Integrated structure of ramjet combustion chamber and tank

Abstract

The application discloses a kind of stamping engine combustion chamber and storage tank integrated structure, including storage tank, hollow in storage tank interior, and the through hole is set in storage tank upper and is penetrated;Combustion chamber is set in through hole, and combustion chamber both ends respectively extend to the outside of storage tank, and the accommodating space that can accommodate fuel is formed between combustion chamber and storage tank;Through integrated design storage tank and combustion chamber, the whole that it is composed is pressure vessel structure, can carry certain internal pressure without structural damage, compared with the storage tank and combustion chamber that independent respectively in prior art, and the connecting structure and pipeline structure that a certain space is arranged between storage tank and combustion chamber, the fuel loading capacity of a kind of stamping engine combustion chamber and storage tank integrated structure of the application can be improved, improve the cruising range of hypersonic aircraft, reduce the structure weight ratio;At the same time, integrated design and only simple mechanical, electrical connection outside, for different use requirements of hypersonic aircraft have strong compatibility, high universality advantage.

Description

Technical Field

[0001] This disclosure relates to the field of hypersonic aircraft and ramjet engine technology, specifically to an integrated structure of a ramjet engine combustion chamber and storage tank. Background Technology

[0002] With the rapid development of technology, near space has gradually become a new arena for competition among military equipment among nations. This airspace lies between the minimum flight altitude of space orbiting vehicles and the maximum flight altitude of aircraft. It has an altitude advantage over the lower airspace, while also posing a close-range threat to space stations and satellites in outer space.

[0003] The development of hypersonic vehicle technology is another epoch-making milestone for humankind after the invention of airplanes, breaking the sound barrier, and entering space. Its flight airspace is mainly in near-space, with a cruising speed of Mach 6-15. To occupy near-space, countries have made the development of hypersonic technology a crucial path, and the development of high-performance propulsion technology is the core key technology for the development of hypersonic vehicles. Ramjet engines are the best power source for hypersonic flight within the atmosphere, with no rotating parts and good economic efficiency.

[0004] Currently, the fuel tank and combustion chamber of the ramjet engine in hypersonic vehicles are separate systems. Such ramjet engines require a portion of the tank space for structural and pipeline connections, resulting in low overall space utilization, loss of tank space, reduced fuel load, and consequently, reduced cruise range of hypersonic vehicles. At the same time, the presence of numerous connecting structures increases the proportion of structural weight, sacrificing the payload weight of the hypersonic vehicle. Summary of the Invention

[0005] In view of the above-mentioned defects or deficiencies in the prior art, it is desirable to provide an integrated structure for the combustion chamber and reservoir of a ramjet engine.

[0006] In a first aspect, this application provides an integrated structure for the combustion chamber and reservoir of a ramjet engine, comprising:

[0007] The storage tank has an axis extending along a first direction, the interior of the storage tank is hollow, and a through opening is provided on the storage tank along the first direction.

[0008] A combustion chamber, wherein the axis of the combustion chamber extends along the first direction, the combustion chamber is disposed within the through opening, and both ends of the combustion chamber extend to the outside of the storage tank;

[0009] A space for containing fuel is formed between the combustion chamber and the storage tank.

[0010] According to the technical solution provided in the embodiments of this application, the storage tank includes:

[0011] A shell, wherein the shell axis extends along the first direction, the shell is hollow inside, and both ends of the shell are open structures;

[0012] A first end cap is detachably disposed at one end of the housing and communicates with the interior of the housing, and a first opening is provided through the first end cap;

[0013] The second end cap is fixedly disposed at the other end of the shell and communicates with the interior of the shell. A second opening is provided through the second end cap.

[0014] According to the technical solution provided in the embodiments of this application, the combustion chamber includes:

[0015] A combustion chamber section is disposed inside the housing. The combustion chamber section is hollow inside, its axis extends along the first direction, and both ends of the combustion chamber section are open structures.

[0016] An isolation section is disposed at one end of the combustion chamber section and is connected to the interior of the combustion chamber section. The isolation section is slidably adapted to be disposed inside the first opening.

[0017] An expansion section is provided at the other end of the combustion chamber section and is connected to the interior of the combustion chamber section. The expansion section is fixedly provided inside the second opening.

[0018] According to the technical solution provided in the embodiments of this application, a cooling channel is provided inside the circumferential sidewall of the combustion chamber section, and a first input end and a first output end are respectively provided on the sidewalls at both ends of the combustion chamber section, and the two ends of the cooling channel are respectively connected to the first input end and the first output end.

[0019] According to the technical solution provided in the embodiments of this application, a plurality of fuel injection plates are uniformly arranged on the circumferential sidewall of the combustion chamber section. The fuel injection plate is provided with a fuel injection channel inside. One end of the fuel injection plate extends into the accommodating space and is provided with a fuel inlet communicating with the fuel injection channel. The other end of the fuel injection plate extends into the interior of the combustion chamber section. The portion of the fuel injection plate located inside the combustion chamber section is provided with a plurality of fuel injection holes communicating with the fuel injection channel.

[0020] According to the technical solution provided in the embodiments of this application, the first end cap is provided with an injection port and a recovery port. The injection port and the first input end are connected through a first pipeline, and the recovery port and the first output end are connected through a second pipeline.

[0021] According to the technical solution provided in the embodiments of this application, the first end cap is provided with an input port, and the input port and the oil supply port are connected through a third pipeline.

[0022] According to the technical solution provided in the embodiments of this application, an igniter interface is provided on the combustion chamber section, and an igniter is provided in the igniter interface for igniting the oil sprayed by the fuel injector plate. A cable interface is provided on the first end cap, and a cable conduit is provided inside the accommodating space. The cable conduit has a first end communicating with the cable interface and a second end communicating with the igniter interface. A cable is provided inside the cable conduit. One end of the cable passes through the cable interface and extends to the outside of the storage tank, and the other end of the cable is connected to the igniter.

[0023] According to the technical solution provided in the embodiments of this application, the first end cap is provided with a fuel port that communicates with the accommodating space for injecting fuel into the accommodating space.

[0024] According to the technical solution provided in the embodiments of this application, it also includes an oil supply system and a control system. The oil supply system is located outside the storage tank. The injection port, the recovery port, and the input port are respectively connected to the oil supply system through pipelines. The cable extends to one end outside the storage tank and is connected to the control system.

[0025] In summary, this technical solution specifically discloses an integrated structure of a ramjet engine combustion chamber and a fuel tank, including a fuel tank, the fuel tank axis extending along a first direction, and the interior of the fuel tank being hollow, with a through opening provided on the fuel tank along the first direction; the combustion chamber is disposed within the through opening, and both ends of the combustion chamber extend to the outside of the fuel tank respectively, forming a space between the combustion chamber and the fuel tank capable of accommodating fuel.

[0026] The integrated design of the fuel tank and combustion chamber forms a pressure vessel structure that can withstand a certain internal pressure without structural damage. Compared with the existing technology where the fuel tank and combustion chamber are separate and require connecting and piping structures that occupy a certain space, the integrated structure of the ramjet engine combustion chamber and fuel tank in this application can increase fuel loading, improve the cruise range of hypersonic vehicles, and reduce the structural weight ratio. At the same time, the integrated design has only simple mechanical and electrical connections with the outside, which has the advantages of strong compatibility and high versatility for hypersonic vehicles with different usage requirements. Attached Figure Description

[0027] Other features, objects, and advantages of this application will become more apparent from the following detailed description of non-limiting embodiments with reference to the accompanying drawings:

[0028] Figure 1 This is a schematic diagram of an integrated structure of a ramjet engine combustion chamber and storage tank.

[0029] Figure 2This is a side view of an integrated structure of a ramjet engine combustion chamber and storage tank.

[0030] Figure 3 This is a side view of the combustion chamber.

[0031] Figure 4 This is a schematic diagram of the paint spray plate.

[0032] The following are the labels in the diagram: 1. Storage tank; 2. Combustion chamber; 3. Shell; 4. First end cap; 5. Second end cap; 6. Combustion chamber section; 7. Isolation section; 8. Expansion section; 9. Injector plate; 10. Injection hole; 11. Inlet; 12. Recycle port; 13. First pipeline; 14. Second pipeline; 15. Input port; 16. Third pipeline; 17. Ignition device; 18. Cable interface; 19. Cable conduit; 20. Cable; 21. Fuel interface. Detailed Implementation

[0033] The present application will now be described in further detail with reference to the accompanying drawings and embodiments. It should be understood that the specific embodiments described herein are merely illustrative of the invention and not intended to limit it. Furthermore, it should be noted that, for ease of description, only the parts relevant to the invention are shown in the accompanying drawings.

[0034] It should be noted that, unless otherwise specified, the embodiments and features described in this application can be combined with each other. This application will now be described in detail with reference to the accompanying drawings and embodiments.

[0035] Example 1

[0036] Please refer to Figure 1 An integrated structure for a ramjet engine combustion chamber and reservoir, comprising:

[0037] Storage tank 1, the axis of storage tank 1 extends along the first direction, the interior of storage tank 1 is hollow, and a through opening is provided on storage tank 1 along the first direction.

[0038] Combustion chamber 2, the axis of combustion chamber 2 extends along the first direction, combustion chamber 2 is disposed in the through opening, and both ends of combustion chamber 2 extend to the outside of storage tank 1 respectively;

[0039] A space for holding fuel is formed between combustion chamber 2 and storage tank 1.

[0040] The first direction is Figure 1 Mid-horizontal direction.

[0041] Specifically, the storage tank 1 can be a hollow cylindrical structure with a through-hole along its axis. The combustion chamber 2 is located inside the through-hole, with both ends extending to the outside of the storage tank 1. Thus, the outer wall of the combustion chamber 2 serves as the inner wall of the storage tank 1, and the space formed between the combustion chamber 2 and the storage tank 1 is used to hold fuel. In the prior art, the storage tank 1 and the combustion chamber 2 are independent systems, and corresponding connecting structures, pipeline structures, etc., are set between the storage tank 1 and the combustion chamber 2, occupying part of the space of the storage tank 1, reducing the fuel loading capacity, and increasing the overall weight. In this application, the connecting structures, pipeline structures, etc., are removed from the internal space of the storage tank 1, and the outer wall of the combustion chamber 2 separates the storage tank 1 and the combustion chamber 2. The space occupied by the original connecting structures, pipeline structures, etc., is used to hold fuel, increasing the fuel loading capacity and reducing the weight. Furthermore, the integrated form of the storage tank 1 and the combustion chamber 2 reduces the material consumption during manufacturing and saves costs.

[0042] Furthermore, tank 1 includes:

[0043] The shell 3 has an axis extending along a first direction, the interior of the shell 3 is hollow, and both ends of the shell 3 are open structures;

[0044] The first end cap 4 is detachably disposed at one end of the housing 3 and communicates with the interior of the housing 3. A first opening is provided through the first end cap 4.

[0045] The second end cap 5 is fixedly disposed at the other end of the housing 3 and is connected to the inside of the housing 3. A second opening is provided through the second end cap 5.

[0046] Specifically, the first end cap 4, the shell 3, and the second end cap 5 are arranged sequentially along the first direction, wherein the first end cap 4 and the shell 3 are connected by screws, and the second end cap 5 and the shell 3 are welded together.

[0047] Furthermore, combustion chamber 2 includes:

[0048] Combustion chamber section 6 is located inside the housing 3. The interior of combustion chamber section 6 is hollow, its axis extends along the first direction, and both ends of combustion chamber section 6 are open structures.

[0049] Isolation section 7 is located at one end of combustion chamber section 6 and is connected to the interior of combustion chamber section 6. Isolation section 7 is slidably adapted to be located inside the first opening.

[0050] Expansion section 8 is located at the other end of combustion chamber section 6 and is connected to the interior of combustion chamber section 6. Expansion section 8 is fixedly located inside the second opening.

[0051] Specifically, the isolation section 7, the combustion chamber section 6, and the expansion section 8 are arranged sequentially along the first direction. The isolation section 7 and the combustion chamber section 6, as well as the combustion chamber section 6 and the expansion section 8, are connected by flanges to ensure a tight connection.

[0052] The expansion section 8 is adapted to be disposed in the second opening, one end of which extends to the outside of the tank 1, and the expansion section 8 and the second end cap 5 are fixedly connected by screws.

[0053] The isolation section 7 is slidably adapted to be disposed in the first opening, with one end extending to the outside of the storage tank 1. Through the sliding cooperation between the isolation section 7 and the first end cap 4, the axial displacement generated by thermal expansion during the operation of the ramjet engine can be released.

[0054] It should be noted that the isolation section 7 and the expansion section 8 are thin-walled structures that are immersed in fuel. The thin-walled structure can significantly reduce the weight of the combustion chamber, improve the thrust-to-weight ratio and payload capacity of the aircraft, and make it easier to transfer heat and be cooled by the fuel. When heated, the thinner wall surface generates less stress due to thermal expansion, which can reduce the risk of structural deformation or cracking caused by temperature changes.

[0055] Furthermore, a cooling channel is provided inside the circumferential sidewall of the combustion chamber section 6, and a first input end and a first output end are respectively provided on the sidewalls at both ends of the combustion chamber section 6, with the two ends of the cooling channel connected to the first input end and the first output end respectively;

[0056] Furthermore, such as Figure 2 As shown, the first end cap 4 is provided with an injection port 11 and a recovery port 12. The injection port 11 is connected to the first input end through the first pipeline 13, and the recovery port 12 is connected to the first output end through the second pipeline 14.

[0057] Therefore, cooling medium is injected through injection port 11, and the cooling medium enters the cooling channel through the first input end to cool the circumferential sidewall of combustion chamber section 6, and then is delivered to recovery port 12 through the first output end; the cooling medium is fuel oil.

[0058] Furthermore, such as Figure 3 and Figure 4 As shown, multiple fuel injection plates 9 are evenly arranged on the circumferential sidewalls of the combustion chamber section 6. The fuel injection plate 9 has a fuel injection channel inside. One end of the fuel injection plate 9 extends into the accommodating space and is provided with a fuel inlet communicating with the fuel injection channel. The other end of the fuel injection plate 9 extends into the interior of the combustion chamber section 6. The part of the fuel injection plate 9 located inside the combustion chamber section 6 is provided with multiple fuel injection holes 10 communicating with the fuel injection channel.

[0059] Furthermore, the first end cap 4 is provided with an inlet 15, and the inlet 15 and the oil outlet are connected through a third pipeline 16.

[0060] Specifically, there can be 6 fuel injection plates 9, which are evenly arranged on the circumferential sidewalls of the combustion chamber section 6; there can be 11 fuel injection holes 10, of which 5 fuel injection holes 10 are provided on the two opposite sidewalls of the fuel injection plate 9, and 1 fuel injection hole 10 is provided at one end of the fuel injection plate 9 located inside the combustion chamber section 6.

[0061] Fuel is supplied to the fuel injector plate 9 through the inlet 15, and the fuel injector plate 9 can spray fuel into the combustion chamber section 6 to ignite the fuel and achieve complete combustion.

[0062] An igniter interface is provided on the combustion chamber section 6, and an igniter 17 is provided inside the igniter interface for igniting the oil sprayed by the fuel injector 9. A cable interface 18 is provided on the first end cap 4, and a cable conduit 19 is provided inside the accommodating space. The cable conduit 19 has a first end connected to the cable interface 18 and a second end connected to the igniter interface. A cable 20 is provided inside the cable conduit 19. One end of the cable 20 passes through the cable interface 18 and extends to the outside of the storage tank 1. The other end of the cable 20 is connected to the igniter 17.

[0063] Specifically, after the fuel injector 9 injects fuel into the combustion chamber section 6, the fuel in the combustion chamber is ignited by the igniter 17, thereby generating thrust for the engine.

[0064] The cable conduit 19 also has a third end connected to the second end cap 5.

[0065] Furthermore, it also includes an oil supply system and a control system. The oil supply system is located outside the storage tank 1. The injection port 11, recovery port 12, and input port 15 are respectively connected to the oil supply system through pipelines. The cable 20 extends to one end outside the storage tank 1 and is connected to the control system.

[0066] Therefore, both the fuel supply system and the control system are located outside the tank 1, and the fuel supply system is connected to the containment space pipeline, which can realize the suction of fuel. The fuel supply system can make the fuel circulate into the cooling channel to achieve multiple active cooling of the combustion chamber section 6. After the combustion chamber section 6 is cooled, the fuel supply system delivers fuel to the fuel injection plate 9. The fuel injection plate 9 sprays fuel into the combustion chamber section 6. The control system sends a command to the igniter 17 through the cable 20. The igniter 17 ignites the fuel, and the fuel burns to generate thrust for the engine.

[0067] It should be noted that the igniter 17 is a non-flammable igniter that can meet the ignition requirements of more than 10 times in a single task.

[0068] Furthermore, the first end cap 4 is provided with a fuel inlet 21 that communicates with the accommodating space for injecting fuel into the accommodating space.

[0069] It should be noted that the first end cap 4 is connected to the shell 3, the first end cap 4 is connected to the isolation section 7, the isolation section 7 is connected to the combustion chamber section 6, the combustion chamber section 6 is connected to the expansion section 8, the expansion section 8 is connected to the second end cap 5, the cable duct 19 is connected to the second end cap 5, and the first end cap 4, the fuel injection plate 9 and the combustion chamber section 6 are all connected by a sealed structure, which is a metal skeleton sealing ring made of high temperature alloy.

[0070] Working principle: Before ignition, fuel is extracted from the containment space through the fuel supply system and fed into the cooling channel through the injection port 11 and the first pipe 13 to cool the combustion chamber section 6. Subsequently, the fuel is returned to the fuel supply system and containment space through the second pipe 14 and the recovery port 12. Through multiple cooling cycles, the temperature of the combustion chamber 2 during use is reduced, thereby increasing the overall service life of the combustion chamber section 6. After cooling, the fuel is delivered to the fuel injector 9 through the third pipe 16 via the fuel supply system. The fuel injector 9 sprays fuel into the combustion chamber section 6 through the fuel injection holes 10. The control system sends an ignition command to the igniter 17, which ignites the fuel sprayed from the fuel injection holes 10, thereby generating thrust for the engine.

[0071] The device's storage tank 1 and combustion chamber 2 are designed as an integrated unit. The overall design has reserved interfaces for connection with the fuel supply system, control system, etc. It has only simple mechanical and electrical connections with the outside world, which has the advantages of strong compatibility and high versatility for hypersonic aircraft with different usage requirements.

[0072] The above description is merely a preferred embodiment of this application and an explanation of the technical principles employed. Those skilled in the art should understand that the scope of the invention involved in this application is not limited to technical solutions formed by specific combinations of the above-described technical features, but should also cover other technical solutions formed by arbitrary combinations of the above-described technical features or their equivalents without departing from the inventive concept. For example, technical solutions formed by substituting the above features with (but not limited to) technical features with similar functions disclosed in this application.

Claims

1. An integrated structure for the combustion chamber and reservoir of a ramjet engine, characterized in that, include: Storage tank (1), the axis of the storage tank (1) extends along a first direction, the storage tank (1) is hollow inside, and a through opening is provided on the storage tank (1) along the first direction; Combustion chamber (2), the axis of which extends along the first direction, the combustion chamber (2) is disposed in the through opening, and both ends of the combustion chamber (2) extend to the outside of the storage tank (1); A storage space for containing fuel is formed between the combustion chamber (2) and the storage tank (1); the outer wall of the combustion chamber (2) is used to separate the storage tank (1) and the combustion chamber (2). The combustion chamber (2) includes a combustion chamber section (6), and a cooling channel is provided inside the circumferential sidewall of the combustion chamber section (6). A first input end and a first output end are respectively provided on the sidewalls at both ends of the combustion chamber section (6), and the two ends of the cooling channel are respectively connected to the first input end and the first output end. The fuel supply system extracts fuel from the containment space and inputs it into the cooling channel through the first input terminal to cool the combustion chamber section (6). Then the fuel returns to the fuel supply system and the containment space through the first output terminal. Through multiple cycles of cooling, the temperature of the combustion chamber (2) during use is reduced, thereby increasing the service life of the combustion chamber section (6).

2. The integrated structure of the combustion chamber and reservoir of a ramjet engine according to claim 1, characterized in that, The storage tank (1) includes: The shell (3) has an axis that extends along the first direction, the shell (3) is hollow inside, and both ends of the shell (3) are open structures; The first end cap (4) is detachably disposed at one end of the housing (3) and communicates with the interior of the housing (3). A first opening is provided through the first end cap (4). The second end cap (5) is fixedly disposed at the other end of the housing (3) and is connected to the interior of the housing (3). A second opening is provided through the second end cap (5).

3. The integrated structure of the combustion chamber and reservoir of a ramjet engine according to claim 2, characterized in that, The combustion chamber (2) includes: Combustion chamber section (6) is disposed inside the housing (3). The combustion chamber section (6) is hollow inside, its axis extends along the first direction, and both ends of the combustion chamber section (6) are open structures. An isolation section (7) is disposed at one end of the combustion chamber section (6) and is connected to the interior of the combustion chamber section (6). The isolation section (7) is slidably adapted to be disposed inside the first opening. Expansion section (8) is disposed at the other end of the combustion chamber section (6) and is connected to the interior of the combustion chamber section (6). The expansion section (8) is fixedly disposed inside the second opening.

4. The integrated structure of the combustion chamber and reservoir of a ramjet engine according to claim 3, characterized in that, Multiple fuel injection plates (9) are evenly arranged on the circumferential sidewall of the combustion chamber section (6). The fuel injection plate (9) has a fuel injection channel inside. One end of the fuel injection plate (9) extends into the accommodating space and is provided with a fuel inlet communicating with the fuel injection channel. The other end of the fuel injection plate (9) extends into the interior of the combustion chamber section (6). The part of the fuel injection plate (9) located inside the combustion chamber section (6) is provided with multiple fuel injection holes (10) communicating with the fuel injection channel.

5. The integrated structure of the combustion chamber and reservoir of a ramjet engine according to claim 4, characterized in that, The first end cap (4) is provided with an injection port (11) and a recovery port (12). The injection port (11) and the first input end are connected through a first pipeline (13), and the recovery port (12) and the first output end are connected through a second pipeline (14).

6. The integrated structure of the combustion chamber and reservoir of a ramjet engine according to claim 5, characterized in that, The first end cap (4) is provided with an inlet (15), and the inlet (15) and the oil outlet are connected through a third pipeline (16).

7. The integrated structure of the combustion chamber and reservoir of a ramjet engine according to claim 6, characterized in that, An igniter interface is provided on the combustion chamber section (6), and an igniter (17) is provided inside the igniter interface for igniting the oil sprayed from the fuel injector plate (9). A cable interface (18) is provided on the first end cap (4), and a cable conduit (19) is provided inside the accommodating space. The cable conduit (19) has a first end connected to the cable interface (18) and a second end connected to the igniter interface. A cable (20) is provided inside the cable conduit (19). One end of the cable (20) passes through the cable interface (18) and extends to the outside of the storage tank (1). The other end of the cable (20) is connected to the igniter (17).

8. The integrated structure of the combustion chamber and reservoir of a ramjet engine according to claim 7, characterized in that, The first end cap (4) is provided with a fuel port (21) that communicates with the accommodating space, for injecting fuel into the accommodating space.

9. The integrated structure of the combustion chamber and reservoir of a ramjet engine according to claim 8, characterized in that, It also includes an oil supply system and a control system. The oil supply system is located outside the tank (1). The injection port (11), the recovery port (12), and the input port (15) are respectively connected to the oil supply system through pipelines. The cable (20) extends to one end outside the tank (1) and is connected to the control system.

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