure 1 Cross-sectional view of the oil supply channel in part B.

[0034] Reference numerals: 1-center body, 2-inner casing, 3-outer casing, 4-outer 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-injection section casing, 36-recommended section casing, 37-recommended section casing, 38-recommended section casing, 39-recommended section casing, 40-recommended section casing, 41-recommended section casing, 42-recommended section casing, 43-recommended section casing, 44-recommended section casing, 45-recommended section casing, 46-recommended section casing, 47-recommended section casing, 48-recommended section casing, 49-recommended section casing, 50-recommended section casing, 51-recommended section casing, 52-recommended section casing, 53-recommended section casing, 54-recommended section casing, 55-recommended section casing, 56-recommended section casing, 57-recommended section casing, 58-recommended section casing, 59-recommended section casing, 60-recommended section casing, 61-recommended section casing, 62-recommended section casing, 63-recommended section casing, 64-recommended section casing, 65-recommended section casing, 66-recommended section casing, 67-recommended section casing, 68 6- afterburner chamber wall, 37- tail nozzle, 41- outer wall of outer heating channel, 42- fuel injection ignition device, 43- jet hole, 51- fuel supply main pipe, 52- fuel nozzle, 61- ignition device, 210- inner air intake channel, 220- main combustion chamber, 240- inner gas channel; 310- outer air intake channel, 330- mixing channel, 340- throat channel, 410- outer heating bleed air channel, 430- rectifier channel. DETAILED DESCRIPTION

[0035] The following will clearly and completely describe the technical solutions in the embodiments of the present invention in conjunction with the accompanying drawings. Obviously, the described embodiments are only part of the embodiments of the present invention, not all of the embodiments. Based on the embodiments of the present invention, all other embodiments obtained by ordinary technicians in this field without making creative efforts are within the scope of protection of the present invention.

[0036] like Figure 1 As shown, an embodiment of the present invention provides a continuous detonation turbine engine provided with an external afterburner combustion chamber. The continuous detonation turbine engine can effectively control the incoming air temperature of the afterburner combustion chamber by providing an external heating channel, thereby achieving stable detonation combustion in the external afterburner combustion chamber.

[0037] The continuous detonation turbine engine comprises a center body 1, an inner casing 2, an outer casing 3, an outer casing heating channel 4 and an oil supply channel 5; wherein, the connection layout relationship between the various parts is as follows: the center body 1, the inner casing 2 and the outer casing 3 are coaxially arranged from the center to the outside, and together constitute a turbine engine; the fan 11, the compressor 12, the turbine 13 and the tail cone 14 are arranged on the center body 1 from upstream to downstream. In this embodiment, Figure 1 The right side of the page is the upstream and serves as the air inlet of the engine, and the left side of the page is the downstream and serves as the air outlet of the engine.

[0038] 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 upstream to downstream. 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 center body 1 constitutes the main combustion chamber 220. The space between the compressor casing 21 and the center body 1 constitutes the inner air intake passage 210, and the space between the gas casing 24 and the tail cone 14 constitutes the inner gas passage 240.

[0039] The outer casing 3 is coaxially arranged around the inner casing 2 and the outer periphery of the fan 11. The outer casing 3 consists 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 chamber wall 36, and a tail nozzle 37, all connected in sequence from upstream to downstream. The outer periphery of the fan 11 constitutes the fan casing 31. The space between the fan casing 31 and the compressor casing 21 forms the outer casing inlet duct 310.

[0040] The downstream of the fan casing 31 is the heating section casing 32, on which are arranged two rectangular outer heating channels 4, such as Figure 2 and Figure 3 As shown, two rectangular outer heating channels 4 are symmetrically arranged and evenly distributed along the circumference. The outer peripheral side of the outer heating channel 4 is the outer wall surface 41 of the outer heating channel. Figure 1 、 Figure 3 and Figure 4 As shown, a fuel injection ignition device 42 is disposed on the outer culvert heating channel 4. A stepped air bleed structure, radially recessed toward the inner side of the outer culvert air inlet channel 310, is disposed upstream of the fuel injection ignition device 42. The stepped air bleed structure forms the outer culvert heating air bleed channel 410. Downstream of the fuel injection ignition device 42, an annular rectifying channel 430 is disposed, surrounding the heating section casing 32. Small injection holes 43 are evenly distributed along the inner circumference of the rectifying channel 430 along the heating section casing 32.

[0041] Downstream of the outer heating channel 4 is the mixing section casing 33, and 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, and 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 bleed channel that contracts in the middle and expands at both ends, that is, the flow cross-sectional area in the middle is relatively small, and the flow cross-sectional area at both ends of the middle part gradually increases from the middle to the two ends. Downstream of the throat section casing 34 is the injection section casing 35, and the injection section casing 35 is arranged with a circular oil supply channel 5. As shown Figure 5 and Figure 6As shown, the fuel supply channel 5 is connected to a fuel supply manifold 51 on the outside. This manifold 51 is used to connect to the fuel pump to supply fuel. Fuel nozzles 52 are evenly arranged around the injection section casing 35 inside the fuel supply channel 5. Downstream of the injection section casing 35 are the afterburner wall 36 and the tail nozzle 37. The space within the afterburner wall 36 constitutes the afterburner 6. This is a hollow chamber, lacking any additional walls or mixing chambers. The external air mixed with fuel and the internal combustion gas can enter the afterburner 6 directly. An ignition device 61 is located on the lower half of the afterburner wall 36.

[0042] Support structures are evenly arranged along the circumferential direction upstream of the fan 11 of the center body 1, on the surface of the tail cone 14, and in the upstream and downstream areas 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 center body 1 with the outer casing 3; the support structures arranged in the upstream and downstream areas of the compressor 12 are used to support the inner casing 2, and the center body 1 is fixedly connected to the inner casing 2 and the outer casing 3 through the support structures.

[0043] The operating principle of the continuous detonation turbine engine of the present invention is as follows: After the engine is started, incoming air is first compressed by fan 11. A portion of this air then enters the internal intake duct 210, where it is compressed by compressor 12 to form high-pressure air that enters the combustion chamber and mixes with fuel for combustion. The high-temperature fuel gas drives turbine 13 and is then introduced into the center of the afterburner 6 through the internal fuel gas duct.

[0044] Another portion of the compressed air after fan 11 enters the outer culvert inlet duct 310. However, due to the limited pressure ratio of fan 11, the temperature rise of the incoming air after compression by fan 11 is limited, insufficient to form a continuous detonation with the liquid kerosene. Therefore, two stepped bleed air structures are symmetrically arranged on the heating section casing 32, forming the outer culvert heating bleed air duct 410, which directs a small portion of the outer culvert air into the outer culvert heating duct 4. Each outer culvert heating duct 4 is equipped with a fuel injection ignition device 42. The fuel and air mix and ignite to form high-temperature combustion gas. After passing through the rectifying duct 430 and the circumferentially arranged injection holes 43, it is introduced into the mixing duct 330. This high-temperature combustion gas mixes with the remaining outer culvert air in the mixing duct 330, forming outer culvert air of a certain temperature. After being heated, the outer culvert air passes through the throat section and fuel injection section to mix with the fuel before entering the outer area of ​​the afterburner 6. The convergence-expansion-contraction channel in the throat section effectively limits the impact of the detonation wave's backpropagation pressure within the afterburner 6 on the operation of the upstream fan 11. By controlling the amount of fuel injected into the sump heating channel 4, the temperature rise of the sump air can be controlled. Because the required temperature rise of the sump air is relatively small, the oxygen concentration of the heated sump air after mixing remains essentially unchanged.

[0045] The afterburner 6 is a hollow barrel combustion chamber, lacking any additional internal wall structure to separate the outer and inner linings. The mixing chamber in front of the traditional afterburner 6 has also been eliminated. The incoming flow at the inlet of the afterburner 6 is radially stratified in concentration. The outer area near the wall contains the outer lining flow, which carries fuel and is used to organize detonation combustion within the afterburner 6. The inner lining combustion gas is located in the center of the afterburner 6. This acts as an inner column of gas during the outer lining afterburner detonation combustion, limiting the radial expansion of the outer lining detonation gas and achieving a higher total pressure gain. Ultimately, the outer lining detonation products and the inner lining combustion gas within the afterburner 6 expand through the tail nozzle 37 to generate thrust.

[0046] Example 1

[0047] like Figure 1 As shown, the continuous detonation turbine engine has a total length of 1400 mm, an inner casing 2 with a diameter of 350 mm, and an outer casing 3 with a maximum diameter of 460 mm. From the center outward, the center body 1, inner casing 2, and outer casing 3 are coaxially connected. Incoming air is compressed by the fan 11 and drawn into the engine. It is then separated by the compressor casing 21 and enters the inner air intake duct 210 and the outer air intake duct 310, respectively. The inner air passes through the compressor 12, the main combustion chamber 220, and the turbine 13 to form combustion gas, which is then introduced into the central region of the afterburner 6 through the inner combustion gas duct.

[0048] The outer casing 3 is symmetrically arranged with two outer heating channels 4, each with a 12° circumferential angle, a height of 20 mm, and a length of 170 mm. The outer heating channels 4 extend 20 mm upstream of the inner duct intake channel 310, forming a stepped outer heating air bleed channel 410. After the outer duct air enters the heating section, a small amount of air is drawn into the outer heating channel 4, where it is burned to form high-temperature combustion gas. An oil injection ignition device 42 is installed on the outer wall of the outer heating channel 4. By controlling the amount of oil injected by the oil injection ignition device 42, the temperature increase of the outer duct air can be controlled.

[0049] The two outer duct heating channels 4 are connected downstream by a rectifying channel 430 arranged circumferentially along the outer side of the heating section casing 32. Twenty-four injection holes 43 are evenly distributed within the rectifying channel 430. High-temperature combustion gas is injected into the outer duct through the injection holes 43 and mixed with the outer duct air in the mixing channel 330, raising its temperature while maintaining minimal change in oxygen concentration. This facilitates detonation with the fuel in the downstream afterburner 6.

[0050] The heated outer envelope air is then accelerated through the throat passage 340. Downstream of the throat section casing 34 is the fuel injection section casing 35, which is surrounded by a peripheral fuel supply passage 5. Correspondingly, twelve fuel nozzles 52 are evenly spaced circumferentially within the inner portion of the fuel injection section casing 35. An oil pump connects to the fuel supply manifold 51 to provide fuel, which is then injected through the fuel supply passage 5 and the fuel nozzles 52 and mixed with the heated and accelerated outer envelope air. The mixed outer envelope air and the inner combustion gas enter the afterburner 6 together. The afterburner 6 exhibits radial fuel concentration stratification. The outermost portion contains the fuel and air used for detonation combustion, which is detonated by the ignition device 61 downstream of the afterburner 6. The central region contains the inner combustion gas, which serves as the gas column. The inner combustion gas limits the radial expansion of the outer detonation products, achieving a higher total pressure gain and more effectively leveraging the advantages of detonation combustion.

[0051] Obviously, those skilled in the art may 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 such modifications and variations of the present invention fall within the scope of the claims and their equivalents, the present invention is intended to include such modifications and variations.

Claims

1. A continuous detonation turbine engine provided with an external afterburner, characterized in that: It includes a center body, an inner casing, an outer casing, an outer casing heating channel and an oil supply channel; the center body, the inner casing and the outer casing are coaxially arranged and arranged in sequence from the center to the outside in a radial direction; The center body is arranged with a fan, compressor, turbine and tail cone from upstream to downstream; the inner casing is composed of the compressor casing, main combustion chamber casing, turbine casing and gas casing connected in sequence from upstream to downstream; the compressor casing is located outside the compressor; the space between the compressor casing and the center body constitutes the inner air intake channel; the space between the main combustion chamber casing and the center body constitutes the main combustion chamber; the turbine casing is located outside the turbine; the space between the gas casing and the tail cone constitutes the inner gas channel; The outer culvert casing is composed of a fan casing, a heating section casing, a mixing section casing, a throat section casing, an injection section casing, an afterburner combustion chamber wall and a tail nozzle, which are connected in sequence from upstream to downstream; the fan casing is located on the outside of the fan; the space between the fan casing and the compressor casing constitutes the outer culvert air intake channel; the heating section casing is provided with an outer culvert heating channel, and the outer culvert heating channel is provided with an injection ignition device; the space between the mixing section casing and the main combustion chamber casing constitutes the mixing channel; the space between the throat section casing and the gas casing constitutes the throat channel; a ring-shaped oil supply channel is arranged on the outside of the injection section casing; the space inside the afterburner combustion chamber wall constitutes the afterburner combustion chamber; and an ignition device is arranged on the end of the afterburner combustion chamber wall facing the tail nozzle.

2. The continuous detonation turbine engine according to claim 1, characterized in that The outer peripheral side of the outer culvert heating channel is the outer wall surface of the outer culvert heating channel; the fuel injection ignition device is arranged on the outer wall surface of the outer culvert heating channel; the outer culvert heating channel is provided with a stepped air induction structure recessed toward one side of the outer culvert air inlet channel upstream of the fuel injection ignition device, forming an outer culvert heating air induction channel; the outer culvert heating channel is provided with an annular rectifying channel surrounding the heating section casing downstream of the fuel injection ignition device; a circle of jet holes is 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, characterized in that: The outer heating channel is a rectangular parallelepiped structure, and two of them are symmetrically arranged in the heating section casing.

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

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

6. The continuous detonation turbine engine according to claim 1, characterized in that: Support structures are evenly arranged along the circumference on the upstream of the fan of the center body, the surface of the tail cone, and the upstream and downstream areas of the compressor. The support structures are used to fix the center body to the inner casing and the outer casing.

7. The continuous detonation turbine engine according to claim 6, characterized in that: The support structure arranged on the upstream surface of the fan and the tail cone is used to connect the center body and the outer casing; the support structure arranged in the upstream and downstream areas of the compressor is used to support the inner casing.

8. The continuous detonation turbine engine according to any one of claims 1 to 7, characterized in that: The fuel supply channel is connected to a fuel supply main pipe on the outside of the injection section casing for connecting to an oil pump to provide fuel; the fuel supply channel is provided with a plurality of fuel nozzles evenly distributed along the circumference on the inside of the 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, characterized in that: There are 10-20 fuel nozzles.

Images