Renewable cooling wedge-shaped liquid rocket engine

Abstract

The invention provides a renewable cooling wedge-shaped liquid rocket engine which is integrally formed through additive manufacturing 3D printing, the renewable cooling wedge-shaped liquid rocket engine comprises an engine body, a spray pipe and an oil inlet device, the oil inlet device comprises an oxidizing agent flow equalizing cavity and a fuel oil equalizing cavity, and oil equalizing grooves are formed in the oxidizing agent flow equalizing cavity and the fuel oil equalizing cavity; the oxidant flow equalizing chamber and the fuel oil equalizing chamber are communicated with the oxidant flow channel and the fuel oil flow channel; the fuel oil flow channel extends to the end, close to the oil inlet device, of the topmost end of the first combustion cavity along with the interior of the outer wall of the engine body. The oxidizing agent flow channel extends to the side, opposite to the tail end of the fuel oil flow channel, of the topmost end of the first combustion cavity along with the interior of the outer wall of the engine body, and the angle between the first combustion cavity and the center axis of the engine body is 70 degrees. And no backflow area exists in the second combustion chamber, so that larger engine thrust can be generated.

Description

TECHNICAL FIELD

[0001] The application belongs to the technical field of aerospace, and particularly relates to a renewable cooling wedge-shaped liquid rocket engine. BACKGROUND

[0002] The existing liquid rocket engine is composed of low-temperature oxidant (liquid oxygen) and normal-temperature propellant (kerosene) or low-temperature propellant (liquid hydrogen, liquid methane). The conventional liquid rocket engine processing pattern adopts traditional mechanical processing. The conventional liquid rocket engine has a long axial dimension, and the engine has a large size and heavy weight, which affects the performance of the engine, such as the thrust-to-weight ratio. The conventional liquid rocket engine has a high combustion temperature, a high wall surface temperature of the thrust chamber, a large cooling difficulty coefficient, and uneven fuel consumption, and the generated thrust is unstable. SUMMARY

[0003] (I) Technical problems solved

[0004] In view of the deficiencies of the prior art, the application solves the above problems, and the liquid rocket engine is made by using an integrated molding method, and the oil equalizing pipe and a reasonable thrust chamber angle are used to realize an engine with a smaller size, a larger thrust and better stability.

[0005] (II) Technical solutions

[0006] To achieve the above purpose, the application proposes a first scheme:

[0007] A renewable cooling wedge-shaped liquid rocket engine is integrally formed by additive manufacturing 3D printing, comprising:

[0008] An engine body, wherein the inner part of the engine body is a first combustion chamber and a second combustion chamber, the engine body is circular along the axial section, the first combustion chamber is arranged on the outer side of the second combustion chamber, and the outer wall surface of the first combustion chamber is provided with an oxidant flow channel and a fuel flow channel;

[0009] A nozzle is arranged on the left side of the second combustion chamber and is used for jetting, after the propellant is combusted in the combustion chamber, the high-temperature and high-pressure gas after combustion is jetted and accelerated through the nozzle to generate thrust;

[0010] An oil inlet device is arranged on the side of the second combustion chamber opposite to the nozzle, and comprises an oxidant flow equalizing chamber and a fuel oil equalizing chamber;

[0011] The oxidant flow equalization chamber and the fuel flow equalization chamber are each equipped with a flow equalization groove; the oxidant flow equalization chamber and the fuel flow equalization chamber are connected to the oxidant flow channel and the fuel flow channel; the fuel flow channel extends along the inner wall of the engine body to the top of the first combustion chamber near the fuel inlet device, that is, the inner wall of the top of the first combustion chamber near the fuel inlet device; the oxidant flow channel extends along the inner wall of the engine body to the top of the first combustion chamber opposite to the end of the fuel flow channel, that is, the inner wall of the top of the first combustion chamber near the nozzle.

[0012] Preferably, the oxidant flow equalization chamber is located on the outer wall of the fuel flow equalization chamber, and the oxidant flow equalization chamber and the fuel flow equalization chamber are independent of each other and are coaxial.

[0013] Preferably, the first combustion chamber is at an angle of 70° to the central axis of the engine body.

[0014] Preferably, the oxidant flow equalization chamber is provided with an oxidant inlet, and the fuel flow equalization chamber is provided with a fuel inlet. The oxidant inlet is located on the oxidant flow equalization chamber perpendicular to it, and the fuel inlet is located on the same axis as the fuel flow equalization chamber.

[0015] Preferably, the oxidant flow channel is provided with an oxidant nozzle at its end, and the fuel flow channel is provided with a fuel nozzle at its end.

[0016] Preferably, the oil leveling groove is one of the following: a serrated groove, a triangular groove, or a square groove.

[0017] Preferably, there are eight oxidizer channels and eight fuel channels evenly distributed on the engine body.

[0018] (III) Beneficial Effects

[0019] The invention features a more vortex system in the first combustion chamber, which is beneficial for stable flame combustion, and no backflow zone in the second combustion chamber, which can generate greater engine thrust. Attached Figure Description

[0020] Figure 1 This is a schematic diagram of the overall invention;

[0021] Figure 2 This is a side cross-sectional view of the present invention. Figure 1 ;

[0022] Figure 3 This is a side view of the oil equalization tank of the present invention;

[0023] Figure 4 This is a side view of the present invention;

[0024] Figure 5 This is a side cross-sectional view of the present invention. Figure 2 ;

[0025] Figure 6 This is a perspective view of the engine body of the present invention;

[0026] Figure 7 This is a comparison chart of data after the thrust chamber angle changes;

[0027] Figure 8 This is a data diagram showing the flow channels between the presence and absence of an oil equalization tank. Detailed Implementation

[0028] The technical solutions of the embodiments of the present invention will be clearly and completely described below with reference to the accompanying drawings. Obviously, the described embodiments are only some embodiments of the present invention, and not all embodiments. Based on the embodiments of the present invention, all other embodiments obtained by those skilled in the art without creative effort are within the scope of protection of the present invention.

[0029] Example 1: As Figures 1-5 As shown, a regeneratively cooled wedge-shaped liquid rocket motor, which is integrally formed by additive 3D printing, includes:

[0030] The engine body has a first combustion chamber 1-1 and a second combustion chamber 1-2 inside. The first combustion chamber 1-1 is arranged around the outside of the second combustion chamber 1-2. The outer wall of the engine body 1 has an oxidizer flow channel 4 and a fuel flow channel 5.

[0031] Nozzle 2 is located on the left side of the second combustion chamber 1-2 and is used to inject high-temperature and high-pressure gas after combustion. The high-temperature and high-pressure gas after combustion in the combustion chamber is injected through the nozzle to generate thrust.

[0032] The fuel inlet device 3 is located on one side of the second combustion chamber 1-2, opposite to the nozzle 2, and includes an oxidant flow equalization chamber 3-1 and a fuel flow equalization chamber 3-2; the oxidant flow equalization chamber 3-1 is located on the outer wall of the fuel flow equalization chamber 3-2, and the oxidant flow equalization chamber 3-1 and the fuel flow equalization chamber 3-2 are independent of each other;

[0033] Both the oxidant equalization chamber 3-1 and the fuel equalization chamber 3-2 are equipped with equalization grooves 3-3; the oxidant equalization chamber 3-1 and the fuel equalization chamber 3-2 are connected to the oxidant flow channel 4 and the fuel flow channel 5; the fuel flow channel 5 extends along the inner wall of the engine body 1 to the top of the first combustion chamber 1-1 near the fuel inlet device 3; the oxidant flow channel 4 extends along the inner wall of the engine body 1 to the top of the first combustion chamber 1-1 on the side opposite to the end of the fuel flow channel 5; the end of the oxidant flow channel 4 is equipped with an oxidant nozzle orifice 9, and the end of the fuel flow channel 5 is equipped with a fuel nozzle orifice 8. The first combustion chamber 1-1 is at a 70° angle to the central axis of the engine body 1, which enables more vortex systems and generates greater engine thrust. An oxidizer inlet 6 is provided on the oxidizer equalization chamber 3-1, and a fuel inlet 7 is provided on the fuel equalization chamber 3-2. Oxidizer and fuel enter their respective chambers through the inlets, and then flow into the first combustion chamber 1-1 along with the oxidizer channel 4 and fuel channel 5. They mix and burn within the first combustion chamber 1-1 through the oxidizer nozzle 9 at the end of the oxidizer channel 4 and the fuel nozzle 8 at the end of the fuel channel 5, generating thrust. The equalization groove 3-3 can be any of a serrated groove, a triangular groove, or a square groove. Eight oxidizer channels 4 and fuel channels 5 are evenly distributed on the engine body 1. Oxidizer and fuel enter their respective chambers through the inlets, and then flow into the eight oxidizer channels 4 and fuel channels 5, ultimately mixing and burning within the first combustion chamber 1-1 to generate thrust.

[0034] Comparative Example 1: Based on Example 1, the angle between the first combustion chamber 1-1 and the central axis of the engine body 1 is 60°.

[0035] Comparative Example 2: Based on Example 1, the angle between the first combustion chamber 1-1 and the central axis of the engine body 1 is 80°.

[0036] Comparative Example 3: Based on Example 1, the oil equalization tank 3-3 is not set up.

[0037] Data Comparison 1: To consider the influence of the angle between the first combustion chamber 1-1 and the central axis of the engine body 1 on the final thrust, the applicant adjusted the angle between the first combustion chamber 1-1 and the central axis of the engine body 1 (where the thrust chamber angle is the angle between the first combustion chamber 1-1 and the central axis of the engine body 1) while keeping other conditions constant, and finally obtained the following data: See attached... Figure 7

[0038] In summary, regarding the selection of the thrust chamber angle, when the thrust chamber angle is 70 degrees (e.g....), Figure 5 As shown in the figure, this is an important condition for the stable combustion and huge thrust of this application.

[0039] Data Comparison 2: To consider the impact of the fuel equalization groove on the uniformity of fuel distribution and combustion temperature distribution in the engine thrust chamber, the applicant ensured that, under identical conditions, data were compared between rocket engines with and without fuel equalization grooves. The total fuel mass flow rate was 640 g / s, and the fuel was introduced through eight channels (e.g., Figure 6 The eight flow channels in the system are analyzed, and the throughput of each channel is statistically analyzed, as follows:

[0040] 1 2 3 4 5 6 7 8 Mean (g / s) Comparative Example Three 85 90 88 80 70 78 75 74 80 Example One 82 84 83 79 80 75 78 79 80

[0041] Table 1: Flow rate values ​​in each channel

[0042] Also visible Figure 8 The data clearly shows the relationship between the flow channels with and without an oil equalization groove, indicating that the oil equalization groove provides better performance, is closer to the average value, and has a better oil supply effect than the oil equalization groove.

[0043] From Table 1 and Figure 8 It is known that when an oil equalization groove is installed, the flow rate fluctuation between each channel is relatively small, while when no oil equalization groove is installed, the flow rate fluctuation between each channel is relatively large. When the flow rate fluctuation between each channel is relatively large, the fuel and oxidant injected into the first combustion chamber will become uneven, which will affect the combustion uniformity of the combustion chamber, thereby affecting the temperature distribution of the combustion chamber wall, affecting engine cooling, and in severe cases, affecting engine life and thrust. However, after installing an oil equalization groove and setting the thrust chamber angle as in Example 1, the vortex system inside the combustion chamber is as follows: Figure 7 As shown, it is more uniform and stable.

Claims

1. A regeneratively cooled wedge-shaped liquid rocket motor, wherein the liquid rocket motor is integrally formed by additive manufacturing 3D printing, characterized in that, include: The engine body (1) has a first combustion chamber (1-1) and a second combustion chamber (1-2) inside. The first combustion chamber (1-1) is arranged around the outside of the second combustion chamber (1-2). The outer wall of the engine body (1) is provided with an oxidizer flow channel (4) and a fuel flow channel (5). The nozzle (2) is located on the left side of the second combustion chamber (1-2) and is used for injection; The fuel inlet device (3) is located on one side of the second combustion chamber (1-2) opposite to the nozzle (2), and includes an oxidant equalization chamber (3-1) and a fuel equalization chamber (3-2); The oxidant equalization chamber (3-1) and the fuel equalization chamber (3-2) are each provided with an equalization groove (3-3); the oxidant equalization chamber (3-1) and the fuel equalization chamber (3-2) are connected to the oxidant flow channel (4) and the fuel flow channel (5); the fuel flow channel (5) extends along the inner wall of the engine body (1) to the top of the first combustion chamber (1-1) near the end of the fuel inlet device (3); the oxidant flow channel (4) extends along the inner wall of the engine body (1) to the side of the top of the first combustion chamber (1-1) opposite to the end of the fuel flow channel (5).

2. The regeneratively cooled wedge-shaped liquid rocket engine according to claim 1, characterized in that, The oxidant flow equalization chamber (3-1) is located on the outer wall of the fuel oil equalization chamber (3-2), and the oxidant flow equalization chamber (3-1) and the fuel oil equalization chamber (3-2) are independent of each other.

3. A regeneratively cooled wedge-shaped liquid rocket engine according to claim 1, characterized in that, The angle between the first combustion chamber (1-1) and the central axis of the engine body (1) is 70°.

4. A regeneratively cooled wedge-shaped liquid rocket engine according to claim 1, characterized in that, The oxidant flow equalization chamber (3-1) is provided with an oxidant inlet (6), and the fuel oil equalization chamber (3-2) is provided with a fuel inlet (7).

5. A regeneratively cooled wedge-shaped liquid rocket engine according to claim 1, characterized in that, The oxidant flow channel (4) is provided with an oxidant nozzle (9) at its end, and the fuel flow channel (5) is provided with a fuel nozzle (8) at its end.

6. A regeneratively cooled wedge-shaped liquid rocket engine according to claim 1, characterized in that, The oil leveling groove (3-3) can be any one of a serrated groove, a triangular groove, or a square groove.

7. A regeneratively cooled wedge-shaped liquid rocket engine according to claim 1, characterized in that, The oxidant flow channel (4) and fuel flow channel (5) are evenly distributed in eight places on the engine body (1).

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