An automatic fuel recovery system based on a rotating detonation combustor

Abstract

The present invention discloses an automatic fuel recovery system based on a rotating detonation combustion chamber, which includes an air supply chamber, a fuel supply chamber, an annular combustion chamber, and a fuel recovery system; the annular combustion chamber is a ring cavity structure composed of an outer combustion chamber ring and an inner combustion chamber column distributed along the same axis, and the air supply holes and fuel supply holes are located at the head of the annular combustion chamber; the air supply chamber and the fuel supply chamber are respectively a ring cavity structure composed of an intake chamber component and a combustion chamber cover plate and a cylindrical cavity structure, both of which are located at the head of the annular combustion chamber; the fuel recovery system is embedded in the outer combustion chamber ring. The present invention can recover and recycle the unburned fuel during long-term multiple working intervals, solving the problems of fuel waste and environmental pollution caused by the formation of fuel accumulation in the cavity due to poor atomization effect during the operation of the existing rotating detonation combustion chamber. The present invention can be used in the field of rotating detonation combustion.

Description

Technical Field

[0001] The present invention belongs to the technical field of rotating detonation combustors, and specifically relates to a fuel automatic recovery system based on a rotating detonation combustor. Background Technique

[0002] In traditional aeroengines and gas turbine devices, the combustors are basically based on the isobaric combustion method, and its technical level has tended to be mature, and it is very difficult to further improve the thermal efficiency. Compared with the isobaric combustion method, due to the self-pressurization effect of the detonation wave in detonation combustion, the rotating detonation combustor based on the detonation combustion method theoretically has a higher thermal cycle efficiency, and at the same time has the advantages of a small combustor volume, a simple structure, and a fast heat release rate. Therefore, the rotating detonation combustor has broad application prospects in the fields of aeroengines and gas turbines and has become a research hotspot at home and abroad in recent years.

[0003] Generally, gaseous fuel or liquid fuel is mainly used in rotating detonation combustors. Compared with gaseous fuel, liquid fuel has a higher energy density and is safer to store. The rotating detonation combustor based on liquid fuel has obvious advantages when applied to power plants (such as airplanes and ships). Generally speaking, the propagation speed of the rotating detonation wave can reach the order of several kilometers per second, and the corresponding single-cycle time is less than the millisecond order. When liquid fuel is used, it is difficult to complete atomization, evaporation, and mixing with the oxidant in a very short time, and the fuel cannot all participate in detonation combustion. Therefore, unreacted fuel will accumulate at the bottom of the combustor. If this part of the fuel is not discharged in time, on the one hand, the equivalence ratio in the local area will increase sharply, resulting in an increase in the emissions of pollutants such as CO and NO x and so on; on the other hand, part of the fuel will be discharged from the combustor with the burned gas, and the mass of the fuel participating in combustion will decrease, which is not conducive to economy. Therefore, for a rotating detonation combustor based on liquid fuel, it is necessary to design a fuel recovery device that can automatically recover the fuel that has not participated in detonation combustion in the combustor, improve the economy of the combustor, and reduce pollutant emissions, which has an important role in the engineering application of the rotating detonation combustor. Summary of the Invention

[0004] The purpose of the present invention is to propose a fuel automatic recovery system based on a rotating detonation combustor, aiming to solve the problems in traditional rotating detonation combustors that the fuel cannot all participate in combustion quickly, resulting in oil accumulation at the bottom of the combustor and a sharp increase in the local equivalence ratio, which leads to poor stable operation characteristics of the combustor, poor fuel economy, and high pollutant emissions. The present invention can be applied to fields such as gas turbines and aeroengines.

[0005] The present invention is implemented by adopting the following technical solutions:

[0006] An automatic fuel recovery system based on a rotating detonation combustor, comprising an air supply chamber, a fuel supply chamber, an annular combustion chamber, and a fuel recovery system;

[0007] The annular combustion chamber is a ring-shaped cavity structure composed of an outer combustion chamber ring and an inner combustion chamber column distributed along the same axis. The air supply holes and fuel supply holes are located at the head of the annular combustion chamber;

[0008] The air supply chamber and the fuel supply chamber are respectively a ring-shaped cavity structure composed of an intake chamber component and a combustion chamber cover plate and a cylindrical cavity structure, both located at the head of the annular combustion chamber;

[0009] The fuel recovery system is embedded within the outer combustion chamber ring.

[0010] A further improvement of the present invention lies in that the axial directions of the air supply holes and the fuel supply holes form an angle of 120° with the axis of the annular combustion chamber.

[0011] A further improvement of the present invention lies in that ignition device installation holes are reserved on the outer combustion chamber ring for installing an igniter.

[0012] A further improvement of the present invention lies in that a cooling water ring cavity is arranged on the side of the outer combustion chamber ring close to the inner wall surface, and the temperature of the combustion chamber wall surface is reduced by circulating cooling water supplied.

[0013] A further improvement of the present invention lies in that the fuel recovery system includes a fuel recovery chamber, a compression airbag, fuel recovery holes, an outer ring movable plate, and an outer ring movable plate hinge;

[0014] The fuel recovery chamber is located inside the outer combustion chamber ring, axially close to the head of the combustion chamber, and circumferentially located on one side of the bottom of the combustion chamber, and the circumferential angle is 10°. The compression airbag is located inside the fuel recovery chamber. The outer ring movable plate is located at the boundary between the fuel recovery chamber and the annular combustion chamber. One end is the outer ring movable plate hinge, and the rotation of the outer ring movable plate is realized through the outer ring movable plate hinge, thereby controlling whether the annular combustion chamber is communicated with the fuel recovery chamber. When the annular combustion chamber is communicated with the fuel recovery chamber, the fuel droplets that have not participated in the detonation combustion in time in the annular combustion chamber flow into the fuel recovery chamber under the action of gravity;

[0015] The fuel recovery holes are located at the bottom of the fuel recovery chamber, one end is communicated with the fuel recovery chamber, and the other end is connected to the fuel recovery pipeline of the fuel recovery system.

[0016] A further improvement of the present invention lies in that the fuel recovery chamber is a fan-shaped cavity structure.

[0017] A further improvement of the present invention lies in that the angle between the fuel recovery chamber and the axis of the combustion chamber is 60°, and its function is to lead the fuel in the fuel recovery chamber from the annular combustion chamber to the fuel recovery pipeline.

[0018] A further improvement of the present invention lies in that the supply system of the annular combustion chamber includes an air supply pipeline, a fuel supply pipeline, an air source, a fuel tank, a solenoid valve, a pressure regulating valve and a solenoid valve control unit;

[0019] The air supply pipeline is used to supply the air from the air source to the air supply chamber of the annular combustion chamber, and the fuel supply pipeline is used to supply the fuel from the fuel tank to the fuel supply chamber of the combustion chamber. Solenoid valves, pressure regulating valves and solenoid valve control units are provided on both the air supply pipeline and the fuel supply pipeline. The solenoid valve and the solenoid valve control unit automatically control whether air and fuel are supplied through computer instructions, and the pressure regulating valve controls the supply pressure of air and fuel.

[0020] A further improvement of the present invention lies in that the fuel recovery system outside the annular combustion chamber includes a fuel recovery pipeline and an anti-backfire device. One end of the fuel recovery pipeline is connected to the fuel recovery hole, and the other end is connected to the fuel tank, and is used to guide the fuel flowing out of the fuel recovery hole back to the fuel tank. The anti-backfire device is located on the fuel recovery pipeline.

[0021] The present invention has at least the following beneficial technical effects:

[0022] A fuel automatic recovery system based on a rotating detonation combustion chamber provided by the present invention adopts an embedded fuel automatic recovery device, which can timely recover the fuel accumulated at the bottom of the combustion chamber, effectively avoid the occurrence of a locally fuel-rich area in the combustion chamber, ensure the stability of the combustion chamber operation, improve the economy of the combustion chamber, and at the same time reduce the pollutant emissions of the combustion chamber. When the combustion chamber operates stably, the fuel automatic recovery device will not affect the flow field structure in the combustion chamber, nor cause performance loss of the combustion chamber. In addition, the fuel automatic recovery device basically adopts mechanical devices, with reasonable design, which can ensure the reliability and stability of the work. Brief Description of the Drawings

[0023] Figure 1 It is a schematic structural diagram of a rotating detonation combustion chamber;

[0024] Figure 2 It is a sectional view of the rotating detonation combustion chamber A-A (mode 1);

[0025] Figure 3 It is a sectional view of the rotating detonation combustion chamber B-B;

[0026] Figure 4 It is a structural diagram of the fuel recovery chamber of the combustion chamber (mode 1);

[0027] Figure 5 It is the supply system of the rotating detonation combustion chamber;

[0028] Figure 6 It is a sectional view of the rotating detonation combustion chamber A-A of mode 2 (mode 2);

[0029] Figure 7 It is the structural diagram of the fuel recovery chamber in the combustion chamber (mode 2).

[0030] Description of reference numerals:

[0031] 1 is the combustion chamber cover plate, 2 is the intake chamber component, 3 is the air inlet hole, 4 is the air supply chamber, 5 is the air supply hole, 6 is the fuel inlet hole, 7 is the fuel supply chamber, 8 is the fuel supply hole, 9 is the outer ring of the combustion chamber, 10 is the inner column of the combustion chamber, 11 is the annular combustion chamber, 12 is the fuel recovery chamber, 13 is the compression airbag, 14 is the fuel recovery hole, 15 is the outer ring movable plate, 16 is the hinge of the outer ring movable plate, 17 is the cooling water ring chamber, 18 is the ignition device installation hole, 19 is the screw, 20 is the screw installation hole, 21 is the igniter, 22 is the anti-backfire device, 23 is the solenoid valve, 24 is the pressure regulating valve, 25 is the solenoid valve control unit, 26 is the air supply pipeline, 27 is the fuel supply pipeline, 28 is the fuel recovery pipeline, 29 is the fuel storage tank, 30 is the air gas source. Specific embodiments

[0032] Hereinafter, exemplary embodiments of the present disclosure will be described in more detail with reference to the accompanying drawings. Although the exemplary embodiments of the present disclosure are shown in the drawings, it should be understood that the present disclosure can be implemented in various forms and should not be limited by the embodiments set forth herein. On the contrary, these embodiments are provided so that the present disclosure can be more thoroughly understood and the scope of the present disclosure can be fully conveyed to those skilled in the art. It should be noted that, without conflict, the embodiments in the present invention and the features in the embodiments can be combined with each other. Hereinafter, the present invention will be described in detail with reference to the drawings and in combination with the embodiments.

[0033] Refer to Figure 1 and Figure 2 As shown in

[0034] An automatic fuel recovery system based on a rotating detonation combustion chamber provided by the present invention includes an air supply chamber 4, a fuel supply chamber 7, an annular combustion chamber 11, and a fuel recovery chamber 12.

[0035] Air and fuel are supplied to the annular combustion chamber 11 from the side near the head of the combustion chamber (left side). Through 8 circumferentially evenly distributed air inlet holes 3, air is supplied from the air source to the air supply chamber 4. Through 120 circumferentially evenly distributed air supply holes 5, air is supplied from the air supply chamber 4 to the annular combustion chamber 11. Fuel is supplied to the fuel supply chamber 4 through the fuel inlet hole 6 at the center position of the combustion chamber, and through 120 circumferentially evenly distributed fuel supply holes 8, fuel is supplied from the fuel supply chamber 7 to the annular combustion chamber 11. The axial directions of the air supply holes 5 and the fuel supply holes 8 form an angle of 120° with the axis of the annular combustion chamber 11. The air supply chamber 4 and the fuel supply chamber 7 are respectively an annular cavity structure composed of the intake chamber component 2 and a cylindrical cavity structure composed of the combustion chamber cover plate 1, and are both located at the head of the annular combustion chamber 11. Ignition device mounting holes 18 are reserved on the outer ring 9 of the combustion chamber for installing the igniter 21, which plays an ignition role when the engine starts to work. A cooling water ring cavity 17 is arranged on the side of the outer ring 9 of the combustion chamber close to the inner wall surface. By circulating and supplying cooling water, the temperature of the combustion chamber wall surface is reduced, which can effectively prevent problems such as damage to the combustion chamber wall surface material caused by overheating of the combustion chamber wall surface.

[0036] Refer to Figures 2 to 4 As shown, the fuel recovery system in the combustion chamber is embedded inside the outer ring 9 of the combustion chamber, and includes a fuel recovery chamber 12, a compression airbag 13, a fuel recovery hole 14, an outer ring movable plate 15, and an outer ring movable plate hinge 16. Among them, the fuel recovery chamber 12 is a fan-shaped cavity structure, located inside the outer ring 9 of the combustion chamber, axially close to the head of the combustion chamber, and circumferentially located on the bottom side of the combustion chamber, and the circumferential angle is 10°. The compression airbag 13 is located inside the fuel recovery chamber 12. When the compression airbag 13 is filled with air, the volume of the compression airbag 13 increases, thereby changing the volume of the fuel recovery chamber 12. When the compression airbag 13 deflates, the volume decreases. The compression airbag 13 is made of a flexible material with high pressure resistance and easy deformation. The outer ring movable plate 15 is located at the boundary between the fuel recovery chamber 12 and the annular combustion chamber 11. One end is the outer ring movable plate hinge 16. Through the outer ring movable plate hinge 16, the rotation of the outer ring movable plate 15 is realized, thereby controlling whether the annular combustion chamber 11 is communicated with the fuel recovery chamber 12. When the annular combustion chamber 11 is communicated with the fuel recovery chamber 12, the fuel droplets in the annular combustion chamber 11 that have not participated in the detonation combustion in time flow into the fuel recovery chamber 12 under the action of gravity. The fuel recovery hole 14 is located at the bottom of the fuel recovery chamber 12, and the angle with the axis of the combustion chamber is 60°. One end is communicated with the fuel recovery chamber 12, and the other end is connected to the fuel recovery pipeline 28. Its main function is to export the fuel in the fuel recovery chamber 12 from the annular combustion chamber 11 to the fuel recovery pipeline 28.

[0037] Refer to Figure 5As shown, the supply system of the annular combustion chamber 11 includes an air supply pipeline 26, a fuel supply pipeline 27, an air source 29, a fuel tank 30, a solenoid valve 23, a pressure regulating valve 24 and a solenoid valve control unit 25. The function of the air supply pipeline 26 is to supply the air from the air source 29 to the air supply chamber 4 of the annular combustion chamber 11, and the function of the fuel supply pipeline 27 is to supply the fuel from the fuel tank 30 to the fuel supply chamber 7 of the combustion chamber. The air supply pipeline 26 and the fuel supply pipeline 27 are both designed with a solenoid valve 23, a pressure regulating valve 24 and a solenoid valve control unit 25. The solenoid valve 23 and the solenoid valve control unit 25 can automatically control whether air and fuel are supplied through computer instructions; the pressure regulating valve 24 controls the supply pressure of air and fuel. The fuel recovery system outside the annular combustion chamber 11 includes a fuel recovery pipeline 28, an anti-backfire device 22 and a solenoid valve 23. One end of the fuel recovery pipe 28 is connected to the fuel recovery hole 14, and the other end is connected to the fuel tank 30. The main purpose is to guide the fuel flowing out of the fuel recovery hole 14 back to the fuel tank 30. The anti-backfire device 22 is located on the fuel recovery pipe 28 and close to the side of the fuel recovery hole 14. The interior is a densely distributed microporous structure. The diameter of the micropores must be significantly smaller than the minimum size that the flame can maintain and propagate. The main function is to block the flame in the combustion chamber from propagating to the fuel recovery pipe and the fuel tank to prevent danger.

[0038] Embodiment 1:

[0039] This embodiment is mainly applicable to the state where the rotating detonation combustion chamber operates stably and the fuel recovery system does not collect fuel, and is described below with reference to the accompanying drawings.

[0040] Combination Figures 1 to 4 When the rotating detonation combustion chamber is working stably, air and fuel are supplied to the annular combustion chamber through the air supply hole and the fuel supply hole respectively. The propagation characteristic of the rotating detonation wave is that it propagates circumferentially at the head of the combustion chamber, and the peak pressure of the rotating detonation wave (that is, the pressure in the area where the rotating detonation wave is located) is significantly higher than the average pressure in other areas of the annular combustion chamber. At this moment, the rotating detonation wave propagates at the head of the combustion chamber, but does not propagate to the area where the fuel recovery chamber is located. The filling pressure of the air in the compressed airbag is controlled to be higher than the average pressure of the combustion chamber, but lower than the peak pressure of the rotating detonation wave. Since the air pressure in the compressed airbag is higher than the average pressure of the combustion chamber, the compressed airbag is filled with sufficient air, and the volume expands to the maximum, squeezing the outer ring movable plate to rotate to a position flush with the inner wall of the outer ring of the combustion chamber, and the fuel in the combustion chamber that does not participate in the detonation combustion cannot flow into the fuel recovery chamber, that is, the fuel recovery system does not collect the fuel droplets in the combustion chamber.

[0041] Embodiment 2:

[0042] This embodiment is mainly applicable to the state where the rotating detonation combustor operates stably and the fuel recovery system collects the fuel that has not participated in the detonation combustion. The following will be described with reference to the accompanying drawings.

[0043] Combined with Figure 5 , during the stable operation of the rotating detonation combustor, when the rotating detonation wave propagates circumferentially in the combustor to the area where the fuel recovery chamber is located. Since the peak pressure of the rotating detonation wave is much higher than the filling pressure of the air in the compression airbag, the rotating detonation wave squeezes the outer ring movable plate, causing the outer ring movable plate to squeeze the compression airbag, discharging the air in the compression airbag, and the volume of the compression airbag decreases. At the same time, the outer ring movable plate is subjected to the squeezing effect and rotates counterclockwise by a certain angle, and the fuel collection hole communicates with the annular combustion chamber. At this time, the fuel droplets that have not participated in the detonation combustion in the annular combustion chamber flow into the fuel collection hole along the outer ring movable plate, then flow into the fuel collection pipeline from the fuel collection hole, and finally return to the fuel tank. At the same time, since a flame arrestor is designed in the fuel recovery pipeline, when the flame propagates to the flame arrestor, it cannot continue to propagate, ensuring the safety of the experimental system.

[0044] After the rotating detonation wave propagates past the area where the fuel recovery chamber is located, due to the rapid decrease in pressure in this area, the system returns to the state of Embodiment 1 again. When the rotating detonation combustor operates stably, the rotating detonation wave always propagates circumferentially at the head of the combustor, that is, the circumferential position of the rotating detonation wave changes at all times. Therefore, the fuel recovery system also continuously and alternately repeats the working states of Embodiment 1 and Embodiment 2, and at the same time, there will be no state where a large amount of fuel accumulates and cannot be discharged from the annular combustion chamber.

[0045] Embodiment 3:

[0046] This embodiment is mainly applicable to the state where the rotating detonation combustor ends its operation and the fuel recovery system collects the fuel that has not participated in the detonation combustion. The following will be described with reference to the accompanying drawings.

[0047] Combined with Figure 5 , when the operation of the rotating detonation combustor ends, the solenoid valve control unit closes the solenoid valves of the air supply pipeline and the fuel supply pipeline, and air and fuel cannot continue to be supplied to the annular combustion chamber. Therefore, the rotating detonation wave cannot continue to propagate and extinguishes. At the same time, the air in the compression airbag is controlled to be discharged, and the volume of the compression airbag decreases and cannot continue to squeeze the outer ring movable plate. The outer ring movable plate is affected by gravity and rotates counterclockwise by a certain angle, and the fuel collection hole communicates with the annular combustion chamber (the same position as in Embodiment 2). At this time, the fuel droplets that have not participated in the detonation combustion in the annular combustion chamber flow into the fuel collection hole along the outer ring movable plate, then flow into the fuel collection pipeline from the fuel collection hole, and finally return to the fuel tank, effectively avoiding the occurrence of oil accumulation in the annular combustion chamber when it is not working, and improving the safety and economy of the system.

[0048] The specific embodiments of the present invention have been described in detail above in conjunction with the accompanying drawings and specific implementation processes. However, the present invention is not limited to the above embodiments. Without departing from the principle of the present invention, those skilled in the art can make various changes and optimizations to the above methods.

Claims

1. An automatic fuel recovery system based on a rotating detonation combustor, characterized in that, It includes an air supply chamber (4), a fuel supply chamber (7), an annular combustion chamber (11) and a fuel recovery system; The annular combustion chamber (11) is a ring cavity structure composed of an outer combustion chamber ring (9) and an inner combustion chamber column (10) distributed along the same axis. The air supply holes (5) and fuel supply holes (8) are located at the head of the annular combustion chamber (11); The air supply chamber (4) and the fuel supply chamber (7) are a ring cavity structure and a cylindrical cavity structure composed of an intake chamber component (2) and a combustion chamber cover plate (1) respectively, and both are located at the head of the annular combustion chamber (11); The fuel recovery system is embedded in the outer combustion chamber ring (9); The axial directions of the air supply holes (5) and the fuel supply holes (8) form an angle of 120° with the axis of the annular combustion chamber (11); The fuel recovery system includes a fuel recovery chamber (12), a compression airbag (13), a fuel recovery hole (14), an outer ring movable plate (15) and an outer ring movable plate hinge (16); The fuel recovery chamber (12) is located inside the outer combustion chamber ring (9), close to the head of the combustion chamber along the axial direction, and on the bottom side of the combustion chamber along the circumferential direction, and the circumferential angle is 10°. The compression airbag (13) is located inside the fuel recovery chamber (12). The outer ring movable plate (15) is located at the boundary between the fuel recovery chamber (12) and the annular combustion chamber (11). One end is the outer ring movable plate hinge (16). The rotation of the outer ring movable plate (15) is realized through the outer ring movable plate hinge (16), thereby controlling whether the annular combustion chamber (11) is communicated with the fuel recovery chamber (12). When the annular combustion chamber (11) is communicated with the fuel recovery chamber (12), the fuel droplets that have not participated in the detonation combustion in time in the annular combustion chamber (11) flow into the fuel recovery chamber (12) under the action of gravity; The fuel recovery hole (14) is located at the bottom of the fuel recovery chamber (12). One end is communicated with the fuel recovery chamber (12), and the other end is connected to the fuel recovery pipeline (28) of the fuel recovery system.

2. The fuel automatic recovery system based on a rotating detonation combustor according to claim 1, wherein Ignition device mounting holes (18) are reserved on the outer combustion chamber ring (9) for mounting an igniter (21).

3. The fuel automatic recovery system based on a rotating detonation combustor according to claim 1, wherein, A cooling water ring cavity (17) is arranged on the side of the outer combustion chamber ring (9) close to the inner wall surface to reduce the temperature of the combustion chamber wall surface by circulating cooling water supply.

4. The fuel automatic recovery system based on a rotating detonation combustor according to claim 1, characterized in that, The fuel recovery chamber (12) is a fan-shaped cavity structure.

5. A fuel automatic recovery system based on a rotating detonation combustor according to claim 1, characterized in that, The angle between the fuel recovery chamber (12) and the axis of the combustion chamber is 60°, and its function is to lead the fuel in the fuel recovery chamber (12) from the annular combustion chamber (11) into the fuel recovery pipeline (28).

6. The fuel automatic recovery system based on a rotating detonation combustor according to claim 1, characterized in that, The supply system of the annular combustion chamber (11) includes an air supply pipeline (26), a fuel supply pipeline (27), an air gas source (29), a fuel tank (30), a solenoid valve (23), a pressure regulating valve (24) and a solenoid valve control unit (25); An air supply pipeline (26) is used to supply the air from an air source (29) to an air supply chamber (4) of an annular combustion chamber (11). A fuel supply pipeline (27) is used to supply the fuel from a fuel tank (30) to a fuel supply chamber (7) of the combustion chamber. Solenoid valves (23), pressure regulating valves (24) and solenoid valve control units (25) are provided on both the air supply pipeline (26) and the fuel supply pipeline (27). The solenoid valves (23) and the solenoid valve control units (25) automatically control whether the air and the fuel are supplied through computer instructions, and the pressure regulating valves (24) control the supply pressures of the air and the fuel.

7. The fuel automatic recovery system based on a rotating detonation combustor according to claim 6, characterized in that, The fuel recovery system outside the annular combustion chamber (11) includes a fuel recovery pipeline (28) and a backfire prevention device (22). One end of the fuel recovery pipeline (28) is connected to a fuel recovery hole (14), and the other end is connected to the fuel tank (30), and is used to guide the fuel flowing out of the fuel recovery hole (14) back to the fuel tank (30). The backfire prevention device (22) is located on the fuel recovery pipeline (28).

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