Liquid oxygen kerosene rocket engine chemical ignition system and method of use thereof

Abstract

The present application relates to the field of engine chemical ignition system, and particularly relates to a liquid oxygen kerosene rocket engine chemical ignition system and a use method thereof. The system comprises an igniter, an inlet guide pipe and an outlet guide pipe. The igniter comprises a barrel with two open ends, a first diaphragm valve and a second diaphragm valve arranged at the two ends of the barrel respectively, and a control gas pipe connected with the control ends of the first diaphragm valve and the second diaphragm valve respectively. When the engine is shut down, the fuel main valve is closed to cut off the kerosene supply of the ignition path, and a high pressure difference check valve or an ignition agent control valve does not need to be arranged in the ignition path. By reasonably arranging the inlet guide pipe and the outlet guide pipe, the dead space and the low flow rate area are eliminated. In the working process, the ignition agent is completely extruded by kerosene, and after the test, the ignition agent does not need to be discharged. The ignition agent removal valve and the related pipeline can be omitted. The system is simple, easy to use and maintain, and has high reliability.

Description

Technical Field

[0001] This invention relates to a chemical ignition system for an engine, specifically to a chemical ignition system for a liquid oxygen-kerosene rocket engine and its method of use. Background Technology

[0002] Liquid oxygen-kerosene rocket engines have the advantages of being non-toxic, pollution-free, and having high specific impulse. However, liquid oxygen and kerosene are non-spontaneous propellants, requiring an external energy source for engine ignition. Chemical igniters (a mixture of triethylaluminum and triethylboron) that spontaneously combust with oxidizers (oxygen and air) offer advantages such as reliable ignition and low ignition impact, and are widely used in liquid oxygen-kerosene rocket engine ignition systems.

[0003] Patent CN200910122426.3 discloses a chemical ignition device for a liquid oxygen kerosene engine. However, this chemical ignition system has many components and a complex structure. The timing of the ignition agent filling is coupled with the working timing of the other components, making timing adjustment difficult. Summary of the Invention

[0004] The purpose of this invention is to solve the technical problems of existing chemical ignition systems having many components and complex structures, and the coupling of the ignition agent filling sequence with the working sequence of other components, making timing adjustment difficult. The invention provides a chemical ignition system for liquid oxygen kerosene rocket engines and its usage method.

[0005] To achieve the above objectives, the technical solution adopted by the present invention is as follows:

[0006] A liquid oxygen-kerosene rocket engine chemical ignition system, characterized by:

[0007] Includes igniter, inlet conduit and outlet conduit;

[0008] The igniter includes a cylinder with openings at both ends, a first diaphragm valve and a second diaphragm valve respectively disposed at both ends of the cylinder, and a control gas pipeline whose output end is connected to the control ends of the first diaphragm valve and the second diaphragm valve respectively.

[0009] The cylinder body is fixedly installed on the thrust chamber of the engine, and the ignition agent is sealed inside;

[0010] One end of the inlet conduit is connected to one end of the second diaphragm valve, and the other end is connected to the engine's main fuel pipeline, close to the main fuel valve. One end of the outlet conduit is connected to one end of the first diaphragm valve, and the other end is connected to the engine's thrust chamber. By rationally setting the path of the main fuel pipeline, as well as the paths of the inlet and outlet conduits, the time it takes for kerosene to enter the engine's thrust chamber via the main fuel pipeline is greater than the time it takes for kerosene to enter the engine's thrust chamber via the inlet and outlet conduits, thus ensuring that there is no kerosene in the thrust chamber when the igniter enters it.

[0011] The input end of the control gas pipeline is connected to an external control gas source. The control gas output from the control gas source is used to open the first diaphragm valve and the second diaphragm valve during ignition. This allows the kerosene output from the fuel main valve to push the igniter into the thrust chamber, where it comes into contact with the liquid oxygen supplied to the thrust chamber and ignites spontaneously.

[0012] Furthermore, the control air duct includes a first straight tube, a bend tube, and a second straight tube;

[0013] One end of the first straight tube serves as the input end of the control air pipeline, connected to an external control air source, while the other end serves as the first output end of the control air pipeline, connected to the control end of the first diaphragm valve.

[0014] One end of the bent pipe is connected to the circumference of the first straight pipe, and the other end is connected to one end of the second straight pipe, and is connected to the first straight pipe and the second straight pipe respectively;

[0015] The other end of the second straight pipe serves as the second output end of the control gas pipeline, which is connected to the control end of the second diaphragm valve.

[0016] The axial direction of both the first and second straight pipes is parallel to the radial direction of the thrust chamber.

[0017] Furthermore, the axial direction of the cylinder is parallel to the axial direction of the thrust chamber, and the axis of the cylinder coincides with the axis of the first diaphragm valve and the second diaphragm valve.

[0018] Furthermore, the inlet conduit is a straight pipe, and its axis is set parallel to the axis of the thrust chamber; the diameter of the inlet conduit is larger than that of the outlet conduit.

[0019] The outlet conduit includes a first sub-tube, a second sub-tube, and a third sub-tube connected in sequence;

[0020] The first and third sub-tubes are both arranged parallel to the axis of the thrust chamber, while the second sub-tube is arranged parallel to the radial direction of the thrust chamber.

[0021] One end of the first sub-tube is connected to one end of the first diaphragm valve, and one end of the second sub-tube is connected to the thrust chamber.

[0022] Furthermore, the igniter is equipped with an integrated rectifier grid and rectifier plate, and the igniter uses a high filling coefficient to reduce the filling volume.

[0023] Furthermore, this invention also provides a method for using the aforementioned liquid oxygen-kerosene rocket engine chemical ignition system, characterized by the following steps:

[0024] Step 1: Open the main fuel valve to allow kerosene to enter the main fuel pipeline. Part of the kerosene enters the thrust chamber through the main fuel pipeline, and the other part fills the first diaphragm valve through the inlet conduit.

[0025] Step 2: Connect the control gas source. The control gas output from the control gas source cuts through the diaphragm of the first diaphragm valve and the second diaphragm valve, allowing kerosene to enter the cylinder through the first diaphragm valve.

[0026] Step 3: The igniter sealed in the cylinder is squeezed by kerosene, so that the igniter is delivered to the thrust chamber through the outlet pipe, and the igniter is delivered to the thrust chamber before the kerosene in the fuel main pipe in Step 1.

[0027] Step 4: Liquid oxygen is delivered into the thrust chamber, where it comes into contact with the ignition agent that has entered the thrust chamber and spontaneously combusts. The flame formed by the ignition agent ignites the kerosene that is subsequently delivered into the thrust chamber, and the thrust chamber is ignited.

[0028] Step 5: After the ignition agent is exhausted by compression, cut off the control gas source, and keep the first diaphragm valve and the second diaphragm valve at both ends of the cylinder open.

[0029] Step 6: After the engine has finished running, close the main fuel valve to cut off the kerosene supply to the ignition circuit.

[0030] The beneficial effects of this invention are:

[0031] 1. When shutting down, this invention can cut off the kerosene supply to the ignition circuit by closing the main fuel valve, eliminating the need for a high-pressure differential check valve or ignition agent control valve in the ignition circuit. By rationally setting the inlet and outlet conduits, dead space and low flow rate zones are eliminated. During operation, the ignition agent is completely squeezed out by the kerosene. After the test run, there is no need to release the ignition agent, and the ignition agent purge valve and related pipelines can be omitted. The system is simple, easy to use and maintain, and has high reliability.

[0032] 2. The first diaphragm valve and the second diaphragm valve of the present invention are both opened by independent control gas sources and are not coupled with the working relationship of other components, thus having a wide range of applications. If the diaphragm of the first diaphragm valve and the second diaphragm valve are cut by room temperature gas, the housing of the first diaphragm valve and the second diaphragm valve can be reused. Attached Figure Description

[0033] Figure 1 This is a schematic diagram of an embodiment of a liquid oxygen kerosene rocket engine chemical ignition system according to the present invention;

[0034] In the diagram: 1-Igniter, 11-Cylinder body, 12-First diaphragm valve, 13-Second diaphragm valve, 2-Inlet conduit, 3-Outlet conduit, 31-First sub-pipe, 32-Second sub-pipe, 33-Third sub-pipe; 4-Control gas pipeline, 41-First straight pipe, 42-Bend pipe, 43-Second straight pipe; 5-Thrust chamber, 6-Main fuel valve, 7-Clamp, 8-Main fuel pipeline. Detailed Implementation

[0035] To make the objectives, advantages, and features of the present invention clearer, the following detailed description, in conjunction with the accompanying drawings and specific embodiments, provides a further detailed explanation of the liquid oxygen-kerosene rocket engine chemical ignition system and its usage method proposed in this invention. The advantages and features of the present invention will become clearer according to the following specific embodiments. It should be noted that the accompanying drawings are all in a very simplified form and use non-precise proportions, used only to facilitate and clarify the explanation of the embodiments of the present invention; furthermore, the structures shown in the drawings are often part of the actual structures.

[0036] See Figure 1 This embodiment of a liquid oxygen kerosene rocket engine chemical ignition system mainly includes an igniter 1, an inlet conduit 2, and an outlet conduit 3.

[0037] In this embodiment, the igniter 1 mainly includes a cylindrical body 11 with openings at both ends, a first diaphragm valve 12 and a second diaphragm valve 13 respectively disposed at both ends of the cylindrical body 11, and a control gas pipeline 4 whose output end is connected to the control ends of the first diaphragm valve 12 and the second diaphragm valve 13 respectively.

[0038] The cylinder body 11 is made of stainless steel and incorporates an integrated flow rectifier grid and flow plate, manufactured using 3D printing. The cylinder body 11 is fixedly mounted to the outer circumferential surface of the engine's thrust chamber 5 near the liquid oxygen inlet using clamps 7. The axial direction of the cylinder body 11 is parallel to the axial direction of the thrust chamber 5, shortening the length of the inlet conduit 2 and outlet conduit 3. Furthermore, the axis of the cylinder body 11 coincides with the axes of the first diaphragm valve 12 and the second diaphragm valve 13, resulting in low flow resistance and no dead space, thus achieving the goals of small filling volume, low flow resistance, and rapid filling. An igniter is sealed inside the cylinder body 11. The igniter uses a high filling coefficient, reducing the filling volume, allowing the igniter to arrive at the thrust chamber 5 before the liquid oxygen, preventing the presence of kerosene in the thrust chamber 5 before ignition.

[0039] The inlet conduit 2 is a straight pipe, and its axis is set parallel to the axis of the thrust chamber 5. One end of the inlet conduit 2 is connected to one end of the second diaphragm valve 13, and the other end is connected to the fuel main pipeline 8 of the engine near the fuel main valve 6. The inlet conduit 2 is a large-diameter conduit.

[0040] One end of the outlet conduit 3 is connected to one end of the first diaphragm valve 12, and the other end is connected to the thrust chamber 5 of the engine. The outlet conduit 3 adopts a gate-shaped orientation, is short in length, has low flow resistance, and is easy to disassemble and replace.

[0041] Specifically, the outlet conduit 3 includes a first sub-tube 31, a second sub-tube 32, and a third sub-tube 33 connected in sequence; the axial directions of the first sub-tube 31 and the third sub-tube 33 are both parallel to the axial direction of the thrust chamber 5, and the axial direction of the second sub-tube 32 is parallel to the radial direction of the thrust chamber 5; one end of the first sub-tube 31 is connected to one end of the first diaphragm valve 12, and one end of the second sub-tube 32 is connected to the thrust chamber 5.

[0042] The input end of the control gas pipeline 4 is connected to an external control gas source. The control gas output from the control gas source is used to open the first diaphragm valve 12 and the second diaphragm valve 13 during ignition. This allows the kerosene output from the fuel main valve 6 to transport the igniter to the thrust chamber 5, where it comes into contact with the liquid oxygen transported to the thrust chamber 5 and spontaneously combusts, thus achieving ignition.

[0043] Specifically, the control air duct adopts an arc-shaped orientation, providing strong compensation capability. The inlet end of the duct is located at the first diaphragm valve 12, ensuring that the first diaphragm valve 12 is cut off first, followed by the second diaphragm valve 13, thus preventing backflow at the moment the diaphragm valves are cut off. Specifically, it includes a first straight pipe 41, a bent pipe 42, and a second straight pipe 43. The axial directions of both the first straight pipe 41 and the second straight pipe 43 are parallel to the radial direction of the thrust chamber 5. One end of the first straight pipe 41 serves as the inlet end of the control air duct 4, connected to an external control air source, while the other end serves as the first outlet end of the control air duct 4, connected to the control end of the first diaphragm valve 12. One end of the bent pipe 42 is connected to the circumference of the first straight pipe 41, and the other end is connected to one end of the second straight pipe 43. The other end of the second straight pipe 43 serves as the second outlet end of the control air duct 4, connected to the control end of the second diaphragm valve 13.

[0044] The method of using the above-mentioned liquid oxygen kerosene rocket engine chemical ignition system specifically includes the following steps:

[0045] 【1】Press Figure 1 After completing the component connection, the igniter 1 is filled with igniter. Open the main fuel valve 6 to allow kerosene to enter. Part of it enters the thrust chamber 5 through the main fuel pipeline 8, and the other part fills the first diaphragm valve 12 of the igniter 1 through the inlet conduit 2.

[0046] [2] Connect the control gas source and cut the diaphragm of the first diaphragm valve 12 and the second diaphragm valve 13 through the control gas source to form a passage in the ignition circuit.

[0047] [3] The ignition agent sealed in the kerosene extrusion cylinder 11 flows, and the ignition agent filling outlet pipe 3 enters the thrust chamber 5. Through reasonable layout and optimized design, the kerosene in the fuel main pipe 8 in the ignition agent leading step [1] reaches the thrust chamber 5, preventing kerosene from accumulating in the thrust chamber 5 during ignition.

[0048] [4] When liquid oxygen flows out from the liquid oxygen inlet, it comes into contact with the ignition agent that first enters the inner cavity of the thrust chamber 5 and spontaneously combusts. The flame formed by the ignition agent ignites the kerosene that is subsequently delivered to the thrust chamber 5, and the thrust chamber 5 completes the ignition.

[0049] [5] After the igniter is exhausted by compression, the control gas source is cut off. The first diaphragm valve 12 and the second diaphragm valve 13 at both ends of the cylinder 11 remain open. During the engine operation, the inlet pipe, cylinder 11, and outlet pipe become the flow channels for kerosene.

[0050] [6] After the engine has finished working, close the main fuel valve 6 to cut off the kerosene supply to the ignition circuit.

[0051] [7] If you need to prepare for another test run, there is no need to drain the ignition agent; simply replace igniter 1.

Claims

1. A chemical ignition system for a liquid oxygen-kerosene rocket engine, characterized in that: It includes an igniter (1), an inlet conduit (2), and an outlet conduit (3); The igniter (1) includes a cylindrical body (11) with openings at both ends, a first diaphragm valve (12) and a second diaphragm valve (13) respectively disposed at both ends of the cylindrical body (11), and a control gas pipeline (4) whose output end is connected to the control end of the first diaphragm valve (12) and the second diaphragm valve (13) respectively. The cylinder body (11) is fixedly installed on the thrust chamber (5) of the engine, and an ignition agent is sealed inside it; One end of the inlet conduit (2) is connected to one end of the second diaphragm valve (13), and the other end is connected to the main fuel pipeline (8) of the engine and close to one end of the main fuel valve (6); one end of the outlet conduit (3) is connected to one end of the first diaphragm valve (12), and the other end is connected to the thrust chamber (5) of the engine; The input end of the control gas pipeline (4) is connected to an external control gas source. The control gas output from the control gas source is used to open the first diaphragm valve (12) and the second diaphragm valve (13) during ignition. The kerosene output from the fuel main valve (6) is used to push the igniter into the thrust chamber (5) and ignite it by contacting the liquid oxygen delivered to the thrust chamber (5).

2. The chemical ignition system for a liquid oxygen / kerosene rocket engine according to claim 1, characterized in that: The control air duct includes a first straight tube (41), a bend tube (42), and a second straight tube (43); One end of the first straight pipe (41) serves as the input end of the control air pipeline (4), which is connected to an external control air source, and the other end serves as the first output end of the control air pipeline (4), which is connected to the control end of the first diaphragm valve (12). One end of the bent pipe (42) is connected to the periphery of the first straight pipe (41), and the other end is connected to one end of the second straight pipe (43), and is connected to the first straight pipe (41) and the second straight pipe (43) respectively; The other end of the second straight pipe (43) serves as the second output end of the control air pipeline (4), which is connected to the control end of the second diaphragm valve (13). The axial direction of the first straight pipe (41) and the second straight pipe (43) is parallel to the radial direction of the thrust chamber (5).

3. A chemical ignition system for a liquid oxygen-kerosene rocket engine according to claim 1 or 2, characterized in that: The axial direction of the cylinder (11) is parallel to the axial direction of the thrust chamber (5), and the axis of the cylinder (11) coincides with the axis of the first diaphragm valve (12) and the second diaphragm valve (13).

4. The chemical ignition system for a liquid oxygen-kerosene rocket engine according to claim 3, characterized in that: The inlet conduit (2) is a straight pipe, and its axis is parallel to the axis of the thrust chamber (5); the diameter of the inlet conduit (2) is larger than the diameter of the outlet conduit (3); The outlet conduit (3) includes a first sub-tube (31), a second sub-tube (32), and a third sub-tube (33) connected in sequence; The first sub-tube (31) and the third sub-tube (33) are both arranged parallel to the axis of the thrust chamber (5), and the second sub-tube (32) is arranged parallel to the radial direction of the thrust chamber (5). One end of the first sub-tube (31) is connected to one end of the first diaphragm valve (12), and one end of the second sub-tube (32) is connected to the thrust chamber (5).

5. The chemical ignition system for a liquid oxygen-kerosene rocket engine according to claim 1, characterized in that: The cylinder body (11) is equipped with an integrated rectifier grid and rectifier plate inside.

6. A method of using the chemical ignition system for liquid oxygen kerosene rocket engine as claimed in any one of claims 1 to 5, wherein, Includes the following steps: Step 1: Open the main fuel valve (6) to allow kerosene to enter the main fuel pipeline (8). Part of the kerosene enters the thrust chamber (5) through the main fuel pipeline (8), and the other part fills the first diaphragm valve (12) through the inlet conduit (2). Step 2: Connect the control gas source. The control gas output from the control gas source cuts through the diaphragms of the first diaphragm valve (12) and the second diaphragm valve (13) in sequence, so that kerosene enters the cylinder (11) through the first diaphragm valve (12). Step 3: The igniter sealed in the cylinder body (11) is extruded by kerosene, so that the igniter is delivered to the thrust chamber (5) through the outlet pipe (3); Step 4: Liquid oxygen is delivered to the thrust chamber (5), so that the liquid oxygen comes into contact with the ignition agent entering the thrust chamber (5) and spontaneously combusts. The flame formed by the ignition agent ignites the kerosene delivered to the thrust chamber (5), so that the thrust chamber (5) is ignited. Step 5: After the ignition agent is exhausted by compression, the control gas source is cut off, and the first diaphragm valve (12) and the second diaphragm valve (13) at both ends of the cylinder (11) remain open; Step 6: After the engine has finished working, close the main fuel valve (6) to cut off the kerosene supply to the ignition circuit.

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