Stamping rotary detonation engine based on outer wall surface afterburning

Abstract

The ramjet rotary detonation engine comprises a main fuel supply device, a mixing device and a combustion chamber outer wall face, the main fuel supply device is connected with the mixing device and located in the combustion chamber outer wall face, a plurality of afterburning fuel nozzle sets are arranged on the combustion chamber outer wall face, and the main fuel supply device is connected with the mixing device and located in the combustion chamber outer wall face. The multiple afterburning fuel nozzle sets correspond to the position of the mixing device in the axial direction of the ramjet rotary detonation engine and are arranged at intervals in the axial direction, and each afterburning fuel nozzle set comprises a plurality of fuel nozzles distributed on the outer wall face of the combustion chamber in the circumferential direction. Multi-stage afterburning is formed on the outer wall face of the combustion chamber, rotary detonation can be stabilized, the thermal protection requirement of rotary detonation stamping on the wall face of the combustion chamber is lowered, and the thermal protection design of the wall face of the combustion chamber is simplified.

Description

Technical Field

[0001] The invention relates to a ramjet rotary detonation engine, belonging to the technical field of engines. Background Art

[0002] The rotating detonation combustion chamber usually adopts a coaxial annular cavity structure. The propellant (fuel and oxidizer) is continuously injected and mixed from the head of the rotating detonation combustion chamber in a non-premixed manner. After ignition and detonation, one or more detonation waves are formed in the combustion chamber, which propagate in a circumferential direction and consume the fuel, while the combustion chamber itself is stationary in the circumferential direction. The detonation products after the rotating detonation wave expand rapidly and flow in the axial direction, and are discharged at high speed at the combustion chamber outlet to generate thrust.

[0003] Since the rotating detonation combustion generated in the rotating detonation ramjet engine has a high heat release rate, coupled with the high total temperature of the incoming air, wall thermal protection is one of the problems that need to be urgently solved before the engineering application of the rotating detonation engine is realized. Summary of the invention

[0004] In view of the above-mentioned defects of the prior art, the task of the present invention is to provide a ramjet rotating detonation engine based on external wall supplemental combustion, so as to solve the problem of engine wall cooling and protection to prevent excessive temperature.

[0005] The technical solution of the present invention is as follows: a ramjet rotary detonation engine based on external wall surface supplemental combustion, comprising a main fuel supply device, a mixing device and an outer wall surface of a combustion chamber, wherein the main fuel supply device is connected to the mixing device and is located inside the outer wall surface of the combustion chamber, and a plurality of supplemental combustion fuel nozzle groups are arranged on the outer wall surface of the combustion chamber, wherein the plurality of supplemental combustion fuel nozzle groups correspond to the positions of the mixing device in the axial direction of the ramjet rotary detonation engine and are arranged axially at intervals, and each of the supplemental combustion fuel nozzle groups comprises a plurality of fuel nozzles distributed circumferentially on the outer wall surface of the combustion chamber.

[0006] Furthermore, the outer wall of the combustion chamber includes multiple wall segments, each of the wall segments includes equal straight segments, the diameters of the multiple wall segments increase from front to rear along the axial direction of the ramjet rotary detonation engine, and the supplementary combustion fuel nozzle group is arranged at the connection between adjacent wall segments.

[0007] Furthermore, adjacent wall segments are connected via flanges, the fuel nozzle is arranged on the flange, and the injection direction of the fuel nozzle is the axial direction of the ramjet rotary detonation engine.

[0008] Furthermore, the fuel nozzles of each of the supplementary combustion fuel nozzle groups are equally distributed in the circumferential direction of the outer wall surface of the combustion chamber.

[0009] Furthermore, the mixing device includes a reduced diameter section, a cylindrical straight section and a conical tail section arranged in sequence, the head end of the reduced diameter section is connected to the main fuel supply device, and a plurality of supplementary combustion fuel nozzle groups correspond to the position of the cylindrical straight section in the axial direction of the ramjet rotary detonation engine.

[0010] Furthermore, the conical tail section is located at the end of a plurality of wall segments, and the distance between the outer surface of the conical tail section and the inner surface of the wall segment first decreases and then increases from front to back along the axial direction of the ramjet rotary detonation engine.

[0011] Furthermore, the mixing device includes a reduced diameter section, a cylindrical straight section and a conical tail section which are arranged in sequence, the diameter of the reduced diameter section is smaller than the diameter of the main fuel supply device and the cylindrical straight section, and the inner surface of the outer wall of the combustion chamber corresponding to the reduced diameter section is straight in the axial direction of the ramjet rotary detonation engine.

[0012] Furthermore, the main fuel supply device is provided with a tapered section, and the distance between the outer surface of the tapered section and the inner surface of the outer wall of the combustion chamber increases from front to rear along the axial direction of the ramjet rotary detonation engine. A main fuel storage tank is provided in the main fuel supply device, and the tapered section is provided with a plurality of main fuel injection holes arranged along the circumferential direction. The main fuel injection holes inject the fuel in the main fuel storage tank into between the main fuel supply device and the outer wall of the combustion chamber.

[0013] Furthermore, the injection direction of the main fuel injection hole forms an axial angle of 30° to 60° with respect to the ramjet rotating detonation engine.

[0014] Furthermore, the main fuel injection holes are arranged at equal intervals in the circumferential direction of the tapered section, and the diameter of the main fuel injection holes is 0.3-0.5 mm.

[0015] The advantages of the present invention compared with the prior art are: The present invention provides a plurality of axially spaced supplementary combustion fuel nozzle groups on the outer wall of the combustion chamber to form multi-stage wall segmented supplementary combustion. After the fuel absorbs heat, the outer wall surface is cooled, thereby reducing the thermal protection requirements of the rotating detonation ramjet combustion chamber wall surface and simplifying the thermal protection design of the combustion chamber wall surface. At the same time, the fuel combustion of the multi-stage wall segmented supplementary combustion is utilized to produce the effect of stabilizing the rotating detonation, thereby avoiding the waste of high-speed air and further improving the performance of the rotating detonation combustion chamber. BRIEF DESCRIPTION OF THE DRAWINGS

[0016] Figure 1 This is a schematic diagram of the cross-sectional structure of a ramjet rotating detonation engine based on external wall afterburning.

[0017] Figure 2It is a schematic diagram of the three-dimensional structure of the main fuel supply device of the ramjet rotating detonation engine based on external wall afterburning.

[0018] Figure 3 This is a schematic diagram of the cross-sectional structure of the main fuel supply device of the ramjet rotating detonation engine based on external wall afterburning.

[0019] Figure 4 It is a schematic diagram of the three-dimensional structure of the mixing device of the ramjet rotating detonation engine based on external wall afterburning.

[0020] Figure 5 It is a schematic diagram of the cross-sectional structure of the mixing device of the ramjet rotating detonation engine based on external wall afterburning.

[0021] Figure 6 This is a schematic diagram of the three-dimensional structure of the first-stage wall segment of a ramjet rotating detonation engine based on external wall afterburning.

[0022] Figure 7 This is a schematic diagram of the cross-sectional structure of the first-stage wall segment of a ramjet rotating detonation engine based on external wall afterburning.

[0023] Figure 8 It is a schematic diagram of the three-dimensional structure of the secondary wall segment of a ramjet rotating detonation engine based on external wall afterburning.

[0024] Fig. 9 This is a schematic diagram of the cross-sectional structure of the secondary wall segment of a ramjet rotating detonation engine based on external wall afterburning.

[0025] Fig.10 It is a schematic diagram of the three-stage structure of the wall segment of the ramjet rotating detonation engine based on external wall afterburning.

[0026] Fig.11 It is a schematic diagram of the cross-sectional structure of the three-stage wall segment of a ramjet rotating detonation engine based on external wall afterburning.

[0027] Fig.12 It is a schematic diagram of the three-dimensional structure of the four-stage wall segment of a ramjet rotating detonation engine based on external wall afterburning.

[0028] Fig.13 This is a schematic diagram of the cross-sectional structure of the four-stage wall segment of a ramjet rotating detonation engine based on external wall afterburning. DETAILED DESCRIPTION

[0029] The present invention will be further described below in conjunction with the embodiments, but are not intended to limit the present invention.

[0030] Please combine Figures 1 to 3 As shown, the ramjet rotary detonation engine based on external wall surface supplementary combustion of this embodiment includes a main fuel supply device 1, a mixing device 2 and the outer wall surface of the combustion chamber.

[0031] The main fuel supply device 1 and the mixing device 2 are connected to each other and are arranged together inside the outer wall surface of the combustion chamber.

[0032] The main fuel supply device 1 is coaxially arranged along the exhaust gas emission direction with a front connecting section 101, a main fuel storage tank outer wall straight section 103, a main fuel storage tank outer wall tapered section 104 and a rear connecting section 106.

[0033] The main fuel supply device 1 is connected to the inner wall surface of the air intake passage matching the present invention through the thread of the front connecting section 101 .

[0034] The main fuel supply device 1 includes a main fuel storage tank 102, which is mainly used to store main fuel for ramjet rotation detonation combustion, preferably liquid kerosene with more practical value, but other liquid fuels may also be used.

[0035] Along the axial direction of the ramjet rotating detonation engine, that is, the exhaust gas discharge direction, the downstream of the straight section 103 of the outer wall of the main fuel storage tank is immediately followed by the tapered section 104 of the outer wall of the main fuel storage tank, and main fuel injection holes 105 are distributed at equal intervals along the circumferential direction on the tapered section 104 of the outer wall of the main fuel storage tank.

[0036] The injection direction of the main fuel injection hole 105 forms a certain angle α with the axial direction of the ramjet rotating detonation engine, preferably in the range of 30° to 60°, and the aperture of the main fuel injection hole 105 preferably ranges from 0.3 to 0.5 mm.

[0037] Please combine Figure 4 and Figure 5 As shown, the mixing device 2 is coaxially arranged at the rear end of the main fuel supply device 1 and is threadedly connected. The mixing device 2 includes a mixing device connecting section 201, a reduced diameter section 202, a cylindrical straight section 203 and a conical tail section 204, which are coaxially arranged in sequence along the axial direction of the ramjet rotary detonation engine.

[0038] The mixing device 2 is connected to the rear connecting section 106 of the main fuel supply device 1 through the thread of the mixing device connecting section 201 and is coaxially fixed.

[0039] The main function of the reduced diameter section 202 is to promote the mixing of liquid fuel and high-speed incoming air, and the presence of a stationary flame in the chamber formed by the reduced diameter section 202 and the outer wall of the combustion chamber can increase the temperature of the fuel / air mixture and further enhance the stability of the rotating detonation.

[0040] The cylindrical straight section 203 is a section of a cylinder with a constant diameter, followed by a conical tail section 204 , which is a cone whose cross-sectional area increases first and then decreases.

[0041] Please combine Figures 6 to 13 As shown, the outer wall of the combustion chamber includes multiple wall segments, which are specifically divided into a combustion chamber primary wall segment 3, a combustion chamber secondary wall segment 4, a combustion chamber tertiary wall segment 5 and a combustion chamber quaternary wall segment 6 in this embodiment.

[0042] The first-stage wall segment 3 of the combustion chamber is coaxially arranged outside the main fuel supply device 1, and the first-stage wall segment 3 of the combustion chamber is coaxially arranged in sequence along the axial direction of the ramjet rotary detonation engine with a first-stage front connecting flange 301, a first-stage straight section 302, a first-stage expansion section 303 and a first-stage rear connecting flange 305.

[0043] The combustion chamber first-stage wall segment 3 is fixedly connected to the air inlet matched with the present invention through a first-stage front connecting flange 301, and the front connecting flange 301 has connecting through holes arranged at equal intervals along the circumferential direction.

[0044] The first-stage straight section 302 is coaxially arranged with the straight section 103 on the outer wall of the main fuel storage tank, and together they form an annular channel with a constant flow area.

[0045] The first-stage expansion section 303 is coaxially arranged with the tapered section 104 on the outer wall of the main fuel storage tank. The inner diameter of the first-stage expansion section 303 gradually increases, corresponding to the gradually decreasing outer diameter of the tapered section 104 on the outer wall of the main fuel storage tank. The distance between the two increases from front to back along the axial direction of the ramjet rotary detonation engine, together forming an annular channel with a gradually increasing flow area.

[0046] The first-stage supplementary combustion fuel nozzle 304 is arranged at the first-stage rear connecting flange 305 at the rear end of the first-stage wall segment 3 of the combustion chamber to supplement the fuel to the combustion chamber and reduce the heat load on the combustion chamber wall.

[0047] The first-stage supplementary combustion fuel nozzles 304 are arranged at equal intervals along the circumferential direction of the first-stage rear connecting flange 305, and the exhaust gas discharge direction is consistent with the injection direction. The first-stage rear connecting flange 305 is arranged with connecting through holes at equal intervals along the circumferential direction for fixing with the second-stage front connecting flange 401.

[0048] The secondary wall segment 4 of the combustion chamber is coaxially arranged at the rear end of the primary wall segment 3 of the combustion chamber. The secondary wall segment 4 of the combustion chamber is coaxially arranged with a secondary front connecting flange 401, a secondary combustion chamber outer wall 402 and a secondary rear connecting flange 404 in sequence along the axial direction of the ramjet rotary detonation engine.

[0049] The secondary front connecting flange 401 is cooperatively connected with the primary rear connecting flange 305 to fix the secondary wall segment 4 of the combustion chamber.

[0050] The secondary supplementary combustion fuel nozzle 403 is similar to the primary supplementary combustion fuel nozzle 304. The secondary supplementary combustion fuel nozzle 403 is arranged at equal intervals along the circumferential direction of the secondary rear connecting flange 404, and the injection direction and exhaust gas discharge direction are consistent. The secondary rear connecting flange 404 is arranged with connecting through holes at equal intervals along the circumferential direction for fixing with the tertiary front connecting flange 501.

[0051] The combustion chamber tertiary wall segment 5 is coaxially arranged at the rear end of the combustion chamber secondary wall segment 4. The combustion chamber tertiary wall segment 5 is coaxially arranged with a tertiary front connecting flange 501, a tertiary combustion chamber outer wall 502 and a tertiary rear connecting flange 504 in sequence along the axial direction of the ramjet rotary detonation engine.

[0052] The third-stage front connecting flange 501 is connected with the second-stage rear connecting flange 404 to fix the third-stage wall segment 5 of the combustion chamber.

[0053] The third-stage supplementary combustion fuel nozzle 503 is similar to the first-stage supplementary combustion fuel nozzle 304 and the second-stage supplementary combustion fuel nozzle 403. The third-stage supplementary combustion fuel nozzle 503 is arranged at equal intervals along the circumferential direction of the third-stage rear connecting flange 504, and the injection direction is consistent with the exhaust gas discharge direction. The third-stage rear connecting flange 504 is provided with connecting through holes arranged at equal intervals along the circumferential direction for fixing with the fourth-stage front connecting flange 601.

[0054] The fourth stage wall segment 6 of the combustion chamber is coaxially arranged at the rear end of the third stage wall segment 5 of the combustion chamber. The fourth stage wall segment 6 of the combustion chamber is coaxially arranged with a fourth stage front connecting flange 601 and a fourth stage combustion chamber outer wall 602 in sequence along the axial direction of the ramjet rotary detonation engine.

[0055] The connection positions between the aforementioned combustion chamber primary wall segment 3, combustion chamber secondary wall segment 4, combustion chamber primary wall segment 5 and combustion chamber fourth wall segment 6, that is, the axial positions of the primary rear connecting flange 305 and the secondary front connecting flange 401, the secondary rear connecting flange 404 and the third front connecting flange 501, and the third rear connecting flange 504 and the fourth front connecting flange 601 in the ramjet rotary detonation engine correspond to the position of the cylindrical equal straight section 203 of the mixing device 2, and the combustion chamber secondary wall segment 4, the combustion chamber primary wall segment 5 and the combustion chamber fourth wall segment 6 are all equal straight sections, that is to say, the distances between the outer surface of the cylindrical equal straight section 203 of the mixing device 2 and the inner surfaces of the combustion chamber secondary wall segment 4, the combustion chamber primary wall segment 5 and the combustion chamber fourth wall segment 6 remain unchanged in the axial direction of the ramjet rotary detonation engine.

[0056] The operation process of the ramjet rotary detonation engine based on external wall afterburning is as follows: it is connected to the matching air inlet duct, and after the high-speed airflow completely flows through the ramjet rotary detonation combustion chamber, the main fuel supply device 1 starts to inject fuel. When the fuel and air are fully and evenly mixed, the mixture is detonated by the ignition device. The first-stage afterburning fuel nozzle 304, the second-stage afterburning fuel nozzle 403, and the third-stage afterburning fuel nozzle 503 are opened respectively for afterburning, thereby realizing afterburning of the rotary detonation combustion, and the low-temperature fuel injected by each stage of the afterburning fuel nozzle cools the outer wall of the combustion chamber where the afterburning fuel nozzle of this stage is located to reduce the heat load.

Claims

1. A ramjet rotary detonation engine based on external wall afterburning, comprising a main fuel supply device, a mixing device and an external wall surface of a combustion chamber, wherein the main fuel supply device is connected to the mixing device and is located inside the external wall surface of the combustion chamber, It is characterized in that A plurality of supplementary combustion fuel nozzle groups are arranged on the outer wall surface of the combustion chamber, and the plurality of supplementary combustion fuel nozzle groups correspond to the positions of the mixing devices in the axial direction of the ramjet rotary detonation engine and are arranged axially at intervals, and each of the supplementary combustion fuel nozzle groups includes a plurality of fuel nozzles distributed circumferentially on the outer wall surface of the combustion chamber.

2. The ramjet rotating detonation engine based on external wall afterburning according to claim 1, It is characterized in that The outer wall of the combustion chamber includes a plurality of wall segments, each of which includes an equal straight segment, and the diameters of the plurality of wall segments increase from front to rear along the axial direction of the ramjet rotary detonation engine, and the supplementary combustion fuel nozzle group is arranged at the connection between adjacent wall segments.

3. The ramjet rotating detonation engine based on external wall afterburning according to claim 2, It is characterized in that The adjacent wall segments are connected by flanges, the fuel nozzle is arranged on the flange, and the injection direction of the fuel nozzle is the axial direction of the ramjet rotary detonation engine.

4. The ramjet rotating detonation engine based on external wall afterburning according to any one of claims 1 to 3, It is characterized in that The fuel nozzles of each of the supplementary combustion fuel nozzle groups are equally distributed in the circumferential direction of the outer wall surface of the combustion chamber.

5. The ramjet rotating detonation engine based on external wall afterburning according to claim 2, It is characterized in that The mixing device includes a reduced diameter section, a cylindrical straight section and a conical tail section arranged in sequence, the head end of the reduced diameter section is connected to the main fuel supply device, and a plurality of supplementary combustion fuel nozzle groups correspond to the positions of the cylindrical straight sections in the axial direction of the ramjet rotary detonation engine.

6. The ramjet rotating detonation engine based on external wall afterburning according to claim 5, It is characterized in that The conical tail section is located at the end of a plurality of wall segments, and the distance between the outer surface of the conical tail section and the inner surface of the wall segment first decreases and then increases from front to back along the axial direction of the ramjet rotary detonation engine.

7. The ramjet rotating detonation engine based on external wall afterburning according to claim 1, It is characterized in that The mixing device includes a reduced diameter section, a cylindrical straight section and a conical tail section which are arranged in sequence. The diameter of the reduced diameter section is smaller than the diameters of the main fuel supply device and the cylindrical straight section. The inner surface of the outer wall of the combustion chamber corresponding to the reduced diameter section is straight in the axial direction of the ramjet rotary detonation engine.

8. The ramjet rotating detonation engine based on external wall afterburning according to claim 1, It is characterized in that The main fuel supply device is provided with a tapered section, and the distance between the outer surface of the tapered section and the inner surface of the outer wall of the combustion chamber increases from front to rear along the axial direction of the ramjet rotary detonation engine. A main fuel storage tank is provided in the main fuel supply device, and the tapered section is provided with a plurality of main fuel injection holes arranged along the circumferential direction. The main fuel injection holes inject the fuel in the main fuel storage tank into between the main fuel supply device and the outer wall of the combustion chamber.

9. The ramjet rotating detonation engine based on external wall afterburning according to claim 8, It is characterized in that The injection direction of the main fuel injection hole and the axial angle of the ramjet rotary detonation engine are 30° to 60°.

10. The ramjet rotating detonation engine based on external wall afterburning according to claim 8, It is characterized in that The main fuel injection holes are arranged at equal intervals in the circumferential direction of the tapered section, and the diameters of the main fuel injection holes are 0.3-0.5 mm.

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