Rocket engine with strong oxidant fuel

Abstract

The utility model discloses a rocket engine with strong oxidant fuel, which belongs to the technical field of aerospace and comprises an engine throat, an engine shell is fixedly mounted at the top of the engine throat, a mixing component is arranged at the top of the engine shell, and a heat expansion prevention component is arranged at the bottom of the engine throat. According to the utility model, through the arrangement of the heat expansion prevention assembly and the mixing assembly, the function of improving the combustion efficiency of the engine is realized, and meanwhile, the function of heat protection on the spray head part can be realized, so that the waste of resources caused by combustion when an oxidizing agent and fuel are not fully mixed is avoided; and meanwhile, the situation that the rocket engine cannot perform effective thermal protection due to the fact that uniform distribution of heat of the nozzle diverging section cannot be achieved when the rocket engine is used, and the heat prevention and insulation effect of the rocket engine is reduced can be avoided.

Description

Technical Field

[0001] The utility model belongs to the field of aerospace technology, and in particular relates to a rocket engine with strong oxidant fuel. Background Art

[0002] Rockets and space vehicles require the support of a power propulsion system during the process of changing orbits and adjusting attitudes, and the rocket engine is the most critical component of the space propulsion system. In liquid rocket engines, the combustion chamber is also an important component of the liquid rocket engine, which generates all or most of the thrust of the liquid rocket engine.

[0003] With the continuous development of science and technology, there are more and more types of rocket engines. However, since the caliber of the existing air inlet duct is fixed and cannot be changed, the oxidizer and fuel are not fully mixed before combustion, resulting in a waste of resources, which in turn leads to low combustion efficiency of the engine. In addition, the rocket engine cannot achieve uniform distribution of heat in the nozzle expansion section when in use, which leads to the inability of the rocket engine to perform effective thermal protection, reduces the rocket engine's anti-insulation effect, and easily causes the nozzle to be damaged due to the high exhaust gas temperature. In order to solve the above problems, a rocket engine with a strong oxidizer fuel is urgently needed to solve the above problems. Utility Model Content

[0004] The purpose of the utility model is to solve the problem that with the continuous development of science and technology, there are more and more types of rocket engines, but since the caliber of the existing air inlet duct is fixed and cannot be changed, the oxidant and fuel are not fully mixed before combustion, resulting in a waste of resources, which in turn leads to a low combustion efficiency of the engine, and the rocket engine cannot achieve a uniform distribution of heat in the nozzle expansion section when in use, which leads to the rocket engine being unable to perform effective thermal protection, reducing the rocket engine's anti-insulation effect, and easily causing the nozzle to be damaged due to the high exhaust gas temperature. A rocket engine with a strong oxidant fuel is proposed.

[0005] In order to achieve the above-mentioned purpose, the utility model adopts the following technical scheme: a rocket engine with strong oxidizer fuel, including an engine throat, an engine casing is fixedly installed on the top of the engine throat, a mixing assembly is arranged on the top of the engine casing, and a heat protection expansion assembly is arranged on the bottom of the engine throat.

[0006] As a further description of the above technical solution:

[0007] The heat protection extension component includes a first nozzle, the bottom end of the engine throat is fixedly mounted with the first nozzle, the inner wall of the first nozzle is fixedly mounted with a heat protection sleeve, and the bottom of the first nozzle is fixedly mounted with a fitting ring.

[0008] As a further description of the above technical solution:

[0009] A mounting frame is fixedly mounted on the outer wall of the first nozzle, a mounting hole is arranged inside the mounting frame, and a connecting frame is fixedly mounted on the outer wall of the fitting ring.

[0010] As a further description of the above technical solution:

[0011] The mixing assembly comprises an injector, the injector is fixedly mounted on the top of the engine housing, a plurality of air holes are arranged on the top of the injector, and a fuel inlet is fixedly mounted on the top surface of the injector.

[0012] As a further description of the above technical solution:

[0013] An oxidant inlet is fixedly installed on the top surface of the injector, a mixing tube is fixedly installed on the bottom of the injector, an air supply pipe is fixedly installed on the bottom of the injector, a fan is fixedly installed inside the air supply pipe, and a mixing tube is fixedly installed on the bottom end of the air supply pipe.

[0014] As a further description of the above technical solution:

[0015] A valve is fixedly installed on the outside of the mixing tube, a sealing ring is fixedly installed on the outside of the valve, and a second nozzle is fixedly installed on the bottom end of the valve.

[0016] In summary, due to the adoption of the above technical solution, the beneficial effects of the utility model are:

[0017] 1. In the utility model, a heat-proof extension component and a mixing component are provided. When the device is used, when the engine needs to be started, liquid fuel and oxidant are added to the fuel inlet and the oxidant inlet into the injector for atomization. The atomized fuel and oxidant collide in the mixing tube to mix. At this time, the fan is started, and the rotation of the fan inhales external air through the air holes provided on the top of the injector, and supplies air to the engine casing through the air supply pipe, the mixing tube and the valve. At the same time, the mixed fuel and oxidant are sent to the engine casing together, and diffused through the second nozzle, so that the mixed fuel and oxidant can be fully burned. The role of the heat-proof sleeve is that when the first nozzle is spraying, the heat-proof sleeve is attached to the inner side of the first nozzle to play a heat-proof role, and the multiple fitting rings and the connecting frame can evenly absorb the heat on the inner wall of the first nozzle, thereby achieving The heat on the inner wall of the first nozzle is evenly distributed, thereby achieving the effect of thermal protection, and the mounting frame and the mounting holes arranged therein not only facilitate the installation of the nozzle part inside the rocket, but also prevent the high heat of the fitting ring from causing damage to the inside of the rocket. Through this design, not only the function of improving the combustion efficiency of the engine is achieved, but also the function of thermal protection of the nozzle part is achieved, avoiding the waste of resources due to the failure of the oxidant and the fuel to be fully mixed before combustion, thereby causing the low combustion efficiency of the engine. At the same time, it can also avoid the rocket engine being unable to achieve uniform distribution of heat in the nozzle expansion section when in use, thereby causing the rocket engine to be unable to perform effective thermal protection, reducing the rocket engine's anti-insulation effect, and easily causing the nozzle to be damaged due to the high exhaust gas temperature. In addition, it is simple and convenient to use and has strong practicality.

[0018] 2. In the utility model, by providing a valve and a sealing ring, during the use of the device, the setting of the valve can control whether the mixed oxidant and fuel enter the interior of the engine casing, and can prevent the flame from entering the mixing tube due to excessive combustion inside the engine casing. The sealing ring is used to prevent the leakage of fuel gas, which may cause an explosion inside the engine. The utility model is simple and convenient to use and has strong practicality. BRIEF DESCRIPTION OF THE DRAWINGS

[0019] Figure 1 This is a three-dimensional structural schematic diagram of a rocket engine with a strong oxidant fuel proposed by the utility model;

[0020] Figure 2 This is a schematic diagram of the explosion three-dimensional structure of a rocket engine with a strong oxidant fuel proposed by the utility model;

[0021] Figure 3 This is a schematic diagram of the explosion three-dimensional structure of an anti-jump component in a rocket engine with a strong oxidant fuel proposed by the utility model;

[0022] Figure 4 The utility model discloses a schematic diagram of an exploded three-dimensional structure of an adjusting component in a rocket engine with a strong oxidant fuel.

[0023] Legend:

[0024] 1. Engine casing; 2. Engine throat; 3. Heat protection extension assembly; 31. First nozzle; 32. Heat protection sleeve; 33. Mounting frame; 34. Fitting ring; 35. Connecting frame; 4. Mixing assembly; 41. Injector; 42. Fuel inlet; 43. Fan; 44. Air supply pipe; 45. Oxidant inlet; 46. Mixing pipe; 47. Sealing ring; 48. Valve; 49. Second nozzle. DETAILED DESCRIPTION

[0025] The following will be combined with the drawings in the embodiments of the utility model to clearly and completely describe the technical solutions in the embodiments of the utility model. Obviously, the described embodiments are only part of the embodiments of the utility model, not all of the embodiments. Based on the embodiments of the utility model, all other embodiments obtained by ordinary technicians in this field without creative work are within the scope of protection of the utility model.

[0026] See also Figure 1-4 The utility model provides a technical solution: a rocket engine with a strong oxidant fuel, comprising an engine throat 2, an engine housing 1 is fixedly mounted on the top of the engine throat 2, a mixing assembly 4 is arranged on the top of the engine housing 1, and a heat protection extension assembly 3 is arranged on the bottom of the engine throat 2;

[0027] The heat protection extension component 3 includes a first nozzle 31, the first nozzle 31 is fixedly installed at the bottom end of the engine throat 2, a heat protection sleeve 32 is fixedly installed on the inner wall of the first nozzle 31, a fitting ring 34 is fixedly installed on the bottom of the first nozzle 31, a mounting frame 33 is fixedly installed on the outer wall of the first nozzle 31, a mounting hole is provided inside the mounting frame 33, a connecting frame 35 is fixedly installed on the outer wall of the fitting ring 34, the mixing component 4 includes an injector 41, the engine An injector 41 is fixedly mounted on the top of the engine housing 1, a plurality of air holes are arranged on the top of the injector 41, a fuel inlet 42 is fixedly mounted on the top surface of the injector 41, an oxidant inlet 45 is fixedly mounted on the top surface of the injector 41, a mixing tube 46 is fixedly mounted on the bottom of the injector 41, an air supply pipe 44 is fixedly mounted on the bottom of the injector 41, a fan 43 is fixedly mounted inside the air supply pipe 44, and a mixing tube 46 is fixedly mounted on the bottom end of the air supply pipe 44;

[0028] The specific implementation method is as follows: when the device is used, when the engine needs to be started, liquid fuel and oxidant are added to the fuel inlet 42 and the oxidant inlet 45 into the injector 41 for atomization, and the atomized fuel and oxidant collide in the mixing tube 46 to mix. At this time, the fan 43 is started, and the rotation of the fan 43 inhales external air through the air holes set at the top of the injector 41, and supplies air to the engine housing 1 through the air supply pipe 44, the mixing tube 46 and the valve 48, and at the same time, the mixed fuel and oxidant are sent to the engine housing 1 together, and diffused through the second nozzle 49. , so that the mixed fuel and oxidant can be fully burned, and the role of the heat protection sleeve 32 is that when the first nozzle is spraying, the heat protection sleeve 32 is attached to the inner side of the first nozzle to play a heat protection role, and the multiple fitting rings 34 and the connecting frame 35 can evenly absorb the heat on the inner wall of the first nozzle, so as to achieve a uniform distribution of heat on the inner wall of the first nozzle, thereby achieving a heat protection effect, and the mounting frame 33 and the mounting holes arranged therein not only facilitate the installation of the nozzle part inside the rocket, but also prevent the high heat of the fitting ring 34 from causing damage to the inside of the rocket;

[0029] A valve 48 is fixedly installed on the outside of the mixing tube 46 , a sealing ring 47 is fixedly installed on the outside of the valve 48 , and a second nozzle 49 is fixedly installed on the bottom end of the valve 48 .

[0030] The specific implementation method is as follows: during the use of the device, the setting of the valve 48 can control whether the mixed oxidant and fuel enter the interior of the engine casing 1, and can prevent the flame from entering the mixing tube 46 due to excessive combustion inside the engine casing 1, while the sealing ring 47 is used to prevent the fuel gas from leaking, which may cause an explosion inside the engine.

[0031] Working principle: When the device is used, when the engine needs to be started, liquid fuel and oxidant are added to the fuel inlet 42 and the oxidant inlet 45 into the injector 41 for atomization. The atomized fuel and oxidant collide in the mixing tube 46 to mix. At this time, the fan 43 is started. The rotation of the fan 43 inhales external air through the air holes set on the top of the injector 41, and supplies air to the engine casing 1 through the air supply pipe 44, the mixing tube 46 and the valve 48. At the same time, the mixed fuel and oxidant are sent to the engine casing 1 together, and diffused through the second nozzle 49, so that the mixed fuel and oxidant can be fully burned. The function of the heat shield 32 is that when the first nozzle is spraying, the heat shield 32 is attached to the inner side of the first nozzle. It plays a role in heat protection, and multiple fitting rings 34 and connecting frames 35 can evenly absorb the heat on the inner wall of the first nozzle, so as to achieve uniform distribution of heat on the inner wall of the first nozzle, and then achieve the effect of thermal protection. The mounting frame 33 and the mounting holes arranged therein not only facilitate the installation of the nozzle part inside the rocket, but also prevent the high heat of the fitting ring 34 from causing damage to the inside of the rocket. During the use of the device, the setting of the valve 48 can control whether the mixed oxidant and fuel enter the interior of the engine casing 1, and can prevent the flame from entering the mixing tube 46 due to excessive combustion inside the engine casing 1, and the sealing ring 47 is to prevent the leakage of fuel gas, which may cause an explosion inside the engine.

[0032] The above description is only a preferred specific implementation manner of the present invention, but the protection scope of the present invention is not limited thereto. Any technician familiar with the technical field can make equivalent replacements or changes within the technical scope disclosed by the present invention according to the technical scheme and the utility model concept of the present invention, which should be covered by the protection scope of the present invention.

Claims

1. A rocket engine with a strong oxidizer fuel, comprising an engine throat (2), characterized in that An engine casing (1) is fixedly mounted on the top of the engine throat (2), a mixing assembly (4) is arranged on the top of the engine casing (1), and a heat protection expansion assembly (3) is arranged on the bottom of the engine throat (2).

2. A rocket engine with a strong oxidizer fuel according to claim 1, characterized in that: The heat protection extension component (3) comprises a first nozzle (31), the first nozzle (31) is fixedly mounted on the bottom end of the engine throat (2), a heat protection sleeve (32) is fixedly mounted on the inner wall of the first nozzle (31), and a fitting ring (34) is fixedly mounted on the bottom of the first nozzle (31).

3. A rocket engine with strong oxidizer fuel according to claim 2, characterized in that: A mounting frame (33) is fixedly mounted on the outer wall of the first nozzle (31), a mounting hole is provided inside the mounting frame (33), and a connecting frame (35) is fixedly mounted on the outer wall of the fitting ring (34).

4. A rocket engine with strong oxidizer fuel according to claim 3, characterized in that: The mixing assembly (4) comprises an injector (41), the injector (41) is fixedly mounted on the top of the engine housing (1), a plurality of air holes are arranged on the top of the injector (41), and a fuel inlet (42) is fixedly mounted on the top surface of the injector (41).

5. A rocket engine with a strong oxidizer fuel according to claim 4, characterized in that: An oxidant inlet (45) is fixedly installed on the top surface of the injector (41), a mixing tube (46) is fixedly installed on the bottom of the injector (41), an air supply pipe (44) is fixedly installed on the bottom of the injector (41), a fan (43) is fixedly installed inside the air supply pipe (44), and a mixing tube (46) is fixedly installed at the bottom end of the air supply pipe (44).

6. A rocket engine with strong oxidizer fuel according to claim 5, characterized in that: A valve (48) is fixedly mounted on the outside of the mixing tube (46), a sealing ring (47) is fixedly mounted on the outside of the valve (48), and a second nozzle (49) is fixedly mounted on the bottom end of the valve (48).

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